void updateGpsStateForHomeAndHoldMode(void)
{
float sin_yaw_y = sinf(heading * 0.0174532925f);
float cos_yaw_x = cosf(heading * 0.0174532925f);
if (gpsProfile->nav_slew_rate) {
nav_rated[LON] += constrain(wrap_18000(nav[LON] - nav_rated[LON]), -gpsProfile->nav_slew_rate, gpsProfile->nav_slew_rate); // TODO check this on uint8
nav_rated[LAT] += constrain(wrap_18000(nav[LAT] - nav_rated[LAT]), -gpsProfile->nav_slew_rate, gpsProfile->nav_slew_rate);
GPS_angle[AI_ROLL] = (nav_rated[LON] * cos_yaw_x - nav_rated[LAT] * sin_yaw_y) / 10;
GPS_angle[AI_PITCH] = (nav_rated[LON] * sin_yaw_y + nav_rated[LAT] * cos_yaw_x) / 10;
} else {
GPS_angle[AI_ROLL] = (nav[LON] * cos_yaw_x - nav[LAT] * sin_yaw_y) / 10;
GPS_angle[AI_PITCH] = (nav[LON] * sin_yaw_y + nav[LAT] * cos_yaw_x) / 10;
}
}
void updateGpsStateForHomeAndHoldMode(void)
{
float sin_yaw_y = sin_approx(DECIDEGREES_TO_DEGREES(attitude.values.yaw) * 0.0174532925f);
float cos_yaw_x = cos_approx(DECIDEGREES_TO_DEGREES(attitude.values.yaw) * 0.0174532925f);
if (gpsProfile()->nav_slew_rate) {
nav_rated[LON] += constrain(wrap_18000(nav[LON] - nav_rated[LON]), -gpsProfile()->nav_slew_rate, gpsProfile()->nav_slew_rate); // TODO check this on uint8
nav_rated[LAT] += constrain(wrap_18000(nav[LAT] - nav_rated[LAT]), -gpsProfile()->nav_slew_rate, gpsProfile()->nav_slew_rate);
GPS_angle[AI_ROLL] = (nav_rated[LON] * cos_yaw_x - nav_rated[LAT] * sin_yaw_y) / 10;
GPS_angle[AI_PITCH] = (nav_rated[LON] * sin_yaw_y + nav_rated[LAT] * cos_yaw_x) / 10;
} else {
GPS_angle[AI_ROLL] = (nav[LON] * cos_yaw_x - nav[LAT] * sin_yaw_y) / 10;
GPS_angle[AI_PITCH] = (nav[LON] * sin_yaw_y + nav[LAT] * cos_yaw_x) / 10;
}
}
bool check_missed_wp(void)
{
float temp;
temp = (float)(target_bearing - original_target_bearing);
temp = wrap_18000(temp);
return (abs(temp) > 10000); // we passed the waypoint by 100 degrees
}
////////////////////////////////////////////////////////////////////////////////////
// Check if we missed the destination somehow
//
static bool check_missed_wp(void)
{
int32_t temp;
temp = target_bearing - original_target_bearing;
temp = wrap_18000(temp);
return (abs(temp) > 10000); // we passed the waypoint by 100 degrees
}
/***********************
函数功能：检查目标是否因各种原因消失
输入参数：木有
***********************/
static bool check_missed_wp(void)
{
int32_t temp;
temp = target_bearing - original_target_bearing;
temp = wrap_18000(temp);
return (abs(temp) > 10000); //如果大于100度就认为没有目标了
}
////////////////////////////////////////////////////////////////////////////////////
// Calculating cross track error, this tries to keep the copter on a direct line
// when flying to a waypoint.
//
static void GPS_update_crosstrack(void) {
if (fabs(wrap_18000(target_bearing - original_target_bearing)) < 4500) { // If we are too far off or too close we don't do track following
float temp = (target_bearing - original_target_bearing) * RADX100;
crosstrack_error = sin(temp) * (wp_distance * CROSSTRACK_GAIN); // Meters we are off track line
nav_bearing = target_bearing + constrain(crosstrack_error, -3000, 3000);
nav_bearing = wrap_36000(nav_bearing);
}else{
nav_bearing = target_bearing;
}
}
static float getVelocityHeadingAttenuationFactor(void)
{
// In WP mode scale velocity if heading is different from bearing
if (navGetCurrentStateFlags() & NAV_AUTO_WP) {
int32_t headingError = constrain(wrap_18000(posControl.desiredState.yaw - posControl.actualState.yaw), -9000, 9000);
float velScaling = cos_approx(CENTIDEGREES_TO_RADIANS(headingError));
return constrainf(velScaling * velScaling, 0.05f, 1.0f);
} else {
return 1.0f;
}
}
/***********************
函数功能：偏离航线计算纠正角，纠正角会叠加在目标航向上
输入参数：
***********************/
static void GPS_update_crosstrack(void) //偏离航线计算纠正角，纠正角会叠加在目标航向上
{
float crosstrack_output;
if (abs(wrap_18000(target_bearing - original_target_bearing)) < 4500) // 偏差角度太大就不需要这种做法 ，大于45度纠正会出现纠航向大于90度
{
float temp = (target_bearing - original_target_bearing) * RADX100;
crosstrack_error = sinf(temp) * wp_distance; //算出偏离航线的距离，点到线的距离
crosstrack_output = AC_PID_get_p(&pid_nav_crosstrack, crosstrack_error, &nav_crosstrackPID)
+ AC_PID_get_i(&pid_nav_crosstrack, crosstrack_error, &dTnav, &nav_crosstrackPID)
+ AC_PID_get_d(&pid_nav_crosstrack, crosstrack_error, &dTnav, &nav_crosstrackPID);
nav_bearing = target_bearing + constrain(crosstrack_output, -4500, 4500); //限制纠正角为30度
nav_bearing = wrap_36000(nav_bearing);
}
else
{
nav_bearing = target_bearing;
}
}
static void updatePositionHeadingController_FW(uint32_t deltaMicros)
{
static bool forceTurnDirection = false;
// We have virtual position target, calculate heading error
int32_t virtualTargetBearing = calculateBearingToDestination(&virtualDesiredPosition);
// Calculate NAV heading error
int32_t headingError = wrap_18000(virtualTargetBearing - posControl.actualState.yaw);
// Forced turn direction
// If heading error is close to 180 deg we initiate forced turn and only disable it when heading error goes below 90 deg
if (ABS(headingError) > 17000) {
forceTurnDirection = true;
}
else if (ABS(headingError) < 9000 && forceTurnDirection) {
forceTurnDirection = false;
}
// If forced turn direction flag is enabled we fix the sign of the direction
if (forceTurnDirection) {
headingError = ABS(headingError);
}
// Input error in (deg*100), output pitch angle (deg*100)
float rollAdjustment = navPidApply2(posControl.actualState.yaw + headingError, posControl.actualState.yaw, US2S(deltaMicros), &posControl.pids.fw_nav,
-DEGREES_TO_CENTIDEGREES(posControl.navConfig->fw_max_bank_angle),
DEGREES_TO_CENTIDEGREES(posControl.navConfig->fw_max_bank_angle),
true);
// Apply low-pass filter to prevent rapid correction
rollAdjustment = pt1FilterApply4(&fwPosControllerCorrectionFilterState, rollAdjustment, NAV_FW_ROLL_CUTOFF_FREQUENCY_HZ, US2S(deltaMicros));
// Convert rollAdjustment to decidegrees (rcAdjustment holds decidegrees)
posControl.rcAdjustment[ROLL] = CENTIDEGREES_TO_DECIDEGREES(rollAdjustment);
// Update magHold heading lock in case pilot is using MAG mode (prevent MAGHOLD to fight navigation)
posControl.desiredState.yaw = wrap_36000(posControl.actualState.yaw + headingError);
updateMagHoldHeading(CENTIDEGREES_TO_DEGREES(posControl.desiredState.yaw));
// Add pitch compensation
//posControl.rcAdjustment[PITCH] = -CENTIDEGREES_TO_DECIDEGREES(ABS(rollAdjustment)) * 0.50f;
}
////////////////////////////////////////////////////////////////////////////////////
// Calculate the desired nav_lat and nav_lon for distance flying such as RTH
void GPS_calc_nav_rate(uint16_t max_speed)
{
float trig[2], rate_error;
float temp, tiltcomp, trgtspeed;
uint8_t axis;
int32_t crosstrack_error;
if ((abs(wrap_18000(target_bearing - original_target_bearing)) < 4500) && cfg.nav_ctrkgain != 0)// If we are too far off or too close we don't do track following
{
temp = (float)(target_bearing - original_target_bearing) * RADX100;
crosstrack_error = sinf(temp) * (float)wp_distance * cfg.nav_ctrkgain; // Meters we are off track line
nav_bearing = target_bearing + constrain(crosstrack_error, -3000, 3000);
while (nav_bearing < 0) nav_bearing += 36000; // nav_bearing = wrap_36000(nav_bearing);
while (nav_bearing >= 36000) nav_bearing -= 36000;
}
else nav_bearing = target_bearing;
temp = (float)(9000l - nav_bearing) * RADX100; // nav_bearing and maybe crosstrack
trig[GPS_X] = cosf(temp);
trig[GPS_Y] = sinf(temp);
for (axis = 0; axis < 2; axis++)
{
trgtspeed = (trig[axis] * (float)max_speed); // Target speed
rate_error = trgtspeed - MIX_speed[axis]; // Since my INS Stuff is shit, reduce ACC influence to 50% anyway better than leadfilter
rate_error = constrain(rate_error, -1000, 1000);
nav[axis] = get_P(rate_error, &navPID_PARAM) + // P + I + D
get_I(rate_error, &ACCDeltaTimeINS, &navPID[axis], &navPID_PARAM) +
get_D(rate_error, &ACCDeltaTimeINS, &navPID[axis], &navPID_PARAM);
if (cfg.nav_tiltcomp) // Do the apm 2.9.1 magic tiltcompensation
{
tiltcomp = trgtspeed * trgtspeed * ((float)cfg.nav_tiltcomp * 0.0001f);
if(trgtspeed < 0) tiltcomp = -tiltcomp;
}
else tiltcomp = 0;
nav[axis] = nav[axis] + tiltcomp; // Constrain is done at the end of all GPS stuff
poshold_ratePID[axis].integrator = navPID[axis].integrator;
}
}
void loop(void)
{
static uint8_t rcDelayCommand; // this indicates the number of time (multiple of RC measurement at 50Hz) the sticks must be maintained to run or switch off motors
uint8_t axis, i;
int16_t error, errorAngle;
int16_t delta, deltaSum;
int16_t PTerm, ITerm, PTermACC, ITermACC = 0, PTermGYRO = 0, ITermGYRO = 0, DTerm;
static int16_t lastGyro[3] = { 0, 0, 0 };
static int16_t delta1[3], delta2[3];
static int16_t errorGyroI[3] = { 0, 0, 0 };
static int16_t errorAngleI[2] = { 0, 0 };
static uint32_t rcTime = 0;
static int16_t initialThrottleHold;
static uint32_t loopTime;
uint16_t auxState = 0;
int16_t prop;
// this will return false if spektrum is disabled. shrug.
