コード例 #1
0
void
FixedwingAttitudeControl::task_main()
{
	/*
	 * do subscriptions
	 */
	_att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
	_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
	_vcontrol_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));
	_global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
	_vehicle_status_sub = orb_subscribe(ORB_ID(vehicle_status));
	_vehicle_land_detected_sub = orb_subscribe(ORB_ID(vehicle_land_detected));
	_battery_status_sub = orb_subscribe(ORB_ID(battery_status));

	parameters_update();

	/* get an initial update for all sensor and status data */
	vehicle_setpoint_poll();
	vehicle_control_mode_poll();
	vehicle_manual_poll();
	vehicle_status_poll();
	vehicle_land_detected_poll();
	battery_status_poll();
	_sub_airspeed.update();

	/* wakeup source */
	px4_pollfd_struct_t fds[1];

	/* Setup of loop */
	fds[0].fd = _att_sub;
	fds[0].events = POLLIN;

	_task_running = true;

	while (!_task_should_exit) {
		static int loop_counter = 0;

		/* wait for up to 500ms for data */
		int pret = px4_poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 100);

		/* timed out - periodic check for _task_should_exit, etc. */
		if (pret == 0) {
			continue;
		}

		/* this is undesirable but not much we can do - might want to flag unhappy status */
		if (pret < 0) {
			PX4_WARN("poll error %d, %d", pret, errno);
			continue;
		}

		perf_begin(_loop_perf);

		/* only update parameters if they changed */
		bool params_updated = false;
		orb_check(_params_sub, &params_updated);

		if (params_updated) {
			/* read from param to clear updated flag */
			parameter_update_s update;
			orb_copy(ORB_ID(parameter_update), _params_sub, &update);

			/* update parameters from storage */
			parameters_update();
		}

		/* only run controller if attitude changed */
		if (fds[0].revents & POLLIN) {
			static uint64_t last_run = 0;
			float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
			last_run = hrt_absolute_time();

			/* guard against too large deltaT's */
			if (deltaT > 1.0f) {
				deltaT = 0.01f;
			}

			/* load local copies */
			orb_copy(ORB_ID(vehicle_attitude), _att_sub, &_att);

			/* get current rotation matrix and euler angles from control state quaternions */
			math::Quaternion q_att(_att.q[0], _att.q[1], _att.q[2], _att.q[3]);
			_R = q_att.to_dcm();

			math::Vector<3> euler_angles;
			euler_angles = _R.to_euler();
			_roll    = euler_angles(0);
			_pitch   = euler_angles(1);
			_yaw     = euler_angles(2);

			if (_vehicle_status.is_vtol && _parameters.vtol_type == vtol_type::TAILSITTER) {
				/* vehicle is a tailsitter, we need to modify the estimated attitude for fw mode
				 *
				 * Since the VTOL airframe is initialized as a multicopter we need to
				 * modify the estimated attitude for the fixed wing operation.
				 * Since the neutral position of the vehicle in fixed wing mode is -90 degrees rotated around
				 * the pitch axis compared to the neutral position of the vehicle in multicopter mode
				 * we need to swap the roll and the yaw axis (1st and 3rd column) in the rotation matrix.
				 * Additionally, in order to get the correct sign of the pitch, we need to multiply
				 * the new x axis of the rotation matrix with -1
				 *
				 * original:			modified:
				 *
				 * Rxx  Ryx  Rzx		-Rzx  Ryx  Rxx
				 * Rxy	Ryy  Rzy		-Rzy  Ryy  Rxy
				 * Rxz	Ryz  Rzz		-Rzz  Ryz  Rxz
				 * */
				math::Matrix<3, 3> R_adapted = _R;		//modified rotation matrix

				/* move z to x */
				R_adapted(0, 0) = _R(0, 2);
				R_adapted(1, 0) = _R(1, 2);
				R_adapted(2, 0) = _R(2, 2);

				/* move x to z */
				R_adapted(0, 2) = _R(0, 0);
				R_adapted(1, 2) = _R(1, 0);
				R_adapted(2, 2) = _R(2, 0);

				/* change direction of pitch (convert to right handed system) */
				R_adapted(0, 0) = -R_adapted(0, 0);
				R_adapted(1, 0) = -R_adapted(1, 0);
				R_adapted(2, 0) = -R_adapted(2, 0);
				euler_angles = R_adapted.to_euler();  //adapted euler angles for fixed wing operation

