2 * Copyright © 2009 Keith Packard <keithp@keithp.com>
4 * This program is free software; you can redistribute it and/or modify
5 * it under the terms of the GNU General Public License as published by
6 * the Free Software Foundation; version 2 of the License.
8 * This program is distributed in the hope that it will be useful, but
9 * WITHOUT ANY WARRANTY; without even the implied warranty of
10 * MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
11 * General Public License for more details.
13 * You should have received a copy of the GNU General Public License along
14 * with this program; if not, write to the Free Software Foundation, Inc.,
15 * 59 Temple Place, Suite 330, Boston, MA 02111-1307 USA.
18 #ifndef AO_FLIGHT_TEST
22 /* Main flight thread. */
24 __pdata enum ao_flight_state ao_flight_state; /* current flight state */
25 __pdata uint16_t ao_flight_tick; /* time of last data */
26 __pdata uint16_t ao_flight_prev_tick; /* time of previous data */
27 __pdata int16_t ao_flight_accel; /* filtered acceleration */
28 __pdata int16_t ao_flight_pres; /* filtered pressure */
29 __pdata int16_t ao_ground_pres; /* startup pressure */
30 __pdata int16_t ao_ground_accel; /* startup acceleration */
31 __pdata int16_t ao_min_pres; /* minimum recorded pressure */
32 __pdata uint16_t ao_launch_tick; /* time of launch detect */
33 __pdata int16_t ao_main_pres; /* pressure to eject main */
36 * track min/max data over a long interval to detect
39 __pdata uint16_t ao_interval_end;
40 __pdata int16_t ao_interval_cur_min_accel;
41 __pdata int16_t ao_interval_cur_max_accel;
42 __pdata int16_t ao_interval_cur_min_pres;
43 __pdata int16_t ao_interval_cur_max_pres;
44 __pdata int16_t ao_interval_min_accel;
45 __pdata int16_t ao_interval_max_accel;
46 __pdata int16_t ao_interval_min_pres;
47 __pdata int16_t ao_interval_max_pres;
49 __data uint8_t ao_flight_adc;
50 __pdata int16_t ao_raw_accel, ao_raw_accel_prev, ao_raw_pres;
51 __pdata int16_t ao_accel_2g;
53 __xdata uint8_t ao_flight_force_idle;
55 /* Accelerometer calibration
57 * We're sampling the accelerometer through a resistor divider which
58 * consists of 5k and 10k resistors. This multiplies the values by 2/3.
59 * That goes into the cc1111 A/D converter, which is running at 11 bits
60 * of precision with the bits in the MSB of the 16 bit value. Only positive
61 * values are used, so values should range from 0-32752 for 0-3.3V. The
62 * specs say we should see 40mV/g (uncalibrated), multiply by 2/3 for what
63 * the A/D converter sees (26.67 mV/g). We should see 32752/3300 counts/mV,
64 * for a final computation of:
66 * 26.67 mV/g * 32767/3300 counts/mV = 264.8 counts/g
68 * Zero g was measured at 16000 (we would expect 16384).
69 * Note that this value is only require to tell if the
70 * rocket is standing upright. Once that is determined,
71 * the value of the accelerometer is averaged for 100 samples
72 * to find the resting accelerometer value, which is used
73 * for all further flight computations
76 #define GRAVITY 9.80665
77 /* convert m/s to velocity count */
78 #define VEL_MPS_TO_COUNT(mps) (((int32_t) (((mps) / GRAVITY) * (AO_HERTZ/2))) * (int32_t) ao_accel_2g)
80 #define ACCEL_NOSE_UP (ao_accel_2g >> 2)
81 #define ACCEL_BOOST ao_accel_2g
82 #define ACCEL_COAST (ao_accel_2g >> 3)
83 #define ACCEL_INT_LAND (ao_accel_2g >> 3)
84 #define ACCEL_VEL_MACH VEL_MPS_TO_COUNT(200)
85 #define ACCEL_VEL_BOOST VEL_MPS_TO_COUNT(5)
87 int32_t accel_vel_mach;
88 int32_t accel_vel_boost;
91 * Barometer calibration
93 * We directly sample the barometer. The specs say:
95 * Pressure range: 15-115 kPa
96 * Voltage at 115kPa: 2.82
97 * Output scale: 27mV/kPa
99 * If we want to detect launch with the barometer, we need
100 * a large enough bump to not be fooled by noise. At typical
101 * launch elevations (0-2000m), a 200Pa pressure change cooresponds
102 * to about a 20m elevation change. This is 5.4mV, or about 3LSB.