if (spektrumFrameComplete())
computeRC();
if ((int32_t)(currentTime - rcTime) >= 0) { // 50Hz
rcTime = currentTime + 20000;
// TODO clean this up. computeRC should handle this check
if (!feature(FEATURE_SPEKTRUM))
computeRC();
// Failsafe routine
if (feature(FEATURE_FAILSAFE)) {
if (failsafeCnt > (5 * cfg.failsafe_delay) && f.ARMED) { // Stabilize, and set Throttle to specified level
for (i = 0; i < 3; i++)
rcData[i] = cfg.midrc; // after specified guard time after RC signal is lost (in 0.1sec)
rcData[THROTTLE] = cfg.failsafe_throttle;
if (failsafeCnt > 5 * (cfg.failsafe_delay + cfg.failsafe_off_delay)) { // Turn OFF motors after specified Time (in 0.1sec)
f.ARMED = 0; // This will prevent the copter to automatically rearm if failsafe shuts it down and prevents
f.OK_TO_ARM = 0; // to restart accidentely by just reconnect to the tx - you will have to switch off first to rearm
}
failsafeEvents++;
}
if (failsafeCnt > (5 * cfg.failsafe_delay) && !f.ARMED) { // Turn off "Ok To arm to prevent the motors from spinning after repowering the RX with low throttle and aux to arm
f.ARMED = 0; // This will prevent the copter to automatically rearm if failsafe shuts it down and prevents
f.OK_TO_ARM = 0; // to restart accidentely by just reconnect to the tx - you will have to switch off first to rearm
}
failsafeCnt++;
}
if (rcData[THROTTLE] < cfg.mincheck) {
errorGyroI[ROLL] = 0;
errorGyroI[PITCH] = 0;
errorGyroI[YAW] = 0;
errorAngleI[ROLL] = 0;
errorAngleI[PITCH] = 0;
rcDelayCommand++;
if (rcData[YAW] < cfg.mincheck && rcData[PITCH] < cfg.mincheck && !f.ARMED) {
if (rcDelayCommand == 20) {
calibratingG = 1000;
if (feature(FEATURE_GPS))
GPS_reset_home_position();
}
} else if (feature(FEATURE_INFLIGHT_ACC_CAL) && (!f.ARMED && rcData[YAW] < cfg.mincheck && rcData[PITCH] > cfg.maxcheck && rcData[ROLL] > cfg.maxcheck)) {
if (rcDelayCommand == 20) {
if (AccInflightCalibrationMeasurementDone) { // trigger saving into eeprom after landing
AccInflightCalibrationMeasurementDone = 0;
AccInflightCalibrationSavetoEEProm = 1;
} else {
AccInflightCalibrationArmed = !AccInflightCalibrationArmed;
if (AccInflightCalibrationArmed) {
toggleBeep = 2;
} else {
toggleBeep = 3;
}
}
}
} else if (cfg.activate[BOXARM] > 0) {
if (rcOptions[BOXARM] && f.OK_TO_ARM) {
// TODO: feature(FEATURE_FAILSAFE) && failsafeCnt == 0
f.ARMED = 1;
headFreeModeHold = heading;
} else if (f.ARMED)
f.ARMED = 0;
rcDelayCommand = 0;
} else if ((rcData[YAW] < cfg.mincheck || (cfg.retarded_arm == 1 && rcData[ROLL] < cfg.mincheck)) && f.ARMED) {
if (rcDelayCommand == 20)
f.ARMED = 0; // rcDelayCommand = 20 => 20x20ms = 0.4s = time to wait for a specific RC command to be acknowledged
} else if ((rcData[YAW] > cfg.maxcheck || (rcData[ROLL] > cfg.maxcheck && cfg.retarded_arm == 1)) && rcData[PITCH] < cfg.maxcheck && !f.ARMED && calibratingG == 0 && f.ACC_CALIBRATED) {
if (rcDelayCommand == 20) {
f.ARMED = 1;
headFreeModeHold = heading;
}
} else
rcDelayCommand = 0;
} else if (rcData[THROTTLE] > cfg.maxcheck && !f.ARMED) {
if (rcData[YAW] < cfg.mincheck && rcData[PITCH] < cfg.mincheck) { // throttle=max, yaw=left, pitch=min
if (rcDelayCommand == 20)
calibratingA = 400;
rcDelayCommand++;
} else if (rcData[YAW] > cfg.maxcheck && rcData[PITCH] < cfg.mincheck) { // throttle=max, yaw=right, pitch=min
if (rcDelayCommand == 20)
f.CALIBRATE_MAG = 1; // MAG calibration request
rcDelayCommand++;
} else if (rcData[PITCH] > cfg.maxcheck) {
cfg.angleTrim[PITCH] += 2;
writeParams(1);
#ifdef LEDRING
if (feature(FEATURE_LED_RING))
ledringBlink();
#endif
} else if (rcData[PITCH] < cfg.mincheck) {
cfg.angleTrim[PITCH] -= 2;
writeParams(1);
#ifdef LEDRING
if (feature(FEATURE_LED_RING))
ledringBlink();
#endif
} else if (rcData[ROLL] > cfg.maxcheck) {
cfg.angleTrim[ROLL] += 2;
writeParams(1);
#ifdef LEDRING
if (feature(FEATURE_LED_RING))
ledringBlink();
#endif
} else if (rcData[ROLL] < cfg.mincheck) {
cfg.angleTrim[ROLL] -= 2;
writeParams(1);
#ifdef LEDRING
if (feature(FEATURE_LED_RING))
ledringBlink();
#endif
} else {
rcDelayCommand = 0;
}
}
if (feature(FEATURE_INFLIGHT_ACC_CAL)) {
if (AccInflightCalibrationArmed && f.ARMED && rcData[THROTTLE] > cfg.mincheck && !rcOptions[BOXARM]) { // Copter is airborne and you are turning it off via boxarm : start measurement
InflightcalibratingA = 50;
AccInflightCalibrationArmed = 0;
}
if (rcOptions[BOXPASSTHRU]) { // Use the Passthru Option to activate : Passthru = TRUE Meausrement started, Land and passtrhu = 0 measurement stored
if (!AccInflightCalibrationActive && !AccInflightCalibrationMeasurementDone)
InflightcalibratingA = 50;
} else if (AccInflightCalibrationMeasurementDone && !f.ARMED) {
AccInflightCalibrationMeasurementDone = 0;
AccInflightCalibrationSavetoEEProm = 1;
}
}
for(i = 0; i < 4; i++)
auxState |= (rcData[AUX1 + i] < 1300) << (3 * i) | (1300 < rcData[AUX1 + i] && rcData[AUX1 + i] < 1700) << (3 * i + 1) | (rcData[AUX1 + i] > 1700) << (3 * i + 2);
for(i = 0; i < CHECKBOXITEMS; i++)
rcOptions[i] = (auxState & cfg.activate[i]) > 0;
// note: if FAILSAFE is disable, failsafeCnt > 5*FAILSAVE_DELAY is always false
if ((rcOptions[BOXANGLE] || (failsafeCnt > 5 * cfg.failsafe_delay)) && (sensors(SENSOR_ACC))) {
// bumpless transfer to Level mode
if (!f.ANGLE_MODE) {
errorAngleI[ROLL] = 0;
errorAngleI[PITCH] = 0;
f.ANGLE_MODE = 1;
}
} else {
f.ANGLE_MODE = 0; // failsave support
}
if (rcOptions[BOXHORIZON]) {
if (!f.HORIZON_MODE) {
errorAngleI[ROLL] = 0;
errorAngleI[PITCH] = 0;
f.HORIZON_MODE = 1;
}
} else {
f.HORIZON_MODE = 0;
}
if ((rcOptions[BOXARM]) == 0)
f.OK_TO_ARM = 1;
if (f.ANGLE_MODE || f.HORIZON_MODE) {
LED1_ON;
} else {
LED1_OFF;
}
#ifdef BARO
if (sensors(SENSOR_BARO)) {
if (rcOptions[BOXBARO]) {
if (!f.BARO_MODE) {
f.BARO_MODE = 1;
AltHold = EstAlt;
initialThrottleHold = rcCommand[THROTTLE];
errorAltitudeI = 0;
BaroPID = 0;
}
} else
f.BARO_MODE = 0;
}
#endif
#ifdef MAG
if (sensors(SENSOR_MAG)) {
if (rcOptions[BOXMAG]) {
if (!f.MAG_MODE) {
f.MAG_MODE = 1;
magHold = heading;
}
} else
f.MAG_MODE = 0;
if (rcOptions[BOXHEADFREE]) {
if (!f.HEADFREE_MODE) {
f.HEADFREE_MODE = 1;
}
} else {
f.HEADFREE_MODE = 0;
}
if (rcOptions[BOXHEADADJ]) {
headFreeModeHold = heading; // acquire new heading
}
}
#endif
if (sensors(SENSOR_GPS)) {
if (f.GPS_FIX && GPS_numSat >= 5) {
if (rcOptions[BOXGPSHOME]) {
if (!f.GPS_HOME_MODE) {
f.GPS_HOME_MODE = 1;
GPS_set_next_wp(&GPS_home[LAT], &GPS_home[LON]);
nav_mode = NAV_MODE_WP;
}
} else {
f.GPS_HOME_MODE = 0;
}
if (rcOptions[BOXGPSHOLD]) {
if (!f.GPS_HOLD_MODE) {
f.GPS_HOLD_MODE = 1;
GPS_hold[LAT] = GPS_coord[LAT];
GPS_hold[LON] = GPS_coord[LON];
GPS_set_next_wp(&GPS_hold[LAT], &GPS_hold[LON]);
nav_mode = NAV_MODE_POSHOLD;
}
} else {
f.GPS_HOLD_MODE = 0;
}
}
}
if (rcOptions[BOXPASSTHRU]) {
f.PASSTHRU_MODE = 1;
} else {
f.PASSTHRU_MODE = 0;
}
if (cfg.mixerConfiguration == MULTITYPE_FLYING_WING || cfg.mixerConfiguration == MULTITYPE_AIRPLANE) {
f.HEADFREE_MODE = 0;
}
} else { // not in rc loop
static int8_t taskOrder = 0; // never call all function in the same loop, to avoid high delay spikes
switch (taskOrder++ % 4) {
case 0:
#ifdef MAG
if (sensors(SENSOR_MAG))
Mag_getADC();
#endif
break;
case 1:
#ifdef BARO
if (sensors(SENSOR_BARO))
Baro_update();
#endif
break;
case 2:
#ifdef BARO
if (sensors(SENSOR_BARO))
getEstimatedAltitude();
#endif
break;
case 3:
#ifdef SONAR
if (sensors(SENSOR_SONAR)) {
Sonar_update();
debug[2] = sonarAlt;
}
#endif
break;
default:
taskOrder = 0;
break;
}
}
currentTime = micros();
if (cfg.looptime == 0 || (int32_t)(currentTime - loopTime) >= 0) {
loopTime = currentTime + cfg.looptime;
computeIMU();
// Measure loop rate just afer reading the sensors
currentTime = micros();
cycleTime = (int32_t)(currentTime - previousTime);
previousTime = currentTime;
#ifdef MPU6050_DMP
mpu6050DmpLoop();
#endif
#ifdef MAG
if (sensors(SENSOR_MAG)) {
if (abs(rcCommand[YAW]) < 70 && f.MAG_MODE) {
int16_t dif = heading - magHold;
if (dif <= -180)
dif += 360;
if (dif >= +180)
dif -= 360;
if (f.SMALL_ANGLES_25)
rcCommand[YAW] -= dif * cfg.P8[PIDMAG] / 30; // 18 deg
} else
magHold = heading;
}
#endif
#ifdef BARO
if (sensors(SENSOR_BARO)) {
if (f.BARO_MODE) {
if (abs(rcCommand[THROTTLE] - initialThrottleHold) > cfg.alt_hold_throttle_neutral) {
f.BARO_MODE = 0; // so that a new althold reference is defined
}
rcCommand[THROTTLE] = initialThrottleHold + BaroPID;
}
}
#endif
if (sensors(SENSOR_GPS)) {
// Check that we really need to navigate ?
