// althold_init - initialise althold controller
bool Sub::althold_init()
{
if(!control_check_barometer()) {
return false;
}
// initialize vertical speeds and leash lengths
// sets the maximum speed up and down returned by position controller
pos_control.set_max_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control.set_max_accel_z(g.pilot_accel_z);
// initialise position and desired velocity
pos_control.set_alt_target(inertial_nav.get_altitude());
pos_control.set_desired_velocity_z(inertial_nav.get_velocity_z());
last_pilot_heading = ahrs.yaw_sensor;
return true;
}
// circle_init - initialise circle controller flight mode
bool Sub::circle_init()
{
if (!position_ok()) {
return false;
}
circle_pilot_yaw_override = false;
// initialize speeds and accelerations
pos_control.set_speed_xy(wp_nav.get_speed_xy());
pos_control.set_accel_xy(wp_nav.get_wp_acceleration());
pos_control.set_jerk_xy_to_default();
pos_control.set_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control.set_accel_z(g.pilot_accel_z);
// initialise circle controller including setting the circle center based on vehicle speed
circle_nav.init();
return true;
}
// circle_init - initialise circle controller flight mode
bool Copter::ModeCircle::init(bool ignore_checks)
{
if (copter.position_ok() || ignore_checks) {
pilot_yaw_override = false;
// initialize speeds and accelerations
pos_control->set_speed_xy(wp_nav->get_speed_xy());
pos_control->set_accel_xy(wp_nav->get_wp_acceleration());
pos_control->set_jerk_xy_to_default();
pos_control->set_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control->set_accel_z(g.pilot_accel_z);
// initialise circle controller including setting the circle center based on vehicle speed
copter.circle_nav->init();
return true;
}else{
return false;
}
}
// get_pilot_desired_climb_rate - transform pilot's throttle input to climb rate in cm/s
// without any deadzone at the bottom
float Copter::get_pilot_desired_climb_rate(float throttle_control)
{
// throttle failsafe check
if( failsafe.radio ) {
return 0.0f;
}
#if TOY_MODE_ENABLED == ENABLED
if (g2.toy_mode.enabled()) {
// allow throttle to be reduced after throttle arming and for
// slower descent close to the ground
g2.toy_mode.throttle_adjust(throttle_control);
}
#endif
float desired_rate = 0.0f;
float mid_stick = get_throttle_mid();
float deadband_top = mid_stick + g.throttle_deadzone;
float deadband_bottom = mid_stick - g.throttle_deadzone;
// ensure a reasonable throttle value
throttle_control = constrain_float(throttle_control,0.0f,1000.0f);
// ensure a reasonable deadzone
g.throttle_deadzone = constrain_int16(g.throttle_deadzone, 0, 400);
// check throttle is above, below or in the deadband
if (throttle_control < deadband_bottom) {
// below the deadband
desired_rate = get_pilot_speed_dn() * (throttle_control-deadband_bottom) / deadband_bottom;
}else if (throttle_control > deadband_top) {
// above the deadband
desired_rate = g.pilot_speed_up * (throttle_control-deadband_top) / (1000.0f-deadband_top);
}else{
// must be in the deadband
desired_rate = 0.0f;
}
return desired_rate;
}
// loiter_init - initialise loiter controller
bool Copter::ModeLoiter::init(bool ignore_checks)
{
if (copter.position_ok() || ignore_checks) {
// set target to current position
wp_nav->init_loiter_target();
// initialize vertical speed and acceleration
pos_control->set_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control->set_accel_z(g.pilot_accel_z);
// initialise position and desired velocity
if (!pos_control->is_active_z()) {
pos_control->set_alt_target_to_current_alt();
pos_control->set_desired_velocity_z(inertial_nav.get_velocity_z());
}
return true;
}else{
return false;
}
}
// flowhold_init - initialise flowhold controller
bool Copter::ModeFlowHold::init(bool ignore_checks)
{
#if FRAME_CONFIG == HELI_FRAME
// do not allow helis to enter Flow Hold if the Rotor Runup is not complete
if (!ignore_checks && !motors->rotor_runup_complete()){
return false;
}
#endif
if (!copter.optflow.enabled() || !copter.optflow.healthy()) {
return false;
}
// initialize vertical speeds and leash lengths
copter.pos_control->set_max_speed_z(-get_pilot_speed_dn(), copter.g.pilot_speed_up);
copter.pos_control->set_max_accel_z(copter.g.pilot_accel_z);
// initialise position and desired velocity
if (!copter.pos_control->is_active_z()) {
copter.pos_control->set_alt_target_to_current_alt();
copter.pos_control->set_desired_velocity_z(copter.inertial_nav.get_velocity_z());
}
flow_filter.set_cutoff_frequency(copter.scheduler.get_loop_rate_hz(), flow_filter_hz.get());
quality_filtered = 0;
flow_pi_xy.reset_I();
limited = false;
flow_pi_xy.set_dt(1.0/copter.scheduler.get_loop_rate_hz());
// start with INS height
last_ins_height = copter.inertial_nav.get_altitude() * 0.01;
height_offset = 0;
return true;
}
// flowhold_run - runs the flowhold controller
// should be called at 100hz or more
void Copter::ModeFlowHold::run()
{
FlowHoldModeState flowhold_state;
float takeoff_climb_rate = 0.0f;
update_height_estimate();
// initialize vertical speeds and acceleration
copter.pos_control->set_max_speed_z(-get_pilot_speed_dn(), copter.g.pilot_speed_up);
copter.pos_control->set_max_accel_z(copter.g.pilot_accel_z);
// apply SIMPLE mode transform to pilot inputs
copter.update_simple_mode();
// check for filter change
if (!is_equal(flow_filter.get_cutoff_freq(), flow_filter_hz.get())) {
flow_filter.set_cutoff_frequency(flow_filter_hz.get());
}
// get pilot desired climb rate
float target_climb_rate = copter.get_pilot_desired_climb_rate(copter.channel_throttle->get_control_in());
target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), copter.g.pilot_speed_up);
// get pilot's desired yaw rate
float target_yaw_rate = copter.get_pilot_desired_yaw_rate(copter.channel_yaw->get_control_in());
if (!copter.motors->armed() || !copter.motors->get_interlock()) {
flowhold_state = FlowHold_MotorStopped;
} else if (takeoff.running() || takeoff.triggered(target_climb_rate)) {
flowhold_state = FlowHold_Takeoff;
