mode_stabilize.cpp

#include "Sub.h"


bool ModeStabilize::init(bool ignore_checks) {
    // set target altitude to zero for reporting
    position_control->set_pos_desired_U_cm(0);
    sub.last_pilot_heading_rad = ahrs.get_yaw_rad();

    return true;
    return true;
}

void ModeStabilize::run()
{
  uint32_t tnow = AP_HAL::millis();
    float target_roll, target_pitch;

    // if not armed set throttle to zero and exit immediately
    if (!motors.armed()) {
        motors.set_desired_spool_state(AP_Motors::DesiredSpoolState::GROUND_IDLE);
        attitude_control->set_throttle_out(NEUTRAL_THROTTLE,true,g.throttle_filt);
        attitude_control->relax_attitude_controllers();
        sub.last_pilot_heading_rad = ahrs.get_yaw_rad();
        return;
    }

    motors.set_desired_spool_state(AP_Motors::DesiredSpoolState::THROTTLE_UNLIMITED);

    // convert pilot input to lean angles
    // To-Do: convert sub.get_pilot_desired_lean_angles to return angles as floats
    // TODO2: move into mode.h
    sub.get_pilot_desired_lean_angles(channel_roll->get_control_in(), channel_pitch->get_control_in(), target_roll, target_pitch, attitude_control->lean_angle_max_cd());

    // get pilot's desired yaw rate
    float yaw_input = channel_yaw->pwm_to_angle_dz_trim(channel_yaw->get_dead_zone() * sub.gain, channel_yaw->get_radio_trim());
    float target_yaw_rate = sub.get_pilot_desired_yaw_rate(yaw_input);

    // call attitude controller
    // update attitude controller targets

    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_cd(target_roll, target_pitch, target_yaw_rate);
        sub.last_pilot_heading_rad = ahrs.get_yaw_rad();
        sub.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 < sub.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_cd(target_roll, target_pitch, target_yaw_rate);
            sub.last_pilot_heading_rad = ahrs.get_yaw_rad(); // update heading to hold

        } else { // call attitude controller holding absolute absolute bearing
            attitude_control->input_euler_angle_roll_pitch_yaw_cd(target_roll, target_pitch, rad_to_cd(sub.last_pilot_heading_rad), true);
        }
    }

    // output pilot's throttle
    attitude_control->set_throttle_out((channel_throttle->norm_input() + 1.0f) / 2.0f, false, g.throttle_filt);

    //control_in is range -1000-1000
    //radio_in is raw pwm value
    motors.set_forward(channel_forward->norm_input());
    motors.set_lateral(channel_lateral->norm_input());
}