void ECL_L1_Pos_Controller::navigate_loiter(const math::Vector2f &vector_A, const math::Vector2f &vector_curr_position, float radius, int8_t loiter_direction,
const math::Vector2f &ground_speed_vector)
{
/* the complete guidance logic in this section was proposed by [2] */
/* calculate the gains for the PD loop (circle tracking) */
float omega = (2.0f * M_PI_F / _L1_period);
float K_crosstrack = omega * omega;
float K_velocity = 2.0f * _L1_damping * omega;
/* update bearing to next waypoint */
_target_bearing = get_bearing_to_next_waypoint(vector_curr_position.getX(), vector_curr_position.getY(), vector_A.getX(), vector_A.getY());
/* ground speed, enforce minimum of 0.1 m/s to avoid singularities */
float ground_speed = math::max(ground_speed_vector.length() , 0.1f);
/* calculate the L1 length required for the desired period */
_L1_distance = _L1_ratio * ground_speed;
/* calculate the vector from waypoint A to current position */
math::Vector2f vector_A_to_airplane = get_local_planar_vector(vector_A, vector_curr_position);
/* store the normalized vector from waypoint A to current position */
math::Vector2f vector_A_to_airplane_unit = (vector_A_to_airplane).normalized();
/* calculate eta angle towards the loiter center */
/* velocity across / orthogonal to line from waypoint to current position */
float xtrack_vel_center = vector_A_to_airplane_unit % ground_speed_vector;
/* velocity along line from waypoint to current position */
float ltrack_vel_center = - (ground_speed_vector * vector_A_to_airplane_unit);
float eta = atan2f(xtrack_vel_center, ltrack_vel_center);
/* limit eta to 90 degrees */
eta = math::constrain(eta, -M_PI_F / 2.0f, +M_PI_F / 2.0f);
/* calculate the lateral acceleration to capture the center point */
float lateral_accel_sp_center = _K_L1 * ground_speed * ground_speed / _L1_distance * sinf(eta);
/* for PD control: Calculate radial position and velocity errors */
/* radial velocity error */
float xtrack_vel_circle = -ltrack_vel_center;
/* radial distance from the loiter circle (not center) */
float xtrack_err_circle = vector_A_to_airplane.length() - radius;
/* cross track error for feedback */
_crosstrack_error = xtrack_err_circle;
/* calculate PD update to circle waypoint */
float lateral_accel_sp_circle_pd = (xtrack_err_circle * K_crosstrack + xtrack_vel_circle * K_velocity);
/* calculate velocity on circle / along tangent */
float tangent_vel = xtrack_vel_center * loiter_direction;
/* prevent PD output from turning the wrong way */
if (tangent_vel < 0.0f) {
lateral_accel_sp_circle_pd = math::max(lateral_accel_sp_circle_pd , 0.0f);
}
/* calculate centripetal acceleration setpoint */
float lateral_accel_sp_circle_centripetal = tangent_vel * tangent_vel / math::max((0.5f * radius) , (radius + xtrack_err_circle));
/* add PD control on circle and centripetal acceleration for total circle command */
float lateral_accel_sp_circle = loiter_direction * (lateral_accel_sp_circle_pd + lateral_accel_sp_circle_centripetal);
/*
* Switch between circle (loiter) and capture (towards waypoint center) mode when
* the commands switch over. Only fly towards waypoint if outside the circle.
*/
// XXX check switch over
if ((lateral_accel_sp_center < lateral_accel_sp_circle && loiter_direction > 0 && xtrack_err_circle > 0.0f) |
(lateral_accel_sp_center > lateral_accel_sp_circle && loiter_direction < 0 && xtrack_err_circle > 0.0f)) {
_lateral_accel = lateral_accel_sp_center;
_circle_mode = false;
/* angle between requested and current velocity vector */
_bearing_error = eta;
/* bearing from current position to L1 point */
_nav_bearing = atan2f(-vector_A_to_airplane_unit.getY() , -vector_A_to_airplane_unit.getX());
} else {
_lateral_accel = lateral_accel_sp_circle;
_circle_mode = true;
_bearing_error = 0.0f;
/* bearing from current position to L1 point */
_nav_bearing = atan2f(-vector_A_to_airplane_unit.getY() , -vector_A_to_airplane_unit.getX());
}
}
void ECL_L1_Pos_Controller::navigate_waypoints(const math::Vector2f &vector_A, const math::Vector2f &vector_B, const math::Vector2f &vector_curr_position,
const math::Vector2f &ground_speed_vector)
{
/* this follows the logic presented in [1] */
float eta;
float xtrack_vel;
float ltrack_vel;
/* get the direction between the last (visited) and next waypoint */
_target_bearing = get_bearing_to_next_waypoint(vector_curr_position.getX(), vector_curr_position.getY(), vector_B.getX(), vector_B.getY());
/* enforce a minimum ground speed of 0.1 m/s to avoid singularities */
float ground_speed = math::max(ground_speed_vector.length(), 0.1f);
/* calculate the L1 length required for the desired period */
_L1_distance = _L1_ratio * ground_speed;
/* calculate vector from A to B */
math::Vector2f vector_AB = get_local_planar_vector(vector_A, vector_B);
/*
* check if waypoints are on top of each other. If yes,
* skip A and directly continue to B
*/
if (vector_AB.length() < 1.0e-6f) {
vector_AB = get_local_planar_vector(vector_curr_position, vector_B);
}
vector_AB.normalize();
/* calculate the vector from waypoint A to the aircraft */
math::Vector2f vector_A_to_airplane = get_local_planar_vector(vector_A, vector_curr_position);
/* calculate crosstrack error (output only) */
_crosstrack_error = vector_AB % vector_A_to_airplane;
/*
* If the current position is in a +-135 degree angle behind waypoint A
* and further away from A than the L1 distance, then A becomes the L1 point.
