void ECL_L1_Pos_Controller::navigate_heading(float navigation_heading, float current_heading, const math::Vector2f &ground_speed_vector)
{
/* the complete guidance logic in this section was proposed by [2] */
float eta;
/*
* As the commanded heading is the only reference
* (and no crosstrack correction occurs),
* target and navigation bearing become the same
*/
_target_bearing = _nav_bearing = _wrap_pi(navigation_heading);
eta = _target_bearing - _wrap_pi(current_heading);
eta = _wrap_pi(eta);
/* consequently the bearing error is exactly eta: */
_bearing_error = eta;
/* ground speed is the length of the ground speed vector */
float ground_speed = ground_speed_vector.length();
/* adjust L1 distance to keep constant frequency */
_L1_distance = ground_speed / _heading_omega;
float omega_vel = ground_speed * _heading_omega;
/* not circling a waypoint */
_circle_mode = false;
/* navigating heading means by definition no crosstrack error */
_crosstrack_error = 0;
/* limit eta to 90 degrees */
eta = math::constrain(eta, (-M_PI_F) / 2.0f, +M_PI_F / 2.0f);
_lateral_accel = 2.0f * sinf(eta) * omega_vel;
}
__EXPORT int get_distance_to_line(struct crosstrack_error_s *crosstrack_error, double lat_now, double lon_now,
double lat_start, double lon_start, double lat_end, double lon_end)
{
// This function returns the distance to the nearest point on the track line. Distance is positive if current
// position is right of the track and negative if left of the track as seen from a point on the track line
// headed towards the end point.
float dist_to_end;
float bearing_end;
float bearing_track;
float bearing_diff;
int return_value = ERROR; // Set error flag, cleared when valid result calculated.
crosstrack_error->past_end = false;
crosstrack_error->distance = 0.0f;
crosstrack_error->bearing = 0.0f;
dist_to_end = get_distance_to_next_waypoint(lat_now, lon_now, lat_end, lon_end);
// Return error if arguments are bad
if (dist_to_end < 0.1f) {
return ERROR;
}
bearing_end = get_bearing_to_next_waypoint(lat_now, lon_now, lat_end, lon_end);
bearing_track = get_bearing_to_next_waypoint(lat_start, lon_start, lat_end, lon_end);
bearing_diff = bearing_track - bearing_end;
bearing_diff = _wrap_pi(bearing_diff);
// Return past_end = true if past end point of line
if (bearing_diff > M_PI_2_F || bearing_diff < -M_PI_2_F) {
crosstrack_error->past_end = true;
return_value = OK;
return return_value;
}
crosstrack_error->distance = (dist_to_end) * sinf(bearing_diff);
if (sin(bearing_diff) >= 0) {
crosstrack_error->bearing = _wrap_pi(bearing_track - M_PI_2_F);
} else {
crosstrack_error->bearing = _wrap_pi(bearing_track + M_PI_2_F);
}
return_value = OK;
return return_value;
}
float ECL_WheelController::control_attitude(const struct ECL_ControlData &ctl_data)
{
/* Do not calculate control signal with bad inputs */
if (!(ISFINITE(ctl_data.yaw_setpoint) &&
ISFINITE(ctl_data.yaw))) {
return _rate_setpoint;
}
/* Calculate the error */
float yaw_error = _wrap_pi(ctl_data.yaw_setpoint - ctl_data.yaw);
/* Apply P controller: rate setpoint from current error and time constant */
_rate_setpoint = yaw_error / _tc;
/* limit the rate */
if (_max_rate > 0.01f) {
if (_rate_setpoint > 0.0f) {
_rate_setpoint = (_rate_setpoint > _max_rate) ? _max_rate : _rate_setpoint;
} else {
_rate_setpoint = (_rate_setpoint < -_max_rate) ? -_max_rate : _rate_setpoint;
}
}
return _rate_setpoint;
}
int
MavlinkMissionManager::parse_mavlink_mission_item(const mavlink_mission_item_t *mavlink_mission_item, struct mission_item_s *mission_item)
{
/* only support global waypoints for now */
switch (mavlink_mission_item->frame) {
case MAV_FRAME_GLOBAL:
mission_item->lat = (double)mavlink_mission_item->x;
mission_item->lon = (double)mavlink_mission_item->y;
mission_item->altitude = mavlink_mission_item->z;
mission_item->altitude_is_relative = false;
break;
case MAV_FRAME_GLOBAL_RELATIVE_ALT:
mission_item->lat = (double)mavlink_mission_item->x;
mission_item->lon = (double)mavlink_mission_item->y;
mission_item->altitude = mavlink_mission_item->z;
mission_item->altitude_is_relative = true;
break;
case MAV_FRAME_LOCAL_NED:
case MAV_FRAME_LOCAL_ENU:
return MAV_MISSION_UNSUPPORTED_FRAME;
case MAV_FRAME_MISSION:
default:
return MAV_MISSION_ERROR;
}
switch (mavlink_mission_item->command) {
case MAV_CMD_NAV_TAKEOFF:
mission_item->pitch_min = mavlink_mission_item->param1;
break;
case MAV_CMD_DO_JUMP:
mission_item->do_jump_mission_index = mavlink_mission_item->param1;
mission_item->do_jump_current_count = 0;
mission_item->do_jump_repeat_count = mavlink_mission_item->param2;
break;
default:
mission_item->acceptance_radius = mavlink_mission_item->param2;
mission_item->time_inside = mavlink_mission_item->param1;
break;
}
mission_item->yaw = _wrap_pi(mavlink_mission_item->param4 * M_DEG_TO_RAD_F);
mission_item->loiter_radius = fabsf(mavlink_mission_item->param3);
mission_item->loiter_direction = (mavlink_mission_item->param3 > 0) ? 1 : -1; /* 1 if positive CW, -1 if negative CCW */
mission_item->nav_cmd = (NAV_CMD)mavlink_mission_item->command;
mission_item->autocontinue = mavlink_mission_item->autocontinue;
// mission_item->index = mavlink_mission_item->seq;
mission_item->origin = ORIGIN_MAVLINK;
/* reset DO_JUMP count */
mission_item->do_jump_current_count = 0;
return MAV_MISSION_ACCEPTED;
}
void
Delivery::heading_sp_update()
{
if (_takeoff) {
/* we don't want to be yawing during takeoff */
return;
}
struct position_setpoint_triplet_s *pos_sp_triplet = _navigator->get_position_setpoint_triplet();
/* Don't change setpoint if last and current waypoint are not valid */
if (!pos_sp_triplet->previous.valid || !pos_sp_triplet->current.valid ||
!isfinite(_on_arrival_yaw)) {
return;
}
/* Don't do FOH for landing and takeoff waypoints, the ground may be near
* and the FW controller has a custom landing logic */
if (_mission_item.nav_cmd == NAV_CMD_LAND || _mission_item.nav_cmd == NAV_CMD_TAKEOFF) {
return;
}
/* set yaw angle for the waypoint iff a loiter time has been specified */
if (_waypoint_position_reached && _mission_item.time_inside > 0.0f) {
_mission_item.yaw = _on_arrival_yaw;
/* always keep the front of the rotary wing pointing to the next waypoint */
} else if (_param_yawmode.get() == MISSION_YAWMODE_FRONT_TO_WAYPOINT) {
_mission_item.yaw = get_bearing_to_next_waypoint(
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_mission_item.lat,
_mission_item.lon);
/* always keep the back of the rotary wing pointing towards home */
} else if (_param_yawmode.get() == MISSION_YAWMODE_FRONT_TO_HOME) {
_mission_item.yaw = get_bearing_to_next_waypoint(
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_navigator->get_home_position()->lat,
_navigator->get_home_position()->lon);
/* always keep the back of the rotary wing pointing towards home */
} else if (_param_yawmode.get() == MISSION_YAWMODE_BACK_TO_HOME) {
_mission_item.yaw = _wrap_pi(get_bearing_to_next_waypoint(
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_navigator->get_home_position()->lat,
_navigator->get_home_position()->lon) + M_PI_F);
}
mission_item_to_position_setpoint(&_mission_item, &pos_sp_triplet->current);
_navigator->set_position_setpoint_triplet_updated();
}
__EXPORT float get_bearing_to_next_waypoint(double lat_now, double lon_now, double lat_next, double lon_next)
{
double lat_now_rad = lat_now * M_DEG_TO_RAD;
double lon_now_rad = lon_now * M_DEG_TO_RAD;
double lat_next_rad = lat_next * M_DEG_TO_RAD;
double lon_next_rad = lon_next * M_DEG_TO_RAD;
double d_lon = lon_next_rad - lon_now_rad;
/* conscious mix of double and float trig function to maximize speed and efficiency */
float theta = atan2f(sin(d_lon) * cos(lat_next_rad) , cos(lat_now_rad) * sin(lat_next_rad) - sin(lat_now_rad) * cos(lat_next_rad) * cos(d_lon));
theta = _wrap_pi(theta);
return theta;
}
void
MavlinkReceiver::handle_message_hil_gps(mavlink_message_t *msg)
{
mavlink_hil_gps_t gps;
mavlink_msg_hil_gps_decode(msg, &gps);
uint64_t timestamp = hrt_absolute_time();
struct vehicle_gps_position_s hil_gps;
memset(&hil_gps, 0, sizeof(hil_gps));
hil_gps.timestamp_time = timestamp;
hil_gps.time_gps_usec = gps.time_usec;
hil_gps.timestamp_position = timestamp;
hil_gps.lat = gps.lat;
hil_gps.lon = gps.lon;
hil_gps.alt = gps.alt;
hil_gps.eph_m = (float)gps.eph * 1e-2f; // from cm to m
hil_gps.epv_m = (float)gps.epv * 1e-2f; // from cm to m
hil_gps.timestamp_variance = timestamp;
hil_gps.s_variance_m_s = 5.0f;
hil_gps.p_variance_m = hil_gps.eph_m * hil_gps.eph_m;
hil_gps.timestamp_velocity = timestamp;
hil_gps.vel_m_s = (float)gps.vel * 1e-2f; // from cm/s to m/s
hil_gps.vel_n_m_s = gps.vn * 1e-2f; // from cm to m
hil_gps.vel_e_m_s = gps.ve * 1e-2f; // from cm to m
hil_gps.vel_d_m_s = gps.vd * 1e-2f; // from cm to m
hil_gps.vel_ned_valid = true;
hil_gps.cog_rad = _wrap_pi(gps.cog * M_DEG_TO_RAD_F * 1e-2f);
hil_gps.timestamp_satellites = timestamp;
hil_gps.fix_type = gps.fix_type;
hil_gps.satellites_visible = gps.satellites_visible;
if (_gps_pub < 0) {
_gps_pub = orb_advertise(ORB_ID(vehicle_gps_position), &hil_gps);
} else {
orb_publish(ORB_ID(vehicle_gps_position), _gps_pub, &hil_gps);
}
}
int set_vehicle_global_position_setpoint (int index, float yaw_sp, struct vehicle_global_position_setpoint_s* g_sp)
{
mission_command_t cmd = mission.command_list[index];
float navigation_alt, navigation_lat, navigation_lon;
navigation_alt = cmd.option1;
navigation_lat = (cmd.name == accepted_command_rtl ||
cmd.name == accepted_command_land)? home_position.latitude : cmd.option2;
navigation_lon = (cmd.name == accepted_command_rtl ||
cmd.name == accepted_command_land)? home_position.longitude : cmd.option3;
/* Update setpoints */
g_sp->altitude = navigation_alt;
g_sp->latitude = navigation_lat * 1e7f;
g_sp->longitude = navigation_lon * 1e7f;
g_sp->altitude_is_relative = 0;
g_sp->yaw = _wrap_pi(yaw_sp / 180.0f * M_PI);
return set_special_fields(cmd.name, cmd.option4, cmd.option5, g_sp);
}
bool
MissionBlock::is_mission_item_reached()
{
/* handle non-navigation or indefinite waypoints */
switch (_mission_item.nav_cmd) {
case NAV_CMD_DO_SET_SERVO:
return true;
case NAV_CMD_LAND: /* fall through */
case NAV_CMD_VTOL_LAND:
return _navigator->get_land_detected()->landed;
case NAV_CMD_IDLE: /* fall through */
case NAV_CMD_LOITER_UNLIMITED:
return false;
case NAV_CMD_DO_LAND_START:
case NAV_CMD_DO_TRIGGER_CONTROL:
case NAV_CMD_DO_DIGICAM_CONTROL:
case NAV_CMD_IMAGE_START_CAPTURE:
case NAV_CMD_IMAGE_STOP_CAPTURE:
case NAV_CMD_VIDEO_START_CAPTURE:
case NAV_CMD_VIDEO_STOP_CAPTURE:
case NAV_CMD_DO_MOUNT_CONFIGURE:
case NAV_CMD_DO_MOUNT_CONTROL:
case NAV_CMD_DO_SET_ROI:
case NAV_CMD_DO_SET_CAM_TRIGG_DIST:
case NAV_CMD_DO_SET_CAM_TRIGG_INTERVAL:
case NAV_CMD_SET_CAMERA_MODE:
return true;
case NAV_CMD_DO_VTOL_TRANSITION:
/*
* We wait half a second to give the transition command time to propagate.
* Then monitor the transition status for completion.
*/
// TODO: check desired transition state achieved and drop _action_start
if (hrt_absolute_time() - _action_start > 500000 &&
!_navigator->get_vstatus()->in_transition_mode) {
_action_start = 0;
return true;
} else {
return false;
}
case NAV_CMD_DO_CHANGE_SPEED:
return true;
default:
/* do nothing, this is a 3D waypoint */
break;
}
hrt_abstime now = hrt_absolute_time();
if (!_navigator->get_land_detected()->landed && !_waypoint_position_reached) {
float dist = -1.0f;
float dist_xy = -1.0f;
float dist_z = -1.0f;
float altitude_amsl = _mission_item.altitude_is_relative
? _mission_item.altitude + _navigator->get_home_position()->alt
: _mission_item.altitude;
dist = get_distance_to_point_global_wgs84(_mission_item.lat, _mission_item.lon, altitude_amsl,
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_navigator->get_global_position()->alt,
&dist_xy, &dist_z);
/* FW special case for NAV_CMD_WAYPOINT to achieve altitude via loiter */
if (!_navigator->get_vstatus()->is_rotary_wing &&
(_mission_item.nav_cmd == NAV_CMD_WAYPOINT)) {
struct position_setpoint_s *curr_sp = &_navigator->get_position_setpoint_triplet()->current;
/* close to waypoint, but altitude error greater than twice acceptance */
if ((dist >= 0.0f)
&& (dist_z > 2 * _navigator->get_altitude_acceptance_radius())
&& (dist_xy < 2 * _navigator->get_loiter_radius())) {
/* SETPOINT_TYPE_POSITION -> SETPOINT_TYPE_LOITER */
if (curr_sp->type == position_setpoint_s::SETPOINT_TYPE_POSITION) {
curr_sp->type = position_setpoint_s::SETPOINT_TYPE_LOITER;
curr_sp->loiter_radius = _navigator->get_loiter_radius();
curr_sp->loiter_direction = 1;
_navigator->set_position_setpoint_triplet_updated();
}
} else {
/* restore SETPOINT_TYPE_POSITION */
if (curr_sp->type == position_setpoint_s::SETPOINT_TYPE_LOITER) {
/* loiter acceptance criteria required to revert back to SETPOINT_TYPE_POSITION */
if ((dist >= 0.0f)
&& (dist_z < _navigator->get_loiter_radius())
&& (dist_xy <= _navigator->get_loiter_radius() * 1.2f)) {
curr_sp->type = position_setpoint_s::SETPOINT_TYPE_POSITION;
_navigator->set_position_setpoint_triplet_updated();
}
}
}
}
if ((_mission_item.nav_cmd == NAV_CMD_TAKEOFF || _mission_item.nav_cmd == NAV_CMD_VTOL_TAKEOFF)
&& _navigator->get_vstatus()->is_rotary_wing) {
/* We want to avoid the edge case where the acceptance radius is bigger or equal than
* the altitude of the takeoff waypoint above home. Otherwise, we do not really follow
* take-off procedures like leaving the landing gear down. */
float takeoff_alt = _mission_item.altitude_is_relative ?
_mission_item.altitude :
(_mission_item.altitude - _navigator->get_home_position()->alt);
float altitude_acceptance_radius = _navigator->get_altitude_acceptance_radius();
/* It should be safe to just use half of the takoeff_alt as an acceptance radius. */
if (takeoff_alt > 0 && takeoff_alt < altitude_acceptance_radius) {
altitude_acceptance_radius = takeoff_alt / 2.0f;
}
/* require only altitude for takeoff for multicopter */
if (_navigator->get_global_position()->alt >
altitude_amsl - altitude_acceptance_radius) {
_waypoint_position_reached = true;
}
} else if (_mission_item.nav_cmd == NAV_CMD_TAKEOFF) {
/* for takeoff mission items use the parameter for the takeoff acceptance radius */
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius()
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
_waypoint_position_reached = true;
}
} else if (!_navigator->get_vstatus()->is_rotary_wing &&
(_mission_item.nav_cmd == NAV_CMD_LOITER_UNLIMITED ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TIME_LIMIT)) {
/* Loiter mission item on a non rotary wing: the aircraft is going to circle the
* coordinates with a radius equal to the loiter_radius field. It is not flying
* through the waypoint center.
* Therefore the item is marked as reached once the system reaches the loiter
* radius (+ some margin). Time inside and turn count is handled elsewhere.
