X-Git-Url: https://git.gag.com/?p=fw%2Faltos;a=blobdiff_plain;f=src%2Fao_flight.c;fp=src%2Fao_flight.c;h=c65670f0d4d5f8c521a06b23826a32f9e6fe44f7;hp=493913b2c1b2a91732bde0fc9cbf407ee2609196;hb=7b009b2efe3af8722c358c304c2243652594e0d5;hpb=20427ae4965f756aac0cedc5179a1c45b9a781f2 diff --git a/src/ao_flight.c b/src/ao_flight.c index 493913b2..c65670f0 100644 --- a/src/ao_flight.c +++ b/src/ao_flight.c @@ -31,22 +31,14 @@ #error Please define HAS_USB #endif -#ifndef USE_KALMAN -#error Please define USE_KALMAN -#endif - /* Main flight thread. */ __pdata enum ao_flight_state ao_flight_state; /* current flight state */ __pdata uint16_t ao_flight_tick; /* time of last data */ __pdata uint16_t ao_flight_prev_tick; /* time of previous data */ -__pdata int16_t ao_flight_pres; /* filtered pressure */ -__pdata int16_t ao_ground_pres; /* startup pressure */ -__pdata int16_t ao_min_pres; /* minimum recorded pressure */ +__xdata int16_t ao_ground_pres; /* startup pressure */ __pdata uint16_t ao_launch_tick; /* time of launch detect */ -__pdata int16_t ao_main_pres; /* pressure to eject main */ #if HAS_ACCEL -__pdata int16_t ao_flight_accel; /* filtered acceleration */ __pdata int16_t ao_ground_accel; /* startup acceleration */ #endif @@ -55,16 +47,8 @@ __pdata int16_t ao_ground_accel; /* startup acceleration */ * resting */ __pdata uint16_t ao_interval_end; -__pdata int16_t ao_interval_cur_min_pres; -__pdata int16_t ao_interval_cur_max_pres; -__pdata int16_t ao_interval_min_pres; -__pdata int16_t ao_interval_max_pres; -#if HAS_ACCEL -__pdata int16_t ao_interval_cur_min_accel; -__pdata int16_t ao_interval_cur_max_accel; -__pdata int16_t ao_interval_min_accel; -__pdata int16_t ao_interval_max_accel; -#endif +__pdata int16_t ao_interval_min_height; +__pdata int16_t ao_interval_max_height; __data uint8_t ao_flight_adc; __pdata int16_t ao_raw_pres; @@ -96,15 +80,8 @@ __pdata int16_t ao_accel_2g; */ #define GRAVITY 9.80665 -/* convert m/s to velocity count */ -#define VEL_MPS_TO_COUNT(mps) (((int32_t) (((mps) / GRAVITY) * (AO_HERTZ/2))) * (int32_t) ao_accel_2g) #define ACCEL_NOSE_UP (ao_accel_2g >> 2) -#define ACCEL_BOOST ao_accel_2g -#define ACCEL_COAST (ao_accel_2g >> 3) -#define ACCEL_INT_LAND (ao_accel_2g >> 3) -#define ACCEL_VEL_MACH VEL_MPS_TO_COUNT(200) -#define ACCEL_VEL_BOOST VEL_MPS_TO_COUNT(5) #endif @@ -127,91 +104,185 @@ __pdata int16_t ao_accel_2g; * 27 mV/kPa * 32767 / 3300 counts/mV = 268.1 counts/kPa */ -#define BARO_kPa 268 -#define BARO_LAUNCH (BARO_kPa / 5) /* .2kPa, or about 20m */ -#define BARO_APOGEE (BARO_kPa / 10) /* .1kPa, or about 10m */ -#define BARO_COAST (BARO_kPa * 5) /* 5kpa, or about 500m */ -#define BARO_MAIN (BARO_kPa) /* 1kPa, or about 100m */ -#define BARO_INT_LAND (BARO_kPa / 20) /* .05kPa, or about 5m */ -#define BARO_LAND (BARO_kPa * 10) /* 10kPa or about 1000m */ - /* We also have a clock, which can be used to sanity check things in * case of other failures */ #define BOOST_TICKS_MAX