* If the aircraft is already between A and B normal L1 logic is applied.
*/
float distance_A_to_airplane = vector_A_to_airplane.length();
float alongTrackDist = vector_A_to_airplane * vector_AB;
/* estimate airplane position WRT to B */
math::Vector2f vector_B_to_airplane_unit = get_local_planar_vector(vector_B, vector_curr_position).normalized();
float bearing_wp_b = atan2f(-vector_B_to_airplane_unit.getY() , -vector_B_to_airplane_unit.getX());
/* extension from [2], fly directly to A */
if (distance_A_to_airplane > _L1_distance && alongTrackDist / math::max(distance_A_to_airplane , 1.0f) < -0.7071f) {
/* calculate eta to fly to waypoint A */
/* unit vector from waypoint A to current position */
math::Vector2f vector_A_to_airplane_unit = vector_A_to_airplane.normalized();
/* velocity across / orthogonal to line */
xtrack_vel = ground_speed_vector % (-vector_A_to_airplane_unit);
/* velocity along line */
ltrack_vel = ground_speed_vector * (-vector_A_to_airplane_unit);
eta = atan2f(xtrack_vel, ltrack_vel);
/* bearing from current position to L1 point */
_nav_bearing = atan2f(-vector_A_to_airplane_unit.getY() , -vector_A_to_airplane_unit.getX());
// XXX this can be useful as last-resort guard, but is currently not needed
#if 0
} else if (absf(bearing_wp_b) > math::radians(80.0f)) {
/* extension, fly back to waypoint */
/* calculate eta to fly to waypoint B */
/* velocity across / orthogonal to line */
xtrack_vel = ground_speed_vector % (-vector_B_to_airplane_unit);
/* velocity along line */
ltrack_vel = ground_speed_vector * (-vector_B_to_airplane_unit);
eta = atan2f(xtrack_vel, ltrack_vel);
/* bearing from current position to L1 point */
_nav_bearing = bearing_wp_b;
#endif
} else {
/* calculate eta to fly along the line between A and B */
/* velocity across / orthogonal to line */
xtrack_vel = ground_speed_vector % vector_AB;
/* velocity along line */
ltrack_vel = ground_speed_vector * vector_AB;
/* calculate eta2 (angle of velocity vector relative to line) */
float eta2 = atan2f(xtrack_vel, ltrack_vel);
/* calculate eta1 (angle to L1 point) */
float xtrackErr = vector_A_to_airplane % vector_AB;
float sine_eta1 = xtrackErr / math::max(_L1_distance , 0.1f);
/* limit output to 45 degrees */
sine_eta1 = math::constrain(sine_eta1, -M_PI_F / 4.0f, +M_PI_F / 4.0f);
float eta1 = asinf(sine_eta1);
eta = eta1 + eta2;
/* bearing from current position to L1 point */
_nav_bearing = atan2f(vector_AB.getY(), vector_AB.getX()) + eta1;
}
/* limit angle to +-90 degrees */
eta = math::constrain(eta, (-M_PI_F) / 2.0f, +M_PI_F / 2.0f);
_lateral_accel = _K_L1 * ground_speed * ground_speed / _L1_distance * sinf(eta);
/* flying to waypoints, not circling them */
_circle_mode = false;
/* the bearing angle, in NED frame */
_bearing_error = eta;
}
void ECL_L1_Pos_Controller::navigate_waypoints(const math::Vector2f &vector_A, const math::Vector2f &vector_B, const math::Vector2f &vector_curr_position,
const math::Vector2f &ground_speed_vector)
{
/* this follows the logic presented in [1] */
float eta;
float xtrack_vel;
float ltrack_vel;
/* get the direction between the last (visited) and next waypoint */
_target_bearing = get_bearing_to_next_waypoint(vector_curr_position.getX(), vector_curr_position.getY(), vector_B.getX(), vector_B.getY());
/* enforce a minimum ground speed of 0.1 m/s to avoid singularities */
float ground_speed = math::max(ground_speed_vector.length(), 0.1f);
/* calculate the L1 length required for the desired period */
_L1_distance = _L1_ratio * ground_speed;
/* calculate vector from A to B */
math::Vector2f vector_AB = get_local_planar_vector(vector_A, vector_B);
/*
* check if waypoints are on top of each other. If yes,
* skip A and directly continue to B
*/
if (vector_AB.length() < 1.0e-6f) {
vector_AB = get_local_planar_vector(vector_curr_position, vector_B);
}
vector_AB.normalize();
/* calculate the vector from waypoint A to the aircraft */
math::Vector2f vector_A_to_airplane = get_local_planar_vector(vector_A, vector_curr_position);
/* calculate crosstrack error (output only) */
_crosstrack_error = vector_AB % vector_A_to_airplane;
/*
* If the current position is in a +-135 degree angle behind waypoint A
* and further away from A than the L1 distance, then A becomes the L1 point.