} else if (!copter.ap.auto_armed || copter.ap.land_complete) {
flowhold_state = FlowHold_Landed;
} else {
flowhold_state = FlowHold_Flying;
}
if (copter.optflow.healthy()) {
const float filter_constant = 0.95;
quality_filtered = filter_constant * quality_filtered + (1-filter_constant) * copter.optflow.quality();
} else {
quality_filtered = 0;
}
Vector2f bf_angles;
// calculate alt-hold angles
int16_t roll_in = copter.channel_roll->get_control_in();
int16_t pitch_in = copter.channel_pitch->get_control_in();
float angle_max = copter.attitude_control->get_althold_lean_angle_max();
get_pilot_desired_lean_angles(bf_angles.x, bf_angles.y,angle_max, attitude_control->get_althold_lean_angle_max());
if (quality_filtered >= flow_min_quality &&
AP_HAL::millis() - copter.arm_time_ms > 3000) {
// don't use for first 3s when we are just taking off
Vector2f flow_angles;
flowhold_flow_to_angle(flow_angles, (roll_in != 0) || (pitch_in != 0));
flow_angles.x = constrain_float(flow_angles.x, -angle_max/2, angle_max/2);
flow_angles.y = constrain_float(flow_angles.y, -angle_max/2, angle_max/2);
bf_angles += flow_angles;
}
bf_angles.x = constrain_float(bf_angles.x, -angle_max, angle_max);
bf_angles.y = constrain_float(bf_angles.y, -angle_max, angle_max);
// Flow Hold State Machine
switch (flowhold_state) {
case FlowHold_MotorStopped:
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
#if FRAME_CONFIG == HELI_FRAME
// force descent rate and call position controller
copter.pos_control->set_alt_target_from_climb_rate(-abs(copter.g.land_speed), copter.G_Dt, false);
#else
copter.attitude_control->reset_rate_controller_I_terms();
copter.attitude_control->set_yaw_target_to_current_heading();
copter.pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
#endif
flow_pi_xy.reset_I();
copter.pos_control->update_z_controller();
break;
case FlowHold_Takeoff:
// set motors to full range
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// initiate take-off
if (!takeoff.running()) {
takeoff.start(constrain_float(g.pilot_takeoff_alt,0.0f,1000.0f));
// indicate we are taking off
copter.set_land_complete(false);
// clear i terms
copter.set_throttle_takeoff();
}
// get take-off adjusted pilot and takeoff climb rates
takeoff.get_climb_rates(target_climb_rate, takeoff_climb_rate);
// get avoidance adjusted climb rate
target_climb_rate = copter.get_avoidance_adjusted_climbrate(target_climb_rate);
// call attitude controller
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
// call position controller
copter.pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, copter.G_Dt, false);
copter.pos_control->add_takeoff_climb_rate(takeoff_climb_rate, copter.G_Dt);
copter.pos_control->update_z_controller();
break;
case FlowHold_Landed:
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle)
if (target_climb_rate < 0.0f) {
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_SPIN_WHEN_ARMED);
} else {
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
copter.attitude_control->reset_rate_controller_I_terms();
copter.attitude_control->set_yaw_target_to_current_heading();
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
copter.pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
copter.pos_control->update_z_controller();
break;
case FlowHold_Flying:
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
#if AC_AVOID_ENABLED == ENABLED
// apply avoidance
copter.avoid.adjust_roll_pitch(bf_angles.x, bf_angles.y, copter.aparm.angle_max);
#endif
// call attitude controller
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
// adjust climb rate using rangefinder
target_climb_rate = copter.get_surface_tracking_climb_rate(target_climb_rate, copter.pos_control->get_alt_target(), copter.G_Dt);
// get avoidance adjusted climb rate
target_climb_rate = copter.get_avoidance_adjusted_climbrate(target_climb_rate);
// call position controller
copter.pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, copter.G_Dt, false);
copter.pos_control->update_z_controller();
break;
}
}
// loiter_run - runs the loiter controller
// should be called at 100hz or more
void Copter::ModeLoiter::run()
{
float target_roll, target_pitch;
float target_yaw_rate = 0.0f;
float target_climb_rate = 0.0f;
float takeoff_climb_rate = 0.0f;
// initialize vertical speed and acceleration
pos_control->set_max_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control->set_max_accel_z(g.pilot_accel_z);
// process pilot inputs unless we are in radio failsafe
if (!copter.failsafe.radio) {
// apply SIMPLE mode transform to pilot inputs
update_simple_mode();
// convert pilot input to lean angles
get_pilot_desired_lean_angles(target_roll, target_pitch, loiter_nav->get_angle_max_cd(), attitude_control->get_althold_lean_angle_max());
// process pilot's roll and pitch input
loiter_nav->set_pilot_desired_acceleration(target_roll, target_pitch, G_Dt);
// get pilot's desired yaw rate
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
// get pilot desired climb rate
target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up);
} else {
// clear out pilot desired acceleration in case radio failsafe event occurs and we do not switch to RTL for some reason
loiter_nav->clear_pilot_desired_acceleration();
}
// relax loiter target if we might be landed
if (ap.land_complete_maybe) {
loiter_nav->soften_for_landing();
}
// Loiter State Machine Determination
AltHoldModeState loiter_state = get_alt_hold_state(target_climb_rate);
// Loiter State Machine
switch (loiter_state) {
case AltHold_MotorStopped:
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
loiter_nav->init_target();
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(loiter_nav->get_roll(), loiter_nav->get_pitch(), target_yaw_rate);
pos_control->update_z_controller();
break;
case AltHold_Takeoff:
// initiate take-off
if (!takeoff.running()) {
takeoff.start(constrain_float(g.pilot_takeoff_alt,0.0f,1000.0f));
// indicate we are taking off
set_land_complete(false);
// clear i term when we're taking off