AO_SEC_TO_TICKS(15) -#if HAS_ACCEL -/* This value is scaled in a weird way. It's a running total of accelerometer - * readings minus the ground accelerometer reading. That means it measures - * velocity, and quite accurately too. As it gets updated 100 times a second, - * it's scaled by 100 - */ -__pdata int32_t ao_flight_vel; -__pdata int32_t ao_min_vel; -__pdata int32_t ao_old_vel; -__pdata int16_t ao_old_vel_tick; -__xdata int32_t ao_raw_accel_sum; -#endif - -#if USE_KALMAN -__pdata int16_t ao_ground_height; -__pdata int32_t ao_k_max_height; -__pdata int32_t ao_k_height; -__pdata int32_t ao_k_speed; -__pdata int32_t ao_k_accel; - #define to_fix16(x) ((int16_t) ((x) * 65536.0 + 0.5)) #define to_fix32(x) ((int32_t) ((x) * 65536.0 + 0.5)) - #define from_fix(x) ((x) >> 16) -#define AO_K0_100 to_fix16(0.05680323) -#define AO_K1_100 to_fix16(0.16608182) -#define AO_K2_100 to_fix16(0.24279580) +#include "ao_kalman.h" + +__pdata int16_t ao_ground_height; +__pdata int16_t ao_height; +__pdata int16_t ao_speed; +__pdata int16_t ao_accel; +__pdata int16_t ao_max_height; + +static __pdata int32_t ao_k_height; +static __pdata int32_t ao_k_speed; +static __pdata int32_t ao_k_accel; #define AO_K_STEP_100 to_fix16(0.01) #define AO_K_STEP_2_2_100 to_fix16(0.00005) -#define AO_K0_10 to_fix16(0.23772023) -#define AO_K1_10 to_fix16(0.32214149) -#define AO_K2_10 to_fix16(0.21827159) - #define AO_K_STEP_10 to_fix16(0.1) #define AO_K_STEP_2_2_10 to_fix16(0.005) +/* + * Above this height, the baro sensor doesn't work + */ +#define AO_MAX_BARO_HEIGHT 8000 + +/* + * Above this speed, baro measurements are unreliable + */ +#define AO_MAX_BARO_SPEED 300 + +static void +ao_kalman_predict(void) +{ +#ifdef AO_FLIGHT_TEST + if (ao_flight_tick - ao_flight_prev_tick > 5) { + ao_k_height += ((int32_t) ao_speed * AO_K_STEP_10 + + (int32_t) ao_accel * AO_K_STEP_2_2_10) >> 4; + ao_k_speed += (int32_t) ao_accel * AO_K_STEP_10; + + return; + } +#endif + ao_k_height += ((int32_t) ao_speed * AO_K_STEP_100 + + (int32_t) ao_accel * AO_K_STEP_2_2_100) >> 4; + ao_k_speed += (int32_t) ao_accel * AO_K_STEP_100; +} + +static __pdata int16_t ao_error_h; +static __pdata int16_t ao_raw_alt; +static __pdata int16_t ao_raw_height; +static __pdata int16_t ao_error_h_sq_avg; + static void -ao_kalman_baro(void) +ao_kalman_err_height(void) { - int16_t err = ((ao_pres_to_altitude(ao_raw_pres) - ao_ground_height)) - - (int16_t) (ao_k_height >> 16); + int16_t e; + ao_error_h = ao_raw_height - (int16_t) (ao_k_height >> 16); + + e = ao_error_h; + if (e < 0) + e = -e; + if (e > 127) + e = 127; + ao_error_h_sq_avg -= ao_error_h_sq_avg >> 4; + ao_error_h_sq_avg += (e * e) >> 4; +} +static void +ao_kalman_correct_baro(void) +{ + ao_kalman_err_height(); #ifdef AO_FLIGHT_TEST if (ao_flight_tick - ao_flight_prev_tick > 5) { - ao_k_height += ((ao_k_speed >> 16) * AO_K_STEP_10 + - (ao_k_accel >> 16) * AO_K_STEP_2_2_10); - ao_k_speed += (ao_k_accel >> 