int EKFINS::get_euler(float *euler)
{
Quaternion2RPY(&x[0], euler);
return 0;
}
/**
* @brief Quickly initialize INS assuming stationary and gravity is down
*
* Currently this is done iteratively but I'm sure it can be directly computed
* when I sit down and work it out
*/
void converge_insgps()
{
AHRSCalibrationData calibration;
AHRSCalibrationGet( &calibration );
float pos[3] = { 0, 0, 0 }, vel[3] = {
0, 0, 0
}, BaroAlt = 0, mag[3], accel[3], temp_gyro[3] = {
0, 0, 0
};
INSGPSInit();
INSSetAccelVar( calibration.accel_var );
INSSetGyroBias( temp_gyro ); // set this to zero - crude bias corrected from downsample_data
INSSetGyroVar( calibration.gyro_var );
INSSetMagVar( calibration.mag_var );
float temp_var[3] = { 10, 10, 10 };
INSSetGyroVar( temp_var ); // ignore gyro's
accel[0] = accel_data.filtered.x;
accel[1] = accel_data.filtered.y;
accel[2] = accel_data.filtered.z;
// Iteratively constrain pitch and roll while updating yaw to align magnetic axis.
for( int i = 0; i < 50; i++ ) {
// This should be done directly but I'm too dumb.
float rpy[3];
Quaternion2RPY( Nav.q, rpy );
rpy[1] =
-atan2( accel_data.filtered.x,
accel_data.filtered.z ) * 180 / M_PI;
rpy[0] =
-atan2( accel_data.filtered.y,
accel_data.filtered.z ) * 180 / M_PI;
// Get magnetic readings
#if defined(PIOS_INCLUDE_HMC5843) && defined(PIOS_INCLUDE_I2C)
PIOS_HMC5843_ReadMag( mag_data.raw.axis );
#endif
mag[0] = -mag_data.raw.axis[1];
mag[1] = -mag_data.raw.axis[0];
mag[2] = -mag_data.raw.axis[2];
RPY2Quaternion( rpy, Nav.q );
INSStatePrediction( temp_gyro, accel, 1 / ( float )EKF_RATE );
INSCovariancePrediction( 1 / ( float )EKF_RATE );
FullCorrection( mag, pos, vel, BaroAlt );
}
INSSetGyroVar( calibration.gyro_var );
}
void updateAttitude(void)
{
updateSensors();
static uint32_t now, last;
float dT;
now = micros();
dT = (float)(now - last) * 1e-6f;
last = now;
AHRSUpdate( stateData.gyro[ROLL], -stateData.gyro[PITCH], stateData.gyro[YAW],
stateData.accel[X], stateData.accel[Y], stateData.accel[Z],
stateData.mag[X], stateData.mag[Y], stateData.mag[Z],
dT);
zeroSensorAccumulators();
Quaternion2RPY(stateData.q, &stateData.roll, &stateData.pitch, &stateData.yaw);
stateData.heading += cfg.magDeclination * DEG2RAD;
}
/**
* Module task
*/
static void stabilizationTask(void* parameters)
{
portTickType lastSysTime;
portTickType thisSysTime;
UAVObjEvent ev;
ActuatorDesiredData actuatorDesired;
StabilizationDesiredData stabDesired;
RateDesiredData rateDesired;
AttitudeActualData attitudeActual;
AttitudeRawData attitudeRaw;
SystemSettingsData systemSettings;
FlightStatusData flightStatus;
SettingsUpdatedCb((UAVObjEvent *) NULL);
// Main task loop
lastSysTime = xTaskGetTickCount();
ZeroPids();
while(1) {
PIOS_WDG_UpdateFlag(PIOS_WDG_STABILIZATION);
// Wait until the AttitudeRaw object is updated, if a timeout then go to failsafe
if ( xQueueReceive(queue, &ev, FAILSAFE_TIMEOUT_MS / portTICK_RATE_MS) != pdTRUE )
{
AlarmsSet(SYSTEMALARMS_ALARM_STABILIZATION,SYSTEMALARMS_ALARM_WARNING);
continue;
}
// Check how long since last update
thisSysTime = xTaskGetTickCount();
if(thisSysTime > lastSysTime) // reuse dt in case of wraparound
dT = (thisSysTime - lastSysTime) / portTICK_RATE_MS / 1000.0f;
lastSysTime = thisSysTime;
FlightStatusGet(&flightStatus);
StabilizationDesiredGet(&stabDesired);
AttitudeActualGet(&attitudeActual);
AttitudeRawGet(&attitudeRaw);
RateDesiredGet(&rateDesired);
SystemSettingsGet(&systemSettings);
#if defined(PIOS_QUATERNION_STABILIZATION)
// Quaternion calculation of error in each axis. Uses more memory.
float rpy_desired[3];
float q_desired[4];
float q_error[4];
float local_error[3];
// Essentially zero errors for anything in rate or none
if(stabDesired.StabilizationMode[STABILIZATIONDESIRED_STABILIZATIONMODE_ROLL] == STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE)
rpy_desired[0] = stabDesired.Roll;
else
rpy_desired[0] = attitudeActual.Roll;
if(stabDesired.StabilizationMode[STABILIZATIONDESIRED_STABILIZATIONMODE_PITCH] == STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE)
rpy_desired[1] = stabDesired.Pitch;
else
rpy_desired[1] = attitudeActual.Pitch;
if(stabDesired.StabilizationMode[STABILIZATIONDESIRED_STABILIZATIONMODE_YAW] == STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE)
rpy_desired[2] = stabDesired.Yaw;
else
rpy_desired[2] = attitudeActual.Yaw;
RPY2Quaternion(rpy_desired, q_desired);
quat_inverse(q_desired);
quat_mult(q_desired, &attitudeActual.q1, q_error);
quat_inverse(q_error);
Quaternion2RPY(q_error, local_error);
#else
// Simpler algorithm for CC, less memory
float local_error[3] = {stabDesired.Roll - attitudeActual.Roll,
stabDesired.Pitch - attitudeActual.Pitch,
stabDesired.Yaw - attitudeActual.Yaw};
local_error[2] = fmod(local_error[2] + 180, 360) - 180;
#endif
for(uint8_t i = 0; i < MAX_AXES; i++) {
gyro_filtered[i] = gyro_filtered[i] * gyro_alpha + attitudeRaw.gyros[i] * (1 - gyro_alpha);
}
float *attitudeDesiredAxis = &stabDesired.Roll;
float *actuatorDesiredAxis = &actuatorDesired.Roll;
float *rateDesiredAxis = &rateDesired.Roll;
//Calculate desired rate
for(uint8_t i=0; i< MAX_AXES; i++)
{
switch(stabDesired.StabilizationMode[i])
{
case STABILIZATIONDESIRED_STABILIZATIONMODE_RATE:
rateDesiredAxis[i] = attitudeDesiredAxis[i];
axis_lock_accum[i] = 0;
break;
case STABILIZATIONDESIRED_STABILIZATIONMODE_WEAKLEVELING:
{
float weak_leveling = local_error[i] * weak_leveling_kp;
if(weak_leveling > weak_leveling_max)
weak_leveling = weak_leveling_max;
if(weak_leveling < -weak_leveling_max)
weak_leveling = -weak_leveling_max;
rateDesiredAxis[i] = attitudeDesiredAxis[i] + weak_leveling;
axis_lock_accum[i] = 0;
break;
}
case STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE:
rateDesiredAxis[i] = ApplyPid(&pids[PID_ROLL + i], local_error[i]);
axis_lock_accum[i] = 0;
break;
case STABILIZATIONDESIRED_STABILIZATIONMODE_AXISLOCK:
if(fabs(attitudeDesiredAxis[i]) > max_axislock_rate) {
// While getting strong commands act like rate mode
rateDesiredAxis[i] = attitudeDesiredAxis[i];
axis_lock_accum[i] = 0;
} else {
// For weaker commands or no command simply attitude lock (almost) on no gyro change
axis_lock_accum[i] += (attitudeDesiredAxis[i] - gyro_filtered[i]) * dT;
if(axis_lock_accum[i] > max_axis_lock)
axis_lock_accum[i] = max_axis_lock;
else if(axis_lock_accum[i] < -max_axis_lock)
axis_lock_accum[i] = -max_axis_lock;
rateDesiredAxis[i] = ApplyPid(&pids[PID_ROLL + i], axis_lock_accum[i]);
}
break;
}
}
uint8_t shouldUpdate = 1;
RateDesiredSet(&rateDesired);
ActuatorDesiredGet(&actuatorDesired);
//Calculate desired command
for(int8_t ct=0; ct< MAX_AXES; ct++)
{
if(rateDesiredAxis[ct] > settings.MaximumRate[ct])
rateDesiredAxis[ct] = settings.MaximumRate[ct];
else if(rateDesiredAxis[ct] < -settings.MaximumRate[ct])
rateDesiredAxis[ct] = -settings.MaximumRate[ct];
switch(stabDesired.StabilizationMode[ct])
{
case STABILIZATIONDESIRED_STABILIZATIONMODE_RATE:
case STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE:
case STABILIZATIONDESIRED_STABILIZATIONMODE_AXISLOCK:
case STABILIZATIONDESIRED_STABILIZATIONMODE_WEAKLEVELING:
{
float command = ApplyPid(&pids[PID_RATE_ROLL + ct], rateDesiredAxis[ct] - gyro_filtered[ct]);
actuatorDesiredAxis[ct] = bound(command);
break;
}
case STABILIZATIONDESIRED_STABILIZATIONMODE_NONE:
switch (ct)
{
case ROLL:
actuatorDesiredAxis[ct] = bound(attitudeDesiredAxis[ct]);
shouldUpdate = 1;
break;
case PITCH:
actuatorDesiredAxis[ct] = bound(attitudeDesiredAxis[ct]);
shouldUpdate = 1;
break;
case YAW:
actuatorDesiredAxis[ct] = bound(attitudeDesiredAxis[ct]);
shouldUpdate = 1;
break;
}
break;
}
}
// Save dT
actuatorDesired.UpdateTime = dT * 1000;
if(PARSE_FLIGHT_MODE(flightStatus.FlightMode) == FLIGHTMODE_MANUAL)
shouldUpdate = 0;
if(shouldUpdate)
{
actuatorDesired.Throttle = stabDesired.Throttle;
if(dT > 15)
actuatorDesired.NumLongUpdates++;
ActuatorDesiredSet(&actuatorDesired);
}
if(flightStatus.Armed != FLIGHTSTATUS_ARMED_ARMED ||
(lowThrottleZeroIntegral && stabDesired.Throttle < 0) ||
!shouldUpdate)
{
ZeroPids();
}
// Clear alarms
AlarmsClear(SYSTEMALARMS_ALARM_STABILIZATION);
}
}
/**
* @brief
*/
__attribute__((optimize("O3"))) void attitudeUpdate(PIMUStruct pIMU) {
float accelErr[3] = {0.0f};
float mag;
float dq[4];
pIMU->accelData[0] -= pIMU->accelBias[0];
pIMU->accelData[1] -= pIMU->accelBias[1];
pIMU->accelData[2] -= pIMU->accelBias[2];
// Account for accel's magnitude.
