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raw | patch | inline | side by side (parent: 905f479)
adding many of my other airframe projects
authorBdale Garbee <bdale@gag.com>
Mon, 22 Mar 2010 03:52:56 +0000 (21:52 -0600)
committerBdale Garbee <bdale@gag.com>
Mon, 22 Mar 2010 03:52:56 +0000 (21:52 -0600)
20 files changed:
rockets/airframes/FreedomFlies/index.mdwn [new file with mode: 0644] patch | blob
rockets/airframes/Goblin10/Polecat_Goblin_10.jpg [new file with mode: 0644] patch | blob
rockets/airframes/Goblin10/Polecat_Goblin_10.rkt [new file with mode: 0644] patch | blob
rockets/airframes/Goblin10/index.html [new file with mode: 0644] patch | blob
rockets/airframes/Horizon/index.mdwn [new file with mode: 0644] patch | blob
rockets/airframes/HorizonRebuild/index.mdwn [new file with mode: 0644] patch | blob
rockets/airframes/Horizon_Rebuild.mdwn [deleted file] patch | blob | history
rockets/airframes/NoNukes/index.mdwn [new file with mode: 0644] patch | blob
rockets/airframes/Thor/index.mdwn [new file with mode: 0644] patch | blob
rockets/airframes/YikStik/YikStik.jpg [new file with mode: 0755] patch | blob
rockets/airframes/YikStik/YikStik.rkt [new file with mode: 0755] patch | blob
rockets/airframes/YikStik/index.html [new file with mode: 0644] patch | blob
rockets/airframes/goblin10.mdwn [deleted file] patch | blob | history
rockets/airframes/goblin10/Polecat_Goblin_10.jpg [deleted file] patch | blob | history
rockets/airframes/goblin10/Polecat_Goblin_10.rkt [deleted file] patch | blob | history
rockets/airframes/goblin10/index.html [deleted file] patch | blob | history
rockets/airframes/yikstik.mdwn [deleted file] patch | blob | history
rockets/airframes/yikstik/YikStik.jpg [deleted file] patch | blob | history
rockets/airframes/yikstik/YikStik.rkt [deleted file] patch | blob | history
rockets/airframes/yikstik/index.html [deleted file] patch | blob | history

diff --git a/rockets/airframes/FreedomFlies/index.mdwn b/rockets/airframes/FreedomFlies/index.mdwn
new file mode 100644 (file)
index 0000000..b1add94
--- /dev/null
+++ b/rockets/airframes/FreedomFlies/index.mdwn
@@ -0,0 +1,28 @@
+# Freedom Flies
+
+This was Bdale's first dual deploy airframe.
+
+## Motivation
+
+After successful L1 and L2 certs, Bdale wanted to try his hand at a full
+custom high power aiframe, and chose the 
+[PerfectFlite](http://www.perfectflite.com/) 
+[MAWD](http://www.perfectflite.com/catalog/MAWD.html) commercial recording
+altimeter to make this a dual deployment system.
+
+## Design Details
+
+* 75mm phenolic air frame
+* 38mm BSD cardboard motor mount
+* [Giant Leap](http://giantleaprocketry.com/) old-style 75mm nose cone
+* 1/16 inch G10 fins in a custom shape, with rounded edges, cut from surplus
+  printed circuit board material.
+* 3/8 inch birch plywood centering rings and bulkheads, CNC milled, the two 
+  that hold the fins are notched for perfect fin alignment.
+
+## Build
+
+## Publicity
+
+## Flights
+
diff --git a/rockets/airframes/Goblin10/Polecat_Goblin_10.jpg b/rockets/airframes/Goblin10/Polecat_Goblin_10.jpg
new file mode 100644 (file)
index 0000000..b5ee82d
Binary files /dev/null and b/rockets/airframes/Goblin10/Polecat_Goblin_10.jpg differ
diff --git a/rockets/airframes/Goblin10/Polecat_Goblin_10.rkt b/rockets/airframes/Goblin10/Polecat_Goblin_10.rkt
new file mode 100644 (file)
index 0000000..9a1aec6
--- /dev/null
+++ b/rockets/airframes/Goblin10/Polecat_Goblin_10.rkt
@@ -0,0 +1,3737 @@
+<RockSimDocument>
+<FileVersion>3</FileVersion>
+<DesignInformation>
+<RocketDesign>
+<Name>Polecat Goblin 10 as built by Bdale for Sucessful L3 Cert</Name>
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+<CasingCG>0.</CasingCG>
+<MountSerialNo>13</MountSerialNo>
+<EjectionDelay>-2.</EjectionDelay>
+<RotateXaboutY>0.</RotateXaboutY>
+<RotateEngineAxisAboutX>0.</RotateEngineAxisAboutX>
+</EngineSet>
+</Stage3Engines>
+</SimulationResults>
+</SimulationResultsList>
+</RockSimDocument>
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+<html><head><meta http-equiv="Content-Type" content="text/html; charset=ISO-8859-1"><title>Goblin 10</title><meta name="generator" content="DocBook XSL Stylesheets V1.73.2"></head><body bgcolor="white" text="black" link="#0000FF" vlink="#840084" alink="#0000FF"><div class="book" lang="en"><div class="titlepage"><div><div><h1 class="title"><a name="id2481338"></a>Goblin 10</h1></div><div><h2 class="subtitle">A NAR L3 Certification Rocket</h2></div><div><div class="author"><h3 class="author"><span class="firstname">Bdale</span> <span class="surname">Garbee</span></h3></div></div><div><p class="copyright">Copyright © 2008 Bdale Garbee</p></div><div><div class="legalnotice"><a name="id2736747"></a><p>
+        This document is released under the terms of the 
+        <a class="ulink" href="http://creativecommons.org/licenses/by-sa/3.0/" target="_top">
+          Creative Commons ShareAlike 3.0
+        </a>
+        license.
+      </p></div></div><div><div class="revhistory"><table border="1" width="100%" summary="Revision history"><tr><th align="left" valign="top" colspan="2"><b>Revision History</b></th></tr><tr><td align="left">Revision 1.0</td><td align="left">15 November 2008</td></tr><tr><td align="left" colspan="2">Successful certification flight at Hudson Ranch</td></tr><tr><td align="left">Revision 0.2</td><td align="left">28 October 2008</td></tr><tr><td align="left" colspan="2">Revising during flight to DC</td></tr><tr><td align="left">Revision 0.1</td><td align="left">23 October 2008</td></tr><tr><td align="left" colspan="2">Initial content, derived from YikStik</td></tr></table></div></div></div><hr></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="chapter"><a href="#id2744045">1. Introduction</a></span></dt><dt><span class="chapter"><a href="#id2749934">2. Design</a></span></dt><dd><dl><dt><span class="section"><a href="#id2759790">Overview</a></span></dt><dt><span class="section"><a href="#id2737277">Rocksim File</a></span></dt><dt><span class="section"><a href="#id2763689">Drawing from Rocksim</a></span></dt><dt><span class="section"><a href="#id2744686">Motor Retention</a></span></dt><dt><span class="section"><a href="#id2754969">Nose Cone Electronics Bay</a></span></dt><dt><span class="section"><a href="#id2733689">Electronics</a></span></dt><dd><dl><dt><span class="section"><a href="#id2763384">Avionics</a></span></dt><dt><span class="section"><a href="#id2740504">Stability Evaluation</a></span></dt><dt><span class="section"><a href="#id2748086">Expected Performance</a></span></dt><dt><span class="section"><a href="#id2767164">Recovery System</a></span></dt></dl></dd></dl></dd><dt><span class="chapter"><a href="#id2768933">3. Construction Details</a></span></dt><dd><dl><dt><span class="section"><a href="#id2749141">Airframe</a></span></dt><dt><span class="section"><a href="#id2754017">Nose Cone</a></span></dt><dt><span class="section"><a href="#id2771414">Avionics Bay</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2745741">4. Recovery Systems Package</a></span></dt><dd><dl><dt><span class="section"><a href="#id2740673">Recovery System Description</a></span></dt><dt><span class="section"><a href="#id2752914">Recovery Initiation Control Components</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2748101">5.  Checklists </a></span></dt><dt><span class="chapter"><a href="#id2750187">6. Flight Summary</a></span></dt><dt><span class="chapter"><a href="#id2764884">7. Analysis and Conclusions</a></span></dt></dl></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2744045"></a>Chapter 1. Introduction</h2></div></div></div><p>
+      This is a rocket I'm building for my second attempt at a NAR Level 3 
+      certification flight.  It's basically a Polecat Aerospace Goblin 10 kit
+      augmented with an additional electronics bay in the nose cone, some
+      structural reinforcement, and incorporating a few personal build 
+      preferences.
+    </p><p>
+      Preliminary analysis suggests that it should reach just under 7k feet
+      on the Aerotech M1297W reload, and could break two miles on the
+      Cesaroni M795W moon-burner.  This means that a certification flight can
+      be supported at Hudson Ranch with the standing 8k waiver, at the Tripoli
+      Colorado site under their higher-altitude window, or at either of the 
+      NCR launch sites under their standing waivers.
+      The smallest reasonable motor for this rocket would be a Cesaroni
+      K445 or equivalent, which would yield an apogee of about 2300 feet.
+    </p></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2749934"></a>Chapter 2. Design</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2759790">Overview</a></span></dt><dt><span class="section"><a href="#id2737277">Rocksim File</a></span></dt><dt><span class="section"><a href="#id2763689">Drawing from Rocksim</a></span></dt><dt><span class="section"><a href="#id2744686">Motor Retention</a></span></dt><dt><span class="section"><a href="#id2754969">Nose Cone Electronics Bay</a></span></dt><dt><span class="section"><a href="#id2733689">Electronics</a></span></dt><dd><dl><dt><span class="section"><a href="#id2763384">Avionics</a></span></dt><dt><span class="section"><a href="#id2740504">Stability Evaluation</a></span></dt><dt><span class="section"><a href="#id2748086">Expected Performance</a></span></dt><dt><span class="section"><a href="#id2767164">Recovery System</a></span></dt></dl></dd></dl></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2759790"></a>Overview</h2></div></div></div><p>
+        The Goblin 10 kit is a simple "four fins and a nose cone" rocket 
+       that is short and squat, with a 98mm motor mount.  
+       It supports dual-deploy by
+        using the forward end of the long motor mount tube to hold the main.
+        The primary electronics bay is between the forward two motor mount
+        centering rings, accessed by a side hatch.  An additional payload bay
+        will be built inside the nose cone to carry experimental altimeters,
+        a tracking beacon, and possibly a GPS position reporting system.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2737277"></a>Rocksim File</h2></div></div></div>
+      This is the current working design in Rocksim format:
+      <a class="ulink" href="Polecat_Goblin_10.rkt" target="_top"> Polecat_Goblin_10.rkt </a></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2763689"></a>Drawing from Rocksim</h2></div></div></div><span class="inlinemediaobject"><img src="Polecat_Goblin_10.jpg" height="450"></span></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2744686"></a>Motor Retention</h2></div></div></div><p>
+        I will include 8-24 T-nuts in the aft centering ring spaced to allow
+        the use of an Aeropack 98mm retainer and associated 75mm adapter.  
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2754969"></a>Nose Cone Electronics Bay</h2></div></div></div><p>
+        Instead of using the supplied nose cone bulkhead, I intend to cut a
+        custom one that would support installing a length of 98mm motor mount
+        from the tip of the nose to the bulkhead.  With a plate cut to cover
+        the aft end of the airframe tube, this would form an electronics bay
+        capable of holding a beacon transmitter, GPS system, or other custom
+        electronics.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2733689"></a>Electronics</h2></div></div></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2763384"></a>Avionics</h3></div></div></div><p>
+          The recovery system will feature dual redundant barometric altimeters
+          in the main avionics bay between the two forward motor mount 
+          centering rings.
+        </p><p>
+          A PerfectFlite MAWD will be flown as the primary altimeter and to 
+          record the flight altitude profile.
+          A MissileWorks Mini-RRC2 will fly as backup altimeter and to 
+          directly capture max velocity.
+        </p><p>
+          Each altimeter will have a separate battery and rotary power switch.
+          A third rotary switch will be used as a SAFE/ARM switch configured 
+          to interrupt connectivity to all ejection charges in accordance with
+          NAR certification requirements.
+        </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2740504"></a>Stability Evaluation</h3></div></div></div><p>
+          The Goblin 10 kit designers indicate
+          that the rocket is unconditionally stable with all motors that fit
+          the motor mount geometry.  Since we're adding mass at both ends, by
+         putting a payload in the nose cone and by glassing the fins, the
+         overall stability of the design should be retained, but simulation
+         to confirm that seems prudent.
+        </p><p>
+          Thorough analysis using 
+          <a class="ulink" href="http://www.apogeerockets.com/rocksim.asp" target="_top">
+            RockSim
+          </a>
+          with various motors ranging from the Cesaroni K445 through the 
+          Aerotech M1939W always shows the stability as marginal.
+          This is typical of short fat rockets that don't meet normal length
+          to airframe diameter ratio expectations.  
+         Given this, I take the fact that RockSim shows the stability as 
+         marginal instead of unstable as strong evidence that the rocket 
+         will in fact be stable in flight.
+         I also note that the simulated margin of stability
+         in my as-built configuration is fairly close to the margin of
+         stability of the as-designed model.  
+        </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2748086"></a>Expected Performance</h3></div></div></div><p>
+          The Aerotech M1297W reload should carry this vehicle to just under
+          7000 feet AGL from Colorado Front Range launch sites.  It 
+          should reach just over 2 miles on a Cesaroni M795 moon burner 
+          or equivalent.
+        </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2767164"></a>Recovery System</h3></div></div></div><p>
+          The recovery system will use dual redundant barometric altimeters 
+         firing 4F black powder charges using commercial e-matches. 
+          At apogee, a drogue chute will deploy with separation of the nose 
+         cone.  A Giant Leap TAC-1 36 inch chute already in hand will serve
+         as the drogue.
+         At a preset altitude, a main chute will be deployed from the forward
+          end of the motor mount tube to achieve recovery of the bulk of the 
+          rocket at approximately 20 ft/sec.  
+        </p><p>
+          I intend to sew the main parachute from scratch with my wife's help
+         using a design documented by 
+          <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
+            Team Vatsaas
+          </a>
+          using 1.9oz rip-stop nylon and 550 lb parachute cord.  The anticipated
+          build weight implies that a 10 foot parachute would be appropriately
+          sized.
+        </p><p>
+          The recovery system attachment points will all use 1/4 inch u-bolts 
+          with nuts, washers, and backing plates through bulkheads.
+        </p></div></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2768933"></a>Chapter 3. Construction Details</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2749141">Airframe</a></span></dt><dt><span class="section"><a href="#id2754017">Nose Cone</a></span></dt><dt><span class="section"><a href="#id2771414">Avionics Bay</a></span></dt></dl></div><p>
+        I have collected all of my
+        <a class="ulink" href="http://gallery.gag.com/rockets/goblin10" target="_top">
+        build photos
+        </a>
+        in one place, they may show better than I can explain how various
+        aspects of the Goblin went together.
+      </p><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2749141"></a>Airframe</h2></div></div></div><p>
+        The airframe tubing provided in the Polecat kit is thick cardboard tube
+        with a thin exterior fiberglass wrap.  To increase airframe strength, 
+       and particularly to prevent zippers, additional reinforcement seemed
+       warranted.  
+      </p><p>
+       The inner layer of paper was removed from the front 9" or
+       so of the tube.  The tube was soaked with West Systems epoxy diluted
+       with about 20% by volume with acetone, and then a carbon fiber wrap was
+       applied to the interior front of the tube and held in place during
+       curing by an inflatable child's bounce toy inside a plastic garbage
+       bag.  The result is a substantially strengthened tube, with carbon
+       fiber lining from the leading edge back past the first centering ring.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2754017"></a>Nose Cone</h2></div></div></div><p>
+       The provided nose cone bulkhead was replaced by a custom centering
+       ring cut from 3/8 inch birch plywood.  The ring's outer diameter was
+       adjusted put place the ring approximately an inch forward of the end
+       of the motor mount tube, and the inner diameter was cut to fit Giant
+       Leap 98mm phenolic airframe tubing.  A length of such tubing was cut 
+       to fit inside the nose cone and extend back to flush with the trailing
+       edge of the ring.  The centering ring was drilled and fitted with two
+       u-bolts for recovery system attachment and four 6-32 T-nuts to hold
+       a payload mounting plate in place over the aft end of the 98mm tube.
+      </p><p>
+       The airframe tubing was glued into the tip of the nose cone with West
+       Systems epoxy using both milled glass and microlite filler to thicken
+       the mix.  The centering ring was then epoxied in place using a similar
+       mix around the outer edge to form a heavy fillet and 5-minute epoxy to
+       the piece of airframe tubing.  After the epoxies cured, a rotary tool
+       was used to cut the airframe tubing off flush with the aft surface of
+       the centering ring.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2771414"></a>Avionics Bay</h2></div></div></div><p>
+       The avionics bay walls were installed approximately 90 degrees apart
+       prior to installation of the motor mount assembly in the airframe.
+       The airframe wall was marked for a 3.5 x 6.5" access hatch centered
+       over the bay 90 degrees from the rail button line.  This allows
+       sufficient room to install the switches on one side of the hatch yet
+       still inside the bay, and to place the static vent on the other side
+       of the hatch so that there will be minimal effect from air disturbed
+       by movement over the hatch cover edges.
+      </p><p>
+       Rails were fabricated from 3/8" birch plywood and 6-32 blind nuts to
+       allow for a removable avionics sled, rectangular, with 4 screws to 
+       hold the sled in place.
+       A suitably sized avionics sled should be possible to install and remove
+       through the avionics bay hatch allowing for possible future experiments
+       with alternative avionics.
+      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2745741"></a>Chapter 4. Recovery Systems Package</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2740673">Recovery System Description</a></span></dt><dt><span class="section"><a href="#id2752914">Recovery Initiation Control Components</a></span></dt></dl></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2740673"></a>Recovery System Description</h2></div></div></div><p>
+        This rocket uses dual deployment.  
+      </p><p>
+        The apogee event separates the nose cone from the
+        airframe.  The nose cone is attached to the airframe with a length 
+        of heavy-duty tubular nylon shock cord.  A drogue chute protected 
+       during ejection by a kevlar blanket is attached to the shock cord
+       close to the nose cone end.
+      </p><p>
+       The main is a 10 foot chute sewn from the design documented by 
+        <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
+          Team Vatsaas.
+        </a>
+       It is held in place prior to ejection by a layer of paper taped over
+       the front of the motor mount tube.  At ejection, a piston pushes the
+       chute forward through the paper and ejects it from the rocket.
+        This chute is attached to the airframe through an additional length of
+       heavy-duty tubular nylon shock cord.
+      </p><p>
+       Depending on the results of ground testing, the main chute may be 
+       packed in a Giant Leap kevlar deployment bag attached at the main
+       chute apex, with a smaller drogue chute deployed to pull off the bag
+       and cleanly deploy the main.  The primary motivation for this is to
+       prevent the main chute shrouds from tangling during ejection.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2752914"></a>Recovery Initiation Control Components</h2></div></div></div><p>
+        The main avionics bay between the forward two centering rings is 
+        populated with two commercial altimeters, a PerfectFlite MAWD 
+        and a Missile Works miniRRC2.  
+        Each is powered by a dedicated 9V alkaline battery, and has a 
+        dedicated on/off power switch mounted for access from outside the 
+        rocket.  Additionally, a single safe/arm switch with two poles is used
+        to interrupt the return circuits from the igniters to each altimeter.
+        See the attached schematic of the avionics bay contents for more
+        details.
+      </p><p>
+        Details of ejection charge design goes here.
+      </p><p>
+        The    
+        <a class="ulink" href="http://www.info-central.org/recovery_powder.shtml" target="_top">
+          Info Central Black Powder Sizing
+        </a>
+        page is the most authoritative site I've found on this topic.
+       The formula they suggest is diameter in inches squared times 
+       length in inches times a coefficient in grams of black powder.
+        For the main charge, which will be in the 98mm motor mount tube, a
+       pressure of 15psi is appropriate giving a coefficient of 0.006.
+       For the drogue charge, which will be in the main airframe, a 
+       pressure of 5psi is more appropriate, leading to a coefficient
+       of 0.002.
+      </p><p>
+        The drogue bay is 10 inches ID at the widest point, but contains
+       the protrusion of the main bay and a decreasing radius in the 
+       nose cone.  Thus some fudging on the length is appropriate, and
+       we will use 18 inches.  That works out to 3.6 grams of BP.  This
+       rocket will not fly high enough for there to be a significant
+       effect on BP burn characteristics, so no special compensation 
+       should be required.
