mirror of https://github.com/ArduPilot/ardupilot
246 lines
7.9 KiB
C++
246 lines
7.9 KiB
C++
// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
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#include "Plane.h"
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// set the nav_controller pointer to the right controller
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void Plane::set_nav_controller(void)
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{
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switch ((AP_Navigation::ControllerType)g.nav_controller.get()) {
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case AP_Navigation::CONTROLLER_L1:
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nav_controller = &L1_controller;
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break;
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}
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}
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/*
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reset the total loiter angle
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*/
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void Plane::loiter_angle_reset(void)
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{
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loiter.sum_cd = 0;
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loiter.total_cd = 0;
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}
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/*
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update the total angle we have covered in a loiter. Used to support
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commands to do N circles of loiter
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*/
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void Plane::loiter_angle_update(void)
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{
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int32_t target_bearing_cd = nav_controller->target_bearing_cd();
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int32_t loiter_delta_cd;
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if (loiter.sum_cd == 0) {
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// use 1 cd for initial delta
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loiter_delta_cd = 1;
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} else {
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loiter_delta_cd = target_bearing_cd - loiter.old_target_bearing_cd;
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}
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loiter.old_target_bearing_cd = target_bearing_cd;
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loiter_delta_cd = wrap_180_cd(loiter_delta_cd);
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loiter.sum_cd += loiter_delta_cd * loiter.direction;
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}
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//****************************************************************
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// Function that will calculate the desired direction to fly and distance
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//****************************************************************
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void Plane::navigate()
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{
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// allow change of nav controller mid-flight
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set_nav_controller();
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// do not navigate with corrupt data
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// ---------------------------------
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if (!have_position) {
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return;
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}
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if (next_WP_loc.lat == 0) {
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return;
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}
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// waypoint distance from plane
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// ----------------------------
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auto_state.wp_distance = get_distance(current_loc, next_WP_loc);
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auto_state.wp_proportion = location_path_proportion(current_loc,
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prev_WP_loc, next_WP_loc);
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SpdHgt_Controller->set_path_proportion(auto_state.wp_proportion);
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// update total loiter angle
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loiter_angle_update();
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// control mode specific updates to navigation demands
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// ---------------------------------------------------
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update_navigation();
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}
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void Plane::calc_airspeed_errors()
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{
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float aspeed_cm = airspeed.get_airspeed_cm();
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// Normal airspeed target
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target_airspeed_cm = g.airspeed_cruise_cm;
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// FBW_B airspeed target
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if (control_mode == FLY_BY_WIRE_B ||
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control_mode == CRUISE) {
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target_airspeed_cm = ((int32_t)(aparm.airspeed_max -
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aparm.airspeed_min) *
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channel_throttle->control_in) +
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((int32_t)aparm.airspeed_min * 100);
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}
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// Set target to current airspeed + ground speed undershoot,
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// but only when this is faster than the target airspeed commanded
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// above.
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if (control_mode >= FLY_BY_WIRE_B && (g.min_gndspeed_cm > 0)) {
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int32_t min_gnd_target_airspeed = aspeed_cm + groundspeed_undershoot;
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if (min_gnd_target_airspeed > target_airspeed_cm)
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target_airspeed_cm = min_gnd_target_airspeed;
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}
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// Bump up the target airspeed based on throttle nudging
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if (control_mode >= AUTO && airspeed_nudge_cm > 0) {
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target_airspeed_cm += airspeed_nudge_cm;
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}
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// Apply airspeed limit
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if (target_airspeed_cm > (aparm.airspeed_max * 100))
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target_airspeed_cm = (aparm.airspeed_max * 100);
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// use the TECS view of the target airspeed for reporting, to take
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// account of the landing speed
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airspeed_error_cm = SpdHgt_Controller->get_target_airspeed()*100 - aspeed_cm;
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}
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void Plane::calc_gndspeed_undershoot()
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{
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// Use the component of ground speed in the forward direction
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// This prevents flyaway if wind takes plane backwards
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if (gps.status() >= AP_GPS::GPS_OK_FIX_2D) {
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Vector2f gndVel = ahrs.groundspeed_vector();
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const Matrix3f &rotMat = ahrs.get_rotation_body_to_ned();
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Vector2f yawVect = Vector2f(rotMat.a.x,rotMat.b.x);
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yawVect.normalize();
