ekf_aw_wrapper.c

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#include "modules/meteo/ekf_aw_wrapper.h"
#include "modules/meteo/ekf_aw.h"
#include <stdio.h>
 
#include "state.h"
#include "filters/low_pass_filter.h"
#include "math/pprz_algebra.h"
 
#include "modules/core/abi.h"
 
#include "autopilot.h"
#include "modules/actuators/actuators.h"
 
#include "mcu_periph/sys_time.h" // FOR DEBUG
 
 
 
#ifndef EKF_AW_WRAPPER_ROTWING
#define EKF_AW_WRAPPER_ROTWING false
#endif
#ifndef EKF_AW_WRAPPER_RANDOM_INPUTS
#define EKF_AW_WRAPPER_RANDOM_INPUTS false
#endif
#ifndef EKF_AW_QUICK_CONVERGENCE
#define EKF_AW_QUICK_CONVERGENCE false
#endif
#ifndef EKF_AW_QUICK_CONVERGENCE_TIME
#define EKF_AW_QUICK_CONVERGENCE_TIME 10.0f
#endif
#ifndef EKF_AW_DEBUG
#define EKF_AW_DEBUG false
#endif
 
#if EKF_AW_WRAPPER_ROTWING
#include "modules/rotwing_drone/wing_rotation_controller_servo.h"
#endif
 
#if PERIODIC_TELEMETRY
#include "modules/datalink/telemetry.h"
 
// TO DO: implement circular wrap filter for psi angle
// TO DO: modify force functions to simpler model (wing)
 
// Telemetry Message functions
static void send_airspeed_wind_ekf(struct transport_tx *trans, struct link_device *dev)
{
  uint8_t healthy = (uint8_t)ekf_aw.health.healthy;
 
  pprz_msg_send_AIRSPEED_WIND_ESTIMATOR_EKF(trans, dev, AC_ID,
      &ekf_aw.V_body.x, &ekf_aw.V_body.y, &ekf_aw.V_body.z,
      &ekf_aw.wind.x, &ekf_aw.wind.y, &ekf_aw.wind.z,
      &ekf_aw.offset.x, &ekf_aw.offset.y, &ekf_aw.offset.z,
      &healthy,
      &ekf_aw.health.crashes_n,
      &ekf_aw.innov_V_gnd.x, &ekf_aw.innov_V_gnd.y, &ekf_aw.innov_V_gnd.z,
      &ekf_aw.innov_acc_filt.x, &ekf_aw.innov_acc_filt.y, &ekf_aw.innov_acc_filt.z,
      &ekf_aw.innov_V_pitot,
      &ekf_aw.acc.x,
      &ekf_aw.acc.y,
      &ekf_aw.acc.z);
}
static void send_airspeed_wind_ekf(struct transport_tx *trans, struct link_device *dev) {…}
 
static void debug_vect(struct transport_tx *trans, struct link_device *dev, char *name, float *data, int datasize)
{
  pprz_msg_send_DEBUG_VECT(trans, dev, AC_ID,
                           strlen(name), name,
                           datasize, data);
}
static void debug_vect(struct transport_tx *trans, struct link_device *dev, char *name, float *data, int datasize) {…}
 
 
 
static void send_airspeed_wind_ekf_debug(struct transport_tx *trans, struct link_device *dev)
{
  debug_vect(trans, dev, "process_cov", ekf_aw.process_cov, 12);
  debug_vect(trans, dev, "meas_cov", ekf_aw.meas_cov, 7);
  debug_vect(trans, dev, "state_cov", ekf_aw.state_cov, 9);
 
  debug_vect(trans, dev, "fuselage_force", ekf_aw.fuselage_force, 3);
  debug_vect(trans, dev, "wing_force", ekf_aw.wing_force, 3);
  debug_vect(trans, dev, "elevator_force", ekf_aw.elevator_force, 3);
  debug_vect(trans, dev, "hover_force", ekf_aw.hover_force, 3);
  debug_vect(trans, dev, "pusher_force", ekf_aw.pusher_force, 3);
 
  float rw_state[4];
  rw_state[0] = ekf_aw.skew;
  rw_state[1] = ekf_aw.elevator_angle;
  rw_state[2] = ekf_aw.RPM_pusher;
  rw_state[3] = ekf_aw.RPM_hover[0];
 
  debug_vect(trans, dev, "rw_state", rw_state, 4);
}
static void send_airspeed_wind_ekf_debug(struct transport_tx *trans, struct link_device *dev) {…}
#endif
 