				/* fill in new attitude data */
				_R = R_adapted;
				_roll    = euler_angles(0);
				_pitch   = euler_angles(1);
				_yaw     = euler_angles(2);

				/* lastly, roll- and yawspeed have to be swaped */
				float helper = _att.rollspeed;
				_att.rollspeed = -_att.yawspeed;
				_att.yawspeed = helper;
			}

			_sub_airspeed.update();
			vehicle_setpoint_poll();
			vehicle_control_mode_poll();
			vehicle_manual_poll();
			global_pos_poll();
			vehicle_status_poll();
			vehicle_land_detected_poll();
			battery_status_poll();

			// the position controller will not emit attitude setpoints in some modes
			// we need to make sure that this flag is reset
			_att_sp.fw_control_yaw = _att_sp.fw_control_yaw && _vcontrol_mode.flag_control_auto_enabled;

			/* lock integrator until control is started */
			bool lock_integrator = !(_vcontrol_mode.flag_control_rates_enabled && !_vehicle_status.is_rotary_wing);

			/* Simple handling of failsafe: deploy parachute if failsafe is on */
			if (_vcontrol_mode.flag_control_termination_enabled) {
				_actuators_airframe.control[7] = 1.0f;
				//warnx("_actuators_airframe.control[1] = 1.0f;");

			} else {
				_actuators_airframe.control[7] = 0.0f;
				//warnx("_actuators_airframe.control[1] = -1.0f;");
			}

			/* if we are in rotary wing mode, do nothing */
			if (_vehicle_status.is_rotary_wing && !_vehicle_status.is_vtol) {
				continue;
			}

			/* default flaps to center */
			float flap_control = 0.0f;

			/* map flaps by default to manual if valid */
			if (PX4_ISFINITE(_manual.flaps) && _vcontrol_mode.flag_control_manual_enabled
			    && fabsf(_parameters.flaps_scale) > 0.01f) {
				flap_control = 0.5f * (_manual.flaps + 1.0f) * _parameters.flaps_scale;

			} else if (_vcontrol_mode.flag_control_auto_enabled
				   && fabsf(_parameters.flaps_scale) > 0.01f) {
				flap_control = _att_sp.apply_flaps ? 1.0f * _parameters.flaps_scale : 0.0f;
			}

			// move the actual control value continuous with time, full flap travel in 1sec
			if (fabsf(_flaps_applied - flap_control) > 0.01f) {
				_flaps_applied += (_flaps_applied - flap_control) < 0 ? deltaT : -deltaT;

			} else {
				_flaps_applied = flap_control;
			}

			/* default flaperon to center */
			float flaperon_control = 0.0f;

			/* map flaperons by default to manual if valid */
			if (PX4_ISFINITE(_manual.aux2) && _vcontrol_mode.flag_control_manual_enabled
			    && fabsf(_parameters.flaperon_scale) > 0.01f) {
				flaperon_control = 0.5f * (_manual.aux2 + 1.0f) * _parameters.flaperon_scale;

			} else if (_vcontrol_mode.flag_control_auto_enabled
				   && fabsf(_parameters.flaperon_scale) > 0.01f) {
				flaperon_control = _att_sp.apply_flaps ? 1.0f * _parameters.flaperon_scale : 0.0f;
			}

			// move the actual control value continuous with time, full flap travel in 1sec
			if (fabsf(_flaperons_applied - flaperon_control) > 0.01f) {
				_flaperons_applied += (_flaperons_applied - flaperon_control) < 0 ? deltaT : -deltaT;

			} else {
				_flaperons_applied = flaperon_control;
			}

			// Check if we are in rattitude mode and the pilot is above the threshold on pitch
			if (_vcontrol_mode.flag_control_rattitude_enabled) {
				if (fabsf(_manual.y) > _parameters.rattitude_thres ||
				    fabsf(_manual.x) > _parameters.rattitude_thres) {
					_vcontrol_mode.flag_control_attitude_enabled = false;
				}
			}

			/* decide if in stabilized or full manual control */
			if (_vcontrol_mode.flag_control_rates_enabled) {
				/* scale around tuning airspeed */
				float airspeed;