set_throttle_takeoff();
}
// get takeoff adjusted pilot and takeoff climb rates
takeoff.get_climb_rates(target_climb_rate, takeoff_climb_rate);
// get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// run loiter controller
loiter_nav->update();
// call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(loiter_nav->get_roll(), loiter_nav->get_pitch(), target_yaw_rate);
// update altitude target and call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt);
pos_control->update_z_controller();
break;
case AltHold_Landed_Ground_Idle:
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
// FALLTHROUGH
case AltHold_Landed_Pre_Takeoff:
loiter_nav->init_target();
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0.0f, 0.0f, 0.0f);
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller();
break;
case AltHold_Flying:
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DesiredSpoolState::THROTTLE_UNLIMITED);
#if PRECISION_LANDING == ENABLED
if (do_precision_loiter()) {
precision_loiter_xy();
}
#endif
// run loiter controller
loiter_nav->update();
// call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(loiter_nav->get_roll(), loiter_nav->get_pitch(), target_yaw_rate);
// adjust climb rate using rangefinder
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
// get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->update_z_controller();
break;
}
}
// sport_run - runs the sport controller
// should be called at 100hz or more
void Copter::ModeSport::run()
{
SportModeState sport_state;
float takeoff_climb_rate = 0.0f;
// initialize vertical speed and acceleration
pos_control->set_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control->set_accel_z(g.pilot_accel_z);
// apply SIMPLE mode transform
update_simple_mode();
// get pilot's desired roll and pitch rates
// calculate rate requests
float target_roll_rate = channel_roll->get_control_in() * g.acro_rp_p;
float target_pitch_rate = channel_pitch->get_control_in() * g.acro_rp_p;
// get attitude targets
const Vector3f att_target = attitude_control->get_att_target_euler_cd();
// Calculate trainer mode earth frame rate command for roll
int32_t roll_angle = wrap_180_cd(att_target.x);
target_roll_rate -= constrain_int32(roll_angle, -ACRO_LEVEL_MAX_ANGLE, ACRO_LEVEL_MAX_ANGLE) * g.acro_balance_roll;
// Calculate trainer mode earth frame rate command for pitch
int32_t pitch_angle = wrap_180_cd(att_target.y);
target_pitch_rate -= constrain_int32(pitch_angle, -ACRO_LEVEL_MAX_ANGLE, ACRO_LEVEL_MAX_ANGLE) * g.acro_balance_pitch;
AP_Vehicle::MultiCopter &aparm = copter.aparm;
if (roll_angle > aparm.angle_max){
target_roll_rate -= g.acro_rp_p*(roll_angle-aparm.angle_max);
}else if (roll_angle < -aparm.angle_max) {
target_roll_rate -= g.acro_rp_p*(roll_angle+aparm.angle_max);
}
if (pitch_angle > aparm.angle_max){
target_pitch_rate -= g.acro_rp_p*(pitch_angle-aparm.angle_max);
}else if (pitch_angle < -aparm.angle_max) {
target_pitch_rate -= g.acro_rp_p*(pitch_angle+aparm.angle_max);
}
// get pilot's desired yaw rate
float target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
// get pilot desired climb rate
float target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up);
// State Machine Determination
if (!motors->armed() || !motors->get_interlock()) {
sport_state = Sport_MotorStopped;
} else if (takeoff_state.running || takeoff_triggered(target_climb_rate)) {
sport_state = Sport_Takeoff;
} else if (!ap.auto_armed || ap.land_complete) {
sport_state = Sport_Landed;
} else {
sport_state = Sport_Flying;
}
// State Machine
switch (sport_state) {
case Sport_MotorStopped:
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate);
#if FRAME_CONFIG == HELI_FRAME
// force descent rate and call position controller
pos_control->set_alt_target_from_climb_rate(-abs(g.land_speed), G_Dt, false);
#else
attitude_control->relax_attitude_controllers();
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
#endif
pos_control->update_z_controller();
break;
case Sport_Takeoff:
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// initiate take-off
if (!takeoff_state.running) {
takeoff_timer_start(constrain_float(g.pilot_takeoff_alt,0.0f,1000.0f));
// indicate we are taking off
set_land_complete(false);
// clear i terms
set_throttle_takeoff();
}
// get take-off adjusted pilot and takeoff climb rates
takeoff_get_climb_rates(target_climb_rate, takeoff_climb_rate);
// get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// call attitude controller
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate);
// call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt);
pos_control->update_z_controller();
break;
case Sport_Landed:
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle)
if (target_climb_rate < 0.0f) {
motors->set_desired_spool_state(AP_Motors::DESIRED_SPIN_WHEN_ARMED);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate);
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller();
break;
case Sport_Flying:
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// call attitude controller
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate);
// adjust climb rate using rangefinder
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
// get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->update_z_controller();
break;
}
}
// circle_run - runs the circle flight mode
// should be called at 100hz or more
void Sub::circle_run()
{
float target_yaw_rate = 0;
float target_climb_rate = 0;
// update parameters, to allow changing at runtime
pos_control.set_max_speed_xy(wp_nav.get_default_speed_xy());
pos_control.set_max_accel_xy(wp_nav.get_wp_acceleration());
pos_control.set_max_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control.set_max_accel_z(g.pilot_accel_z);
// if not armed set throttle to zero and exit immediately
if (!motors.armed()) {
// To-Do: add some initialisation of position controllers
motors.set_desired_spool_state(AP_Motors::DesiredSpoolState::GROUND_IDLE);
// Sub vehicles do not stabilize roll/pitch/yaw when disarmed