mag = QInvSqrtf(pIMU->accelData[0]*pIMU->accelData[0] + pIMU->accelData[1]*pIMU->accelData[1] + pIMU->accelData[2]*pIMU->accelData[2]);
if ((mag > 0.0724f) && (mag < 0.1724f)) {
float v2[3];
/* Compute estimated direction of gravity halved.
*
* Rotated gravity vector v2 is calculated by multiplying gravity
* vector v={0,0,1} by conjugate (q`) of attitude quaternion (q) (v2=q`vq),
* because MPU6050 senses gravity in opposite direction.
*/
v2[0] = (pIMU->qIMU[1]*pIMU->qIMU[3] - pIMU->qIMU[0]*pIMU->qIMU[2]);
v2[1] = (pIMU->qIMU[2]*pIMU->qIMU[3] + pIMU->qIMU[0]*pIMU->qIMU[1]);
v2[2] = (pIMU->qIMU[0]*pIMU->qIMU[0] + pIMU->qIMU[3]*pIMU->qIMU[3]) - 0.5f;
// Apply smoothing to accel values, to reduce vibration noise before main calculations.
accelFilterApply(pIMU->accelData, pIMU->accelFiltered);
// Apply the same filtering to the estimated direction of gravity to match phase shift.
accelFilterApply(v2, pIMU->v2Filtered);
// Compute the error between the predicted direction of gravity and smoothed acceleration.
CrossProduct(pIMU->accelFiltered, pIMU->v2Filtered, accelErr);
// Normalize accel_error.
accelErr[0] *= mag;
accelErr[1] *= mag;
accelErr[2] *= mag;
}
// Correct rates based on error.
pIMU->gyroBias[0] -= accelErr[0]*accel2Ki;
pIMU->gyroBias[1] -= accelErr[1]*accel2Ki;
pIMU->gyroBias[2] -= accelErr[2]*accel2Ki;
pIMU->gyroData[0] -= pIMU->gyroBias[0];
pIMU->gyroData[1] -= pIMU->gyroBias[1];
pIMU->gyroData[2] -= pIMU->gyroBias[2];
// Correct rates based on error.
pIMU->gyroData[0] += accelErr[0]*accel2Kp;
pIMU->gyroData[1] += accelErr[1]*accel2Kp;
pIMU->gyroData[2] += accelErr[2]*accel2Kp;
dq[0] = (-pIMU->qIMU[1]*pIMU->gyroData[0] - pIMU->qIMU[2]*pIMU->gyroData[1] - pIMU->qIMU[3]*pIMU->gyroData[2])*(FIXED_DT_STEP*DEG2RAD*0.5f);
dq[1] = ( pIMU->qIMU[0]*pIMU->gyroData[0] - pIMU->qIMU[3]*pIMU->gyroData[1] + pIMU->qIMU[2]*pIMU->gyroData[2])*(FIXED_DT_STEP*DEG2RAD*0.5f);
dq[2] = ( pIMU->qIMU[3]*pIMU->gyroData[0] + pIMU->qIMU[0]*pIMU->gyroData[1] - pIMU->qIMU[1]*pIMU->gyroData[2])*(FIXED_DT_STEP*DEG2RAD*0.5f);
dq[3] = (-pIMU->qIMU[2]*pIMU->gyroData[0] + pIMU->qIMU[1]*pIMU->gyroData[1] + pIMU->qIMU[0]*pIMU->gyroData[2])*(FIXED_DT_STEP*DEG2RAD*0.5f);
pIMU->qIMU[0] += dq[0];
pIMU->qIMU[1] += dq[1];
pIMU->qIMU[2] += dq[2];
pIMU->qIMU[3] += dq[3];
// Normalize attitude quaternion.
mag = QInvSqrtf(pIMU->qIMU[0]*pIMU->qIMU[0] + pIMU->qIMU[1]*pIMU->qIMU[1] + pIMU->qIMU[2]*pIMU->qIMU[2] + pIMU->qIMU[3]*pIMU->qIMU[3]);
pIMU->qIMU[0] *= mag;
pIMU->qIMU[1] *= mag;
pIMU->qIMU[2] *= mag;
pIMU->qIMU[3] *= mag;
// Convert attitude into Euler angles;
Quaternion2RPY(pIMU->qIMU, pIMU->rpy);
}
static void updateAttitude(AttitudeRawData * attitudeRaw)
{
AttitudeActualData attitudeActual;
AttitudeActualGet(&attitudeActual);
static portTickType lastSysTime = 0;
static portTickType thisSysTime;
static float dT = 0;
thisSysTime = xTaskGetTickCount();
if(thisSysTime > lastSysTime) // reuse dt in case of wraparound
dT = (thisSysTime - lastSysTime) / portTICK_RATE_MS / 1000.0f;
lastSysTime = thisSysTime;
// Bad practice to assume structure order, but saves memory
float * q = &attitudeActual.q1;
float gyro[3];
gyro[0] = attitudeRaw->gyros[0];
gyro[1] = attitudeRaw->gyros[1];
gyro[2] = attitudeRaw->gyros[2];
{
float * accels = attitudeRaw->accels;
float grot[3];
float accel_err[3];
// Rotate gravity to body frame and cross with accels
grot[0] = -(2 * (q[1] * q[3] - q[0] * q[2]));
grot[1] = -(2 * (q[2] * q[3] + q[0] * q[1]));
grot[2] = -(q[0] * q[0] - q[1]*q[1] - q[2]*q[2] + q[3]*q[3]);
CrossProduct((const float *) accels, (const float *) grot, accel_err);
// Account for accel magnitude
float accel_mag = sqrt(accels[0]*accels[0] + accels[1]*accels[1] + accels[2]*accels[2]);
accel_err[0] /= accel_mag;
accel_err[1] /= accel_mag;
accel_err[2] /= accel_mag;
// Accumulate integral of error. Scale here so that units are (rad/s) but Ki has units of s
gyro_correct_int[0] += accel_err[0] * accelKi;
gyro_correct_int[1] += accel_err[1] * accelKi;
//gyro_correct_int[2] += accel_err[2] * settings.AccelKI * dT;
// Correct rates based on error, integral component dealt with in updateSensors
gyro[0] += accel_err[0] * accelKp / dT;
gyro[1] += accel_err[1] * accelKp / dT;
gyro[2] += accel_err[2] * accelKp / dT;
}
{ // scoping variables to save memory
// Work out time derivative from INSAlgo writeup
// Also accounts for the fact that gyros are in deg/s
float qdot[4];
qdot[0] = (-q[1] * gyro[0] - q[2] * gyro[1] - q[3] * gyro[2]) * dT * M_PI / 180 / 2;
qdot[1] = (q[0] * gyro[0] - q[3] * gyro[1] + q[2] * gyro[2]) * dT * M_PI / 180 / 2;
qdot[2] = (q[3] * gyro[0] + q[0] * gyro[1] - q[1] * gyro[2]) * dT * M_PI / 180 / 2;
qdot[3] = (-q[2] * gyro[0] + q[1] * gyro[1] + q[0] * gyro[2]) * dT * M_PI / 180 / 2;
// Take a time step
q[0] = q[0] + qdot[0];
q[1] = q[1] + qdot[1];
q[2] = q[2] + qdot[2];
q[3] = q[3] + qdot[3];
}
// Renomalize
float qmag = sqrt(q[0]*q[0] + q[1]*q[1] + q[2]*q[2] + q[3]*q[3]);
q[0] = q[0] / qmag;
q[1] = q[1] / qmag;
q[2] = q[2] / qmag;
q[3] = q[3] / qmag;
attitudeActual.q1 = q[0];
attitudeActual.q2 = q[1];
attitudeActual.q3 = q[2];
attitudeActual.q4 = q[3];
// Convert into eueler degrees (makes assumptions about RPY order)
Quaternion2RPY(q,&attitudeActual.Roll);
AttitudeActualSet(&attitudeActual);
}
static void updateAttitude(AttitudeRawData * attitudeRaw)
{
float dT;
portTickType thisSysTime = xTaskGetTickCount();
static portTickType lastSysTime = 0;
dT = (thisSysTime == lastSysTime) ? 0.001 : (portMAX_DELAY & (thisSysTime - lastSysTime)) / portTICK_RATE_MS / 1000.0f;
lastSysTime = thisSysTime;
// Bad practice to assume structure order, but saves memory
float gyro[3];
gyro[0] = attitudeRaw->gyros[0];
gyro[1] = attitudeRaw->gyros[1];
gyro[2] = attitudeRaw->gyros[2];
{
float * accels = attitudeRaw->accels;
float grot[3];
float accel_err[3];
// Rotate gravity to body frame and cross with accels
grot[0] = -(2 * (q[1] * q[3] - q[0] * q[2]));
grot[1] = -(2 * (q[2] * q[3] + q[0] * q[1]));
grot[2] = -(q[0] * q[0] - q[1]*q[1] - q[2]*q[2] + q[3]*q[3]);
CrossProduct((const float *) accels, (const float *) grot, accel_err);
// Account for accel magnitude
float accel_mag = sqrt(accels[0]*accels[0] + accels[1]*accels[1] + accels[2]*accels[2]);