+      </p><p>
+        The main bay is 3.9 inches ID and perhaps as much as 24 inches long
+        depending on which motor is selected.  
+       That works out to 2.2 grams of BP.
+      </p><p>
+       Ground testing yielded 3.5 grams for the apogee charge and 1.5 grams 
+       for the main.
+       Backup charges will contain additional BP in accordance
+       with the "blow it off or blow it up" philosophy.
+      </p><p>
+       With a 10 foot Team Vatsaas design parachute and our
+       anticipated build weight, the descent rate under main
+       should be just over 20 feet per second.
+      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2748101"></a>Chapter 5.  Checklists </h2></div></div></div><div class="orderedlist"><ol type="1"><li> 
+        Planning
+        <div class="orderedlist"><ol type="1"><li>
+            Pick a club launch with suitable waiver and facilities to 
+            support flight.
+          </li><li>
+            Confirm L3CC member(s) available to attend selected launch.
+          </li><li>
+            Confirm that required loaner motor hardware will be available at launch.
+          </li><li>
+            Notify launch sponsor (club president) of intended flight.
+          </li><li>
+            Notify interested friends of intended flight.
+          </li><li>
+            Perform final pre-flight simulation with as-built masses, etc.
+          </li><li>
+            Gather consummables and tools required to support flight
+            <div class="orderedlist"><ol type="1"><li>
+                fresh 9V batteries
+              </li><li>
+                black powder 
+              </li><li>
+                e-matches 
+              </li><li>
+                motor retainer and adapter parts
+              </li><li>
+                small nylon wire ties
+              </li><li>
+                cellulose wadding material
+              </li><li>
+                masking tape
+              </li><li>
+                screwdriver for phillips-head avionics bay screws
+              </li><li>
+                small straight-blade screwdriver for power switches
+              </li><li>
+                motor reload kit (or arrangements to procure at launch)
+              </li><li>
+                high temperature grease
+              </li><li>
+                long small diameter dowels for igniter insertion
+              </li></ol></div></li></ol></div></li><li> 
+        Before Leaving Home 
+        <div class="orderedlist"><ol type="1"><li>
+            program altimeters for suitable mach delay and recovery deployment
+            <div class="itemizedlist"><ul type="disc"><li>
+                MAWD
+                <div class="itemizedlist"><ul type="circle"><li>
+                    no mach delay
+                  </li><li>
+                    1300 foot main deploy
+                  </li></ul></div></li><li>
+                
+                miniRRC2
+                <div class="itemizedlist"><ul type="circle"><li>
+                    no mach delay
+                  </li><li>
+                    1000 foot main deploy
+                  </li><li>
+                    2 seconds apogee delay
+                  </li><li>
+                    no main delay
+                  </li><li>
+                    dual deploy
+                  </li><li>
+                    ops mode 16 (default)
+                  </li></ul></div></li></ul></div></li><li>
+            assemble all recovery system components and ensure everything fits
+          </li><li>
+            confirm wiring and operation of altimeter power and safe/arm 
+            switches
+          </li><li>
+            Ground test recovery system to confirm suitable black powder 
+            charge sizing
+          </li></ol></div></li><li>
+        Pre-Flight
+        <div class="orderedlist"><ol type="1"><li>
+            confirm payload batteries in good condition, bay loaded, 
+            power switch works
+          </li><li>
+            confirm reception of signals from transmitter(s)
+          </li><li>
+            install fresh 9V batteries for altimeters on avionics bay sled
+          </li><li>
+            inspect altimeters and associated avionics bay wiring for 
+            visible faults
+          </li><li>
+            close up avionics bay 
+          </li><li>
+            build and install BP charges
+            <div class="orderedlist"><ol type="1"><li>
+                Drogue Primary Charge - 3.5 grams 4F BP
+              </li><li>
+                Drogue Backup Charge - 4.0 grams 4F BP
+              </li><li>
+                Main Primary Charge - 1.5 grams 4F BP
+              </li><li>
+                Main Backup Charge - 2.0 grams 4F BP
+              </li></ol></div></li><li>
+            fold main chute, connect recovery harness to piston and airframe,
+            install in MMT and tape paper over the front end
+          </li><li>
+            fold drogue chute into a kevlar pad, connect recovery harness to 
+            nose cone and airframe, install in airframe
+          </li><li>
+            power up payload using switch on base plate in nose cone, then
+            install nose cone, using masking tape to adjust fit as required
+          </li><li>
+            safely power up altimeters, operate safe/arm switch, 
+            and confirm e-match continuity
+          </li><li>
+            safe and power-down the altimeters
+          </li><li>
+            load motor per manufacturer instructions
+          </li><li>
+            install motor in motor mount
+          </li><li>
+            install motor retention
+          </li><li>
+            prepare igniter using e-matches, 1/8 inch dowel
+          </li><li>
+            confirm all screws in place, avionics off and safe
+          </li><li>
+            fill out a launch card
+          </li><li>
+            notify RSO/LCO of readiness for inspection and launch, obtain 
+            a rail assignment and permission to move rocket to launch pad for 
+            final prep
+          </li><li>
+            coordinate readiness with support team members, photographers, 
+            observers
+          </li></ol></div></li><li>
+        Final Prep
+        <div class="orderedlist"><ol type="1"><li>
+            move rocket to launch area
+          </li><li>
+            clean and lubricate launch rail if necessary
+          </li><li>
+            confirm reception of signals from payload transmitter(s)
+          </li><li>
+            mount rocket on launch rail, rotate to vertical
+          </li><li>
+            power up primary altimeter, confirm expected beep pattern
+          </li><li>
+            power up backup altimeter, confirm expected beep pattern
+          </li><li>
+            arm ejection charges
+          </li><li>
+            confirm altimeters both giving expected beep patterns for 
+            igniter continuity
+          </li><li>
+            install igniter and connect to launch control system
+          </li><li>
+            capture GPS waypoint for rail location
+          </li><li>
+            smile for the cameras, make sure we have enough "foil Murphy!" 
+            shots taken
+          </li><li>
+            retreat to safe area behind LCO
+          </li><li>
+            confirm continued reception of transmitter signal(s) from 
+            payload bay
+          </li><li>
+            confirm photographers and observers are ready and know what to 
+            expect
+          </li><li>
+            make sure binoculars and backpack with water and recovery tools 
+            are at hand
+          </li><li>
+            tell RSO and LCO we're ready to launch
+          </li><li>
+            try to relax and enjoy watching the flight!
+          </li></ol></div></li><li>
+        Recovery
+        <div class="orderedlist"><ol type="1"><li>
+            track rocket to landing site
+          </li><li>
+            capture GPS waypoint of landing site, take lots of photos
+          </li><li>
+            note any damage
+          </li><li>
+            gather up and roughly re-pack recovery system for return to 
+            flight line
+          </li><li>
+            bring the rocket to observers for post-flight inspection
+          </li></ol></div></li></ol></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2750187"></a>Chapter 6. Flight Summary</h2></div></div></div><p>
+       A successful level 3 certification flight occurred on 15 November 2008
+       at the SCORE Hudson Ranch launch facility.  The motor was an Aerotech
+       M1297W provided by Tim Thomas of Giant Leap Motors, the igniter was
+       assembled by James Russell using his special thermite mixture, and 
+       numerious SCORE, COSROCS, and NCR members were present to assist with
+       the launch!  Great weather for November... mostly clear and sunny,
+       light winds, dry ground, temps above freezing.
+      </p><p>
+       The motor came up to pressure very quickly and the rocket leapt off
+       the pad, climbing smoothly under power and then doing about two slow 
+       rolls during the coast phase.  Deployment of the nose cone and drogue
+       occurred as planned when the primary apogee charge fired.  
+       Unfortunately, the main deployed around the time the backup apogee
+       charge fired, so the descent was under main from apogee.  Fortunately,
+       the winds were low enough and the descent rate high enough that the
+       rocket touched down without damage within the waiver area for a
+       successful certification!
+      </p><p>
+       The rocket weighed 25.2 pounds prepared for launch without the motor.
+       The motor weighed about 10.25 pounds, which included about 6 pounds
+       of propellant.  Thus the descent mass under chute was just over 29
+       pounds.
+       The miniRRC2 altimeter reported 5949 feet apogee, 980 feet per second
+       max velocity, and 19 seconds to apogee.  The MAWD reported 5953 feet
+       apogee.
+      </p><div class="itemizedlist"><ul type="disc"><li><a class="ulink" href="http://picasaweb.google.com/jamesr2/StealeyMemorialLaunchSiteHudsonRanch" target="_top">
+       Photos of the launch taken by James Russell
+        </a></li><li><a class="ulink" href="http://cosrocs.org/all%20other%20videos/2008videos/11-15hudson/bdale_L3.mov" target="_top">
+       Video of the launch taken by Jeff Lane
+        </a></li><li><a class="ulink" href="http://www.youtube.com/watch?v=xaJnl89wfWU" target="_top">
+       Video of the launch taken by Jason Unwin
+        </a></li></ul></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2764884"></a>Chapter 7. Analysis and Conclusions</h2></div></div></div><p>
+       The ascent was straighter than expected... very smooth during
+       the motor burn, then a couple slow rolls during coast.  The two 
+       altimeters agreed within 4 feet on the apogee.  The max
+       velocity recorded is a little higher than predicted by simulation,
+       but the accuracy of that measurement is likely limited since it is
+       based on pressure data.
+      </p><p>
+       I was able to watch the apogee events through binoculars, and could
+       clearly see the main deploy as the backup apogee charge fired.  I saw
+       some evidence of tearing of the paper taped over the motor mount to 
+       retain the main chute during ground testing, so assume this was the
+       root cause of the early deployment.  When the backup apogee charge 
+       fired, the shock cord was not yet in tension, and thus the charge 
+       probably kicked the airframe backwards hard enough to allow the main 
+       chute to slide out through the torn paper and deploy.  The best fix 
+       for this might be
+       to fabricate a second piston to use as a cap and retain it with two
+       shear pins.  This would be much less likely to prematurely deploy than
+       the current taped paper approach.
+      </p><p>
+       The most significant variance from expectation was the descent rate.
+       The spreadsheet provided by the Team Vatsaas folks for their design
+       suggested we'd see around 21 feet per second.  Analysis of the flight
+       profile from the MAWD shows that our actual descent rate was about
+       32 feet per second.  There are three possible sources of error to 
+       consider.  
+       </p><div class="orderedlist"><ol type="1"><li> 
+               The first is descent mass.  Pre-flight calculations used
+               25 pounds.  
+               The actual flight weight was 25.2 pounds plus the burn-out
+               weight of the M1297W, which should be about 4.5 pounds. 
+               That yields 29.5 pounds total.  All pre-flight calculations
+               were done using 25 lbs, with the thought that the motor mass
+               might cancel out against the drag provided by the drogue.
+               In flight, it appeared the drogue supported the nose and the
+               main supported the fin can with very little interaction between
+               the two.
+         </li><li> 
+               Second, the dimensions given by Team Vatsaas' spreadsheet
+               for the pattern grid seem small.  For a 10 foot chute, they
+               suggest a grid size of 5 inches, which looks more like an 8.5
+               foot finished chute size to me.
+         </li><li> 
+               Finally, the Cd in the spreadsheet is 1.5, which may be overly
+               optimistic.
+         </li></ol></div><p>
+       My calculations show that if we assume a chute size of 8.5 feet and
+       a Cd closer to 1, we can get to a descent rate of 32 feet per second.
+      </p><p>
+       So, overall, this was a successful flight, but with three things to
+       change before we fly the airframe again... 
+       </p><div class="orderedlist"><ol type="1"><li> 
+               the main chute may be too small
+         </li><li> 
+               switch to a piston to cap the main chute bay
+         </li><li> 
+               beef up the battery retention on the avionics sled
+         </li></ol></div><p>
+      </p></div></div></body></html>
diff --git a/rockets/airframes/Horizon/index.mdwn b/rockets/airframes/Horizon/index.mdwn
new file mode 100644 (file)
index 0000000..3a350e5
--- /dev/null
+++ b/rockets/airframes/Horizon/index.mdwn
@@ -0,0 +1,21 @@
+# BSD Horizon
+
+This was Bdale's first high power airframe.
+
+## Motivation
+
+This is the airframe the earned Bdale his L1 and L2 certifications.
+
+## Design Details
+
+* 98mm BSD cardboard air frame
+* 38mm BSD cardboard motor mount
+* 1/8 inch G10 fins 
+* 1/4 inch birch plywood centering rings and bulkhead
+
+## Build
+
+## Publicity
+
+## Flights
+
diff --git a/rockets/airframes/HorizonRebuild/index.mdwn b/rockets/airframes/HorizonRebuild/index.mdwn
new file mode 100644 (file)
index 0000000..45f7626
--- /dev/null
+++ b/rockets/airframes/HorizonRebuild/index.mdwn
@@ -0,0 +1,30 @@
+# Horizon Rebuild
+
+This is an improved redesign and rebuild of Bdale's first high power airframe.
+
+## Motivation
+
+The airframe that earned Bdale his L1 and L2 certifications was severely
+damaged after the nylon strap portion of the recovery harness failed at
+altitude during a flight at the NCR North launch site.  The nose cone, payload
+bay, and parachute were recovered on the day.  The fin can turned up later
+in the weekend after Bdale had to leave, and was returned a few weeks 
+later.  Only the nose cone, fins, and rail buttons from the original airframe
+survive in this rebuild.
+
+This rebuild is configured with a 54mm motor mount and electronics bay capable
+of dual deployment with redundant electronics.
+
+## Design Details
+
+* 98mm Giant Leap DynaWind air frame
+* 54mm Giant Leap phenolic motor mount
+* 1/8 inch G10 fins, recycled from [Horizon](../Horizon)
+* 3/8 inch birch plywood centering rings and bulkheads
+
+## Build
+
+## Publicity
+
+## Flights
+
diff --git a/rockets/airframes/Horizon_Rebuild.mdwn b/rockets/airframes/Horizon_Rebuild.mdwn
deleted file mode 100644 (file)
index 19a2c60..0000000
--- a/rockets/airframes/Horizon_Rebuild.mdwn
+++ /dev/null
@@ -1,14 +0,0 @@
-## Basic Data ##
-
-### When Built ###
-### Who Built It ###
-### Rocksim Model ###
-### CNC Files ###
-### Photos ###
-
-## Objectives ##
-## Special Techniques ##
-## Observations ##
-## List of Flights ##
-
-[[!tag tags/rockets]]
diff --git a/rockets/airframes/NoNukes/index.mdwn b/rockets/airframes/NoNukes/index.mdwn
new file mode 100644 (file)
index 0000000..bc3b22e
--- /dev/null
+++ b/rockets/airframes/NoNukes/index.mdwn
@@ -0,0 +1,30 @@
+# No Nukes
+
+## Motivation
+
+Bdale's wife Karen bought an air brush and asked for a rocket to paint.  Bdale
+scrounged the parts pile and threw this rocket together very quickly.  This is
+a simple single-deploy rocket for motor based ejection.
+
+## Design Details
+
+* 98mm [Giant Leap](http://giantleaprocketry.com) phenolic air frame
+* 38mm phenolic motor mount
+* 6-32 t-nuts for Kaplow clips
+* MadCow Rocketry [98mm nose cone](http://www.madcowrocketry.com/servlet/Detail?no=74), though we debated using the [Giant Leap](http://giantleaprocketry.com/) Pinnacle 98mm nose cone, which would also be a good choice
+* 1/4 inch birch plywood fins, upscaled from the LOC Lil Nuke
+* 3/8 inch birch plywood centering rings and bulkheads, CNC milled, the two 
+  that hold the fins are notched for perfect fin alignment.
+
+## Build
+
+Construction occurred during September 2009.
+
+## Publicity
+
+## Flights
+
+First flown at NCR's Oktoberfest 2009, on a Cesaroni Pro38 2-grain Imax
+motor.  This was my first use of a Pro38 grain spacer to fly this reload
+in my 3-grain case.  It was a beautiful flight, but the airframe acquired 
+a lengthy zipper at deployment.
diff --git a/rockets/airframes/Thor/index.mdwn b/rockets/airframes/Thor/index.mdwn
new file mode 100644 (file)
index 0000000..625a2af
--- /dev/null
+++ b/rockets/airframes/Thor/index.mdwn
@@ -0,0 +1,20 @@
+# BSD Thor 3"
+
+A kit that caught Bdale's eye.
+
+## Motivation
+
+## Design Details
+
+* 75mm BSD cardboard air frame with full-length coupler
+* 38mm BSD cardboard motor mount
+* 1/4 inch birch plywood fins 
+* 1/4 inch birch plywood centering rings and bulkheads
+
+## Build
+
+## Publicity
+
+## Flights
+
+Not yet flown.
diff --git a/rockets/airframes/YikStik/YikStik.jpg b/rockets/airframes/YikStik/YikStik.jpg
new file mode 100755 (executable)
index 0000000..314a89d
Binary files /dev/null and b/rockets/airframes/YikStik/YikStik.jpg differ
diff --git a/rockets/airframes/YikStik/YikStik.rkt b/rockets/airframes/YikStik/YikStik.rkt
new file mode 100755 (executable)
index 0000000..427ef76
--- /dev/null
+++ b/rockets/airframes/YikStik/YikStik.rkt
@@ -0,0 +1,4432 @@
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+      <Comments>Potential L3 Certification Rocket</Comments>
+      <Designer>Bdale Garbee</Designer>
+      <Revisions>Initial design 2 March 2008 during OSI board meeting in Chicago
+Worked on 6 March 2008 during OSLO staff meeting in Roseville
+Revised 29 March 2008 based on feedback from James Russell
+Revised 22 August 2008 based on build progress to date</Revisions>
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diff --git a/rockets/airframes/YikStik/index.html b/rockets/airframes/YikStik/index.html
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@@ -0,0 +1,835 @@
+<html><head><meta http-equiv="Content-Type" content="text/html; charset=ISO-8859-1"><title>YikStik</title><meta name="generator" content="DocBook XSL Stylesheets V1.73.2"></head><body bgcolor="white" text="black" link="#0000FF" vlink="#840084" alink="#0000FF"><div class="book" lang="en"><div class="titlepage"><div><div><h1 class="title"><a name="id2322390"></a>YikStik</h1></div><div><h2 class="subtitle">A NAR L3 Certification Rocket</h2></div><div><div class="author"><h3 class="author"><span class="firstname">Bdale</span> <span class="surname">Garbee</span></h3></div></div><div><p class="copyright">Copyright © 2008 Bdale Garbee</p></div><div><div class="legalnotice"><a name="id2577753"></a><p>
+        This document is released under the terms of the 
+        <a class="ulink" href="http://creativecommons.org/licenses/by-sa/3.0/" target="_top">
+          Creative Commons ShareAlike 3.0
+        </a>
+        license.
+      </p></div></div><div><div class="revhistory"><table border="1" width="100%" summary="Revision history"><tr><th align="left" valign="top" colspan="2"><b>Revision History</b></th></tr><tr><td align="left">Revision 1.2</td><td align="left">12 January 2009</td></tr><tr><td align="left" colspan="2">
+         Document firmware bug in miniRRC2 and possible impact on flight.
+        </td></tr><tr><td align="left">Revision 1.1</td><td align="left">5 December 2008</td></tr><tr><td align="left" colspan="2">
+         Remove embedded images in favor of references to gallery.gag.com
+        </td></tr><tr><td align="left">Revision 1.0</td><td align="left">28 October 2008</td></tr><tr><td align="left" colspan="2">
+         Recording results of first, and only, flight attempt.