if ((!f.GPS_HOME_MODE && !f.GPS_HOLD_MODE) || !f.GPS_FIX_HOME) {
// If not. Reset nav loops and all nav related parameters
GPS_reset_nav();
} else {
float sin_yaw_y = sinf(heading * 0.0174532925f);
float cos_yaw_x = cosf(heading * 0.0174532925f);
if (cfg.nav_slew_rate) {
nav_rated[LON] += constrain(wrap_18000(nav[LON] - nav_rated[LON]), -cfg.nav_slew_rate, cfg.nav_slew_rate); // TODO check this on uint8
nav_rated[LAT] += constrain(wrap_18000(nav[LAT] - nav_rated[LAT]), -cfg.nav_slew_rate, cfg.nav_slew_rate);
GPS_angle[ROLL] = (nav_rated[LON] * cos_yaw_x - nav_rated[LAT] * sin_yaw_y) / 10;
GPS_angle[PITCH] = (nav_rated[LON] * sin_yaw_y + nav_rated[LAT] * cos_yaw_x) / 10;
} else {
GPS_angle[ROLL] = (nav[LON] * cos_yaw_x - nav[LAT] * sin_yaw_y) / 10;
GPS_angle[PITCH] = (nav[LON] * sin_yaw_y + nav[LAT] * cos_yaw_x) / 10;
}
}
}
// **** PITCH & ROLL & YAW PID ****
prop = max(abs(rcCommand[PITCH]), abs(rcCommand[ROLL])); // range [0;500]
for (axis = 0; axis < 3; axis++) {
if ((f.ANGLE_MODE || f.HORIZON_MODE) && axis < 2) { // MODE relying on ACC
// 50 degrees max inclination
errorAngle = constrain(2 * rcCommand[axis] + GPS_angle[axis], -500, +500) - angle[axis] + cfg.angleTrim[axis];
#ifdef LEVEL_PDF
PTermACC = -(int32_t)angle[axis] * cfg.P8[PIDLEVEL] / 100;
#else
PTermACC = (int32_t)errorAngle * cfg.P8[PIDLEVEL] / 100; // 32 bits is needed for calculation: errorAngle*P8[PIDLEVEL] could exceed 32768 16 bits is ok for result
#endif
PTermACC = constrain(PTermACC, -cfg.D8[PIDLEVEL] * 5, +cfg.D8[PIDLEVEL] * 5);
errorAngleI[axis] = constrain(errorAngleI[axis] + errorAngle, -10000, +10000); // WindUp
ITermACC = ((int32_t)errorAngleI[axis] * cfg.I8[PIDLEVEL]) >> 12;
}
if (!f.ANGLE_MODE || axis == 2) { // MODE relying on GYRO or YAW axis
error = (int32_t)rcCommand[axis] * 10 * 8 / cfg.P8[axis];
error -= gyroData[axis];
PTermGYRO = rcCommand[axis];
errorGyroI[axis] = constrain(errorGyroI[axis] + error, -16000, +16000); // WindUp
if (abs(gyroData[axis]) > 640)
errorGyroI[axis] = 0;
ITermGYRO = (errorGyroI[axis] / 125 * cfg.I8[axis]) >> 6;
}
uint8_t GPS_NewData(void) {
uint8_t axis;
#if defined(I2C_GPS)
static uint8_t _i2c_gps_status;
//Do not use i2c_writereg, since writing a register does not work if an i2c_stop command is issued at the end
//Still investigating, however with separated i2c_repstart and i2c_write commands works... and did not caused i2c errors on a long term test.
GPS_numSat = (_i2c_gps_status & 0xf0) >> 4;
_i2c_gps_status = i2c_readReg(I2C_GPS_ADDRESS,I2C_GPS_STATUS_00); //Get status register
uint8_t *varptr;
#if defined(I2C_GPS_SONAR)
i2c_rep_start(I2C_GPS_ADDRESS<<1);
i2c_write(I2C_GPS_SONAR_ALT);
i2c_rep_start((I2C_GPS_ADDRESS<<1)|1);
varptr = (uint8_t *)&sonarAlt; // altitude (in cm? maybe)
*varptr++ = i2c_readAck();
*varptr = i2c_readNak();
#endif
if (_i2c_gps_status & I2C_GPS_STATUS_3DFIX) { //Check is we have a good 3d fix (numsats>5)
f.GPS_FIX = 1;
if (_i2c_gps_status & I2C_GPS_STATUS_NEW_DATA) { //Check about new data
GPS_Frame = 1;
i2c_rep_start(I2C_GPS_ADDRESS<<1);
i2c_write(I2C_GPS_LOCATION); //Start read from here 2x2 bytes distance and direction
i2c_rep_start((I2C_GPS_ADDRESS<<1)|1);
varptr = (uint8_t *)&GPS_coord[LAT]; // for latitude displaying
*varptr++ = i2c_readAck();
*varptr++ = i2c_readAck();
*varptr++ = i2c_readAck();
*varptr = i2c_readAck();
varptr = (uint8_t *)&GPS_coord[LON]; // for longitude displaying
*varptr++ = i2c_readAck();
*varptr++ = i2c_readAck();
*varptr++ = i2c_readAck();
*varptr = i2c_readNak();
i2c_rep_start(I2C_GPS_ADDRESS<<1);
i2c_write(I2C_GPS_GROUND_SPEED);
i2c_rep_start((I2C_GPS_ADDRESS<<1)|1);
varptr = (uint8_t *)&GPS_speed; // speed in cm/s for OSD
*varptr++ = i2c_readAck();
*varptr = i2c_readAck();
varptr = (uint8_t *)&GPS_altitude; // altitude in meters for OSD
*varptr++ = i2c_readAck();
*varptr = i2c_readAck();
varptr = (uint8_t *)&GPS_ground_course;
*varptr++ = i2c_readAck();
*varptr = i2c_readNak();
} else {
return 0;
}
} else {
f.GPS_FIX = 0;
return 0;
}
#endif
#if defined(GPS_SERIAL) || defined(GPS_FROM_OSD)
#if defined(GPS_SERIAL)
uint8_t c = SerialAvailable(GPS_SERIAL);
if (c==0) return 0;
while (c--) {
if (GPS_newFrame(SerialRead(GPS_SERIAL))) {
#elif defined(GPS_FROM_OSD)
{
if(GPS_update & 2) { // Once second bit of GPS_update is set, indicate new GPS datas is readed from OSD - all in right format.
GPS_update &= 1; // We have: GPS_fix(0-2), GPS_numSat(0-15), GPS_coord[LAT & LON](signed, in 1/10 000 000 degres), GPS_altitude(signed, in meters) and GPS_speed(in cm/s)
#endif
GPS_Frame = 1;
}
}
#endif
return 1;
}
uint8_t GPS_Compute(void) {
if (GPS_Frame == 0) return 0; else GPS_Frame = 0;
if (GPS_update == 1) GPS_update = 0; else GPS_update = 1;
if (f.GPS_FIX && GPS_numSat >= 5) {
#if !defined(DONT_RESET_HOME_AT_ARM)
if (!f.ARMED) {f.GPS_FIX_HOME = 0;}
#endif
if (!f.GPS_FIX_HOME && f.ARMED) {
GPS_reset_home_position();
}
//Apply moving average filter to GPS data
#if defined(GPS_FILTERING)
GPS_filter_index = (GPS_filter_index+1) % GPS_FILTER_VECTOR_LENGTH;
for (uint8_t axis = 0; axis< 2; axis++) {
GPS_read[axis] = GPS_coord[axis]; //latest unfiltered data is in GPS_latitude and GPS_longitude
GPS_degree[axis] = GPS_read[axis] / 10000000; // get the degree to assure the sum fits to the int32_t
// How close we are to a degree line ? its the first three digits from the fractions of degree
// later we use it to Check if we are close to a degree line, if yes, disable averaging,
fraction3[axis] = (GPS_read[axis]- GPS_degree[axis]*10000000) / 10000;
GPS_filter_sum[axis] -= GPS_filter[axis][GPS_filter_index];
GPS_filter[axis][GPS_filter_index] = GPS_read[axis] - (GPS_degree[axis]*10000000);
GPS_filter_sum[axis] += GPS_filter[axis][GPS_filter_index];
GPS_filtered[axis] = GPS_filter_sum[axis] / GPS_FILTER_VECTOR_LENGTH + (GPS_degree[axis]*10000000);
if ( nav_mode == NAV_MODE_POSHOLD) { //we use gps averaging only in poshold mode...