attitude_control.set_throttle_out(0,true,g.throttle_filt);
attitude_control.relax_attitude_controllers();
pos_control.set_alt_target_to_current_alt();
return;
}
// process pilot inputs
// get pilot's desired yaw rate
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
if (!is_zero(target_yaw_rate)) {
circle_pilot_yaw_override = true;
}
// get pilot desired climb rate
target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
// set motors to full range
motors.set_desired_spool_state(AP_Motors::DesiredSpoolState::THROTTLE_UNLIMITED);
// run circle controller
circle_nav.update();
///////////////////////
// update xy outputs //
float lateral_out, forward_out;
translate_circle_nav_rp(lateral_out, forward_out);
// Send to forward/lateral outputs
motors.set_lateral(lateral_out);
motors.set_forward(forward_out);
// call attitude controller
if (circle_pilot_yaw_override) {
attitude_control.input_euler_angle_roll_pitch_euler_rate_yaw(channel_roll->get_control_in(), channel_pitch->get_control_in(), target_yaw_rate);
} else {
attitude_control.input_euler_angle_roll_pitch_yaw(channel_roll->get_control_in(), channel_pitch->get_control_in(), circle_nav.get_yaw(), true);
}
// adjust climb rate using rangefinder
if (rangefinder_alt_ok()) {
// if rangefinder is ok, use surface tracking
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control.get_alt_target(), G_Dt);
}
// update altitude target and call position controller
pos_control.set_alt_target_from_climb_rate(target_climb_rate, G_Dt, false);
pos_control.update_z_controller();
}
// althold_run - runs the althold controller
// should be called at 100hz or more
void Sub::althold_run()
{
uint32_t tnow = AP_HAL::millis();
// initialize vertical speeds and acceleration
pos_control.set_max_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control.set_max_accel_z(g.pilot_accel_z);
if (!motors.armed()) {
motors.set_desired_spool_state(AP_Motors::DesiredSpoolState::GROUND_IDLE);
// Sub vehicles do not stabilize roll/pitch/yaw when not auto-armed (i.e. on the ground, pilot has never raised throttle)
attitude_control.set_throttle_out(0,true,g.throttle_filt);
attitude_control.relax_attitude_controllers();
pos_control.relax_alt_hold_controllers(motors.get_throttle_hover());
last_pilot_heading = ahrs.yaw_sensor;
return;
}
motors.set_desired_spool_state(AP_Motors::DesiredSpoolState::THROTTLE_UNLIMITED);
// get pilot desired lean angles
float target_roll, target_pitch;
// Check if set_attitude_target_no_gps is valid
if (tnow - sub.set_attitude_target_no_gps.last_message_ms < 5000) {
float target_yaw;
Quaternion(
set_attitude_target_no_gps.packet.q
).to_euler(
target_roll,
target_pitch,
target_yaw
);
target_roll = degrees(target_roll);
target_pitch = degrees(target_pitch);
target_yaw = degrees(target_yaw);
attitude_control.input_euler_angle_roll_pitch_yaw(target_roll * 1e2f, target_pitch * 1e2f, target_yaw * 1e2f, true);
return;
}
get_pilot_desired_lean_angles(channel_roll->get_control_in(), channel_pitch->get_control_in(), target_roll, target_pitch, attitude_control.get_althold_lean_angle_max());
// get pilot's desired yaw rate
float target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
// call attitude controller
if (!is_zero(target_yaw_rate)) { // call attitude controller with rate yaw determined by pilot input
attitude_control.input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
last_pilot_heading = ahrs.yaw_sensor;
last_pilot_yaw_input_ms = tnow; // time when pilot last changed heading
} else { // hold current heading
// this check is required to prevent bounce back after very fast yaw maneuvers
// the inertia of the vehicle causes the heading to move slightly past the point when pilot input actually stopped
if (tnow < last_pilot_yaw_input_ms + 250) { // give 250ms to slow down, then set target heading
target_yaw_rate = 0; // Stop rotation on yaw axis
// call attitude controller with target yaw rate = 0 to decelerate on yaw axis
attitude_control.input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
last_pilot_heading = ahrs.yaw_sensor; // update heading to hold
} else { // call attitude controller holding absolute absolute bearing
attitude_control.input_euler_angle_roll_pitch_yaw(target_roll, target_pitch, last_pilot_heading, true);
}
}
// Hold actual position until zero derivative is detected
static bool engageStopZ = true;
// Get last user velocity direction to check for zero derivative points
static bool lastVelocityZWasNegative = false;
if (fabsf(channel_throttle->norm_input()-0.5f) > 0.05f) { // Throttle input above 5%
// output pilot's throttle
attitude_control.set_throttle_out(channel_throttle->norm_input(), false, g.throttle_filt);
// reset z targets to current values
pos_control.relax_alt_hold_controllers();
engageStopZ = true;
lastVelocityZWasNegative = is_negative(inertial_nav.get_velocity_z());
} else { // hold z
if (ap.at_bottom) {
pos_control.relax_alt_hold_controllers(); // clear velocity and position targets
pos_control.set_alt_target(inertial_nav.get_altitude() + 10.0f); // set target to 10 cm above bottom
} else if (rangefinder_alt_ok()) {
// if rangefinder is ok, use surface tracking
float target_climb_rate = get_surface_tracking_climb_rate(0, pos_control.get_alt_target(), G_Dt);
pos_control.set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
}
// Detects a zero derivative
// When detected, move the altitude set point to the actual position
// This will avoid any problem related to joystick delays
// or smaller input signals
if(engageStopZ && (lastVelocityZWasNegative ^ is_negative(inertial_nav.get_velocity_z()))) {
engageStopZ = false;
pos_control.relax_alt_hold_controllers();
}
pos_control.update_z_controller();
}
motors.set_forward(channel_forward->norm_input());
motors.set_lateral(channel_lateral->norm_input());
}
// loiter_run - runs the loiter controller
// should be called at 100hz or more
void Copter::ModeLoiter::run()
{
LoiterModeState loiter_state;
float target_yaw_rate = 0.0f;
float target_climb_rate = 0.0f;
