ardupilot/ArduPlane/mode_qloiter.cpp

#include "mode.h"
#include "Plane.h"

#if HAL_QUADPLANE_ENABLED

bool ModeQLoiter::_enter()
{
    // initialise loiter
    loiter_nav->clear_pilot_desired_acceleration();
    loiter_nav->init_target();

    // set vertical speed and acceleration limits
    pos_control->set_max_speed_accel_z(-quadplane.get_pilot_velocity_z_max_dn(), quadplane.pilot_velocity_z_max_up, quadplane.pilot_accel_z);
    pos_control->set_correction_speed_accel_z(-quadplane.get_pilot_velocity_z_max_dn(), quadplane.pilot_velocity_z_max_up, quadplane.pilot_accel_z);

    quadplane.init_throttle_wait();

    // prevent re-init of target position
    quadplane.last_loiter_ms = AP_HAL::millis();
    return true;
}

void ModeQLoiter::update()
{
    plane.mode_qstabilize.update();
}

// run quadplane loiter controller
void ModeQLoiter::run()
{
    const uint32_t now = AP_HAL::millis();
    if (quadplane.tailsitter.in_vtol_transition(now)) {
        // Tailsitters in FW pull up phase of VTOL transition run FW controllers
        Mode::run();
        return;
    }

    if (quadplane.throttle_wait) {
        quadplane.set_desired_spool_state(AP_Motors::DesiredSpoolState::GROUND_IDLE);
        attitude_control->set_throttle_out(0, true, 0);
        quadplane.relax_attitude_control();
        pos_control->relax_z_controller(0);
        loiter_nav->clear_pilot_desired_acceleration();
        loiter_nav->init_target();

        // Stabilize with fixed wing surfaces
        plane.stabilize_roll();
        plane.stabilize_pitch();
        return;
    }
    if (!quadplane.motors->armed()) {
        plane.mode_qloiter._enter();
    }

    if (quadplane.should_relax()) {
        loiter_nav->soften_for_landing();
    }

    if (now - quadplane.last_loiter_ms > 500) {
        loiter_nav->clear_pilot_desired_acceleration();
        loiter_nav->init_target();
    }
    quadplane.last_loiter_ms = now;

    // motors use full range
    quadplane.set_desired_spool_state(AP_Motors::DesiredSpoolState::THROTTLE_UNLIMITED);

    // set vertical speed and acceleration limits
    pos_control->set_max_speed_accel_z(-quadplane.get_pilot_velocity_z_max_dn(), quadplane.pilot_velocity_z_max_up, quadplane.pilot_accel_z);

    // process pilot's roll and pitch input
    float target_roll_cd, target_pitch_cd;
    quadplane.get_pilot_desired_lean_angles(target_roll_cd, target_pitch_cd, loiter_nav->get_angle_max_cd(), attitude_control->get_althold_lean_angle_max_cd());
    loiter_nav->set_pilot_desired_acceleration(target_roll_cd, target_pitch_cd);
    
    // run loiter controller
    if (!pos_control->is_active_xy()) {
        pos_control->init_xy_controller();
    }
    loiter_nav->update();

    // nav roll and pitch are controller by loiter controller
    plane.nav_roll_cd = loiter_nav->get_roll();
    plane.nav_pitch_cd = loiter_nav->get_pitch();

    plane.quadplane.assign_tilt_to_fwd_thr();

    if (quadplane.transition->set_VTOL_roll_pitch_limit(plane.nav_roll_cd, plane.nav_pitch_cd)) {
        pos_control->set_externally_limited_xy();
    }

    // Pilot input, use yaw rate time constant
    quadplane.set_pilot_yaw_rate_time_constant();

    // call attitude controller with conservative smoothing gain of 4.0f
    attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(plane.nav_roll_cd,
                                                                  plane.nav_pitch_cd,
                                                                  quadplane.get_desired_yaw_rate_cds());

    if (plane.control_mode == &plane.mode_qland) {
        if (poscontrol.get_state() < QuadPlane::QPOS_LAND_FINAL && quadplane.check_land_final()) {
            poscontrol.set_state(QuadPlane::QPOS_LAND_FINAL);
            quadplane.setup_target_position();
#if AP_ICENGINE_ENABLED
            // cut IC engine if enabled
            if (quadplane.land_icengine_cut != 0) {
                plane.g2.ice_control.engine_control(0, 0, 0);
            }
#endif  // AP_ICENGINE_ENABLED
        }
        float height_above_ground = plane.relative_ground_altitude(plane.g.rangefinder_landing);
        float descent_rate_cms = quadplane.landing_descent_rate_cms(height_above_ground);

        if (poscontrol.get_state() == QuadPlane::QPOS_LAND_FINAL && !quadplane.option_is_set(QuadPlane::OPTION::DISABLE_GROUND_EFFECT_COMP)) {
            ahrs.set_touchdown_expected(true);
        }

        pos_control->land_at_climb_rate_cm(-descent_rate_cms, descent_rate_cms>0);
        quadplane.check_land_complete();
    } else if (plane.control_mode == &plane.mode_guided && quadplane.guided_takeoff) {
        quadplane.set_climb_rate_cms(0);
    } else {
        // update altitude target and call position controller
        quadplane.set_climb_rate_cms(quadplane.get_pilot_desired_climb_rate_cms());
    }
    quadplane.run_z_controller();

    // Stabilize with fixed wing surfaces
    plane.stabilize_roll();
    plane.stabilize_pitch();
}

#endif