accel_err[0] /= accel_mag;
accel_err[1] /= accel_mag;
accel_err[2] /= accel_mag;
// Accumulate integral of error. Scale here so that units are (deg/s) but Ki has units of s
gyro_correct_int[0] += accel_err[0] * accelKi;
gyro_correct_int[1] += accel_err[1] * accelKi;
//gyro_correct_int[2] += accel_err[2] * settings.AccelKI * dT;
// Correct rates based on error, integral component dealt with in updateSensors
gyro[0] += accel_err[0] * accelKp / dT;
gyro[1] += accel_err[1] * accelKp / dT;
gyro[2] += accel_err[2] * accelKp / dT;
}
{ // scoping variables to save memory
// Work out time derivative from INSAlgo writeup
// Also accounts for the fact that gyros are in deg/s
float qdot[4];
qdot[0] = (-q[1] * gyro[0] - q[2] * gyro[1] - q[3] * gyro[2]) * dT * M_PI / 180 / 2;
qdot[1] = (q[0] * gyro[0] - q[3] * gyro[1] + q[2] * gyro[2]) * dT * M_PI / 180 / 2;
qdot[2] = (q[3] * gyro[0] + q[0] * gyro[1] - q[1] * gyro[2]) * dT * M_PI / 180 / 2;
qdot[3] = (-q[2] * gyro[0] + q[1] * gyro[1] + q[0] * gyro[2]) * dT * M_PI / 180 / 2;
// Take a time step
q[0] = q[0] + qdot[0];
q[1] = q[1] + qdot[1];
q[2] = q[2] + qdot[2];
q[3] = q[3] + qdot[3];
}
// Renomalize
float qmag = sqrt(q[0]*q[0] + q[1]*q[1] + q[2]*q[2] + q[3]*q[3]);
q[0] = q[0] / qmag;
q[1] = q[1] / qmag;
q[2] = q[2] / qmag;
q[3] = q[3] / qmag;
// If quaternion has become inappropriately short or is nan reinit.
// THIS SHOULD NEVER ACTUALLY HAPPEN
if((fabs(qmag) < 1e-3) || (qmag != qmag)) {
q[0] = 1;
q[1] = 0;
q[2] = 0;
q[3] = 0;
}
AttitudeActualData attitudeActual;
AttitudeActualGet(&attitudeActual);
quat_copy(q, &attitudeActual.q1);
// Convert into eueler degrees (makes assumptions about RPY order)
Quaternion2RPY(&attitudeActual.q1,&attitudeActual.Roll);
AttitudeActualSet(&attitudeActual);
}
/**
* This method performs a simple simulation of a car
*
* It takes in the ActuatorDesired command to rotate the aircraft and performs
* a simple kinetic model where the throttle increases the energy and drag decreases
* it. Changing altitude moves energy from kinetic to potential.
*
* 1. Update attitude based on ActuatorDesired
* 2. Update position based on velocity
*/
static void simulateModelCar()
{
static double pos[3] = {0,0,0};
static double vel[3] = {0,0,0};
static double ned_accel[3] = {0,0,0};
static float q[4] = {1,0,0,0};
static float rpy[3] = {0,0,0}; // Low pass filtered actuator
static float baro_offset = 0.0f;
float Rbe[3][3];
const float ACTUATOR_ALPHA = 0.8;
const float MAX_THRUST = 9.81 * 0.5;
const float K_FRICTION = 0.2;
const float GPS_PERIOD = 0.1;
const float MAG_PERIOD = 1.0 / 75.0;
const float BARO_PERIOD = 1.0 / 20.0;
static uint32_t last_time;
float dT = (PIOS_DELAY_DiffuS(last_time) / 1e6);
if(dT < 1e-3)
dT = 2e-3;
last_time = PIOS_DELAY_GetRaw();
FlightStatusData flightStatus;
FlightStatusGet(&flightStatus);
ActuatorDesiredData actuatorDesired;
ActuatorDesiredGet(&actuatorDesired);
float thrust = (flightStatus.Armed == FLIGHTSTATUS_ARMED_ARMED) ? actuatorDesired.Throttle * MAX_THRUST : 0;
if (thrust < 0)
thrust = 0;
if (thrust != thrust)
thrust = 0;
// float control_scaling = thrust * thrustToDegs;
// // In rad/s
// rpy[0] = control_scaling * actuatorDesired.Roll * (1 - ACTUATOR_ALPHA) + rpy[0] * ACTUATOR_ALPHA;
// rpy[1] = control_scaling * actuatorDesired.Pitch * (1 - ACTUATOR_ALPHA) + rpy[1] * ACTUATOR_ALPHA;
// rpy[2] = control_scaling * actuatorDesired.Yaw * (1 - ACTUATOR_ALPHA) + rpy[2] * ACTUATOR_ALPHA;
//
// GyrosData gyrosData; // Skip get as we set all the fields
// gyrosData.x = rpy[0] * 180 / M_PI + rand_gauss();
// gyrosData.y = rpy[1] * 180 / M_PI + rand_gauss();
// gyrosData.z = rpy[2] * 180 / M_PI + rand_gauss();
/**** 1. Update attitude ****/
RateDesiredData rateDesired;
RateDesiredGet(&rateDesired);
// Need to get roll angle for easy cross coupling
AttitudeActualData attitudeActual;
AttitudeActualGet(&attitudeActual);
rpy[0] = 0; // cannot roll
rpy[1] = 0; // cannot pitch
rpy[2] = (flightStatus.Armed == FLIGHTSTATUS_ARMED_ARMED) * rateDesired.Yaw * (1 - ACTUATOR_ALPHA) + rpy[2] * ACTUATOR_ALPHA;
GyrosData gyrosData; // Skip get as we set all the fields
gyrosData.x = rpy[0] + rand_gauss();
gyrosData.y = rpy[1] + rand_gauss();
gyrosData.z = rpy[2] + rand_gauss();
GyrosSet(&gyrosData);
// Predict the attitude forward in time
float qdot[4];
qdot[0] = (-q[1] * rpy[0] - q[2] * rpy[1] - q[3] * rpy[2]) * dT * DEG2RAD / 2;
qdot[1] = (q[0] * rpy[0] - q[3] * rpy[1] + q[2] * rpy[2]) * dT * DEG2RAD / 2;
qdot[2] = (q[3] * rpy[0] + q[0] * rpy[1] - q[1] * rpy[2]) * dT * DEG2RAD / 2;
qdot[3] = (-q[2] * rpy[0] + q[1] * rpy[1] + q[0] * rpy[2]) * dT * DEG2RAD / 2;
// Take a time step
q[0] = q[0] + qdot[0];
q[1] = q[1] + qdot[1];
q[2] = q[2] + qdot[2];
q[3] = q[3] + qdot[3];
float qmag = sqrtf(q[0]*q[0] + q[1]*q[1] + q[2]*q[2] + q[3]*q[3]);
q[0] = q[0] / qmag;
q[1] = q[1] / qmag;
q[2] = q[2] / qmag;
q[3] = q[3] / qmag;
if(overideAttitude){
AttitudeActualData attitudeActual;
AttitudeActualGet(&attitudeActual);
attitudeActual.q1 = q[0];
attitudeActual.q2 = q[1];
attitudeActual.q3 = q[2];
attitudeActual.q4 = q[3];
AttitudeActualSet(&attitudeActual);
}
/**** 2. Update position based on velocity ****/
// Rbe takes a vector from body to earth. If we take (1,0,0)^T through this and then dot with airspeed
// we get forward airspeed
Quaternion2R(q,Rbe);
double groundspeed[3] = {vel[0], vel[1], vel[2] };
double forwardSpeed = Rbe[0][0] * groundspeed[0] + Rbe[0][1] * groundspeed[1] + Rbe[0][2] * groundspeed[2];
double sidewaysSpeed = Rbe[1][0] * groundspeed[0] + Rbe[1][1] * groundspeed[1] + Rbe[1][2] * groundspeed[2];
/* Compute aerodynamic forces in body referenced frame. Later use more sophisticated equations */
/* TODO: This should become more accurate. Use the force equations to calculate lift from the */
/* various surfaces based on AoA and airspeed. From that compute torques and forces. For later */
double forces[3]; // X, Y, Z
forces[0] = thrust - forwardSpeed * K_FRICTION; // Friction is applied in all directions in NED
forces[1] = 0 - sidewaysSpeed * K_FRICTION * 100; // No side slip
forces[2] = 0;
// Negate force[2] as NED defines down as possitive, aircraft convention is Z up is positive (?)