*/
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius(fabsf(_mission_item.loiter_radius) * 1.2f)
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
_waypoint_position_reached = true;
} else {
_time_first_inside_orbit = 0;
}
} else if (!_navigator->get_vstatus()->is_rotary_wing &&
(_mission_item.nav_cmd == NAV_CMD_LOITER_TO_ALT)) {
// NAV_CMD_LOITER_TO_ALT only uses mission item altitude once it's in the loiter
// first check if the altitude setpoint is the mission setpoint
struct position_setpoint_s *curr_sp = &_navigator->get_position_setpoint_triplet()->current;
if (fabsf(curr_sp->alt - altitude_amsl) >= FLT_EPSILON) {
// check if the initial loiter has been accepted
dist_xy = -1.0f;
dist_z = -1.0f;
dist = get_distance_to_point_global_wgs84(_mission_item.lat, _mission_item.lon, curr_sp->alt,
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_navigator->get_global_position()->alt,
&dist_xy, &dist_z);
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius(fabsf(_mission_item.loiter_radius) * 1.2f)
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
// now set the loiter to the final altitude in the NAV_CMD_LOITER_TO_ALT mission item
curr_sp->alt = altitude_amsl;
_navigator->set_position_setpoint_triplet_updated();
}
} else {
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius(fabsf(_mission_item.loiter_radius) * 1.2f)
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
_waypoint_position_reached = true;
// set required yaw from bearing to the next mission item
if (_mission_item.force_heading) {
struct position_setpoint_s next_sp = _navigator->get_position_setpoint_triplet()->next;
if (next_sp.valid) {
_mission_item.yaw = get_bearing_to_next_waypoint(_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
next_sp.lat, next_sp.lon);
_waypoint_yaw_reached = false;
} else {
_waypoint_yaw_reached = true;
}
}
}
}
} else if (_mission_item.nav_cmd == NAV_CMD_DELAY) {
_waypoint_position_reached = true;
_waypoint_yaw_reached = true;
_time_wp_reached = now;
} else {
/* for normal mission items used their acceptance radius */
float mission_acceptance_radius = _navigator->get_acceptance_radius(_mission_item.acceptance_radius);
/* if set to zero use the default instead */
if (mission_acceptance_radius < NAV_EPSILON_POSITION) {
mission_acceptance_radius = _navigator->get_acceptance_radius();
}
/* for vtol back transition calculate acceptance radius based on time and ground speed */
if (_mission_item.vtol_back_transition) {
float velocity = sqrtf(_navigator->get_local_position()->vx * _navigator->get_local_position()->vx +
_navigator->get_local_position()->vy * _navigator->get_local_position()->vy);
if (_param_back_trans_dec_mss.get() > FLT_EPSILON && velocity > FLT_EPSILON) {
mission_acceptance_radius = ((velocity / _param_back_trans_dec_mss.get() / 2) * velocity) + _param_reverse_delay.get() *
velocity;
}
}
if (dist >= 0.0f && dist <= mission_acceptance_radius
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
_waypoint_position_reached = true;
}
}
if (_waypoint_position_reached) {
// reached just now
_time_wp_reached = now;
}
}
/* Check if the waypoint and the requested yaw setpoint. */
if (_waypoint_position_reached && !_waypoint_yaw_reached) {
if ((_navigator->get_vstatus()->is_rotary_wing
|| (_mission_item.nav_cmd == NAV_CMD_LOITER_TO_ALT && _mission_item.force_heading))
&& PX4_ISFINITE(_mission_item.yaw)) {
/* check course if defined only for rotary wing except takeoff */
float cog = _navigator->get_vstatus()->is_rotary_wing ? _navigator->get_global_position()->yaw : atan2f(
_navigator->get_global_position()->vel_e,
_navigator->get_global_position()->vel_n);
float yaw_err = _wrap_pi(_mission_item.yaw - cog);
/* accept yaw if reached or if timeout is set in which case we ignore not forced headings */
if (fabsf(yaw_err) < math::radians(_param_yaw_err.get())
|| (_param_yaw_timeout.get() >= FLT_EPSILON && !_mission_item.force_heading)) {
_waypoint_yaw_reached = true;
}
/* if heading needs to be reached, the timeout is enabled and we don't make it, abort mission */
if (!_waypoint_yaw_reached && _mission_item.force_heading &&
(_param_yaw_timeout.get() >= FLT_EPSILON) &&
(now - _time_wp_reached >= (hrt_abstime)_param_yaw_timeout.get() * 1e6f)) {
_navigator->set_mission_failure("unable to reach heading within timeout");
}
} else {
_waypoint_yaw_reached = true;
}
}
/* Once the waypoint and yaw setpoint have been reached we can start the loiter time countdown */
if (_waypoint_position_reached && _waypoint_yaw_reached) {
if (_time_first_inside_orbit == 0) {
_time_first_inside_orbit = now;
}
/* check if the MAV was long enough inside the waypoint orbit */
if ((get_time_inside(_mission_item) < FLT_EPSILON) ||
(now - _time_first_inside_orbit >= (hrt_abstime)(get_time_inside(_mission_item) * 1e6f))) {
position_setpoint_s &curr_sp = _navigator->get_position_setpoint_triplet()->current;
const position_setpoint_s &next_sp = _navigator->get_position_setpoint_triplet()->next;
const float range = get_distance_to_next_waypoint(curr_sp.lat, curr_sp.lon, next_sp.lat, next_sp.lon);
// exit xtrack location
// reset lat/lon of loiter waypoint so vehicle follows a tangent
if (_mission_item.loiter_exit_xtrack && next_sp.valid && PX4_ISFINITE(range) &&
(_mission_item.nav_cmd == NAV_CMD_LOITER_TIME_LIMIT ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TO_ALT)) {
float bearing = get_bearing_to_next_waypoint(curr_sp.lat, curr_sp.lon, next_sp.lat, next_sp.lon);
float inner_angle = M_PI_2_F - asinf(_mission_item.loiter_radius / range);
// Compute "ideal" tangent origin
if (curr_sp.loiter_direction > 0) {
bearing -= inner_angle;
} else {
bearing += inner_angle;
}
// Replace current setpoint lat/lon with tangent coordinate
waypoint_from_heading_and_distance(curr_sp.lat, curr_sp.lon,
bearing, curr_sp.loiter_radius,
&curr_sp.lat, &curr_sp.lon);
}
return true;
}
}
// all acceptance criteria must be met in the same iteration
_waypoint_position_reached = false;
_waypoint_yaw_reached = false;
return false;
}
/**
* This callback is executed each time a waypoint changes.
*
* It publishes the vehicle_global_position_setpoint_s or the
* vehicle_local_position_setpoint_s topic, depending on the type of waypoint
*/
void mavlink_missionlib_current_waypoint_changed(uint16_t index, float param1,
float param2, float param3, float param4, float param5_lat_x,
float param6_lon_y, float param7_alt_z, uint8_t frame, uint16_t command)
{
static orb_advert_t global_position_setpoint_pub = -1;
static orb_advert_t global_position_set_triplet_pub = -1;
static orb_advert_t local_position_setpoint_pub = -1;
static unsigned last_waypoint_index = -1;
char buf[50] = {0};
// XXX include check if WP is supported, jump to next if not
/* Update controller setpoints */
if (frame == (int)MAV_FRAME_GLOBAL) {
/* global, absolute waypoint */
struct vehicle_global_position_setpoint_s sp;
sp.lat = param5_lat_x * 1e7f;
sp.lon = param6_lon_y * 1e7f;
sp.altitude = param7_alt_z;
sp.altitude_is_relative = false;
sp.yaw = _wrap_pi(param4 / 180.0f * M_PI_F);
set_special_fields(param1, param2, param3, param4, command, &sp);
/* Initialize setpoint publication if necessary */
if (global_position_setpoint_pub < 0) {
global_position_setpoint_pub = orb_advertise(ORB_ID(vehicle_global_position_setpoint), &sp);
} else {
orb_publish(ORB_ID(vehicle_global_position_setpoint), global_position_setpoint_pub, &sp);
}
/* fill triplet: previous, current, next waypoint */
struct vehicle_global_position_set_triplet_s triplet;
/* current waypoint is same as sp */
memcpy(&(triplet.current), &sp, sizeof(sp));
/*
* Check if previous WP (in mission, not in execution order)
* is available and identify correct index
*/
int last_setpoint_index = -1;
bool last_setpoint_valid = false;
if (index > 0) {
last_setpoint_index = index - 1;
}
while (last_setpoint_index >= 0) {
if (wpm->waypoints[last_setpoint_index].frame == (int)MAV_FRAME_GLOBAL &&
(wpm->waypoints[last_setpoint_index].command == (int)MAV_CMD_NAV_WAYPOINT ||
wpm->waypoints[last_setpoint_index].command == (int)MAV_CMD_NAV_LOITER_TURNS ||
wpm->waypoints[last_setpoint_index].command == (int)MAV_CMD_NAV_LOITER_TIME ||
wpm->waypoints[last_setpoint_index].command == (int)MAV_CMD_NAV_LOITER_UNLIM)) {
last_setpoint_valid = true;
break;
}
last_setpoint_index--;
}
/*
* Check if next WP (in mission, not in execution order)
* is available and identify correct index
*/
int next_setpoint_index = -1;
bool next_setpoint_valid = false;
/* next waypoint */
if (wpm->size > 1) {
next_setpoint_index = index + 1;
}
while (next_setpoint_index < wpm->size - 1) {
if (wpm->waypoints[next_setpoint_index].frame == (int)MAV_FRAME_GLOBAL && (wpm->waypoints[next_setpoint_index].command == (int)MAV_CMD_NAV_WAYPOINT ||
wpm->waypoints[next_setpoint_index].command == (int)MAV_CMD_NAV_LOITER_TURNS ||
wpm->waypoints[next_setpoint_index].command == (int)MAV_CMD_NAV_LOITER_TIME ||
wpm->waypoints[next_setpoint_index].command == (int)MAV_CMD_NAV_LOITER_UNLIM)) {
next_setpoint_valid = true;
break;
}
next_setpoint_index++;
}
/* populate last and next */
triplet.previous_valid = false;
triplet.next_valid = false;
if (last_setpoint_valid) {
triplet.previous_valid = true;
struct vehicle_global_position_setpoint_s sp;
sp.lat = wpm->waypoints[last_setpoint_index].x * 1e7f;
sp.lon = wpm->waypoints[last_setpoint_index].y * 1e7f;
sp.altitude = wpm->waypoints[last_setpoint_index].z;
sp.altitude_is_relative = false;
sp.yaw = (wpm->waypoints[last_setpoint_index].param4 / 180.0f) * M_PI_F - M_PI_F;
set_special_fields(wpm->waypoints[last_setpoint_index].param1,
wpm->waypoints[last_setpoint_index].param2,
wpm->waypoints[last_setpoint_index].param3,
wpm->waypoints[last_setpoint_index].param4,
wpm->waypoints[last_setpoint_index].command, &sp);
memcpy(&(triplet.previous), &sp, sizeof(sp));
}
if (next_setpoint_valid) {
triplet.next_valid = true;
struct vehicle_global_position_setpoint_s sp;
sp.lat = wpm->waypoints[next_setpoint_index].x * 1e7f;
sp.lon = wpm->waypoints[next_setpoint_index].y * 1e7f;
sp.altitude = wpm->waypoints[next_setpoint_index].z;
sp.altitude_is_relative = false;
sp.yaw = (wpm->waypoints[next_setpoint_index].param4 / 180.0f) * M_PI_F - M_PI_F;
set_special_fields(wpm->waypoints[next_setpoint_index].param1,
wpm->waypoints[next_setpoint_index].param2,
wpm->waypoints[next_setpoint_index].param3,
wpm->waypoints[next_setpoint_index].param4,
wpm->waypoints[next_setpoint_index].command, &sp);
memcpy(&(triplet.next), &sp, sizeof(sp));
}
/* Initialize triplet publication if necessary */
if (global_position_set_triplet_pub < 0) {
global_position_set_triplet_pub = orb_advertise(ORB_ID(vehicle_global_position_set_triplet), &triplet);
} else {
orb_publish(ORB_ID(vehicle_global_position_set_triplet), global_position_set_triplet_pub, &triplet);
}
sprintf(buf, "[mp] WP#%i lat: % 3.6f/lon % 3.6f/alt % 4.6f/hdg %3.4f\n", (int)index, (double)param5_lat_x, (double)param6_lon_y, (double)param7_alt_z, (double)param4);
} else if (frame == (int)MAV_FRAME_GLOBAL_RELATIVE_ALT) {
/* global, relative alt (in relation to HOME) waypoint */
struct vehicle_global_position_setpoint_s sp;
sp.lat = param5_lat_x * 1e7f;
sp.lon = param6_lon_y * 1e7f;
sp.altitude = param7_alt_z;
sp.altitude_is_relative = true;
sp.yaw = (param4 / 180.0f) * M_PI_F - M_PI_F;
set_special_fields(param1, param2, param3, param4, command, &sp);
/* Initialize publication if necessary */
if (global_position_setpoint_pub < 0) {
global_position_setpoint_pub = orb_advertise(ORB_ID(vehicle_global_position_setpoint), &sp);
} else {
orb_publish(ORB_ID(vehicle_global_position_setpoint), global_position_setpoint_pub, &sp);
}
sprintf(buf, "[mp] WP#%i (lat: %f/lon %f/rel alt %f/hdg %f\n", (int)index, (double)param5_lat_x, (double)param6_lon_y, (double)param7_alt_z, (double)param4);
} else if (frame == (int)MAV_FRAME_LOCAL_ENU || frame == (int)MAV_FRAME_LOCAL_NED) {
/* local, absolute waypoint */
struct vehicle_local_position_setpoint_s sp;
sp.x = param5_lat_x;
sp.y = param6_lon_y;
sp.z = param7_alt_z;
sp.yaw = (param4 / 180.0f) * M_PI_F - M_PI_F;
/* Initialize publication if necessary */
if (local_position_setpoint_pub < 0) {
local_position_setpoint_pub = orb_advertise(ORB_ID(vehicle_local_position_setpoint), &sp);
} else {
orb_publish(ORB_ID(vehicle_local_position_setpoint), local_position_setpoint_pub, &sp);
}
sprintf(buf, "[mp] WP#%i (x: %f/y %f/z %f/hdg %f\n", (int)index, (double)param5_lat_x, (double)param6_lon_y, (double)param7_alt_z, (double)param4);
} else {
warnx("non-navigation WP, ignoring");
mavlink_missionlib_send_gcs_string("[mp] Unknown waypoint type, ignoring.");
return;
}
/* only set this for known waypoint types (non-navigation types would have returned earlier) */
last_waypoint_index = index;
mavlink_missionlib_send_gcs_string(buf);
printf("%s\n", buf);
//printf("[mavlink mp] new setpoint\n");//: frame: %d, lat: %d, lon: %d, alt: %d, yaw: %d\n", frame, param5_lat_x*1000, param6_lon_y*1000, param7_alt_z*1000, param4*1000);
}
bool
MissionBlock::is_mission_item_reached()
{
if (_mission_item.nav_cmd == NAV_CMD_IDLE) {
return false;
}
if (_mission_item.nav_cmd == NAV_CMD_LAND) {
return _navigator->get_vstatus()->condition_landed;
}
/* TODO: count turns */
if ((/*_mission_item.nav_cmd == NAV_CMD_LOITER_TURN_COUNT ||*/
_mission_item.nav_cmd == NAV_CMD_LOITER_UNLIMITED)) {
return false;
}
hrt_abstime now = hrt_absolute_time();
if (!_waypoint_position_reached) {
float dist = -1.0f;
float dist_xy = -1.0f;
float dist_z = -1.0f;
float altitude_amsl = _mission_item.altitude_is_relative
? _mission_item.altitude + _navigator->get_home_position()->alt
: _mission_item.altitude;
dist = get_distance_to_point_global_wgs84(_mission_item.lat, _mission_item.lon, altitude_amsl,
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_navigator->get_global_position()->alt,
&dist_xy, &dist_z);
if (_mission_item.nav_cmd == NAV_CMD_TAKEOFF && _navigator->get_vstatus()->is_rotary_wing) {
/* require only altitude for takeoff for multicopter */
if (_navigator->get_global_position()->alt >
altitude_amsl - _navigator->get_acceptance_radius()) {
_waypoint_position_reached = true;
}
} else if (_mission_item.nav_cmd == NAV_CMD_TAKEOFF) {
/* for takeoff mission items use the parameter for the takeoff acceptance radius */
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius()) {
_waypoint_position_reached = true;
}
} else if (!_navigator->get_vstatus()->is_rotary_wing &&
(_mission_item.nav_cmd == NAV_CMD_LOITER_UNLIMITED ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TIME_LIMIT ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TURN_COUNT)) {
/* Loiter mission item on a non rotary wing: the aircraft is going to circle the
* coordinates with a radius equal to the loiter_radius field. It is not flying
* through the waypoint center.
* Therefore the item is marked as reached once the system reaches the loiter
* radius (+ some margin). Time inside and turn count is handled elsewhere.
*/
if (dist >= 0.0f && dist <= _mission_item.loiter_radius * 1.2f) {
_waypoint_position_reached = true;
}
} else {
/* for normal mission items used their acceptance radius */
if (dist >= 0.0f && dist <= _mission_item.acceptance_radius) {
_waypoint_position_reached = true;
}
}
}
if (_waypoint_position_reached && !_waypoint_yaw_reached) {
/* TODO: removed takeoff, why? */
if (_navigator->get_vstatus()->is_rotary_wing && isfinite(_mission_item.yaw)) {
/* check yaw if defined only for rotary wing except takeoff */
float yaw_err = _wrap_pi(_mission_item.yaw - _navigator->get_global_position()->yaw);
if (fabsf(yaw_err) < 0.2f) { /* TODO: get rid of magic number */
_waypoint_yaw_reached = true;
}
} else {
_waypoint_yaw_reached = true;
}
}
/* check if the current waypoint was reached */
if (_waypoint_position_reached && _waypoint_yaw_reached) {
if (_time_first_inside_orbit == 0) {
_time_first_inside_orbit = now;
// if (_mission_item.time_inside > 0.01f) {
// mavlink_log_info(_mavlink_fd, "#audio: waypoint reached, wait for %.1fs",
// (double)_mission_item.time_inside);
// }
}
/* check if the MAV was long enough inside the waypoint orbit */
if (now - _time_first_inside_orbit >= (hrt_abstime)_mission_item.time_inside * 1e6f) {
return true;
}
}
return false;
}
int
MavlinkMissionManager::parse_mavlink_mission_item(const mavlink_mission_item_t *mavlink_mission_item,
struct mission_item_s *mission_item)
{
if (mavlink_mission_item->frame == MAV_FRAME_GLOBAL ||
mavlink_mission_item->frame == MAV_FRAME_GLOBAL_RELATIVE_ALT) {
if (_int_mode) {
/* The argument is actually a mavlink_mission_item_int_t in int_mode.