103 * As all of our calculations are done in 16 bits, we'll actually see a change
104 * of 16 times this though
106 * 27 mV/kPa * 32767 / 3300 counts/mV = 268.1 counts/kPa
110 #define BARO_LAUNCH (BARO_kPa / 5) /* .2kPa, or about 20m */
111 #define BARO_APOGEE (BARO_kPa / 10) /* .1kPa, or about 10m */
112 #define BARO_COAST (BARO_kPa * 5) /* 5kpa, or about 500m */
113 #define BARO_MAIN (BARO_kPa) /* 1kPa, or about 100m */
114 #define BARO_INT_LAND (BARO_kPa / 20) /* .05kPa, or about 5m */
115 #define BARO_LAND (BARO_kPa * 10) /* 10kPa or about 1000m */
117 /* We also have a clock, which can be used to sanity check things in
118 * case of other failures
121 #define BOOST_TICKS_MAX AO_SEC_TO_TICKS(15)
123 /* This value is scaled in a weird way. It's a running total of accelerometer
124 * readings minus the ground accelerometer reading. That means it measures
125 * velocity, and quite accurately too. As it gets updated 100 times a second,
128 __pdata int32_t ao_flight_vel;
129 __pdata int32_t ao_min_vel;
130 __pdata int32_t ao_old_vel;
131 __pdata int16_t ao_old_vel_tick;
132 __xdata int32_t ao_raw_accel_sum, ao_raw_pres_sum;
134 /* Landing is detected by getting constant readings from both pressure and accelerometer
135 * for a fairly long time (AO_INTERVAL_TICKS)
137 #define AO_INTERVAL_TICKS AO_SEC_TO_TICKS(5)
139 #define abs(a) ((a) < 0 ? -(a) : (a))
144 __pdata static uint16_t nsamples = 0;
146 ao_flight_adc = ao_adc_head;
147 ao_raw_accel_prev = 0;
152 ao_sleep(&ao_adc_ring);
153 while (ao_flight_adc != ao_adc_head) {
154 __pdata uint8_t ticks;
155 __pdata int16_t ao_vel_change;
156 ao_flight_prev_tick = ao_flight_tick;
158 /* Capture a sample */
159 ao_raw_accel = ao_adc_ring[ao_flight_adc].accel;
160 ao_raw_pres = ao_adc_ring[ao_flight_adc].pres;
161 ao_flight_tick = ao_adc_ring[ao_flight_adc].tick;
163 ao_flight_accel -= ao_flight_accel >> 4;
164 ao_flight_accel += ao_raw_accel >> 4;
165 ao_flight_pres -= ao_flight_pres >> 4;
166 ao_flight_pres += ao_raw_pres >> 4;
169 * The accelerometer is mounted so that
170 * acceleration yields negative values
171 * while deceleration yields positive values,
172 * so subtract instead of add.
174 ticks = ao_flight_tick - ao_flight_prev_tick;
175 ao_vel_change = ao_ground_accel - (((ao_raw_accel + 1) >> 1) + ((ao_raw_accel_prev + 1) >> 1));
176 ao_raw_accel_prev = ao_raw_accel;
178 /* one is a common interval */
180 ao_flight_vel += (int32_t) ao_vel_change;
182 ao_flight_vel += (int32_t) ao_vel_change * (int32_t) ticks;
184 ao_flight_adc = ao_adc_ring_next(ao_flight_adc);
187 if (ao_flight_pres < ao_min_pres)
188 ao_min_pres = ao_flight_pres;
189 if (ao_flight_vel >= 0) {
190 if (ao_flight_vel < ao_min_vel)
191 ao_min_vel = ao_flight_vel;
193 if (-ao_flight_vel < ao_min_vel)
194 ao_min_vel = -ao_flight_vel;
197 switch (ao_flight_state) {
198 case ao_flight_startup:
202 * Collect 1000 samples of acceleration and pressure
203 * data and average them to find the resting values
205 if (nsamples < 1000) {
206 ao_raw_accel_sum += ao_raw_accel;
207 ao_raw_pres_sum += ao_raw_pres;
