forked from Archive/PX4-Autopilot
373 lines
14 KiB
C++
373 lines
14 KiB
C++
/****************************************************************************
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*
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* Copyright (c) 2013 Estimation and Control Library (ECL). All rights reserved.
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*
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* Redistribution and use in source and binary forms, with or without
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* modification, are permitted provided that the following conditions
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* are met:
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*
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* 1. Redistributions of source code must retain the above copyright
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* notice, this list of conditions and the following disclaimer.
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* 2. Redistributions in binary form must reproduce the above copyright
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* notice, this list of conditions and the following disclaimer in
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* the documentation and/or other materials provided with the
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* distribution.
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* 3. Neither the name ECL nor the names of its contributors may be
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* used to endorse or promote products derived from this software
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* without specific prior written permission.
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*
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* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
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* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
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* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
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* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
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* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
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* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
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* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
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* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
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* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
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* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
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* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
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* POSSIBILITY OF SUCH DAMAGE.
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*
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****************************************************************************/
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/**
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* @file ecl_l1_pos_controller.h
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* Implementation of L1 position control.
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* Authors and acknowledgements in header.
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*
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*/
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#include <float.h>
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#include "ecl_l1_pos_controller.h"
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float ECL_L1_Pos_Controller::nav_roll()
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{
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float ret = atanf(_lateral_accel * 1.0f / CONSTANTS_ONE_G);
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ret = math::constrain(ret, -_roll_lim_rad, _roll_lim_rad);
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return ret;
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}
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float ECL_L1_Pos_Controller::nav_lateral_acceleration_demand()
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{
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return _lateral_accel;
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}
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float ECL_L1_Pos_Controller::nav_bearing()
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{
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return _wrap_pi(_nav_bearing);
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}
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float ECL_L1_Pos_Controller::bearing_error()
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{
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return _bearing_error;
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}
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float ECL_L1_Pos_Controller::target_bearing()
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{
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return _target_bearing;
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}
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float ECL_L1_Pos_Controller::switch_distance(float wp_radius)
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{
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/* following [2], switching on L1 distance */
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return math::min(wp_radius, _L1_distance);
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}
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bool ECL_L1_Pos_Controller::reached_loiter_target()
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{
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return _circle_mode;
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}
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float ECL_L1_Pos_Controller::crosstrack_error()
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{
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return _crosstrack_error;
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}
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void ECL_L1_Pos_Controller::navigate_waypoints(const math::Vector<2> &vector_A, const math::Vector<2> &vector_B, const math::Vector<2> &vector_curr_position,
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const math::Vector<2> &ground_speed_vector)
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{
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/* this follows the logic presented in [1] */
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float eta;
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float xtrack_vel;
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float ltrack_vel;
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/* get the direction between the last (visited) and next waypoint */
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_target_bearing = get_bearing_to_next_waypoint(vector_curr_position(0), vector_curr_position(1), vector_B(0), vector_B(1));
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/* enforce a minimum ground speed of 0.1 m/s to avoid singularities */
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float ground_speed = math::max(ground_speed_vector.length(), 0.1f);
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/* calculate the L1 length required for the desired period */
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_L1_distance = _L1_ratio * ground_speed;
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/* calculate vector from A to B */
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math::Vector<2> vector_AB = get_local_planar_vector(vector_A, vector_B);
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/*
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* check if waypoints are on top of each other. If yes,
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* skip A and directly continue to B
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*/
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if (vector_AB.length() < 1.0e-6f) {
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vector_AB = get_local_planar_vector(vector_curr_position, vector_B);
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}
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vector_AB.normalize();
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/* calculate the vector from waypoint A to the aircraft */
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math::Vector<2> vector_A_to_airplane = get_local_planar_vector(vector_A, vector_curr_position);
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/* calculate crosstrack error (output only) */
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_crosstrack_error = vector_AB % vector_A_to_airplane;
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/*
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* If the current position is in a +-135 degree angle behind waypoint A
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* and further away from A than the L1 distance, then A becomes the L1 point.
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* If the aircraft is already between A and B normal L1 logic is applied.
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*/
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float distance_A_to_airplane = vector_A_to_airplane.length();
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float alongTrackDist = vector_A_to_airplane * vector_AB;
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/* estimate airplane position WRT to B */
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math::Vector<2> vector_B_to_P_unit = get_local_planar_vector(vector_B, vector_curr_position).normalized();
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/* calculate angle of airplane position vector relative to line) */
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// XXX this could probably also be based solely on the dot product
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float AB_to_BP_bearing = atan2f(vector_B_to_P_unit % vector_AB, vector_B_to_P_unit * vector_AB);
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/* extension from [2], fly directly to A */
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if (distance_A_to_airplane > _L1_distance && alongTrackDist / math::max(distance_A_to_airplane , 1.0f) < -0.7071f) {
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/* calculate eta to fly to waypoint A */
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/* unit vector from waypoint A to current position */
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math::Vector<2> vector_A_to_airplane_unit = vector_A_to_airplane.normalized();
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/* velocity across / orthogonal to line */
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xtrack_vel = ground_speed_vector % (-vector_A_to_airplane_unit);
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/* velocity along line */
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ltrack_vel = ground_speed_vector * (-vector_A_to_airplane_unit);
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eta = atan2f(xtrack_vel, ltrack_vel);
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/* bearing from current position to L1 point */
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_nav_bearing = atan2f(-vector_A_to_airplane_unit(1) , -vector_A_to_airplane_unit(0));
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/*
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* If the AB vector and the vector from B to airplane point in the same
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* direction, we have missed the waypoint. At +- 90 degrees we are just passing it.