* mavlink_mission_item_t and mavlink_mission_item_int_t have the same
* alignment, so we can just swap float for int32_t. */
const mavlink_mission_item_int_t *item_int
= reinterpret_cast<const mavlink_mission_item_int_t *>(mavlink_mission_item);
mission_item->lat = ((double)item_int->x)*1e-7;
mission_item->lon = ((double)item_int->y)*1e-7;
} else {
mission_item->lat = (double)mavlink_mission_item->x;
mission_item->lon = (double)mavlink_mission_item->y;
}
mission_item->altitude = mavlink_mission_item->z;
if (mavlink_mission_item->frame == MAV_FRAME_GLOBAL) {
mission_item->altitude_is_relative = false;
} else if (mavlink_mission_item->frame == MAV_FRAME_GLOBAL_RELATIVE_ALT) {
mission_item->altitude_is_relative = true;
}
mission_item->time_inside = 0.0f;
switch (mavlink_mission_item->command) {
case MAV_CMD_NAV_WAYPOINT:
mission_item->nav_cmd = NAV_CMD_WAYPOINT;
mission_item->time_inside = mavlink_mission_item->param1;
mission_item->acceptance_radius = mavlink_mission_item->param2;
mission_item->yaw = _wrap_pi(mavlink_mission_item->param4 * M_DEG_TO_RAD_F);
break;
case MAV_CMD_NAV_LOITER_UNLIM:
mission_item->nav_cmd = NAV_CMD_LOITER_UNLIMITED;
mission_item->loiter_radius = fabsf(mavlink_mission_item->param3);
mission_item->loiter_direction = (mavlink_mission_item->param3 > 0) ? 1 : -1; /* 1 if positive CW, -1 if negative CCW */
mission_item->yaw = _wrap_pi(mavlink_mission_item->param4 * M_DEG_TO_RAD_F);
break;
case MAV_CMD_NAV_LOITER_TIME:
mission_item->nav_cmd = NAV_CMD_LOITER_TIME_LIMIT;
mission_item->time_inside = mavlink_mission_item->param1;
mission_item->loiter_radius = fabsf(mavlink_mission_item->param3);
mission_item->loiter_direction = (mavlink_mission_item->param3 > 0) ? 1 : -1; /* 1 if positive CW, -1 if negative CCW */
mission_item->loiter_exit_xtrack = (mavlink_mission_item->param4 > 0) ? true : false;
break;
case MAV_CMD_NAV_LAND:
mission_item->nav_cmd = NAV_CMD_LAND;
// TODO: abort alt param1
mission_item->yaw = _wrap_pi(mavlink_mission_item->param4 * M_DEG_TO_RAD_F);
break;
case MAV_CMD_NAV_TAKEOFF:
mission_item->nav_cmd = NAV_CMD_TAKEOFF;
mission_item->pitch_min = mavlink_mission_item->param1;
mission_item->yaw = _wrap_pi(mavlink_mission_item->param4 * M_DEG_TO_RAD_F);
break;
case MAV_CMD_NAV_LOITER_TO_ALT:
mission_item->nav_cmd = NAV_CMD_LOITER_TO_ALT;
mission_item->force_heading = (mavlink_mission_item->param1 > 0) ? true : false;
mission_item->loiter_radius = fabsf(mavlink_mission_item->param2);
mission_item->loiter_direction = (mavlink_mission_item->param2 > 0) ? 1 : -1; /* 1 if positive CW, -1 if negative CCW */
mission_item->loiter_exit_xtrack = (mavlink_mission_item->param4 > 0) ? true : false;
break;
case MAV_CMD_NAV_VTOL_TAKEOFF:
case MAV_CMD_NAV_VTOL_LAND:
mission_item->nav_cmd = (NAV_CMD)mavlink_mission_item->command;
mission_item->yaw = _wrap_pi(mavlink_mission_item->param4 * M_DEG_TO_RAD_F);
break;
default:
mission_item->nav_cmd = NAV_CMD_INVALID;
return MAV_MISSION_UNSUPPORTED;
}
mission_item->frame = mavlink_mission_item->frame;
} else if (mavlink_mission_item->frame == MAV_FRAME_MISSION) {
// this is a mission item with no coordinates
mission_item->params[0] = mavlink_mission_item->param1;
mission_item->params[1] = mavlink_mission_item->param2;
mission_item->params[2] = mavlink_mission_item->param3;
mission_item->params[3] = mavlink_mission_item->param4;
mission_item->params[4] = mavlink_mission_item->x;
mission_item->params[5] = mavlink_mission_item->y;
mission_item->params[6] = mavlink_mission_item->z;
switch (mavlink_mission_item->command) {
case MAV_CMD_DO_JUMP:
mission_item->nav_cmd = NAV_CMD_DO_JUMP;
mission_item->do_jump_mission_index = mavlink_mission_item->param1;
mission_item->do_jump_current_count = 0;
mission_item->do_jump_repeat_count = mavlink_mission_item->param2;
break;
case MAV_CMD_DO_CHANGE_SPEED:
case MAV_CMD_DO_SET_SERVO:
case MAV_CMD_DO_DIGICAM_CONTROL:
case MAV_CMD_DO_MOUNT_CONFIGURE:
case MAV_CMD_DO_MOUNT_CONTROL:
case MAV_CMD_DO_SET_CAM_TRIGG_DIST:
case MAV_CMD_DO_VTOL_TRANSITION:
mission_item->nav_cmd = (NAV_CMD)mavlink_mission_item->command;
break;
default:
mission_item->nav_cmd = NAV_CMD_INVALID;
return MAV_MISSION_UNSUPPORTED;
}
mission_item->frame = MAV_FRAME_MISSION;
} else {
return MAV_MISSION_UNSUPPORTED_FRAME;
}
mission_item->autocontinue = mavlink_mission_item->autocontinue;
// mission_item->index = mavlink_mission_item->seq;
/* reset DO_JUMP count */
mission_item->do_jump_current_count = 0;
mission_item->origin = ORIGIN_MAVLINK;
return MAV_MISSION_ACCEPTED;
}
float ECL_L1_Pos_Controller::nav_bearing()
{
return _wrap_pi(_nav_bearing);
}
bool
MissionBlock::is_mission_item_reached()
{
/* handle non-navigation or indefinite waypoints */
switch (_mission_item.nav_cmd) {
case NAV_CMD_DO_SET_SERVO:
return true;
case NAV_CMD_LAND: /* fall through */
case NAV_CMD_VTOL_LAND:
return _navigator->get_land_detected()->landed;
case NAV_CMD_IDLE: /* fall through */
case NAV_CMD_LOITER_UNLIMITED:
return false;
case NAV_CMD_DO_DIGICAM_CONTROL:
case NAV_CMD_IMAGE_START_CAPTURE:
case NAV_CMD_IMAGE_STOP_CAPTURE:
case NAV_CMD_VIDEO_START_CAPTURE:
case NAV_CMD_VIDEO_STOP_CAPTURE:
case NAV_CMD_DO_MOUNT_CONFIGURE:
case NAV_CMD_DO_MOUNT_CONTROL:
case NAV_CMD_DO_SET_ROI:
case NAV_CMD_ROI:
case NAV_CMD_DO_SET_CAM_TRIGG_DIST:
return true;
case NAV_CMD_DO_VTOL_TRANSITION:
/*
* We wait half a second to give the transition command time to propagate.
* Then monitor the transition status for completion.
*/
if (hrt_absolute_time() - _action_start > 500000 &&
!_navigator->get_vstatus()->in_transition_mode) {
_action_start = 0;
return true;
} else {
return false;
}
case NAV_CMD_DO_CHANGE_SPEED:
// XXX not differentiating ground and airspeed yet
if (_mission_item.params[1] > 0.0f) {
_navigator->set_cruising_speed(_mission_item.params[1]);
} else {
_navigator->set_cruising_speed();
/* if no speed target was given try to set throttle */
if (_mission_item.params[2] > 0.0f) {
_navigator->set_cruising_throttle(_mission_item.params[2] / 100);
} else {
_navigator->set_cruising_throttle();
}
}
return true;
default:
/* do nothing, this is a 3D waypoint */
break;
}
hrt_abstime now = hrt_absolute_time();
if ((_navigator->get_land_detected()->landed == false)
&& !_waypoint_position_reached) {
float dist = -1.0f;
float dist_xy = -1.0f;
float dist_z = -1.0f;
float altitude_amsl = _mission_item.altitude_is_relative
? _mission_item.altitude + _navigator->get_home_position()->alt
: _mission_item.altitude;
dist = get_distance_to_point_global_wgs84(_mission_item.lat, _mission_item.lon, altitude_amsl,
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_navigator->get_global_position()->alt,
&dist_xy, &dist_z);
if ((_mission_item.nav_cmd == NAV_CMD_TAKEOFF || _mission_item.nav_cmd == NAV_CMD_VTOL_TAKEOFF)
&& _navigator->get_vstatus()->is_rotary_wing) {
/* We want to avoid the edge case where the acceptance radius is bigger or equal than
* the altitude of the takeoff waypoint above home. Otherwise, we do not really follow
* take-off procedures like leaving the landing gear down. */
float takeoff_alt = _mission_item.altitude_is_relative ?
_mission_item.altitude :
(_mission_item.altitude - _navigator->get_home_position()->alt);
float altitude_acceptance_radius = _navigator->get_altitude_acceptance_radius();
/* It should be safe to just use half of the takoeff_alt as an acceptance radius. */
if (takeoff_alt > 0 && takeoff_alt < altitude_acceptance_radius) {
altitude_acceptance_radius = takeoff_alt / 2.0f;
}
/* require only altitude for takeoff for multicopter */
if (_navigator->get_global_position()->alt >
altitude_amsl - altitude_acceptance_radius) {
_waypoint_position_reached = true;
}
} else if (_mission_item.nav_cmd == NAV_CMD_TAKEOFF) {
/* for takeoff mission items use the parameter for the takeoff acceptance radius */
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius()
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
_waypoint_position_reached = true;
}
} else if (!_navigator->get_vstatus()->is_rotary_wing &&
(_mission_item.nav_cmd == NAV_CMD_LOITER_UNLIMITED ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TIME_LIMIT)) {
/* Loiter mission item on a non rotary wing: the aircraft is going to circle the
* coordinates with a radius equal to the loiter_radius field. It is not flying
* through the waypoint center.
* Therefore the item is marked as reached once the system reaches the loiter
* radius (+ some margin). Time inside and turn count is handled elsewhere.
*/
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius(fabsf(_mission_item.loiter_radius) * 1.2f)
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
_waypoint_position_reached = true;
} else {
_time_first_inside_orbit = 0;
}
} else if (!_navigator->get_vstatus()->is_rotary_wing &&
(_mission_item.nav_cmd == NAV_CMD_LOITER_TO_ALT)) {
// NAV_CMD_LOITER_TO_ALT only uses mission item altitude once it's in the loiter
// first check if the altitude setpoint is the mission setpoint
struct position_setpoint_s *curr_sp = &_navigator->get_position_setpoint_triplet()->current;
if (fabsf(curr_sp->alt - altitude_amsl) >= FLT_EPSILON) {
// check if the initial loiter has been accepted
dist = -1.0f;
dist_xy = -1.0f;
dist_z = -1.0f;
dist = get_distance_to_point_global_wgs84(_mission_item.lat, _mission_item.lon, curr_sp->alt,
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_navigator->get_global_position()->alt,
&dist_xy, &dist_z);
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius(fabsf(_mission_item.loiter_radius) * 1.2f)
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
// now set the loiter to the final altitude in the NAV_CMD_LOITER_TO_ALT mission item
curr_sp->alt = altitude_amsl;
_navigator->set_position_setpoint_triplet_updated();
}
} else {
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius(fabsf(_mission_item.loiter_radius) * 1.2f)
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
_waypoint_position_reached = true;
// set required yaw from bearing to the next mission item
if (_mission_item.force_heading) {
struct position_setpoint_s next_sp = _navigator->get_position_setpoint_triplet()->next;
if (next_sp.valid) {
_mission_item.yaw = get_bearing_to_next_waypoint(_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
next_sp.lat, next_sp.lon);
_waypoint_yaw_reached = false;
} else {
_waypoint_yaw_reached = true;
}
}
}
}
} else {
/* for normal mission items used their acceptance radius */
float mission_acceptance_radius = _navigator->get_acceptance_radius(_mission_item.acceptance_radius);
/* if set to zero use the default instead */
if (mission_acceptance_radius < NAV_EPSILON_POSITION) {
mission_acceptance_radius = _navigator->get_acceptance_radius();
}
if (dist >= 0.0f && dist <= mission_acceptance_radius
&& dist_z <= _navigator->get_altitude_acceptance_radius()) {
_waypoint_position_reached = true;
}
}
if (_waypoint_position_reached) {
// reached just now
_time_wp_reached = now;
}
}
/* Check if the waypoint and the requested yaw setpoint. */
if (_waypoint_position_reached && !_waypoint_yaw_reached) {
if ((_navigator->get_vstatus()->is_rotary_wing
|| (_mission_item.nav_cmd == NAV_CMD_LOITER_TO_ALT && _mission_item.force_heading))
&& PX4_ISFINITE(_mission_item.yaw)) {
/* check yaw if defined only for rotary wing except takeoff */
float yaw_err = _wrap_pi(_mission_item.yaw - _navigator->get_global_position()->yaw);
/* accept yaw if reached or if timeout is set in which case we ignore not forced headings */
if (fabsf(yaw_err) < math::radians(_param_yaw_err.get())
|| (_param_yaw_timeout.get() >= FLT_EPSILON && !_mission_item.force_heading)) {
_waypoint_yaw_reached = true;
}
/* if heading needs to be reached, the timeout is enabled and we don't make it, abort mission */
if (!_waypoint_yaw_reached && _mission_item.force_heading &&
(_param_yaw_timeout.get() >= FLT_EPSILON) &&
(now - _time_wp_reached >= (hrt_abstime)_param_yaw_timeout.get() * 1e6f)) {
_navigator->set_mission_failure("unable to reach heading within timeout");
}
} else {
_waypoint_yaw_reached = true;
}
}
/* Once the waypoint and yaw setpoint have been reached we can start the loiter time countdown */
if (_waypoint_position_reached && _waypoint_yaw_reached) {
if (_time_first_inside_orbit == 0) {
_time_first_inside_orbit = now;
}
/* check if the MAV was long enough inside the waypoint orbit */
if ((Navigator::get_time_inside(_mission_item) < FLT_EPSILON) ||
(now - _time_first_inside_orbit >= (hrt_abstime)(Navigator::get_time_inside(_mission_item) * 1e6f))) {
// exit xtrack location
if (_mission_item.loiter_exit_xtrack &&
(_mission_item.nav_cmd == NAV_CMD_LOITER_TIME_LIMIT ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TO_ALT)) {
// reset lat/lon of loiter waypoint so vehicle exits on a tangent
struct position_setpoint_s *curr_sp = &_navigator->get_position_setpoint_triplet()->current;
curr_sp->lat = _navigator->get_global_position()->lat;
curr_sp->lon = _navigator->get_global_position()->lon;
}
return true;
}
}
// all acceptance criteria must be met in the same iteration
_waypoint_position_reached = false;
_waypoint_yaw_reached = false;
return false;
}
void Standard::update_mc_state()
{
VtolType::update_mc_state();
// enable MC motors here in case we transitioned directly to MC mode
if (_flag_enable_mc_motors) {
set_max_mc(2000);
set_idle_mc();
_flag_enable_mc_motors = false;
}
// if the thrust scale param is zero or the drone is on manual mode,
// then the pusher-for-pitch strategy is disabled and we can return
if (_params_standard.forward_thrust_scale < FLT_EPSILON ||
!_v_control_mode->flag_control_position_enabled) {
return;
}
// Do not engage pusher assist during a failsafe event
// There could be a problem with the fixed wing drive
if (_attc->get_vtol_vehicle_status()->vtol_transition_failsafe) {
return;
}
// disable pusher assist during landing
if (_attc->get_pos_sp_triplet()->current.valid
&& _attc->get_pos_sp_triplet()->current.type == position_setpoint_s::SETPOINT_TYPE_LAND) {
return;
}
matrix::Dcmf R(matrix::Quatf(_v_att->q));
matrix::Dcmf R_sp(matrix::Quatf(_v_att_sp->q_d));
matrix::Eulerf euler(R);
matrix::Eulerf euler_sp(R_sp);
_pusher_throttle = 0.0f;
// direction of desired body z axis represented in earth frame
matrix::Vector3f body_z_sp(R_sp(0, 2), R_sp(1, 2), R_sp(2, 2));
// rotate desired body z axis into new frame which is rotated in z by the current
// heading of the vehicle. we refer to this as the heading frame.