+        </td></tr><tr><td align="left">Revision 0.5</td><td align="left">27 September 2008</td></tr><tr><td align="left" colspan="2">
+          Building checklists
+        </td></tr><tr><td align="left">Revision 0.4</td><td align="left">17 September 2008</td></tr><tr><td align="left" colspan="2">
+          Documenting the build process as it happens
+        </td></tr><tr><td align="left">Revision 0.3</td><td align="left">29 March 2008</td></tr><tr><td align="left" colspan="2">
+          Incorporate ideas from James Russell during initial L3CC review
+        </td></tr><tr><td align="left">Revision 0.2</td><td align="left">27 March 2008</td></tr><tr><td align="left" colspan="2">Cleaned up for initial review</td></tr><tr><td align="left">Revision 0.1</td><td align="left">16 March 2008</td></tr><tr><td align="left" colspan="2">Initial content</td></tr></table></div></div></div><hr></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="chapter"><a href="#id2565537">1. Introduction</a></span></dt><dd><dl><dt><span class="section"><a href="#id2565574">Why "YikStik"?</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2557207">2. Design</a></span></dt><dd><dl><dt><span class="section"><a href="#id2557213">Overview</a></span></dt><dt><span class="section"><a href="#id2557231">Rocksim File</a></span></dt><dt><span class="section"><a href="#id2557244">Drawing from Rocksim</a></span></dt><dt><span class="section"><a href="#id2557261">Airframe Tubing</a></span></dt><dt><span class="section"><a href="#id2557277">Nose Cone</a></span></dt><dt><span class="section"><a href="#id2557288">Fins</a></span></dt><dt><span class="section"><a href="#id2608670">Centering Rings and Bulkheads </a></span></dt><dt><span class="section"><a href="#id2597438">Motor Retention</a></span></dt><dt><span class="section"><a href="#id2599532">Electronics</a></span></dt><dd><dl><dt><span class="section"><a href="#id2612550">Avionics</a></span></dt><dt><span class="section"><a href="#id2589090">Payload</a></span></dt></dl></dd><dt><span class="section"><a href="#id2581651">Stability Evaluation</a></span></dt><dt><span class="section"><a href="#id2581446">Expected Performance</a></span></dt><dt><span class="section"><a href="#id2599074">Recovery System</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2592234">3. Construction Details</a></span></dt><dd><dl><dt><span class="section"><a href="#id2599259">Airframe and Couplers</a></span></dt><dt><span class="section"><a href="#id2596433">Fins</a></span></dt><dt><span class="section"><a href="#id2606804">Centering Rings and Bulkheads</a></span></dt><dt><span class="section"><a href="#id2588775">Assembling the Booster Section</a></span></dt><dt><span class="section"><a href="#id2584973">Avionics Bay</a></span></dt><dt><span class="section"><a href="#id2606384">Payload Bay</a></span></dt><dt><span class="section"><a href="#id2607348">Recovery System</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2600260">4. Recovery Systems Package</a></span></dt><dd><dl><dt><span class="section"><a href="#id2595964">Recovery System Description</a></span></dt><dt><span class="section"><a href="#id2609782">Recovery Initiation Control Components</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2585586">5. Stability Evaluation</a></span></dt><dt><span class="chapter"><a href="#id2606777">6. Expected Performance</a></span></dt><dt><span class="chapter"><a href="#id2611290">7.  Checklists </a></span></dt><dt><span class="chapter"><a href="#id2610811">8. Flight Summary</a></span></dt><dt><span class="chapter"><a href="#id2607490">9. Analysis and Conclusions</a></span></dt></dl></div><p>
+       Please note that I stopped adding photos to this document at some 
+       point.  I have many more photos of the YikStik build, but haven't
+       decided how best to present them yet... update coming someday!
+  </p><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2565537"></a>Chapter 1. Introduction</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2565574">Why "YikStik"?</a></span></dt></dl></div><p>
+      This is the rocket I'm designing for my NAR Level 3 certification flight.
+      The general idea is to build a fairly cheap rocket capable of reliably 
+      flying this year's Aerotech level 3 special, which is an M1297W reload.
+      I'd like to be able to fly the prototype of my own altimeter design, and
+      to be able to fly it often on smaller / cheaper reloads at launch sites
+      with modest waivers like Hudson Ranch.
+    </p><p>
+      I want to experiment with vacuum bagging carbon fiber reinforcements, and
+      intend to use my CNC milling machine to cut all the centering rings, etc.
+      The new Giant Leap "Dynawind" tubing feels like a good choice, and if we
+      stick to the 4 inch version we can use a cheap plastic nosecone to keep
+      the cost down.
+    </p><p>
+      Preliminary analysis suggests that a roughly 8 foot rocket made from 4 inch
+      airframe with a 75mm mount and three fins should fly to something around
+      14k feet on the M1297W, could break three miles on the M1850W, and yet
+      could safely fly on reloads as small as a J for economical fun.  Those
+      altitudes mean the certification flight will need to be at a site with a
+      high-altitude waiver like the NCR north site.
+    </p><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2565574"></a>Why "YikStik"?</h2></div></div></div><p>
+        I've always thought the high-gloss red paint job on one of my son's rockets
+        when out on a launch rod in the sun looks a lot like glistening wet 
+        lipstick.  
+      </p><p>
+        Combine that with the fact that my wife who isn't fond of the stuff 
+        refers to lipstick as "yik stick"...  and the rest should be obvious.
+      </p><p>
+        My planned paint scheme is a bright red nosecone, gold tube, and black fin
+        can, which is the mental image I have of what lipstick applicators look 
+        like, most likely from a stick my mother or one of my grandmothers had 
+        when I was a child. 
+      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2557207"></a>Chapter 2. Design</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2557213">Overview</a></span></dt><dt><span class="section"><a href="#id2557231">Rocksim File</a></span></dt><dt><span class="section"><a href="#id2557244">Drawing from Rocksim</a></span></dt><dt><span class="section"><a href="#id2557261">Airframe Tubing</a></span></dt><dt><span class="section"><a href="#id2557277">Nose Cone</a></span></dt><dt><span class="section"><a href="#id2557288">Fins</a></span></dt><dt><span class="section"><a href="#id2608670">Centering Rings and Bulkheads </a></span></dt><dt><span class="section"><a href="#id2597438">Motor Retention</a></span></dt><dt><span class="section"><a href="#id2599532">Electronics</a></span></dt><dd><dl><dt><span class="section"><a href="#id2612550">Avionics</a></span></dt><dt><span class="section"><a href="#id2589090">Payload</a></span></dt></dl></dd><dt><span class="section"><a href="#id2581651">Stability Evaluation</a></span></dt><dt><span class="section"><a href="#id2581446">Expected Performance</a></span></dt><dt><span class="section"><a href="#id2599074">Recovery System</a></span></dt></dl></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557213"></a>Overview</h2></div></div></div><p>
+        YikStik is a fairly simple "three fins and a nose cone" dual-deploy 
+        rocket using a 75mm motor mount, 4 inch glass-wrapped phenolic airframe 
+        with zipperless fin can, plastic nose cone, plywood fins, 
+        and lots of glass and carbon fiber reinforcing.  
+        The primary electronics bay will be designed to
+        hold two altimeters, and a distinct payload bay may carry an 
+        experimental altimeter, GPS receiver, and downlink transmitter.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557231"></a>Rocksim File</h2></div></div></div>
+      This is the current working design in Rocksim format:
+      <a class="ulink" href="YikStik.rkt" target="_top"> YikStik.rkt </a></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557244"></a>Drawing from Rocksim</h2></div></div></div><span class="inlinemediaobject"><img src="YikStik.jpg"></span></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557261"></a>Airframe Tubing</h2></div></div></div><p>
+        I intend to cut the airframe components from two 48 inch lengths of 
+        98mm Giant Leap Dynawind tubing.  The 30 inch main bay and 18 inch drogue
+        bay will be cut from one length, while the 33 inches of fin can, 2 inches
+        of electronics bay, and 8 inches of payload bay will be cut from the 
+        second.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557277"></a>Nose Cone</h2></div></div></div><p>
+        I intend to use a Giant Leap "Pinnacle" 3.9 inch nose cone.  
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557288"></a>Fins</h2></div></div></div><p>
+        The fins are designed from scratch, and I intend to build them up from
+        two layers of 1/8 inch birch plywood, three layers of carbon fiber, and
+        two layers of 6 oz glass.  The stack will be glass, carbon fiber, 
+        plywood, carbon fiber, plywood, carbon fiber, glass.  The edges of the
+        plywood will be routed to give a modified airfoil shape to the finished
+        fins.  The stack will be laminated using West Systems epoxy products
+        and vacuum bagged.
+        The shape is a compromise between mass, surviving Mach-transition stress,
+        optimal stability margin, and avoiding damage during handling and on 
+        contact with the ground during recovery.
+      </p><p>
+        The fins will be locked in to milled slots in two of the centering rings,
+        and will be epoxied to the motor mount with glass reinforcing tape. 
+        The airframe will be slotted to allow the completed motor mount / fin 
+        assembly to be inserted from the rear, with fillets of epoxy applied 
+        inside and outside the airframe after insertion.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2608670"></a>Centering Rings and Bulkheads </h2></div></div></div><p>
+        All centering rings and bulkheads will be custom machined from 3/8 inch 
+        birch plywood using my 3-axis CNC milling machine.  Some rings will use
+        laminated pairs of 3/4 inch total thickness to enable use of threaded
+        inserts for 1/4-20 rail button screws or deep routing for fin alignment
+        slots.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2597438"></a>Motor Retention</h2></div></div></div><p>
+        I will embed three 8-24 T-nuts in the aft centering ring spaced to allow
+        the use of home-made Kaplow clips to retain 75mm motors.
+        The same holes may be used to attach custom motor mount adapters for
+        smaller diameter motors.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2599532"></a>Electronics</h2></div></div></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2612550"></a>Avionics</h3></div></div></div><p>
+          The recovery system will feature dual redundant barometric altimeters
+          in an electronics bay similar to the LOC design located between the
+          drogue and main parachute bays.
+        </p><p>
+          A PerfectFlite MAWD will be flown as the primary altimeter and to 
+          record the flight altitude profile.
+          A MissileWorks Mini-RRC2 will fly as backup altimeter and to 
+          directly capture max velocity.
+        </p><p>
+          Each altimeter will have a separate battery and power switch. A 4PDT 
+          slide switch will be used as a SAFE/ARM switch configured to interrupt 
+          connectivity to the ejection charges.
+        </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2589090"></a>Payload</h3></div></div></div><p>
+          I hope to fly 
+          <a class="ulink" href="http://altusmetrum.org/" target="_top">
+            my own altimeter design 
+          </a>
+          as a payload in a short payload section just behind the nose cone.  
+          I have acquired the pieces to add a GPS receiver and RF downlink using
+          ham radio frequencies to the payload to track the rocket's position 
+          during flight.  
+          This is not essential to fly,
+          but could make recovery simpler and would just be fun to fly if I can
+          get it all working and suitably ground and/or flight tested in time.
+        </p></div></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2581651"></a>Stability Evaluation</h2></div></div></div><p>
+        This design has been thoroughly analyzed using 
+        <a class="ulink" href="http://www.apogeerockets.com/rocksim.asp" target="_top">
+          RockSim
+        </a>
+        with motors ranging from the
+        Cesaroni J285 through the Aerotech M1850W and appears to be 
+        unconditionally stable across that range.  The lowest margin is around
+        1.2 seen with the M1297W planned for my level 3 certification flight,
+        albeit with many masses still only roughly estimated.  
+      </p><p>
+        These simulations will be refined as the build proceeds and as-built
+        stability verified before flight. 
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2581446"></a>Expected Performance</h2></div></div></div><p>
+        The Aerotech M1297W reload should carry this vehicle without ballast 
+        to just over 14 thousand feet AGL.  It should make over 16 thousand 
+        feet AGL on an M1850W, and should fly stably to roughly 2.5k feet AGL 
+        on a Cesaroni J285.
+      </p><p>
+        Hitting optimal mass on the largest motors may require 
+        ballast, depending on final build weight.
+        My plan is to fly without ballast on the certification flight, 
+        trading some altitude for a slower and softer recovery.  
+        If the cert succeeds, then I might try an optimal mass 
+        flight sometime later on an M1850W or equivalent "bigger M" 
+        reload to join the "three mile club".
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2599074"></a>Recovery System</h2></div></div></div><p>
+        The recovery system will use dual redundant barometric altimeters firing
+        black powder charges. 
+        At apogee, a drogue chute will deploy from just forward of the fin can,
+        with size selected for an approximately 100 ft/sec descent rate.
+        At a preset altitude, a main chute will be deployed to achieve recovery
+        of the bulk of the rocket at under 20 ft/sec.  
+        The main chute will be packed in a deployment bag, configured as a 
+        "freebag" and pulled out of the airframe by a second drogue chute.  This
+        drogue will recover the nosecone and deployment bag separately from the
+        remainder of the rocket which will recover under the main.
+      </p><p>
+        I intend to sew the parachutes from scratch using a design documented by 
+        <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
+          Team Vatsaas
+        </a>
+        using 1.9oz rip-stop nylon and 550 lb parachute cord.  
+        If time runs short, equivalent chutes from SkyAngle, 
+        Rocketman, or Giant Leap could be substituted (at significantly higher 
+        cost).
+      </p><p>
+        The deployment bag will probably be purchased from Giant Leap.  The
+        recovery harness will probably use tubular kevlar, also from Giant Leap.
+      </p><p>
+        The recovery system attachment points will all use 1/4 inch u-bolts with
+        nuts, washers, and backing plates through bulkheads except for the fin
+        can.  The fin can has insufficient room between the motor mount and
+        the airframe inner wall for nuts and washers, so an alternative means of
+        recovery system attachment is required.  The fin can will be equipped 
+        with either a 3/16 inch stainless steel aircraft cable loop, or a loop 
+        of 1/2 inch tubular kevlar, bonded to the motor mount.
+        If available, a screw-eye attached to the forward motor closure may be 
+        used instead of or in addition to this recovery attachment loop.
+      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2592234"></a>Chapter 3. Construction Details</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2599259">Airframe and Couplers</a></span></dt><dt><span class="section"><a href="#id2596433">Fins</a></span></dt><dt><span class="section"><a href="#id2606804">Centering Rings and Bulkheads</a></span></dt><dt><span class="section"><a href="#id2588775">Assembling the Booster Section</a></span></dt><dt><span class="section"><a href="#id2584973">Avionics Bay</a></span></dt><dt><span class="section"><a href="#id2606384">Payload Bay</a></span></dt><dt><span class="section"><a href="#id2607348">Recovery System</a></span></dt></dl></div><p>
+       I have collected all of my
+       <a class="ulink" href="http://gallery.gag.com/rockets/yikstik" target="_top">
+       build photos
+        </a>
+       in one place, they may show better than I can explain how various
+       aspects of YikStik went together.
+      </p><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2599259"></a>Airframe and Couplers</h2></div></div></div><p>
+        The tubing for the airframe, couplers, and motor mount was all cut
+        using a carefully aligned and adjusted power mitre saw, and the ends
+        lightly sanded to remove rough spots.  
+        The main and drogue bays were cut from one 48 inch length of Giant 
+        Leap 98mm Dynawind tubing, the fin can, electronics bay, and payload 
+        bay were cut from the second.  The three couplers for the fin can, 
+        electronics bay, and payload bay were cut from Giant Leap 98mm phenolic
+        coupler stock.  And the motor mount was cut from Giant Leap 75mm
+        phenolic airframe stock.  
+        Note that the motor mount is the longest piece because of 
+        the zipperless design with full-length motor mount.
+      </p><p>
+        The airframe tubing selected includes a wrap of 10oz glass in epoxy
+        over the base phenolic tubing (visible in some photos as a 
+        shine on the outside of the tubing), 
+       but the coupler stock is unreinforced.
+        To ensure the couplers can handle the anticipated loading, I reinforced
+        each with one layer of interior carbon fiber, using the "kitchen 
+        vacuum bagging" technique documented by 
+        <a class="ulink" href="http://www.jcrocket.com/kitchenbagging.shtml" target="_top"> 
+          John Coker.  
+        </a>
+      </p><p>
+        This was my first hands-on experience working with carbon fiber.  The
+        end of the coupler nearest the unit during bagging experienced some
+        crushing of the fibers right at the end.  It doesn't matter for this
+        project because each of the couplers will have at least one end fitted
+        with a bulkhead or centering ring, but in the future I'll be tempted 
+        to cut the coupler stock a bit long before bagging and trim to length
+        after reinforcing to get "perfect" ends.  The technique worked 
+        marvelously otherwise, and the resulting couplers look and should work
+        great!
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2596433"></a>Fins</h2></div></div></div><p>
+        Six pieces of 1/8 inch birch plywood were stacked, edge-aligned on what
+        would be the fin root edge, and clamped.  The outline of the fin design
+        was marked in pencil, and three 1/8 inch holes drilled through the
+        stack inside the fins to allow using 4-40 screws and nuts to hold the
+        blanks together while making the initial cuts, so that they would all be
+        matched in size.  The clamps were removed to avoid interference
+        during cutting.  The fin outline was then cut using a radial arm saw.
+      </p><p>
+        A router table with 1/8 inch
+       roundover bit was then used to round over the outer edge, 3 blanks on
+        one side and three on the other.  This edge might have been left square,
+        but I prefer the look and feel of rounding.  The router table with a 1/2
+        inch diameter straight cutting bit and a fin beveling jig was used
+        to impart a 10-degree bevel on the leading and trailing edge of each fin
+        blank, again 3 on one side and three on the other.  The resulting 6 
+        blanks thus form 3 pairs of fin components with a modified 
+       airfoil shape.
+      </p><p>
+        The fin assembly started with a simple lamination of two layers of ply
+        sandwiching a layer of carbon fiber.  Each fin used "one pump" of West
+        Systems epoxy and the stack was vacuum bagged using the Foodsaver with
+        wide bagging material.  To keep everything flat while the epoxy cured,
+        the stack of fins was sandwiched between two unused extra shelves for 
+        a storage cabinet I had on hand 
+       (particle board covered in laminate, very
+        flat and smooth, nearly inflexible at this loading), and stacked with 
+        about 75 lbs of loose barbell weights.  
+      </p><p>
+        On one of the three fins, the plywood layers are out of alignment by
+        1-2mm in the longest axis.  The other two are nearly perfect.  Light
+        sanding should allow me to match them before laminating the outer layers
+        of carbon fiber and glass.
+      </p><p>
+        After the fins cured, they were bulk sanded with medium and fine 
+        sandpaper and an electric palm sander.  Final sanding of the leading
+        and trailing edges was done using 400 grit paper on a flat surface,
+        holding the fin the way you'd sharpen a knife against a stone.  The
+        results seem good, all three fins match pretty closely.
+      </p><p>
+        A fin holding jig was cut from 1/8" hardboard using my rotary tool 
+        with a fiber cutoff wheel.  The fin slots were made to be a snug fit.
+        A small batch of epoxy was used to apply a bead to the root edge and
+        tab at the leading edge, then the fins were installed against the 
+        motor mount and locked into place with the jig to cure.  The centering
+        ring that locks the aft edge of the fins was dry-fit during this
+        operation to ensure proper alignment, but was not glued yet.  It will
+        go on after the airframe and internal fin filets are installed.
+      </p><p>
+        The fins were reinforced with fiberglass and epoxy.  Masking tape was
+        used to carefully delineate where the airframe ID will be, then 6oz
+        glass 14.25" by 3.5" was epoxied fin-fin across the MMT.  Strips of
+        8.6oz "boat tape" fiberglass were worked into the joints with more
+        epoxy, and a sheet of plastic covered by ziplog bags of water were
+        used to hold things in place during the initial curing.  The three
+        sides were done one at a time and allowed to cure before proceeding.
+        The results look good, and in combination with internal and external
+        airframe filets should yield a super-strong fin can.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2606804"></a>Centering Rings and Bulkheads</h2></div></div></div><p>
+        Pairs of 3/8 inch birch plywood blanks were laminated using Titebond
+        wood glue and clamped while curing to form 3/4 inch blanks for centering
+        rings.  From a strength perspective, 3/8 inch should suffice, but there
+        are two reasons for going with thicker blanks in some places.  The first
+        is that the rail buttons chosen use 1/4-20 mounting screws, and threaded
+        inserts in that size are nearly 3/8 inch outside diameter 
+       (and thus would
+        tear up a ring only 3/8 inch thick on insertion).  The second is that I
+        like to mill slots in the centering rings on each end of the fins to
+        "lock" the fins into position.  Doubling the blanks used to cut those
+        rings will allow me to cut 1/4 inch deep fin slots and still have a half
+        inch of unmolested wood in the rings for strength.
+      </p><p>
+        The aft centering ring and the one just aft of the zipperless
+        coupler section were edge-drilled for the installation of brass
+        1/4-20 threaded inserts to hold rail buttons.  The inserts were
+        locked in place with epoxy, then ground down until nothing protruded
+        beyond the OD of the ring.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2588775"></a>Assembling the Booster Section</h2></div></div></div><p>
+        The forward two centering rings were installed on the MMT using
+        JB Weld high-temperature epoxy, and incorporating an aircraft cable
+        loop for recovery system retention since there just wasn't room for
+        u-bolts.