16) * AO_K_STEP_10; - - /* correct */ - ao_k_height += (int32_t) AO_K0_10 * err; - ao_k_speed += (int32_t) AO_K1_10 * err; - ao_k_accel += (int32_t) AO_K2_10 * err; + ao_k_height += (int32_t) AO_BARO_K0_10 * ao_error_h; + ao_k_speed += (int32_t) AO_BARO_K1_10 * ao_error_h; + ao_k_accel += (int32_t) AO_BARO_K2_10 * ao_error_h; return; } #endif - ao_k_height += ((ao_k_speed >> 16) * AO_K_STEP_100 + - (ao_k_accel >> 16) * AO_K_STEP_2_2_100); - ao_k_speed += (ao_k_accel >> 16) * AO_K_STEP_100; - - /* correct */ - ao_k_height += (int32_t) AO_K0_100 * err; - ao_k_speed += (int32_t) AO_K1_100 * err; - ao_k_accel += (int32_t) AO_K2_100 * err; + ao_k_height += (int32_t) AO_BARO_K0_100 * ao_error_h; + ao_k_speed += (int32_t) AO_BARO_K1_100 * ao_error_h; + ao_k_accel += (int32_t) AO_BARO_K2_100 * ao_error_h; } + +#if HAS_ACCEL +static __pdata int16_t ao_error_a; +static __pdata int32_t ao_accel_scale; + +static void +ao_kalman_err_accel(void) +{ + int32_t accel; + + accel = (ao_ground_accel - ao_raw_accel) * ao_accel_scale; + + /* Can't use ao_accel here as it is the pre-prediction value still */ + ao_error_a = (accel - ao_k_accel) >> 16; +} + +static void +ao_kalman_correct_both(void) +{ + ao_kalman_err_height(); + ao_kalman_err_accel(); + +#if 0 + /* + * Check to see if things are crazy here -- + * if the computed height is far above the + * measured height, we assume that the flight + * trajectory is not vertical, and so ignore + * the accelerometer for the remainder of the + * flight. + */ + if (ao_error_h_sq_avg > 10) + { + ao_kalman_correct_baro(); + return; + } +#endif + +#ifdef AO_FLIGHT_TEST + if (ao_flight_tick - ao_flight_prev_tick > 5) { + ao_k_height += + (int32_t) AO_BOTH_K00_10 * ao_error_h + + (int32_t) (AO_BOTH_K01_10 >> 4) * ao_error_a; + ao_k_speed += + ((int32_t) AO_BOTH_K10_10 << 4) * ao_error_h + + (int32_t) AO_BOTH_K11_10 * ao_error_a; + ao_k_accel += + ((int32_t) AO_BOTH_K20_10 << 4) * ao_error_h + + (int32_t) AO_BOTH_K21_10 * ao_error_a; + return; + } +#endif + ao_k_height += + (int32_t) AO_BOTH_K00_100 * ao_error_h + + (int32_t) AO_BOTH_K01_100 * ao_error_a; + ao_k_speed += + (int32_t) AO_BOTH_K10_100 * ao_error_h + + (int32_t) AO_BOTH_K11_100 * ao_error_a; + ao_k_accel += + (int32_t) AO_BOTH_K20_100 * ao_error_h + + (int32_t) AO_BOTH_K21_100 * ao_error_a; +} + +static void +ao_kalman_correct_accel(void) +{ + ao_kalman_err_accel(); + +#ifdef AO_FLIGHT_TEST + if (ao_flight_tick - ao_flight_prev_tick > 5) { + ao_k_height +=(int32_t) AO_ACCEL_K0_10 * ao_error_a; + ao_k_speed += (int32_t) AO_ACCEL_K1_10 * ao_error_a; + ao_k_accel += (int32_t) AO_ACCEL_K2_10 * ao_error_a; + return; + } #endif + ao_k_height += (int32_t) AO_ACCEL_K0_100 * ao_error_a; + ao_k_speed += (int32_t) AO_ACCEL_K1_100 * ao_error_a; + ao_k_accel += (int32_t) AO_ACCEL_K2_100 * ao_error_a; +} +#endif /* HAS_ACCEL */ __xdata int32_t ao_raw_pres_sum; +#ifdef HAS_ACCEL +__xdata int32_t ao_raw_accel_sum; +#endif + /* Landing