// RPM ABI Event
abi_event RPM_ev;
float time_of_rpm = 0.0f;
static void rpm_cb(uint8_t sender_id __attribute__((unused)), struct act_feedback_t *rpm_message, uint8_t num_act);
 
// Filter struct
struct ekfAw ekf_aw; // Local wrapper
static struct ekfAwParameters *ekf_params; 
 
// Define settings to change filter tau value
float tau_filter_high = 25.0f;
float tau_filter_low = 0.2f;
 
// Bool Reset EKF Filter
bool reset_filter = false;
 
struct NedCoor_f zero_speed = {
  .x = 0.0f,
  .y = 0.0f,
  .z = 0.0f
};
struct NedCoor_f zero_speed = {…};
 
// Define filter arrays
Butterworth2LowPass filt_groundspeed[3];
Butterworth2LowPass filt_acc[3];
Butterworth2LowPass filt_acc_low[3];
Butterworth2LowPass filt_rate[3];
Butterworth2LowPass filt_euler[3];
Butterworth2LowPass filt_hover_prop_rpm[EKF_AW_RPM_HOVER_NUM];
Butterworth2LowPass filt_pusher_prop_rpm;
Butterworth2LowPass filt_skew;
Butterworth2LowPass filt_elevator_pprz;
Butterworth2LowPass filt_airspeed_pitot;
 
#ifndef PERIODIC_FREQUENCY_AIRSPEED_EKF_FETCH
#define PERIODIC_FREQUENCY_AIRSPEED_EKF_FETCH 100
#endif
 
#ifndef PERIODIC_FREQUENCY_AIRSPEED_EKF
#define PERIODIC_FREQUENCY_AIRSPEED_EKF 25
#endif
 
void ekf_aw_wrapper_init(void)
{
 
  // Define filter frequencies
  float sample_time = 1.0f / PERIODIC_FREQUENCY_AIRSPEED_EKF_FETCH;
  float tau_low = 1.0f / (2.0f * M_PI * tau_filter_low);
  float tau_high = 1.0f / (2.0f * M_PI * tau_filter_high);
 
  // Init filters
  for (int8_t i = 0; i < 3; i++) {
    init_butterworth_2_low_pass(&filt_groundspeed[i], tau_high, sample_time, 0.0); // Init filters groundspeed
    init_butterworth_2_low_pass(&filt_acc[i], tau_high, sample_time, 0.0); // Init filters Accelerations
    init_butterworth_2_low_pass(&filt_acc_low[i], tau_low, sample_time, 0.0); // Init filters Accelerations Low
    init_butterworth_2_low_pass(&filt_rate[i], tau_high, sample_time, 0.0); // Init filters Rate
    init_butterworth_2_low_pass(&filt_euler[i], tau_high, sample_time, 0.0); // Init filters Euler
  }
 
  for (int8_t i = 0; i < EKF_AW_RPM_HOVER_NUM; i++) {
    init_butterworth_2_low_pass(&filt_hover_prop_rpm[i], tau_low, sample_time, 0.0);
    ekf_aw.last_RPM_hover[i] = 0;
  }
 
  init_butterworth_2_low_pass(&filt_pusher_prop_rpm, tau_low, sample_time, 0.0); // Init filters Pusher Prop
  init_butterworth_2_low_pass(&filt_skew, tau_low, sample_time, 0.0); // Init filters Skew
  init_butterworth_2_low_pass(&filt_elevator_pprz, tau_low, sample_time, 0.0); // Init filters Pusher Prop
  init_butterworth_2_low_pass(&filt_airspeed_pitot, tau_low, sample_time, 0.0); // Init filters Pusher Prop
 