+      </p><p>
+        The ring at the leading edge of the fins was initially installed 
+        assuming the aft ring would be nearly flush with the rear of the MMT
+        and equipped with Kaplow-clip style retainers, but before the fins
+        were installed a Giant Leap Slimline Tailcone Retainer for 75mm motor
+        in 98mm airframe became available thanks to Tim Thomas, and so this
+        ring was cut out and replaced with another one inch farther forward 
+        to allow installation of the tailcone at the rear of the MMT.  I 
+        really like the tailcone on my Vertical Assault kit, and think it'll
+        work out to be a great addition for this rocket!
+      </p><p>
+        An alignment jig for the fins was carefully marked out and then cut 
+        from 1/8 inch hardboard using my rotary tool and abrasive cutoff wheel.
+        The fins were then epoxied at the root and short leading edge to the
+        motor mount tube and into the slots in the forward centering ring,
+        and held rigidly aligned by the jig until the epoxy set.  The fins
+        were then masked at what would be the ID of the airframe tube, and
+        reinforced with 6oz glass fin-fin across the motor mount tube between
+        each fin pair, further reinforced with strips of 1 inch glass "boat
+        tape" at each fin root joint.
+      </p><p>
+        The airframe tubing section was carefully marked for fin slots, which
+        were then cut using my rotary tool with abrasive cutoff wheel.  Epoxy
+        was applied ahead of the center two rings as the frame was slid into
+        place, and the frame left standing upright until the epoxy set to
+        hopefully form ring-fin fillets on those two rings.  The interior
+        fin to airframe joints were reinforced one fin at a time using West
+        Systems epoxy will milled glass as a filler.  A long 3/8" dowel was
+        used to place and smooth these interior filets.  The aft centering ring
+        was installed by pouring West Systems epoxy in the three fin-fin gaps, 
+        placing the ring, then standing the airframe up to allow the epoxy to
+        flow over the forward surface of the ring and into the gaps between it,
+        the motor mount, and the airframe tubing.  After it set, the booster
+        was placed nose-down, the airframe gaps behind the fins were taped,
+        and more epoxy was applied to seal the aft of the ring to the tubes.
+        Before this epoxy set, JB Weld was used to glue the tail cone retainer
+        in place on the MMT.  
+      </p><p>
+        The exterior fin to
+        airframe joints were filleted using 5-minute epoxy thickened with 
+        baby powder and smoothed with the tip of a plastic spoon, which I 
+        learned about building the Vertical Assault kit.  Gives great results,
+        and allowed all 6 joints to be done in one session.  The space
+        above the top surface of the forward centering ring and between the 
+        motor mount and zipperless-design coupler tubing was filled with epoxy
+        and milled glass.  Minor gaps in the airframe behind each fin were
+        filled with epoxy clay.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2584973"></a>Avionics Bay</h2></div></div></div><p>
+        The avionics bay contains the two commercial altimeters used to
+        record information about the flight and deploy the drogue and main
+        recovery systems.  It is constructed of a piece of Giant Leap 98mm
+        coupler tubing reinforced with an interior wrap of vacuum-bagged
+        carbon fiber, and a 2 inch length of Giant Leap 98mm DynaWind airframe
+        tubing.  
+      </p><p>
+        The bulkheads are custom-milled from 3/8 inch birch plywood
+        milled so that about 3/16" fits inside the coupler and the remainder
+        seals the end of the coupler and just fits inside the airframe.  Each
+        bulkhead has a u-bolt for attaching the recovery harnesses, and dual
+        CPVC end caps as ejection charge holders with screw terminal blocks
+        from Missile Works to attach the igniters.  Two lengths of 1/4 inch
+        all-thread with nuts and washers tie the bulkheads together, with
+        wing-nuts used on one end to allow for easy disassembly.
+      </p><p>
+        A sled was fabricated to hold the altimeters and batteries.  It
+        consists of 1/8 inch birch ply laminated with 6oz fiberglass on each 
+        side, epoxied to cardboard tubes taken from the packaging for Aerotech
+        igniters that slide over the all-thread, further reinforced with nylon
+        ties at each end.  The tubes are staggered one on either side so that
+        the sled goes right up the center of the airframe tubing.
+      </p><p>
+        Two "centering rings" containing three each 6-32 threaded inserts are
+        epoxied inside the bay to provide hard points for attaching the 
+        airframe tubes for the drogue and main recovery bays.  The inside
+        diameter of these rings is notched for the avionics sled, and thus
+        these rings also provide physical support for the sled.
+      </p><p>
+        Three rotary switches from Missile Works are installed through the
+        short airframe tubing section, drilled such that they end up 
+        essentially flush with the outside of the airframe, clamp the coupler
+        tubing, and project inside the bay.  Two are wired as SPST switches
+        for power to the two altimeters, the third is wired as a DPST switch
+        that open-circuits the igniters for the required "safe/arm" function
+        called for in the NAR L3 certification requirements.
+      </p><p>
+        The wiring of the avionics bay is documented in the attached 
+        schematic diagram.  Connectors were used to allow each bulkhead and
+        the switches in the housing to be quickly detached from the sled.
+        The connectors are 9-pin D shells for the switch wiring, and 4-pin
+        Molex connectors like those used on older PC hard drive power cables
+        for the bulkheads.  To allow use of a single switch pole for the 
+        safe/arm function for each altimeter, the two igniters attached to
+        each altimeter are safed by interrupting the common return lines as
+        shown in the schematic.  
+      </p><p>
+        Sizing the static port for the avionics bay was done by applying the
+        formulas suggested by PerfectFlite and Missile Works for their
+        respective altimeter products, then comparing the results with each
+        other and with information found on the web.  I've personally had 
+        better luck with single ports than with multiple holes, perhaps because
+        I've been working with relatively small rockets.  Regardless, I'm 
+        sticking with what I know and will use a single static port hole here.
+      </p><p>
+        The measured dimensions
+        of the avionics bay as constructed are 95mm ID and approximately 250mm
+        between bulkheads.  This works out to 108.73 cubic inches before
+        accounting for the volume of the sled, electronics, and wiring and
+        other components inside the bay.  By the PerfectFlight formula, the 
+        static port should be 0.221 inches in diameter.  By the Missile Works 
+        formula for a bay over 100 cubic inches the answer is 0.261 inches.  
+        The closest standard drill size, which happens to split the difference,
+        is 0.250 inches.  Easy enough!
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2606384"></a>Payload Bay</h2></div></div></div><p>
+        The construction of the payload bay is very similar to the avionics
+        bay, except that there is a hard-epoxied rear bulkhead, and only one
+        screw ring to hard-mount the nose cone.  The forward end of the 
+        payload bay is open to the open interior volume of the nose cone in
+        anticipation of extending downlink antennas above the carbon fiber 
+        reinforcement in the coupler and into the nose cone, since carbon 
+        fiber is opaque to RF.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2607348"></a>Recovery System</h2></div></div></div><p>
+        Pre-sewn 1/4 inch tubular kevlar harness sections were purchased 
+        from Giant Leap, along with a small kevlar deployment bag and two
+        kevlar chute protectors.
+      </p><p>
+        For an apogee drogue, I plan to fly a Public Missiles 4 x 144 inch
+        nylon streamer.  It will be protected with one of the kevlar blankets
+        and attached to one of the kevlar harness sections holding the booster
+        to the avionics bay.
+      </p><p>
+        The main parachute will be sewn from 1.9 oz rip-stop nylon purchased
+        from the 
+        <a class="ulink" href="http://www.milloutletfabric.com/" target="_top">
+          Mill Outlet Fabric Shop
+        </a>
+        in Colorado Springs.  Using the spreadsheet from 
+        <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
+          Team Vatsaas
+        </a>
+        I calculate that we want an 8 foot chute to keep the airframe less
+        nose cone and payload bay below 20 feet per second at touch-down.
+      </p><p>
+        To extract the main chute and recover the nose cone and payload bay,
+        a 3 foot parachute from BSD Rocketry will be packed in a kevlar
+        blanket ahead of the main chute deployment bag, attached by kevlar
+        harness to the nose cone and payload bay assembly, and to the top of
+        the deployment bag.  This assembly will recover separately from the
+        rest of the rocket.
+      </p><p>
+        The altimeters are programmed such that the MAWD fires its drogue
+        charge at apogee and its main charge at 1100 feet.  The miniRRC2
+        is programmed to fire its drogue charge two seconds past apogee, 
+        and its main charge at 900 feet.  Thus the MAWD is primary and the
+        miniRRC2 is the backup.  Since the M1297W has a burn time of about
+        5 seconds, mach inhibit is programmed on both altimeters to 8 seconds.
+      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2600260"></a>Chapter 4. Recovery Systems Package</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2595964">Recovery System Description</a></span></dt><dt><span class="section"><a href="#id2609782">Recovery Initiation Control Components</a></span></dt></dl></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2595964"></a>Recovery System Description</h2></div></div></div><p>
+        This rocket uses dual deployment.  
+      </p><p>
+        The apogee event separates the
+        airframe between the zipperless-design booster section and the 
+        drogue bay.  These two sections are linked by a Giant Leap 20 foot
+        pre-sewn 1/4 inch tubular kevlar assembly, attached to which is a
+        Public Missiles 4 x 144 inch red nylon streamer packed in a Giant Leap
+        kevlar chute protection pad.
+      </p><p>
+        The main event separates the airframe between the forward payload bay
+        and the main bay.  Attached to the nose cone and payload bay assembly
+        is a Giant Leap 15 foot pre-sewn 1/4 inch tubular kevlar assembly, 
+        attached "free bag" style to the top of a Giant Leap deployment bag
+        containing the main chute.  A 36 inch BSD Rocketry nylon parachute
+        packed in a Giant Leap kevlar chute protection pad serves to pull the
+        deployment bag off the main chute, after which it allows for safe
+        recovery of the nose cone and payload assembly at just under 20 feet
+        per second.
+      </p><p>
+        The 8 foot main chute is home-made from 1.9 oz rip-stop nylon using 
+        the design documented by 
+        <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
+          Team Vatsaas.
+        </a>
+        It is attached to the remainder of the rocket using another Giant Leap
+        pre-sewn 1/4 inch tubular kevlar assembly.
+      </p><p>
+        The anchor points are all 5/16 inch u-bolts, except for on the booster
+        which is equipped with an embedded loop of 3/16 inch stainless aircraft
+        cable.  All connections are made with suitable quick-links.
+      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2609782"></a>Recovery Initiation Control Components</h2></div></div></div><p>
+        The LOC-style avionics bay between the main and drogue bays is 
+        populated with two commercial altimeters, a PerfectFlite MAWD 
+        and a Missile Works miniRRC2.  
+        Each is powered by a dedicated 9V battery, and has a 
+        dedicated on/off power switch mounted for access from outside the 
+        rocket.  Additionally, a single safe/arm switch with two poles is used
+        to interrupt the return circuits from the igniters to each altimeter.
+        See the attached schematic of the avionics bay contents for more
+        details.
+      </p><p>
+        The bulkheads at each end of the avionics bay have two CPVC end caps
+        for ejection charge holders, and two-terminal screw blocks for 
+        attachment of electric matches purchase from Giant Leap used to ignite
+        Goex 4F black powder ejection charges.  Each charge holder and terminal
+        block pair is labelled as to main or backup since the charges will be
+        different for each.
+      </p><p>
+        The    
+        <a class="ulink" href="http://www.info-central.org/recovery_powder.shtml" target="_top">
+          Info Central Black Powder Sizing
+        </a>
+        page is the most authoritative site I've found on this topic.
+        Each of the main and drogue bay interfaces will use 2 2-56 nylon screws
+        as shear pins, each of which needs 35 pounds of force or so to shear.
+        Designing for 15psi puts us between 150 and 200 pounds total force in
+        a 4 inch airframe.  The formula is thus 0.006 grams times diameter 
+        squared in inches times length in inches.
+      </p><p>
+        My drogue bay is 3.9 inches ID and 8 inches long, or 95.52 cubic 
+        inches.  That works out to about 0.73 grams.  However, there will be
+        some volume in the motor mount tube above the motor that also must
+        be accounted for, enough to nearly double the total volume when flying
+        on the M1297W certification motor.  Also, since this charge must fire 
+        reliably at 15-18k feet above ground level of around 5k feet, such 
+        that combustion is likely to be incomplete, we need to add some margin.
+      </p><p>
+        My main bay is 3.9 inches ID and about 25 inches between bulkheads,
+        or about 298.50 cubic inches.  That works out to 2.28 grams.  
+      </p><p>
+        Sanity checking, PerfectFlite recommends that a 4F black powder charge 
+        be sized by multiplying the volume of the bay in cubic inches by 0.01 
+        grams.  That yields about 1.8 grams for the drogue bay and 3 grams for
+        the main bay.
+      </p><p>
+        That suggested to me that a good starting point for ground testing is
+        1.5 grams for the drogue bay and 2.5 grams for the main bay.  Ground
+        tests were done using the PC interface cable for the MAWD routed in
+        through the static test port to manually trigger ejections.  Testing
+        of the apogee bay showed that 1.5 grams was sufficient for deployment
+        and 1.8 grams was more authoritative.  A single test of main deploy 
+        with 2.5 grams gave a nearly perfect result.
+        Given the altitude of our expected apogee, we should be generous with
+        the apogee charge, perhaps using 2.0 grams for the primary.  The main 
+        will deploy at an altitude below where the tests were performed, so
+        no adjustment in charge size should be required.
+      </p><p>
+        Descent rate of the nose cone and payload bay which mass just under
+        1kg will be less than 20 feet per second with a 36 inch chute based
+        on manufacturer recommendations and Rocksim v8 simulation.
+        Descent rate of the remainder of the rocket under the 8 foot chute
+        should be about 18 feet per second by the spreadsheet provided by
+        the designers of this chute pattern, sanity checked using the descent
+        rate tables of similar commercial parachute designs, like those from
+        The Rocketman.
+      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2585586"></a>Chapter 5. Stability Evaluation</h2></div></div></div><p>
+      Simulation using Rocksim v8 with a variety of motors showed that the
+      rocket is unconditionally stable with all motors likely to be flown.
+      The worst-case stability among 75mm motors is actually with the 
+      M1297W chosen for the certification flight, at margin 1.05.  This is
+      because the front of this motor falls almost exactly at the CP.  Using 
+      a longer motor like the M1850W raises the initial stability margin to
+      1.10 because the front fuel grain is ahead of the CP, and lesser
+      motors also increase the stability because less mass is behind the CP.
+      The smallest motor I can conceive of flying in this rocket (a Cesaroni
+      J285) would leave us overstable with margin 3.79 on the way to about
+      1800 feet apogee.
+    </p></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2606777"></a>Chapter 6. Expected Performance</h2></div></div></div><p>
+      On the certification flight, using an Aerotech M1297W reload and
+      associated hardware, the anticipated apogee is round 14,700 feet.  This
+      is just under 75% of the NCR North Site standing waiver of 20,000 feet.
+    </p><p>
+      The highest altitude simulated would be achieved with an Aerotech 
+      M1850W reload at nearly 18,000 feet.  The lowest altitude simulated 
+      is with a Cesaroni J285 and Slimline adapters to just over 1800 feet.
+    </p><p>
+      add description of anticipated flight profile here, including launch
+      weight, estimated drag coefficient, velocity leaving the rail, max
+      expected velocity, altitude, and acceleration
+    </p></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2611290"></a>Chapter 7.  Checklists </h2></div></div></div><div class="orderedlist"><ol type="1"><li> 
+        Planning
+        <div class="orderedlist"><ol type="1"><li>
+            Pick a club launch with suitable waiver and facilities to 
+            support flight.
+          </li><li>
+            Confirm L3CC member(s) available to attend selected launch.
+          </li><li>
+            Confirm that required loaner motor hardware will be available at launch.
+          </li><li>
+            Notify launch sponsor (club president) of intended flight.
+          </li><li>
+            Notify interested friends of intended flight.
+          </li><li>
+            Perform final pre-flight simulation with as-built masses, etc.
+          </li><li>
+            Gather consummables and tools required to support flight
+            <div class="orderedlist"><ol type="1"><li>
+                fresh 9V batteries
+              </li><li>
+                black powder 
+              </li><li>
+                e-matches 
+              </li><li>
+                motor retainer snap rings
+              </li><li>
+                small nylon wire ties
+              </li><li>
+                cellulose wadding material
+              </li><li>
+                masking tape
+              </li><li>
+                screwdriver for phillips-head airframe screws
+              </li><li>
+                small straight-blade screwdriver for power switches
+              </li><li>
+                motor reload kit
+              </li><li>
+                high temperature grease
+              </li><li>
+                long small diameter dowels for igniter insertion
+              </li></ol></div></li></ol></div></li><li> 
+        Before Leaving Home 
+        <div class="orderedlist"><ol type="1"><li>
+            program altimeters for suitable mach delay and recovery deployment
+            <div class="itemizedlist"><ul type="disc"><li>
+                MAWD
+                <div class="itemizedlist"><ul type="circle"><li>
+                    8 seconds mach delay
+                  </li><li>
+                    1500 foot main deploy
+                  </li></ul></div></li><li>
+                
+                miniRRC2
+                <div class="itemizedlist"><ul type="circle"><li>
+                    8 seconds mach delay
+                  </li><li>
+                    1000 foot main deploy
+                  </li><li>
+                    2 seconds apogee delay
+                  </li><li>
+                    no main delay
+                  </li><li>
+                    dual deploy
+                  </li><li>
+                    ops mode 16 (default)
+                  </li></ul></div></li></ul></div></li><li>
+            assemble all recovery system components and ensure everything fits
+          </li><li>
+            confirm wiring and operation of altimeter power and safe/arm switches
+          </li><li>
+            Ground test recovery system to confirm suitable black powder 
+            charge sizing
+          </li></ol></div></li><li>
+        Pre-Flight
+        <div class="orderedlist"><ol type="1"><li>
+            confirm payload batteries in good condition, bay loaded, power switch works
+          </li><li>
+            confirm reception of signals from transmitter(s) in payload bay
+          </li><li>
+            install fresh 9V batteries for altimeters on avionics bay sled
+          </li><li>
+            inspect altimeters and associated avionics bay wiring for visible faults
+          </li><li>
+            close up avionics bay 
+          </li><li>
+            install e-matches, confirming resistance of 1-2 ohms and fit in charge cups
+          </li><li>
+            power up altimeters, operate safe/arm switch, and confirm e-match continuity
+          </li><li>
+            load BP charges into charge cups 
+            <div class="orderedlist"><ol type="1"><li>
+                Drogue Primary Charge - 2.0 grams 4F BP
+              </li><li>
+                Drogue Backup Charge - 2.5 grams 4F BP
+              </li><li>
+                Main Primary Charge - 2.5 grams 4F BP
+              </li><li>
+                Main Backup Charge - 3.0 grams 4F BP
+              </li></ol></div></li><li>
+            connect recovery harnesses and install recovery bay airframe sections
+          </li><li>
+            power up altimeters, operate safe/arm switch, and confirm e-match continuity
+          </li><li>
+            safe and power-down the altimeters
+          </li><li>
+            load main recovery bay, attaching nosecone and payload bay assembly
+          </li><li>
+            install nylon 2-56 screws as shear pins between main bay and payload bay
+          </li><li>
+            load drogue recovery bay, feeding harness end through fin can motor tube
+          </li><li>
+            install nylon 2-56 screws as shear pins between drogue bay and fin can
+          </li><li>
+            load motor per manufacturer instructions
+          </li><li>
+            attach forged eye-bolt to forward closure if not already present
+          </li><li>
+            attach drogue harness to eye-bolt on forward motor closure
+          </li><li>
+            install motor in motor mount
+          </li><li>
+            install motor retention snap rings
+          </li><li>
+            prepare igniter for later installation by attaching to long 1/8" dowel
+          </li><li>
+            confirm all screws in place, avionics off and safe
+          </li><li>
+            fill out a launch card
+          </li><li>
+            notify RSO/LCO of readiness for inspection and launch, obtain a rail
+            assignment and permission to move rocket to launch pad for final prep
+          </li><li>
+            coordinate readiness with support team members, photographers, observers
+          </li></ol></div></li><li>
+        Final Prep
+        <div class="orderedlist"><ol type="1"><li>
+            move rocket to launch area
+          </li><li>
+            clean and lubricate launch rail if necessary
+          </li><li>
+            power up payload and confirm reception of signals from transmitter(s)
+          </li><li>
+            mount rocket on launch rail, rotate to vertical
+          </li><li>
+            power up primary altimeter, confirm expected beep pattern
+          </li><li>
+            power up backup altimeter, confirm expected beep pattern
+          </li><li>
+            arm ejection charges
+          </li><li>
+            confirm altimeters both giving expected beep patterns for igniter continuity
+          </li><li>
+            install igniter and connect to launch control system
+          </li><li>
+            capture GPS waypoint for rail location
+          </li><li>
+            smile for the cameras, make sure we have enough "foil Murphy!" shots taken
+          </li><li>
+            retreat to safe area behind LCO
+          </li><li>
+            confirm continued reception of transmitter signal(s) from payload bay
+          </li><li>
+            confirm photographers and observers are ready and know what to expect
+          </li><li>
+            make sure binoculars and backpack with water and recovery tools are at hand
+          </li><li>
+            tell RSO and LCO we're ready to launch
+          </li><li>
+            try to relax and enjoy watching the flight!