is detected by getting constant readings from both pressure and accelerometer * for a fairly long time (AO_INTERVAL_TICKS) */ @@ -235,10 +306,6 @@ ao_flight(void) ao_wakeup(DATA_TO_XDATA(&ao_flight_adc)); ao_sleep(DATA_TO_XDATA(&ao_adc_head)); while (ao_flight_adc != ao_adc_head) { -#if HAS_ACCEL - __pdata uint8_t ticks; - __pdata int16_t ao_vel_change; -#endif __xdata struct ao_adc *ao_adc; ao_flight_prev_tick = ao_flight_tick; @@ -246,9 +313,8 @@ ao_flight(void) ao_adc = &ao_adc_ring[ao_flight_adc]; ao_flight_tick = ao_adc->tick; ao_raw_pres = ao_adc->pres; - ao_flight_pres -= ao_flight_pres >> 4; - ao_flight_pres += ao_raw_pres >> 4; - + ao_raw_alt = ao_pres_to_altitude(ao_raw_pres); + ao_raw_height = ao_raw_alt - ao_ground_height; #if HAS_ACCEL ao_raw_accel = ao_adc->accel; #if HAS_ACCEL_REF @@ -335,45 +401,31 @@ ao_flight(void) ao_raw_accel = (uint16_t) ((((uint32_t) ao_raw_accel << 16) / (ao_accel_ref[ao_flight_adc] << 1))) >> 1; ao_adc->accel = ao_raw_accel; #endif - - ao_flight_accel -= ao_flight_accel >> 4; - ao_flight_accel += ao_raw_accel >> 4; - /* Update velocity - * - * The accelerometer is mounted so that - * acceleration yields negative values - * while deceleration yields positive values, - * so subtract instead of add. - */ - ticks = ao_flight_tick - ao_flight_prev_tick; - ao_vel_change = ao_ground_accel - (((ao_raw_accel + 1) >> 1) + ((ao_raw_accel_prev + 1) >> 1)); - ao_raw_accel_prev = ao_raw_accel; - - /* one is a common interval */ - if (ticks == 1) - ao_flight_vel += (int32_t) ao_vel_change; - else - ao_flight_vel += (int32_t) ao_vel_change * (int32_t) ticks; #endif -#if USE_KALMAN - if (ao_flight_state > ao_flight_idle) - ao_kalman_baro(); -#endif - ao_flight_adc = ao_adc_ring_next(ao_flight_adc); - } - - if (ao_flight_pres < ao_min_pres) - ao_min_pres = ao_flight_pres; + if (ao_flight_state > ao_flight_idle) { + ao_kalman_predict(); #if HAS_ACCEL - if (ao_flight_vel >= 0) { - if (ao_flight_vel < ao_min_vel) - ao_min_vel = ao_flight_vel; - } else { - if (-ao_flight_vel < ao_min_vel) - ao_min_vel = -ao_flight_vel; + if (ao_flight_state <= ao_flight_coast) { +#ifndef FORCE_ACCEL + if (/*ao_speed < AO_MS_TO_SPEED(AO_MAX_BARO_SPEED) &&*/ + ao_raw_alt < AO_MAX_BARO_HEIGHT) + ao_kalman_correct_both(); + else +#endif + ao_kalman_correct_accel(); + } else +#endif + if (ao_raw_alt < AO_MAX_BARO_HEIGHT || ao_flight_state >= ao_flight_drogue) + ao_kalman_correct_baro(); + ao_height = from_fix(ao_k_height); + ao_speed = from_fix(ao_k_speed); + ao_accel = from_fix(ao_k_accel); + if (ao_height > ao_max_height) + ao_max_height = ao_height; + } + ao_flight_adc = ao_adc_ring_next(ao_flight_adc); } -#endif switch (ao_flight_state) { case ao_flight_startup: @@ -391,35 +443,25 @@ ao_flight(void) ++nsamples; continue; } + ao_config_get(); #if HAS_ACCEL ao_ground_accel = ao_raw_accel_sum >> 9; + ao_accel_2g = ao_config.accel_minus_g - ao_config.accel_plus_g; + ao_accel_scale = to_fix32(GRAVITY * 2 * 16) / ao_accel_2g; #endif ao_ground_pres = ao_raw_pres_sum >> 9; - ao_min_pres = ao_ground_pres; - ao_config_get(); -#if USE_KALMAN ao_ground_height = ao_pres_to_altitude(ao_ground_pres); -#endif - ao_main_pres = ao_altitude_to_pres(ao_pres_to_altitude(ao_ground_pres) + ao_config.main_deploy); -#if HAS_ACCEL - ao_accel_2g = ao_config.accel_minus_g - ao_config.accel_plus_g; - ao_flight_vel = 0; - ao_min_vel = 0; - ao_old_vel = ao_flight_vel; - ao_old_vel_tick = ao_flight_tick; -#endif /* Check to see what mode we should go to. * - Invalid mode if accel cal appears to be out * - pad mode if we're upright, * - idle mode otherwise */ - ao_config_get(); #if HAS_ACCEL if (ao_config.accel_plus_g == 0 || ao_config.accel_minus_g == 0 || - ao_flight_accel < ao_config.accel_plus_g - ACCEL_NOSE_UP || - ao_flight_accel > ao_config.accel_minus_g + ACCEL_NOSE_UP) + ao_ground_accel < ao_config.accel_plus_g - ACCEL_NOSE_UP || + ao_ground_accel > ao_config.accel_minus_g + ACCEL_NOSE_UP) { /* Detected an accel value outside -1.5g to 1.5g * (or uncalibrated values), so we go into invalid mode @@ -430,7 +472,7 @@ ao_flight(void) #endif if (!ao_flight_force_idle #if HAS_ACCEL - && ao_flight_accel < ao_config.accel_plus_g + ACCEL_NOSE_UP + && ao_ground_accel < ao_config.accel_plus_g + ACCEL_NOSE_UP #endif ) { @@ -465,57 +507,27 @@ ao_flight(void) break; case ao_flight_pad: -#if HAS_ACCEL - /* Trim velocity - * - * Once a second, remove any velocity from - * a second ago - */ - if ((int16_t) (ao_flight_tick - ao_old_vel_tick) >= AO_SEC_TO_TICKS(1)) { - ao_old_vel_tick = ao_flight_tick; - ao_flight_vel -= ao_old_vel; - ao_old_vel = ao_flight_vel; - } -#endif /* pad to boost: * - * accelerometer: > 2g AND velocity > 5m/s - * OR * barometer: > 20m vertical motion + * OR + * accelerometer: > 2g AND velocity > 5m/s * * The accelerometer should always detect motion before * the barometer, but we use both to make sure this - * transition is detected + * transition is detected. If the device + * doesn't have an accelerometer, then ignore the + * speed and acceleration as they are quite noisy + * on the pad. */ -#if USE_KALMAN + if (ao_height > AO_M_TO_HEIGHT(20) #if HAS_ACCEL - /* - * With an accelerometer, either to detect launch - */ - if ((ao_k_accel > to_fix32(20) && - ao_k_speed > to_fix32(5)) || - ao_k_height > to_fix32(20)) -#else - /* - * Without an accelerometer, the barometer is far too - * noisy to rely on speed or acceleration data - */ - if (ao_k_height > to_fix32(20)) -#endif -#else - if ( -#if HAS_ACCEL - (ao_flight_accel < ao_ground_accel - ACCEL_BOOST && - ao_flight_vel > ACCEL_VEL_BOOST) || -#endif - ao_flight_pres < ao_ground_pres - BARO_LAUNCH) + || (ao_accel > AO_MSS_TO_ACCEL(20) && + ao_speed > AO_MS_TO_SPEED(5)) #endif + ) { -#if HAS_ACCEL || USE_KALMAN ao_flight_state = ao_flight_boost; -#else - ao_flight_state = ao_flight_coast; -#endif ao_launch_tick = ao_flight_tick; /* start logging data */ @@ -537,7 +549,6 @@ ao_flight(void) break; } break; -#if HAS_ACCEL || USE_KALMAN case ao_flight_boost: /* boost to fast: @@ -550,13 +561,8 @@ ao_flight(void) * deceleration, or by waiting until the maximum burn duration * (15 seconds) has past. */ -#if USE_KALMAN - if ((ao_k_accel < to_fix32(-10) && ao_k_height > to_fix32(100)) || - (int16_t) (ao_flight_tick - ao_launch_tick) > BOOST_TICKS_MAX) -#else - if (ao_flight_accel > ao_ground_accel + ACCEL_COAST || + if ((ao_accel < AO_MSS_TO_ACCEL(-2.5) && ao_height > AO_M_TO_HEIGHT(100)) || (int16_t) (ao_flight_tick - ao_launch_tick) > BOOST_TICKS_MAX) -#endif { ao_flight_state = ao_flight_fast; ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); @@ -564,62 +570,28 @@ ao_flight(void) } break; case ao_flight_fast: - - /* fast to coast: - * - * accelerometer: integrated velocity < 200 m/s - * OR - * barometer: fall at least 500m from max altitude - * - * This extra state is required to avoid mis-detecting - * apogee due to mach transitions. - * - * XXX this is essentially a single-detector test - * as the 500m altitude change would likely result - * in a loss of the rocket. More data on precisely - * how big a pressure change the mach transition - * generates would be useful here. + /* + * This is essentially the same as coast, + * but the barometer is being ignored as + * it may be unreliable. */ -#if USE_KALMAN - if (ao_k_speed < to_fix32(200) || - ao_k_height < ao_k_max_height - to_fix32(500)) -#else - if (ao_flight_vel < ACCEL_VEL_MACH || - ao_flight_pres > ao_min_pres + BARO_COAST) -#endif - { -#if HAS_ACCEL - /* set min velocity to current velocity for - * apogee detect - */ - ao_min_vel = abs(ao_flight_vel); -#endif + if (ao_speed < AO_MS_TO_SPEED(AO_MAX_BARO_SPEED)) { ao_flight_state = ao_flight_coast; ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); + break; } break; -#endif /* HAS_ACCEL */ case ao_flight_coast: -#if USE_KALMAN /* apogee detect: coast to drogue deploy: * * speed: < 0 - */ - if (ao_k_speed < 0) -#else - /* apogee detect: coast to drogue deploy: - * - * barometer: fall at least 10m * - * It would be nice to use the accelerometer - * to detect apogee as well, but tests have - * shown that flights far from vertical would - * grossly mis-detect apogee. So, for now, - * we'll trust to a single sensor for this test + * Also make sure the model altitude is tracking + * the measured altitude reasonably closely; otherwise + * we're probably transsonic. */ - if (ao_flight_pres > ao_min_pres + BARO_APOGEE) -#endif + if (ao_speed < 0 && (ao_raw_alt >= AO_MAX_BARO_HEIGHT || ao_error_h_sq_avg < 100)) { /* ignite the drogue charge */ ao_ignite(ao_igniter_drogue); @@ -627,32 +599,15 @@ ao_flight(void) /* slow down the telemetry system */ ao_telemetry_set_interval(AO_TELEMETRY_INTERVAL_RECOVER); -#if !USE_KALMAN - /* slow down the ADC sample rate */ - ao_timer_set_adc_interval(10); -#endif - /* - * Start recording min/max accel and pres