capture grain masses from batch 4, skeleton files for tomorrow's flights
authorBdale Garbee <bdale@gag.com>
Sat, 3 Jun 2017 04:38:02 +0000 (22:38 -0600)
committerBdale Garbee <bdale@gag.com>
Sat, 3 Jun 2017 04:38:02 +0000 (22:38 -0600)
rockets/research/2017-batch-04.mdwn
rockets/research/2017-test-05.mdwn [new file with mode: 0755]
rockets/research/2017-test-06.mdwn [new file with mode: 0755]

index 99be728..ed976cb 100755 (executable)
@@ -35,28 +35,26 @@ Simulation says:
 
 ## Results ##
 
-Average casting tube mass 1.25g.
+Average 29mm casting tube mass 1.25g.
 
 29mm grains
 
-* Grain 1, ?g gross, ?g net
-* Grain 2, ?g gross, ?g net
-* Grain 3, ?g gross, ?g net
-* Grain 4, ?g gross, ?g net
+* Grain 1, 29.3g gross, 28.05g net
+* Grain 2, 29.1g gross, 27.85g net
+* Grain 3, 28.9g gross, 27.65g net
+* Grain 4, 28.5g gross, 27.25g net
 
-Total of ?g propellant, vs 122g simulated.
+Total of 110.8g propellant, vs 122g simulated.
 
 With a 7.40" liner, 14/64" nozzle throat, buna-n o-rings, simulation says
 this reload will be a 99% G-180, 159 Ns, with about an 0.8 sec burn.
 
 54mm grains
 
-* Grain 5, ?g gross, ?g net
-* Grain 6, ?g gross, ?g net
-* Grain 7, ?g gross, ?g net
-* Grain 8, ?g gross, ?g net
-* Grain 9, ?g gross, ?g net
-* Grain 10, ?g gross, ?g net
-
-Total of ?g propellant, vs 122g simulated.
+* Grain 5, 184.6g gross, ?g net
+* Grain 6, 183.3g gross, ?g net
+* Grain 7, 186.2g gross, ?g net
+* Grain 8, 182.6g gross, ?g net (canted - casting tube tilted at pour time)
+* Grain 9, 184.0g gross, ?g net
+* Grain 10, 180.5g gross, ?g net
 
diff --git a/rockets/research/2017-test-05.mdwn b/rockets/research/2017-test-05.mdwn
new file mode 100755 (executable)
index 0000000..250f080
--- /dev/null
@@ -0,0 +1,14 @@
+# Test 2017-05 #
+
+3 grain 54mm sorbitol motor 
+
+With a 10.250" liner, 8.9mm nozzle throat, buna-n o-rings, simulation says
+this is a 25% J-432, 763 Ns, with about a 1.6 sec burn
+
+* Grain 2017-01-08, 182.6g gross, ?g net
+* Grain 2017-01-09, 184.0g gross, ?g net
+* Grain 2017-01-10, 180.5g gross, ?g net
+
+## Results ##
+
+Flight data logged as ? sn ?, flight ?.
diff --git a/rockets/research/2017-test-06.mdwn b/rockets/research/2017-test-06.mdwn
new file mode 100755 (executable)
index 0000000..a3b95dc
--- /dev/null
@@ -0,0 +1,23 @@
+# Test 2017-05 #
+
+4 grain 29mm sorbitol motor 
+
+With a 7.40" liner, 14/64" nozzle throat, buna-n o-rings, simulation says
+this reload will be a 99% G-180, 159 Ns, with about an 0.8 sec burn.
+
+<p>
+<!--Begin motor 29mm 4-grain Sorbitol #14 HTML export from MotorSim-->
+<table class='motor' style='text-align: left; border: 1px solid black'><tr><th colspan='6' class='title'>29mm 4-grain Sorbitol #14</th></tr><tr class='summary'><th>Rating:</th><td>99% G-180</td><th>Max Pressure:</th><td>6.47 MPa (939 psi)</td></tr><tr class='summary'><th>Total Impulse:</th><td>159 Ns</td><th>Specific Impulse:</th><td>133 s</td></tr><tr class='summary'><th>Max Thrust:</th><td>228 N</td><th>Volume Loading:</th><td>69%</td></tr><tr class='summary'><th>Average Thrust:</th><td>180 N</td><th>Fuel Mass:</th><td>122 g</td></tr><tr><td colspan='4' class='thrust'><img src='http://chart.apis.google.com/chart?chxt=x,x,y,y,r,r&chs=400x200&cht=lxy&chco=3072F3&chds=0,0.89,0,227.96&chxr=0,0,0.89|2,0,227.96|4,0,51.25&chd=t:0,0,0,0,0,0,0,0,0,0,0.02,0.04,0.07,0.12,0.19,0.29,0.44,0.52,0.65,0.78,0.8,0.88,0.89|0,10.15,19.94,29.95,39.31,47.83,55.66,62.85,69.45,75.47,134.47,149.05,157.98,170.21,186.92,207.36,225.35,227.96,219.77,198.86,37.95,0.12,0.06&chxl=1:|s|3:|N|5:|lbf&chxp=1,50|3,50|5,50' width='400' height='200' alt='null' /></td></tr></table>
+<!--End motor 29mm 4-grain Sorbitol #14-->
+</p>
+
+* Grain 2017-04-01, 29.3g gross, 28.05g net
+* Grain 2017-04-02, 29.1g gross, 27.85g net
+* Grain 2017-04-03, 28.9g gross, 27.65g net
+* Grain 2017-04-04, 28.5g gross, 27.25g net
+
+Total of 110.8g propellant, vs 122g simulated.
+
+## Results ##
+
+Flight data logged as ? sn ?, flight ?.