if ( fraction3[axis]>1 && fraction3[axis]<999 ) GPS_coord[axis] = GPS_filtered[axis];
}
}
#endif
//dTnav calculation
//Time for calculating x,y speed and navigation pids
static uint32_t nav_loopTimer;
dTnav = (float)(millis() - nav_loopTimer)/ 1000.0;
nav_loopTimer = millis();
// prevent runup from bad GPS
dTnav = min(dTnav, 1.0);
//calculate distance and bearings for gui and other stuff continously - From home to copter
uint32_t dist;
int32_t dir;
GPS_distance_cm_bearing(&GPS_coord[LAT],&GPS_coord[LON],&GPS_home[LAT],&GPS_home[LON],&dist,&dir);
GPS_distanceToHome = dist/100;
GPS_directionToHome = dir/100;
if (!f.GPS_FIX_HOME) { //If we don't have home set, do not display anything
GPS_distanceToHome = 0;
GPS_directionToHome = 0;
}
//calculate the current velocity based on gps coordinates continously to get a valid speed at the moment when we start navigating
GPS_calc_velocity();
if (f.GPS_HOLD_MODE || f.GPS_HOME_MODE){ //ok we are navigating
//do gps nav calculations here, these are common for nav and poshold
#if defined(GPS_LEAD_FILTER)
GPS_distance_cm_bearing(&GPS_coord_lead[LAT],&GPS_coord_lead[LON],&GPS_WP[LAT],&GPS_WP[LON],&wp_distance,&target_bearing);
GPS_calc_location_error(&GPS_WP[LAT],&GPS_WP[LON],&GPS_coord_lead[LAT],&GPS_coord_lead[LON]);
#else
GPS_distance_cm_bearing(&GPS_coord[LAT],&GPS_coord[LON],&GPS_WP[LAT],&GPS_WP[LON],&wp_distance,&target_bearing);
GPS_calc_location_error(&GPS_WP[LAT],&GPS_WP[LON],&GPS_coord[LAT],&GPS_coord[LON]);
#endif
switch (nav_mode) {
case NAV_MODE_POSHOLD:
//Desired output is in nav_lat and nav_lon where 1deg inclination is 100
GPS_calc_poshold();
break;
case NAV_MODE_WP:
int16_t speed = GPS_calc_desired_speed(NAV_SPEED_MAX, NAV_SLOW_NAV); //slow navigation
// use error as the desired rate towards the target
//Desired output is in nav_lat and nav_lon where 1deg inclination is 100
GPS_calc_nav_rate(speed);
//Tail control
if (NAV_CONTROLS_HEADING) {
if (NAV_TAIL_FIRST) {
magHold = wrap_18000(nav_bearing-18000)/100;
} else {
magHold = nav_bearing/100;
}
}
// Are we there yet ?(within 2 meters of the destination)
if ((wp_distance <= GPS_wp_radius) || check_missed_wp()){ //if yes switch to poshold mode
nav_mode = NAV_MODE_POSHOLD;
if (NAV_SET_TAKEOFF_HEADING) { magHold = nav_takeoff_bearing; }
}
break;
}
} //end of gps calcs
}
}
void GPS_reset_home_position(void) {
if (f.GPS_FIX && GPS_numSat >= 5) {
GPS_home[LAT] = GPS_coord[LAT];
GPS_home[LON] = GPS_coord[LON];
GPS_calc_longitude_scaling(GPS_coord[LAT]); //need an initial value for distance and bearing calc
nav_takeoff_bearing = att.heading; //save takeoff heading
//Set ground altitude
f.GPS_FIX_HOME = 1;
}
}
//reset navigation (stop the navigation processor, and clear nav)
void GPS_reset_nav(void) {
uint8_t i;
for(i=0;i<2;i++) {
nav_rated[i] = 0;
nav[i] = 0;
reset_PID(&posholdPID[i]);
reset_PID(&poshold_ratePID[i]);
reset_PID(&navPID[i]);
nav_mode = NAV_MODE_NONE;
}
}
//Get the relevant P I D values and set the PID controllers
void GPS_set_pids(void) {
posholdPID_PARAM.kP = (float)conf.pid[PIDPOS].P8/100.0;
posholdPID_PARAM.kI = (float)conf.pid[PIDPOS].I8/100.0;
posholdPID_PARAM.Imax = POSHOLD_RATE_IMAX * 100;
poshold_ratePID_PARAM.kP = (float)conf.pid[PIDPOSR].P8/10.0;
poshold_ratePID_PARAM.kI = (float)conf.pid[PIDPOSR].I8/100.0;
poshold_ratePID_PARAM.kD = (float)conf.pid[PIDPOSR].D8/1000.0;
poshold_ratePID_PARAM.Imax = POSHOLD_RATE_IMAX * 100;
navPID_PARAM.kP = (float)conf.pid[PIDNAVR].P8/10.0;
navPID_PARAM.kI = (float)conf.pid[PIDNAVR].I8/100.0;
navPID_PARAM.kD = (float)conf.pid[PIDNAVR].D8/1000.0;
navPID_PARAM.Imax = POSHOLD_RATE_IMAX * 100;
}
void GPS_NewData(uint16_t c)
{
uint8_t axis;
static uint32_t nav_loopTimer;
uint32_t dist;
int32_t dir;
int16_t speed;
if (GPS_newFrame(c)) {
if (GPS_update == 1)
GPS_update = 0;
else
GPS_update = 1;
if (GPS_fix == 1 && GPS_numSat >= 5) {
if (armed == 0) {
GPS_fix_home = 0;
}
if (GPS_fix_home == 0 && armed) {
GPS_fix_home = 1;
GPS_home[LAT] = GPS_coord[LAT];
GPS_home[LON] = GPS_coord[LON];
GPS_calc_longitude_scaling(GPS_coord[LAT]); // need an initial value for distance and bearing calc
nav_takeoff_bearing = heading; // save takeoff heading
}
// Apply moving average filter to GPS data
#if defined(GPS_FILTERING)
GPS_filter_index = ++GPS_filter_index % GPS_FILTER_VECTOR_LENGTH;
for (axis = 0; axis < 2; axis++) {
GPS_read[axis] = GPS_coord[axis]; // latest unfiltered data is in GPS_latitude and GPS_longitude
GPS_degree[axis] = GPS_read[axis] / 10000000; // get the degree to assure the sum fits to the int32_t
// How close we are to a degree line ? its the first three digits from the fractions of degree
// later we use it to Check if we are close to a degree line, if yes, disable averaging,
fraction3[axis] = (GPS_read[axis] - GPS_degree[axis] * 10000000) / 10000;
GPS_filter_sum[axis] -= GPS_filter[axis][GPS_filter_index];
GPS_filter[axis][GPS_filter_index] = GPS_read[axis] - (GPS_degree[axis] * 10000000);
GPS_filter_sum[axis] += GPS_filter[axis][GPS_filter_index];
GPS_filtered[axis] = GPS_filter_sum[axis] / GPS_FILTER_VECTOR_LENGTH + (GPS_degree[axis] * 10000000);
if (nav_mode == NAV_MODE_POSHOLD) { //we use gps averaging only in poshold mode...
if (fraction3[axis] > 1 && fraction3[axis] < 999)
GPS_coord[axis] = GPS_filtered[axis];
}
}
#endif
// dTnav calculation
// Time for calculating x,y speed and navigation pids
dTnav = (float) (millis() - nav_loopTimer) / 1000.0f;
nav_loopTimer = millis();
// prevent runup from bad GPS
dTnav = min(dTnav, 1.0f);
// calculate distance and bearings for gui and other stuff continously - From home to copter
GPS_distance_cm_bearing(&GPS_coord[LAT], &GPS_coord[LON], &GPS_home[LAT], &GPS_home[LON], &dist, &dir);
GPS_distanceToHome = dist / 100;
GPS_directionToHome = dir / 100;
//calculate the current velocity based on gps coordinates continously to get a valid speed at the moment when we start navigating
GPS_calc_velocity();
if (GPSModeHold == 1 || GPSModeHome == 1) { // ok we are navigating
// do gps nav calculations here, these are common for nav and poshold
GPS_distance_cm_bearing(&GPS_coord[LAT], &GPS_coord[LON], &GPS_WP[LAT], &GPS_WP[LON], &wp_distance, &target_bearing);
GPS_calc_location_error(&GPS_WP[LAT], &GPS_WP[LON], &GPS_coord[LAT], &GPS_coord[LON]);
switch (nav_mode) {
case NAV_MODE_POSHOLD:
// Desired output is in nav_lat and nav_lon where 1deg inclination is 100
GPS_calc_poshold();
break;
case NAV_MODE_WP:
speed = GPS_calc_desired_speed(cfg.nav_speed_max, NAV_SLOW_NAV); //slow navigation
// use error as the desired rate towards the target
// Desired output is in nav_lat and nav_lon where 1deg inclination is 100
GPS_calc_nav_rate(speed);
// Tail control
if (cfg.nav_controls_heading) {
if (NAV_TAIL_FIRST) {
magHold = wrap_18000(nav_bearing - 18000) / 100;
} else {
magHold = nav_bearing / 100;
}
}
// Are we there yet ?(within x meters of the destination)
if ((wp_distance <= cfg.gps_wp_radius) || check_missed_wp()) { // if yes switch to poshold mode
nav_mode = NAV_MODE_POSHOLD;
if (NAV_SET_TAKEOFF_HEADING) {
magHold = nav_takeoff_bearing;
}
}
break;
}
} //end of gps calcs
}
}
}
/***********************
函数功能：GPS数据更新,将由串口中断调用，在GPS初始化时传入了
***********************/
static void GPS_NewData(void)
{
int axis;
static uint32_t nav_loopTimer; //记录上一次的循环的时间戳
uint32_t dist; //距离
int32_t dir; //方向
int16_t speed; //速度
SensorsSet(SENSOR_GPS); //置位GPS存在标志
if(GPS_update == 1)
GPS_update = 0;
else
GPS_update = 1;
if(f.GPS_FIX && GPS_numSat >= 5)//如果数据有效和卫星数大于5
{
if(!f.ARMED)
{
f.GPS_FIX_HOME = 0;//在没有解锁状态下，清楚GPS HOME点
}
if(!f.GPS_FIX_HOME && f.ARMED)//在没有GPS原点又已经解锁了，则设置原点
{
f.GPS_FIX_HOME = 1;//标记有原点
GPS_home[LAT] = GPS_coord[LAT];//将当前经纬度记录下
GPS_home[LON] = GPS_coord[LON];
GPS_calc_longitude_scaling(GPS_coord[LAT]); //得到一个初始值用于计算距离和方位
nav_takeoff_bearing = heading; // save takeoff heading
XbeePro_ImportanceInfo = XbeePro_ImportanceInfo | 0x10;//发送HOME点给上位机
}
//进行滤波，美其名曰滑动平均滤波
GPS_filter_index = (GPS_filter_index + 1) % GPS_FILTER_VECTOR_LENGTH;
for (axis = 0; axis < 2; axis++) //axis=0时为纬度，=1时为经度
{
GPS_read[axis] = GPS_coord[axis]; //得到最新的未过滤的经纬度
GPS_degree[axis] = GPS_read[axis] / 10000000; //得到经纬度的度
// How close we are to a degree line ? its the first three digits from the fractions of degree