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float gndSpdFwd = yawVect * gndVel;
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groundspeed_undershoot = (g.min_gndspeed_cm > 0) ? (g.min_gndspeed_cm - gndSpdFwd*100) : 0;
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}
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}
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void Plane::update_loiter(uint16_t radius)
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{
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if (radius == 0) {
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radius = abs(g.loiter_radius);
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}
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if (loiter.start_time_ms == 0 &&
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control_mode == AUTO &&
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!auto_state.no_crosstrack &&
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get_distance(current_loc, next_WP_loc) > radius*2) {
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// if never reached loiter point and using crosstrack and somewhat far away from loiter point
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// navigate to it like in auto-mode for normal crosstrack behavior
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nav_controller->update_waypoint(prev_WP_loc, next_WP_loc);
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} else {
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nav_controller->update_loiter(next_WP_loc, radius, loiter.direction);
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}
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if (loiter.start_time_ms == 0) {
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if (nav_controller->reached_loiter_target()) {
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// we've reached the target, start the timer
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loiter.start_time_ms = millis();
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if (control_mode == GUIDED) {
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// starting a loiter in GUIDED means we just reached the target point
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gcs_send_mission_item_reached_message(0);
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}
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}
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}
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}
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/*
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handle CRUISE mode, locking heading to GPS course when we have
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sufficient ground speed, and no aileron or rudder input
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*/
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void Plane::update_cruise()
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{
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if (!cruise_state.locked_heading &&
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channel_roll->control_in == 0 &&
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rudder_input == 0 &&
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gps.status() >= AP_GPS::GPS_OK_FIX_2D &&
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gps.ground_speed() >= 3 &&
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cruise_state.lock_timer_ms == 0) {
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// user wants to lock the heading - start the timer
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cruise_state.lock_timer_ms = millis();
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}
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if (cruise_state.lock_timer_ms != 0 &&
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(millis() - cruise_state.lock_timer_ms) > 500) {
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// lock the heading after 0.5 seconds of zero heading input
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// from user
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cruise_state.locked_heading = true;
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cruise_state.lock_timer_ms = 0;
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cruise_state.locked_heading_cd = gps.ground_course_cd();
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prev_WP_loc = current_loc;
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}
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if (cruise_state.locked_heading) {
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next_WP_loc = prev_WP_loc;
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// always look 1km ahead
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location_update(next_WP_loc,
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cruise_state.locked_heading_cd*0.01f,
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get_distance(prev_WP_loc, current_loc) + 1000);
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nav_controller->update_waypoint(prev_WP_loc, next_WP_loc);
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}
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}
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/*
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handle speed and height control in FBWB or CRUISE mode.
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In this mode the elevator is used to change target altitude. The
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throttle is used to change target airspeed or throttle
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*/
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void Plane::update_fbwb_speed_height(void)
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{
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static float last_elevator_input;
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float elevator_input;
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elevator_input = channel_pitch->control_in / 4500.0f;
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if (g.flybywire_elev_reverse) {
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elevator_input = -elevator_input;
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}
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change_target_altitude(g.flybywire_climb_rate * elevator_input * delta_us_fast_loop * 0.0001f);
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if (is_zero(elevator_input) && !is_zero(last_elevator_input)) {
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// the user has just released the elevator, lock in
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// the current altitude
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set_target_altitude_current();
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}
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// check for FBWB altitude limit
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check_minimum_altitude();
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altitude_error_cm = calc_altitude_error_cm();
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last_elevator_input = elevator_input;
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calc_throttle();
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calc_nav_pitch();
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}
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/*
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calculate the turn angle for the next leg of the mission
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*/
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void Plane::setup_turn_angle(void)
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{
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int32_t next_ground_course_cd = mission.get_next_ground_course_cd(-1);
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if (next_ground_course_cd == -1) {
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// the mission library can't determine a turn angle, assume 90 degrees
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auto_state.next_turn_angle = 90.0f;
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} else {
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// get the heading of the current leg
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int32_t ground_course_cd = get_bearing_cd(prev_WP_loc, next_WP_loc);
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// work out the angle we need to turn through
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auto_state.next_turn_angle = wrap_180_cd(next_ground_course_cd - ground_course_cd) * 0.01f;
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}
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}
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