+          </li></ol></div></li><li>
+        Recovery
+        <div class="orderedlist"><ol type="1"><li>
+            track rocket to landing site
+          </li><li>
+            capture GPS waypoint of landing site, take lots of photos
+          </li><li>
+            note any damage
+          </li><li>
+            gather up and roughly re-pack recovery system for return to flight line
+          </li><li>
+            bring the rocket to observers for post-flight inspection
+          </li></ol></div></li></ol></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2610811"></a>Chapter 8. Flight Summary</h2></div></div></div><p>
+       YikStik was flown on an M1297W on Saturday morning at NCR's Oktoberfest
+       2008.  The boost was beautiful.  Unfortunately, we lost visual as the
+       rocket climbed into high clouds near apogee.  Radio tracking signals
+       remained strong for several minutes, then disappeared.  We were 
+       confused by viewing what we thought was YikStik descending before
+       signals were lost in about the right direction, but now believe we 
+       were actually watching a previously launched rocket and did not see
+       YikStik descend.  This confusion prevented location of any of the
+       rocket until Sunday evening, after I had left the launch area.
+      </p><p>
+       After an extensive search, the nose cone assembly was finally found
+       with the Walston tracking gear nearly 3.5 miles down range.  The
+       remainder of the rocket has not been found despite extensive searching
+       on the ground and from the air.  
+      </p><p>
+       Reward if returned posters were placed in the area during the week 
+       following the launch but have elicited no useful reponses yet.
+      </p></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2607490"></a>Chapter 9. Analysis and Conclusions</h2></div></div></div><p>
+       Consideration of how the nose cone ended up where it did suggests 
+       we may have had an apogee deployment of the main, perhaps due to 
+       stress on the shear pins before launch, during boost, or during 
+       apogee drogue deployment causing them to break early.
+      </p><p>
+       It is unfortunate that we were confused by seeing another rocket 
+       descending about the expected amount of time after YikStik's launch
+       in approximately the right direction.  This caused us to believe that
+       the rocket was much closer than the nose cone turned out to be, causing
+       us to waste a lot of time searching in an area too close to the launch
+       site. 
+       It also caused us to assume something really weird had happened to the 
+       transmitters, such that the tracking signal was suddenly lost long 
+       after the rocket was on the ground, instead of what seems to really 
+       have happened, which is that the rocket was farther away descending 
+       after a main deployment at apogee, and the loss of signal was simply
+       due to dropping below a ridge line a couple miles from the launch site.
+       I can't help but think that if we'd been 
+       looking in the right area sooner after the launch that we might have
+       found the rocket before someone else apparently picked it up.
+      </p><p>
+       I regret the decision to use a "free bag" configuration of the 
+       deployment bag.  
+       Since both tracking transmitters were in the payload bay behind
+       the nose cone, and we were eventually able to recover that portion 
+       of the rocket, it is possible that if the deployment bag were tethered
+       to the main that we might have recovered the remainder of the rocket.
+      </p><p>
+       If the rocket is recovered and able to fly again, the two changes I
+       would like to make are to tether the deployment bag to the apex of the
+       main, and to move from 2-56 nylon screws to 4-40 nylon screws for the
+       main deployment shear pins, ensuring the holes through the airframe
+       are a loose enough fit to avoid stresses on the pins during boost.  I
+       have no way to know what happened for sure, but believe this might 
+       solve the assumed problem of main deployment at apogee.
+      </p><p>
+       All in all, the design and build process was educational, and a lot
+       of fun!  I'm looking forward to fabricating more custom parts using
+       carbon fiber and vacuum bagging in the future.  
+       The beautiful boost and obvious survival of the rocket airframe
+       through the expected mach transitions confirms my design and 
+       construction skills are adequate to attain an L3 cert.  
+       While I hope to recover the remainder of YikStik someday, I won't 
+       waste any time before trying again with a new airframe!
+      </p><p>
+       [update]  We have learned that one of the altimeters used in this 
+       flight, the Missile Works miniRRC2, was subject to a fault in 
+       firmware that could cause premature ejection of the main
+       in flights above 10k feet.  Thus, it now seems even more likely
+       that we sustained an apogee ejection of the main, but that it
+       may well have been through no fault of the rocket's design,
+       construction, or preparation.  Frustrating!
+      </p></div></div></body></html>
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diff --git a/rockets/airframes/goblin10/index.html b/rockets/airframes/goblin10/index.html
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-<html><head><meta http-equiv="Content-Type" content="text/html; charset=ISO-8859-1"><title>Goblin 10</title><meta name="generator" content="DocBook XSL Stylesheets V1.73.2"></head><body bgcolor="white" text="black" link="#0000FF" vlink="#840084" alink="#0000FF"><div class="book" lang="en"><div class="titlepage"><div><div><h1 class="title"><a name="id2481338"></a>Goblin 10</h1></div><div><h2 class="subtitle">A NAR L3 Certification Rocket</h2></div><div><div class="author"><h3 class="author"><span class="firstname">Bdale</span> <span class="surname">Garbee</span></h3></div></div><div><p class="copyright">Copyright © 2008 Bdale Garbee</p></div><div><div class="legalnotice"><a name="id2736747"></a><p>
-        This document is released under the terms of the 
-        <a class="ulink" href="http://creativecommons.org/licenses/by-sa/3.0/" target="_top">
-          Creative Commons ShareAlike 3.0
-        </a>
-        license.
-      </p></div></div><div><div class="revhistory"><table border="1" width="100%" summary="Revision history"><tr><th align="left" valign="top" colspan="2"><b>Revision History</b></th></tr><tr><td align="left">Revision 1.0</td><td align="left">15 November 2008</td></tr><tr><td align="left" colspan="2">Successful certification flight at Hudson Ranch</td></tr><tr><td align="left">Revision 0.2</td><td align="left">28 October 2008</td></tr><tr><td align="left" colspan="2">Revising during flight to DC</td></tr><tr><td align="left">Revision 0.1</td><td align="left">23 October 2008</td></tr><tr><td align="left" colspan="2">Initial content, derived from YikStik</td></tr></table></div></div></div><hr></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="chapter"><a href="#id2744045">1. Introduction</a></span></dt><dt><span class="chapter"><a href="#id2749934">2. Design</a></span></dt><dd><dl><dt><span class="section"><a href="#id2759790">Overview</a></span></dt><dt><span class="section"><a href="#id2737277">Rocksim File</a></span></dt><dt><span class="section"><a href="#id2763689">Drawing from Rocksim</a></span></dt><dt><span class="section"><a href="#id2744686">Motor Retention</a></span></dt><dt><span class="section"><a href="#id2754969">Nose Cone Electronics Bay</a></span></dt><dt><span class="section"><a href="#id2733689">Electronics</a></span></dt><dd><dl><dt><span class="section"><a href="#id2763384">Avionics</a></span></dt><dt><span class="section"><a href="#id2740504">Stability Evaluation</a></span></dt><dt><span class="section"><a href="#id2748086">Expected Performance</a></span></dt><dt><span class="section"><a href="#id2767164">Recovery System</a></span></dt></dl></dd></dl></dd><dt><span class="chapter"><a href="#id2768933">3. Construction Details</a></span></dt><dd><dl><dt><span class="section"><a href="#id2749141">Airframe</a></span></dt><dt><span class="section"><a href="#id2754017">Nose Cone</a></span></dt><dt><span class="section"><a href="#id2771414">Avionics Bay</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2745741">4. Recovery Systems Package</a></span></dt><dd><dl><dt><span class="section"><a href="#id2740673">Recovery System Description</a></span></dt><dt><span class="section"><a href="#id2752914">Recovery Initiation Control Components</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2748101">5.  Checklists </a></span></dt><dt><span class="chapter"><a href="#id2750187">6. Flight Summary</a></span></dt><dt><span class="chapter"><a href="#id2764884">7. Analysis and Conclusions</a></span></dt></dl></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2744045"></a>Chapter 1. Introduction</h2></div></div></div><p>
-      This is a rocket I'm building for my second attempt at a NAR Level 3 
-      certification flight.  It's basically a Polecat Aerospace Goblin 10 kit
-      augmented with an additional electronics bay in the nose cone, some
-      structural reinforcement, and incorporating a few personal build 
-      preferences.
-    </p><p>
-      Preliminary analysis suggests that it should reach just under 7k feet
-      on the Aerotech M1297W reload, and could break two miles on the
-      Cesaroni M795W moon-burner.  This means that a certification flight can
-      be supported at Hudson Ranch with the standing 8k waiver, at the Tripoli
-      Colorado site under their higher-altitude window, or at either of the 
-      NCR launch sites under their standing waivers.
-      The smallest reasonable motor for this rocket would be a Cesaroni
-      K445 or equivalent, which would yield an apogee of about 2300 feet.
-    </p></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2749934"></a>Chapter 2. Design</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2759790">Overview</a></span></dt><dt><span class="section"><a href="#id2737277">Rocksim File</a></span></dt><dt><span class="section"><a href="#id2763689">Drawing from Rocksim</a></span></dt><dt><span class="section"><a href="#id2744686">Motor Retention</a></span></dt><dt><span class="section"><a href="#id2754969">Nose Cone Electronics Bay</a></span></dt><dt><span class="section"><a href="#id2733689">Electronics</a></span></dt><dd><dl><dt><span class="section"><a href="#id2763384">Avionics</a></span></dt><dt><span class="section"><a href="#id2740504">Stability Evaluation</a></span></dt><dt><span class="section"><a href="#id2748086">Expected Performance</a></span></dt><dt><span class="section"><a href="#id2767164">Recovery System</a></span></dt></dl></dd></dl></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2759790"></a>Overview</h2></div></div></div><p>
-        The Goblin 10 kit is a simple "four fins and a nose cone" rocket 
-       that is short and squat, with a 98mm motor mount.  
-       It supports dual-deploy by
-        using the forward end of the long motor mount tube to hold the main.
-        The primary electronics bay is between the forward two motor mount
-        centering rings, accessed by a side hatch.  An additional payload bay
-        will be built inside the nose cone to carry experimental altimeters,
-        a tracking beacon, and possibly a GPS position reporting system.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2737277"></a>Rocksim File</h2></div></div></div>
-      This is the current working design in Rocksim format:
-      <a class="ulink" href="Polecat_Goblin_10.rkt" target="_top"> Polecat_Goblin_10.rkt </a></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2763689"></a>Drawing from Rocksim</h2></div></div></div><span class="inlinemediaobject"><img src="Polecat_Goblin_10.jpg" height="450"></span></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2744686"></a>Motor Retention</h2></div></div></div><p>
-        I will include 8-24 T-nuts in the aft centering ring spaced to allow
-        the use of an Aeropack 98mm retainer and associated 75mm adapter.  
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2754969"></a>Nose Cone Electronics Bay</h2></div></div></div><p>
-        Instead of using the supplied nose cone bulkhead, I intend to cut a
-        custom one that would support installing a length of 98mm motor mount
-        from the tip of the nose to the bulkhead.  With a plate cut to cover
-        the aft end of the airframe tube, this would form an electronics bay
-        capable of holding a beacon transmitter, GPS system, or other custom
-        electronics.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2733689"></a>Electronics</h2></div></div></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2763384"></a>Avionics</h3></div></div></div><p>
-          The recovery system will feature dual redundant barometric altimeters
-          in the main avionics bay between the two forward motor mount 
-          centering rings.
-        </p><p>
-          A PerfectFlite MAWD will be flown as the primary altimeter and to 
-          record the flight altitude profile.
-          A MissileWorks Mini-RRC2 will fly as backup altimeter and to 
-          directly capture max velocity.
-        </p><p>
-          Each altimeter will have a separate battery and rotary power switch.
-          A third rotary switch will be used as a SAFE/ARM switch configured 
-          to interrupt connectivity to all ejection charges in accordance with
-          NAR certification requirements.
-        </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2740504"></a>Stability Evaluation</h3></div></div></div><p>
-          The Goblin 10 kit designers indicate
-          that the rocket is unconditionally stable with all motors that fit
-          the motor mount geometry.  Since we're adding mass at both ends, by
-         putting a payload in the nose cone and by glassing the fins, the
-         overall stability of the design should be retained, but simulation
-         to confirm that seems prudent.
-        </p><p>
-          Thorough analysis using 
-          <a class="ulink" href="http://www.apogeerockets.com/rocksim.asp" target="_top">
-            RockSim
-          </a>
-          with various motors ranging from the Cesaroni K445 through the 
-          Aerotech M1939W always shows the stability as marginal.
-          This is typical of short fat rockets that don't meet normal length
-          to airframe diameter ratio expectations.  
-         Given this, I take the fact that RockSim shows the stability as 
-         marginal instead of unstable as strong evidence that the rocket 
-         will in fact be stable in flight.
-         I also note that the simulated margin of stability
-         in my as-built configuration is fairly close to the margin of
-         stability of the as-designed model.  
-        </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2748086"></a>Expected Performance</h3></div></div></div><p>
-          The Aerotech M1297W reload should carry this vehicle to just under
-          7000 feet AGL from Colorado Front Range launch sites.  It 
-          should reach just over 2 miles on a Cesaroni M795 moon burner 
-          or equivalent.
-        </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2767164"></a>Recovery System</h3></div></div></div><p>
-          The recovery system will use dual redundant barometric altimeters 
-         firing 4F black powder charges using commercial e-matches. 
-          At apogee, a drogue chute will deploy with separation of the nose 
-         cone.  A Giant Leap TAC-1 36 inch chute already in hand will serve
-         as the drogue.
-         At a preset altitude, a main chute will be deployed from the forward
-          end of the motor mount tube to achieve recovery of the bulk of the 
-          rocket at approximately 20 ft/sec.  
-        </p><p>
-          I intend to sew the main parachute from scratch with my wife's help
-         using a design documented by 
-          <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
-            Team Vatsaas
-          </a>
-          using 1.9oz rip-stop nylon and 550 lb parachute cord.  The anticipated
-          build weight implies that a 10 foot parachute would be appropriately
-          sized.
-        </p><p>
-          The recovery system attachment points will all use 1/4 inch u-bolts 
-          with nuts, washers, and backing plates through bulkheads.
-        </p></div></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2768933"></a>Chapter 3. Construction Details</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2749141">Airframe</a></span></dt><dt><span class="section"><a href="#id2754017">Nose Cone</a></span></dt><dt><span class="section"><a href="#id2771414">Avionics Bay</a></span></dt></dl></div><p>
-        I have collected all of my
-        <a class="ulink" href="http://gallery.gag.com/rockets/goblin10" target="_top">
-        build photos
-        </a>
-        in one place, they may show better than I can explain how various
-        aspects of the Goblin went together.
-      </p><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2749141"></a>Airframe</h2></div></div></div><p>
-        The airframe tubing provided in the Polecat kit is thick cardboard tube
-        with a thin exterior fiberglass wrap.  To increase airframe strength, 
-       and particularly to prevent zippers, additional reinforcement seemed
-       warranted.  
-      </p><p>
-       The inner layer of paper was removed from the front 9" or
-       so of the tube.  The tube was soaked with West Systems epoxy diluted
-       with about 20% by volume with acetone, and then a carbon fiber wrap was
-       applied to the interior front of the tube and held in place during
-       curing by an inflatable child's bounce toy inside a plastic garbage
-       bag.  The result is a substantially strengthened tube, with carbon
-       fiber lining from the leading edge back past the first centering ring.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2754017"></a>Nose Cone</h2></div></div></div><p>
-       The provided nose cone bulkhead was replaced by a custom centering
-       ring cut from 3/8 inch birch plywood.  The ring's outer diameter was
-       adjusted put place the ring approximately an inch forward of the end
-       of the motor mount tube, and the inner diameter was cut to fit Giant
-       Leap 98mm phenolic airframe tubing.  A length of such tubing was cut 
-       to fit inside the nose cone and extend back to flush with the trailing
-       edge of the ring.  The centering ring was drilled and fitted with two
-       u-bolts for recovery system attachment and four 6-32 T-nuts to hold
-       a payload mounting plate in place over the aft end of the 98mm tube.
-      </p><p>
-       The airframe tubing was glued into the tip of the nose cone with West
-       Systems epoxy using both milled glass and microlite filler to thicken
-       the mix.  The centering ring was then epoxied in place using a similar
-       mix around the outer edge to form a heavy fillet and 5-minute epoxy to
-       the piece of airframe tubing.  After the epoxies cured, a rotary tool
-       was used to cut the airframe tubing off flush with the aft surface of
-       the centering ring.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2771414"></a>Avionics Bay</h2></div></div></div><p>
-       The avionics bay walls were installed approximately 90 degrees apart
-       prior to installation of the motor mount assembly in the airframe.
-       The airframe wall was marked for a 3.5 x 6.5" access hatch centered
-       over the bay 90 degrees from the rail button line.  This allows
-       sufficient room to install the switches on one side of the hatch yet
-       still inside the bay, and to place the static vent on the other side
-       of the hatch so that there will be minimal effect from air disturbed
-       by movement over the hatch cover edges.
-      </p><p>
-       Rails were fabricated from 3/8" birch plywood and 6-32 blind nuts to
-       allow for a removable avionics sled, rectangular, with 4 screws to 
-       hold the sled in place.
-       A suitably sized avionics sled should be possible to install and remove
-       through the avionics bay hatch allowing for possible future experiments
-       with alternative avionics.
-      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2745741"></a>Chapter 4. Recovery Systems Package</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2740673">Recovery System Description</a></span></dt><dt><span class="section"><a href="#id2752914">Recovery Initiation Control Components</a></span></dt></dl></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2740673"></a>Recovery System Description</h2></div></div></div><p>
-        This rocket uses dual deployment.  
-      </p><p>
-        The apogee event separates the nose cone from the
-        airframe.  The nose cone is attached to the airframe with a length 
-        of heavy-duty tubular nylon shock cord.  A drogue chute protected 
-       during ejection by a kevlar blanket is attached to the shock cord
-       close to the nose cone end.
-      </p><p>
-       The main is a 10 foot chute sewn from the design documented by 
-        <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
-          Team Vatsaas.
-        </a>
-       It is held in place prior to ejection by a layer of paper taped over
-       the front of the motor mount tube.  At ejection, a piston pushes the
-       chute forward through the paper and ejects it from the rocket.
-        This chute is attached to the airframe through an additional length of
-       heavy-duty tubular nylon shock cord.
-      </p><p>
-       Depending on the results of ground testing, the main chute may be 
-       packed in a Giant Leap kevlar deployment bag attached at the main
-       chute apex, with a smaller drogue chute deployed to pull off the bag
-       and cleanly deploy the main.  The primary motivation for this is to
-       prevent the main chute shrouds from tangling during ejection.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2752914"></a>Recovery Initiation Control Components</h2></div></div></div><p>
-        The main avionics bay between the forward two centering rings is 
-        populated with two commercial altimeters, a PerfectFlite MAWD 
-        and a Missile Works miniRRC2.  
-        Each is powered by a dedicated 9V alkaline battery, and has a 
-        dedicated on/off power switch mounted for access from outside the 
-        rocket.  Additionally, a single safe/arm switch with two poles is used
-        to interrupt the return circuits from the igniters to each altimeter.
-        See the attached schematic of the avionics bay contents for more
-        details.
-      </p><p>
-        Details of ejection charge design goes here.
-      </p><p>
-        The    
-        <a class="ulink" href="http://www.info-central.org/recovery_powder.shtml" target="_top">
-          Info Central Black Powder Sizing
-        </a>
-        page is the most authoritative site I've found on this topic.
-       The formula they suggest is diameter in inches squared times 
-       length in inches times a coefficient in grams of black powder.
-        For the main charge, which will be in the 98mm motor mount tube, a
-       pressure of 15psi is appropriate giving a coefficient of 0.006.
-       For the drogue charge, which will be in the main airframe, a 
-       pressure of 5psi is more appropriate, leading to a coefficient
-       of 0.002.
-      </p><p>
-        The drogue bay is 10 inches ID at the widest point, but contains
-       the protrusion of the main bay and a decreasing radius in the 
-       nose cone.  Thus some fudging on the length is appropriate, and
-       we will use 18 inches.  That works out to 3.6 grams of BP.  This
-       rocket will not fly high enough for there to be a significant
-       effect on BP burn characteristics, so no special compensation 
-       should be required.