// later we use it to Check if we are close to a degree line, if yes, disable averaging,
fraction3[axis] = (GPS_read[axis] - GPS_degree[axis] * 10000000) / 10000;//得到小数点后三位的分,即0.xxx度的xxx
GPS_filter_sum[axis] -= GPS_filter[axis][GPS_filter_index];
GPS_filter[axis][GPS_filter_index] = GPS_read[axis] - (GPS_degree[axis] * 10000000);
GPS_filter_sum[axis] += GPS_filter[axis][GPS_filter_index];
GPS_filtered[axis] = GPS_filter_sum[axis] / GPS_FILTER_VECTOR_LENGTH + (GPS_degree[axis] * 10000000);
if (nav_mode == NAV_MODE_POSHOLD) //我们只在poshold模式下使用GPS平均值 nav_mode == NAV_MODE_POSHOLD
{
if (fraction3[axis] > 1 && fraction3[axis] < 999)
GPS_coord[axis] = GPS_filtered[axis]; //将滤波后的值保存
}
}
//进入计算 x,y 、速度、航向 的PID等
dTnav = (float) (TimMsGet() - nav_loopTimer) / 1000.0f;//计算两次之间的时间差 现在单位为s
nav_loopTimer = TimMsGet(); //记录时间戳 单位为ms
dTnav = min(dTnav, 1.0f); //防止GPS出错，产生超长时间差(不大于1S)
//计算距离、方位给GUI，从原点到灰机的
GPS_distance_cm_bearing(&GPS_coord[LAT], &GPS_coord[LON], &GPS_home[LAT], &GPS_home[LON], &dist, &dir);
GPS_distanceToHome = dist / 100; //将单位变为米
GPS_directionToHome = dir / 100; //现在单位是度了
//计算基于GPS的速率，当我们有启动导航
GPS_calc_velocity();
if(f.GPS_HOLD_MODE || f.GPS_HOME_MODE) //悬停或者返回原点模式，则启动导航哈
{
if(GS_Nav) // 地面站有新导航任务 GS_Nav标志置一 ReadyForNextWP置一 ReadyToMove = 0; nav_mode = NAV_MODE_POSHOLD; wp=0;
{
if(ReadyForNextWP) //已经到达航点，为下一个航点做准备
{
if(AutoHeading==0) //如果不需要自动转向 就直接飞向下一个航点
{
ReadyToMove = 1; //这样就不会执行下面的转向和等待转向
}
if(ReadyToMove) // 如果转向完毕，或不需要转向，则设定下一个航点并开启飞航线模式
{
Set_nextwp();
nav_mode = NAV_MODE_WP;
pid_nav_crosstrack._integrator = 0;
pid_nav_crosstrack._last_input = 0;
pid_nav_crosstrack._last_derivative = 0;
}
else //执行自动转向
{
magHold = GPS_BearingForNextwp(&GPS_coord[LAT], &GPS_coord[LON], &Waypoint[wp][LAT], &Waypoint[wp][LON]);//计算下个点的方位角
magHold /=100; //切记切记
// if(abs(heading - magHold) < 10 || abs(heading - magHold) > 350) //航向调整完再走 nav_bearing/100
// {
ReadyToMove = 1;
// }
}
}
}
//GPS导航计算
GPS_distance_cm_bearing(&GPS_coord[LAT], &GPS_coord[LON], &GPS_WP[LAT], &GPS_WP[LON], &wp_distance, &target_bearing);//计算直线距离和方位角
GPS_calc_location_error(&GPS_WP[LAT], &GPS_WP[LON], &GPS_coord[LAT], &GPS_coord[LON]);//得到X,Y距离
switch (nav_mode)
{
case NAV_MODE_POSHOLD: //位置保持模式
GPS_calc_poshold();
break;
case NAV_MODE_WP:
// if(Waypoint[wp+1][0]==0)
speed = GPS_calc_desired_speed(NAV_Speed, true);//只有到最后一个点才减速
// else
// speed = GPS_calc_desired_speed(NAV_Speed, false); // cfg.nav_speed_max
// use error as the desired rate towards the target
// 期望的输出是在导航纬度和经度,1度倾向是100
GPS_calc_nav_rate(speed);
//方向控制，即调整YAW
if (AutoHeading)
{
#if (NAV_TAIL_FIRST)
magHold = wrap_18000(target_bearing - 18000) / 100;
#else
magHold = target_bearing / 100; // nav_bearing
#endif
}
//判断是否到达目的地（在一个允许的半径内）
if ((wp_distance <= cfg.gps_wp_radius) || check_missed_wp()) //暂时是2米半径
{
// nav_mode = NAV_MODE_POSHOLD;//如果到达或失去目标则进入悬停
ReadyForNextWP=1;
ReadyToMove = 1 ;
if(Waypoint[wp][LAT]==0) //没有下一个航点了
{
nav_mode = NAV_MODE_POSHOLD;//如果到达或失去目标则进入悬停
GPS_hold[LAT] = GPS_WP[LAT]; //更新hold点坐标
GPS_hold[LON] = GPS_WP[LON];
XbeePro_ImportanceInfo = XbeePro_ImportanceInfo | 0x01;//发送HOLD点给上位机
ReadyForNextWP=0;
GS_Nav = 0; //没有新航点时 ，保证不更行航点
if (NAV_SET_TAKEOFF_HEADING)//是否保持与起飞时的方向相同
{
magHold = nav_takeoff_bearing;
}
}
}
else
{
ReadyForNextWP = 0; //不要更新航点
}
break;
}
}
}
}
void fw_nav(void)
{
int16_t GPS_Heading = GPS_ground_course; // Store current bearing
int16_t Current_Heading; // Store current bearing
int16_t altDiff = 0;
uint8_t RTH_Alt = cfg.fw_rth_alt; // Min Altitude to keep during RTH. (Max 200m)
int16_t delta[2] = { 0, 0 }; // D-Term
static int16_t NAV_deltaSum, ALT_deltaSum, GPS_FwTarget, GPS_AltErr, NAV_Thro;
int16_t TX_Thro = rcData[THROTTLE]; // Read and store Throttle pos.
int16_t navDiff; // Navigation error
float navDT;
static uint32_t nav_loopT;
int16_t groundSpeed;
int spDiff;
uint8_t i;
// Nav timer
static uint32_t gpsTimer = 0;
static uint16_t gpsFreq = 1000 / GPS_UPD_HZ; // 5HZ 200ms DT
// Calculated Altitude over home in meters
int16_t currAlt = GPS_altitude - GPS_home[ALT]; // GPS
int16_t navTargetAlt = GPS_hold[ALT] - GPS_home[ALT]; // Diff from homeAlt.
// Handles ReSetting RTH alt if rth is enabled to low!
if (f.CLIMBOUT_FW && currAlt < RTH_Alt)
GPS_hold[ALT] = GPS_home[ALT] + RTH_Alt;
// Wrap GPS_Heading 1800
GPS_Heading = wrap_18000(GPS_Heading * 10) / 10;
// Only use MAG if Mag and GPS_Heading aligns
if (sensors(SENSOR_MAG)) {
if (abs(heading - (GPS_Heading / 10)) > 10 && GPS_speed > 200)
Current_Heading = GPS_Heading / 10;
else
Current_Heading = heading;
} else
Current_Heading = GPS_Heading / 10;
// Calculate Navigation errors
GPS_FwTarget = nav_bearing / 100;
navDiff = GPS_FwTarget - Current_Heading; // Navigation Error
GPS_AltErr = currAlt - navTargetAlt; // Altitude error Negative means you're to low
// Start of NavTimer
if (millis() - gpsTimer >= gpsFreq) {
gpsTimer = millis();
// Throttle control
// Deadpan for throttle at correct Alt.
if (abs(GPS_AltErr) < 1) // Just cruise along in deadpan.
NAV_Thro = cfg.fw_cruise_throttle;
else
// Add AltitudeError and scale up with a factor to throttle
NAV_Thro = constrain(cfg.fw_cruise_throttle - (GPS_AltErr * cfg.fw_scaler_throttle), cfg.fw_idle_throttle, cfg.fw_climb_throttle);
// Reset Climbout Flag when Alt have been reached
if (f.CLIMBOUT_FW && GPS_AltErr >= 0)
f.CLIMBOUT_FW = 0;
// Climb out before RTH
if (f.GPS_HOME_MODE) {
if (f.CLIMBOUT_FW) {
GPS_AltErr = -(cfg.fw_gps_maxclimb * 10); // Max climbAngle
NAV_Thro = cfg.fw_climb_throttle; // Max Allowed Throttle
if (currAlt < SAFE_NAV_ALT)
navDiff = 0; // Force climb with Level Wings below safe Alt
}
if ((GPS_distanceToHome < SAFE_DECSCEND_ZONE) && currAlt > RTH_Alt)
GPS_hold[ALT] = GPS_home[ALT] + RTH_Alt; // Start descend to correct RTH Alt.
}
// Always DISARM when Home is within 10 meters if FC is in failsafe.
if (f.FW_FAILSAFE_RTH_ENABLE && (GPS_distanceToHome < 10)) {
f.ARMED = 0;
f.CLIMBOUT_FW = 0; // Abort Climbout
GPS_hold[ALT] = GPS_home[ALT] + 5; // Come down
}
// Filtering of navDiff around home to stop nervous servos
if (GPS_distanceToHome < 10)
navDiff *= 0.1f;
// Wrap Heading 180
navDiff = wrap_18000(navDiff * 100) / 100;
if (abs(navDiff) > 170)
navDiff = 175; // Forced turn.
// PID for Navigating planes.
navDT = (float) (millis() - nav_loopT) / 1000;
nav_loopT = millis();
// Altitude PID
if (abs(GPS_AltErr) <= 3)
altErrorI *= navDT; // Remove I-Term in deadspan
GPS_AltErr *= 10;
altErrorI += (GPS_AltErr * altPID_PARAM.kI) * navDT; // Acumulate I from PIDPOSR
altErrorI = constrain(altErrorI, -500, 500); // limits I term influence
delta[0] = (GPS_AltErr - lastAltDiff);
lastAltDiff = GPS_AltErr;
if (abs(delta[0]) > 100)
delta[0] = 0;
for (i = 0; i < GPS_UPD_HZ; i++)
altHist[i] = altHist[i + 1];
altHist[GPS_UPD_HZ - 1] = delta[0];
// Store 1 sec history for D-term in shift register
ALT_deltaSum = 0; // Sum History
for (i = 0; i < GPS_UPD_HZ; i++)
ALT_deltaSum += altHist[i];
ALT_deltaSum = (ALT_deltaSum * altPID_PARAM.kD) / navDT;
altDiff = GPS_AltErr * altPID_PARAM.kP; // Add P in Elevator compensation.
altDiff += (altErrorI); // Add I
// Start of NavPID
if (abs(navDiff) <= 3)
navErrorI *= navDT; // Remove I-Term in deadspan
navDiff *= 10;
navErrorI += (navDiff * navPID_PARAM.kI) * navDT;
navErrorI = constrain(navErrorI, -500, 500);
delta[1] = (navDiff - lastnavDiff);
lastnavDiff = navDiff;
if (abs(delta[1]) > 100)
delta[1] = 0;
// Store 1 sec history for D-term in shift register
for (i = 0; i < GPS_UPD_HZ; i++)
navDif[i] = navDif[i + 1];
navDif[GPS_UPD_HZ - 1] = delta[1];
NAV_deltaSum = 0; // Sum History
for (i = 0; i < GPS_UPD_HZ; i++)
NAV_deltaSum += navDif[i];
NAV_deltaSum = (NAV_deltaSum * navPID_PARAM.kD) / navDT; // Add D
navDiff *= navPID_PARAM.kP; // Add P
navDiff += navErrorI; // Add I
// End of NavPID
// Limit outputs
GPS_angle[PITCH] = constrain(altDiff / 10, -cfg.fw_gps_maxclimb * 10, cfg.fw_gps_maxdive * 10) + ALT_deltaSum;
GPS_angle[ROLL] = constrain(navDiff / 10, -cfg.fw_gps_maxcorr * 10, cfg.fw_gps_maxcorr * 10) + NAV_deltaSum;
GPS_angle[YAW] = constrain(navDiff / 10, -cfg.fw_gps_rudder * 10, cfg.fw_gps_rudder * 10) + NAV_deltaSum;
// Elevator compensation depending on behaviour.