* If the aircraft is already between A and B normal L1 logic is applied.
*/
float distance_A_to_airplane = vector_A_to_airplane.length();
float alongTrackDist = vector_A_to_airplane * vector_AB;
/* estimate airplane position WRT to B */
math::Vector2f vector_B_to_P_unit = get_local_planar_vector(vector_B, vector_curr_position).normalized();
/* calculate angle of airplane position vector relative to line) */
// XXX this could probably also be based solely on the dot product
float AB_to_BP_bearing = atan2f(vector_B_to_P_unit % vector_AB, vector_B_to_P_unit * vector_AB);
/* extension from [2], fly directly to A */
if (distance_A_to_airplane > _L1_distance && alongTrackDist / math::max(distance_A_to_airplane , 1.0f) < -0.7071f) {
/* calculate eta to fly to waypoint A */
/* unit vector from waypoint A to current position */
math::Vector2f vector_A_to_airplane_unit = vector_A_to_airplane.normalized();
/* velocity across / orthogonal to line */
xtrack_vel = ground_speed_vector % (-vector_A_to_airplane_unit);
/* velocity along line */
ltrack_vel = ground_speed_vector * (-vector_A_to_airplane_unit);
eta = atan2f(xtrack_vel, ltrack_vel);
/* bearing from current position to L1 point */
_nav_bearing = atan2f(-vector_A_to_airplane_unit.getY() , -vector_A_to_airplane_unit.getX());
/*
* If the AB vector and the vector from B to airplane point in the same
* direction, we have missed the waypoint. At +- 90 degrees we are just passing it.
*/
} else if (fabsf(AB_to_BP_bearing) < math::radians(100.0f)) {
/*
* Extension, fly back to waypoint.
*
* This corner case is possible if the system was following
* the AB line from waypoint A to waypoint B, then is
* switched to manual mode (or otherwise misses the waypoint)
* and behind the waypoint continues to follow the AB line.
*/
/* calculate eta to fly to waypoint B */
/* velocity across / orthogonal to line */
xtrack_vel = ground_speed_vector % (-vector_B_to_P_unit);
/* velocity along line */
ltrack_vel = ground_speed_vector * (-vector_B_to_P_unit);
eta = atan2f(xtrack_vel, ltrack_vel);
/* bearing from current position to L1 point */
_nav_bearing = atan2f(-vector_B_to_P_unit.getY() , -vector_B_to_P_unit.getX());
} else {
/* calculate eta to fly along the line between A and B */
/* velocity across / orthogonal to line */
xtrack_vel = ground_speed_vector % vector_AB;
/* velocity along line */
ltrack_vel = ground_speed_vector * vector_AB;
/* calculate eta2 (angle of velocity vector relative to line) */
float eta2 = atan2f(xtrack_vel, ltrack_vel);
/* calculate eta1 (angle to L1 point) */
float xtrackErr = vector_A_to_airplane % vector_AB;
float sine_eta1 = xtrackErr / math::max(_L1_distance , 0.1f);
/* limit output to 45 degrees */
sine_eta1 = math::constrain(sine_eta1, -0.7071f, 0.7071f); //sin(pi/4) = 0.7071
float eta1 = asinf(sine_eta1);
eta = eta1 + eta2;
/* bearing from current position to L1 point */
_nav_bearing = atan2f(vector_AB.getY(), vector_AB.getX()) + eta1;
}
/* limit angle to +-90 degrees */
eta = math::constrain(eta, (-M_PI_F) / 2.0f, +M_PI_F / 2.0f);
_lateral_accel = _K_L1 * ground_speed * ground_speed / _L1_distance * sinf(eta);
/* flying to waypoints, not circling them */
_circle_mode = false;
/* the bearing angle, in NED frame */
_bearing_error = eta;
}