ned_accel[0] = forces[0] * Rbe[0][0] + forces[1] * Rbe[1][0] - forces[2] * Rbe[2][0];
ned_accel[1] = forces[0] * Rbe[0][1] + forces[1] * Rbe[1][1] - forces[2] * Rbe[2][1];
ned_accel[2] = 0;
// Apply acceleration based on velocity
ned_accel[0] -= K_FRICTION * (vel[0]);
ned_accel[1] -= K_FRICTION * (vel[1]);
// Predict the velocity forward in time
vel[0] = vel[0] + ned_accel[0] * dT;
vel[1] = vel[1] + ned_accel[1] * dT;
vel[2] = vel[2] + ned_accel[2] * dT;
// Predict the position forward in time
pos[0] = pos[0] + vel[0] * dT;
pos[1] = pos[1] + vel[1] * dT;
pos[2] = pos[2] + vel[2] * dT;
// Simulate hitting ground
if(pos[2] > 0) {
pos[2] = 0;
vel[2] = 0;
ned_accel[2] = 0;
}
// Sensor feels gravity (when not acceleration in ned frame e.g. ned_accel[2] = 0)
ned_accel[2] -= GRAVITY;
// Transform the accels back in to body frame
AccelsData accelsData; // Skip get as we set all the fields
accelsData.x = ned_accel[0] * Rbe[0][0] + ned_accel[1] * Rbe[0][1] + ned_accel[2] * Rbe[0][2] + accel_bias[0];
accelsData.y = ned_accel[0] * Rbe[1][0] + ned_accel[1] * Rbe[1][1] + ned_accel[2] * Rbe[1][2] + accel_bias[1];
accelsData.z = ned_accel[0] * Rbe[2][0] + ned_accel[1] * Rbe[2][1] + ned_accel[2] * Rbe[2][2] + accel_bias[2];
accelsData.temperature = 30;
AccelsSet(&accelsData);
if(baro_offset == 0) {
// Hacky initialization
baro_offset = 50;// * rand_gauss();
} else {
// Very small drift process
baro_offset += rand_gauss() / 100;
}
// Update baro periodically
static uint32_t last_baro_time = 0;
if(PIOS_DELAY_DiffuS(last_baro_time) / 1.0e6 > BARO_PERIOD) {
BaroAltitudeData baroAltitude;
BaroAltitudeGet(&baroAltitude);
baroAltitude.Altitude = -pos[2] + baro_offset;
BaroAltitudeSet(&baroAltitude);
last_baro_time = PIOS_DELAY_GetRaw();
}
HomeLocationData homeLocation;
HomeLocationGet(&homeLocation);
static float gps_vel_drift[3] = {0,0,0};
gps_vel_drift[0] = gps_vel_drift[0] * 0.65 + rand_gauss() / 5.0;
gps_vel_drift[1] = gps_vel_drift[1] * 0.65 + rand_gauss() / 5.0;
gps_vel_drift[2] = gps_vel_drift[2] * 0.65 + rand_gauss() / 5.0;
// Update GPS periodically
static uint32_t last_gps_time = 0;
if(PIOS_DELAY_DiffuS(last_gps_time) / 1.0e6 > GPS_PERIOD) {
// Use double precision here as simulating what GPS produces
double T[3];
T[0] = homeLocation.Altitude+6.378137E6f * DEG2RAD;
T[1] = cosf(homeLocation.Latitude / 10e6 * DEG2RAD)*(homeLocation.Altitude+6.378137E6) * DEG2RAD;
T[2] = -1.0;
static float gps_drift[3] = {0,0,0};
gps_drift[0] = gps_drift[0] * 0.95 + rand_gauss() / 10.0;
gps_drift[1] = gps_drift[1] * 0.95 + rand_gauss() / 10.0;
gps_drift[2] = gps_drift[2] * 0.95 + rand_gauss() / 10.0;
GPSPositionData gpsPosition;
GPSPositionGet(&gpsPosition);
gpsPosition.Latitude = homeLocation.Latitude + ((pos[0] + gps_drift[0]) / T[0] * 10.0e6);
gpsPosition.Longitude = homeLocation.Longitude + ((pos[1] + gps_drift[1])/ T[1] * 10.0e6);
gpsPosition.Altitude = homeLocation.Altitude + ((pos[2] + gps_drift[2]) / T[2]);
gpsPosition.Groundspeed = sqrtf(pow(vel[0] + gps_vel_drift[0],2) + pow(vel[1] + gps_vel_drift[1],2));
gpsPosition.Heading = 180 / M_PI * atan2f(vel[1] + gps_vel_drift[1],vel[0] + gps_vel_drift[0]);
gpsPosition.Satellites = 7;
gpsPosition.PDOP = 1;
GPSPositionSet(&gpsPosition);
last_gps_time = PIOS_DELAY_GetRaw();
}
// Update GPS Velocity measurements
static uint32_t last_gps_vel_time = 1000; // Delay by a millisecond
if(PIOS_DELAY_DiffuS(last_gps_vel_time) / 1.0e6 > GPS_PERIOD) {
GPSVelocityData gpsVelocity;
GPSVelocityGet(&gpsVelocity);
gpsVelocity.North = vel[0] + gps_vel_drift[0];
gpsVelocity.East = vel[1] + gps_vel_drift[1];
gpsVelocity.Down = vel[2] + gps_vel_drift[2];
GPSVelocitySet(&gpsVelocity);
last_gps_vel_time = PIOS_DELAY_GetRaw();
}
// Update mag periodically
static uint32_t last_mag_time = 0;
if(PIOS_DELAY_DiffuS(last_mag_time) / 1.0e6 > MAG_PERIOD) {
MagnetometerData mag;
mag.x = 100+homeLocation.Be[0] * Rbe[0][0] + homeLocation.Be[1] * Rbe[0][1] + homeLocation.Be[2] * Rbe[0][2];
mag.y = 100+homeLocation.Be[0] * Rbe[1][0] + homeLocation.Be[1] * Rbe[1][1] + homeLocation.Be[2] * Rbe[1][2];
mag.z = 100+homeLocation.Be[0] * Rbe[2][0] + homeLocation.Be[1] * Rbe[2][1] + homeLocation.Be[2] * Rbe[2][2];
magOffsetEstimation(&mag);
MagnetometerSet(&mag);
last_mag_time = PIOS_DELAY_GetRaw();
}
AttitudeSimulatedData attitudeSimulated;
AttitudeSimulatedGet(&attitudeSimulated);
attitudeSimulated.q1 = q[0];
attitudeSimulated.q2 = q[1];
attitudeSimulated.q3 = q[2];
attitudeSimulated.q4 = q[3];
Quaternion2RPY(q,&attitudeSimulated.Roll);
attitudeSimulated.Position[0] = pos[0];
attitudeSimulated.Position[1] = pos[1];
attitudeSimulated.Position[2] = pos[2];
attitudeSimulated.Velocity[0] = vel[0];
attitudeSimulated.Velocity[1] = vel[1];
attitudeSimulated.Velocity[2] = vel[2];
AttitudeSimulatedSet(&attitudeSimulated);
}
static void simulateModelQuadcopter()
{
static double pos[3] = {0,0,0};
static double vel[3] = {0,0,0};
static double ned_accel[3] = {0,0,0};
static float q[4] = {1,0,0,0};
static float rpy[3] = {0,0,0}; // Low pass filtered actuator
static float baro_offset = 0.0f;
static float temperature = 20;
float Rbe[3][3];
const float ACTUATOR_ALPHA = 0.8;
const float MAX_THRUST = GRAVITY * 2;
const float K_FRICTION = 1;
const float GPS_PERIOD = 0.1;
const float MAG_PERIOD = 1.0 / 75.0;
const float BARO_PERIOD = 1.0 / 20.0;
static uint32_t last_time;
float dT = (PIOS_DELAY_DiffuS(last_time) / 1e6);
if(dT < 1e-3)
dT = 2e-3;
last_time = PIOS_DELAY_GetRaw();
FlightStatusData flightStatus;
FlightStatusGet(&flightStatus);
ActuatorDesiredData actuatorDesired;
ActuatorDesiredGet(&actuatorDesired);
float thrust = (flightStatus.Armed == FLIGHTSTATUS_ARMED_ARMED) ? actuatorDesired.Throttle * MAX_THRUST : 0;
if (thrust < 0)
thrust = 0;
if (thrust != thrust)
thrust = 0;
// float control_scaling = thrust * thrustToDegs;
// // In rad/s
// rpy[0] = control_scaling * actuatorDesired.Roll * (1 - ACTUATOR_ALPHA) + rpy[0] * ACTUATOR_ALPHA;
// rpy[1] = control_scaling * actuatorDesired.Pitch * (1 - ACTUATOR_ALPHA) + rpy[1] * ACTUATOR_ALPHA;
// rpy[2] = control_scaling * actuatorDesired.Yaw * (1 - ACTUATOR_ALPHA) + rpy[2] * ACTUATOR_ALPHA;
//
// GyrosData gyrosData; // Skip get as we set all the fields
// gyrosData.x = rpy[0] * 180 / M_PI + rand_gauss();
// gyrosData.y = rpy[1] * 180 / M_PI + rand_gauss();
// gyrosData.z = rpy[2] * 180 / M_PI + rand_gauss();
RateDesiredData rateDesired;
RateDesiredGet(&rateDesired);
rpy[0] = (flightStatus.Armed == FLIGHTSTATUS_ARMED_ARMED) * rateDesired.Roll * (1 - ACTUATOR_ALPHA) + rpy[0] * ACTUATOR_ALPHA;
rpy[1] = (flightStatus.Armed == FLIGHTSTATUS_ARMED_ARMED) * rateDesired.Pitch * (1 - ACTUATOR_ALPHA) + rpy[1] * ACTUATOR_ALPHA;
rpy[2] = (flightStatus.Armed == FLIGHTSTATUS_ARMED_ARMED) * rateDesired.Yaw * (1 - ACTUATOR_ALPHA) + rpy[2] * ACTUATOR_ALPHA;