// Prevent stall with Disarmed motor
if (f.MOTORS_STOPPED)
GPS_angle[PITCH] = constrain(GPS_angle[PITCH], 0, cfg.fw_gps_maxdive * 10);
// Add elevator compared with rollAngle
if (!f.CLIMBOUT_FW)
GPS_angle[PITCH] -= (abs(angle[ROLL]) * cfg.fw_roll_comp);
// Throttle compensation depending on behaviour.
// Compensate throttle with pitch Angle
NAV_Thro -= constrain(angle[PITCH] * PITCH_COMP, 0, 450);
NAV_Thro = constrain(NAV_Thro, cfg.fw_idle_throttle, cfg.fw_climb_throttle);
// Force the Plane move forward in headwind with speedBoost
groundSpeed = GPS_speed;
spDiff = (GPS_MINSPEED - groundSpeed) * I_TERM;
if (GPS_speed < GPS_MINSPEED - 50 || GPS_speed > GPS_MINSPEED + 50)
speedBoost += spDiff;
speedBoost = constrain(speedBoost, 0, 500);
NAV_Thro += speedBoost;
}
// End of NavTimer
// PassThru for throttle In AcroMode
if ((!f.ANGLE_MODE && !f.HORIZON_MODE) || (f.PASSTHRU_MODE && !f.FW_FAILSAFE_RTH_ENABLE)) {
NAV_Thro = TX_Thro;
GPS_angle[PITCH] = 0;
GPS_angle[ROLL] = 0;
GPS_angle[YAW] = 0;
}
rcCommand[THROTTLE] = NAV_Thro;
rcCommand[YAW] += GPS_angle[YAW];
}
void onGpsNewData(void)
{
int axis;
static uint32_t nav_loopTimer;
uint16_t speed;
if (!(STATE(GPS_FIX) && GPS_numSat >= 5)) {
return;
}
if (!ARMING_FLAG(ARMED))
DISABLE_STATE(GPS_FIX_HOME);
if (!STATE(GPS_FIX_HOME) && ARMING_FLAG(ARMED))
GPS_reset_home_position();
// Apply moving average filter to GPS data
#if defined(GPS_FILTERING)
GPS_filter_index = (GPS_filter_index + 1) % GPS_FILTER_VECTOR_LENGTH;
for (axis = 0; axis < 2; axis++) {
GPS_read[axis] = GPS_coord[axis]; // latest unfiltered data is in GPS_latitude and GPS_longitude
GPS_degree[axis] = GPS_read[axis] / 10000000; // get the degree to assure the sum fits to the int32_t
// How close we are to a degree line ? its the first three digits from the fractions of degree
// later we use it to Check if we are close to a degree line, if yes, disable averaging,
fraction3[axis] = (GPS_read[axis] - GPS_degree[axis] * 10000000) / 10000;
GPS_filter_sum[axis] -= GPS_filter[axis][GPS_filter_index];
GPS_filter[axis][GPS_filter_index] = GPS_read[axis] - (GPS_degree[axis] * 10000000);
GPS_filter_sum[axis] += GPS_filter[axis][GPS_filter_index];
GPS_filtered[axis] = GPS_filter_sum[axis] / GPS_FILTER_VECTOR_LENGTH + (GPS_degree[axis] * 10000000);
if (nav_mode == NAV_MODE_POSHOLD) { // we use gps averaging only in poshold mode...
if (fraction3[axis] > 1 && fraction3[axis] < 999)
GPS_coord[axis] = GPS_filtered[axis];
}
}
#endif
//
// Calculate time delta for navigation loop, range 0-1.0f, in seconds
//
// Time for calculating x,y speed and navigation pids
dTnav = (float)(millis() - nav_loopTimer) / 1000.0f;
nav_loopTimer = millis();
// prevent runup from bad GPS
dTnav = min(dTnav, 1.0f);
GPS_calculateDistanceAndDirectionToHome();
// calculate the current velocity based on gps coordinates continously to get a valid speed at the moment when we start navigating
GPS_calc_velocity();
if (FLIGHT_MODE(GPS_HOLD_MODE) || FLIGHT_MODE(GPS_HOME_MODE)) {
// we are navigating
// gps nav calculations, these are common for nav and poshold
GPS_distance_cm_bearing(&GPS_coord[LAT], &GPS_coord[LON], &GPS_WP[LAT], &GPS_WP[LON], &wp_distance, &target_bearing);
GPS_calc_location_error(&GPS_WP[LAT], &GPS_WP[LON], &GPS_coord[LAT], &GPS_coord[LON]);
switch (nav_mode) {
case NAV_MODE_POSHOLD:
// Desired output is in nav_lat and nav_lon where 1deg inclination is 100
GPS_calc_poshold();
break;
case NAV_MODE_WP:
speed = GPS_calc_desired_speed(gpsProfile->nav_speed_max, NAV_SLOW_NAV); // slow navigation
// use error as the desired rate towards the target
// Desired output is in nav_lat and nav_lon where 1deg inclination is 100
GPS_calc_nav_rate(speed);
// Tail control
if (gpsProfile->nav_controls_heading) {
if (NAV_TAIL_FIRST) {
magHold = wrap_18000(nav_bearing - 18000) / 100;
} else {
magHold = nav_bearing / 100;
}
}
// Are we there yet ?(within x meters of the destination)
if ((wp_distance <= gpsProfile->gps_wp_radius) || check_missed_wp()) { // if yes switch to poshold mode
nav_mode = NAV_MODE_POSHOLD;
if (NAV_SET_TAKEOFF_HEADING) {
magHold = nav_takeoff_bearing;
}
}
break;
default:
break;
}
} //end of gps calcs
}
void GPS_NewData(void) {
static uint32_t nav_loopTimer;
uint32_t dist;
int32_t dir;
uint8_t axis;
int16_t speed;
uint16_t c = GPSBufferAvailable();
while (c--) {
if (GPS_newFrame(GPSBufferRead())) {
if (GPS_Info.GPS_update == 1)
GPS_Info.GPS_update = 0;
else
GPS_Info.GPS_update = 1;
if (fgps.GPS_FIX && GPS_Info.GPS_numSat >= 5) {
if (!checkArm()) {
fgps.GPS_FIX_HOME = 0;
}
if (!fgps.GPS_FIX_HOME && checkArm()) {
GPS_reset_home_position();
}
//Apply moving average filter to GPS data
#if defined(GPS_FILTERING)
GPS_filter_index = (GPS_filter_index+1) % GPS_FILTER_VECTOR_LENGTH;
for (axis = 0; axis< 2; axis++) {
GPS_data[axis] = GPS_Info.GPS_coord[axis]; //latest unfiltered data is in GPS_latitude and GPS_longitude
GPS_degree[axis] = GPS_data[axis] / 10000000; // get the degree to assure the sum fits to the int32_t
// How close we are to a degree line ? its the first three digits from the fractions of degree
// later we use it to Check if we are close to a degree line, if yes, disable averaging,
fraction3[axis] = (GPS_data[axis]- GPS_degree[axis]*10000000) / 10000;
GPS_filter_sum[axis] -= GPS_filter[axis][GPS_filter_index];
GPS_filter[axis][GPS_filter_index] = GPS_data[axis] - (GPS_degree[axis]*10000000);
GPS_filter_sum[axis] += GPS_filter[axis][GPS_filter_index];
GPS_filtered[axis] = GPS_filter_sum[axis] / GPS_FILTER_VECTOR_LENGTH + (GPS_degree[axis]*10000000);
if ( nav_mode == NAV_MODE_POSHOLD) { //we use gps averaging only in poshold mode...
if ( fraction3[axis]>1 && fraction3[axis]<999 )
GPS_Info.GPS_coord[axis] = GPS_filtered[axis];
}
}
#endif
//Time for calculating x,y speed and navigation pids
dTnav = (float)(getTickCount() - nav_loopTimer)/ 10000.0f;
nav_loopTimer = getTickCount();
// prevent runup from bad GPS
dTnav = min(dTnav, 1.0f);
//calculate distance and bearings for gui and other stuff continously - From home to copter
GPS_distance_cm_bearing(&GPS_Info.GPS_coord[LAT],&GPS_Info.GPS_coord[LON],&GPS_Info.GPS_home[LAT],&GPS_Info.GPS_home[LON],&dist,&dir);
GPS_Info.GPS_distanceToHome = dist/100;
GPS_Info.GPS_directionToHome = dir/100;
if (!fgps.GPS_FIX_HOME) { //If we don't have home set, do not display anything
GPS_Info.GPS_distanceToHome = 0;
GPS_Info.GPS_directionToHome = 0;
}
//calculate the current velocity based on gps coordinates continously to get a valid speed at the moment when we start navigating
GPS_calc_velocity();
if (fgps.GPS_HOLD_MODE || fgps.GPS_HOME_MODE){ //ok we are navigating
//do gps nav calculations here, these are common for nav and poshold
#if defined(GPS_LEAD_FILTER)
GPS_distance_cm_bearing(&GPS_coord_lead[LAT],&GPS_coord_lead[LON],&GPS_WP[LAT],&GPS_WP[LON],&wp_distance,&target_bearing);
GPS_calc_location_error(&GPS_WP[LAT],&GPS_WP[LON],&GPS_coord_lead[LAT],&GPS_coord_lead[LON]);
#else
GPS_distance_cm_bearing(&GPS_coord[LAT],&GPS_coord[LON],&GPS_WP[LAT],&GPS_WP[LON],&wp_distance,&target_bearing);
GPS_calc_location_error(&GPS_WP[LAT],&GPS_WP[LON],&GPS_coord[LAT],&GPS_coord[LON]);
#endif
switch (nav_mode) {
case NAV_MODE_POSHOLD:
//Desired output is in nav_lat and nav_lon where 1deg inclination is 100
GPS_calc_poshold();
break;
case NAV_MODE_WP:
speed = GPS_calc_desired_speed(NAV_SPEED_MAX, NAV_SLOW_NAV); //slow navigation
// use error as the desired rate towards the target
//Desired output is in nav_lat and nav_lon where 1deg inclination is 100
GPS_calc_nav_rate(speed);
//Tail control
if (NAV_CONTROLS_HEADING) {
if (NAV_TAIL_FIRST) {
magHold = wrap_18000(nav_bearing-18000)/100;
} else {
magHold = nav_bearing/100;
}
}
// Are we there yet ?(within 2 meters of the destination)
if ((wp_distance <= GPS_wp_radius) || check_missed_wp()){ //if yes switch to poshold mode
nav_mode = NAV_MODE_POSHOLD;
if (NAV_SET_TAKEOFF_HEADING) { magHold = nav_takeoff_bearing; }
}
break;
}
} //end of gps calcs
}
}
}
}
/*******************************************************************************
** Main Function main()
*******************************************************************************/
int main (void)
{
/* Basic chip initialization is taken care of in SystemInit() called
* from the startup code. SystemInit() and chip settings are defined
* in the CMSIS system_<part family>.c file.