float takeoff_climb_rate = 0.0f;
// initialize vertical speed and acceleration
pos_control->set_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control->set_accel_z(g.pilot_accel_z);
// process pilot inputs unless we are in radio failsafe
if (!copter.failsafe.radio) {
// apply SIMPLE mode transform to pilot inputs
update_simple_mode();
// process pilot's roll and pitch input
wp_nav->set_pilot_desired_acceleration(channel_roll->get_control_in(), channel_pitch->get_control_in());
// get pilot's desired yaw rate
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
// get pilot desired climb rate
target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up);
} else {
// clear out pilot desired acceleration in case radio failsafe event occurs and we do not switch to RTL for some reason
wp_nav->clear_pilot_desired_acceleration();
}
// relax loiter target if we might be landed
if (ap.land_complete_maybe) {
wp_nav->loiter_soften_for_landing();
}
// Loiter State Machine Determination
if (!motors->armed() || !motors->get_interlock()) {
loiter_state = Loiter_MotorStopped;
} else if (takeoff_state.running || takeoff_triggered(target_climb_rate)) {
loiter_state = Loiter_Takeoff;
} else if (!ap.auto_armed || ap.land_complete) {
loiter_state = Loiter_Landed;
} else {
loiter_state = Loiter_Flying;
}
// Loiter State Machine
switch (loiter_state) {
case Loiter_MotorStopped:
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
#if FRAME_CONFIG == HELI_FRAME
// force descent rate and call position controller
pos_control->set_alt_target_from_climb_rate(-abs(g.land_speed), G_Dt, false);
#else
wp_nav->init_loiter_target();
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
#endif
wp_nav->update_loiter(ekfGndSpdLimit, ekfNavVelGainScaler);
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(wp_nav->get_roll(), wp_nav->get_pitch(), target_yaw_rate, get_smoothing_gain());
pos_control->update_z_controller();
break;
case Loiter_Takeoff:
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// initiate take-off
if (!takeoff_state.running) {
takeoff_timer_start(constrain_float(g.pilot_takeoff_alt,0.0f,1000.0f));
// indicate we are taking off
set_land_complete(false);
// clear i term when we're taking off
set_throttle_takeoff();
}
// get takeoff adjusted pilot and takeoff climb rates
takeoff_get_climb_rates(target_climb_rate, takeoff_climb_rate);
// get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// run loiter controller
wp_nav->update_loiter(ekfGndSpdLimit, ekfNavVelGainScaler);
// call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(wp_nav->get_roll(), wp_nav->get_pitch(), target_yaw_rate, get_smoothing_gain());
// update altitude target and call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt);
pos_control->update_z_controller();
break;
case Loiter_Landed:
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle)
if (target_climb_rate < 0.0f) {
motors->set_desired_spool_state(AP_Motors::DESIRED_SPIN_WHEN_ARMED);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
wp_nav->init_loiter_target();
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0, 0, 0, get_smoothing_gain());
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller();
break;
case Loiter_Flying:
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
#if PRECISION_LANDING == ENABLED
if (do_precision_loiter()) {
precision_loiter_xy();
}
#endif
// run loiter controller
wp_nav->update_loiter(ekfGndSpdLimit, ekfNavVelGainScaler);
// call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(wp_nav->get_roll(), wp_nav->get_pitch(), target_yaw_rate, get_smoothing_gain());
// adjust climb rate using rangefinder
if (copter.rangefinder_alt_ok()) {
// if rangefinder is ok, use surface tracking
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
}
// get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// update altitude target and call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->update_z_controller();
break;
}
}
// circle_run - runs the circle flight mode
// should be called at 100hz or more
void Copter::ModeCircle::run()
{
float target_yaw_rate = 0;
float target_climb_rate = 0;
// initialize speeds and accelerations
pos_control->set_speed_xy(wp_nav->get_speed_xy());
pos_control->set_accel_xy(wp_nav->get_wp_acceleration());
pos_control->set_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control->set_accel_z(g.pilot_accel_z);
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || ap.land_complete || !motors->get_interlock()) {
// To-Do: add some initialisation of position controllers
zero_throttle_and_relax_ac();
pos_control->set_alt_target_to_current_alt();
return;
}
// process pilot inputs
if (!copter.failsafe.radio) {
// get pilot's desired yaw rate
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
if (!is_zero(target_yaw_rate)) {
pilot_yaw_override = true;
}
// get pilot desired climb rate
target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
// check for pilot requested take-off
if (ap.land_complete && target_climb_rate > 0) {
// indicate we are taking off
set_land_complete(false);
// clear i term when we're taking off
set_throttle_takeoff();
}
}
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// run circle controller
copter.circle_nav->update();
// call attitude controller
if (pilot_yaw_override) {
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(copter.circle_nav->get_roll(),
copter.circle_nav->get_pitch(),
target_yaw_rate, get_smoothing_gain());
}else{
attitude_control->input_euler_angle_roll_pitch_yaw(copter.circle_nav->get_roll(),
copter.circle_nav->get_pitch(),
copter.circle_nav->get_yaw(),true, get_smoothing_gain());
}
// adjust climb rate using rangefinder
if (copter.rangefinder_alt_ok()) {
// if rangefinder is ok, use surface tracking
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
}
// update altitude target and call position controller
pos_control->set_alt_target_from_climb_rate(target_climb_rate, G_Dt, false);
pos_control->update_z_controller();
}