matrix::Dcmf R_yaw = matrix::Eulerf(0.0f, 0.0f, -euler(2));
body_z_sp = R_yaw * body_z_sp;
body_z_sp.normalize();
// calculate the desired pitch seen in the heading frame
// this value corresponds to the amount the vehicle would try to pitch forward
float pitch_forward = atan2f(body_z_sp(0), body_z_sp(2));
// only allow pitching forward up to threshold, the rest of the desired
// forward acceleration will be compensated by the pusher
if (pitch_forward < -_params_standard.down_pitch_max) {
// desired roll angle in heading frame stays the same
float roll_new = -asinf(body_z_sp(1));
_pusher_throttle = (sinf(-pitch_forward) - sinf(_params_standard.down_pitch_max))
* _params_standard.forward_thrust_scale;
// return the vehicle to level position
float pitch_new = 0.0f;
// create corrected desired body z axis in heading frame
matrix::Dcmf R_tmp = matrix::Eulerf(roll_new, pitch_new, 0.0f);
matrix::Vector3f tilt_new(R_tmp(0, 2), R_tmp(1, 2), R_tmp(2, 2));
// rotate the vector into a new frame which is rotated in z by the desired heading
// with respect to the earh frame.
float yaw_error = _wrap_pi(euler_sp(2) - euler(2));
matrix::Dcmf R_yaw_correction = matrix::Eulerf(0.0f, 0.0f, -yaw_error);
tilt_new = R_yaw_correction * tilt_new;
// now extract roll and pitch setpoints
_v_att_sp->pitch_body = atan2f(tilt_new(0), tilt_new(2));
_v_att_sp->roll_body = -asinf(tilt_new(1));
R_sp = matrix::Eulerf(_v_att_sp->roll_body, _v_att_sp->pitch_body, euler_sp(2));
matrix::Quatf q_sp(R_sp);
q_sp.copyTo(_v_att_sp->q_d);
}
_pusher_throttle = _pusher_throttle < 0.0f ? 0.0f : _pusher_throttle;
}
void check_waypoints_reached(uint64_t now, const struct vehicle_global_position_s *global_pos, struct vehicle_local_position_s *local_pos)
{
static uint16_t counter;
if (!global_pos->valid && !local_pos->xy_valid) {
/* nothing to check here, return */
return;
}
if (wpm->current_active_wp_id < wpm->size) {
float orbit;
if (wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_WAYPOINT) {
orbit = wpm->waypoints[wpm->current_active_wp_id].param2;
} else if (wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_TURNS ||
wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_TIME ||
wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_UNLIM) {
orbit = wpm->waypoints[wpm->current_active_wp_id].param3;
} else {
// XXX set default orbit via param
orbit = 15.0f;
}
int coordinate_frame = wpm->waypoints[wpm->current_active_wp_id].frame;
float dist = -1.0f;
if (coordinate_frame == (int)MAV_FRAME_GLOBAL) {
dist = mavlink_wpm_distance_to_point_global_wgs84(wpm->current_active_wp_id, (float)global_pos->lat * 1e-7f, (float)global_pos->lon * 1e-7f, global_pos->alt);
} else if (coordinate_frame == (int)MAV_FRAME_GLOBAL_RELATIVE_ALT) {
dist = mavlink_wpm_distance_to_point_global_wgs84(wpm->current_active_wp_id, (float)global_pos->lat * 1e-7f, (float)global_pos->lon * 1e-7f, global_pos->relative_alt);
} else if (coordinate_frame == (int)MAV_FRAME_LOCAL_ENU || coordinate_frame == (int)MAV_FRAME_LOCAL_NED) {
dist = mavlink_wpm_distance_to_point_local(wpm->current_active_wp_id, local_pos->x, local_pos->y, local_pos->z);
} else if (coordinate_frame == (int)MAV_FRAME_MISSION) {
/* Check if conditions of mission item are satisfied */
// XXX TODO
}
if (dist >= 0.f && dist <= orbit) {
wpm->pos_reached = true;
}
// check if required yaw reached
float yaw_sp = _wrap_pi(wpm->waypoints[wpm->current_active_wp_id].param4 / 180.0f * FM_PI);
float yaw_err = _wrap_pi(yaw_sp - local_pos->yaw);
if (fabsf(yaw_err) < 0.05f) {
wpm->yaw_reached = true;
}
}
//check if the current waypoint was reached
if (wpm->pos_reached && /*wpm->yaw_reached &&*/ !wpm->idle) {
if (wpm->current_active_wp_id < wpm->size) {
mavlink_mission_item_t *cur_wp = &(wpm->waypoints[wpm->current_active_wp_id]);
if (wpm->timestamp_firstinside_orbit == 0) {
// Announce that last waypoint was reached
mavlink_wpm_send_waypoint_reached(cur_wp->seq);
wpm->timestamp_firstinside_orbit = now;
}
// check if the MAV was long enough inside the waypoint orbit
//if (now-timestamp_lastoutside_orbit > (cur_wp->hold_time*1000))
bool time_elapsed = false;
if (now - wpm->timestamp_firstinside_orbit >= cur_wp->param1 * 1000 * 1000) {
time_elapsed = true;
} else if (cur_wp->command == (int)MAV_CMD_NAV_TAKEOFF) {
time_elapsed = true;
}
if (time_elapsed) {
if (cur_wp->autocontinue) {
cur_wp->current = 0;
float navigation_lat = -1.0f;
float navigation_lon = -1.0f;
float navigation_alt = -1.0f;
int navigation_frame = -1;
/* initialize to current position in case we don't find a suitable navigation waypoint */
if (global_pos->valid) {
navigation_lat = global_pos->lat/1e7;
navigation_lon = global_pos->lon/1e7;
navigation_alt = global_pos->alt;
navigation_frame = MAV_FRAME_GLOBAL;
} else if (local_pos->xy_valid && local_pos->z_valid) {
navigation_lat = local_pos->x;
navigation_lon = local_pos->y;
navigation_alt = local_pos->z;
navigation_frame = MAV_FRAME_LOCAL_NED;
}
/* only accept supported navigation waypoints, skip unknown ones */
do {
/* pick up the last valid navigation waypoint, this will be one we hold on to after the mission */
if (wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_WAYPOINT ||
wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_TURNS ||
wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_TIME ||
wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_UNLIM) {
/* this is a navigation waypoint */
navigation_frame = cur_wp->frame;
navigation_lat = cur_wp->x;
navigation_lon = cur_wp->y;
navigation_alt = cur_wp->z;
}
if (wpm->current_active_wp_id == wpm->size - 1 && wpm->size > 1) {
/* the last waypoint was reached, if auto continue is
* activated keep the system loitering there.
*/
cur_wp->command = MAV_CMD_NAV_LOITER_UNLIM;
cur_wp->param3 = 20.0f; // XXX magic number 20 m loiter radius
cur_wp->frame = navigation_frame;
cur_wp->x = navigation_lat;
cur_wp->y = navigation_lon;
cur_wp->z = navigation_alt;
cur_wp->autocontinue = false;
/* we risk an endless loop for missions without navigation waypoints, abort. */
break;
} else {
if ((uint16_t)(wpm->current_active_wp_id + 1) < wpm->size)
wpm->current_active_wp_id++;
}
} while (!(wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_WAYPOINT ||
wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_TURNS ||
wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_TIME ||
wpm->waypoints[wpm->current_active_wp_id].command == (int)MAV_CMD_NAV_LOITER_UNLIM));
// Fly to next waypoint
wpm->timestamp_firstinside_orbit = 0;
mavlink_wpm_send_waypoint_current(wpm->current_active_wp_id);
mavlink_wpm_send_setpoint(wpm->current_active_wp_id);
wpm->waypoints[wpm->current_active_wp_id].current = true;
wpm->pos_reached = false;
wpm->yaw_reached = false;
printf("Set new waypoint (%u)\n", wpm->current_active_wp_id);
}
}
}
} else {
wpm->timestamp_lastoutside_orbit = now;
}
counter++;
}
void
Mission::heading_sp_update()
{
if (_takeoff) {
/* we don't want to be yawing during takeoff */
return;
}
struct position_setpoint_triplet_s *pos_sp_triplet = _navigator->get_position_setpoint_triplet();
/* Don't change setpoint if last and current waypoint are not valid */
if (!pos_sp_triplet->previous.valid || !pos_sp_triplet->current.valid ||
!PX4_ISFINITE(_on_arrival_yaw)) {
return;
}
/* Don't change heading for takeoff waypoints, the ground may be near */
if (_mission_item.nav_cmd == NAV_CMD_TAKEOFF) {
return;
}
/* set yaw angle for the waypoint iff a loiter time has been specified */
if (_waypoint_position_reached && _mission_item.time_inside > 0.0f) {
_mission_item.yaw = _on_arrival_yaw;
} else {
/* calculate direction the vehicle should point to:
* normal waypoint: current position to {waypoint or home or home + 180deg}
* landing waypoint: last waypoint to {waypoint or home or home + 180deg}
* For landing the last waypoint (= constant) is used to avoid excessive yawing near the ground
*/
double point_from_latlon[2];
if (_mission_item.nav_cmd == NAV_CMD_LAND) {
point_from_latlon[0] = pos_sp_triplet->previous.lat;
point_from_latlon[1] = pos_sp_triplet->previous.lon;
} else {
point_from_latlon[0] = _navigator->get_global_position()->lat;
point_from_latlon[1] = _navigator->get_global_position()->lon;
}
/* always keep the front of the rotary wing pointing to the next waypoint */
if (_param_yawmode.get() == MISSION_YAWMODE_FRONT_TO_WAYPOINT) {
_mission_item.yaw = get_bearing_to_next_waypoint(
point_from_latlon[0],
point_from_latlon[1],
_mission_item.lat,
_mission_item.lon);
/* always keep the back of the rotary wing pointing towards home */
} else if (_param_yawmode.get() == MISSION_YAWMODE_FRONT_TO_HOME) {
_mission_item.yaw = get_bearing_to_next_waypoint(
point_from_latlon[0],
point_from_latlon[1],
_navigator->get_home_position()->lat,
_navigator->get_home_position()->lon);
/* always keep the back of the rotary wing pointing towards home */
} else if (_param_yawmode.get() == MISSION_YAWMODE_BACK_TO_HOME) {
_mission_item.yaw = _wrap_pi(get_bearing_to_next_waypoint(
point_from_latlon[0],
point_from_latlon[1],
_navigator->get_home_position()->lat,
_navigator->get_home_position()->lon) + M_PI_F);
}
}
mission_item_to_position_setpoint(&_mission_item, &pos_sp_triplet->current);
_navigator->set_position_setpoint_triplet_updated();
}
int
MavlinkMissionManager::parse_mavlink_mission_item(const mavlink_mission_item_t *mavlink_mission_item, struct mission_item_s *mission_item)
{
/* only support global waypoints for now */
switch (mavlink_mission_item->frame) {
case MAV_FRAME_GLOBAL:
mission_item->lat = (double)mavlink_mission_item->x;
mission_item->lon = (double)mavlink_mission_item->y;
mission_item->altitude = mavlink_mission_item->z;
mission_item->altitude_is_relative = false;
break;
case MAV_FRAME_GLOBAL_RELATIVE_ALT:
mission_item->lat = (double)mavlink_mission_item->x;
mission_item->lon = (double)mavlink_mission_item->y;
mission_item->altitude = mavlink_mission_item->z;
mission_item->altitude_is_relative = true;
break;
case MAV_FRAME_MISSION:
// This is a mission item with no coordinate
mission_item->params[0] = mavlink_mission_item->param1;
mission_item->params[1] = mavlink_mission_item->param2;
mission_item->params[2] = mavlink_mission_item->param3;
mission_item->params[3] = mavlink_mission_item->param4;
mission_item->params[4] = mavlink_mission_item->x;
mission_item->params[5] = mavlink_mission_item->y;
mission_item->params[6] = mavlink_mission_item->z;
break;
default:
return MAV_MISSION_UNSUPPORTED_FRAME;
}
mission_item->frame = mavlink_mission_item->frame;
switch (mavlink_mission_item->command) {
case MAV_CMD_NAV_TAKEOFF:
mission_item->pitch_min = mavlink_mission_item->param1;
break;
case MAV_CMD_DO_JUMP:
mission_item->do_jump_mission_index = mavlink_mission_item->param1;
mission_item->do_jump_current_count = 0;
mission_item->do_jump_repeat_count = mavlink_mission_item->param2;
break;
default:
mission_item->acceptance_radius = mavlink_mission_item->param2;
mission_item->time_inside = mavlink_mission_item->param1;
break;
}
mission_item->yaw = _wrap_pi(mavlink_mission_item->param4 * M_DEG_TO_RAD_F);
mission_item->loiter_radius = fabsf(mavlink_mission_item->param3);
mission_item->loiter_direction = (mavlink_mission_item->param3 > 0) ? 1 : -1; /* 1 if positive CW, -1 if negative CCW */
/* unsigned, so can't be negative, only check for overflow */
if (mavlink_mission_item->command >= NAV_CMD_INVALID) {
mission_item->nav_cmd = NAV_CMD_INVALID;
} else {
mission_item->nav_cmd = (NAV_CMD)mavlink_mission_item->command;
}
mission_item->autocontinue = mavlink_mission_item->autocontinue;
// mission_item->index = mavlink_mission_item->seq;
mission_item->origin = ORIGIN_MAVLINK;
/* reset DO_JUMP count */
mission_item->do_jump_current_count = 0;
return MAV_MISSION_ACCEPTED;
}
void check_waypoints_reached(absolute_time now, const struct vehicle_global_position_s *global_pos, float turn_distance)
{
mission_command_t current_command;
bool_t time_elapsed = 0;
float vertical_switch_distance, yaw_sp, yaw_err;
float dist = -1.0f, dist_xy = -1.0f, dist_z = -1.0f;
float current_lat = -1.0f, current_lon = -1.0f, current_alt = -1.0f;
float orbit = mission_waypoint_manager_parameters.orbit_def_radius;
float orbit_hold_time = mission_waypoint_manager_parameters.orbit_hold_time;
/* position not valid */
if (!global_pos->valid || check_out_of_bounds(wp_manager.current_setpoint_index, 0, mission.n_commands)) {
/* nothing to check here, return */
return;
}
current_command = mission.command_list[wp_manager.current_setpoint_index];
if (wp_manager.current_setpoint_index < mission.n_commands) {
if (current_command.name == accepted_command_waypoint ||
current_command.name == accepted_command_loiter_time ||
current_command.name == accepted_command_loiter_circle ||
current_command.name == accepted_command_loiter_unlim) {
if (current_command.option4 >= mission_waypoint_manager_parameters.orbit_min_radius)
orbit = current_command.option4;
}
/* keep vertical orbit */
vertical_switch_distance = orbit;
/* Take the larger turn distance - orbit or turn_distance */
if (orbit < turn_distance)
orbit = turn_distance;
current_alt = current_command.option1;
current_lat = (current_command.name == accepted_command_rtl ||
current_command.name == accepted_command_land)? home_position.latitude : current_command.option2;
current_lon = (current_command.name == accepted_command_rtl ||
current_command.name == accepted_command_land)? home_position.longitude : current_command.option3;
dist = wpm_distance_to_point_global_wgs84(current_alt, current_lat, current_lon, global_pos->altitude, (float)global_pos->latitude * 1e-7f, (float)global_pos->longitude * 1e-7f, &dist_xy, &dist_z);
if (dist >= 0.f && dist_xy <= orbit && dist_z >= 0.0f && dist_z <= vertical_switch_distance) {
wp_manager.pos_reached = 1;
}
// check if required yaw reached
yaw_sp = get_yaw_to_next_waypoint (wp_manager.current_setpoint_index, wp_manager.next_setpoint_index);
yaw_err = _wrap_pi(yaw_sp - global_pos->yaw);
if (fabsf(yaw_err) < 0.05f) {
wp_manager.yaw_reached = 1;
}
}
//check if the current waypoint was reached
if (wp_manager.pos_reached /* && wp_manager.yaw_reached */) {
if (wp_manager.timestamp_firstinside_orbit == 0) {
// Announce that last waypoint was reached
//wpm_send_waypoint_reached(wp_manager.current_setpoint_index);
wp_manager.timestamp_firstinside_orbit = now;
}
// check if the MAV was long enough inside the waypoint orbit
if (current_command.name != accepted_command_loiter_unlim && // XXX check this
(now - wp_manager.timestamp_firstinside_orbit >= orbit_hold_time * 1000000 ||
current_command.name == accepted_command_takeoff)) {
time_elapsed = 1;
}
if (time_elapsed) {
current_command.current = 0;
wp_manager.last_setpoint_index = wp_manager.current_setpoint_index;
wp_manager.last_setpoint_valid = wp_manager.current_setpoint_valid;
wp_manager.current_setpoint_index = wp_manager.next_setpoint_index;
wp_manager.current_setpoint_valid = wp_manager.next_setpoint_valid;
if (wp_manager.current_setpoint_valid)
find_next_setpoint_index (wp_manager.current_setpoint_index, &wp_manager.next_setpoint_index, &wp_manager.next_setpoint_valid);
/* if an error occur abort and return to home (then loiter unlim) */
if (!wp_manager.current_setpoint_valid) {
wp_manager.current_setpoint_index = mission.n_commands;
wp_manager.current_setpoint_valid = 1;
}
// Fly to next waypoint
wp_manager.timestamp_firstinside_orbit = 0;
wp_manager.timestamp_lastoutside_orbit = 0;
wp_manager.pos_reached = 0;
wp_manager.yaw_reached = 0;
mission.command_list[wp_manager.current_setpoint_index].current = 1;
//wpm_send_waypoint_current(wp_manager.current_setpoint_index);
missionlib_current_waypoint_changed();
}
}
else {
wp_manager.timestamp_lastoutside_orbit = now;
}
}
void
MulticopterPositionControl::task_main()
{
_mavlink_fd = open(MAVLINK_LOG_DEVICE, 0);
/*
* do subscriptions
*/
_att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
_control_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_manual_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_arming_sub = orb_subscribe(ORB_ID(actuator_armed));