*/
setup();
static uint8_t rcDelayCommand; // this indicates the number of time (multiple of RC measurement at 50Hz) the sticks must be maintained to run or switch off motors
uint8_t axis,i;
int16_t delta,deltaSum;
int16_t PTerm,ITerm,DTerm;
static int16_t lastGyro[3] = {0,0,0};
static int16_t delta1[3],delta2[3];
static int16_t errorAngleI[2] = {0,0};
static uint32_t rcTime = 0;
static int16_t initialThrottleHold;
int16_t error,errorAngle =0;
#if PIDcontroller ==1
static int16_t errorGyroI[3] = {0,0,0};
#elif PIDcontroller == 2
int32_t AngleRateTmp = 0, RateError = 0, AngleITerm = 0;
static int32_t errorGyroI[3] = {0,0,0};
#endif
#define RC_FREQ 50
while(1)
{
#ifdef LCD_TELEMETRY_STEP
static char telemetryStepSequence [] = LCD_TELEMETRY_STEP;
static uint8_t telemetryStepIndex = 0;
#endif
#if defined(SPEKTRUM)
if (rcFrameComplete) computeRC();
#endif
#if defined(OPENLRSv2MULTI)
Read_OpenLRS_RC();
#endif
if ((currentTime > rcTime) || rcTime > (currentTime + 20000)) { // 50Hz + additional check to ensure rcTime can reach currentTime
rcTime = currentTime + 20000;
computeRC();
//reset watchdog timer in RC loop to ensure user is not locked out of control
feedWatchDog();
// Failsafe routine - added by MIS
#if defined(FAILSAFE)
if ( failsafeCnt > (5*FAILSAVE_DELAY) && f.ARMED) { // Stabilize, and set Throttle to specified level
for(i=0; i<3; i++) rcData[i] = MIDRC; // after specified guard time after RC signal is lost (in 0.1sec)
rcData[THROTTLE] = FAILSAVE_THROTTLE;
if (failsafeCnt > 5*(FAILSAVE_DELAY+FAILSAVE_OFF_DELAY)) { // Turn OFF motors after specified Time (in 0.1sec)
f.ARMED = 0; // This will prevent the copter to automatically rearm if failsafe shuts it down and prevents
f.OK_TO_ARM = 0; // to restart accidentely by just reconnect to the tx - you will have to switch off first to rearm
}
failsafeEvents++;
}
if ( failsafeCnt > (5*FAILSAVE_DELAY) && !f.ARMED) { //Turn of "Ok To arm to prevent the motors from spinning after repowering the RX with low throttle and aux to arm
f.ARMED = 0; // This will prevent the copter to automatically rearm if failsafe shuts it down and prevents
f.OK_TO_ARM = 0; // to restart accidentely by just reconnect to the tx - you will have to switch off first to rearm
}
failsafeCnt++;
#endif
// end of failsave routine - next change is made with RcOptions setting
if (rcData[THROTTLE] < MINCHECK) {
errorGyroI[ROLL] = 0; errorGyroI[PITCH] = 0; errorGyroI[YAW] = 0;
errorAngleI[ROLL] = 0; errorAngleI[PITCH] = 0;
rcDelayCommand++;
if (rcData[YAW] < MINCHECK && rcData[PITCH] < MINCHECK && !f.ARMED) {
if (rcDelayCommand == 20) {
calibratingG=400;
#if GPS
GPS_reset_home_position();
#endif
}
} else if (rcData[YAW] > MAXCHECK && rcData[PITCH] > MAXCHECK && !f.ARMED) {
if (rcDelayCommand == 20) {
#ifdef TRI
servo[5] = 1500; // we center the yaw servo in conf mode
writeServos();
#endif
#ifdef FLYING_WING
servo[0] = conf.wing_left_mid;
servo[1] = conf.wing_right_mid;
writeServos();
#endif
#ifdef AIRPLANE
for(i = 4; i<7 ;i++) servo[i] = 1500;
writeServos();
#endif
#if defined(LCD_CONF)
configurationLoop(); // beginning LCD configuration
#endif
previousTime = micros();
}
}
#if defined(INFLIGHT_ACC_CALIBRATION)
else if (!f.ARMED && rcData[YAW] < MINCHECK && rcData[PITCH] > MAXCHECK && rcData[ROLL] > MAXCHECK){
if (rcDelayCommand == 20){
if (AccInflightCalibrationMeasurementDone){ // trigger saving into eeprom after landing
AccInflightCalibrationMeasurementDone = 0;
AccInflightCalibrationSavetoEEProm = 1;
}else{
AccInflightCalibrationArmed = !AccInflightCalibrationArmed;
#if defined(BUZZER)
if (AccInflightCalibrationArmed){
toggleBeep = 2;
} else {
toggleBeep = 3;
}
#endif
}
}
}
#endif
else if (conf.activate[BOXARM] > 0) {
if ( rcOptions[BOXARM] && f.OK_TO_ARM
#if defined(FAILSAFE)
&& failsafeCnt <= 1
#endif
) {
f.ARMED = 1;
headFreeModeHold = heading;
} else if (f.ARMED) f.ARMED = 0;
rcDelayCommand = 0;
#ifdef ALLOW_ARM_DISARM_VIA_TX_YAW
} else if ( (rcData[YAW] < MINCHECK ) && f.ARMED) {
if (rcDelayCommand == 20) f.ARMED = 0; // rcDelayCommand = 20 => 20x20ms = 0.4s = time to wait for a specific RC command to be acknowledged
} else if ( (rcData[YAW] > MAXCHECK ) && rcData[PITCH] < MAXCHECK && !f.ARMED && calibratingG == 0 && f.ACC_CALIBRATED) {
if (rcDelayCommand == 20) {
f.ARMED = 1;
headFreeModeHold = heading;
}
#endif
#ifdef ALLOW_ARM_DISARM_VIA_TX_ROLL
} else if ( (rcData[ROLL] < MINCHECK) && f.ARMED) {
if (rcDelayCommand == 20) f.ARMED = 0; // rcDelayCommand = 20 => 20x20ms = 0.4s = time to wait for a specific RC command to be acknowledged
} else if ( (rcData[ROLL] > MAXCHECK) && rcData[PITCH] < MAXCHECK && !f.ARMED && calibratingG == 0 && f.ACC_CALIBRATED) {
if (rcDelayCommand == 20) {
f.ARMED = 1;
headFreeModeHold = heading;
}
#endif
#ifdef LCD_TELEMETRY_AUTO
} else if (rcData[ROLL] < MINCHECK && rcData[PITCH] > MAXCHECK && !f.ARMED) {
if (rcDelayCommand == 20) {
if (telemetry_auto) {
telemetry_auto = 0;
telemetry = 0;
} else
telemetry_auto = 1;
}
#endif
#ifdef LCD_TELEMETRY_STEP
} else if (rcData[ROLL] > MAXCHECK && rcData[PITCH] > MAXCHECK && !f.ARMED) {
if (rcDelayCommand == 20) {
telemetry = telemetryStepSequence[++telemetryStepIndex % strlen(telemetryStepSequence)];
LCDclear(); // make sure to clear away remnants
}
#endif
} else
rcDelayCommand = 0;
} else if (rcData[THROTTLE] > MAXCHECK && !f.ARMED) {
if (rcData[YAW] < MINCHECK && rcData[PITCH] < MINCHECK) { // throttle=max, yaw=left, pitch=min
if (rcDelayCommand == 20) calibratingA=400;
rcDelayCommand++;
} else if (rcData[YAW] > MAXCHECK && rcData[PITCH] < MINCHECK) { // throttle=max, yaw=right, pitch=min
if (rcDelayCommand == 20) f.CALIBRATE_MAG = 1; // MAG calibration request
rcDelayCommand++;
} else if (rcData[PITCH] > MAXCHECK) {
conf.angleTrim[PITCH]+=2;writeParams(1);
#if defined(LED_RING)
blinkLedRing();
#endif
} else if (rcData[PITCH] < MINCHECK) {
conf.angleTrim[PITCH]-=2;writeParams(1);
#if defined(LED_RING)
blinkLedRing();
#endif
} else if (rcData[ROLL] > MAXCHECK) {
conf.angleTrim[ROLL]+=2;writeParams(1);
#if defined(LED_RING)
blinkLedRing();
#endif
} else if (rcData[ROLL] < MINCHECK) {
conf.angleTrim[ROLL]-=2;writeParams(1);
#if defined(LED_RING)
blinkLedRing();
#endif
} else {
rcDelayCommand = 0;
}
}
#if defined(LED_FLASHER)
led_flasher_autoselect_sequence();
#endif
#if defined(INFLIGHT_ACC_CALIBRATION)
if (AccInflightCalibrationArmed && f.ARMED && rcData[THROTTLE] > MINCHECK && !rcOptions[BOXARM] ){ // Copter is airborne and you are turning it off via boxarm : start measurement
InflightcalibratingA = 50;
AccInflightCalibrationArmed = 0;
}
if (rcOptions[BOXPASSTHRU]) { // Use the Passthru Option to activate : Passthru = TRUE Meausrement started, Land and passtrhu = 0 measurement stored
if (!AccInflightCalibrationActive && !AccInflightCalibrationMeasurementDone){
InflightcalibratingA = 50;
}
}else if(AccInflightCalibrationMeasurementDone && !f.ARMED){
AccInflightCalibrationMeasurementDone = 0;
AccInflightCalibrationSavetoEEProm = 1;
}
#endif
uint16_t auxState = 0;
for(i=0;i<4;i++)
auxState |= (rcData[AUX1+i]<1300)<<(3*i) | (1300<rcData[AUX1+i] && rcData[AUX1+i]<1700)<<(3*i+1) | (rcData[AUX1+i]>1700)<<(3*i+2);
for(i=0;i<CHECKBOXITEMS;i++)
rcOptions[i] = (auxState & conf.activate[i])>0;
// note: if FAILSAFE is disable, failsafeCnt > 5*FAILSAVE_DELAY is always false
if (( rcOptions[BOXACC] || (failsafeCnt > 5*FAILSAVE_DELAY) ) && ACC ) {
// bumpless transfer to Level mode
if (!f.ACC_MODE) {
errorAngleI[ROLL] = 0; errorAngleI[PITCH] = 0;
f.ACC_MODE = 1;
}
} else {
// failsafe support
f.ACC_MODE = 0;
}
if (rcOptions[BOXARM] == 0) f.OK_TO_ARM = 1;
//if (f.ACC_MODE) {STABLEPIN_ON;} else {STABLEPIN_OFF;}
#if BARO