211 ao_ground_accel = (ao_raw_accel_sum / nsamples);
212 ao_ground_pres = (ao_raw_pres_sum / nsamples);
213 ao_min_pres = ao_ground_pres;
215 ao_main_pres = ao_altitude_to_pres(ao_pres_to_altitude(ao_ground_pres) + ao_config.main_deploy);
216 ao_accel_2g = ao_config.accel_minus_g - ao_config.accel_plus_g;
217 accel_vel_mach = ACCEL_VEL_MACH;
218 accel_vel_boost = ACCEL_VEL_BOOST;
221 ao_old_vel = ao_flight_vel;
222 ao_old_vel_tick = ao_flight_tick;
224 /* Go to pad state if the nose is pointing up */
226 if (ao_config.accel_plus_g != 0 &&
227 ao_config.accel_minus_g != 0 &&
228 ao_flight_accel < ao_config.accel_plus_g + ACCEL_NOSE_UP &&
229 !ao_flight_force_idle)
231 /* Disable the USB controller in flight mode
236 /* Turn on telemetry system
239 ao_telemetry_set_interval(AO_TELEMETRY_INTERVAL_PAD);
241 ao_flight_state = ao_flight_pad;
242 ao_wakeup(DATA_TO_XDATA(&ao_flight_state));
244 ao_flight_state = ao_flight_idle;
246 /* Turn on packet system in idle mode
248 ao_packet_slave_start();
249 ao_wakeup(DATA_TO_XDATA(&ao_flight_state));
251 /* signal successful initialization by turning off the LED */
252 ao_led_off(AO_LED_RED);
258 * Once a second, remove any velocity from
261 if ((int16_t) (ao_flight_tick - ao_old_vel_tick) >= AO_SEC_TO_TICKS(1)) {
262 ao_old_vel_tick = ao_flight_tick;
263 ao_flight_vel -= ao_old_vel;
264 ao_old_vel = ao_flight_vel;
268 * accelerometer: > 2g AND velocity > 5m/s
270 * barometer: > 20m vertical motion
272 * The accelerometer should always detect motion before
273 * the barometer, but we use both to make sure this
274 * transition is detected
276 if ((ao_flight_accel < ao_ground_accel - ACCEL_BOOST &&
277 ao_flight_vel > ACCEL_VEL_BOOST) ||
278 ao_flight_pres < ao_ground_pres - BARO_LAUNCH)
280 ao_flight_state = ao_flight_boost;
281 ao_launch_tick = ao_flight_tick;
283 /* start logging data */
286 /* Increase telemetry rate */
287 ao_telemetry_set_interval(AO_TELEMETRY_INTERVAL_FLIGHT);
289 /* disable RDF beacon */
292 /* Record current GPS position by waking up GPS log tasks */
293 ao_wakeup(&ao_gps_data);
294 ao_wakeup(&ao_gps_tracking_data);
296 ao_wakeup(DATA_TO_XDATA(&ao_flight_state));
300 case ao_flight_boost:
304 * accelerometer: start to fall at > 1/4 G
306 * time: boost for more than 15 seconds
308 * Detects motor burn out by the switch from acceleration to
309 * deceleration, or by waiting until the maximum burn duration
310 * (15 seconds) has past.
312 if (ao_flight_accel > ao_ground_accel + ACCEL_COAST ||
313 (int16_t) (ao_flight_tick - ao_launch_tick) > BOOST_TICKS_MAX)
315 ao_flight_state = ao_flight_fast;
316 ao_wakeup(DATA_TO_XDATA(&ao_flight_state));
324 * accelerometer: integrated velocity < 200 m/s
326 * barometer: fall at least 500m from max altitude
328 * This extra state is required to avoid mis-detecting
329 * apogee due to mach transitions.
331 * XXX this is essentially a single-detector test
332 * as the 500m altitude change would likely result
333 * in a loss of the rocket. More data on precisely
334 * how big a pressure change the mach transition
335 * generates would be useful here.