_local_pos_sub = orb_subscribe(ORB_ID(vehicle_local_position));
_pos_sp_triplet_sub = orb_subscribe(ORB_ID(position_setpoint_triplet));
_local_pos_sp_sub = orb_subscribe(ORB_ID(vehicle_local_position_setpoint));
_global_vel_sp_sub = orb_subscribe(ORB_ID(vehicle_global_velocity_setpoint));
parameters_update(true);
/* initialize values of critical structs until first regular update */
_arming.armed = false;
/* get an initial update for all sensor and status data */
poll_subscriptions();
bool reset_int_z = true;
bool reset_int_z_manual = false;
bool reset_int_xy = true;
bool reset_yaw_sp = true;
bool was_armed = false;
hrt_abstime t_prev = 0;
_hover_time = 0.0; // miao:
_mode_mission = 1;
math::Vector<3> thrust_int;
thrust_int.zero();
math::Matrix<3, 3> R;
R.identity();
/* wakeup source */
struct pollfd fds[1];
fds[0].fd = _local_pos_sub;
fds[0].events = POLLIN;
while (!_task_should_exit) {
/* wait for up to 500ms for data */
int pret = poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 500);
/* timed out - periodic check for _task_should_exit */
if (pret == 0) {
continue;
}
/* this is undesirable but not much we can do */
if (pret < 0) {
warn("poll error %d, %d", pret, errno);
continue;
}
poll_subscriptions();
parameters_update(false);
hrt_abstime t = hrt_absolute_time();
float dt = t_prev != 0 ? (t - t_prev) * 0.000001f : 0.0f;
t_prev = t;
if (_control_mode.flag_armed && !was_armed) {
/* reset setpoints and integrals on arming */
_reset_pos_sp = true;
_reset_alt_sp = true;
reset_int_z = true;
reset_int_xy = true;
reset_yaw_sp = true;
_reset_mission = true;//miao:
}
//Update previous arming state
was_armed = _control_mode.flag_armed;
update_ref();
if (_control_mode.flag_control_altitude_enabled ||
_control_mode.flag_control_position_enabled ||
_control_mode.flag_control_climb_rate_enabled ||
_control_mode.flag_control_velocity_enabled) {
_pos(0) = _local_pos.x;
_pos(1) = _local_pos.y;
_pos(2) = _local_pos.z;
_vel(0) = _local_pos.vx;
_vel(1) = _local_pos.vy;
_vel(2) = _local_pos.vz;
_vel_ff.zero();
_sp_move_rate.zero();
/* select control source */
if (_control_mode.flag_control_manual_enabled) {
/* manual control */
control_manual(dt);
_mode_auto = false;
} else if (_control_mode.flag_control_offboard_enabled) {
/* offboard control */
control_offboard(dt);
_mode_auto = false;
} else {
/* AUTO */
control_auto(dt);
}
if (!_control_mode.flag_control_manual_enabled && _pos_sp_triplet.current.valid && _pos_sp_triplet.current.type == position_setpoint_s::SETPOINT_TYPE_IDLE) {
/* idle state, don't run controller and set zero thrust */
R.identity();
memcpy(&_att_sp.R_body[0], R.data, sizeof(_att_sp.R_body));
_att_sp.R_valid = true;
_att_sp.roll_body = 0.0f;
_att_sp.pitch_body = 0.0f;
_att_sp.yaw_body = _att.yaw;
_att_sp.thrust = 0.0f;
_att_sp.timestamp = hrt_absolute_time();
/* publish attitude setpoint */
if (_att_sp_pub > 0) {
orb_publish(ORB_ID(vehicle_attitude_setpoint), _att_sp_pub, &_att_sp);
} else {
_att_sp_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &_att_sp);
}
} else {
/* run position & altitude controllers, calculate velocity setpoint */
math::Vector<3> pos_err = _pos_sp - _pos;
_vel_sp = pos_err.emult(_params.pos_p) + _vel_ff;
if (!_control_mode.flag_control_altitude_enabled) {
_reset_alt_sp = true;
_vel_sp(2) = 0.0f;
}
if (!_control_mode.flag_control_position_enabled) {
_reset_pos_sp = true;
_vel_sp(0) = 0.0f;
_vel_sp(1) = 0.0f;
}
/* use constant descend rate when landing, ignore altitude setpoint */
//if (!_control_mode.flag_control_manual_enabled && _pos_sp_triplet.current.valid && _pos_sp_triplet.current.type == position_setpoint_s::SETPOINT_TYPE_LAND) {
// miao: for auto landing test with manual mode
if (_mode_mission==3) {
_vel_sp(2) = _params.land_speed;
}
_global_vel_sp.vx = _vel_sp(0);
_global_vel_sp.vy = _vel_sp(1);
_global_vel_sp.vz = _vel_sp(2);
/* publish velocity setpoint */
if (_global_vel_sp_pub > 0) {
orb_publish(ORB_ID(vehicle_global_velocity_setpoint), _global_vel_sp_pub, &_global_vel_sp);
} else {
_global_vel_sp_pub = orb_advertise(ORB_ID(vehicle_global_velocity_setpoint), &_global_vel_sp);
}
if (_control_mode.flag_control_climb_rate_enabled || _control_mode.flag_control_velocity_enabled) {
/* reset integrals if needed */
if (_control_mode.flag_control_climb_rate_enabled) {
if (reset_int_z) {
reset_int_z = false;
float i = _params.thr_min;
if (reset_int_z_manual) {
i = _manual.z;
if (i < _params.thr_min) {
i = _params.thr_min;
} else if (i > _params.thr_max) {
i = _params.thr_max;
}
}
thrust_int(2) = -i;
}
} else {
reset_int_z = true;
}
if (_control_mode.flag_control_velocity_enabled) {
if (reset_int_xy) {
reset_int_xy = false;
thrust_int(0) = 0.0f;
thrust_int(1) = 0.0f;
}
} else {
reset_int_xy = true;
}
/* velocity error */
math::Vector<3> vel_err = _vel_sp - _vel;
/* derivative of velocity error, not includes setpoint acceleration */
math::Vector<3> vel_err_d = (_sp_move_rate - _vel).emult(_params.pos_p) - (_vel - _vel_prev) / dt;
_vel_prev = _vel;
/* thrust vector in NED frame */
math::Vector<3> thrust_sp = vel_err.emult(_params.vel_p) + vel_err_d.emult(_params.vel_d) + thrust_int;
if (!_control_mode.flag_control_velocity_enabled) {
thrust_sp(0) = 0.0f;
thrust_sp(1) = 0.0f;
}
if (!_control_mode.flag_control_climb_rate_enabled) {
thrust_sp(2) = 0.0f;
}
/* limit thrust vector and check for saturation */
bool saturation_xy = false;
bool saturation_z = false;
/* limit min lift */
float thr_min = _params.thr_min;
if (!_control_mode.flag_control_velocity_enabled && thr_min < 0.0f) {
/* don't allow downside thrust direction in manual attitude mode */
thr_min = 0.0f;
}
float tilt_max = _params.tilt_max_air;
/* adjust limits for landing mode */
if (!_control_mode.flag_control_manual_enabled && _pos_sp_triplet.current.valid &&
_pos_sp_triplet.current.type == position_setpoint_s::SETPOINT_TYPE_LAND) {
/* limit max tilt and min lift when landing */
tilt_max = _params.tilt_max_land;
if (thr_min < 0.0f) {
thr_min = 0.0f;
}
}
/* limit min lift */
if (-thrust_sp(2) < thr_min) {
thrust_sp(2) = -thr_min;
saturation_z = true;
}
if (_control_mode.flag_control_velocity_enabled) {
/* limit max tilt */
if (thr_min >= 0.0f && tilt_max < M_PI_F / 2 - 0.05f) {
/* absolute horizontal thrust */
float thrust_sp_xy_len = math::Vector<2>(thrust_sp(0), thrust_sp(1)).length();
if (thrust_sp_xy_len > 0.01f) {
/* max horizontal thrust for given vertical thrust*/
float thrust_xy_max = -thrust_sp(2) * tanf(tilt_max);
if (thrust_sp_xy_len > thrust_xy_max) {
float k = thrust_xy_max / thrust_sp_xy_len;
thrust_sp(0) *= k;
thrust_sp(1) *= k;
saturation_xy = true;
}
}
}
} else {
/* thrust compensation for altitude only control mode */
float att_comp;
if (PX4_R(_att.R, 2, 2) > TILT_COS_MAX) {
att_comp = 1.0f / PX4_R(_att.R, 2, 2);
} else if (PX4_R(_att.R, 2, 2) > 0.0f) {
att_comp = ((1.0f / TILT_COS_MAX - 1.0f) / TILT_COS_MAX) * PX4_R(_att.R, 2, 2) + 1.0f;
saturation_z = true;
} else {
att_comp = 1.0f;
saturation_z = true;
}
thrust_sp(2) *= att_comp;
}
/* limit max thrust */
float thrust_abs = thrust_sp.length();
if (thrust_abs > _params.thr_max) {
if (thrust_sp(2) < 0.0f) {
if (-thrust_sp(2) > _params.thr_max) {
/* thrust Z component is too large, limit it */
thrust_sp(0) = 0.0f;
thrust_sp(1) = 0.0f;
thrust_sp(2) = -_params.thr_max;
saturation_xy = true;
saturation_z = true;
} else {
/* preserve thrust Z component and lower XY, keeping altitude is more important than position */
float thrust_xy_max = sqrtf(_params.thr_max * _params.thr_max - thrust_sp(2) * thrust_sp(2));
float thrust_xy_abs = math::Vector<2>(thrust_sp(0), thrust_sp(1)).length();
float k = thrust_xy_max / thrust_xy_abs;
thrust_sp(0) *= k;
thrust_sp(1) *= k;
saturation_xy = true;
}
} else {
/* Z component is negative, going down, simply limit thrust vector */
float k = _params.thr_max / thrust_abs;
thrust_sp *= k;
saturation_xy = true;
saturation_z = true;
}
thrust_abs = _params.thr_max;
}
/* update integrals */
if (_control_mode.flag_control_velocity_enabled && !saturation_xy) {
thrust_int(0) += vel_err(0) * _params.vel_i(0) * dt;
thrust_int(1) += vel_err(1) * _params.vel_i(1) * dt;
}
if (_control_mode.flag_control_climb_rate_enabled && !saturation_z) {
thrust_int(2) += vel_err(2) * _params.vel_i(2) * dt;
/* protection against flipping on ground when landing */
if (thrust_int(2) > 0.0f) {
thrust_int(2) = 0.0f;
}
}
/* calculate attitude setpoint from thrust vector */
if (_control_mode.flag_control_velocity_enabled) {
/* desired body_z axis = -normalize(thrust_vector) */
math::Vector<3> body_x;
math::Vector<3> body_y;
math::Vector<3> body_z;
if (thrust_abs > SIGMA) {
body_z = -thrust_sp / thrust_abs;
} else {
/* no thrust, set Z axis to safe value */
body_z.zero();
body_z(2) = 1.0f;
}
/* vector of desired yaw direction in XY plane, rotated by PI/2 */
math::Vector<3> y_C(-sinf(_att_sp.yaw_body), cosf(_att_sp.yaw_body), 0.0f);
if (fabsf(body_z(2)) > SIGMA) {
/* desired body_x axis, orthogonal to body_z */
body_x = y_C % body_z;
/* keep nose to front while inverted upside down */
if (body_z(2) < 0.0f) {
body_x = -body_x;
}
body_x.normalize();
} else {
/* desired thrust is in XY plane, set X downside to construct correct matrix,
* but yaw component will not be used actually */
body_x.zero();
body_x(2) = 1.0f;
}
/* desired body_y axis */
body_y = body_z % body_x;
/* fill rotation matrix */
for (int i = 0; i < 3; i++) {
R(i, 0) = body_x(i);
R(i, 1) = body_y(i);
R(i, 2) = body_z(i);
}
/* copy rotation matrix to attitude setpoint topic */
memcpy(&_att_sp.R_body[0], R.data, sizeof(_att_sp.R_body));
_att_sp.R_valid = true;
/* calculate euler angles, for logging only, must not be used for control */
math::Vector<3> euler = R.to_euler();
_att_sp.roll_body = euler(0);
_att_sp.pitch_body = euler(1);
/* yaw already used to construct rot matrix, but actual rotation matrix can have different yaw near singularity */
} else if (!_control_mode.flag_control_manual_enabled) {
/* autonomous altitude control without position control (failsafe landing),
* force level attitude, don't change yaw */
R.from_euler(0.0f, 0.0f, _att_sp.yaw_body);
/* copy rotation matrix to attitude setpoint topic */
memcpy(&_att_sp.R_body[0], R.data, sizeof(_att_sp.R_body));
_att_sp.R_valid = true;
_att_sp.roll_body = 0.0f;
_att_sp.pitch_body = 0.0f;
}
_att_sp.thrust = thrust_abs;
/* save thrust setpoint for logging */
_local_pos_sp.acc_x = thrust_sp(0);
_local_pos_sp.acc_x = thrust_sp(1);
_local_pos_sp.acc_x = thrust_sp(2);
_att_sp.timestamp = hrt_absolute_time();
} else {
reset_int_z = true;
}
}
/* fill local position, velocity and thrust setpoint */
_local_pos_sp.timestamp = hrt_absolute_time();
_local_pos_sp.x = _pos_sp(0);
_local_pos_sp.y = _pos_sp(1);
_local_pos_sp.z = _pos_sp(2);
_local_pos_sp.yaw = _att_sp.yaw_body;
_local_pos_sp.vx = _vel_sp(0);
_local_pos_sp.vy = _vel_sp(1);
_local_pos_sp.vz = _vel_sp(2);
/* publish local position setpoint */
if (_local_pos_sp_pub > 0) {
orb_publish(ORB_ID(vehicle_local_position_setpoint), _local_pos_sp_pub, &_local_pos_sp);
} else {
_local_pos_sp_pub = orb_advertise(ORB_ID(vehicle_local_position_setpoint), &_local_pos_sp);
}
} else {
/* position controller disabled, reset setpoints */
_reset_alt_sp = true;
_reset_pos_sp = true;
_mode_auto = false;
reset_int_z = true;
reset_int_xy = true;
}
// generate attitude setpoint from manual controls
if(_control_mode.flag_control_manual_enabled && _control_mode.flag_control_attitude_enabled) {
// reset yaw setpoint to current position if needed
if (reset_yaw_sp) {
reset_yaw_sp = false;
_att_sp.yaw_body = _att.yaw;
}
// do not move yaw while arming
else if (_manual.z > 0.1f)
{
const float YAW_OFFSET_MAX = _params.man_yaw_max / _params.mc_att_yaw_p;
_att_sp.yaw_sp_move_rate = _manual.r * _params.man_yaw_max;
_att_sp.yaw_body = _wrap_pi(_att_sp.yaw_body + _att_sp.yaw_sp_move_rate * dt);
float yaw_offs = _wrap_pi(_att_sp.yaw_body - _att.yaw);
if (yaw_offs < - YAW_OFFSET_MAX) {
_att_sp.yaw_body = _wrap_pi(_att.yaw - YAW_OFFSET_MAX);
} else if (yaw_offs > YAW_OFFSET_MAX) {
_att_sp.yaw_body = _wrap_pi(_att.yaw + YAW_OFFSET_MAX);
}
}
//Control roll and pitch directly if we no aiding velocity controller is active
if(!_control_mode.flag_control_velocity_enabled) {
_att_sp.roll_body = _manual.y * _params.man_roll_max;
_att_sp.pitch_body = -_manual.x * _params.man_pitch_max;
}
//Control climb rate directly if no aiding altitude controller is active
if(!_control_mode.flag_control_climb_rate_enabled) {
_att_sp.thrust = _manual.z;
}
//Construct attitude setpoint rotation matrix
math::Matrix<3,3> R_sp;
R_sp.from_euler(_att_sp.roll_body,_att_sp.pitch_body,_att_sp.yaw_body);
memcpy(&_att_sp.R_body[0], R_sp.data, sizeof(_att_sp.R_body));
_att_sp.timestamp = hrt_absolute_time();
}
else {
reset_yaw_sp = true;
}
/* publish attitude setpoint
* Do not publish if offboard is enabled but position/velocity control is disabled,
* in this case the attitude setpoint is published by the mavlink app
*/
if (!(_control_mode.flag_control_offboard_enabled &&
!(_control_mode.flag_control_position_enabled ||
_control_mode.flag_control_velocity_enabled))) {
if (_att_sp_pub > 0) {
orb_publish(ORB_ID(vehicle_attitude_setpoint), _att_sp_pub, &_att_sp);
} else {
_att_sp_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &_att_sp);
}
}
/* reset altitude controller integral (hovering throttle) to manual throttle after manual throttle control */
reset_int_z_manual = _control_mode.flag_armed && _control_mode.flag_control_manual_enabled && !_control_mode.flag_control_climb_rate_enabled;
}
warnx("stopped");
mavlink_log_info(_mavlink_fd, "[mpc] stopped");
_control_task = -1;
_exit(0);
}
void BlockMultiModeBacksideAutopilot::update()
{
// wait for a sensor update, check for exit condition every 100 ms
if (poll(&_attPoll, 1, 100) < 0) return; // poll error
uint64_t newTimeStamp = hrt_absolute_time();
float dt = (newTimeStamp - _timeStamp) / 1.0e6f;
_timeStamp = newTimeStamp;
// check for sane values of dt
// to prevent large control responses
if (dt > 1.0f || dt < 0) return;
// set dt for all child blocks
setDt(dt);
// store old position command before update if new command sent
if (_posCmd.updated()) {
_lastPosCmd = _posCmd.getData();
}
// check for new updates
if (_param_update.updated()) updateParams();
// get new information from subscriptions
updateSubscriptions();
// default all output to zero unless handled by mode
for (unsigned i = 4; i < NUM_ACTUATOR_CONTROLS; i++)
_actuators.control[i] = 0.0f;
// only update guidance in auto mode
if (_status.state_machine == SYSTEM_STATE_AUTO) {
// update guidance
_guide.update(_pos, _att, _posCmd, _lastPosCmd);
}
// XXX handle STABILIZED (loiter on spot) as well
// once the system switches from manual or auto to stabilized
// the setpoint should update to loitering around this position
// handle autopilot modes
if (_status.state_machine == SYSTEM_STATE_AUTO ||
_status.state_machine == SYSTEM_STATE_STABILIZED) {
// update guidance
_guide.update(_pos, _att, _posCmd, _lastPosCmd);
// calculate velocity, XXX should be airspeed, but using ground speed for now
float v = sqrtf(_pos.vx * _pos.vx + _pos.vy * _pos.vy + _pos.vz * _pos.vz);
// altitude hold
float dThrottle = _h2Thr.update(_posCmd.altitude - _pos.alt);
// heading hold
float psiError = _wrap_pi(_guide.getPsiCmd() - _att.yaw);
float phiCmd = _phiLimit.update(_psi2Phi.update(psiError));
float pCmd = _phi2P.update(phiCmd - _att.roll);
// velocity hold
// negative sign because nose over to increase speed
float thetaCmd = _theLimit.update(-_v2Theta.update(
_vLimit.update(_vCmd.get()) - v));
float qCmd = _theta2Q.update(thetaCmd - _att.pitch);
// yaw rate cmd
float rCmd = 0;
// stabilization
_stabilization.update(pCmd, qCmd, rCmd,
_att.rollspeed, _att.pitchspeed, _att.yawspeed);
// output
_actuators.control[CH_AIL] = _stabilization.getAileron() + _trimAil.get();
_actuators.control[CH_ELV] = _stabilization.getElevator() + _trimElv.get();
_actuators.control[CH_RDR] = _stabilization.getRudder() + _trimRdr.get();
_actuators.control[CH_THR] = dThrottle + _trimThr.get();
// XXX limit throttle to manual setting (safety) for now.