if (rcOptions[BOXBARO]) {
if (!f.BARO_MODE) {
f.BARO_MODE = 1;
AltHold = EstAlt;
initialThrottleHold = rcCommand[THROTTLE];
errorAltitudeI = 0;
BaroPID=0;
}
} else {
f.BARO_MODE = 0;
}
#endif
#if MAG
if (rcOptions[BOXMAG]) {
if (!f.MAG_MODE) {
f.MAG_MODE = 1;
magHold = heading;
}
} else {
f.MAG_MODE = 0;
}
if (rcOptions[BOXHEADFREE]) {
if (!f.HEADFREE_MODE) {
f.HEADFREE_MODE = 1;
}
} else {
f.HEADFREE_MODE = 0;
}
if (rcOptions[BOXHEADADJ]) {
headFreeModeHold = heading; // acquire new heading
}
#endif
#if GPS
#if defined(I2C_NAV)
static uint8_t GPSNavReset = 1;
if (f.GPS_FIX && GPS_numSat >= 5 ) {
if (!rcOptions[BOXGPSHOME] && !rcOptions[BOXGPSHOLD] )
{ //Both boxes are unselected
if (GPSNavReset == 0 ) {
GPSNavReset = 1;
GPS_reset_nav();
}
}
if (rcOptions[BOXGPSHOME]) {
if (!f.GPS_HOME_MODE) {
f.GPS_HOME_MODE = 1;
GPSNavReset = 0;
GPS_I2C_command(I2C_GPS_COMMAND_START_NAV,0); //waypoint zero
}
} else {
f.GPS_HOME_MODE = 0;
}
if (rcOptions[BOXGPSHOLD]) {
if (!f.GPS_HOLD_MODE & !f.GPS_HOME_MODE) {
f.GPS_HOLD_MODE = 1;
GPSNavReset = 0;
GPS_I2C_command(I2C_GPS_COMMAND_POSHOLD,0);
}
} else {
f.GPS_HOLD_MODE = 0;
}
}
#endif
#if defined(GPS_SERIAL) || defined(TINY_GPS) || defined(GPS_FROM_OSD)||defined(I2C_GPS)
if (f.GPS_FIX && GPS_numSat >= 5 ) {
if (rcOptions[BOXGPSHOME]) {
if (!f.GPS_HOME_MODE) {
f.GPS_HOME_MODE = 1;
GPS_set_next_wp(&GPS_home[LAT],&GPS_home[LON]);
nav_mode = NAV_MODE_WP;
}
} else {
f.GPS_HOME_MODE = 0;
}
if (rcOptions[BOXGPSHOLD]) {
if (!f.GPS_HOLD_MODE) {
f.GPS_HOLD_MODE = 1;
GPS_hold[LAT] = GPS_coord[LAT];
GPS_hold[LON] = GPS_coord[LON];
GPS_set_next_wp(&GPS_hold[LAT],&GPS_hold[LON]);
nav_mode = NAV_MODE_POSHOLD;
}
} else {
f.GPS_HOLD_MODE = 0;
}
}
#endif
#endif
#ifdef FLOW
if(rcOptions[BOXFLOWHOLD])
{
if (!f.FLOW_HOLD_MODE)
{
f.FLOW_HOLD_MODE = 1;
GPS_hold[LAT] = GPS_coord[LAT];
GPS_hold[LON] = GPS_coord[LON];
flow_set_next_wp(&GPS_hold[LAT],&GPS_hold[LON]);
nav_mode = NAV_MODE_POSHOLD;
}
//debug[1] = 1;
}
else
{
f.FLOW_HOLD_MODE = 0;
//debug[1] = 0;
}
#endif
if (rcOptions[BOXPASSTHRU]) {f.PASSTHRU_MODE = 1;}
else {f.PASSTHRU_MODE = 0;}
#ifdef FIXEDWING
f.HEADFREE_MODE = 0;
#endif
} else { // not in rc loop
static uint8_t taskOrder=0; // never call all functions in the same loop, to avoid high delay spikes
if(taskOrder>4) taskOrder-=5;
switch (taskOrder) {
case 0:
taskOrder++;
#if MAG
if (Mag_getADC()) break; // max 350 µs (HMC5883) // only break when we actually did something
#endif
case 1:
taskOrder++;
#if BARO
if (Baro_update() != 0 ) break;
#endif
case 2:
taskOrder++;
#if BARO
if (getEstimatedAltitude() !=0) break;
#endif
case 3:
taskOrder++;
if(flowUpdate() !=0) break;
#if GPS
if(GPS_Enable) GPS_NewData();
break;
#endif
case 4:
taskOrder++;
#if SONAR
#if !defined(MAXSONAR_PWM) && !defined(FLOW)
Sonar_update();
#endif
//debug[2] = sonarAlt;
#endif
#ifdef LANDING_LIGHTS_DDR
auto_switch_landing_lights();
#endif
#ifdef VARIOMETER
if (f.VARIO_MODE) vario_signaling();
#endif
break;
}
}
computeIMU();
// Measure loop rate just afer reading the sensors
currentTime = micros();
cycleTime = currentTime - previousTime;
previousTime = currentTime;
//delayMs(500);
//if(cycleTime > 3150)
// debug[0]++;
#if MAG
if (fabs(rcCommand[YAW]) <70 && f.MAG_MODE) {
int16_t dif = heading - magHold;
if (dif <= - 180) dif += 360;
if (dif >= + 180) dif -= 360;
if ( f.SMALL_ANGLES_25 ) rcCommand[YAW] -= dif*conf.P8[PIDMAG]/30; // 18 deg
} else magHold = heading;
#endif
#if BARO
if (f.BARO_MODE) {
if (fabs(rcCommand[THROTTLE]-initialThrottleHold)>ALT_HOLD_THROTTLE_NEUTRAL_ZONE) {
f.BARO_MODE = 0; // so that a new althold reference is defined
}
rcCommand[THROTTLE] = initialThrottleHold + BaroPID;
}
#endif
#if GPS
if ( (!f.GPS_HOME_MODE && !f.GPS_HOLD_MODE) || !f.GPS_FIX_HOME ) {
GPS_reset_nav(); // If GPS is not activated. Reset nav loops and all nav related parameters
GPS_angle[ROLL] = 0;
GPS_angle[PITCH] = 0;
} else {
float sin_yaw_y = sinf(heading*0.0174532925f);
float cos_yaw_x = cosf(heading*0.0174532925f);
#if defined(NAV_SLEW_RATE)
nav_rated[LON] += constrain(wrap_18000(nav[LON]-nav_rated[LON]),-NAV_SLEW_RATE,NAV_SLEW_RATE);
nav_rated[LAT] += constrain(wrap_18000(nav[LAT]-nav_rated[LAT]),-NAV_SLEW_RATE,NAV_SLEW_RATE);
GPS_angle[ROLL] = (nav_rated[LON]*cos_yaw_x - nav_rated[LAT]*sin_yaw_y) /10;
GPS_angle[PITCH] = (nav_rated[LON]*sin_yaw_y + nav_rated[LAT]*cos_yaw_x) /10;
#else
GPS_angle[ROLL] = (nav[LON]*cos_yaw_x - nav[LAT]*sin_yaw_y) /10;
GPS_angle[PITCH] = (nav[LON]*sin_yaw_y + nav[LAT]*cos_yaw_x) /10;
#endif
}
//debug[2] = GPS_angle[ROLL];
//debug[3] = GPS_angle[PITCH];
#endif
#ifdef FLOW
if (!f.FLOW_HOLD_MODE) {
flow_reset_nav(); // If GPS is not activated. Reset nav loops and all nav related parameters
GPS_angle[ROLL] = 0;
GPS_angle[PITCH] = 0;
} else {
float sin_yaw_y = sinf(heading*0.0174532925f);
float cos_yaw_x = cosf(heading*0.0174532925f);
#if defined(NAV_SLEW_RATE)
nav_rated[LON] += constrain(wrap_18000(nav[LON]-nav_rated[LON]),-NAV_SLEW_RATE,NAV_SLEW_RATE);
nav_rated[LAT] += constrain(wrap_18000(nav[LAT]-nav_rated[LAT]),-NAV_SLEW_RATE,NAV_SLEW_RATE);
GPS_angle[ROLL] = (nav_rated[LON]*cos_yaw_x - nav_rated[LAT]*sin_yaw_y) /10;
GPS_angle[PITCH] = (nav_rated[LON]*sin_yaw_y + nav_rated[LAT]*cos_yaw_x) /10;
#else
GPS_angle[ROLL] = (nav[LON]*cos_yaw_x - nav[LAT]*sin_yaw_y) /10;
GPS_angle[PITCH] = (nav[LON]*sin_yaw_y + nav[LAT]*cos_yaw_x) /10;
#endif
}
//debug[2] = GPS_angle[ROLL];
//debug[3] = GPS_angle[PITCH];
#endif
#if PIDcontroller == 1
//**** PITCH & ROLL & YAW PID ****
for(axis=0;axis<3;axis++) {
if (f.ACC_MODE && axis<2 ) { //LEVEL MODE
// 50 degrees max inclination
errorAngle = constrain(2*rcCommand[axis] + GPS_angle[axis],-500,+500) - angle[axis] + conf.angleTrim[axis]; //16 bits is ok here
#ifdef LEVEL_PDF
PTerm = -(int32_t)angle[axis]*conf.P8[PIDLEVEL]/100 ;
#else
PTerm = (int32_t)errorAngle*conf.P8[PIDLEVEL]/100 ; // 32 bits is needed for calculation: errorAngle*P8[PIDLEVEL] could exceed 32768 16 bits is ok for result
#endif
PTerm = constrain(PTerm,-conf.D8[PIDLEVEL]*5,+conf.D8[PIDLEVEL]*5);
errorAngleI[axis] = constrain(errorAngleI[axis]+errorAngle,-10000,+10000); // WindUp //16 bits is ok here
ITerm = ((int32_t)errorAngleI[axis]*conf.I8[PIDLEVEL])>>12; // 32 bits is needed for calculation:10000*I8 could exceed 32768 16 bits is ok for result
} else { //ACRO MODE or YAW axis
if (fabs(rcCommand[axis])<350) error = rcCommand[axis]*10*8/conf.P8[axis] ; // 16 bits is needed for calculation: 350*10*8 = 28000 16 bits is ok for result if P8>2 (P>0.2)
else error = (int32_t)rcCommand[axis]*10*8/conf.P8[axis] ; // 32 bits is needed for calculation: 500*5*10*8 = 200000 16 bits is ok for result if P8>2 (P>0.2)
error -= gyroData[axis];
PTerm = rcCommand[axis];
errorGyroI[axis] = constrain(errorGyroI[axis]+error,-16000,+16000); // WindUp 16 bits is ok here
if (fabs(gyroData[axis])>640) errorGyroI[axis] = 0;
ITerm = (errorGyroI[axis]/125*conf.I8[axis])>>6; // 16 bits is ok here 16000/125 = 128 ; 128*250 = 32000
}
if (fabs(gyroData[axis])<160) PTerm -= gyroData[axis]*dynP8[axis]/10/8; // 16 bits is needed for calculation 160*200 = 32000 16 bits is ok for result
else PTerm -= (int32_t)gyroData[axis]*dynP8[axis]/10/8; // 32 bits is needed for calculation
delta = gyroData[axis] - lastGyro[axis]; // 16 bits is ok here, the dif between 2 consecutive gyro reads is limited to 800
lastGyro[axis] = gyroData[axis];
deltaSum = delta1[axis]+delta2[axis]+delta;
delta2[axis] = delta1[axis];
delta1[axis] = delta;
if (fabs(deltaSum)<640) DTerm = (deltaSum*dynD8[axis])>>5; // 16 bits is needed for calculation 640*50 = 32000 16 bits is ok for result
else DTerm = ((int32_t)deltaSum*dynD8[axis])>>5; // 32 bits is needed for calculation