#if PERIODIC_TELEMETRY
  register_periodic_telemetry(DefaultPeriodic, PPRZ_MSG_ID_AIRSPEED_WIND_ESTIMATOR_EKF, send_airspeed_wind_ekf);
  register_periodic_telemetry(DefaultPeriodic, PPRZ_MSG_ID_DEBUG_VECT, send_airspeed_wind_ekf_debug);
#endif
 
  // Init EKF Filter
  ekf_aw_init();
 
  // Register ABI message
  AbiBindMsgACT_FEEDBACK(ACT_FEEDBACK_RPM_SENSOR_ID, &RPM_ev, rpm_cb);
 
 
  //Get EKF param handle
  ekf_params = ekf_aw_get_param_handle();
 
  // Related to in air / on ground logic
  ekf_aw.in_air = false;
  ekf_aw.internal_clock = 0;
  ekf_aw.time_last_on_gnd = 0;
 
  // For override of filter using dlsettings
  ekf_aw.override_start = false;
  ekf_aw.override_quick_convergence = false;
 
  // Init of public filter states //TO DO: Is it necessary or just safer?
  for (int i = 0; i < EKF_AW_RPM_HOVER_NUM; i++) {
    ekf_aw.last_RPM_hover[i] = 0;
  }
  ekf_aw.last_RPM_pusher = 0;
 
  ekf_aw.V_body.x = 0.0f; ekf_aw.V_body.y = 0.0f; ekf_aw.V_body.z = 0.0f;
  ekf_aw.wind.x = 0.0f;   ekf_aw.wind.y = 0.0f;   ekf_aw.wind.z = 0.0f;
  ekf_aw.offset.x = 0.0f; ekf_aw.offset.y = 0.0f; ekf_aw.offset.z = 0.0f;
  ekf_aw.health.healthy = true; ekf_aw.health.crashes_n = 0.0f;
  ekf_aw.innov_V_gnd.x = 0.0f; ekf_aw.innov_V_gnd.y = 0.0f; ekf_aw.innov_V_gnd.z = 0.0f;
  ekf_aw.innov_acc_filt.y = 0.0f; ekf_aw.innov_acc_filt.y = 0.0f; ekf_aw.innov_acc_filt.z = 0.0f;
  ekf_aw.innov_V_pitot = 0.0f;
 
  ekf_aw.fuselage_force[0] = 0.0f; ekf_aw.fuselage_force[1] = 0.0f; ekf_aw.fuselage_force[2] = 0.0f;
  ekf_aw.wing_force[0] = 0.0f; ekf_aw.wing_force[1] = 0.0f; ekf_aw.wing_force[2] = 0.0f;
  ekf_aw.elevator_force[0] = 0.0f; ekf_aw.elevator_force[1] = 0.0f; ekf_aw.elevator_force[2] = 0.0f;
  ekf_aw.pusher_force[0] = 0.0f; ekf_aw.pusher_force[1] = 0.0f; ekf_aw.pusher_force[2] = 0.0f;
  ekf_aw.hover_force[0] = 0.0f; ekf_aw.hover_force[1] = 0.0f; ekf_aw.hover_force[2] = 0.0f;
 
  ekf_aw.skew = 0.0f;
  ekf_aw.elevator_angle = 0.0f;
  ekf_aw.RPM_pusher = 0.0f;
  for (int i = 0; i < EKF_AW_RPM_HOVER_NUM; i++) {
    ekf_aw.RPM_hover[i] = 0.0f;
  }
};
void ekf_aw_wrapper_init(void) {…}
 
void ekf_aw_wrapper_periodic(void)
{
 
  // FOR DEBUG
  // uint32_t tic = get_sys_time_usec();
 
  //printf("Running periodic Airspeed EKF Module\n");
  //printf("Airspeed is: %2.2f\n",filt_groundspeed[0].o[0]);
 