// If it turns out to be confusing, it can be removed later once
// a first binary release can be targeted.
// This is not a hack, but a design choice.
/* do not limit in HIL */
if (!_status.flag_hil_enabled) {
/* limit to value of manual throttle */
_actuators.control[CH_THR] = (_actuators.control[CH_THR] < _manual.throttle) ?
_actuators.control[CH_THR] : _manual.throttle;
}
} else if (_status.state_machine == SYSTEM_STATE_MANUAL) {
if (_status.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_DIRECT) {
_actuators.control[CH_AIL] = _manual.roll;
_actuators.control[CH_ELV] = _manual.pitch;
_actuators.control[CH_RDR] = _manual.yaw;
_actuators.control[CH_THR] = _manual.throttle;
} else if (_status.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_SAS) {
// calculate velocity, XXX should be airspeed, but using ground speed for now
float v = sqrtf(_pos.vx * _pos.vx + _pos.vy * _pos.vy + _pos.vz * _pos.vz);
// pitch channel -> rate of climb
// TODO, might want to put a gain on this, otherwise commanding
// from +1 -> -1 m/s for rate of climb
//float dThrottle = _roc2Thr.update(
//_rocMax.get()*_manual.pitch - _pos.vz);
// roll channel -> bank angle
float phiCmd = _phiLimit.update(_manual.roll * _phiLimit.getMax());
float pCmd = _phi2P.update(phiCmd - _att.roll);
// throttle channel -> velocity
// negative sign because nose over to increase speed
float vCmd = _manual.throttle * (_vLimit.getMax() - _vLimit.getMin()) + _vLimit.getMin();
float thetaCmd = _theLimit.update(-_v2Theta.update(_vLimit.update(vCmd) - v));
float qCmd = _theta2Q.update(thetaCmd - _att.pitch);
// yaw rate cmd
float rCmd = 0;
// stabilization
_stabilization.update(pCmd, qCmd, rCmd,
_att.rollspeed, _att.pitchspeed, _att.yawspeed);
// output
_actuators.control[CH_AIL] = _stabilization.getAileron() + _trimAil.get();
_actuators.control[CH_ELV] = _stabilization.getElevator() + _trimElv.get();
_actuators.control[CH_RDR] = _stabilization.getRudder() + _trimRdr.get();
// currenlty using manual throttle
// XXX if you enable this watch out, vz might be very noisy
//_actuators.control[CH_THR] = dThrottle + _trimThr.get();
_actuators.control[CH_THR] = _manual.throttle;
// XXX limit throttle to manual setting (safety) for now.
// If it turns out to be confusing, it can be removed later once
// a first binary release can be targeted.
// This is not a hack, but a design choice.
/* do not limit in HIL */
if (!_status.flag_hil_enabled) {
/* limit to value of manual throttle */
_actuators.control[CH_THR] = (_actuators.control[CH_THR] < _manual.throttle) ?
_actuators.control[CH_THR] : _manual.throttle;
}
}
// body rates controller, disabled for now
else if (0 /*_status.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_SAS*/) {
_stabilization.update(_manual.roll, _manual.pitch, _manual.yaw,
_att.rollspeed, _att.pitchspeed, _att.yawspeed);
_actuators.control[CH_AIL] = _stabilization.getAileron();
_actuators.control[CH_ELV] = _stabilization.getElevator();
_actuators.control[CH_RDR] = _stabilization.getRudder();
_actuators.control[CH_THR] = _manual.throttle;
}
}
// update all publications
updatePublications();
}
float BlockHeadingHold::update(float psiCmd, float phi, float psi, float p)
{
float psiError = _wrap_pi(psiCmd - psi);
float phiCmd = _phiLimit.update(_psi2Phi.update(psiError));
return _phi2P.update(phiCmd - phi);
}
/*
* Attitude controller.
* Input: 'manual_control_setpoint' and 'vehicle_attitude_setpoint' topics (depending on mode)
* Output: '_rates_sp' vector, '_thrust_sp', 'vehicle_attitude_setpoint' topic (for manual modes)
*/
void
MulticopterAttitudeControl::control_attitude(float dt)
{
float yaw_sp_move_rate = 0.0f;
bool publish_att_sp = false;
if (_v_control_mode.flag_control_manual_enabled) {
/* manual input, set or modify attitude setpoint */
if (_v_control_mode.flag_control_velocity_enabled || _v_control_mode.flag_control_climb_rate_enabled) {
/* in assisted modes poll 'vehicle_attitude_setpoint' topic and modify it */
vehicle_attitude_setpoint_poll();
}
if (!_v_control_mode.flag_control_climb_rate_enabled) {
/* pass throttle directly if not in altitude stabilized mode */
_v_att_sp.thrust = _manual_control_sp.z;
publish_att_sp = true;
}
if (!_armed.armed) {
/* reset yaw setpoint when disarmed */
_reset_yaw_sp = true;
}
/* move yaw setpoint in all modes */
if (_v_att_sp.thrust < 0.1f) {
// TODO
//if (_status.condition_landed) {
/* reset yaw setpoint if on ground */
// reset_yaw_sp = true;
//}
} else {
/* move yaw setpoint */
yaw_sp_move_rate = _manual_control_sp.r * _params.man_yaw_max;
_v_att_sp.yaw_body = _wrap_pi(_v_att_sp.yaw_body + yaw_sp_move_rate * dt);
float yaw_offs_max = _params.man_yaw_max / _params.att_p(2);
float yaw_offs = _wrap_pi(_v_att_sp.yaw_body - _v_att.yaw);
if (yaw_offs < - yaw_offs_max) {
_v_att_sp.yaw_body = _wrap_pi(_v_att.yaw - yaw_offs_max);
} else if (yaw_offs > yaw_offs_max) {
_v_att_sp.yaw_body = _wrap_pi(_v_att.yaw + yaw_offs_max);
}
_v_att_sp.R_valid = false;
publish_att_sp = true;
}
/* reset yaw setpint to current position if needed */
if (_reset_yaw_sp) {
_reset_yaw_sp = false;
_v_att_sp.yaw_body = _v_att.yaw;
_v_att_sp.R_valid = false;
publish_att_sp = true;
}
if (!_v_control_mode.flag_control_velocity_enabled) {
/* update attitude setpoint if not in position control mode */
_v_att_sp.roll_body = _manual_control_sp.y * _params.man_roll_max;
_v_att_sp.pitch_body = -_manual_control_sp.x * _params.man_pitch_max;
_v_att_sp.R_valid = false;
publish_att_sp = true;
}
} else {
/* in non-manual mode use 'vehicle_attitude_setpoint' topic */
vehicle_attitude_setpoint_poll();
/* reset yaw setpoint after non-manual control mode */
_reset_yaw_sp = true;
}
_thrust_sp = _v_att_sp.thrust;
/* construct attitude setpoint rotation matrix */
math::Matrix<3, 3> R_sp;
if (_v_att_sp.R_valid) {
/* rotation matrix in _att_sp is valid, use it */
R_sp.set(&_v_att_sp.R_body[0][0]);
} else {
/* rotation matrix in _att_sp is not valid, use euler angles instead */
R_sp.from_euler(_v_att_sp.roll_body, _v_att_sp.pitch_body, _v_att_sp.yaw_body);
/* copy rotation matrix back to setpoint struct */
memcpy(&_v_att_sp.R_body[0][0], &R_sp.data[0][0], sizeof(_v_att_sp.R_body));
_v_att_sp.R_valid = true;
}
/* publish the attitude setpoint if needed */
if (publish_att_sp) {
_v_att_sp.timestamp = hrt_absolute_time();
if (_att_sp_pub > 0) {
orb_publish(ORB_ID(vehicle_attitude_setpoint), _att_sp_pub, &_v_att_sp);
} else {
_att_sp_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &_v_att_sp);
}
}
/* rotation matrix for current state */
math::Matrix<3, 3> R;
R.set(_v_att.R);
/* all input data is ready, run controller itself */
/* try to move thrust vector shortest way, because yaw response is slower than roll/pitch */
math::Vector<3> R_z(R(0, 2), R(1, 2), R(2, 2));
math::Vector<3> R_sp_z(R_sp(0, 2), R_sp(1, 2), R_sp(2, 2));
/* axis and sin(angle) of desired rotation */
math::Vector<3> e_R = R.transposed() * (R_z % R_sp_z);
/* calculate angle error */
float e_R_z_sin = e_R.length();
float e_R_z_cos = R_z * R_sp_z;
/* calculate weight for yaw control */
float yaw_w = R_sp(2, 2) * R_sp(2, 2);
/* calculate rotation matrix after roll/pitch only rotation */
math::Matrix<3, 3> R_rp;
if (e_R_z_sin > 0.0f) {
/* get axis-angle representation */
float e_R_z_angle = atan2f(e_R_z_sin, e_R_z_cos);
math::Vector<3> e_R_z_axis = e_R / e_R_z_sin;
e_R = e_R_z_axis * e_R_z_angle;
/* cross product matrix for e_R_axis */
math::Matrix<3, 3> e_R_cp;
e_R_cp.zero();
e_R_cp(0, 1) = -e_R_z_axis(2);
e_R_cp(0, 2) = e_R_z_axis(1);
e_R_cp(1, 0) = e_R_z_axis(2);
e_R_cp(1, 2) = -e_R_z_axis(0);
e_R_cp(2, 0) = -e_R_z_axis(1);
e_R_cp(2, 1) = e_R_z_axis(0);
/* rotation matrix for roll/pitch only rotation */
R_rp = R * (_I + e_R_cp * e_R_z_sin + e_R_cp * e_R_cp * (1.0f - e_R_z_cos));
} else {
/* zero roll/pitch rotation */
R_rp = R;
}
/* R_rp and R_sp has the same Z axis, calculate yaw error */
math::Vector<3> R_sp_x(R_sp(0, 0), R_sp(1, 0), R_sp(2, 0));
math::Vector<3> R_rp_x(R_rp(0, 0), R_rp(1, 0), R_rp(2, 0));
e_R(2) = atan2f((R_rp_x % R_sp_x) * R_sp_z, R_rp_x * R_sp_x) * yaw_w;
if (e_R_z_cos < 0.0f) {
/* for large thrust vector rotations use another rotation method:
* calculate angle and axis for R -> R_sp rotation directly */
math::Quaternion q;
q.from_dcm(R.transposed() * R_sp);
math::Vector<3> e_R_d = q.imag();
e_R_d.normalize();
e_R_d *= 2.0f * atan2f(e_R_d.length(), q(0));
/* use fusion of Z axis based rotation and direct rotation */
float direct_w = e_R_z_cos * e_R_z_cos * yaw_w;
e_R = e_R * (1.0f - direct_w) + e_R_d * direct_w;
}
/* calculate angular rates setpoint */
_rates_sp = _params.att_p.emult(e_R);
/* limit yaw rate */
_rates_sp(2) = math::constrain(_rates_sp(2), -_params.yaw_rate_max, _params.yaw_rate_max);
/* feed forward yaw setpoint rate */
_rates_sp(2) += yaw_sp_move_rate * yaw_w * _params.yaw_ff;
}
void FollowTarget::on_active()
{
struct map_projection_reference_s target_ref;
math::Vector<3> target_reported_velocity(0, 0, 0);
follow_target_s target_motion_with_offset = {};
uint64_t current_time = hrt_absolute_time();
bool _radius_entered = false;
bool _radius_exited = false;
bool updated = false;
float dt_ms = 0;
orb_check(_follow_target_sub, &updated);
if (updated) {
follow_target_s target_motion;
_target_updates++;
// save last known motion topic
_previous_target_motion = _current_target_motion;
orb_copy(ORB_ID(follow_target), _follow_target_sub, &target_motion);
if (_current_target_motion.timestamp == 0) {
_current_target_motion = target_motion;
}
_current_target_motion.timestamp = target_motion.timestamp;
_current_target_motion.lat = (_current_target_motion.lat * (double)_responsiveness) + target_motion.lat * (double)(
1 - _responsiveness);
_current_target_motion.lon = (_current_target_motion.lon * (double)_responsiveness) + target_motion.lon * (double)(
1 - _responsiveness);
target_reported_velocity(0) = _current_target_motion.vx;
target_reported_velocity(1) = _current_target_motion.vy;
} else if (((current_time - _current_target_motion.timestamp) / 1000) > TARGET_TIMEOUT_MS && target_velocity_valid()) {
reset_target_validity();
}
// update distance to target
if (target_position_valid()) {
// get distance to target
map_projection_init(&target_ref, _navigator->get_global_position()->lat, _navigator->get_global_position()->lon);
map_projection_project(&target_ref, _current_target_motion.lat, _current_target_motion.lon, &_target_distance(0),
&_target_distance(1));
}
// update target velocity
if (target_velocity_valid() && updated) {
dt_ms = ((_current_target_motion.timestamp - _previous_target_motion.timestamp) / 1000);
// ignore a small dt
if (dt_ms > 10.0F) {
// get last gps known reference for target
map_projection_init(&target_ref, _previous_target_motion.lat, _previous_target_motion.lon);
// calculate distance the target has moved
map_projection_project(&target_ref, _current_target_motion.lat, _current_target_motion.lon,
&(_target_position_delta(0)), &(_target_position_delta(1)));
// update the average velocity of the target based on the position
_est_target_vel = _target_position_delta / (dt_ms / 1000.0f);
// if the target is moving add an offset and rotation
if (_est_target_vel.length() > .5F) {
_target_position_offset = _rot_matrix * _est_target_vel.normalized() * _follow_offset;
}
// are we within the target acceptance radius?
