ardupilot/ArduPlane/navigation.cpp

#include "Plane.h"

// set the nav_controller pointer to the right controller
void Plane::set_nav_controller(void)
{
    switch ((AP_Navigation::ControllerType)g.nav_controller.get()) {

    default:
    case AP_Navigation::CONTROLLER_DEFAULT:
        // no break, fall through to L1 as default controller

    case AP_Navigation::CONTROLLER_L1:
        nav_controller = &L1_controller;
        break;
    }
}

/*
  reset the total loiter angle
 */
void Plane::loiter_angle_reset(void)
{
    loiter.sum_cd = 0;
    loiter.total_cd = 0;
    loiter.reached_target_alt = false;
    loiter.unable_to_acheive_target_alt = false;
}

/*
  update the total angle we have covered in a loiter. Used to support
  commands to do N circles of loiter
 */
void Plane::loiter_angle_update(void)
{
    static const int32_t lap_check_interval_cd = 3*36000;

    const int32_t target_bearing_cd = nav_controller->target_bearing_cd();
    int32_t loiter_delta_cd;

    if (loiter.sum_cd == 0 && !reached_loiter_target()) {
        // we don't start summing until we are doing the real loiter
        loiter_delta_cd = 0;
    } else if (loiter.sum_cd == 0) {
        // use 1 cd for initial delta
        loiter_delta_cd = 1;
        loiter.start_lap_alt_cm = current_loc.alt;
        loiter.next_sum_lap_cd = lap_check_interval_cd;
    } else {
        loiter_delta_cd = target_bearing_cd - loiter.old_target_bearing_cd;
    }

    loiter.old_target_bearing_cd = target_bearing_cd;
    loiter_delta_cd = wrap_180_cd(loiter_delta_cd);
    loiter.sum_cd += loiter_delta_cd * loiter.direction;

    if (labs(current_loc.alt - next_WP_loc.alt) < 500) {
        loiter.reached_target_alt = true;
        loiter.unable_to_acheive_target_alt = false;
        loiter.next_sum_lap_cd = loiter.sum_cd + lap_check_interval_cd;

    } else if (!loiter.reached_target_alt && labs(loiter.sum_cd) >= loiter.next_sum_lap_cd) {
        // check every few laps for scenario where up/downdrafts inhibit you from loitering up/down for too long
        loiter.unable_to_acheive_target_alt = labs(current_loc.alt - loiter.start_lap_alt_cm) < 500;
        loiter.start_lap_alt_cm = current_loc.alt;
        loiter.next_sum_lap_cd += lap_check_interval_cd;
    }
}

//****************************************************************
// Function that will calculate the desired direction to fly and distance
//****************************************************************
void Plane::navigate()
{
    // allow change of nav controller mid-flight
    set_nav_controller();

    // do not navigate with corrupt data
    // ---------------------------------
    if (!have_position) {
        return;
    }

    if (next_WP_loc.lat == 0 && next_WP_loc.lng == 0) {
        return;
    }

    // waypoint distance from plane
    // ----------------------------
    auto_state.wp_distance = current_loc.get_distance(next_WP_loc);
    auto_state.wp_proportion = current_loc.line_path_proportion(prev_WP_loc, next_WP_loc);
    SpdHgt_Controller->set_path_proportion(auto_state.wp_proportion);

    // update total loiter angle
    loiter_angle_update();

    // control mode specific updates to navigation demands
    // ---------------------------------------------------
    update_navigation();
}

void Plane::calc_airspeed_errors()
{
    float airspeed_measured = 0;
    
    // we use the airspeed estimate function not direct sensor as TECS
    // may be using synthetic airspeed
    ahrs.airspeed_estimate(&airspeed_measured);

    // FBW_B/cruise airspeed target
    if (!failsafe.rc_failsafe && (control_mode == &mode_fbwb || control_mode == &mode_cruise)) {
        if (g2.flight_options & FlightOptions::CRUISE_TRIM_AIRSPEED) {
            target_airspeed_cm = aparm.airspeed_cruise_cm;
        } else if (g2.flight_options & FlightOptions::CRUISE_TRIM_THROTTLE) {
            float control_min = 0.0f;
            float control_mid = 0.0f;
            const float control_max = channel_throttle->get_range();
            const float control_in = get_throttle_input();
            switch (channel_throttle->get_type()) {
                case RC_Channel::RC_CHANNEL_TYPE_ANGLE:
                    control_min = -control_max;
                    break;
                case RC_Channel::RC_CHANNEL_TYPE_RANGE:
                    control_mid = channel_throttle->get_control_mid();
                    break;
            }
            if (control_in <= control_mid) {
                target_airspeed_cm = linear_interpolate(aparm.airspeed_min * 100, aparm.airspeed_cruise_cm,
                                                        control_in,
                                                        control_min, control_mid);
            } else {
                target_airspeed_cm = linear_interpolate(aparm.airspeed_cruise_cm, aparm.airspeed_max * 100,
                                                        control_in,
                                                        control_mid, control_max);
            }
        } else {
            target_airspeed_cm = ((int32_t)(aparm.airspeed_max - aparm.airspeed_min) *
                                  get_throttle_input()) + ((int32_t)aparm.airspeed_min * 100);
        }