337 if (ao_flight_vel < ACCEL_VEL_MACH ||
338 ao_flight_pres > ao_min_pres + BARO_COAST)
340 /* set min velocity to current velocity for
343 ao_min_vel = abs(ao_flight_vel);
344 ao_flight_state = ao_flight_coast;
345 ao_wakeup(DATA_TO_XDATA(&ao_flight_state));
348 case ao_flight_coast:
350 /* apogee detect: coast to drogue deploy:
352 * barometer: fall at least 10m
354 * It would be nice to use the accelerometer
355 * to detect apogee as well, but tests have
356 * shown that flights far from vertical would
357 * grossly mis-detect apogee. So, for now,
358 * we'll trust to a single sensor for this test
360 if (ao_flight_pres > ao_min_pres + BARO_APOGEE)
362 /* ignite the drogue charge */
363 ao_ignite(ao_igniter_drogue);
365 /* slow down the telemetry system */
366 ao_telemetry_set_interval(AO_TELEMETRY_INTERVAL_RECOVER);
368 /* slow down the ADC sample rate */
369 ao_timer_set_adc_interval(10);
372 * Start recording min/max accel and pres for a while
373 * to figure out when the rocket has landed
375 /* Set the 'last' limits to max range to prevent
376 * early resting detection
378 ao_interval_min_accel = 0;
379 ao_interval_max_accel = 0x7fff;
380 ao_interval_min_pres = 0;
381 ao_interval_max_pres = 0x7fff;
383 /* initialize interval values */
384 ao_interval_end = ao_flight_tick + AO_INTERVAL_TICKS;
386 ao_interval_cur_min_pres = ao_interval_cur_max_pres = ao_flight_pres;
387 ao_interval_cur_min_accel = ao_interval_cur_max_accel = ao_flight_accel;
389 /* and enter drogue state */
390 ao_flight_state = ao_flight_drogue;
391 ao_wakeup(DATA_TO_XDATA(&ao_flight_state));
395 case ao_flight_drogue:
397 /* drogue to main deploy:
399 * barometer: reach main deploy altitude
401 * Would like to use the accelerometer for this test, but
402 * the orientation of the flight computer is unknown after
403 * drogue deploy, so we ignore it. Could also detect
404 * high descent rate using the pressure sensor to
405 * recognize drogue deploy failure and eject the main
406 * at that point. Perhaps also use the drogue sense lines
407 * to notice continutity?
409 if (ao_flight_pres >= ao_main_pres)
411 ao_ignite(ao_igniter_main);
412 ao_flight_state = ao_flight_main;
413 ao_wakeup(DATA_TO_XDATA(&ao_flight_state));
416 /* fall through... */
419 /* drogue/main to land:
421 * accelerometer: value stable
423 * barometer: altitude stable and within 1000m of the launch altitude
426 if (ao_flight_pres < ao_interval_cur_min_pres)
427 ao_interval_cur_min_pres = ao_flight_pres;
428 if (ao_flight_pres > ao_interval_cur_max_pres)
429 ao_interval_cur_max_pres = ao_flight_pres;
430 if (ao_flight_accel < ao_interval_cur_min_accel)
431 ao_interval_cur_min_accel = ao_flight_accel;
432 if (ao_flight_accel > ao_interval_cur_max_accel)
433 ao_interval_cur_max_accel = ao_flight_accel;
435 if ((int16_t) (ao_flight_tick - ao_interval_end) >= 0) {
436 ao_interval_max_pres = ao_interval_cur_max_pres;
437 ao_interval_min_pres = ao_interval_cur_min_pres;
438 ao_interval_max_accel = ao_interval_cur_max_accel;
439 ao_interval_min_accel = ao_interval_cur_min_accel;
440 ao_interval_end = ao_flight_tick + AO_INTERVAL_TICKS;
441 ao_interval_cur_min_pres = ao_interval_cur_max_pres = ao_flight_pres;
442 ao_interval_cur_min_accel = ao_interval_cur_max_accel = ao_flight_accel;
444 if ((uint16_t) (ao_interval_max_accel - ao_interval_min_accel) < (uint16_t) ACCEL_INT_LAND &&
445 ao_flight_pres > ao_ground_pres - BARO_LAND &&
446 (uint16_t) (ao_interval_max_pres - ao_interval_min_pres) < (uint16_t) BARO_INT_LAND)
448 ao_flight_state = ao_flight_landed;
450 /* turn off the ADC capture */
451 ao_timer_set_adc_interval(0);
452 /* Enable RDF beacon */
455 ao_wakeup(DATA_TO_XDATA(&ao_flight_state));
459 case ao_flight_landed:
465 static __xdata struct ao_task flight_task;
470 ao_flight_state = ao_flight_startup;
471 ao_interval_min_accel = 0;
472 ao_interval_max_accel = 0x7fff;
473 ao_interval_min_pres = 0;
474 ao_interval_max_pres = 0x7fff;
475 ao_interval_end = AO_INTERVAL_TICKS;
477 ao_add_task(&flight_task, ao_flight, "flight");