// give a buffer to exit/enter the radius to give the velocity controller
// a chance to catch up
_radius_exited = ((_target_position_offset + _target_distance).length() > (float) TARGET_ACCEPTANCE_RADIUS_M * 1.5f);
_radius_entered = ((_target_position_offset + _target_distance).length() < (float) TARGET_ACCEPTANCE_RADIUS_M);
// to keep the velocity increase/decrease smooth
// calculate how many velocity increments/decrements
// it will take to reach the targets velocity
// with the given amount of steps also add a feed forward input that adjusts the
// velocity as the position gap increases since
// just traveling at the exact velocity of the target will not
// get any closer or farther from the target
_step_vel = (_est_target_vel - _current_vel) + (_target_position_offset + _target_distance) * FF_K;
_step_vel /= (dt_ms / 1000.0F * (float) INTERPOLATION_PNTS);
_step_time_in_ms = (dt_ms / (float) INTERPOLATION_PNTS);
// if we are less than 1 meter from the target don't worry about trying to yaw
// lock the yaw until we are at a distance that makes sense
if ((_target_distance).length() > 1.0F) {
// yaw rate smoothing
// this really needs to control the yaw rate directly in the attitude pid controller
// but seems to work ok for now since the yaw rate cannot be controlled directly in auto mode
_yaw_angle = get_bearing_to_next_waypoint(_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_current_target_motion.lat,
_current_target_motion.lon);
_yaw_rate = (_yaw_angle - _navigator->get_global_position()->yaw) / (dt_ms / 1000.0F);
_yaw_rate = _wrap_pi(_yaw_rate);
_yaw_rate = math::constrain(_yaw_rate, -1.0F * _yaw_auto_max, _yaw_auto_max);
} else {
_yaw_angle = _yaw_rate = NAN;
}
}
// warnx(" _step_vel x %3.6f y %3.6f cur vel %3.6f %3.6f tar vel %3.6f %3.6f dist = %3.6f (%3.6f) mode = %d con ratio = %3.6f yaw rate = %3.6f",
// (double) _step_vel(0),
// (double) _step_vel(1),
// (double) _current_vel(0),
// (double) _current_vel(1),
// (double) _est_target_vel(0),
// (double) _est_target_vel(1),
// (double) (_target_distance).length(),
// (double) (_target_position_offset + _target_distance).length(),
// _follow_target_state,
// (double)_avg_cos_ratio, (double) _yaw_rate);
}
if (target_position_valid()) {
// get the target position using the calculated offset
map_projection_init(&target_ref, _current_target_motion.lat, _current_target_motion.lon);
map_projection_reproject(&target_ref, _target_position_offset(0), _target_position_offset(1),
&target_motion_with_offset.lat, &target_motion_with_offset.lon);
}
// clamp yaw rate smoothing if we are with in
// 3 degrees of facing target
if (PX4_ISFINITE(_yaw_rate)) {
if (fabsf(fabsf(_yaw_angle) - fabsf(_navigator->get_global_position()->yaw)) < math::radians(3.0F)) {
_yaw_rate = NAN;
}
}
// update state machine
switch (_follow_target_state) {
case TRACK_POSITION: {
if (_radius_entered == true) {
_follow_target_state = TRACK_VELOCITY;
} else if (target_velocity_valid()) {
set_follow_target_item(&_mission_item, _param_min_alt.get(), target_motion_with_offset, _yaw_angle);
// keep the current velocity updated with the target velocity for when it's needed
_current_vel = _est_target_vel;
update_position_sp(true, true, _yaw_rate);
} else {
_follow_target_state = SET_WAIT_FOR_TARGET_POSITION;
}
break;
}
case TRACK_VELOCITY: {
if (_radius_exited == true) {
_follow_target_state = TRACK_POSITION;
} else if (target_velocity_valid()) {
if ((float)(current_time - _last_update_time) / 1000.0f >= _step_time_in_ms) {
_current_vel += _step_vel;
_last_update_time = current_time;
}
set_follow_target_item(&_mission_item, _param_min_alt.get(), target_motion_with_offset, _yaw_angle);
update_position_sp(true, false, _yaw_rate);
} else {
_follow_target_state = SET_WAIT_FOR_TARGET_POSITION;
}
break;
}
case SET_WAIT_FOR_TARGET_POSITION: {
// Climb to the minimum altitude
// and wait until a position is received
follow_target_s target = {};
// for now set the target at the minimum height above the uav
target.lat = _navigator->get_global_position()->lat;
target.lon = _navigator->get_global_position()->lon;
target.alt = 0.0F;
set_follow_target_item(&_mission_item, _param_min_alt.get(), target, _yaw_angle);
update_position_sp(false, false, _yaw_rate);
_follow_target_state = WAIT_FOR_TARGET_POSITION;
}
/* FALLTHROUGH */
case WAIT_FOR_TARGET_POSITION: {
if (is_mission_item_reached() && target_velocity_valid()) {
_target_position_offset(0) = _follow_offset;
_follow_target_state = TRACK_POSITION;
}
break;
}
}
}
bool
MissionBlock::is_mission_item_reached()
{
/* handle non-navigation or indefinite waypoints */
switch (_mission_item.nav_cmd) {
case NAV_CMD_DO_SET_SERVO:
return true;
case NAV_CMD_LAND:
return _navigator->get_vstatus()->condition_landed;
/* TODO: count turns */
/*_mission_item.nav_cmd == NAV_CMD_LOITER_TURN_COUNT ||*/
case NAV_CMD_IDLE: /* fall through */
case NAV_CMD_LOITER_UNLIMITED:
return false;
case NAV_CMD_DO_DIGICAM_CONTROL:
case NAV_CMD_DO_SET_CAM_TRIGG_DIST:
return true;
case NAV_CMD_DO_VTOL_TRANSITION:
/*
* We wait half a second to give the transition command time to propagate.
* As soon as the timeout is over or when we're in transition mode let the mission continue.
*/
if (hrt_absolute_time() - _action_start > 500000 ||
_navigator->get_vstatus()->in_transition_mode) {
_action_start = 0;
return true;
} else {
return false;
}
case vehicle_command_s::VEHICLE_CMD_DO_CHANGE_SPEED:
// XXX not differentiating ground and airspeed yet
if (_mission_item.params[1] > 0.0f) {
_navigator->set_cruising_speed(_mission_item.params[1]);
} else {
_navigator->set_cruising_speed();
}
return true;
default:
/* do nothing, this is a 3D waypoint */
break;
}
hrt_abstime now = hrt_absolute_time();
if ((_navigator->get_vstatus()->condition_landed == false)
&& !_waypoint_position_reached) {
float dist = -1.0f;
float dist_xy = -1.0f;
float dist_z = -1.0f;
float altitude_amsl = _mission_item.altitude_is_relative
? _mission_item.altitude + _navigator->get_home_position()->alt
: _mission_item.altitude;
dist = get_distance_to_point_global_wgs84(_mission_item.lat, _mission_item.lon, altitude_amsl,
_navigator->get_global_position()->lat,
_navigator->get_global_position()->lon,
_navigator->get_global_position()->alt,
&dist_xy, &dist_z);
if (_mission_item.nav_cmd == NAV_CMD_TAKEOFF && _navigator->get_vstatus()->is_rotary_wing) {
/* require only altitude for takeoff for multicopter, do not use waypoint acceptance radius */
if (_navigator->get_global_position()->alt >
altitude_amsl - _navigator->get_acceptance_radius()) {
_waypoint_position_reached = true;
}
} else if (_mission_item.nav_cmd == NAV_CMD_TAKEOFF) {
/* for takeoff mission items use the parameter for the takeoff acceptance radius */
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius()) {
_waypoint_position_reached = true;
}
} else if (!_navigator->get_vstatus()->is_rotary_wing &&
(_mission_item.nav_cmd == NAV_CMD_LOITER_UNLIMITED ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TIME_LIMIT ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TURN_COUNT)) {
/* Loiter mission item on a non rotary wing: the aircraft is going to circle the
* coordinates with a radius equal to the loiter_radius field. It is not flying
* through the waypoint center.
* Therefore the item is marked as reached once the system reaches the loiter
* radius (+ some margin). Time inside and turn count is handled elsewhere.
*/
if (dist >= 0.0f && dist <= _navigator->get_acceptance_radius(_mission_item.loiter_radius * 1.2f)) {
_waypoint_position_reached = true;
}
} else {
/* for normal mission items used their acceptance radius */
float mission_acceptance_radius = _navigator->get_acceptance_radius(_mission_item.acceptance_radius);
/* if set to zero use the default instead */
if (mission_acceptance_radius < NAV_EPSILON_POSITION) {
mission_acceptance_radius = _navigator->get_acceptance_radius();
}
if (dist >= 0.0f && dist <= mission_acceptance_radius) {
_waypoint_position_reached = true;
}
}
if (_waypoint_position_reached) {
// reached just now
_time_wp_reached = now;
}
}
/* Check if the waypoint and the requested yaw setpoint. */
if (_waypoint_position_reached && !_waypoint_yaw_reached) {
/* TODO: removed takeoff, why? */
if (_navigator->get_vstatus()->is_rotary_wing && PX4_ISFINITE(_mission_item.yaw)) {
/* check yaw if defined only for rotary wing except takeoff */
float yaw_err = _wrap_pi(_mission_item.yaw - _navigator->get_global_position()->yaw);
/* accept yaw if reached or if timeout is set in which case we ignore not forced headings */
if (fabsf(yaw_err) < math::radians(_param_yaw_err.get())
|| (_param_yaw_timeout.get() >= FLT_EPSILON && !_mission_item.force_heading)) {
_waypoint_yaw_reached = true;
}
/* if heading needs to be reached, the timeout is enabled and we don't make it, abort mission */
if (!_waypoint_yaw_reached && _mission_item.force_heading &&
_param_yaw_timeout.get() >= FLT_EPSILON &&
now - _time_wp_reached >= (hrt_abstime)_param_yaw_timeout.get() * 1e6f) {
_navigator->set_mission_failure("unable to reach heading within timeout");
}
} else {
_waypoint_yaw_reached = true;
}
}
/* Once the waypoint and yaw setpoint have been reached we can start the loiter time countdown */
if (_waypoint_position_reached && _waypoint_yaw_reached) {
if (_time_first_inside_orbit == 0) {
_time_first_inside_orbit = now;
// if (_mission_item.time_inside > 0.01f) {
// mavlink_log_critical(_mavlink_log_pub, "waypoint reached, wait for %.1fs",
// (double)_mission_item.time_inside);
// }
}
/* check if the MAV was long enough inside the waypoint orbit */
if (now - _time_first_inside_orbit >= (hrt_abstime)_mission_item.time_inside * 1e6f) {
return true;
}
}
return false;
}
bool
Navigator::check_mission_item_reached()
{
/* only check if there is actually a mission item to check */
if (!_mission_item_valid) {
return false;
}
if (_mission_item.nav_cmd == NAV_CMD_LAND) {
return _vstatus.condition_landed;
}
/* XXX TODO count turns */
if ((_mission_item.nav_cmd == NAV_CMD_LOITER_TURN_COUNT ||
_mission_item.nav_cmd == NAV_CMD_LOITER_TIME_LIMIT ||
_mission_item.nav_cmd == NAV_CMD_LOITER_UNLIMITED) &&
_mission_item.loiter_radius > 0.01f) {
return false;
}
uint64_t now = hrt_absolute_time();
if (!_waypoint_position_reached) {
float acceptance_radius;
if (_mission_item.nav_cmd == NAV_CMD_WAYPOINT && _mission_item.acceptance_radius > 0.01f) {
acceptance_radius = _mission_item.acceptance_radius;
} else {
acceptance_radius = _parameters.acceptance_radius;
}
float dist = -1.0f;
float dist_xy = -1.0f;
float dist_z = -1.0f;
/* calculate AMSL altitude for this waypoint */
float wp_alt_amsl = _mission_item.altitude;
if (_mission_item.altitude_is_relative)
wp_alt_amsl += _home_pos.alt;
dist = get_distance_to_point_global_wgs84(_mission_item.lat, _mission_item.lon, wp_alt_amsl,
(double)_global_pos.lat, (double)_global_pos.lon, _global_pos.alt,
&dist_xy, &dist_z);
if (_do_takeoff) {
if (_global_pos.alt > wp_alt_amsl - acceptance_radius) {
/* require only altitude for takeoff */
_waypoint_position_reached = true;
}
} else {
if (dist >= 0.0f && dist <= acceptance_radius) {
_waypoint_position_reached = true;
}
}
}
if (_waypoint_position_reached && !_waypoint_yaw_reached) {
if (_vstatus.is_rotary_wing && !_do_takeoff && isfinite(_mission_item.yaw)) {
/* check yaw if defined only for rotary wing except takeoff */
float yaw_err = _wrap_pi(_mission_item.yaw - _global_pos.yaw);
if (fabsf(yaw_err) < 0.2f) { /* XXX get rid of magic number */
_waypoint_yaw_reached = true;
}
} else {
_waypoint_yaw_reached = true;
}
}
/* check if the current waypoint was reached */
if (_waypoint_position_reached && _waypoint_yaw_reached) {
if (_time_first_inside_orbit == 0) {
_time_first_inside_orbit = now;
if (_mission_item.time_inside > 0.01f) {
mavlink_log_info(_mavlink_fd, "#audio: waypoint reached, wait for %.1fs", (double)_mission_item.time_inside);
}
}
/* check if the MAV was long enough inside the waypoint orbit */
if ((now - _time_first_inside_orbit >= (uint64_t)_mission_item.time_inside * 1e6)
|| _mission_item.nav_cmd == NAV_CMD_TAKEOFF) {
reset_reached();
return true;
}
}
return false;
}
__EXPORT int get_distance_to_arc(struct crosstrack_error_s *crosstrack_error, double lat_now, double lon_now,
double lat_center, double lon_center,
float radius, float arc_start_bearing, float arc_sweep)
{
// This function returns the distance to the nearest point on the track arc. Distance is positive if current
// position is right of the arc and negative if left of the arc as seen from the closest point on the arc and
// headed towards the end point.
// Determine if the current position is inside or outside the sector between the line from the center
// to the arc start and the line from the center to the arc end
float bearing_sector_start;
float bearing_sector_end;
float bearing_now = get_bearing_to_next_waypoint(lat_now, lon_now, lat_center, lon_center);
bool in_sector;
int return_value = ERROR; // Set error flag, cleared when valid result calculated.
crosstrack_error->past_end = false;
crosstrack_error->distance = 0.0f;
crosstrack_error->bearing = 0.0f;
// Return error if arguments are bad
if (radius < 0.1f) { return return_value; }
if (arc_sweep >= 0.0f) {
bearing_sector_start = arc_start_bearing;
bearing_sector_end = arc_start_bearing + arc_sweep;
if (bearing_sector_end > 2.0f * M_PI_F) { bearing_sector_end -= M_TWOPI_F; }
} else {
bearing_sector_end = arc_start_bearing;
bearing_sector_start = arc_start_bearing - arc_sweep;
if (bearing_sector_start < 0.0f) { bearing_sector_start += M_TWOPI_F; }
}
in_sector = false;
// Case where sector does not span zero
if (bearing_sector_end >= bearing_sector_start && bearing_now >= bearing_sector_start
&& bearing_now <= bearing_sector_end) { in_sector = true; }
// Case where sector does span zero
if (bearing_sector_end < bearing_sector_start && (bearing_now > bearing_sector_start
|| bearing_now < bearing_sector_end)) { in_sector = true; }
// If in the sector then calculate distance and bearing to closest point
if (in_sector) {
crosstrack_error->past_end = false;
float dist_to_center = get_distance_to_next_waypoint(lat_now, lon_now, lat_center, lon_center);
if (dist_to_center <= radius) {
crosstrack_error->distance = radius - dist_to_center;
crosstrack_error->bearing = bearing_now + M_PI_F;
} else {
crosstrack_error->distance = dist_to_center - radius;
crosstrack_error->bearing = bearing_now;
}
// If out of the sector then calculate dist and bearing to start or end point
} else {
// Use the approximation that 111,111 meters in the y direction is 1 degree (of latitude)
// and 111,111 * cos(latitude) meters in the x direction is 1 degree (of longitude) to
// calculate the position of the start and end points. We should not be doing this often
// as this function generally will not be called repeatedly when we are out of the sector.
double start_disp_x = (double)radius * sin(arc_start_bearing);
double start_disp_y = (double)radius * cos(arc_start_bearing);
double end_disp_x = (double)radius * sin(_wrap_pi((double)(arc_start_bearing + arc_sweep)));
double end_disp_y = (double)radius * cos(_wrap_pi((double)(arc_start_bearing + arc_sweep)));
double lon_start = lon_now + start_disp_x / 111111.0;
double lat_start = lat_now + start_disp_y * cos(lat_now) / 111111.0;
double lon_end = lon_now + end_disp_x / 111111.0;
double lat_end = lat_now + end_disp_y * cos(lat_now) / 111111.0;
double dist_to_start = get_distance_to_next_waypoint(lat_now, lon_now, lat_start, lon_start);
double dist_to_end = get_distance_to_next_waypoint(lat_now, lon_now, lat_end, lon_end);
if (dist_to_start < dist_to_end) {
crosstrack_error->distance = dist_to_start;
crosstrack_error->bearing = get_bearing_to_next_waypoint(lat_now, lon_now, lat_start, lon_start);
} else {
crosstrack_error->past_end = true;
crosstrack_error->distance = dist_to_end;
crosstrack_error->bearing = get_bearing_to_next_waypoint(lat_now, lon_now, lat_end, lon_end);
}
}
crosstrack_error->bearing = _wrap_pi((double)crosstrack_error->bearing);
return_value = OK;
return return_value;
}
void Standard::update_mc_state()
{
VtolType::update_mc_state();
// enable MC motors here in case we transitioned directly to MC mode
if (_flag_enable_mc_motors) {
set_max_mc(2000);
set_idle_mc();
_flag_enable_mc_motors = false;
}
// if the thrust scale param is zero then the pusher-for-pitch strategy is disabled and we can return
if (_params_standard.forward_thrust_scale < FLT_EPSILON) {
return;
}
matrix::Dcmf R(matrix::Quatf(_v_att->q));
matrix::Dcmf R_sp(&_v_att_sp->R_body[0]);
matrix::Eulerf euler(R);
matrix::Eulerf euler_sp(R_sp);
_pusher_throttle = 0.0f;
// direction of desired body z axis represented in earth frame
matrix::Vector3f body_z_sp(R_sp(0, 2), R_sp(1, 2), R_sp(2, 2));
// rotate desired body z axis into new frame which is rotated in z by the current
// heading of the vehicle. we refer to this as the heading frame.
matrix::Dcmf R_yaw = matrix::Eulerf(0.0f, 0.0f, -euler(2));
body_z_sp = R_yaw * body_z_sp;
body_z_sp.normalize();
// calculate the desired pitch seen in the heading frame
// this value corresponds to the amount the vehicle would try to pitch forward
float pitch_forward = asinf(body_z_sp(0));
// only allow pitching forward up to threshold, the rest of the desired
// forward acceleration will be compensated by the pusher
if (pitch_forward < -_params_standard.down_pitch_max) {
// desired roll angle in heading frame stays the same
float roll_new = -atan2f(body_z_sp(1), body_z_sp(2));
_pusher_throttle = (sinf(-pitch_forward) - sinf(_params_standard.down_pitch_max))
* _v_att_sp->thrust * _params_standard.forward_thrust_scale;
// limit desired pitch
float pitch_new = -_params_standard.down_pitch_max;
// create corrected desired body z axis in heading frame
matrix::Dcmf R_tmp = matrix::Eulerf(roll_new, pitch_new, 0.0f);
matrix::Vector3f tilt_new(R_tmp(0, 2), R_tmp(1, 2), R_tmp(2, 2));
// rotate the vector into a new frame which is rotated in z by the desired heading
// with respect to the earh frame.