-      </p><p>
-        The main bay is 3.9 inches ID and perhaps as much as 24 inches long
-        depending on which motor is selected.  
-       That works out to 2.2 grams of BP.
-      </p><p>
-       Ground testing yielded 3.5 grams for the apogee charge and 1.5 grams 
-       for the main.
-       Backup charges will contain additional BP in accordance
-       with the "blow it off or blow it up" philosophy.
-      </p><p>
-       With a 10 foot Team Vatsaas design parachute and our
-       anticipated build weight, the descent rate under main
-       should be just over 20 feet per second.
-      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2748101"></a>Chapter 5.  Checklists </h2></div></div></div><div class="orderedlist"><ol type="1"><li> 
-        Planning
-        <div class="orderedlist"><ol type="1"><li>
-            Pick a club launch with suitable waiver and facilities to 
-            support flight.
-          </li><li>
-            Confirm L3CC member(s) available to attend selected launch.
-          </li><li>
-            Confirm that required loaner motor hardware will be available at launch.
-          </li><li>
-            Notify launch sponsor (club president) of intended flight.
-          </li><li>
-            Notify interested friends of intended flight.
-          </li><li>
-            Perform final pre-flight simulation with as-built masses, etc.
-          </li><li>
-            Gather consummables and tools required to support flight
-            <div class="orderedlist"><ol type="1"><li>
-                fresh 9V batteries
-              </li><li>
-                black powder 
-              </li><li>
-                e-matches 
-              </li><li>
-                motor retainer and adapter parts
-              </li><li>
-                small nylon wire ties
-              </li><li>
-                cellulose wadding material
-              </li><li>
-                masking tape
-              </li><li>
-                screwdriver for phillips-head avionics bay screws
-              </li><li>
-                small straight-blade screwdriver for power switches
-              </li><li>
-                motor reload kit (or arrangements to procure at launch)
-              </li><li>
-                high temperature grease
-              </li><li>
-                long small diameter dowels for igniter insertion
-              </li></ol></div></li></ol></div></li><li> 
-        Before Leaving Home 
-        <div class="orderedlist"><ol type="1"><li>
-            program altimeters for suitable mach delay and recovery deployment
-            <div class="itemizedlist"><ul type="disc"><li>
-                MAWD
-                <div class="itemizedlist"><ul type="circle"><li>
-                    no mach delay
-                  </li><li>
-                    1300 foot main deploy
-                  </li></ul></div></li><li>
-                
-                miniRRC2
-                <div class="itemizedlist"><ul type="circle"><li>
-                    no mach delay
-                  </li><li>
-                    1000 foot main deploy
-                  </li><li>
-                    2 seconds apogee delay
-                  </li><li>
-                    no main delay
-                  </li><li>
-                    dual deploy
-                  </li><li>
-                    ops mode 16 (default)
-                  </li></ul></div></li></ul></div></li><li>
-            assemble all recovery system components and ensure everything fits
-          </li><li>
-            confirm wiring and operation of altimeter power and safe/arm 
-            switches
-          </li><li>
-            Ground test recovery system to confirm suitable black powder 
-            charge sizing
-          </li></ol></div></li><li>
-        Pre-Flight
-        <div class="orderedlist"><ol type="1"><li>
-            confirm payload batteries in good condition, bay loaded, 
-            power switch works
-          </li><li>
-            confirm reception of signals from transmitter(s)
-          </li><li>
-            install fresh 9V batteries for altimeters on avionics bay sled
-          </li><li>
-            inspect altimeters and associated avionics bay wiring for 
-            visible faults
-          </li><li>
-            close up avionics bay 
-          </li><li>
-            build and install BP charges
-            <div class="orderedlist"><ol type="1"><li>
-                Drogue Primary Charge - 3.5 grams 4F BP
-              </li><li>
-                Drogue Backup Charge - 4.0 grams 4F BP
-              </li><li>
-                Main Primary Charge - 1.5 grams 4F BP
-              </li><li>
-                Main Backup Charge - 2.0 grams 4F BP
-              </li></ol></div></li><li>
-            fold main chute, connect recovery harness to piston and airframe,
-            install in MMT and tape paper over the front end
-          </li><li>
-            fold drogue chute into a kevlar pad, connect recovery harness to 
-            nose cone and airframe, install in airframe
-          </li><li>
-            power up payload using switch on base plate in nose cone, then
-            install nose cone, using masking tape to adjust fit as required
-          </li><li>
-            safely power up altimeters, operate safe/arm switch, 
-            and confirm e-match continuity
-          </li><li>
-            safe and power-down the altimeters
-          </li><li>
-            load motor per manufacturer instructions
-          </li><li>
-            install motor in motor mount
-          </li><li>
-            install motor retention
-          </li><li>
-            prepare igniter using e-matches, 1/8 inch dowel
-          </li><li>
-            confirm all screws in place, avionics off and safe
-          </li><li>
-            fill out a launch card
-          </li><li>
-            notify RSO/LCO of readiness for inspection and launch, obtain 
-            a rail assignment and permission to move rocket to launch pad for 
-            final prep
-          </li><li>
-            coordinate readiness with support team members, photographers, 
-            observers
-          </li></ol></div></li><li>
-        Final Prep
-        <div class="orderedlist"><ol type="1"><li>
-            move rocket to launch area
-          </li><li>
-            clean and lubricate launch rail if necessary
-          </li><li>
-            confirm reception of signals from payload transmitter(s)
-          </li><li>
-            mount rocket on launch rail, rotate to vertical
-          </li><li>
-            power up primary altimeter, confirm expected beep pattern
-          </li><li>
-            power up backup altimeter, confirm expected beep pattern
-          </li><li>
-            arm ejection charges
-          </li><li>
-            confirm altimeters both giving expected beep patterns for 
-            igniter continuity
-          </li><li>
-            install igniter and connect to launch control system
-          </li><li>
-            capture GPS waypoint for rail location
-          </li><li>
-            smile for the cameras, make sure we have enough "foil Murphy!" 
-            shots taken
-          </li><li>
-            retreat to safe area behind LCO
-          </li><li>
-            confirm continued reception of transmitter signal(s) from 
-            payload bay
-          </li><li>
-            confirm photographers and observers are ready and know what to 
-            expect
-          </li><li>
-            make sure binoculars and backpack with water and recovery tools 
-            are at hand
-          </li><li>
-            tell RSO and LCO we're ready to launch
-          </li><li>
-            try to relax and enjoy watching the flight!
-          </li></ol></div></li><li>
-        Recovery
-        <div class="orderedlist"><ol type="1"><li>
-            track rocket to landing site
-          </li><li>
-            capture GPS waypoint of landing site, take lots of photos
-          </li><li>
-            note any damage
-          </li><li>
-            gather up and roughly re-pack recovery system for return to 
-            flight line
-          </li><li>
-            bring the rocket to observers for post-flight inspection
-          </li></ol></div></li></ol></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2750187"></a>Chapter 6. Flight Summary</h2></div></div></div><p>
-       A successful level 3 certification flight occurred on 15 November 2008
-       at the SCORE Hudson Ranch launch facility.  The motor was an Aerotech
-       M1297W provided by Tim Thomas of Giant Leap Motors, the igniter was
-       assembled by James Russell using his special thermite mixture, and 
-       numerious SCORE, COSROCS, and NCR members were present to assist with
-       the launch!  Great weather for November... mostly clear and sunny,
-       light winds, dry ground, temps above freezing.
-      </p><p>
-       The motor came up to pressure very quickly and the rocket leapt off
-       the pad, climbing smoothly under power and then doing about two slow 
-       rolls during the coast phase.  Deployment of the nose cone and drogue
-       occurred as planned when the primary apogee charge fired.  
-       Unfortunately, the main deployed around the time the backup apogee
-       charge fired, so the descent was under main from apogee.  Fortunately,
-       the winds were low enough and the descent rate high enough that the
-       rocket touched down without damage within the waiver area for a
-       successful certification!
-      </p><p>
-       The rocket weighed 25.2 pounds prepared for launch without the motor.
-       The motor weighed about 10.25 pounds, which included about 6 pounds
-       of propellant.  Thus the descent mass under chute was just over 29
-       pounds.
-       The miniRRC2 altimeter reported 5949 feet apogee, 980 feet per second
-       max velocity, and 19 seconds to apogee.  The MAWD reported 5953 feet
-       apogee.
-      </p><div class="itemizedlist"><ul type="disc"><li><a class="ulink" href="http://picasaweb.google.com/jamesr2/StealeyMemorialLaunchSiteHudsonRanch" target="_top">
-       Photos of the launch taken by James Russell
-        </a></li><li><a class="ulink" href="http://cosrocs.org/all%20other%20videos/2008videos/11-15hudson/bdale_L3.mov" target="_top">
-       Video of the launch taken by Jeff Lane
-        </a></li><li><a class="ulink" href="http://www.youtube.com/watch?v=xaJnl89wfWU" target="_top">
-       Video of the launch taken by Jason Unwin
-        </a></li></ul></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2764884"></a>Chapter 7. Analysis and Conclusions</h2></div></div></div><p>
-       The ascent was straighter than expected... very smooth during
-       the motor burn, then a couple slow rolls during coast.  The two 
-       altimeters agreed within 4 feet on the apogee.  The max
-       velocity recorded is a little higher than predicted by simulation,
-       but the accuracy of that measurement is likely limited since it is
-       based on pressure data.
-      </p><p>
-       I was able to watch the apogee events through binoculars, and could
-       clearly see the main deploy as the backup apogee charge fired.  I saw
-       some evidence of tearing of the paper taped over the motor mount to 
-       retain the main chute during ground testing, so assume this was the
-       root cause of the early deployment.  When the backup apogee charge 
-       fired, the shock cord was not yet in tension, and thus the charge 
-       probably kicked the airframe backwards hard enough to allow the main 
-       chute to slide out through the torn paper and deploy.  The best fix 
-       for this might be
-       to fabricate a second piston to use as a cap and retain it with two
-       shear pins.  This would be much less likely to prematurely deploy than
-       the current taped paper approach.
-      </p><p>
-       The most significant variance from expectation was the descent rate.
-       The spreadsheet provided by the Team Vatsaas folks for their design
-       suggested we'd see around 21 feet per second.  Analysis of the flight
-       profile from the MAWD shows that our actual descent rate was about
-       32 feet per second.  There are three possible sources of error to 
-       consider.  
-       </p><div class="orderedlist"><ol type="1"><li> 
-               The first is descent mass.  Pre-flight calculations used
-               25 pounds.  
-               The actual flight weight was 25.2 pounds plus the burn-out
-               weight of the M1297W, which should be about 4.5 pounds. 
-               That yields 29.5 pounds total.  All pre-flight calculations
-               were done using 25 lbs, with the thought that the motor mass
-               might cancel out against the drag provided by the drogue.
-               In flight, it appeared the drogue supported the nose and the
-               main supported the fin can with very little interaction between
-               the two.
-         </li><li> 
-               Second, the dimensions given by Team Vatsaas' spreadsheet
-               for the pattern grid seem small.  For a 10 foot chute, they
-               suggest a grid size of 5 inches, which looks more like an 8.5
-               foot finished chute size to me.
-         </li><li> 
-               Finally, the Cd in the spreadsheet is 1.5, which may be overly
-               optimistic.
-         </li></ol></div><p>
-       My calculations show that if we assume a chute size of 8.5 feet and
-       a Cd closer to 1, we can get to a descent rate of 32 feet per second.
-      </p><p>
-       So, overall, this was a successful flight, but with three things to
-       change before we fly the airframe again... 
-       </p><div class="orderedlist"><ol type="1"><li> 
-               the main chute may be too small
-         </li><li> 
-               switch to a piston to cap the main chute bay
-         </li><li> 
-               beef up the battery retention on the avionics sled
-         </li></ol></div><p>
-      </p></div></div></body></html>
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-      <Stage3Mass>5850.</Stage3Mass>
-      <Stage2Mass>0.</Stage2Mass>
-      <Stage1Mass>0.</Stage1Mass>
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-      <Designer>Bdale Garbee</Designer>
-      <Revisions>Initial design 2 March 2008 during OSI board meeting in Chicago
-Worked on 6 March 2008 during OSLO staff meeting in Roseville
-Revised 29 March 2008 based on feedback from James Russell
-Revised 22 August 2008 based on build progress to date</Revisions>
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diff --git a/rockets/airframes/yikstik/index.html b/rockets/airframes/yikstik/index.html
deleted file mode 100644 (file)
index f1ffbac..0000000
--- a/rockets/airframes/yikstik/index.html
+++ /dev/null
@@ -1,835 +0,0 @@
-<html><head><meta http-equiv="Content-Type" content="text/html; charset=ISO-8859-1"><title>YikStik</title><meta name="generator" content="DocBook XSL Stylesheets V1.73.2"></head><body bgcolor="white" text="black" link="#0000FF" vlink="#840084" alink="#0000FF"><div class="book" lang="en"><div class="titlepage"><div><div><h1 class="title"><a name="id2322390"></a>YikStik</h1></div><div><h2 class="subtitle">A NAR L3 Certification Rocket</h2></div><div><div class="author"><h3 class="author"><span class="firstname">Bdale</span> <span class="surname">Garbee</span></h3></div></div><div><p class="copyright">Copyright © 2008 Bdale Garbee</p></div><div><div class="legalnotice"><a name="id2577753"></a><p>
-        This document is released under the terms of the 
-        <a class="ulink" href="http://creativecommons.org/licenses/by-sa/3.0/" target="_top">
-          Creative Commons ShareAlike 3.0
-        </a>
-        license.
-      </p></div></div><div><div class="revhistory"><table border="1" width="100%" summary="Revision history"><tr><th align="left" valign="top" colspan="2"><b>Revision History</b></th></tr><tr><td align="left">Revision 1.2</td><td align="left">12 January 2009</td></tr><tr><td align="left" colspan="2">
-         Document firmware bug in miniRRC2 and possible impact on flight.
-        </td></tr><tr><td align="left">Revision 1.1</td><td align="left">5 December 2008</td></tr><tr><td align="left" colspan="2">
-         Remove embedded images in favor of references to gallery.gag.com
-        </td></tr><tr><td align="left">Revision 1.0</td><td align="left">28 October 2008</td></tr><tr><td align="left" colspan="2">
-         Recording results of first, and only, flight attempt.
-        </td></tr><tr><td align="left">Revision 0.5</td><td align="left">27 September 2008</td></tr><tr><td align="left" colspan="2">
-          Building checklists
-        </td></tr><tr><td align="left">Revision 0.4</td><td align="left">17 September 2008</td></tr><tr><td align="left" colspan="2">
-          Documenting the build process as it happens
-        </td></tr><tr><td align="left">Revision 0.3</td><td align="left">29 March 2008</td></tr><tr><td align="left" colspan="2">
-          Incorporate ideas from James Russell during initial L3CC review
-        </td></tr><tr><td align="left">Revision 0.2</td><td align="left">27 March 2008</td></tr><tr><td align="left" colspan="2">Cleaned up for initial review</td></tr><tr><td align="left">Revision 0.1</td><td align="left">16 March 2008</td></tr><tr><td align="left" colspan="2">Initial content</td></tr></table></div></div></div><hr></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="chapter"><a href="#id2565537">1. Introduction</a></span></dt><dd><dl><dt><span class="section"><a href="#id2565574">Why "YikStik"?</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2557207">2. Design</a></span></dt><dd><dl><dt><span class="section"><a href="#id2557213">Overview</a></span></dt><dt><span class="section"><a href="#id2557231">Rocksim File</a></span></dt><dt><span class="section"><a href="#id2557244">Drawing from Rocksim</a></span></dt><dt><span class="section"><a href="#id2557261">Airframe Tubing</a></span></dt><dt><span class="section"><a href="#id2557277">Nose Cone</a></span></dt><dt><span class="section"><a href="#id2557288">Fins</a></span></dt><dt><span class="section"><a href="#id2608670">Centering Rings and Bulkheads </a></span></dt><dt><span class="section"><a href="#id2597438">Motor Retention</a></span></dt><dt><span class="section"><a href="#id2599532">Electronics</a></span></dt><dd><dl><dt><span class="section"><a href="#id2612550">Avionics</a></span></dt><dt><span class="section"><a href="#id2589090">Payload</a></span></dt></dl></dd><dt><span class="section"><a href="#id2581651">Stability Evaluation</a></span></dt><dt><span class="section"><a href="#id2581446">Expected Performance</a></span></dt><dt><span class="section"><a href="#id2599074">Recovery System</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2592234">3. Construction Details</a></span></dt><dd><dl><dt><span class="section"><a href="#id2599259">Airframe and Couplers</a></span></dt><dt><span class="section"><a href="#id2596433">Fins</a></span></dt><dt><span class="section"><a href="#id2606804">Centering Rings and Bulkheads</a></span></dt><dt><span class="section"><a href="#id2588775">Assembling the Booster Section</a></span></dt><dt><span class="section"><a href="#id2584973">Avionics Bay</a></span></dt><dt><span class="section"><a href="#id2606384">Payload Bay</a></span></dt><dt><span class="section"><a href="#id2607348">Recovery System</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2600260">4. Recovery Systems Package</a></span></dt><dd><dl><dt><span class="section"><a href="#id2595964">Recovery System Description</a></span></dt><dt><span class="section"><a href="#id2609782">Recovery Initiation Control Components</a></span></dt></dl></dd><dt><span class="chapter"><a href="#id2585586">5. Stability Evaluation</a></span></dt><dt><span class="chapter"><a href="#id2606777">6. Expected Performance</a></span></dt><dt><span class="chapter"><a href="#id2611290">7.  Checklists </a></span></dt><dt><span class="chapter"><a href="#id2610811">8. Flight Summary</a></span></dt><dt><span class="chapter"><a href="#id2607490">9. Analysis and Conclusions</a></span></dt></dl></div><p>
-       Please note that I stopped adding photos to this document at some 
-       point.  I have many more photos of the YikStik build, but haven't
-       decided how best to present them yet... update coming someday!
-  </p><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2565537"></a>Chapter 1. Introduction</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2565574">Why "YikStik"?</a></span></dt></dl></div><p>
-      This is the rocket I'm designing for my NAR Level 3 certification flight.
-      The general idea is to build a fairly cheap rocket capable of reliably 
-      flying this year's Aerotech level 3 special, which is an M1297W reload.
-      I'd like to be able to fly the prototype of my own altimeter design, and
-      to be able to fly it often on smaller / cheaper reloads at launch sites
-      with modest waivers like Hudson Ranch.
-    </p><p>
-      I want to experiment with vacuum bagging carbon fiber reinforcements, and
-      intend to use my CNC milling machine to cut all the centering rings, etc.
-      The new Giant Leap "Dynawind" tubing feels like a good choice, and if we
-      stick to the 4 inch version we can use a cheap plastic nosecone to keep
-      the cost down.
-    </p><p>
-      Preliminary analysis suggests that a roughly 8 foot rocket made from 4 inch
-      airframe with a 75mm mount and three fins should fly to something around
-      14k feet on the M1297W, could break three miles on the M1850W, and yet
-      could safely fly on reloads as small as a J for economical fun.  Those
-      altitudes mean the certification flight will need to be at a site with a
-      high-altitude waiver like the NCR north site.
-    </p><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2565574"></a>Why "YikStik"?</h2></div></div></div><p>
-        I've always thought the high-gloss red paint job on one of my son's rockets
-        when out on a launch rod in the sun looks a lot like glistening wet 
-        lipstick.  
-      </p><p>
-        Combine that with the fact that my wife who isn't fond of the stuff 
-        refers to lipstick as "yik stick"...  and the rest should be obvious.
-      </p><p>
-        My planned paint scheme is a bright red nosecone, gold tube, and black fin
-        can, which is the mental image I have of what lipstick applicators look 
-        like, most likely from a stick my mother or one of my grandmothers had 
-        when I was a child. 