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*/
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} else if (fabsf(AB_to_BP_bearing) < math::radians(100.0f)) {
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/*
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* Extension, fly back to waypoint.
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*
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* This corner case is possible if the system was following
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* the AB line from waypoint A to waypoint B, then is
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* switched to manual mode (or otherwise misses the waypoint)
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* and behind the waypoint continues to follow the AB line.
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*/
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/* calculate eta to fly to waypoint B */
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/* velocity across / orthogonal to line */
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xtrack_vel = ground_speed_vector % (-vector_B_to_P_unit);
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/* velocity along line */
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ltrack_vel = ground_speed_vector * (-vector_B_to_P_unit);
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eta = atan2f(xtrack_vel, ltrack_vel);
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/* bearing from current position to L1 point */
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_nav_bearing = atan2f(-vector_B_to_P_unit(1) , -vector_B_to_P_unit(0));
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} else {
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/* calculate eta to fly along the line between A and B */
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/* velocity across / orthogonal to line */
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xtrack_vel = ground_speed_vector % vector_AB;
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/* velocity along line */
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ltrack_vel = ground_speed_vector * vector_AB;
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/* calculate eta2 (angle of velocity vector relative to line) */
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float eta2 = atan2f(xtrack_vel, ltrack_vel);
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/* calculate eta1 (angle to L1 point) */
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float xtrackErr = vector_A_to_airplane % vector_AB;
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float sine_eta1 = xtrackErr / math::max(_L1_distance , 0.1f);
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/* limit output to 45 degrees */
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sine_eta1 = math::constrain(sine_eta1, -0.7071f, 0.7071f); //sin(pi/4) = 0.7071
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float eta1 = asinf(sine_eta1);
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eta = eta1 + eta2;
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/* bearing from current position to L1 point */
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_nav_bearing = atan2f(vector_AB(1), vector_AB(0)) + eta1;
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}
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/* limit angle to +-90 degrees */
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eta = math::constrain(eta, (-M_PI_F) / 2.0f, +M_PI_F / 2.0f);
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_lateral_accel = _K_L1 * ground_speed * ground_speed / _L1_distance * sinf(eta);
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/* flying to waypoints, not circling them */
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_circle_mode = false;
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/* the bearing angle, in NED frame */
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_bearing_error = eta;
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}
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void ECL_L1_Pos_Controller::navigate_loiter(const math::Vector<2> &vector_A, const math::Vector<2> &vector_curr_position, float radius, int8_t loiter_direction,
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const math::Vector<2> &ground_speed_vector)
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{
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/* the complete guidance logic in this section was proposed by [2] */
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/* calculate the gains for the PD loop (circle tracking) */
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float omega = (2.0f * M_PI_F / _L1_period);
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float K_crosstrack = omega * omega;
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float K_velocity = 2.0f * _L1_damping * omega;
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/* update bearing to next waypoint */
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_target_bearing = get_bearing_to_next_waypoint(vector_curr_position(0), vector_curr_position(1), vector_A(0), vector_A(1));
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/* ground speed, enforce minimum of 0.1 m/s to avoid singularities */
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float ground_speed = math::max(ground_speed_vector.length() , 0.1f);
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/* calculate the L1 length required for the desired period */
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_L1_distance = _L1_ratio * ground_speed;
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/* calculate the vector from waypoint A to current position */
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math::Vector<2> vector_A_to_airplane = get_local_planar_vector(vector_A, vector_curr_position);
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math::Vector<2> vector_A_to_airplane_unit;
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/* prevent NaN when normalizing */
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if (vector_A_to_airplane.length() > FLT_EPSILON) {
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/* store the normalized vector from waypoint A to current position */
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vector_A_to_airplane_unit = vector_A_to_airplane.normalized();
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} else {
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vector_A_to_airplane_unit = vector_A_to_airplane;
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}
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/* calculate eta angle towards the loiter center */
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/* velocity across / orthogonal to line from waypoint to current position */
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float xtrack_vel_center = vector_A_to_airplane_unit % ground_speed_vector;
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/* velocity along line from waypoint to current position */
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float ltrack_vel_center = - (ground_speed_vector * vector_A_to_airplane_unit);
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float eta = atan2f(xtrack_vel_center, ltrack_vel_center);
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/* limit eta to 90 degrees */
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eta = math::constrain(eta, -M_PI_F / 2.0f, +M_PI_F / 2.0f);
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/* calculate the lateral acceleration to capture the center point */
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float lateral_accel_sp_center = _K_L1 * ground_speed * ground_speed / _L1_distance * sinf(eta);
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/* for PD control: Calculate radial position and velocity errors */
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/* radial velocity error */
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float xtrack_vel_circle = -ltrack_vel_center;