float yaw_error = _wrap_pi(euler_sp(2) - euler(2));
matrix::Dcmf R_yaw_correction = matrix::Eulerf(0.0f, 0.0f, -yaw_error);
tilt_new = R_yaw_correction * tilt_new;
// now extract roll and pitch setpoints
float pitch = asinf(tilt_new(0));
float roll = -atan2f(tilt_new(1), tilt_new(2));
R_sp = matrix::Eulerf(roll, pitch, euler_sp(2));
matrix::Quatf q_sp(R_sp);
memcpy(&_v_att_sp->R_body[0], &R_sp._data[0], sizeof(_v_att_sp->R_body));
memcpy(&_v_att_sp->q_d[0], &q_sp._data[0], sizeof(_v_att_sp->q_d));
}
_pusher_throttle = _pusher_throttle < 0.0f ? 0.0f : _pusher_throttle;
}
void
BottleDrop::task_main()
{
_mavlink_fd = open(MAVLINK_LOG_DEVICE, 0);
mavlink_log_info(_mavlink_fd, "[bottle_drop] started");
_command_sub = orb_subscribe(ORB_ID(vehicle_command));
_wind_estimate_sub = orb_subscribe(ORB_ID(wind_estimate));
bool updated = false;
float z_0; // ground properties
float turn_radius; // turn radius of the UAV
float precision; // Expected precision of the UAV
float ground_distance = _alt_clearance; // Replace by closer estimate in loop
// constant
float g = CONSTANTS_ONE_G; // constant of gravity [m/s^2]
float m = 0.5f; // mass of bottle [kg]
float rho = 1.2f; // air density [kg/m^3]
float A = ((0.063f * 0.063f) / 4.0f * M_PI_F); // Bottle cross section [m^2]
float dt_freefall_prediction = 0.01f; // step size of the free fall prediction [s]
// Has to be estimated by experiment
float cd = 0.86f; // Drag coefficient for a cylinder with a d/l ratio of 1/3 []
float t_signal =
0.084f; // Time span between sending the signal and the bottle top reaching level height with the bottom of the plane [s]
float t_door =
0.7f; // The time the system needs to open the door + safety, is also the time the palyload needs to safely escape the shaft [s]
// Definition
float h_0; // height over target
float az; // acceleration in z direction[m/s^2]
float vz; // velocity in z direction [m/s]
float z; // fallen distance [m]
float h; // height over target [m]
float ax; // acceleration in x direction [m/s^2]
float vx; // ground speed in x direction [m/s]
float x; // traveled distance in x direction [m]
float vw; // wind speed [m/s]
float vrx; // relative velocity in x direction [m/s]
float v; // relative speed vector [m/s]
float Fd; // Drag force [N]
float Fdx; // Drag force in x direction [N]
float Fdz; // Drag force in z direction [N]
float x_drop, y_drop; // coordinates of the drop point in reference to the target (projection of NED)
float x_t, y_t; // coordinates of the target in reference to the target x_t = 0, y_t = 0 (projection of NED)
float x_l, y_l; // local position in projected coordinates
float x_f, y_f; // to-be position of the UAV after dt_runs seconds in projected coordinates
double x_f_NED, y_f_NED; // to-be position of the UAV after dt_runs seconds in NED
float distance_open_door; // The distance the UAV travels during its doors open [m]
float approach_error = 0.0f; // The error in radians between current ground vector and desired ground vector
float distance_real = 0; // The distance between the UAVs position and the drop point [m]
float future_distance = 0; // The distance between the UAVs to-be position and the drop point [m]
unsigned counter = 0;
param_t param_gproperties = param_find("BD_GPROPERTIES");
param_t param_turn_radius = param_find("BD_TURNRADIUS");
param_t param_precision = param_find("BD_PRECISION");
param_t param_cd = param_find("BD_OBJ_CD");
param_t param_mass = param_find("BD_OBJ_MASS");
param_t param_surface = param_find("BD_OBJ_SURFACE");
param_get(param_precision, &precision);
param_get(param_turn_radius, &turn_radius);
param_get(param_gproperties, &z_0);
param_get(param_cd, &cd);
param_get(param_mass, &m);
param_get(param_surface, &A);
int vehicle_global_position_sub = orb_subscribe(ORB_ID(vehicle_global_position));
struct parameter_update_s update;
memset(&update, 0, sizeof(update));
int parameter_update_sub = orb_subscribe(ORB_ID(parameter_update));
struct mission_item_s flight_vector_s {};
struct mission_item_s flight_vector_e {};
flight_vector_s.nav_cmd = NAV_CMD_WAYPOINT;
flight_vector_s.acceptance_radius = 50; // TODO: make parameter
flight_vector_s.autocontinue = true;
flight_vector_s.altitude_is_relative = false;
flight_vector_e.nav_cmd = NAV_CMD_WAYPOINT;
flight_vector_e.acceptance_radius = 50; // TODO: make parameter
flight_vector_e.autocontinue = true;
flight_vector_s.altitude_is_relative = false;
struct wind_estimate_s wind;
// wakeup source(s)
struct pollfd fds[1];
// Setup of loop
fds[0].fd = _command_sub;
fds[0].events = POLLIN;
// Whatever state the bay is in, we want it closed on startup
lock_release();
close_bay();
while (!_task_should_exit) {
/* wait for up to 100ms for data */
int pret = poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 50);
/* this is undesirable but not much we can do - might want to flag unhappy status */
if (pret < 0) {
warn("poll error %d, %d", pret, errno);
continue;
}
/* vehicle commands updated */
if (fds[0].revents & POLLIN) {
orb_copy(ORB_ID(vehicle_command), _command_sub, &_command);
handle_command(&_command);
}
orb_check(vehicle_global_position_sub, &updated);
if (updated) {
/* copy global position */
orb_copy(ORB_ID(vehicle_global_position), vehicle_global_position_sub, &_global_pos);
}
if (_global_pos.timestamp == 0) {
continue;
}
const unsigned sleeptime_us = 9500;
hrt_abstime last_run = hrt_absolute_time();
float dt_runs = sleeptime_us / 1e6f;
// switch to faster updates during the drop
while (_drop_state > DROP_STATE_INIT) {
// Get wind estimate
orb_check(_wind_estimate_sub, &updated);
if (updated) {
orb_copy(ORB_ID(wind_estimate), _wind_estimate_sub, &wind);
}
// Get vehicle position
orb_check(vehicle_global_position_sub, &updated);
if (updated) {
// copy global position
orb_copy(ORB_ID(vehicle_global_position), vehicle_global_position_sub, &_global_pos);
}
// Get parameter updates
orb_check(parameter_update_sub, &updated);
if (updated) {
// copy global position
orb_copy(ORB_ID(parameter_update), parameter_update_sub, &update);
// update all parameters
param_get(param_gproperties, &z_0);
param_get(param_turn_radius, &turn_radius);
param_get(param_precision, &precision);
}
orb_check(_command_sub, &updated);
if (updated) {
orb_copy(ORB_ID(vehicle_command), _command_sub, &_command);
handle_command(&_command);
}
float windspeed_norm = sqrtf(wind.windspeed_north * wind.windspeed_north + wind.windspeed_east * wind.windspeed_east);
float groundspeed_body = sqrtf(_global_pos.vel_n * _global_pos.vel_n + _global_pos.vel_e * _global_pos.vel_e);
ground_distance = _global_pos.alt - _target_position.alt;
// Distance to drop position and angle error to approach vector
// are relevant in all states greater than target valid (which calculates these positions)
if (_drop_state > DROP_STATE_TARGET_VALID) {
distance_real = fabsf(get_distance_to_next_waypoint(_global_pos.lat, _global_pos.lon, _drop_position.lat, _drop_position.lon));
float ground_direction = atan2f(_global_pos.vel_e, _global_pos.vel_n);
float approach_direction = get_bearing_to_next_waypoint(flight_vector_s.lat, flight_vector_s.lon, flight_vector_e.lat, flight_vector_e.lon);
approach_error = _wrap_pi(ground_direction - approach_direction);
if (counter % 90 == 0) {
mavlink_log_info(_mavlink_fd, "drop distance %u, heading error %u", (unsigned)distance_real, (unsigned)math::degrees(approach_error));
}
}
switch (_drop_state) {
case DROP_STATE_INIT:
// do nothing
break;
case DROP_STATE_TARGET_VALID:
{
az = g; // acceleration in z direction[m/s^2]
vz = 0; // velocity in z direction [m/s]
z = 0; // fallen distance [m]
h_0 = _global_pos.alt - _target_position.alt; // height over target at start[m]
h = h_0; // height over target [m]
ax = 0; // acceleration in x direction [m/s^2]
vx = groundspeed_body;// XXX project // ground speed in x direction [m/s]
x = 0; // traveled distance in x direction [m]
vw = 0; // wind speed [m/s]
vrx = 0; // relative velocity in x direction [m/s]
v = groundspeed_body; // relative speed vector [m/s]
Fd = 0; // Drag force [N]
Fdx = 0; // Drag force in x direction [N]
Fdz = 0; // Drag force in z direction [N]
// Compute the distance the bottle will travel after it is dropped in body frame coordinates --> x
while (h > 0.05f) {
// z-direction
vz = vz + az * dt_freefall_prediction;
z = z + vz * dt_freefall_prediction;
h = h_0 - z;
// x-direction
vw = windspeed_norm * logf(h / z_0) / logf(ground_distance / z_0);
vx = vx + ax * dt_freefall_prediction;
x = x + vx * dt_freefall_prediction;
vrx = vx + vw;
// drag force
v = sqrtf(vz * vz + vrx * vrx);
Fd = 0.5f * rho * A * cd * (v * v);
Fdx = Fd * vrx / v;
Fdz = Fd * vz / v;
// acceleration
az = g - Fdz / m;
ax = -Fdx / m;
}
// compute drop vector
x = groundspeed_body * t_signal + x;
x_t = 0.0f;
y_t = 0.0f;
float wind_direction_n, wind_direction_e;
if (windspeed_norm < 0.5f) { // If there is no wind, an arbitrarily direction is chosen
wind_direction_n = 1.0f;
wind_direction_e = 0.0f;
} else {
wind_direction_n = wind.windspeed_north / windspeed_norm;
wind_direction_e = wind.windspeed_east / windspeed_norm;
}
x_drop = x_t + x * wind_direction_n;
y_drop = y_t + x * wind_direction_e;
map_projection_reproject(&ref, x_drop, y_drop, &_drop_position.lat, &_drop_position.lon);
_drop_position.alt = _target_position.alt + _alt_clearance;
// Compute flight vector
map_projection_reproject(&ref, x_drop + 2 * turn_radius * wind_direction_n, y_drop + 2 * turn_radius * wind_direction_e,
&(flight_vector_s.lat), &(flight_vector_s.lon));
flight_vector_s.altitude = _drop_position.alt;
map_projection_reproject(&ref, x_drop - turn_radius * wind_direction_n, y_drop - turn_radius * wind_direction_e,
&flight_vector_e.lat, &flight_vector_e.lon);
flight_vector_e.altitude = _drop_position.alt;
// Save WPs in datamanager
const ssize_t len = sizeof(struct mission_item_s);
if (dm_write(DM_KEY_WAYPOINTS_ONBOARD, 0, DM_PERSIST_IN_FLIGHT_RESET, &flight_vector_s, len) != len) {
warnx("ERROR: could not save onboard WP");
}
if (dm_write(DM_KEY_WAYPOINTS_ONBOARD, 1, DM_PERSIST_IN_FLIGHT_RESET, &flight_vector_e, len) != len) {
warnx("ERROR: could not save onboard WP");
}
_onboard_mission.count = 2;
_onboard_mission.current_seq = 0;
if (_onboard_mission_pub > 0) {
orb_publish(ORB_ID(onboard_mission), _onboard_mission_pub, &_onboard_mission);
} else {
_onboard_mission_pub = orb_advertise(ORB_ID(onboard_mission), &_onboard_mission);
}
float approach_direction = get_bearing_to_next_waypoint(flight_vector_s.lat, flight_vector_s.lon, flight_vector_e.lat, flight_vector_e.lon);
mavlink_log_critical(_mavlink_fd, "position set, approach heading: %u", (unsigned)distance_real, (unsigned)math::degrees(approach_direction + M_PI_F));
_drop_state = DROP_STATE_TARGET_SET;
}
break;
case DROP_STATE_TARGET_SET:
{
float distance_wp2 = get_distance_to_next_waypoint(_global_pos.lat, _global_pos.lon, flight_vector_e.lat, flight_vector_e.lon);
if (distance_wp2 < distance_real) {
_onboard_mission.current_seq = 0;
orb_publish(ORB_ID(onboard_mission), _onboard_mission_pub, &_onboard_mission);
} else {
// We're close enough - open the bay
distance_open_door = math::max(10.0f, 3.0f * fabsf(t_door * groundspeed_body));
if (isfinite(distance_real) && distance_real < distance_open_door &&
fabsf(approach_error) < math::radians(20.0f)) {
open_bay();
_drop_state = DROP_STATE_BAY_OPEN;
mavlink_log_info(_mavlink_fd, "#audio: opening bay");
}
}
}
break;
case DROP_STATE_BAY_OPEN:
{
if (_drop_approval) {
map_projection_project(&ref, _global_pos.lat, _global_pos.lon, &x_l, &y_l);
x_f = x_l + _global_pos.vel_n * dt_runs;
y_f = y_l + _global_pos.vel_e * dt_runs;
map_projection_reproject(&ref, x_f, y_f, &x_f_NED, &y_f_NED);
future_distance = get_distance_to_next_waypoint(x_f_NED, y_f_NED, _drop_position.lat, _drop_position.lon);
if (isfinite(distance_real) &&
(distance_real < precision) && ((distance_real < future_distance))) {
drop();
_drop_state = DROP_STATE_DROPPED;
mavlink_log_info(_mavlink_fd, "#audio: payload dropped");
} else {
float distance_wp2 = get_distance_to_next_waypoint(_global_pos.lat, _global_pos.lon, flight_vector_e.lat, flight_vector_e.lon);
if (distance_wp2 < distance_real) {
_onboard_mission.current_seq = 0;
orb_publish(ORB_ID(onboard_mission), _onboard_mission_pub, &_onboard_mission);
}
}
}
}
break;
case DROP_STATE_DROPPED:
/* 2s after drop, reset and close everything again */
if ((hrt_elapsed_time(&_doors_opened) > 2 * 1000 * 1000)) {
_drop_state = DROP_STATE_INIT;
_drop_approval = false;
lock_release();
close_bay();
mavlink_log_info(_mavlink_fd, "#audio: closing bay");
// remove onboard mission
_onboard_mission.current_seq = -1;
_onboard_mission.count = 0;
orb_publish(ORB_ID(onboard_mission), _onboard_mission_pub, &_onboard_mission);
}
break;
case DROP_STATE_BAY_CLOSED:
// do nothing
break;
}
counter++;
// update_actuators();
// run at roughly 100 Hz
usleep(sleeptime_us);
dt_runs = hrt_elapsed_time(&last_run) / 1e6f;
last_run = hrt_absolute_time();
}
}
warnx("exiting.");
_main_task = -1;
_exit(0);
}
void
Mission::heading_sp_update()
{
/* we don't want to be yawing during takeoff, landing or aligning for a transition */
if (_mission_item.nav_cmd == NAV_CMD_TAKEOFF
|| _mission_item.nav_cmd == NAV_CMD_VTOL_TAKEOFF
|| _mission_item.nav_cmd == NAV_CMD_DO_VTOL_TRANSITION
|| _mission_item.nav_cmd == NAV_CMD_LAND
|| _mission_item.nav_cmd == NAV_CMD_VTOL_LAND
|| _work_item_type == WORK_ITEM_TYPE_ALIGN) {
return;
}
struct position_setpoint_triplet_s *pos_sp_triplet = _navigator->get_position_setpoint_triplet();
/* Don't change setpoint if last and current waypoint are not valid */
if (!pos_sp_triplet->previous.valid || !pos_sp_triplet->current.valid) {
return;
}
/* set yaw angle for the waypoint if a loiter time has been specified */
if (_waypoint_position_reached && _mission_item.time_inside > 0.0f) {
// XXX: should actually be param4 from mission item
// at the moment it will just keep the heading it has
//_mission_item.yaw = _on_arrival_yaw;
//pos_sp_triplet->current.yaw = _mission_item.yaw;
} else {
/* Calculate direction the vehicle should point to. */
double point_from_latlon[2];
double point_to_latlon[2];
point_from_latlon[0] = _navigator->get_global_position()->lat;
point_from_latlon[1] = _navigator->get_global_position()->lon;
/* target location is home */
if ((_param_yawmode.get() == MISSION_YAWMODE_FRONT_TO_HOME
|| _param_yawmode.get() == MISSION_YAWMODE_BACK_TO_HOME)
// need to be rotary wing for this but not in a transition
// in VTOL mode this will prevent updating yaw during FW flight
// (which would result in a wrong yaw setpoint spike during back transition)
&& _navigator->get_vstatus()->is_rotary_wing
&& !(_mission_item.nav_cmd == NAV_CMD_DO_VTOL_TRANSITION || _navigator->get_vstatus()->in_transition_mode)) {
point_to_latlon[0] = _navigator->get_home_position()->lat;
point_to_latlon[1] = _navigator->get_home_position()->lon;
/* target location is next (current) waypoint */
} else {
point_to_latlon[0] = pos_sp_triplet->current.lat;
point_to_latlon[1] = pos_sp_triplet->current.lon;
}
float d_current = get_distance_to_next_waypoint(
point_from_latlon[0], point_from_latlon[1],
point_to_latlon[0], point_to_latlon[1]);
/* stop if positions are close together to prevent excessive yawing */
if (d_current > _navigator->get_acceptance_radius()) {
float yaw = get_bearing_to_next_waypoint(
point_from_latlon[0],
point_from_latlon[1],
point_to_latlon[0],
point_to_latlon[1]);
/* always keep the back of the rotary wing pointing towards home */
if (_param_yawmode.get() == MISSION_YAWMODE_BACK_TO_HOME) {
_mission_item.yaw = _wrap_pi(yaw + M_PI_F);
pos_sp_triplet->current.yaw = _mission_item.yaw;
} else {
_mission_item.yaw = yaw;
pos_sp_triplet->current.yaw = _mission_item.yaw;
}
}
}
// we set yaw directly so we can run this in parallel to the FOH update
_navigator->set_position_setpoint_triplet_updated();
}