temperature = 20;
GyrosData gyrosData; // Skip get as we set all the fields
gyrosData.x = rpy[0] + rand_gauss() + (temperature - 20) * 1 + powf(temperature - 20,2) * 0.11; // - powf(temperature - 20,3) * 0.05;;
gyrosData.y = rpy[1] + rand_gauss() + (temperature - 20) * 1 + powf(temperature - 20,2) * 0.11;;
gyrosData.z = rpy[2] + rand_gauss() + (temperature - 20) * 1 + powf(temperature - 20,2) * 0.11;;
gyrosData.temperature = temperature;
GyrosSet(&gyrosData);
// Predict the attitude forward in time
float qdot[4];
qdot[0] = (-q[1] * rpy[0] - q[2] * rpy[1] - q[3] * rpy[2]) * dT * DEG2RAD / 2;
qdot[1] = (q[0] * rpy[0] - q[3] * rpy[1] + q[2] * rpy[2]) * dT * DEG2RAD / 2;
qdot[2] = (q[3] * rpy[0] + q[0] * rpy[1] - q[1] * rpy[2]) * dT * DEG2RAD / 2;
qdot[3] = (-q[2] * rpy[0] + q[1] * rpy[1] + q[0] * rpy[2]) * dT * DEG2RAD / 2;
// Take a time step
q[0] = q[0] + qdot[0];
q[1] = q[1] + qdot[1];
q[2] = q[2] + qdot[2];
q[3] = q[3] + qdot[3];
float qmag = sqrtf(q[0]*q[0] + q[1]*q[1] + q[2]*q[2] + q[3]*q[3]);
q[0] = q[0] / qmag;
q[1] = q[1] / qmag;
q[2] = q[2] / qmag;
q[3] = q[3] / qmag;
if(overideAttitude){
AttitudeActualData attitudeActual;
AttitudeActualGet(&attitudeActual);
attitudeActual.q1 = q[0];
attitudeActual.q2 = q[1];
attitudeActual.q3 = q[2];
attitudeActual.q4 = q[3];
AttitudeActualSet(&attitudeActual);
}
static float wind[3] = {0,0,0};
wind[0] = wind[0] * 0.95 + rand_gauss() / 10.0;
wind[1] = wind[1] * 0.95 + rand_gauss() / 10.0;
wind[2] = wind[2] * 0.95 + rand_gauss() / 10.0;
Quaternion2R(q,Rbe);
// Make thrust negative as down is positive
ned_accel[0] = -thrust * Rbe[2][0];
ned_accel[1] = -thrust * Rbe[2][1];
// Gravity causes acceleration of 9.81 in the down direction
ned_accel[2] = -thrust * Rbe[2][2] + GRAVITY;
// Apply acceleration based on velocity
ned_accel[0] -= K_FRICTION * (vel[0] - wind[0]);
ned_accel[1] -= K_FRICTION * (vel[1] - wind[1]);
ned_accel[2] -= K_FRICTION * (vel[2] - wind[2]);
// Predict the velocity forward in time
vel[0] = vel[0] + ned_accel[0] * dT;
vel[1] = vel[1] + ned_accel[1] * dT;
vel[2] = vel[2] + ned_accel[2] * dT;
// Predict the position forward in time
pos[0] = pos[0] + vel[0] * dT;
pos[1] = pos[1] + vel[1] * dT;
pos[2] = pos[2] + vel[2] * dT;
// Simulate hitting ground
if(pos[2] > 0) {
pos[2] = 0;
vel[2] = 0;
ned_accel[2] = 0;
}
// Sensor feels gravity (when not acceleration in ned frame e.g. ned_accel[2] = 0)
ned_accel[2] -= 9.81;
// Transform the accels back in to body frame
AccelsData accelsData; // Skip get as we set all the fields
accelsData.x = ned_accel[0] * Rbe[0][0] + ned_accel[1] * Rbe[0][1] + ned_accel[2] * Rbe[0][2] + accel_bias[0];
accelsData.y = ned_accel[0] * Rbe[1][0] + ned_accel[1] * Rbe[1][1] + ned_accel[2] * Rbe[1][2] + accel_bias[1];
accelsData.z = ned_accel[0] * Rbe[2][0] + ned_accel[1] * Rbe[2][1] + ned_accel[2] * Rbe[2][2] + accel_bias[2];
accelsData.temperature = 30;
AccelsSet(&accelsData);
if(baro_offset == 0) {
// Hacky initialization
baro_offset = 50;// * rand_gauss();
} else {
// Very small drift process
baro_offset += rand_gauss() / 100;
}
// Update baro periodically
static uint32_t last_baro_time = 0;
if(PIOS_DELAY_DiffuS(last_baro_time) / 1.0e6 > BARO_PERIOD) {
BaroAltitudeData baroAltitude;
BaroAltitudeGet(&baroAltitude);
baroAltitude.Altitude = -pos[2] + baro_offset;
BaroAltitudeSet(&baroAltitude);
last_baro_time = PIOS_DELAY_GetRaw();
}
HomeLocationData homeLocation;
HomeLocationGet(&homeLocation);
static float gps_vel_drift[3] = {0,0,0};
gps_vel_drift[0] = gps_vel_drift[0] * 0.65 + rand_gauss() / 5.0;
gps_vel_drift[1] = gps_vel_drift[1] * 0.65 + rand_gauss() / 5.0;
gps_vel_drift[2] = gps_vel_drift[2] * 0.65 + rand_gauss() / 5.0;
// Update GPS periodically
static uint32_t last_gps_time = 0;
if(PIOS_DELAY_DiffuS(last_gps_time) / 1.0e6 > GPS_PERIOD) {
// Use double precision here as simulating what GPS produces
double T[3];
T[0] = homeLocation.Altitude+6.378137E6f * DEG2RAD;
T[1] = cosf(homeLocation.Latitude / 10e6 * DEG2RAD)*(homeLocation.Altitude+6.378137E6) * DEG2RAD;
T[2] = -1.0;
static float gps_drift[3] = {0,0,0};
gps_drift[0] = gps_drift[0] * 0.95 + rand_gauss() / 10.0;
gps_drift[1] = gps_drift[1] * 0.95 + rand_gauss() / 10.0;
gps_drift[2] = gps_drift[2] * 0.95 + rand_gauss() / 10.0;
GPSPositionData gpsPosition;
GPSPositionGet(&gpsPosition);
gpsPosition.Latitude = homeLocation.Latitude + ((pos[0] + gps_drift[0]) / T[0] * 10.0e6);
gpsPosition.Longitude = homeLocation.Longitude + ((pos[1] + gps_drift[1])/ T[1] * 10.0e6);
gpsPosition.Altitude = homeLocation.Altitude + ((pos[2] + gps_drift[2]) / T[2]);
gpsPosition.Groundspeed = sqrtf(pow(vel[0] + gps_vel_drift[0],2) + pow(vel[1] + gps_vel_drift[1],2));
gpsPosition.Heading = 180 / M_PI * atan2f(vel[1] + gps_vel_drift[1],vel[0] + gps_vel_drift[0]);
gpsPosition.Satellites = 7;
gpsPosition.PDOP = 1;
gpsPosition.Status = GPSPOSITION_STATUS_FIX3D;
GPSPositionSet(&gpsPosition);
last_gps_time = PIOS_DELAY_GetRaw();
}
// Update GPS Velocity measurements
static uint32_t last_gps_vel_time = 1000; // Delay by a millisecond
if(PIOS_DELAY_DiffuS(last_gps_vel_time) / 1.0e6 > GPS_PERIOD) {
GPSVelocityData gpsVelocity;
GPSVelocityGet(&gpsVelocity);
gpsVelocity.North = vel[0] + gps_vel_drift[0];
gpsVelocity.East = vel[1] + gps_vel_drift[1];
gpsVelocity.Down = vel[2] + gps_vel_drift[2];
GPSVelocitySet(&gpsVelocity);
last_gps_vel_time = PIOS_DELAY_GetRaw();
}
// Update mag periodically
static uint32_t last_mag_time = 0;
if(PIOS_DELAY_DiffuS(last_mag_time) / 1.0e6 > MAG_PERIOD) {
MagnetometerData mag;
mag.x = homeLocation.Be[0] * Rbe[0][0] + homeLocation.Be[1] * Rbe[0][1] + homeLocation.Be[2] * Rbe[0][2];
mag.y = homeLocation.Be[0] * Rbe[1][0] + homeLocation.Be[1] * Rbe[1][1] + homeLocation.Be[2] * Rbe[1][2];
mag.z = homeLocation.Be[0] * Rbe[2][0] + homeLocation.Be[1] * Rbe[2][1] + homeLocation.Be[2] * Rbe[2][2];
// Run the offset compensation algorithm from the firmware
magOffsetEstimation(&mag);
MagnetometerSet(&mag);
last_mag_time = PIOS_DELAY_GetRaw();
}
AttitudeSimulatedData attitudeSimulated;
AttitudeSimulatedGet(&attitudeSimulated);
attitudeSimulated.q1 = q[0];
attitudeSimulated.q2 = q[1];
attitudeSimulated.q3 = q[2];
attitudeSimulated.q4 = q[3];
Quaternion2RPY(q,&attitudeSimulated.Roll);
attitudeSimulated.Position[0] = pos[0];
attitudeSimulated.Position[1] = pos[1];
attitudeSimulated.Position[2] = pos[2];
attitudeSimulated.Velocity[0] = vel[0];
attitudeSimulated.Velocity[1] = vel[1];
attitudeSimulated.Velocity[2] = vel[2];
AttitudeSimulatedSet(&attitudeSimulated);
}
/**
* @brief Use the INSGPS fusion algorithm in either indoor or outdoor mode (use GPS)
* @params[in] first_run This is the first run so trigger reinitialization
* @params[in] outdoor_mode If true use the GPS for position, if false weakly pull to (0,0)
* @return 0 for success, -1 for failure
*/
static int32_t updateAttitudeINSGPS(bool first_run, bool outdoor_mode)
{
UAVObjEvent ev;
GyrosData gyrosData;
AccelsData accelsData;
MagnetometerData magData;
BaroAltitudeData baroData;
GPSPositionData gpsData;
GPSVelocityData gpsVelData;
GyrosBiasData gyrosBias;
static bool mag_updated = false;
static bool baro_updated;
static bool gps_updated;
static bool gps_vel_updated;
static float baroOffset = 0;
static uint32_t ins_last_time = 0;
static bool inited;
float NED[3] = {0.0f, 0.0f, 0.0f};
float vel[3] = {0.0f, 0.0f, 0.0f};
float zeros[3] = {0.0f, 0.0f, 0.0f};
// Perform the update
uint16_t sensors = 0;
float dT;
// Wait until the gyro and accel object is updated, if a timeout then go to failsafe
if ( (xQueueReceive(gyroQueue, &ev, FAILSAFE_TIMEOUT_MS / portTICK_RATE_MS) != pdTRUE) ||
(xQueueReceive(accelQueue, &ev, 1 / portTICK_RATE_MS) != pdTRUE) )
{
// Do not set attitude timeout warnings in simulation mode
if (!AttitudeActualReadOnly()){
AlarmsSet(SYSTEMALARMS_ALARM_ATTITUDE,SYSTEMALARMS_ALARM_WARNING);
return -1;
}
}
if (inited) {
mag_updated = 0;
baro_updated = 0;
gps_updated = 0;
gps_vel_updated = 0;
}
if (first_run) {
inited = false;
init_stage = 0;
mag_updated = 0;
baro_updated = 0;
gps_updated = 0;
gps_vel_updated = 0;
ins_last_time = PIOS_DELAY_GetRaw();
return 0;
}
mag_updated |= (xQueueReceive(magQueue, &ev, 0 / portTICK_RATE_MS) == pdTRUE);
baro_updated |= xQueueReceive(baroQueue, &ev, 0 / portTICK_RATE_MS) == pdTRUE;
gps_updated |= (xQueueReceive(gpsQueue, &ev, 0 / portTICK_RATE_MS) == pdTRUE) && outdoor_mode;
gps_vel_updated |= (xQueueReceive(gpsVelQueue, &ev, 0 / portTICK_RATE_MS) == pdTRUE) && outdoor_mode;
// Get most recent data
GyrosGet(&gyrosData);
AccelsGet(&accelsData);
MagnetometerGet(&magData);
BaroAltitudeGet(&baroData);
GPSPositionGet(&gpsData);
GPSVelocityGet(&gpsVelData);
GyrosBiasGet(&gyrosBias);
// Discard mag if it has NAN (normally from bad calibration)
mag_updated &= (magData.x == magData.x && magData.y == magData.y && magData.z == magData.z);
// Don't require HomeLocation.Set to be true but at least require a mag configuration (allows easily
// switching between indoor and outdoor mode with Set = false)
mag_updated &= (homeLocation.Be[0] != 0 || homeLocation.Be[1] != 0 || homeLocation.Be[2]);
// Have a minimum requirement for gps usage
gps_updated &= (gpsData.Satellites >= 7) && (gpsData.PDOP <= 4.0f) && (homeLocation.Set == HOMELOCATION_SET_TRUE);
if (!inited)
AlarmsSet(SYSTEMALARMS_ALARM_ATTITUDE,SYSTEMALARMS_ALARM_ERROR);
else if (outdoor_mode && gpsData.Satellites < 7)
AlarmsSet(SYSTEMALARMS_ALARM_ATTITUDE,SYSTEMALARMS_ALARM_ERROR);
else
AlarmsClear(SYSTEMALARMS_ALARM_ATTITUDE);
if (!inited && mag_updated && baro_updated && (gps_updated || !outdoor_mode)) {
// Don't initialize until all sensors are read
if (init_stage == 0 && !outdoor_mode) {
float Pdiag[16]={25.0f,25.0f,25.0f,5.0f,5.0f,5.0f,1e-5f,1e-5f,1e-5f,1e-5f,1e-5f,1e-5f,1e-5f,1e-4f,1e-4f,1e-4f};
float q[4];
float pos[3] = {0.0f, 0.0f, 0.0f};
// Initialize barometric offset to homelocation altitude
baroOffset = -baroData.Altitude;
pos[2] = -(baroData.Altitude + baroOffset);
// Reset the INS algorithm
INSGPSInit();
INSSetMagVar(revoCalibration.mag_var);
INSSetAccelVar(revoCalibration.accel_var);
INSSetGyroVar(revoCalibration.gyro_var);
INSSetBaroVar(revoCalibration.baro_var);
// Initialize the gyro bias from the settings
float gyro_bias[3] = {gyrosBias.x * F_PI / 180.0f, gyrosBias.y * F_PI / 180.0f, gyrosBias.z * F_PI / 180.0f};
INSSetGyroBias(gyro_bias);
xQueueReceive(magQueue, &ev, 100 / portTICK_RATE_MS);
MagnetometerGet(&magData);
// Set initial attitude
AttitudeActualData attitudeActual;
attitudeActual.Roll = atan2f(-accelsData.y, -accelsData.z) * 180.0f / F_PI;
attitudeActual.Pitch = atan2f(accelsData.x, -accelsData.z) * 180.0f / F_PI;
attitudeActual.Yaw = atan2f(-magData.y, magData.x) * 180.0f / F_PI;
RPY2Quaternion(&attitudeActual.Roll,&attitudeActual.q1);
AttitudeActualSet(&attitudeActual);
q[0] = attitudeActual.q1;
q[1] = attitudeActual.q2;
q[2] = attitudeActual.q3;
q[3] = attitudeActual.q4;
INSSetState(pos, zeros, q, zeros, zeros);
INSResetP(Pdiag);
} else if (init_stage == 0 && outdoor_mode) {
float Pdiag[16]={25.0f,25.0f,25.0f,5.0f,5.0f,5.0f,1e-5f,1e-5f,1e-5f,1e-5f,1e-5f,1e-5f,1e-5f,1e-4f,1e-4f,1e-4f};
float q[4];
float NED[3];
// Reset the INS algorithm
INSGPSInit();
INSSetMagVar(revoCalibration.mag_var);
INSSetAccelVar(revoCalibration.accel_var);
INSSetGyroVar(revoCalibration.gyro_var);
INSSetBaroVar(revoCalibration.baro_var);
INSSetMagNorth(homeLocation.Be);
// Initialize the gyro bias from the settings
float gyro_bias[3] = {gyrosBias.x * F_PI / 180.0f, gyrosBias.y * F_PI / 180.0f, gyrosBias.z * F_PI / 180.0f};
INSSetGyroBias(gyro_bias);
GPSPositionData gpsPosition;
GPSPositionGet(&gpsPosition);
// Transform the GPS position into NED coordinates
getNED(&gpsPosition, NED);
// Initialize barometric offset to cirrent GPS NED coordinate
baroOffset = -NED[2] - baroData.Altitude;
xQueueReceive(magQueue, &ev, 100 / portTICK_RATE_MS);
MagnetometerGet(&magData);
// Set initial attitude
AttitudeActualData attitudeActual;
attitudeActual.Roll = atan2f(-accelsData.y, -accelsData.z) * 180.0f / F_PI;
attitudeActual.Pitch = atan2f(accelsData.x, -accelsData.z) * 180.0f / F_PI;
attitudeActual.Yaw = atan2f(-magData.y, magData.x) * 180.0f / F_PI;
RPY2Quaternion(&attitudeActual.Roll,&attitudeActual.q1);
AttitudeActualSet(&attitudeActual);
q[0] = attitudeActual.q1;
q[1] = attitudeActual.q2;
q[2] = attitudeActual.q3;
q[3] = attitudeActual.q4;
INSSetState(NED, zeros, q, zeros, zeros);
INSResetP(Pdiag);
} else if (init_stage > 0) {
// Run prediction a bit before any corrections
dT = PIOS_DELAY_DiffuS(ins_last_time) / 1.0e6f;
GyrosBiasGet(&gyrosBias);
float gyros[3] = {(gyrosData.x + gyrosBias.x) * F_PI / 180.0f,
(gyrosData.y + gyrosBias.y) * F_PI / 180.0f,
(gyrosData.z + gyrosBias.z) * F_PI / 180.0f};
INSStatePrediction(gyros, &accelsData.x, dT);
AttitudeActualData attitude;
AttitudeActualGet(&attitude);
attitude.q1 = Nav.q[0];
attitude.q2 = Nav.q[1];
attitude.q3 = Nav.q[2];
attitude.q4 = Nav.q[3];
Quaternion2RPY(&attitude.q1,&attitude.Roll);
AttitudeActualSet(&attitude);
}
init_stage++;
if(init_stage > 10)
inited = true;
ins_last_time = PIOS_DELAY_GetRaw();
return 0;
}
if (!inited)
return 0;
dT = PIOS_DELAY_DiffuS(ins_last_time) / 1.0e6f;
ins_last_time = PIOS_DELAY_GetRaw();
// This should only happen at start up or at mode switches
if(dT > 0.01f)
dT = 0.01f;
else if(dT <= 0.001f)
dT = 0.001f;
// If the gyro bias setting was updated we should reset
// the state estimate of the EKF
if(gyroBiasSettingsUpdated) {