// poshold_run - runs the PosHold controller
// should be called at 100hz or more
void Copter::poshold_run()
{
float target_roll, target_pitch; // pilot's roll and pitch angle inputs
float target_yaw_rate = 0; // pilot desired yaw rate in centi-degrees/sec
float target_climb_rate = 0; // pilot desired climb rate in centimeters/sec
float takeoff_climb_rate = 0.0f; // takeoff induced climb rate
float brake_to_loiter_mix; // mix of brake and loiter controls. 0 = fully brake controls, 1 = fully loiter controls
float controller_to_pilot_roll_mix; // mix of controller and pilot controls. 0 = fully last controller controls, 1 = fully pilot controls
float controller_to_pilot_pitch_mix; // mix of controller and pilot controls. 0 = fully last controller controls, 1 = fully pilot controls
float vel_fw, vel_right; // vehicle's current velocity in body-frame forward and right directions
const Vector3f& vel = inertial_nav.get_velocity();
// initialize vertical speeds and acceleration
pos_control->set_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control->set_accel_z(g.pilot_accel_z);
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) {
motors->set_desired_spool_state(AP_Motors::DESIRED_SPIN_WHEN_ARMED);
wp_nav->init_loiter_target();
attitude_control->set_throttle_out_unstabilized(0,true,g.throttle_filt);
pos_control->relax_alt_hold_controllers(0.0f);
return;
}
// process pilot inputs
if (!failsafe.radio) {
// apply SIMPLE mode transform to pilot inputs
update_simple_mode();
// get pilot's desired yaw rate
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
// get pilot desired climb rate (for alt-hold mode and take-off)
target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up);
// get takeoff adjusted pilot and takeoff climb rates
takeoff_get_climb_rates(target_climb_rate, takeoff_climb_rate);
// check for take-off
#if FRAME_CONFIG == HELI_FRAME
// helicopters are held on the ground until rotor speed runup has finished
if (ap.land_complete && (takeoff_state.running || (target_climb_rate > 0.0f && motors->rotor_runup_complete()))) {
#else
if (ap.land_complete && (takeoff_state.running || target_climb_rate > 0.0f)) {
#endif
if (!takeoff_state.running) {
takeoff_timer_start(constrain_float(g.pilot_takeoff_alt,0.0f,1000.0f));
}
// indicate we are taking off
set_land_complete(false);
// clear i term when we're taking off
set_throttle_takeoff();
}
}
// relax loiter target if we might be landed
if (ap.land_complete_maybe) {
wp_nav->loiter_soften_for_landing();
}
// if landed initialise loiter targets, set throttle to zero and exit
if (ap.land_complete) {
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle)
if (target_climb_rate < 0.0f) {
motors->set_desired_spool_state(AP_Motors::DESIRED_SPIN_WHEN_ARMED);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
wp_nav->init_loiter_target();
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0, 0, 0, get_smoothing_gain());
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller();
return;
}else{
// convert pilot input to lean angles
get_pilot_desired_lean_angles(channel_roll->get_control_in(), channel_pitch->get_control_in(), target_roll, target_pitch, aparm.angle_max);
// convert inertial nav earth-frame velocities to body-frame
// To-Do: move this to AP_Math (or perhaps we already have a function to do this)
vel_fw = vel.x*ahrs.cos_yaw() + vel.y*ahrs.sin_yaw();
vel_right = -vel.x*ahrs.sin_yaw() + vel.y*ahrs.cos_yaw();
// If not in LOITER, retrieve latest wind compensation lean angles related to current yaw
if (poshold.roll_mode != POSHOLD_LOITER || poshold.pitch_mode != POSHOLD_LOITER)
poshold_get_wind_comp_lean_angles(poshold.wind_comp_roll, poshold.wind_comp_pitch);
// Roll state machine
// Each state (aka mode) is responsible for:
// 1. dealing with pilot input
// 2. calculating the final roll output to the attitude controller
// 3. checking if the state (aka mode) should be changed and if 'yes' perform any required initialisation for the new state
switch (poshold.roll_mode) {
case POSHOLD_PILOT_OVERRIDE:
// update pilot desired roll angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_roll, target_roll);
// switch to BRAKE mode for next iteration if no pilot input
if (is_zero(target_roll) && (fabsf(poshold.pilot_roll) < 2 * g.poshold_brake_rate)) {
// initialise BRAKE mode
poshold.roll_mode = POSHOLD_BRAKE; // Set brake roll mode
poshold.brake_roll = 0; // initialise braking angle to zero
poshold.brake_angle_max_roll = 0; // reset brake_angle_max so we can detect when vehicle begins to flatten out during braking
poshold.brake_timeout_roll = POSHOLD_BRAKE_TIME_ESTIMATE_MAX; // number of cycles the brake will be applied, updated during braking mode.
poshold.braking_time_updated_roll = false; // flag the braking time can be re-estimated
}
// final lean angle should be pilot input plus wind compensation
poshold.roll = poshold.pilot_roll + poshold.wind_comp_roll;
break;
case POSHOLD_BRAKE:
case POSHOLD_BRAKE_READY_TO_LOITER:
// calculate brake_roll angle to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_roll, vel_right);
// update braking time estimate
if (!poshold.braking_time_updated_roll) {
// check if brake angle is increasing
if (abs(poshold.brake_roll) >= poshold.brake_angle_max_roll) {
poshold.brake_angle_max_roll = abs(poshold.brake_roll);
} else {
// braking angle has started decreasing so re-estimate braking time
poshold.brake_timeout_roll = 1+(uint16_t)(LOOP_RATE_FACTOR*15L*(int32_t)(abs(poshold.brake_roll))/(10L*(int32_t)g.poshold_brake_rate)); // the 1.2 (12/10) factor has to be tuned in flight, here it means 120% of the "normal" time.
poshold.braking_time_updated_roll = true;
}
}
// if velocity is very low reduce braking time to 0.5seconds
if ((fabsf(vel_right) <= POSHOLD_SPEED_0) && (poshold.brake_timeout_roll > 50*LOOP_RATE_FACTOR)) {
poshold.brake_timeout_roll = 50*LOOP_RATE_FACTOR;
}
// reduce braking timer
if (poshold.brake_timeout_roll > 0) {
poshold.brake_timeout_roll--;
} else {
// indicate that we are ready to move to Loiter.