-      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2557207"></a>Chapter 2. Design</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2557213">Overview</a></span></dt><dt><span class="section"><a href="#id2557231">Rocksim File</a></span></dt><dt><span class="section"><a href="#id2557244">Drawing from Rocksim</a></span></dt><dt><span class="section"><a href="#id2557261">Airframe Tubing</a></span></dt><dt><span class="section"><a href="#id2557277">Nose Cone</a></span></dt><dt><span class="section"><a href="#id2557288">Fins</a></span></dt><dt><span class="section"><a href="#id2608670">Centering Rings and Bulkheads </a></span></dt><dt><span class="section"><a href="#id2597438">Motor Retention</a></span></dt><dt><span class="section"><a href="#id2599532">Electronics</a></span></dt><dd><dl><dt><span class="section"><a href="#id2612550">Avionics</a></span></dt><dt><span class="section"><a href="#id2589090">Payload</a></span></dt></dl></dd><dt><span class="section"><a href="#id2581651">Stability Evaluation</a></span></dt><dt><span class="section"><a href="#id2581446">Expected Performance</a></span></dt><dt><span class="section"><a href="#id2599074">Recovery System</a></span></dt></dl></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557213"></a>Overview</h2></div></div></div><p>
-        YikStik is a fairly simple "three fins and a nose cone" dual-deploy 
-        rocket using a 75mm motor mount, 4 inch glass-wrapped phenolic airframe 
-        with zipperless fin can, plastic nose cone, plywood fins, 
-        and lots of glass and carbon fiber reinforcing.  
-        The primary electronics bay will be designed to
-        hold two altimeters, and a distinct payload bay may carry an 
-        experimental altimeter, GPS receiver, and downlink transmitter.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557231"></a>Rocksim File</h2></div></div></div>
-      This is the current working design in Rocksim format:
-      <a class="ulink" href="YikStik.rkt" target="_top"> YikStik.rkt </a></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557244"></a>Drawing from Rocksim</h2></div></div></div><span class="inlinemediaobject"><img src="YikStik.jpg"></span></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557261"></a>Airframe Tubing</h2></div></div></div><p>
-        I intend to cut the airframe components from two 48 inch lengths of 
-        98mm Giant Leap Dynawind tubing.  The 30 inch main bay and 18 inch drogue
-        bay will be cut from one length, while the 33 inches of fin can, 2 inches
-        of electronics bay, and 8 inches of payload bay will be cut from the 
-        second.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557277"></a>Nose Cone</h2></div></div></div><p>
-        I intend to use a Giant Leap "Pinnacle" 3.9 inch nose cone.  
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2557288"></a>Fins</h2></div></div></div><p>
-        The fins are designed from scratch, and I intend to build them up from
-        two layers of 1/8 inch birch plywood, three layers of carbon fiber, and
-        two layers of 6 oz glass.  The stack will be glass, carbon fiber, 
-        plywood, carbon fiber, plywood, carbon fiber, glass.  The edges of the
-        plywood will be routed to give a modified airfoil shape to the finished
-        fins.  The stack will be laminated using West Systems epoxy products
-        and vacuum bagged.
-        The shape is a compromise between mass, surviving Mach-transition stress,
-        optimal stability margin, and avoiding damage during handling and on 
-        contact with the ground during recovery.
-      </p><p>
-        The fins will be locked in to milled slots in two of the centering rings,
-        and will be epoxied to the motor mount with glass reinforcing tape. 
-        The airframe will be slotted to allow the completed motor mount / fin 
-        assembly to be inserted from the rear, with fillets of epoxy applied 
-        inside and outside the airframe after insertion.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2608670"></a>Centering Rings and Bulkheads </h2></div></div></div><p>
-        All centering rings and bulkheads will be custom machined from 3/8 inch 
-        birch plywood using my 3-axis CNC milling machine.  Some rings will use
-        laminated pairs of 3/4 inch total thickness to enable use of threaded
-        inserts for 1/4-20 rail button screws or deep routing for fin alignment
-        slots.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2597438"></a>Motor Retention</h2></div></div></div><p>
-        I will embed three 8-24 T-nuts in the aft centering ring spaced to allow
-        the use of home-made Kaplow clips to retain 75mm motors.
-        The same holes may be used to attach custom motor mount adapters for
-        smaller diameter motors.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2599532"></a>Electronics</h2></div></div></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2612550"></a>Avionics</h3></div></div></div><p>
-          The recovery system will feature dual redundant barometric altimeters
-          in an electronics bay similar to the LOC design located between the
-          drogue and main parachute bays.
-        </p><p>
-          A PerfectFlite MAWD will be flown as the primary altimeter and to 
-          record the flight altitude profile.
-          A MissileWorks Mini-RRC2 will fly as backup altimeter and to 
-          directly capture max velocity.
-        </p><p>
-          Each altimeter will have a separate battery and power switch. A 4PDT 
-          slide switch will be used as a SAFE/ARM switch configured to interrupt 
-          connectivity to the ejection charges.
-        </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h3 class="title"><a name="id2589090"></a>Payload</h3></div></div></div><p>
-          I hope to fly 
-          <a class="ulink" href="http://altusmetrum.org/" target="_top">
-            my own altimeter design 
-          </a>
-          as a payload in a short payload section just behind the nose cone.  
-          I have acquired the pieces to add a GPS receiver and RF downlink using
-          ham radio frequencies to the payload to track the rocket's position 
-          during flight.  
-          This is not essential to fly,
-          but could make recovery simpler and would just be fun to fly if I can
-          get it all working and suitably ground and/or flight tested in time.
-        </p></div></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2581651"></a>Stability Evaluation</h2></div></div></div><p>
-        This design has been thoroughly analyzed using 
-        <a class="ulink" href="http://www.apogeerockets.com/rocksim.asp" target="_top">
-          RockSim
-        </a>
-        with motors ranging from the
-        Cesaroni J285 through the Aerotech M1850W and appears to be 
-        unconditionally stable across that range.  The lowest margin is around
-        1.2 seen with the M1297W planned for my level 3 certification flight,
-        albeit with many masses still only roughly estimated.  
-      </p><p>
-        These simulations will be refined as the build proceeds and as-built
-        stability verified before flight. 
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2581446"></a>Expected Performance</h2></div></div></div><p>
-        The Aerotech M1297W reload should carry this vehicle without ballast 
-        to just over 14 thousand feet AGL.  It should make over 16 thousand 
-        feet AGL on an M1850W, and should fly stably to roughly 2.5k feet AGL 
-        on a Cesaroni J285.
-      </p><p>
-        Hitting optimal mass on the largest motors may require 
-        ballast, depending on final build weight.
-        My plan is to fly without ballast on the certification flight, 
-        trading some altitude for a slower and softer recovery.  
-        If the cert succeeds, then I might try an optimal mass 
-        flight sometime later on an M1850W or equivalent "bigger M" 
-        reload to join the "three mile club".
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2599074"></a>Recovery System</h2></div></div></div><p>
-        The recovery system will use dual redundant barometric altimeters firing
-        black powder charges. 
-        At apogee, a drogue chute will deploy from just forward of the fin can,
-        with size selected for an approximately 100 ft/sec descent rate.
-        At a preset altitude, a main chute will be deployed to achieve recovery
-        of the bulk of the rocket at under 20 ft/sec.  
-        The main chute will be packed in a deployment bag, configured as a 
-        "freebag" and pulled out of the airframe by a second drogue chute.  This
-        drogue will recover the nosecone and deployment bag separately from the
-        remainder of the rocket which will recover under the main.
-      </p><p>
-        I intend to sew the parachutes from scratch using a design documented by 
-        <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
-          Team Vatsaas
-        </a>
-        using 1.9oz rip-stop nylon and 550 lb parachute cord.  
-        If time runs short, equivalent chutes from SkyAngle, 
-        Rocketman, or Giant Leap could be substituted (at significantly higher 
-        cost).
-      </p><p>
-        The deployment bag will probably be purchased from Giant Leap.  The
-        recovery harness will probably use tubular kevlar, also from Giant Leap.
-      </p><p>
-        The recovery system attachment points will all use 1/4 inch u-bolts with
-        nuts, washers, and backing plates through bulkheads except for the fin
-        can.  The fin can has insufficient room between the motor mount and
-        the airframe inner wall for nuts and washers, so an alternative means of
-        recovery system attachment is required.  The fin can will be equipped 
-        with either a 3/16 inch stainless steel aircraft cable loop, or a loop 
-        of 1/2 inch tubular kevlar, bonded to the motor mount.
-        If available, a screw-eye attached to the forward motor closure may be 
-        used instead of or in addition to this recovery attachment loop.
-      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2592234"></a>Chapter 3. Construction Details</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2599259">Airframe and Couplers</a></span></dt><dt><span class="section"><a href="#id2596433">Fins</a></span></dt><dt><span class="section"><a href="#id2606804">Centering Rings and Bulkheads</a></span></dt><dt><span class="section"><a href="#id2588775">Assembling the Booster Section</a></span></dt><dt><span class="section"><a href="#id2584973">Avionics Bay</a></span></dt><dt><span class="section"><a href="#id2606384">Payload Bay</a></span></dt><dt><span class="section"><a href="#id2607348">Recovery System</a></span></dt></dl></div><p>
-       I have collected all of my
-       <a class="ulink" href="http://gallery.gag.com/rockets/yikstik" target="_top">
-       build photos
-        </a>
-       in one place, they may show better than I can explain how various
-       aspects of YikStik went together.
-      </p><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2599259"></a>Airframe and Couplers</h2></div></div></div><p>
-        The tubing for the airframe, couplers, and motor mount was all cut
-        using a carefully aligned and adjusted power mitre saw, and the ends
-        lightly sanded to remove rough spots.  
-        The main and drogue bays were cut from one 48 inch length of Giant 
-        Leap 98mm Dynawind tubing, the fin can, electronics bay, and payload 
-        bay were cut from the second.  The three couplers for the fin can, 
-        electronics bay, and payload bay were cut from Giant Leap 98mm phenolic
-        coupler stock.  And the motor mount was cut from Giant Leap 75mm
-        phenolic airframe stock.  
-        Note that the motor mount is the longest piece because of 
-        the zipperless design with full-length motor mount.
-      </p><p>
-        The airframe tubing selected includes a wrap of 10oz glass in epoxy
-        over the base phenolic tubing (visible in some photos as a 
-        shine on the outside of the tubing), 
-       but the coupler stock is unreinforced.
-        To ensure the couplers can handle the anticipated loading, I reinforced
-        each with one layer of interior carbon fiber, using the "kitchen 
-        vacuum bagging" technique documented by 
-        <a class="ulink" href="http://www.jcrocket.com/kitchenbagging.shtml" target="_top"> 
-          John Coker.  
-        </a>
-      </p><p>
-        This was my first hands-on experience working with carbon fiber.  The
-        end of the coupler nearest the unit during bagging experienced some
-        crushing of the fibers right at the end.  It doesn't matter for this
-        project because each of the couplers will have at least one end fitted
-        with a bulkhead or centering ring, but in the future I'll be tempted 
-        to cut the coupler stock a bit long before bagging and trim to length
-        after reinforcing to get "perfect" ends.  The technique worked 
-        marvelously otherwise, and the resulting couplers look and should work
-        great!
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2596433"></a>Fins</h2></div></div></div><p>
-        Six pieces of 1/8 inch birch plywood were stacked, edge-aligned on what
-        would be the fin root edge, and clamped.  The outline of the fin design
-        was marked in pencil, and three 1/8 inch holes drilled through the
-        stack inside the fins to allow using 4-40 screws and nuts to hold the
-        blanks together while making the initial cuts, so that they would all be
-        matched in size.  The clamps were removed to avoid interference
-        during cutting.  The fin outline was then cut using a radial arm saw.
-      </p><p>
-        A router table with 1/8 inch
-       roundover bit was then used to round over the outer edge, 3 blanks on
-        one side and three on the other.  This edge might have been left square,
-        but I prefer the look and feel of rounding.  The router table with a 1/2
-        inch diameter straight cutting bit and a fin beveling jig was used
-        to impart a 10-degree bevel on the leading and trailing edge of each fin
-        blank, again 3 on one side and three on the other.  The resulting 6 
-        blanks thus form 3 pairs of fin components with a modified 
-       airfoil shape.
-      </p><p>
-        The fin assembly started with a simple lamination of two layers of ply
-        sandwiching a layer of carbon fiber.  Each fin used "one pump" of West
-        Systems epoxy and the stack was vacuum bagged using the Foodsaver with
-        wide bagging material.  To keep everything flat while the epoxy cured,
-        the stack of fins was sandwiched between two unused extra shelves for 
-        a storage cabinet I had on hand 
-       (particle board covered in laminate, very
-        flat and smooth, nearly inflexible at this loading), and stacked with 
-        about 75 lbs of loose barbell weights.  
-      </p><p>
-        On one of the three fins, the plywood layers are out of alignment by
-        1-2mm in the longest axis.  The other two are nearly perfect.  Light
-        sanding should allow me to match them before laminating the outer layers
-        of carbon fiber and glass.
-      </p><p>
-        After the fins cured, they were bulk sanded with medium and fine 
-        sandpaper and an electric palm sander.  Final sanding of the leading
-        and trailing edges was done using 400 grit paper on a flat surface,
-        holding the fin the way you'd sharpen a knife against a stone.  The
-        results seem good, all three fins match pretty closely.
-      </p><p>
-        A fin holding jig was cut from 1/8" hardboard using my rotary tool 
-        with a fiber cutoff wheel.  The fin slots were made to be a snug fit.
-        A small batch of epoxy was used to apply a bead to the root edge and
-        tab at the leading edge, then the fins were installed against the 
-        motor mount and locked into place with the jig to cure.  The centering
-        ring that locks the aft edge of the fins was dry-fit during this
-        operation to ensure proper alignment, but was not glued yet.  It will
-        go on after the airframe and internal fin filets are installed.
-      </p><p>
-        The fins were reinforced with fiberglass and epoxy.  Masking tape was
-        used to carefully delineate where the airframe ID will be, then 6oz
-        glass 14.25" by 3.5" was epoxied fin-fin across the MMT.  Strips of
-        8.6oz "boat tape" fiberglass were worked into the joints with more
-        epoxy, and a sheet of plastic covered by ziplog bags of water were
-        used to hold things in place during the initial curing.  The three
-        sides were done one at a time and allowed to cure before proceeding.
-        The results look good, and in combination with internal and external
-        airframe filets should yield a super-strong fin can.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2606804"></a>Centering Rings and Bulkheads</h2></div></div></div><p>
-        Pairs of 3/8 inch birch plywood blanks were laminated using Titebond
-        wood glue and clamped while curing to form 3/4 inch blanks for centering
-        rings.  From a strength perspective, 3/8 inch should suffice, but there
-        are two reasons for going with thicker blanks in some places.  The first
-        is that the rail buttons chosen use 1/4-20 mounting screws, and threaded
-        inserts in that size are nearly 3/8 inch outside diameter 
-       (and thus would
-        tear up a ring only 3/8 inch thick on insertion).  The second is that I
-        like to mill slots in the centering rings on each end of the fins to
-        "lock" the fins into position.  Doubling the blanks used to cut those
-        rings will allow me to cut 1/4 inch deep fin slots and still have a half
-        inch of unmolested wood in the rings for strength.
-      </p><p>
-        The aft centering ring and the one just aft of the zipperless
-        coupler section were edge-drilled for the installation of brass
-        1/4-20 threaded inserts to hold rail buttons.  The inserts were
-        locked in place with epoxy, then ground down until nothing protruded
-        beyond the OD of the ring.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2588775"></a>Assembling the Booster Section</h2></div></div></div><p>
-        The forward two centering rings were installed on the MMT using
-        JB Weld high-temperature epoxy, and incorporating an aircraft cable
-        loop for recovery system retention since there just wasn't room for
-        u-bolts.
-      </p><p>
-        The ring at the leading edge of the fins was initially installed 
-        assuming the aft ring would be nearly flush with the rear of the MMT
-        and equipped with Kaplow-clip style retainers, but before the fins
-        were installed a Giant Leap Slimline Tailcone Retainer for 75mm motor
-        in 98mm airframe became available thanks to Tim Thomas, and so this
-        ring was cut out and replaced with another one inch farther forward 
-        to allow installation of the tailcone at the rear of the MMT.  I 
-        really like the tailcone on my Vertical Assault kit, and think it'll
-        work out to be a great addition for this rocket!
-      </p><p>
-        An alignment jig for the fins was carefully marked out and then cut 
-        from 1/8 inch hardboard using my rotary tool and abrasive cutoff wheel.
-        The fins were then epoxied at the root and short leading edge to the
-        motor mount tube and into the slots in the forward centering ring,
-        and held rigidly aligned by the jig until the epoxy set.  The fins
-        were then masked at what would be the ID of the airframe tube, and
-        reinforced with 6oz glass fin-fin across the motor mount tube between
-        each fin pair, further reinforced with strips of 1 inch glass "boat
-        tape" at each fin root joint.
-      </p><p>
-        The airframe tubing section was carefully marked for fin slots, which
-        were then cut using my rotary tool with abrasive cutoff wheel.  Epoxy
-        was applied ahead of the center two rings as the frame was slid into
-        place, and the frame left standing upright until the epoxy set to
-        hopefully form ring-fin fillets on those two rings.  The interior
-        fin to airframe joints were reinforced one fin at a time using West
-        Systems epoxy will milled glass as a filler.  A long 3/8" dowel was
-        used to place and smooth these interior filets.  The aft centering ring
-        was installed by pouring West Systems epoxy in the three fin-fin gaps, 
-        placing the ring, then standing the airframe up to allow the epoxy to
-        flow over the forward surface of the ring and into the gaps between it,
-        the motor mount, and the airframe tubing.  After it set, the booster
-        was placed nose-down, the airframe gaps behind the fins were taped,
-        and more epoxy was applied to seal the aft of the ring to the tubes.
-        Before this epoxy set, JB Weld was used to glue the tail cone retainer
-        in place on the MMT.  
-      </p><p>
-        The exterior fin to
-        airframe joints were filleted using 5-minute epoxy thickened with 
-        baby powder and smoothed with the tip of a plastic spoon, which I 
-        learned about building the Vertical Assault kit.  Gives great results,
-        and allowed all 6 joints to be done in one session.  The space
-        above the top surface of the forward centering ring and between the 
-        motor mount and zipperless-design coupler tubing was filled with epoxy
-        and milled glass.  Minor gaps in the airframe behind each fin were
-        filled with epoxy clay.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2584973"></a>Avionics Bay</h2></div></div></div><p>
-        The avionics bay contains the two commercial altimeters used to
-        record information about the flight and deploy the drogue and main
-        recovery systems.  It is constructed of a piece of Giant Leap 98mm
-        coupler tubing reinforced with an interior wrap of vacuum-bagged
-        carbon fiber, and a 2 inch length of Giant Leap 98mm DynaWind airframe
-        tubing.  
-      </p><p>
-        The bulkheads are custom-milled from 3/8 inch birch plywood
-        milled so that about 3/16" fits inside the coupler and the remainder
-        seals the end of the coupler and just fits inside the airframe.  Each
-        bulkhead has a u-bolt for attaching the recovery harnesses, and dual
-        CPVC end caps as ejection charge holders with screw terminal blocks
-        from Missile Works to attach the igniters.  Two lengths of 1/4 inch
-        all-thread with nuts and washers tie the bulkheads together, with
-        wing-nuts used on one end to allow for easy disassembly.
-      </p><p>
-        A sled was fabricated to hold the altimeters and batteries.  It
-        consists of 1/8 inch birch ply laminated with 6oz fiberglass on each 
-        side, epoxied to cardboard tubes taken from the packaging for Aerotech
-        igniters that slide over the all-thread, further reinforced with nylon
-        ties at each end.  The tubes are staggered one on either side so that
-        the sled goes right up the center of the airframe tubing.
-      </p><p>
-        Two "centering rings" containing three each 6-32 threaded inserts are
-        epoxied inside the bay to provide hard points for attaching the 
-        airframe tubes for the drogue and main recovery bays.  The inside
-        diameter of these rings is notched for the avionics sled, and thus
-        these rings also provide physical support for the sled.
-      </p><p>
-        Three rotary switches from Missile Works are installed through the
-        short airframe tubing section, drilled such that they end up 
-        essentially flush with the outside of the airframe, clamp the coupler
-        tubing, and project inside the bay.  Two are wired as SPST switches
-        for power to the two altimeters, the third is wired as a DPST switch
-        that open-circuits the igniters for the required "safe/arm" function
-        called for in the NAR L3 certification requirements.
-      </p><p>
-        The wiring of the avionics bay is documented in the attached 
-        schematic diagram.  Connectors were used to allow each bulkhead and
-        the switches in the housing to be quickly detached from the sled.
-        The connectors are 9-pin D shells for the switch wiring, and 4-pin
-        Molex connectors like those used on older PC hard drive power cables
-        for the bulkheads.  To allow use of a single switch pole for the 
-        safe/arm function for each altimeter, the two igniters attached to
-        each altimeter are safed by interrupting the common return lines as
-        shown in the schematic.  