float gyro_bias[3] = {gyrosBias.x * F_PI / 180.0f, gyrosBias.y * F_PI / 180.0f, gyrosBias.z * F_PI / 180.0f};
INSSetGyroBias(gyro_bias);
gyroBiasSettingsUpdated = false;
}
// Because the sensor module remove the bias we need to add it
// back in here so that the INS algorithm can track it correctly
float gyros[3] = {gyrosData.x * F_PI / 180.0f, gyrosData.y * F_PI / 180.0f, gyrosData.z * F_PI / 180.0f};
if (revoCalibration.BiasCorrectedRaw == REVOCALIBRATION_BIASCORRECTEDRAW_TRUE) {
gyros[0] += gyrosBias.x * F_PI / 180.0f;
gyros[1] += gyrosBias.y * F_PI / 180.0f;
gyros[2] += gyrosBias.z * F_PI / 180.0f;
}
// Advance the state estimate
INSStatePrediction(gyros, &accelsData.x, dT);
// Copy the attitude into the UAVO
AttitudeActualData attitude;
AttitudeActualGet(&attitude);
attitude.q1 = Nav.q[0];
attitude.q2 = Nav.q[1];
attitude.q3 = Nav.q[2];
attitude.q4 = Nav.q[3];
Quaternion2RPY(&attitude.q1,&attitude.Roll);
AttitudeActualSet(&attitude);
// Advance the covariance estimate
INSCovariancePrediction(dT);
if(mag_updated)
sensors |= MAG_SENSORS;
if(baro_updated)
sensors |= BARO_SENSOR;
INSSetMagNorth(homeLocation.Be);
if (gps_updated && outdoor_mode)
{
INSSetPosVelVar(revoCalibration.gps_var[REVOCALIBRATION_GPS_VAR_POS], revoCalibration.gps_var[REVOCALIBRATION_GPS_VAR_VEL]);
sensors |= POS_SENSORS;
if (0) { // Old code to take horizontal velocity from GPS Position update
sensors |= HORIZ_SENSORS;
vel[0] = gpsData.Groundspeed * cosf(gpsData.Heading * F_PI / 180.0f);
vel[1] = gpsData.Groundspeed * sinf(gpsData.Heading * F_PI / 180.0f);
vel[2] = 0;
}
// Transform the GPS position into NED coordinates
getNED(&gpsData, NED);
// Track barometric altitude offset with a low pass filter
baroOffset = BARO_OFFSET_LOWPASS_ALPHA * baroOffset +
(1.0f - BARO_OFFSET_LOWPASS_ALPHA )
* ( -NED[2] - baroData.Altitude );
} else if (!outdoor_mode) {
INSSetPosVelVar(1e2f, 1e2f);
vel[0] = vel[1] = vel[2] = 0;
NED[0] = NED[1] = 0;
NED[2] = -(baroData.Altitude + baroOffset);
sensors |= HORIZ_SENSORS | HORIZ_POS_SENSORS;
sensors |= POS_SENSORS |VERT_SENSORS;
}
if (gps_vel_updated && outdoor_mode) {
sensors |= HORIZ_SENSORS | VERT_SENSORS;
vel[0] = gpsVelData.North;
vel[1] = gpsVelData.East;
vel[2] = gpsVelData.Down;
}
/*
* TODO: Need to add a general sanity check for all the inputs to make sure their kosher
* although probably should occur within INS itself
*/
if (sensors)
INSCorrection(&magData.x, NED, vel, ( baroData.Altitude + baroOffset ), sensors);
// Copy the position and velocity into the UAVO
PositionActualData positionActual;
PositionActualGet(&positionActual);
positionActual.North = Nav.Pos[0];
positionActual.East = Nav.Pos[1];
positionActual.Down = Nav.Pos[2];
PositionActualSet(&positionActual);
VelocityActualData velocityActual;
VelocityActualGet(&velocityActual);
velocityActual.North = Nav.Vel[0];
velocityActual.East = Nav.Vel[1];
velocityActual.Down = Nav.Vel[2];
VelocityActualSet(&velocityActual);
if (revoCalibration.BiasCorrectedRaw == REVOCALIBRATION_BIASCORRECTEDRAW_TRUE && !gyroBiasSettingsUpdated) {
// Copy the gyro bias into the UAVO except when it was updated
// from the settings during the calculation, then consume it
// next cycle
gyrosBias.x = Nav.gyro_bias[0] * 180.0f / F_PI;
gyrosBias.y = Nav.gyro_bias[1] * 180.0f / F_PI;
gyrosBias.z = Nav.gyro_bias[2] * 180.0f / F_PI;
GyrosBiasSet(&gyrosBias);
}
return 0;
}
static int32_t updateAttitudeComplementary(bool first_run)
{
UAVObjEvent ev;
GyrosData gyrosData;
AccelsData accelsData;
static int32_t timeval;
float dT;
static uint8_t init = 0;
// Wait until the AttitudeRaw object is updated, if a timeout then go to failsafe
if ( xQueueReceive(gyroQueue, &ev, FAILSAFE_TIMEOUT_MS / portTICK_RATE_MS) != pdTRUE ||
xQueueReceive(accelQueue, &ev, 1 / portTICK_RATE_MS) != pdTRUE )
{
// When one of these is updated so should the other
// Do not set attitude timeout warnings in simulation mode
if (!AttitudeActualReadOnly()){
AlarmsSet(SYSTEMALARMS_ALARM_ATTITUDE,SYSTEMALARMS_ALARM_WARNING);
return -1;
}
}
AccelsGet(&accelsData);
// During initialization and
FlightStatusData flightStatus;
FlightStatusGet(&flightStatus);
if(first_run) {
#if defined(PIOS_INCLUDE_HMC5883)
// To initialize we need a valid mag reading
if ( xQueueReceive(magQueue, &ev, 0 / portTICK_RATE_MS) != pdTRUE )
return -1;
MagnetometerData magData;
MagnetometerGet(&magData);
#else
MagnetometerData magData;
magData.x = 100;
magData.y = 0;
magData.z = 0;
#endif
AttitudeActualData attitudeActual;
AttitudeActualGet(&attitudeActual);
init = 0;
attitudeActual.Roll = atan2f(-accelsData.y, -accelsData.z) * 180.0f / F_PI;
attitudeActual.Pitch = atan2f(accelsData.x, -accelsData.z) * 180.0f / F_PI;
attitudeActual.Yaw = atan2f(-magData.y, magData.x) * 180.0f / F_PI;
RPY2Quaternion(&attitudeActual.Roll,&attitudeActual.q1);
AttitudeActualSet(&attitudeActual);
timeval = PIOS_DELAY_GetRaw();
return 0;
}
if((init == 0 && xTaskGetTickCount() < 7000) && (xTaskGetTickCount() > 1000)) {
// For first 7 seconds use accels to get gyro bias
attitudeSettings.AccelKp = 1;
attitudeSettings.AccelKi = 0.9;
attitudeSettings.YawBiasRate = 0.23;
magKp = 1;
} else if ((attitudeSettings.ZeroDuringArming == ATTITUDESETTINGS_ZERODURINGARMING_TRUE) && (flightStatus.Armed == FLIGHTSTATUS_ARMED_ARMING)) {
attitudeSettings.AccelKp = 1;
attitudeSettings.AccelKi = 0.9;
attitudeSettings.YawBiasRate = 0.23;
magKp = 1;
init = 0;
} else if (init == 0) {
// Reload settings (all the rates)
AttitudeSettingsGet(&attitudeSettings);
magKp = 0.01f;
init = 1;
}
GyrosGet(&gyrosData);
// Compute the dT using the cpu clock
dT = PIOS_DELAY_DiffuS(timeval) / 1000000.0f;
timeval = PIOS_DELAY_GetRaw();
float q[4];
AttitudeActualData attitudeActual;
AttitudeActualGet(&attitudeActual);
float grot[3];
float accel_err[3];
// Get the current attitude estimate
quat_copy(&attitudeActual.q1, q);
// Rotate gravity to body frame and cross with accels
grot[0] = -(2 * (q[1] * q[3] - q[0] * q[2]));
grot[1] = -(2 * (q[2] * q[3] + q[0] * q[1]));
grot[2] = -(q[0] * q[0] - q[1]*q[1] - q[2]*q[2] + q[3]*q[3]);
CrossProduct((const float *) &accelsData.x, (const float *) grot, accel_err);
// Account for accel magnitude
accel_mag = accelsData.x*accelsData.x + accelsData.y*accelsData.y + accelsData.z*accelsData.z;
accel_mag = sqrtf(accel_mag);
accel_err[0] /= accel_mag;
accel_err[1] /= accel_mag;
accel_err[2] /= accel_mag;
if ( xQueueReceive(magQueue, &ev, 0) != pdTRUE )
{
// Rotate gravity to body frame and cross with accels
float brot[3];
float Rbe[3][3];
MagnetometerData mag;
Quaternion2R(q, Rbe);
MagnetometerGet(&mag);
// If the mag is producing bad data don't use it (normally bad calibration)
if (mag.x == mag.x && mag.y == mag.y && mag.z == mag.z) {
rot_mult(Rbe, homeLocation.Be, brot);