for a while + * Start recording min/max height * to figure out when the rocket has landed */ - /* Set the 'last' limits to max range to prevent - * early resting detection - */ -#if HAS_ACCEL - ao_interval_min_accel = 0; - ao_interval_max_accel = 0x7fff; -#endif - ao_interval_min_pres = 0; - ao_interval_max_pres = 0x7fff; /* initialize interval values */ ao_interval_end = ao_flight_tick + AO_INTERVAL_TICKS; - ao_interval_cur_min_pres = ao_interval_cur_max_pres = ao_flight_pres; -#if HAS_ACCEL - ao_interval_cur_min_accel = ao_interval_cur_max_accel = ao_flight_accel; -#endif + ao_interval_min_height = ao_interval_max_height = ao_height; /* and enter drogue state */ ao_flight_state = ao_flight_drogue; @@ -674,11 +629,7 @@ ao_flight(void) * at that point. Perhaps also use the drogue sense lines * to notice continutity? */ -#if USE_KALMAN - if (from_fix(ao_k_height) < ao_config.main_deploy) -#else - if (ao_flight_pres >= ao_main_pres) -#endif + if (ao_height <= ao_config.main_deploy) { ao_ignite(ao_igniter_main); ao_flight_state = ao_flight_main; @@ -690,39 +641,17 @@ ao_flight(void) /* drogue/main to land: * - * accelerometer: value stable - * AND * barometer: altitude stable and within 1000m of the launch altitude */ - if (ao_flight_pres < ao_interval_cur_min_pres) - ao_interval_cur_min_pres = ao_flight_pres; - if (ao_flight_pres > ao_interval_cur_max_pres) - ao_interval_cur_max_pres = ao_flight_pres; -#if HAS_ACCEL - if (ao_flight_accel < ao_interval_cur_min_accel) - ao_interval_cur_min_accel = ao_flight_accel; - if (ao_flight_accel > ao_interval_cur_max_accel) - ao_interval_cur_max_accel = ao_flight_accel; -#endif + if (ao_height < ao_interval_min_height) + ao_interval_min_height = ao_height; + if (ao_height > ao_interval_max_height) + ao_interval_max_height = ao_height; if ((int16_t) (ao_flight_tick - ao_interval_end) >= 0) { - ao_interval_max_pres = ao_interval_cur_max_pres; - ao_interval_min_pres = ao_interval_cur_min_pres; - ao_interval_cur_min_pres = ao_interval_cur_max_pres = ao_flight_pres; -#if HAS_ACCEL - ao_interval_max_accel = ao_interval_cur_max_accel; - ao_interval_min_accel = ao_interval_cur_min_accel; - ao_interval_cur_min_accel = ao_interval_cur_max_accel = ao_flight_accel; -#endif - ao_interval_end = ao_flight_tick + AO_INTERVAL_TICKS; - - if ( -#if HAS_ACCEL - (uint16_t) (ao_interval_max_accel - ao_interval_min_accel) < (uint16_t) ACCEL_INT_LAND && -#endif - ao_flight_pres > ao_ground_pres - BARO_LAND && - (uint16_t) (ao_interval_max_pres - ao_interval_min_pres) < (uint16_t) BARO_INT_LAND) + if (ao_height < AO_M_TO_HEIGHT(1000) && + ao_interval_max_height - ao_interval_min_height < AO_M_TO_HEIGHT(5)) { ao_flight_state = ao_flight_landed; @@ -733,6 +662,8 @@ ao_flight(void) ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); } + ao_interval_min_height = ao_interval_max_height = ao_height; + ao_interval_end = ao_flight_tick + AO_INTERVAL_TICKS; } break; case ao_flight_landed: