X-Git-Url: https://git.gag.com/?p=fw%2Faltos;a=blobdiff_plain;f=src%2Fao_flight.c;h=39325a69713f86116850a2314f2bcb6e20b7de4b;hp=ec89e7c2f7e97bdbbb850ead7f1015b1e45e83f1;hb=a80d3836cfce3d4cfa7a71068539415c2dc421cd;hpb=fee46389b70a624ab5b1128a8b4c3083c7747bcb diff --git a/src/ao_flight.c b/src/ao_flight.c index ec89e7c2..39325a69 100644 --- a/src/ao_flight.c +++ b/src/ao_flight.c @@ -19,35 +19,44 @@ #include "ao.h" #endif +#ifndef HAS_ACCEL +#error Please define HAS_ACCEL +#endif + +#ifndef HAS_GPS +#error Please define HAS_GPS +#endif + +#ifndef HAS_USB +#error Please define HAS_USB +#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_accel; /* filtered acceleration */ -__pdata int16_t ao_flight_pres; /* filtered pressure */ -__pdata int16_t ao_ground_pres; /* startup pressure */ -__pdata int16_t ao_ground_accel; /* startup acceleration */ -__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_ground_accel; /* startup acceleration */ +#endif /* * track min/max data over a long interval to detect * resting */ __pdata uint16_t ao_interval_end; -__pdata int16_t ao_interval_cur_min_accel; -__pdata int16_t ao_interval_cur_max_accel; -__pdata int16_t ao_interval_cur_min_pres; -__pdata int16_t ao_interval_cur_max_pres; -__pdata int16_t ao_interval_min_accel; -__pdata int16_t ao_interval_max_accel; -__pdata int16_t ao_interval_min_pres; -__pdata int16_t ao_interval_max_pres; +__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_accel, ao_raw_accel_prev, ao_raw_pres; +__pdata int16_t ao_raw_pres; +__xdata uint8_t ao_flight_force_idle; + +#if HAS_ACCEL +__pdata int16_t ao_raw_accel, ao_raw_accel_prev; +__pdata int16_t ao_accel_2g; /* Accelerometer calibration * @@ -71,19 +80,10 @@ __pdata int16_t ao_raw_accel, ao_raw_accel_prev, ao_raw_pres; */ #define GRAVITY 9.80665 -/* convert m/s to velocity count */ -#define VEL_MPS_TO_COUNT(mps) ((int32_t) (((mps) / GRAVITY) * ACCEL_G * 100)) - -#define ACCEL_G 265 -#define ACCEL_ZERO_G 16000 -#define ACCEL_NOSE_UP (ACCEL_G * 2 /3) -#define ACCEL_BOOST ACCEL_G * 2 -#define ACCEL_INT_LAND (ACCEL_G / 10) -#define ACCEL_VEL_LAND VEL_MPS_TO_COUNT(10) -#define ACCEL_VEL_MACH VEL_MPS_TO_COUNT(200) -#define ACCEL_VEL_APOGEE VEL_MPS_TO_COUNT(2) -#define ACCEL_VEL_MAIN VEL_MPS_TO_COUNT(100) -#define ACCEL_VEL_BOOST VEL_MPS_TO_COUNT(5) + +#define ACCEL_NOSE_UP (ao_accel_2g >> 2) + +#endif /* * Barometer calibration @@ -104,35 +104,238 @@ __pdata int16_t ao_raw_accel, ao_raw_accel_prev, ao_raw_pres; * 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) -/* 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 +#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) + +#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_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 */ -__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, ao_raw_pres_sum; +#define AO_MAX_BARO_HEIGHT 12000 + +/* + * Above this speed, baro measurements are unreliable + */ +#define AO_MAX_BARO_SPEED 200 + +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; + } + if (ao_flight_debug) { + printf ("predict speed %g + (%g * %g) = %g\n", + ao_k_speed / (65536.0 * 16.0), ao_accel / 16.0, AO_K_STEP_100 / 65536.0, + (ao_k_speed + (int32_t) ao_accel * AO_K_STEP_100) / (65536.0 * 16.0)); + } +#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_err_height(void) +{ + int16_t e; + int16_t height_distrust; +#if HAS_ACCEL + int16_t speed_distrust; +#endif + + 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; +#if HAS_ACCEL + ao_error_h_sq_avg -= ao_error_h_sq_avg >> 2; + ao_error_h_sq_avg += (e * e) >> 2; +#else + ao_error_h_sq_avg -= ao_error_h_sq_avg >> 4; + ao_error_h_sq_avg += (e * e) >> 4; +#endif + + height_distrust = ao_raw_height - AO_MAX_BARO_HEIGHT; +#if HAS_ACCEL + /* speed is stored * 16, but we need to ramp between 200 and 328, so + * we want to multiply by 2. The result is a shift by 3. + */ + speed_distrust = (ao_speed - AO_MS_TO_SPEED(AO_MAX_BARO_SPEED)) >> (4 - 1); + if (speed_distrust <= 0) + speed_distrust = 0; + else if (speed_distrust > height_distrust) + height_distrust = speed_distrust; +#endif + if (height_distrust <= 0) + height_distrust = 0; + + if (height_distrust) { +#ifdef AO_FLIGHT_TEST + int old_ao_error_h = ao_error_h; +#endif + if (height_distrust > 0x100) + height_distrust = 0x100; + ao_error_h = (int16_t) (((int32_t) ao_error_h * (0x100 - height_distrust)) >> 8); +#ifdef AO_FLIGHT_TEST + if (ao_flight_debug) { + printf("over height %g over speed %g distrust: %g height: error %d -> %d\n", + (double) (ao_raw_height - AO_MAX_BARO_HEIGHT), + (ao_speed - AO_MS_TO_SPEED(AO_MAX_BARO_SPEED)) / 16.0, + height_distrust / 256.0, + old_ao_error_h, ao_error_h); + } +#endif + } +} + +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 += (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 += (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(); + +#ifdef AO_FLIGHT_TEST + if (ao_flight_tick - ao_flight_prev_tick > 5) { + if (ao_flight_debug) { + printf ("correct speed %g + (%g * %g) + (%g * %g) = %g\n", + ao_k_speed / (65536.0 * 16.0), + (double) ao_error_h, AO_BOTH_K10_10 / 65536.0, + (double) ao_error_a, AO_BOTH_K11_10 / 65536.0, + (ao_k_speed + + (int32_t) AO_BOTH_K10_10 * ao_error_h + + (int32_t) AO_BOTH_K11_10 * ao_error_a) / (65536.0 * 16.0)); + } + ao_k_height += + (int32_t) AO_BOTH_K00_10 * ao_error_h + + (int32_t) AO_BOTH_K01_10 * ao_error_a; + ao_k_speed += + (int32_t) AO_BOTH_K10_10 * ao_error_h + + (int32_t) AO_BOTH_K11_10 * ao_error_a; + ao_k_accel += + (int32_t) AO_BOTH_K20_10 * ao_error_h + + (int32_t) AO_BOTH_K21_10 * ao_error_a; + return; + } + if (ao_flight_debug) { + printf ("correct speed %g + (%g * %g) + (%g * %g) = %g\n", + ao_k_speed / (65536.0 * 16.0), + (double) ao_error_h, AO_BOTH_K10_100 / 65536.0, + (double) ao_error_a, AO_BOTH_K11_100 / 65536.0, + (ao_k_speed + + (int32_t) AO_BOTH_K10_100 * ao_error_h + + (int32_t) AO_BOTH_K11_100 * ao_error_a) / (65536.0 * 16.0)); + } +#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; +} + +#ifdef FORCE_ACCEL +static void +ao_kalman_correct_accel(void) +{ + ao_kalman_err_accel(); + + 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; + } + 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 +#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) */ -#define AO_INTERVAL_TICKS AO_SEC_TO_TICKS(20) +#define AO_INTERVAL_TICKS AO_SEC_TO_TICKS(5) #define abs(a) ((a) < 0 ? -(a) : (a)) @@ -142,132 +345,233 @@ ao_flight(void) __pdata static uint16_t nsamples = 0; ao_flight_adc = ao_adc_head; + ao_raw_pres = 0; +#if HAS_ACCEL ao_raw_accel_prev = 0; ao_raw_accel = 0; - ao_raw_pres = 0; +#endif ao_flight_tick = 0; for (;;) { - ao_sleep(&ao_adc_ring); + ao_wakeup(DATA_TO_XDATA(&ao_flight_adc)); + ao_sleep(DATA_TO_XDATA(&ao_adc_head)); while (ao_flight_adc != ao_adc_head) { - __pdata uint8_t ticks; - __pdata int16_t ao_vel_change; + __xdata struct ao_adc *ao_adc; ao_flight_prev_tick = ao_flight_tick; /* Capture a sample */ - ao_raw_accel = ao_adc_ring[ao_flight_adc].accel; - ao_raw_pres = ao_adc_ring[ao_flight_adc].pres; - ao_flight_tick = ao_adc_ring[ao_flight_adc].tick; - - ao_flight_accel -= ao_flight_accel >> 4; - ao_flight_accel += ao_raw_accel >> 4; - ao_flight_pres -= ao_flight_pres >> 4; - ao_flight_pres += ao_raw_pres >> 4; - /* Update velocity - * - * The accelerometer is mounted so that - * acceleration yields negative values - * while deceleration yields positive values, - * so subtract instead of add. + ao_adc = &ao_adc_ring[ao_flight_adc]; + ao_flight_tick = ao_adc->tick; + ao_raw_pres = ao_adc->pres; + 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 + /* + * Ok, the math here is a bit tricky. + * + * ao_raw_accel: ADC output for acceleration + * ao_accel_ref: ADC output for the 5V reference. + * ao_cook_accel: Corrected acceleration value + * Vcc: 3.3V supply to the CC1111 + * Vac: 5V supply to the accelerometer + * accel: input voltage to accelerometer ADC pin + * ref: input voltage to 5V reference ADC pin + * + * + * Measured acceleration is ratiometric to Vcc: + * + * ao_raw_accel accel + * ------------ = ----- + * 32767 Vcc + * + * Measured 5v reference is also ratiometric to Vcc: + * + * ao_accel_ref ref + * ------------ = ----- + * 32767 Vcc + * + * + * ao_accel_ref = 32767 * (ref / Vcc) + * + * Acceleration is measured ratiometric to the 5V supply, + * so what we want is: + * + * ao_cook_accel accel + * ------------- = ----- + * 32767 ref + * + * + * accel Vcc + * = ----- * --- + * Vcc ref + * + * ao_raw_accel 32767 + * = ------------ * ------------ + * 32737 ao_accel_ref + * + * Multiply through by 32767: + * + * ao_raw_accel * 32767 + * ao_cook_accel = -------------------- + * ao_accel_ref + * + * Now, the tricky part. Getting this to compile efficiently + * and keeping all of the values in-range. + * + * First off, we need to use a shift of 16 instead of * 32767 as SDCC + * does the obvious optimizations for byte-granularity shifts: + * + * ao_cook_accel = (ao_raw_accel << 16) / ao_accel_ref + * + * Next, lets check our input ranges: + * + * 0 <= ao_raw_accel <= 0x7fff (singled ended ADC conversion) + * 0x7000 <= ao_accel_ref <= 0x7fff (the 5V ref value is close to 0x7fff) + * + * Plugging in our input ranges, we get an output range of 0 - 0x12490, + * which is 17 bits. That won't work. If we take the accel ref and shift + * by a bit, we'll change its range: + * + * 0xe000 <= ao_accel_ref<<1 <= 0xfffe + * + * ao_cook_accel = (ao_raw_accel << 16) / (ao_accel_ref << 1) + * + * Now the output range is 0 - 0x9248, which nicely fits in 16 bits. It + * is, however, one bit too large for our signed computations. So, we + * take the result and shift that by a bit: + * + * ao_cook_accel = ((ao_raw_accel << 16) / (ao_accel_ref << 1)) >> 1 + * + * This finally creates an output range of 0 - 0x4924. As the ADC only + * provides 11 bits of data, we haven't actually lost any precision, + * just dropped a bit of noise off the low end. */ - ticks = ao_flight_tick - ao_flight_prev_tick; - ao_vel_change = (((ao_raw_accel >> 1) + (ao_raw_accel_prev >> 1)) - ao_ground_accel); - 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; + 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 +#endif + if (ao_flight_state > ao_flight_idle) { + ao_kalman_predict(); +#if HAS_ACCEL + if (ao_flight_state <= ao_flight_coast) { +#ifdef FORCE_ACCEL + ao_kalman_correct_accel(); +#else + ao_kalman_correct_both(); +#endif + } else +#endif + 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); } - if (ao_flight_pres < ao_min_pres) - ao_min_pres = ao_flight_pres; - 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; - } - switch (ao_flight_state) { case ao_flight_startup: /* startup state: * - * Collect 1000 samples of acceleration and pressure + * Collect 512 samples of acceleration and pressure * data and average them to find the resting values */ - if (nsamples < 1000) { + if (nsamples < 512) { +#if HAS_ACCEL ao_raw_accel_sum += ao_raw_accel; +#endif ao_raw_pres_sum += ao_raw_pres; ++nsamples; continue; } - ao_ground_accel = (ao_raw_accel_sum / nsamples); - ao_ground_pres = (ao_raw_pres_sum / nsamples); - ao_min_pres = ao_ground_pres; ao_config_get(); - ao_main_pres = ao_altitude_to_pres(ao_pres_to_altitude(ao_ground_pres) + ao_config.main_deploy); - ao_flight_vel = 0; - ao_min_vel = 0; - ao_old_vel = ao_flight_vel; - ao_old_vel_tick = ao_flight_tick; +#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_ground_height = ao_pres_to_altitude(ao_ground_pres); - /* Go to pad state if the nose is pointing up */ - ao_config_get(); - if (ao_flight_accel < ao_config.accel_zero_g - ACCEL_NOSE_UP) { + /* 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 + */ +#if HAS_ACCEL + if (ao_config.accel_plus_g == 0 || + ao_config.accel_minus_g == 0 || + 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 + */ + ao_flight_state = ao_flight_invalid; + } else +#endif + if (!ao_flight_force_idle +#if HAS_ACCEL + && ao_ground_accel < ao_config.accel_plus_g + ACCEL_NOSE_UP +#endif + ) + { + /* Set pad mode - we can fly! */ + ao_flight_state = ao_flight_pad; +#if HAS_USB /* Disable the USB controller in flight mode * to save power */ ao_usb_disable(); +#endif - /* Turn on telemetry system - */ + /* Disable packet mode in pad state */ + ao_packet_slave_stop(); + + /* Turn on telemetry system */ ao_rdf_set(1); ao_telemetry_set_interval(AO_TELEMETRY_INTERVAL_PAD); - ao_flight_state = ao_flight_pad; - ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); + /* signal successful initialization by turning off the LED */ + ao_led_off(AO_LED_RED); } else { - ao_flight_state = ao_flight_idle; - - /* Turn on the Green LED in idle mode - */ - ao_led_on(AO_LED_GREEN); - ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); + /* Set idle mode */ + ao_flight_state = ao_flight_idle; + + /* signal successful initialization by turning off the LED */ + ao_led_off(AO_LED_RED); } - /* signal successful initialization by turning off the LED */ - ao_led_off(AO_LED_RED); + /* wakeup threads due to state change */ + ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); + break; case ao_flight_pad: - /* 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; - } /* 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 ((ao_flight_accel < ao_ground_accel - ACCEL_BOOST && - ao_flight_vel > ACCEL_VEL_BOOST) || - ao_flight_pres < ao_ground_pres - BARO_LAUNCH) + if (ao_height > AO_M_TO_HEIGHT(20) +#if HAS_ACCEL + || (ao_accel > AO_MSS_TO_ACCEL(20) && + ao_speed > AO_MS_TO_SPEED(5)) +#endif + ) { ao_flight_state = ao_flight_boost; ao_launch_tick = ao_flight_tick; @@ -281,6 +585,12 @@ ao_flight(void) /* disable RDF beacon */ ao_rdf_set(0); +#if HAS_GPS + /* Record current GPS position by waking up GPS log tasks */ + ao_wakeup(&ao_gps_data); + ao_wakeup(&ao_gps_tracking_data); +#endif + ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); break; } @@ -297,59 +607,49 @@ ao_flight(void) * deceleration, or by waiting until the maximum burn duration * (15 seconds) has past. */ - if (ao_flight_accel > ao_ground_accel + (ACCEL_G >> 2) || + 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) { +#if HAS_ACCEL ao_flight_state = ao_flight_fast; +#else + ao_flight_state = ao_flight_coast; +#endif ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); break; } break; +#if HAS_ACCEL 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 (ao_flight_vel < ACCEL_VEL_MACH || - ao_flight_pres > ao_min_pres + BARO_COAST) + if (ao_speed < AO_MS_TO_SPEED(AO_MAX_BARO_SPEED) && + (ao_raw_alt >= AO_MAX_BARO_HEIGHT || ao_error_h_sq_avg < 30)) { - /* set min velocity to current velocity for - * apogee detect - */ - ao_min_vel = abs(ao_flight_vel); ao_flight_state = ao_flight_coast; ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); + break; } break; +#endif case ao_flight_coast: /* apogee detect: coast to drogue deploy: * - * accelerometer: abs(velocity) > min_velocity + 2m/s - * OR - * barometer: fall at least 10m + * speed: < 0 * - * If the barometer saturates because the flight - * goes over its measuring range (about 53k'), - * requiring a 10m fall will avoid prematurely - * detecting apogee; the accelerometer will take - * over in that case and the integrated velocity - * measurement should suffice to find apogee + * Also make sure the model altitude is tracking + * the measured altitude reasonably closely; otherwise + * we're probably transsonic. */ - if (/* abs(ao_flight_vel) > ao_min_vel + ACCEL_VEL_APOGEE || */ - ao_flight_pres > ao_min_pres + BARO_APOGEE) + if (ao_speed < 0 +#if !HAS_ACCEL + && (ao_raw_alt >= AO_MAX_BARO_HEIGHT || ao_error_h_sq_avg < 30) +#endif + ) { /* ignite the drogue charge */ ao_ignite(ao_igniter_drogue); @@ -357,26 +657,15 @@ ao_flight(void) /* slow down the telemetry system */ ao_telemetry_set_interval(AO_TELEMETRY_INTERVAL_RECOVER); - /* slow down the ADC sample rate */ - ao_timer_set_adc_interval(10); - /* - * 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 - */ - ao_interval_min_accel = 0; - ao_interval_max_accel = 0x7fff; - 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; - ao_interval_cur_min_accel = ao_interval_cur_max_accel = ao_flight_accel; + ao_interval_min_height = ao_interval_max_height = ao_height; /* and enter drogue state */ ao_flight_state = ao_flight_drogue; @@ -398,7 +687,7 @@ ao_flight(void) * at that point. Perhaps also use the drogue sense lines * to notice continutity? */ - if (ao_flight_pres >= ao_main_pres) + if (ao_height <= ao_config.main_deploy) { ao_ignite(ao_igniter_main); ao_flight_state = ao_flight_main; @@ -410,42 +699,29 @@ 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 (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; + 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_max_accel = ao_interval_cur_max_accel; - ao_interval_min_accel = ao_interval_cur_min_accel; + 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; + + /* turn off the ADC capture */ + ao_timer_set_adc_interval(0); + /* Enable RDF beacon */ + ao_rdf_set(1); + + 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; - ao_interval_cur_min_pres = ao_interval_cur_max_pres = ao_flight_pres; - ao_interval_cur_min_accel = ao_interval_cur_max_accel = ao_flight_accel; - } - - if ((uint16_t) (ao_interval_max_accel - ao_interval_min_accel) < (uint16_t) ACCEL_INT_LAND && - ao_flight_pres > ao_ground_pres - BARO_LAND && - (uint16_t) (ao_interval_max_pres - ao_interval_min_pres) < (uint16_t) BARO_INT_LAND) - { - ao_flight_state = ao_flight_landed; - - /* turn off the ADC capture */ - ao_timer_set_adc_interval(0); - /* Enable RDF beacon */ - ao_rdf_set(1); - - ao_wakeup(DATA_TO_XDATA(&ao_flight_state)); } break; case ao_flight_landed: @@ -454,37 +730,11 @@ ao_flight(void) } } -#define AO_ACCEL_COUNT_TO_MSS(count) ((count) / 27) -#define AO_VEL_COUNT_TO_MS(count) ((int16_t) ((count) / 2700)) - -static void -ao_flight_status(void) -{ - printf("STATE: %7s accel: %d speed: %d altitude: %d main: %d\n", - ao_state_names[ao_flight_state], - AO_ACCEL_COUNT_TO_MSS(ACCEL_ZERO_G - ao_flight_accel), - AO_VEL_COUNT_TO_MS(ao_flight_vel), - ao_pres_to_altitude(ao_flight_pres), - ao_pres_to_altitude(ao_main_pres)); -} - static __xdata struct ao_task flight_task; -__code struct ao_cmds ao_flight_cmds[] = { - { 'f', ao_flight_status, "f Display current flight state" }, - { 0, ao_flight_status, NULL } -}; - void ao_flight_init(void) { ao_flight_state = ao_flight_startup; - ao_interval_min_accel = 0; - ao_interval_max_accel = 0x7fff; - ao_interval_min_pres = 0; - ao_interval_max_pres = 0x7fff; - ao_interval_end = AO_INTERVAL_TICKS; - ao_add_task(&flight_task, ao_flight, "flight"); - ao_cmd_register(&ao_flight_cmds[0]); }