float mag_len = sqrtf(mag.x * mag.x + mag.y * mag.y + mag.z * mag.z);
mag.x /= mag_len;
mag.y /= mag_len;
mag.z /= mag_len;
float bmag = sqrtf(brot[0] * brot[0] + brot[1] * brot[1] + brot[2] * brot[2]);
brot[0] /= bmag;
brot[1] /= bmag;
brot[2] /= bmag;
// Only compute if neither vector is null
if (bmag < 1 || mag_len < 1)
mag_err[0] = mag_err[1] = mag_err[2] = 0;
else
CrossProduct((const float *) &mag.x, (const float *) brot, mag_err);
}
} else {
mag_err[0] = mag_err[1] = mag_err[2] = 0;
}
// Accumulate integral of error. Scale here so that units are (deg/s) but Ki has units of s
GyrosBiasData gyrosBias;
GyrosBiasGet(&gyrosBias);
gyrosBias.x -= accel_err[0] * attitudeSettings.AccelKi;
gyrosBias.y -= accel_err[1] * attitudeSettings.AccelKi;
gyrosBias.z -= mag_err[2] * magKi;
GyrosBiasSet(&gyrosBias);
// Correct rates based on error, integral component dealt with in updateSensors
gyrosData.x += accel_err[0] * attitudeSettings.AccelKp / dT;
gyrosData.y += accel_err[1] * attitudeSettings.AccelKp / dT;
gyrosData.z += accel_err[2] * attitudeSettings.AccelKp / dT + mag_err[2] * magKp / dT;
// Work out time derivative from INSAlgo writeup
// Also accounts for the fact that gyros are in deg/s
float qdot[4];
qdot[0] = (-q[1] * gyrosData.x - q[2] * gyrosData.y - q[3] * gyrosData.z) * dT * F_PI / 180 / 2;
qdot[1] = (q[0] * gyrosData.x - q[3] * gyrosData.y + q[2] * gyrosData.z) * dT * F_PI / 180 / 2;
qdot[2] = (q[3] * gyrosData.x + q[0] * gyrosData.y - q[1] * gyrosData.z) * dT * F_PI / 180 / 2;
qdot[3] = (-q[2] * gyrosData.x + q[1] * gyrosData.y + q[0] * gyrosData.z) * dT * F_PI / 180 / 2;
// Take a time step
q[0] = q[0] + qdot[0];
q[1] = q[1] + qdot[1];
q[2] = q[2] + qdot[2];
q[3] = q[3] + qdot[3];
if(q[0] < 0) {
q[0] = -q[0];
q[1] = -q[1];
q[2] = -q[2];
q[3] = -q[3];
}
// Renomalize
qmag = sqrtf(q[0]*q[0] + q[1]*q[1] + q[2]*q[2] + q[3]*q[3]);
q[0] = q[0] / qmag;
q[1] = q[1] / qmag;
q[2] = q[2] / qmag;
q[3] = q[3] / qmag;
// If quaternion has become inappropriately short or is nan reinit.
// THIS SHOULD NEVER ACTUALLY HAPPEN
if((fabs(qmag) < 1.0e-3f) || (qmag != qmag)) {
q[0] = 1;
q[1] = 0;
q[2] = 0;
q[3] = 0;
}
quat_copy(q, &attitudeActual.q1);
// Convert into eueler degrees (makes assumptions about RPY order)
Quaternion2RPY(&attitudeActual.q1,&attitudeActual.Roll);
AttitudeActualSet(&attitudeActual);
// Flush these queues for avoid errors
xQueueReceive(baroQueue, &ev, 0);
if ( xQueueReceive(gpsQueue, &ev, 0) == pdTRUE && homeLocation.Set == HOMELOCATION_SET_TRUE ) {
float NED[3];
// Transform the GPS position into NED coordinates
GPSPositionData gpsPosition;
GPSPositionGet(&gpsPosition);
getNED(&gpsPosition, NED);
PositionActualData positionActual;
PositionActualGet(&positionActual);
positionActual.North = NED[0];
positionActual.East = NED[1];
positionActual.Down = NED[2];
PositionActualSet(&positionActual);
}
if ( xQueueReceive(gpsVelQueue, &ev, 0) == pdTRUE ) {
// Transform the GPS position into NED coordinates
GPSVelocityData gpsVelocity;
GPSVelocityGet(&gpsVelocity);
VelocityActualData velocityActual;
VelocityActualGet(&velocityActual);
velocityActual.North = gpsVelocity.North;
velocityActual.East = gpsVelocity.East;
velocityActual.Down = gpsVelocity.Down;
VelocityActualSet(&velocityActual);
}
AlarmsClear(SYSTEMALARMS_ALARM_ATTITUDE);
return 0;
}
static void updateAttitude(AccelsData * accelsData, GyrosData * gyrosData)
{
float dT;
portTickType thisSysTime = xTaskGetTickCount();
static portTickType lastSysTime = 0;
static float accels_filtered[3] = {0,0,0};
static float grot_filtered[3] = {0,0,0};
dT = (thisSysTime == lastSysTime) ? 0.001f : TICKS2MS(portMAX_DELAY & (thisSysTime - lastSysTime)) / 1000.0f;
lastSysTime = thisSysTime;
// Bad practice to assume structure order, but saves memory
float * gyros = &gyrosData->x;
float * accels = &accelsData->x;
float grot[3];
float accel_err[3];
// Apply smoothing to accel values, to reduce vibration noise before main calculations.
apply_accel_filter(accels,accels_filtered);
// Rotate gravity to body frame, filter and cross with accels
grot[0] = -(2 * (q[1] * q[3] - q[0] * q[2]));
grot[1] = -(2 * (q[2] * q[3] + q[0] * q[1]));
grot[2] = -(q[0] * q[0] - q[1]*q[1] - q[2]*q[2] + q[3]*q[3]);
// Apply same filtering to the rotated attitude to match delays
apply_accel_filter(grot,grot_filtered);
// Compute the error between the predicted direction of gravity and smoothed acceleration
CrossProduct((const float *) accels_filtered, (const float *) grot_filtered, accel_err);
// Account for accel magnitude
float accel_mag = sqrtf(accels_filtered[0]*accels_filtered[0] + accels_filtered[1]*accels_filtered[1] + accels_filtered[2]*accels_filtered[2]);
// Account for filtered gravity vector magnitude
float grot_mag;
if (accel_filter_enabled)
grot_mag = sqrtf(grot_filtered[0]*grot_filtered[0] + grot_filtered[1]*grot_filtered[1] + grot_filtered[2]*grot_filtered[2]);
else
grot_mag = 1.0f;
if (grot_mag > 1.0e-3f && accel_mag > 1.0e-3f) {
accel_err[0] /= (accel_mag*grot_mag);
accel_err[1] /= (accel_mag*grot_mag);
accel_err[2] /= (accel_mag*grot_mag);
// Accumulate integral of error. Scale here so that units are (deg/s) but Ki has units of s
gyro_correct_int[0] -= accel_err[0] * accelKi;
gyro_correct_int[1] -= accel_err[1] * accelKi;
// Correct rates based on error, integral component dealt with in updateSensors
gyros[0] += accel_err[0] * accelKp / dT;
gyros[1] += accel_err[1] * accelKp / dT;
gyros[2] += accel_err[2] * accelKp / dT;
}
{ // scoping variables to save memory
// Work out time derivative from INSAlgo writeup
// Also accounts for the fact that gyros are in deg/s
float qdot[4];
qdot[0] = (-q[1] * gyros[0] - q[2] * gyros[1] - q[3] * gyros[2]) * dT * DEG2RAD / 2;
qdot[1] = (q[0] * gyros[0] - q[3] * gyros[1] + q[2] * gyros[2]) * dT * DEG2RAD / 2;
qdot[2] = (q[3] * gyros[0] + q[0] * gyros[1] - q[1] * gyros[2]) * dT * DEG2RAD / 2;
qdot[3] = (-q[2] * gyros[0] + q[1] * gyros[1] + q[0] * gyros[2]) * dT * DEG2RAD / 2;
// Take a time step
q[0] = q[0] + qdot[0];
q[1] = q[1] + qdot[1];
q[2] = q[2] + qdot[2];
q[3] = q[3] + qdot[3];
if(q[0] < 0) {
q[0] = -q[0];
q[1] = -q[1];
q[2] = -q[2];
q[3] = -q[3];
}
}
// Renomalize
float qmag = sqrtf(q[0]*q[0] + q[1]*q[1] + q[2]*q[2] + q[3]*q[3]);
q[0] = q[0] / qmag;
q[1] = q[1] / qmag;
q[2] = q[2] / qmag;
q[3] = q[3] / qmag;
// If quaternion has become inappropriately short or is nan reinit.
// THIS SHOULD NEVER ACTUALLY HAPPEN
if((fabs(qmag) < 1e-3) || (qmag != qmag)) {
q[0] = 1;
q[1] = 0;
q[2] = 0;
q[3] = 0;
}
AttitudeActualData attitudeActual;
AttitudeActualGet(&attitudeActual);
quat_copy(q, &attitudeActual.q1);
// Convert into eueler degrees (makes assumptions about RPY order)
Quaternion2RPY(&attitudeActual.q1,&attitudeActual.Roll);
AttitudeActualSet(&attitudeActual);
}