// Loiter will only actually be engaged once both roll_mode and pitch_mode are changed to POSHOLD_BRAKE_READY_TO_LOITER
// logic for engaging loiter is handled below the roll and pitch mode switch statements
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// final lean angle is braking angle + wind compensation angle
poshold.roll = poshold.brake_roll + poshold.wind_comp_roll;
// check for pilot input
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
}
break;
case POSHOLD_BRAKE_TO_LOITER:
case POSHOLD_LOITER:
// these modes are combined roll-pitch modes and are handled below
break;
case POSHOLD_CONTROLLER_TO_PILOT_OVERRIDE:
// update pilot desired roll angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_roll, target_roll);
// count-down loiter to pilot timer
if (poshold.controller_to_pilot_timer_roll > 0) {
poshold.controller_to_pilot_timer_roll--;
} else {
// when timer runs out switch to full pilot override for next iteration
poshold.roll_mode = POSHOLD_PILOT_OVERRIDE;
}
// calculate controller_to_pilot mix ratio
controller_to_pilot_roll_mix = (float)poshold.controller_to_pilot_timer_roll / (float)POSHOLD_CONTROLLER_TO_PILOT_MIX_TIMER;
// mix final loiter lean angle and pilot desired lean angles
poshold.roll = poshold_mix_controls(controller_to_pilot_roll_mix, poshold.controller_final_roll, poshold.pilot_roll + poshold.wind_comp_roll);
break;
}
// Pitch state machine
// Each state (aka mode) is responsible for:
// 1. dealing with pilot input
// 2. calculating the final pitch output to the attitude contpitcher
// 3. checking if the state (aka mode) should be changed and if 'yes' perform any required initialisation for the new state
switch (poshold.pitch_mode) {
case POSHOLD_PILOT_OVERRIDE:
// update pilot desired pitch angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_pitch, target_pitch);
// switch to BRAKE mode for next iteration if no pilot input
if (is_zero(target_pitch) && (fabsf(poshold.pilot_pitch) < 2 * g.poshold_brake_rate)) {
// initialise BRAKE mode
poshold.pitch_mode = POSHOLD_BRAKE; // set brake pitch mode
poshold.brake_pitch = 0; // initialise braking angle to zero
poshold.brake_angle_max_pitch = 0; // reset brake_angle_max so we can detect when vehicle begins to flatten out during braking
poshold.brake_timeout_pitch = POSHOLD_BRAKE_TIME_ESTIMATE_MAX; // number of cycles the brake will be applied, updated during braking mode.
poshold.braking_time_updated_pitch = false; // flag the braking time can be re-estimated
}
// final lean angle should be pilot input plus wind compensation
poshold.pitch = poshold.pilot_pitch + poshold.wind_comp_pitch;
break;
case POSHOLD_BRAKE:
case POSHOLD_BRAKE_READY_TO_LOITER:
// calculate brake_pitch angle to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_pitch, -vel_fw);
// update braking time estimate
if (!poshold.braking_time_updated_pitch) {
// check if brake angle is increasing
if (abs(poshold.brake_pitch) >= poshold.brake_angle_max_pitch) {
poshold.brake_angle_max_pitch = abs(poshold.brake_pitch);
} else {
// braking angle has started decreasing so re-estimate braking time
poshold.brake_timeout_pitch = 1+(uint16_t)(LOOP_RATE_FACTOR*15L*(int32_t)(abs(poshold.brake_pitch))/(10L*(int32_t)g.poshold_brake_rate)); // the 1.2 (12/10) factor has to be tuned in flight, here it means 120% of the "normal" time.
poshold.braking_time_updated_pitch = true;
}
}
// if velocity is very low reduce braking time to 0.5seconds
if ((fabsf(vel_fw) <= POSHOLD_SPEED_0) && (poshold.brake_timeout_pitch > 50*LOOP_RATE_FACTOR)) {
poshold.brake_timeout_pitch = 50*LOOP_RATE_FACTOR;
}
// reduce braking timer
if (poshold.brake_timeout_pitch > 0) {
poshold.brake_timeout_pitch--;
} else {
// indicate that we are ready to move to Loiter.
// Loiter will only actually be engaged once both pitch_mode and pitch_mode are changed to POSHOLD_BRAKE_READY_TO_LOITER
// logic for engaging loiter is handled below the pitch and pitch mode switch statements
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// final lean angle is braking angle + wind compensation angle
poshold.pitch = poshold.brake_pitch + poshold.wind_comp_pitch;
// check for pilot input
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
}
break;
case POSHOLD_BRAKE_TO_LOITER:
case POSHOLD_LOITER:
// these modes are combined pitch-pitch modes and are handled below
break;
case POSHOLD_CONTROLLER_TO_PILOT_OVERRIDE:
// update pilot desired pitch angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_pitch, target_pitch);
// count-down loiter to pilot timer
if (poshold.controller_to_pilot_timer_pitch > 0) {
poshold.controller_to_pilot_timer_pitch--;
} else {
// when timer runs out switch to full pilot override for next iteration
poshold.pitch_mode = POSHOLD_PILOT_OVERRIDE;
}
// calculate controller_to_pilot mix ratio
controller_to_pilot_pitch_mix = (float)poshold.controller_to_pilot_timer_pitch / (float)POSHOLD_CONTROLLER_TO_PILOT_MIX_TIMER;
// mix final loiter lean angle and pilot desired lean angles
poshold.pitch = poshold_mix_controls(controller_to_pilot_pitch_mix, poshold.controller_final_pitch, poshold.pilot_pitch + poshold.wind_comp_pitch);
break;
}
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
//
// Shared roll & pitch states (POSHOLD_BRAKE_TO_LOITER and POSHOLD_LOITER)
//
// switch into LOITER mode when both roll and pitch are ready
if (poshold.roll_mode == POSHOLD_BRAKE_READY_TO_LOITER && poshold.pitch_mode == POSHOLD_BRAKE_READY_TO_LOITER) {
poshold.roll_mode = POSHOLD_BRAKE_TO_LOITER;
poshold.pitch_mode = POSHOLD_BRAKE_TO_LOITER;
poshold.brake_to_loiter_timer = POSHOLD_BRAKE_TO_LOITER_TIMER;
// init loiter controller
wp_nav->init_loiter_target(inertial_nav.get_position(), poshold.loiter_reset_I); // (false) to avoid I_term reset. In original code, velocity(0,0,0) was used instead of current velocity: wp_nav->init_loiter_target(inertial_nav.get_position(), Vector3f(0,0,0));
// at this stage, we are going to run update_loiter that will reset I_term once. From now, we ensure next time that we will enter loiter and update it, I_term won't be reset anymore