  // FOR DEBUG Random acc inputs to filter
  if (EKF_AW_WRAPPER_RANDOM_INPUTS) {
 
    ekf_aw.acc.x = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.acc.y = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.acc.z = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.gyro.p = 0.1f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.gyro.q = 0.1f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.gyro.r = 0.1f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.euler.phi = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.euler.theta = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.euler.psi = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
    for (int i = 0; i < EKF_AW_RPM_HOVER_NUM; i++) {
      ekf_aw.RPM_hover[i] = 1000.0f * rand() / RAND_MAX; // TO BE REMOVED
    }
    ekf_aw.RPM_pusher = 1000.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.skew = 10.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.elevator_angle = 10.0f * rand() / RAND_MAX; // TO BE REMOVED
 
    ekf_aw.Vg_NED.x = 10.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.Vg_NED.y = 10.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.Vg_NED.z = 10.0f * rand() / RAND_MAX; // TO BE REMOVED
 
    ekf_aw.acc_filt.x = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.acc_filt.y = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
    ekf_aw.acc_filt.z = 1.0f * rand() / RAND_MAX; // TO BE REMOVED
 
    ekf_aw.V_pitot = 10.0f * rand() / RAND_MAX; // TO BE REMOVED
  } else {
    // Get latest filtered values to ekf struct
    ekf_aw.acc.x = filt_acc[0].o[0];
    ekf_aw.acc.y = filt_acc[1].o[0];
    ekf_aw.acc.z = filt_acc[2].o[0];
 
    ekf_aw.gyro.p = filt_rate[0].o[0];
    ekf_aw.gyro.q = filt_rate[1].o[0];
    ekf_aw.gyro.r = filt_rate[2].o[0];
 
    ekf_aw.euler.phi = filt_euler[0].o[0];
    ekf_aw.euler.theta = filt_euler[1].o[0];
    //ekf_aw.euler.psi = filt_euler[2].o[0];
    ekf_aw.euler.psi = stateGetNedToBodyEulers_f()->psi; // TO DO: implement circular wrap filter for psi angle
 
    for (int8_t i = 0; i < EKF_AW_RPM_HOVER_NUM; i++) {
      ekf_aw.RPM_hover[i] = filt_hover_prop_rpm[i].o[0];
    }
 
    ekf_aw.RPM_pusher = filt_pusher_prop_rpm.o[0];
    ekf_aw.skew = filt_skew.o[0];
    ekf_aw.elevator_angle = filt_elevator_pprz.o[0];
 
    ekf_aw.Vg_NED.x = filt_groundspeed[0].o[0];
    ekf_aw.Vg_NED.y = filt_groundspeed[1].o[0];
    ekf_aw.Vg_NED.z = filt_groundspeed[2].o[0];
 
    ekf_aw.acc_filt.x = filt_acc_low[0].o[0];
    ekf_aw.acc_filt.y = filt_acc_low[1].o[0];
    ekf_aw.acc_filt.z = filt_acc_low[2].o[0];
 
    ekf_aw.V_pitot = filt_airspeed_pitot.o[0];
 
  }
 
  // Sample time of EKF filter
  float sample_time = 1.0f / PERIODIC_FREQUENCY_AIRSPEED_EKF_FETCH;
 
  // Check if in flight and altitude higher than 1m
  set_in_air_status(autopilot_in_flight() & (-stateGetPositionNed_f()->z > 1.0f));
 
  // Propagate
  if (ekf_aw.in_air | ekf_aw.override_start) {
    // Quick convergence for the first 10 s
    if (((ekf_aw.internal_clock - ekf_aw.time_last_on_gnd < PERIODIC_FREQUENCY_AIRSPEED_EKF * EKF_AW_QUICK_CONVERGENCE_TIME)
         & EKF_AW_QUICK_CONVERGENCE) | ekf_aw.override_quick_convergence) {
      ekf_params->quick_convergence = true;
    } else {
      ekf_params->quick_convergence = false;
    }
 
    ekf_aw_propagate(&ekf_aw.acc, &ekf_aw.gyro, &ekf_aw.euler, &ekf_aw.RPM_pusher, ekf_aw.RPM_hover, &ekf_aw.skew,
                     &ekf_aw.elevator_angle, &ekf_aw.Vg_NED, &ekf_aw.acc_filt, &ekf_aw.V_pitot, sample_time);
  } else {
    // Set body velocity to 0 when landed
    ekf_aw_set_speed_body(&zero_speed);
  };
 