-      </p><p>
-        Sizing the static port for the avionics bay was done by applying the
-        formulas suggested by PerfectFlite and Missile Works for their
-        respective altimeter products, then comparing the results with each
-        other and with information found on the web.  I've personally had 
-        better luck with single ports than with multiple holes, perhaps because
-        I've been working with relatively small rockets.  Regardless, I'm 
-        sticking with what I know and will use a single static port hole here.
-      </p><p>
-        The measured dimensions
-        of the avionics bay as constructed are 95mm ID and approximately 250mm
-        between bulkheads.  This works out to 108.73 cubic inches before
-        accounting for the volume of the sled, electronics, and wiring and
-        other components inside the bay.  By the PerfectFlight formula, the 
-        static port should be 0.221 inches in diameter.  By the Missile Works 
-        formula for a bay over 100 cubic inches the answer is 0.261 inches.  
-        The closest standard drill size, which happens to split the difference,
-        is 0.250 inches.  Easy enough!
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2606384"></a>Payload Bay</h2></div></div></div><p>
-        The construction of the payload bay is very similar to the avionics
-        bay, except that there is a hard-epoxied rear bulkhead, and only one
-        screw ring to hard-mount the nose cone.  The forward end of the 
-        payload bay is open to the open interior volume of the nose cone in
-        anticipation of extending downlink antennas above the carbon fiber 
-        reinforcement in the coupler and into the nose cone, since carbon 
-        fiber is opaque to RF.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2607348"></a>Recovery System</h2></div></div></div><p>
-        Pre-sewn 1/4 inch tubular kevlar harness sections were purchased 
-        from Giant Leap, along with a small kevlar deployment bag and two
-        kevlar chute protectors.
-      </p><p>
-        For an apogee drogue, I plan to fly a Public Missiles 4 x 144 inch
-        nylon streamer.  It will be protected with one of the kevlar blankets
-        and attached to one of the kevlar harness sections holding the booster
-        to the avionics bay.
-      </p><p>
-        The main parachute will be sewn from 1.9 oz rip-stop nylon purchased
-        from the 
-        <a class="ulink" href="http://www.milloutletfabric.com/" target="_top">
-          Mill Outlet Fabric Shop
-        </a>
-        in Colorado Springs.  Using the spreadsheet from 
-        <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
-          Team Vatsaas
-        </a>
-        I calculate that we want an 8 foot chute to keep the airframe less
-        nose cone and payload bay below 20 feet per second at touch-down.
-      </p><p>
-        To extract the main chute and recover the nose cone and payload bay,
-        a 3 foot parachute from BSD Rocketry will be packed in a kevlar
-        blanket ahead of the main chute deployment bag, attached by kevlar
-        harness to the nose cone and payload bay assembly, and to the top of
-        the deployment bag.  This assembly will recover separately from the
-        rest of the rocket.
-      </p><p>
-        The altimeters are programmed such that the MAWD fires its drogue
-        charge at apogee and its main charge at 1100 feet.  The miniRRC2
-        is programmed to fire its drogue charge two seconds past apogee, 
-        and its main charge at 900 feet.  Thus the MAWD is primary and the
-        miniRRC2 is the backup.  Since the M1297W has a burn time of about
-        5 seconds, mach inhibit is programmed on both altimeters to 8 seconds.
-      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2600260"></a>Chapter 4. Recovery Systems Package</h2></div></div></div><div class="toc"><p><b>Table of Contents</b></p><dl><dt><span class="section"><a href="#id2595964">Recovery System Description</a></span></dt><dt><span class="section"><a href="#id2609782">Recovery Initiation Control Components</a></span></dt></dl></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2595964"></a>Recovery System Description</h2></div></div></div><p>
-        This rocket uses dual deployment.  
-      </p><p>
-        The apogee event separates the
-        airframe between the zipperless-design booster section and the 
-        drogue bay.  These two sections are linked by a Giant Leap 20 foot
-        pre-sewn 1/4 inch tubular kevlar assembly, attached to which is a
-        Public Missiles 4 x 144 inch red nylon streamer packed in a Giant Leap
-        kevlar chute protection pad.
-      </p><p>
-        The main event separates the airframe between the forward payload bay
-        and the main bay.  Attached to the nose cone and payload bay assembly
-        is a Giant Leap 15 foot pre-sewn 1/4 inch tubular kevlar assembly, 
-        attached "free bag" style to the top of a Giant Leap deployment bag
-        containing the main chute.  A 36 inch BSD Rocketry nylon parachute
-        packed in a Giant Leap kevlar chute protection pad serves to pull the
-        deployment bag off the main chute, after which it allows for safe
-        recovery of the nose cone and payload assembly at just under 20 feet
-        per second.
-      </p><p>
-        The 8 foot main chute is home-made from 1.9 oz rip-stop nylon using 
-        the design documented by 
-        <a class="ulink" href="http://www.vatsaas.org/rtv/systems/Parachutes/Chute.aspx" target="_top">
-          Team Vatsaas.
-        </a>
-        It is attached to the remainder of the rocket using another Giant Leap
-        pre-sewn 1/4 inch tubular kevlar assembly.
-      </p><p>
-        The anchor points are all 5/16 inch u-bolts, except for on the booster
-        which is equipped with an embedded loop of 3/16 inch stainless aircraft
-        cable.  All connections are made with suitable quick-links.
-      </p></div><div class="section" lang="en"><div class="titlepage"><div><div><h2 class="title" style="clear: both"><a name="id2609782"></a>Recovery Initiation Control Components</h2></div></div></div><p>
-        The LOC-style avionics bay between the main and drogue bays is 
-        populated with two commercial altimeters, a PerfectFlite MAWD 
-        and a Missile Works miniRRC2.  
-        Each is powered by a dedicated 9V battery, and has a 
-        dedicated on/off power switch mounted for access from outside the 
-        rocket.  Additionally, a single safe/arm switch with two poles is used
-        to interrupt the return circuits from the igniters to each altimeter.
-        See the attached schematic of the avionics bay contents for more
-        details.
-      </p><p>
-        The bulkheads at each end of the avionics bay have two CPVC end caps
-        for ejection charge holders, and two-terminal screw blocks for 
-        attachment of electric matches purchase from Giant Leap used to ignite
-        Goex 4F black powder ejection charges.  Each charge holder and terminal
-        block pair is labelled as to main or backup since the charges will be
-        different for each.
-      </p><p>
-        The    
-        <a class="ulink" href="http://www.info-central.org/recovery_powder.shtml" target="_top">
-          Info Central Black Powder Sizing
-        </a>
-        page is the most authoritative site I've found on this topic.
-        Each of the main and drogue bay interfaces will use 2 2-56 nylon screws
-        as shear pins, each of which needs 35 pounds of force or so to shear.
-        Designing for 15psi puts us between 150 and 200 pounds total force in
-        a 4 inch airframe.  The formula is thus 0.006 grams times diameter 
-        squared in inches times length in inches.
-      </p><p>
-        My drogue bay is 3.9 inches ID and 8 inches long, or 95.52 cubic 
-        inches.  That works out to about 0.73 grams.  However, there will be
-        some volume in the motor mount tube above the motor that also must
-        be accounted for, enough to nearly double the total volume when flying
-        on the M1297W certification motor.  Also, since this charge must fire 
-        reliably at 15-18k feet above ground level of around 5k feet, such 
-        that combustion is likely to be incomplete, we need to add some margin.
-      </p><p>
-        My main bay is 3.9 inches ID and about 25 inches between bulkheads,
-        or about 298.50 cubic inches.  That works out to 2.28 grams.  
-      </p><p>
-        Sanity checking, PerfectFlite recommends that a 4F black powder charge 
-        be sized by multiplying the volume of the bay in cubic inches by 0.01 
-        grams.  That yields about 1.8 grams for the drogue bay and 3 grams for
-        the main bay.
-      </p><p>
-        That suggested to me that a good starting point for ground testing is
-        1.5 grams for the drogue bay and 2.5 grams for the main bay.  Ground
-        tests were done using the PC interface cable for the MAWD routed in
-        through the static test port to manually trigger ejections.  Testing
-        of the apogee bay showed that 1.5 grams was sufficient for deployment
-        and 1.8 grams was more authoritative.  A single test of main deploy 
-        with 2.5 grams gave a nearly perfect result.
-        Given the altitude of our expected apogee, we should be generous with
-        the apogee charge, perhaps using 2.0 grams for the primary.  The main 
-        will deploy at an altitude below where the tests were performed, so
-        no adjustment in charge size should be required.
-      </p><p>
-        Descent rate of the nose cone and payload bay which mass just under
-        1kg will be less than 20 feet per second with a 36 inch chute based
-        on manufacturer recommendations and Rocksim v8 simulation.
-        Descent rate of the remainder of the rocket under the 8 foot chute
-        should be about 18 feet per second by the spreadsheet provided by
-        the designers of this chute pattern, sanity checked using the descent
-        rate tables of similar commercial parachute designs, like those from
-        The Rocketman.
-      </p></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2585586"></a>Chapter 5. Stability Evaluation</h2></div></div></div><p>
-      Simulation using Rocksim v8 with a variety of motors showed that the
-      rocket is unconditionally stable with all motors likely to be flown.
-      The worst-case stability among 75mm motors is actually with the 
-      M1297W chosen for the certification flight, at margin 1.05.  This is
-      because the front of this motor falls almost exactly at the CP.  Using 
-      a longer motor like the M1850W raises the initial stability margin to
-      1.10 because the front fuel grain is ahead of the CP, and lesser
-      motors also increase the stability because less mass is behind the CP.
-      The smallest motor I can conceive of flying in this rocket (a Cesaroni
-      J285) would leave us overstable with margin 3.79 on the way to about
-      1800 feet apogee.
-    </p></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2606777"></a>Chapter 6. Expected Performance</h2></div></div></div><p>
-      On the certification flight, using an Aerotech M1297W reload and
-      associated hardware, the anticipated apogee is round 14,700 feet.  This
-      is just under 75% of the NCR North Site standing waiver of 20,000 feet.
-    </p><p>
-      The highest altitude simulated would be achieved with an Aerotech 
-      M1850W reload at nearly 18,000 feet.  The lowest altitude simulated 
-      is with a Cesaroni J285 and Slimline adapters to just over 1800 feet.
-    </p><p>
-      add description of anticipated flight profile here, including launch
-      weight, estimated drag coefficient, velocity leaving the rail, max
-      expected velocity, altitude, and acceleration
-    </p></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2611290"></a>Chapter 7.  Checklists </h2></div></div></div><div class="orderedlist"><ol type="1"><li> 
-        Planning
-        <div class="orderedlist"><ol type="1"><li>
-            Pick a club launch with suitable waiver and facilities to 
-            support flight.
-          </li><li>
-            Confirm L3CC member(s) available to attend selected launch.
-          </li><li>
-            Confirm that required loaner motor hardware will be available at launch.
-          </li><li>
-            Notify launch sponsor (club president) of intended flight.
-          </li><li>
-            Notify interested friends of intended flight.
-          </li><li>
-            Perform final pre-flight simulation with as-built masses, etc.
-          </li><li>
-            Gather consummables and tools required to support flight
-            <div class="orderedlist"><ol type="1"><li>
-                fresh 9V batteries
-              </li><li>
-                black powder 
-              </li><li>
-                e-matches 
-              </li><li>
-                motor retainer snap rings
-              </li><li>
-                small nylon wire ties
-              </li><li>
-                cellulose wadding material
-              </li><li>
-                masking tape
-              </li><li>
-                screwdriver for phillips-head airframe screws
-              </li><li>
-                small straight-blade screwdriver for power switches
-              </li><li>
-                motor reload kit
-              </li><li>
-                high temperature grease
-              </li><li>
-                long small diameter dowels for igniter insertion
-              </li></ol></div></li></ol></div></li><li> 
-        Before Leaving Home 
-        <div class="orderedlist"><ol type="1"><li>
-            program altimeters for suitable mach delay and recovery deployment
-            <div class="itemizedlist"><ul type="disc"><li>
-                MAWD
-                <div class="itemizedlist"><ul type="circle"><li>
-                    8 seconds mach delay
-                  </li><li>
-                    1500 foot main deploy
-                  </li></ul></div></li><li>
-                
-                miniRRC2
-                <div class="itemizedlist"><ul type="circle"><li>
-                    8 seconds mach delay
-                  </li><li>
-                    1000 foot main deploy
-                  </li><li>
-                    2 seconds apogee delay
-                  </li><li>
-                    no main delay
-                  </li><li>
-                    dual deploy
-                  </li><li>
-                    ops mode 16 (default)
-                  </li></ul></div></li></ul></div></li><li>
-            assemble all recovery system components and ensure everything fits
-          </li><li>
-            confirm wiring and operation of altimeter power and safe/arm switches
-          </li><li>
-            Ground test recovery system to confirm suitable black powder 
-            charge sizing
-          </li></ol></div></li><li>
-        Pre-Flight
-        <div class="orderedlist"><ol type="1"><li>
-            confirm payload batteries in good condition, bay loaded, power switch works
-          </li><li>
-            confirm reception of signals from transmitter(s) in payload bay
-          </li><li>
-            install fresh 9V batteries for altimeters on avionics bay sled
-          </li><li>
-            inspect altimeters and associated avionics bay wiring for visible faults
-          </li><li>
-            close up avionics bay 
-          </li><li>
-            install e-matches, confirming resistance of 1-2 ohms and fit in charge cups
-          </li><li>
-            power up altimeters, operate safe/arm switch, and confirm e-match continuity
-          </li><li>
-            load BP charges into charge cups 
-            <div class="orderedlist"><ol type="1"><li>
-                Drogue Primary Charge - 2.0 grams 4F BP
-              </li><li>
-                Drogue Backup Charge - 2.5 grams 4F BP
-              </li><li>
-                Main Primary Charge - 2.5 grams 4F BP
-              </li><li>
-                Main Backup Charge - 3.0 grams 4F BP
-              </li></ol></div></li><li>
-            connect recovery harnesses and install recovery bay airframe sections
-          </li><li>
-            power up altimeters, operate safe/arm switch, and confirm e-match continuity
-          </li><li>
-            safe and power-down the altimeters
-          </li><li>
-            load main recovery bay, attaching nosecone and payload bay assembly
-          </li><li>
-            install nylon 2-56 screws as shear pins between main bay and payload bay
-          </li><li>
-            load drogue recovery bay, feeding harness end through fin can motor tube
-          </li><li>
-            install nylon 2-56 screws as shear pins between drogue bay and fin can
-          </li><li>
-            load motor per manufacturer instructions
-          </li><li>
-            attach forged eye-bolt to forward closure if not already present
-          </li><li>
-            attach drogue harness to eye-bolt on forward motor closure
-          </li><li>
-            install motor in motor mount
-          </li><li>
-            install motor retention snap rings
-          </li><li>
-            prepare igniter for later installation by attaching to long 1/8" dowel
-          </li><li>
-            confirm all screws in place, avionics off and safe
-          </li><li>
-            fill out a launch card
-          </li><li>
-            notify RSO/LCO of readiness for inspection and launch, obtain a rail
-            assignment and permission to move rocket to launch pad for final prep
-          </li><li>
-            coordinate readiness with support team members, photographers, observers
-          </li></ol></div></li><li>
-        Final Prep
-        <div class="orderedlist"><ol type="1"><li>
-            move rocket to launch area
-          </li><li>
-            clean and lubricate launch rail if necessary
-          </li><li>
-            power up payload and confirm reception of signals from transmitter(s)
-          </li><li>
-            mount rocket on launch rail, rotate to vertical
-          </li><li>
-            power up primary altimeter, confirm expected beep pattern
-          </li><li>
-            power up backup altimeter, confirm expected beep pattern
-          </li><li>
-            arm ejection charges
-          </li><li>
-            confirm altimeters both giving expected beep patterns for igniter continuity
-          </li><li>
-            install igniter and connect to launch control system
-          </li><li>
-            capture GPS waypoint for rail location
-          </li><li>
-            smile for the cameras, make sure we have enough "foil Murphy!" shots taken
-          </li><li>
-            retreat to safe area behind LCO
-          </li><li>
-            confirm continued reception of transmitter signal(s) from payload bay
-          </li><li>
-            confirm photographers and observers are ready and know what to expect
-          </li><li>
-            make sure binoculars and backpack with water and recovery tools are at hand
-          </li><li>
-            tell RSO and LCO we're ready to launch
-          </li><li>
-            try to relax and enjoy watching the flight!
-          </li></ol></div></li><li>
-        Recovery
-        <div class="orderedlist"><ol type="1"><li>
-            track rocket to landing site
-          </li><li>
-            capture GPS waypoint of landing site, take lots of photos
-          </li><li>
-            note any damage
-          </li><li>
-            gather up and roughly re-pack recovery system for return to flight line
-          </li><li>
-            bring the rocket to observers for post-flight inspection
-          </li></ol></div></li></ol></div></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2610811"></a>Chapter 8. Flight Summary</h2></div></div></div><p>
-       YikStik was flown on an M1297W on Saturday morning at NCR's Oktoberfest
-       2008.  The boost was beautiful.  Unfortunately, we lost visual as the
-       rocket climbed into high clouds near apogee.  Radio tracking signals
-       remained strong for several minutes, then disappeared.  We were 
-       confused by viewing what we thought was YikStik descending before
-       signals were lost in about the right direction, but now believe we 
-       were actually watching a previously launched rocket and did not see
-       YikStik descend.  This confusion prevented location of any of the
-       rocket until Sunday evening, after I had left the launch area.
-      </p><p>
-       After an extensive search, the nose cone assembly was finally found
-       with the Walston tracking gear nearly 3.5 miles down range.  The
-       remainder of the rocket has not been found despite extensive searching
-       on the ground and from the air.  
-      </p><p>
-       Reward if returned posters were placed in the area during the week 
-       following the launch but have elicited no useful reponses yet.
-      </p></div><div class="chapter" lang="en"><div class="titlepage"><div><div><h2 class="title"><a name="id2607490"></a>Chapter 9. Analysis and Conclusions</h2></div></div></div><p>
-       Consideration of how the nose cone ended up where it did suggests 
-       we may have had an apogee deployment of the main, perhaps due to 
-       stress on the shear pins before launch, during boost, or during 
-       apogee drogue deployment causing them to break early.
-      </p><p>
-       It is unfortunate that we were confused by seeing another rocket 
-       descending about the expected amount of time after YikStik's launch
-       in approximately the right direction.  This caused us to believe that
-       the rocket was much closer than the nose cone turned out to be, causing
-       us to waste a lot of time searching in an area too close to the launch
-       site. 
-       It also caused us to assume something really weird had happened to the 
-       transmitters, such that the tracking signal was suddenly lost long 
-       after the rocket was on the ground, instead of what seems to really 
-       have happened, which is that the rocket was farther away descending 
-       after a main deployment at apogee, and the loss of signal was simply
-       due to dropping below a ridge line a couple miles from the launch site.
-       I can't help but think that if we'd been 
-       looking in the right area sooner after the launch that we might have
-       found the rocket before someone else apparently picked it up.
-      </p><p>
-       I regret the decision to use a "free bag" configuration of the 
-       deployment bag.  
-       Since both tracking transmitters were in the payload bay behind
-       the nose cone, and we were eventually able to recover that portion 
-       of the rocket, it is possible that if the deployment bag were tethered
-       to the main that we might have recovered the remainder of the rocket.
-      </p><p>
-       If the rocket is recovered and able to fly again, the two changes I
-       would like to make are to tether the deployment bag to the apex of the
-       main, and to move from 2-56 nylon screws to 4-40 nylon screws for the
-       main deployment shear pins, ensuring the holes through the airframe
-       are a loose enough fit to avoid stresses on the pins during boost.  I
-       have no way to know what happened for sure, but believe this might 
-       solve the assumed problem of main deployment at apogee.
-      </p><p>
-       All in all, the design and build process was educational, and a lot
-       of fun!  I'm looking forward to fabricating more custom parts using
-       carbon fiber and vacuum bagging in the future.  
-       The beautiful boost and obvious survival of the rocket airframe
-       through the expected mach transitions confirms my design and 
-       construction skills are adequate to attain an L3 cert.  
-       While I hope to recover the remainder of YikStik someday, I won't 
-       waste any time before trying again with a new airframe!
-      </p><p>
-       [update]  We have learned that one of the altimeters used in this 
-       flight, the Missile Works miniRRC2, was subject to a fault in 
-       firmware that could cause premature ejection of the main
-       in flights above 10k feet.  Thus, it now seems even more likely
-       that we sustained an apogee ejection of the main, but that it
-       may well have been through no fault of the rocket's design,
-       construction, or preparation.  Frustrating!
-      </p></div></div></body></html>
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