    } else if (flight_stage == AP_Vehicle::FixedWing::FLIGHT_LAND) {
        // Landing airspeed target
        target_airspeed_cm = landing.get_target_airspeed_cm();
    } else if ((control_mode == &mode_auto) &&
               (quadplane.options & QuadPlane::OPTION_MISSION_LAND_FW_APPROACH) &&
							 ((vtol_approach_s.approach_stage == Landing_ApproachStage::APPROACH_LINE) ||
							  (vtol_approach_s.approach_stage == Landing_ApproachStage::VTOL_LANDING))) {
        float land_airspeed = SpdHgt_Controller->get_land_airspeed();
        if (is_positive(land_airspeed)) {
            target_airspeed_cm = SpdHgt_Controller->get_land_airspeed() * 100;
        } else {
            // fallover to normal airspeed
            target_airspeed_cm = aparm.airspeed_cruise_cm;
        }
    } else {
        // Normal airspeed target
        target_airspeed_cm = aparm.airspeed_cruise_cm;
    }

    // Set target to current airspeed + ground speed undershoot,
    // but only when this is faster than the target airspeed commanded
    // above.
    if (auto_throttle_mode &&
    	aparm.min_gndspeed_cm > 0 &&
    	control_mode != &mode_circle) {
        int32_t min_gnd_target_airspeed = airspeed_measured*100 + groundspeed_undershoot;
        if (min_gnd_target_airspeed > target_airspeed_cm) {
            target_airspeed_cm = min_gnd_target_airspeed;
        }
    }

    // Bump up the target airspeed based on throttle nudging
    if (throttle_allows_nudging && airspeed_nudge_cm > 0) {
        target_airspeed_cm += airspeed_nudge_cm;
    }

    // Apply airspeed limit
    if (target_airspeed_cm > (aparm.airspeed_max * 100))
        target_airspeed_cm = (aparm.airspeed_max * 100);

    // use the TECS view of the target airspeed for reporting, to take
    // account of the landing speed
    airspeed_error = SpdHgt_Controller->get_target_airspeed() - airspeed_measured;
}

void Plane::calc_gndspeed_undershoot()
{
    // Use the component of ground speed in the forward direction
    // This prevents flyaway if wind takes plane backwards
    if (gps.status() >= AP_GPS::GPS_OK_FIX_2D) {
	      Vector2f gndVel = ahrs.groundspeed_vector();
        const Matrix3f &rotMat = ahrs.get_rotation_body_to_ned();
        Vector2f yawVect = Vector2f(rotMat.a.x,rotMat.b.x);
        if (!yawVect.is_zero()) {
            yawVect.normalize();
            float gndSpdFwd = yawVect * gndVel;
            groundspeed_undershoot = (aparm.min_gndspeed_cm > 0) ? (aparm.min_gndspeed_cm - gndSpdFwd*100) : 0;
        }
    } else {
        groundspeed_undershoot = 0;
    }
}

void Plane::update_loiter(uint16_t radius)
{
    if (radius <= 1) {
        // if radius is <=1 then use the general loiter radius. if it's small, use default
        radius = (abs(aparm.loiter_radius) <= 1) ? LOITER_RADIUS_DEFAULT : abs(aparm.loiter_radius);
        if (next_WP_loc.loiter_ccw == 1) {
            loiter.direction = -1;
        } else {
            loiter.direction = (aparm.loiter_radius < 0) ? -1 : 1;
        }
    }

    if (loiter.start_time_ms != 0 &&
        quadplane.guided_mode_enabled()) {
        if (!auto_state.vtol_loiter) {
            auto_state.vtol_loiter = true;
            // reset loiter start time, so we don't consider the point
            // reached till we get much closer
            loiter.start_time_ms = 0;
            quadplane.guided_start();
        }
    } else if ((loiter.start_time_ms == 0 &&
                (control_mode == &mode_auto || control_mode == &mode_guided) &&
                auto_state.crosstrack &&
                current_loc.get_distance(next_WP_loc) > radius*3) ||
               (control_mode == &mode_rtl && quadplane.available() && quadplane.rtl_mode == 1)) {
        /*
          if never reached loiter point and using crosstrack and somewhat far away from loiter point
          navigate to it like in auto-mode for normal crosstrack behavior