  // Get states, health and innovation from EKF filter
  ekf_aw.V_body = ekf_aw_get_speed_body();
  ekf_aw.wind = ekf_aw_get_wind_ned();
  ekf_aw.offset = ekf_aw_get_offset();
  ekf_aw.health = ekf_aw_get_health();
  ekf_aw.innov_V_gnd = ekf_aw_get_innov_V_gnd();
  ekf_aw.innov_acc_filt = ekf_aw_get_innov_accel_filt();
  ekf_aw.innov_V_pitot = ekf_aw_get_innov_V_pitot();
 
  // Get covariance
  ekf_aw_get_meas_cov(ekf_aw.meas_cov);
  ekf_aw_get_state_cov(ekf_aw.state_cov);
  ekf_aw_get_process_cov(ekf_aw.process_cov);
 
  // Get forces
  ekf_aw_get_fuselage_force(ekf_aw.fuselage_force);
  ekf_aw_get_wing_force(ekf_aw.wing_force);
  ekf_aw_get_elevator_force(ekf_aw.elevator_force);
  ekf_aw_get_hover_force(ekf_aw.hover_force);
  ekf_aw_get_pusher_force(ekf_aw.pusher_force);
 
  ekf_aw.internal_clock++;
 
  // FOR DEBUG
  //ekf_aw.offset.x = get_sys_time_usec()-tic;
};
void ekf_aw_wrapper_periodic(void) {…}
 
// Function to get information from different modules and set it in the different filters
void ekf_aw_wrapper_fetch(void)
{
 
  // For debug
  // uint32_t tic_2 = get_sys_time_usec();
 
  // NED Speed
  update_butterworth_2_low_pass(&filt_groundspeed[0], stateGetSpeedNed_f()->x);
  update_butterworth_2_low_pass(&filt_groundspeed[1], stateGetSpeedNed_f()->y);
  update_butterworth_2_low_pass(&filt_groundspeed[2], stateGetSpeedNed_f()->z);
 
  // Getting body accel
  struct FloatVect3 body_accel_f = {0.0f, 0.0f, 0.0f};
#if EKF_AW_WRAPPER_ROTWING
  // If body accel available, can use this
  struct Int32Vect3 *body_accel_i;
  body_accel_i = stateGetAccelBody_i();
  ACCELS_FLOAT_OF_BFP(body_accel_f, *body_accel_i);
#else
  // Transferring from NED to Body as body is not available right now
  struct NedCoor_i *accel_tmp = stateGetAccelNed_i();
  struct Int32Vect3 ned_accel_i, body_accel_i;
  struct Int32RMat *ned_to_body_rmat = stateGetNedToBodyRMat_i();
  VECT3_COPY(ned_accel_i, (*accel_tmp));
  ned_accel_i.z += ACCEL_BFP_OF_REAL(-9.81); // Add gravity
  int32_rmat_vmult(&body_accel_i, ned_to_body_rmat, &ned_accel_i);
  ACCELS_FLOAT_OF_BFP(body_accel_f, body_accel_i);
#endif
 
  // Body accel
  update_butterworth_2_low_pass(&filt_acc[0], body_accel_f.x);
  update_butterworth_2_low_pass(&filt_acc[1], body_accel_f.y);
  update_butterworth_2_low_pass(&filt_acc[2], body_accel_f.z);
  update_butterworth_2_low_pass(&filt_acc_low[0], body_accel_f.x);
  update_butterworth_2_low_pass(&filt_acc_low[1], body_accel_f.y);
  update_butterworth_2_low_pass(&filt_acc_low[2], body_accel_f.z);
 