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/* radial distance from the loiter circle (not center) */
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float xtrack_err_circle = vector_A_to_airplane.length() - radius;
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/* cross track error for feedback */
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_crosstrack_error = xtrack_err_circle;
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/* calculate PD update to circle waypoint */
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float lateral_accel_sp_circle_pd = (xtrack_err_circle * K_crosstrack + xtrack_vel_circle * K_velocity);
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/* calculate velocity on circle / along tangent */
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float tangent_vel = xtrack_vel_center * loiter_direction;
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/* prevent PD output from turning the wrong way */
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if (tangent_vel < 0.0f) {
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lateral_accel_sp_circle_pd = math::max(lateral_accel_sp_circle_pd , 0.0f);
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}
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/* calculate centripetal acceleration setpoint */
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float lateral_accel_sp_circle_centripetal = tangent_vel * tangent_vel / math::max((0.5f * radius) , (radius + xtrack_err_circle));
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/* add PD control on circle and centripetal acceleration for total circle command */
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float lateral_accel_sp_circle = loiter_direction * (lateral_accel_sp_circle_pd + lateral_accel_sp_circle_centripetal);
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/*
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* Switch between circle (loiter) and capture (towards waypoint center) mode when
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* the commands switch over. Only fly towards waypoint if outside the circle.
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*/
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// XXX check switch over
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if ((lateral_accel_sp_center < lateral_accel_sp_circle && loiter_direction > 0 && xtrack_err_circle > 0.0f) ||
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(lateral_accel_sp_center > lateral_accel_sp_circle && loiter_direction < 0 && xtrack_err_circle > 0.0f)) {
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_lateral_accel = lateral_accel_sp_center;
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_circle_mode = false;
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/* angle between requested and current velocity vector */
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_bearing_error = eta;
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/* bearing from current position to L1 point */
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_nav_bearing = atan2f(-vector_A_to_airplane_unit(1) , -vector_A_to_airplane_unit(0));
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} else {
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_lateral_accel = lateral_accel_sp_circle;
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_circle_mode = true;
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_bearing_error = 0.0f;
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/* bearing from current position to L1 point */
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_nav_bearing = atan2f(-vector_A_to_airplane_unit(1) , -vector_A_to_airplane_unit(0));
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}
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}
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void ECL_L1_Pos_Controller::navigate_heading(float navigation_heading, float current_heading, const math::Vector<2> &ground_speed_vector)
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{
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/* the complete guidance logic in this section was proposed by [2] */
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float eta;
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/*
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* As the commanded heading is the only reference
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* (and no crosstrack correction occurs),
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* target and navigation bearing become the same
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*/
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_target_bearing = _nav_bearing = _wrap_pi(navigation_heading);
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eta = _target_bearing - _wrap_pi(current_heading);
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eta = _wrap_pi(eta);
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/* consequently the bearing error is exactly eta: */
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_bearing_error = eta;
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/* ground speed is the length of the ground speed vector */
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float ground_speed = ground_speed_vector.length();
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/* adjust L1 distance to keep constant frequency */
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_L1_distance = ground_speed / _heading_omega;
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float omega_vel = ground_speed * _heading_omega;
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/* not circling a waypoint */
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_circle_mode = false;
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/* navigating heading means by definition no crosstrack error */
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_crosstrack_error = 0;
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/* limit eta to 90 degrees */
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eta = math::constrain(eta, (-M_PI_F) / 2.0f, +M_PI_F / 2.0f);
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_lateral_accel = 2.0f * sinf(eta) * omega_vel;
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}
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void ECL_L1_Pos_Controller::navigate_level_flight(float current_heading)
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{
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/* the logic in this section is trivial, but originally proposed by [2] */
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/* reset all heading / error measures resulting in zero roll */
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_target_bearing = current_heading;
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_nav_bearing = current_heading;
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_bearing_error = 0;
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_crosstrack_error = 0;
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_lateral_accel = 0;
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/* not circling a waypoint when flying level */
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_circle_mode = false;
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}
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math::Vector<2> ECL_L1_Pos_Controller::get_local_planar_vector(const math::Vector<2> &origin, const math::Vector<2> &target) const
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{
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/* this is an approximation for small angles, proposed by [2] */
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math::Vector<2> out(math::radians((target(0) - origin(0))), math::radians((target(1) - origin(1))*cosf(math::radians(origin(0)))));
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return out * static_cast<float>(CONSTANTS_RADIUS_OF_EARTH);
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}
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