poshold.loiter_reset_I = false;
// set delay to start of wind compensation estimate updates
poshold.wind_comp_start_timer = POSHOLD_WIND_COMP_START_TIMER;
}
// roll-mode is used as the combined roll+pitch mode when in BRAKE_TO_LOITER or LOITER modes
if (poshold.roll_mode == POSHOLD_BRAKE_TO_LOITER || poshold.roll_mode == POSHOLD_LOITER) {
// force pitch mode to be same as roll_mode just to keep it consistent (it's not actually used in these states)
poshold.pitch_mode = poshold.roll_mode;
// handle combined roll+pitch mode
switch (poshold.roll_mode) {
case POSHOLD_BRAKE_TO_LOITER:
// reduce brake_to_loiter timer
if (poshold.brake_to_loiter_timer > 0) {
poshold.brake_to_loiter_timer--;
} else {
// progress to full loiter on next iteration
poshold.roll_mode = POSHOLD_LOITER;
poshold.pitch_mode = POSHOLD_LOITER;
}
// calculate percentage mix of loiter and brake control
brake_to_loiter_mix = (float)poshold.brake_to_loiter_timer / (float)POSHOLD_BRAKE_TO_LOITER_TIMER;
// calculate brake_roll and pitch angles to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_roll, vel_right);
poshold_update_brake_angle_from_velocity(poshold.brake_pitch, -vel_fw);
// run loiter controller
wp_nav->update_loiter(ekfGndSpdLimit, ekfNavVelGainScaler);
// calculate final roll and pitch output by mixing loiter and brake controls
poshold.roll = poshold_mix_controls(brake_to_loiter_mix, poshold.brake_roll + poshold.wind_comp_roll, wp_nav->get_roll());
poshold.pitch = poshold_mix_controls(brake_to_loiter_mix, poshold.brake_pitch + poshold.wind_comp_pitch, wp_nav->get_pitch());
// check for pilot input
if (!is_zero(target_roll) || !is_zero(target_pitch)) {
// if roll input switch to pilot override for roll
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
// switch pitch-mode to brake (but ready to go back to loiter anytime)
// no need to reset poshold.brake_pitch here as wind comp has not been updated since last brake_pitch computation
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// if pitch input switch to pilot override for pitch
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
if (is_zero(target_roll)) {
// switch roll-mode to brake (but ready to go back to loiter anytime)
// no need to reset poshold.brake_roll here as wind comp has not been updated since last brake_roll computation
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
}
}
break;
case POSHOLD_LOITER:
// run loiter controller
wp_nav->update_loiter(ekfGndSpdLimit, ekfNavVelGainScaler);
// set roll angle based on loiter controller outputs
poshold.roll = wp_nav->get_roll();
poshold.pitch = wp_nav->get_pitch();
// update wind compensation estimate
poshold_update_wind_comp_estimate();
// check for pilot input
if (!is_zero(target_roll) || !is_zero(target_pitch)) {
// if roll input switch to pilot override for roll
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
// switch pitch-mode to brake (but ready to go back to loiter anytime)
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
// reset brake_pitch because wind_comp is now different and should give the compensation of the whole previous loiter angle
poshold.brake_pitch = 0;
}
// if pitch input switch to pilot override for pitch
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
// if roll not overriden switch roll-mode to brake (but be ready to go back to loiter any time)
if (is_zero(target_roll)) {
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
poshold.brake_roll = 0;
}
}
}
break;
default:
// do nothing for uncombined roll and pitch modes
break;
}
}
// constrain target pitch/roll angles
poshold.roll = constrain_int16(poshold.roll, -aparm.angle_max, aparm.angle_max);
poshold.pitch = constrain_int16(poshold.pitch, -aparm.angle_max, aparm.angle_max);
// update attitude controller targets
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(poshold.roll, poshold.pitch, target_yaw_rate, get_smoothing_gain());
// adjust climb rate using rangefinder
if (rangefinder_alt_ok()) {
// if rangefinder is ok, use surface tracking
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
}
// get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// update altitude target and call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt);
pos_control->update_z_controller();
}
}
// poshold_update_pilot_lean_angle - update the pilot's filtered lean angle with the latest raw input received
void Copter::poshold_update_pilot_lean_angle(float &lean_angle_filtered, float &lean_angle_raw)
{
// if raw input is large or reversing the vehicle's lean angle immediately set the fitlered angle to the new raw angle
if ((lean_angle_filtered > 0 && lean_angle_raw < 0) || (lean_angle_filtered < 0 && lean_angle_raw > 0) || (fabsf(lean_angle_raw) > POSHOLD_STICK_RELEASE_SMOOTH_ANGLE)) {
lean_angle_filtered = lean_angle_raw;
} else {
// lean_angle_raw must be pulling lean_angle_filtered towards zero, smooth the decrease
if (lean_angle_filtered > 0) {
// reduce the filtered lean angle at 5% or the brake rate (whichever is faster).
lean_angle_filtered -= MAX((float)lean_angle_filtered * POSHOLD_SMOOTH_RATE_FACTOR, MAX(1, g.poshold_brake_rate/LOOP_RATE_FACTOR));
// do not let the filtered angle fall below the pilot's input lean angle.
// the above line pulls the filtered angle down and the below line acts as a catch
lean_angle_filtered = MAX(lean_angle_filtered, lean_angle_raw);
}else{
lean_angle_filtered += MAX(-(float)lean_angle_filtered * POSHOLD_SMOOTH_RATE_FACTOR, MAX(1, g.poshold_brake_rate/LOOP_RATE_FACTOR));
lean_angle_filtered = MIN(lean_angle_filtered, lean_angle_raw);
}
}
}
// poshold_mix_controls - mixes two controls based on the mix_ratio
// mix_ratio of 1 = use first_control completely, 0 = use second_control completely, 0.5 = mix evenly
int16_t Copter::poshold_mix_controls(float mix_ratio, int16_t first_control, int16_t second_control)
{
mix_ratio = constrain_float(mix_ratio, 0.0f, 1.0f);
return (int16_t)((mix_ratio * first_control) + ((1.0f-mix_ratio)*second_control));
}