  // Body rates
  update_butterworth_2_low_pass(&filt_rate[0], stateGetBodyRates_f()->p);
  update_butterworth_2_low_pass(&filt_rate[1], stateGetBodyRates_f()->q);
  update_butterworth_2_low_pass(&filt_rate[2], stateGetBodyRates_f()->r);
 
  // Euler angles
  update_butterworth_2_low_pass(&filt_euler[0], stateGetNedToBodyEulers_f()->phi);
  update_butterworth_2_low_pass(&filt_euler[1], stateGetNedToBodyEulers_f()->theta);
  //update_butterworth_2_low_pass(&filt_euler[2], stateGetNedToBodyEulers_f()->psi); // TO DO: implement circular wrap filter for psi angle
 
  for (int8_t i = 0; i < EKF_AW_RPM_HOVER_NUM; i++) {
    update_butterworth_2_low_pass(&filt_hover_prop_rpm[i], ekf_aw.last_RPM_hover[i] * 1.0f);
  }
  update_butterworth_2_low_pass(&filt_pusher_prop_rpm, ekf_aw.last_RPM_pusher * 1.0f);
 
#if EKF_AW_WRAPPER_ROTWING
  update_butterworth_2_low_pass(&filt_skew, RadOfDeg(wing_rotation.wing_angle_deg));
 
  // Get elevator pprz signal
  int16_t *elev_pprz = &actuators_pprz[5];
  float de = 0.0f;
  // Calculate deflection angle in [deg]
  de = (-0.004885417f * *elev_pprz + 36.6f) * 3.14f / 180.0f;
 
  update_butterworth_2_low_pass(&filt_elevator_pprz, de);
#else
  update_butterworth_2_low_pass(&filt_skew, 0.0f);
  update_butterworth_2_low_pass(&filt_elevator_pprz, 0.0f);
#endif
 
  update_butterworth_2_low_pass(&filt_airspeed_pitot, stateGetAirspeed_f());
 
  // FOR DEBUG
  //ekf_aw.offset.y = get_sys_time_usec()-tic_2;
 
};
void ekf_aw_wrapper_fetch(void) {…}
 
// ABI callback that obtains the RPM from a module
static void rpm_cb(uint8_t sender_id __attribute__((unused)), struct act_feedback_t *rpm_message,
                   uint8_t num_act_message)
{
  for (int i = 0; i < num_act_message; i++) {
    // Sanity check that index is valid
    if (rpm_message[i].idx < EKF_AW_RPM_HOVER_NUM) {
      // Assign rpm to right actuator
      switch (rpm_message[i].idx) {
        case 0:
          ekf_aw.last_RPM_hover[0] = rpm_message[i].rpm;
          break;
        case 1:
          ekf_aw.last_RPM_hover[1] = rpm_message[i].rpm;
          break;
        case 2:
          ekf_aw.last_RPM_hover[2] = rpm_message[i].rpm;
          break;
        case 3:
          ekf_aw.last_RPM_hover[3] = rpm_message[i].rpm;
          break;
        case 4:
          ekf_aw.last_RPM_pusher = rpm_message[i].rpm;
          break;
        default:
          break;
      }
    }
    time_of_rpm = get_sys_time_float();
  }
};
static void rpm_cb(uint8_t sender_id __attribute__((unused)), struct act_feedback_t *rpm_message, {…}
 
// Set vehicle landed status data
void set_in_air_status(bool in_air)
{
  if (!in_air) {
    ekf_aw.time_last_on_gnd = ekf_aw.internal_clock;
 
  } else {
    ekf_aw.time_last_in_air = ekf_aw.internal_clock;
  }
  ekf_aw.in_air = in_air;
}
void set_in_air_status(bool in_air) {…}
 
/*
For this debug config:
 
To start the filter manually
-"Start" dlsetting can be used to put filter on
 
To send random values in the filter:
- Set define EKF_AW_WRAPPER_RANDOM_INPUTS in ekf_aw_wrapper.c to true
 
To check filter timing:
- time required to run different parts of filter sent on telementry  AIRSPEED_WIND_ESTIMATOR_EKF_FORCES, on different fields, if EKF_AW_DEBUG set to TRUE
 
*/