          we also use direct waypoint navigation if we are a quadplane
          that is going to be switching to QRTL when it gets within
          RTL_RADIUS
        */
        nav_controller->update_waypoint(prev_WP_loc, next_WP_loc);
    } else {
        nav_controller->update_loiter(next_WP_loc, radius, loiter.direction);
    }

    if (loiter.start_time_ms == 0) {
        if (reached_loiter_target() ||
            auto_state.wp_proportion > 1) {
            // we've reached the target, start the timer
            loiter.start_time_ms = millis();
            if (control_mode == &mode_guided || control_mode == &mode_avoidADSB) {
                // starting a loiter in GUIDED means we just reached the target point
                gcs().send_mission_item_reached_message(0);
            }
            if (quadplane.guided_mode_enabled()) {
                quadplane.guided_start();
            }
        }
    }
}

/*
  handle CRUISE mode, locking heading to GPS course when we have
  sufficient ground speed, and no aileron or rudder input
 */
void Plane::update_cruise()
{
    if (!cruise_state.locked_heading &&
        channel_roll->get_control_in() == 0 &&
        rudder_input() == 0 &&
        gps.status() >= AP_GPS::GPS_OK_FIX_2D &&
        gps.ground_speed() >= 3 &&
        cruise_state.lock_timer_ms == 0) {
        // user wants to lock the heading - start the timer
        cruise_state.lock_timer_ms = millis();
    }
    if (cruise_state.lock_timer_ms != 0 &&
        (millis() - cruise_state.lock_timer_ms) > 500) {
        // lock the heading after 0.5 seconds of zero heading input
        // from user
        cruise_state.locked_heading = true;
        cruise_state.lock_timer_ms = 0;
        cruise_state.locked_heading_cd = gps.ground_course_cd();
        prev_WP_loc = current_loc;
    }
    if (cruise_state.locked_heading) {
        next_WP_loc = prev_WP_loc;
        // always look 1km ahead
        next_WP_loc.offset_bearing(cruise_state.locked_heading_cd*0.01f, prev_WP_loc.get_distance(current_loc) + 1000);
        nav_controller->update_waypoint(prev_WP_loc, next_WP_loc);
    }
}


/*
  handle speed and height control in FBWB or CRUISE mode. 
  In this mode the elevator is used to change target altitude. The
  throttle is used to change target airspeed or throttle
 */
void Plane::update_fbwb_speed_height(void)
{
    uint32_t now = micros();
    if (now - target_altitude.last_elev_check_us >= 100000) {
        // we don't run this on every loop as it would give too small granularity on quadplanes at 300Hz, and
        // give below 1cm altitude change, which would result in no climb or descent
        float dt = (now - target_altitude.last_elev_check_us) * 1.0e-6;
        dt = constrain_float(dt, 0.1, 0.15);

        target_altitude.last_elev_check_us = now;
        
        float elevator_input = channel_pitch->get_control_in() / 4500.0f;
    
        if (g.flybywire_elev_reverse) {
            elevator_input = -elevator_input;
        }

        int32_t alt_change_cm = g.flybywire_climb_rate * elevator_input * dt * 100;
        change_target_altitude(alt_change_cm);
        
        if (is_zero(elevator_input) && !is_zero(target_altitude.last_elevator_input)) {
            // the user has just released the elevator, lock in
            // the current altitude
            set_target_altitude_current();
        }
        
        target_altitude.last_elevator_input = elevator_input;
    }
    
    check_fbwb_minimum_altitude();

    altitude_error_cm = calc_altitude_error_cm();
    
    calc_throttle();
    calc_nav_pitch();
}

/*
  calculate the turn angle for the next leg of the mission
 */
void Plane::setup_turn_angle(void)
{
    int32_t next_ground_course_cd = mission.get_next_ground_course_cd(-1);
    if (next_ground_course_cd == -1) {
        // the mission library can't determine a turn angle, assume 90 degrees
        auto_state.next_turn_angle = 90.0f;
    } else {
        // get the heading of the current leg
        int32_t ground_course_cd = prev_WP_loc.get_bearing_to(next_WP_loc);

        // work out the angle we need to turn through
        auto_state.next_turn_angle = wrap_180_cd(next_ground_course_cd - ground_course_cd) * 0.01f;
    }
}    

/*
  see if we have reached our loiter target
 */
bool Plane::reached_loiter_target(void)
{
    if (quadplane.in_vtol_auto()) {
        return auto_state.wp_distance < 3;
    }
    return nav_controller->reached_loiter_target();
}