				/* if airspeed is non-finite or not valid or if we are asked not to control it, we assume the normal average speed */
				const bool airspeed_valid = PX4_ISFINITE(_sub_airspeed.get().indicated_airspeed_m_s)
							    && ((_sub_airspeed.get().timestamp - hrt_absolute_time()) < 1e6);

				if (airspeed_valid) {
					/* prevent numerical drama by requiring 0.5 m/s minimal speed */
					airspeed = math::max(0.5f, _sub_airspeed.get().indicated_airspeed_m_s);

				} else {
					airspeed = _parameters.airspeed_trim;
					perf_count(_nonfinite_input_perf);
				}

				/*
				 * For scaling our actuators using anything less than the min (close to stall)
				 * speed doesn't make any sense - its the strongest reasonable deflection we
				 * want to do in flight and its the baseline a human pilot would choose.
				 *
				 * Forcing the scaling to this value allows reasonable handheld tests.
				 */
				float airspeed_scaling = _parameters.airspeed_trim / ((airspeed < _parameters.airspeed_min) ? _parameters.airspeed_min :
							 airspeed);

				/* Use min airspeed to calculate ground speed scaling region.
				 * Don't scale below gspd_scaling_trim
				 */
				float groundspeed = sqrtf(_global_pos.vel_n * _global_pos.vel_n +
							  _global_pos.vel_e * _global_pos.vel_e);
				float gspd_scaling_trim = (_parameters.airspeed_min * 0.6f);
				float groundspeed_scaler = gspd_scaling_trim / ((groundspeed < gspd_scaling_trim) ? gspd_scaling_trim : groundspeed);

				// in STABILIZED mode we need to generate the attitude setpoint
				// from manual user inputs
				if (!_vcontrol_mode.flag_control_climb_rate_enabled && !_vcontrol_mode.flag_control_offboard_enabled) {
					_att_sp.timestamp = hrt_absolute_time();
					_att_sp.roll_body = _manual.y * _parameters.man_roll_max + _parameters.rollsp_offset_rad;
					_att_sp.roll_body = math::constrain(_att_sp.roll_body, -_parameters.man_roll_max, _parameters.man_roll_max);
					_att_sp.pitch_body = -_manual.x * _parameters.man_pitch_max + _parameters.pitchsp_offset_rad;
					_att_sp.pitch_body = math::constrain(_att_sp.pitch_body, -_parameters.man_pitch_max, _parameters.man_pitch_max);
					_att_sp.yaw_body = 0.0f;
					_att_sp.thrust = _manual.z;

					Quatf q(Eulerf(_att_sp.roll_body, _att_sp.pitch_body, _att_sp.yaw_body));
					q.copyTo(_att_sp.q_d);
					_att_sp.q_d_valid = true;

					int instance;
					orb_publish_auto(_attitude_setpoint_id, &_attitude_sp_pub, &_att_sp, &instance, ORB_PRIO_DEFAULT);
				}

				/* reset integrals where needed */
				if (_att_sp.roll_reset_integral) {
					_roll_ctrl.reset_integrator();
				}

				if (_att_sp.pitch_reset_integral) {
					_pitch_ctrl.reset_integrator();
				}

				if (_att_sp.yaw_reset_integral) {
					_yaw_ctrl.reset_integrator();
					_wheel_ctrl.reset_integrator();
				}

				/* Reset integrators if the aircraft is on ground
				 * or a multicopter (but not transitioning VTOL)
				 */
				if (_vehicle_land_detected.landed
				    || (_vehicle_status.is_rotary_wing && !_vehicle_status.in_transition_mode)) {

					_roll_ctrl.reset_integrator();
					_pitch_ctrl.reset_integrator();
					_yaw_ctrl.reset_integrator();
					_wheel_ctrl.reset_integrator();
				}

				float roll_sp = _att_sp.roll_body;
				float pitch_sp = _att_sp.pitch_body;
				float yaw_sp = _att_sp.yaw_body;
				float throttle_sp = _att_sp.thrust;

				/* Prepare data for attitude controllers */
				struct ECL_ControlData control_input = {};
				control_input.roll = _roll;
				control_input.pitch = _pitch;
				control_input.yaw = _yaw;
				control_input.body_x_rate = _att.rollspeed;
				control_input.body_y_rate = _att.pitchspeed;
				control_input.body_z_rate = _att.yawspeed;
				control_input.roll_setpoint = roll_sp;
				control_input.pitch_setpoint = pitch_sp;
				control_input.yaw_setpoint = yaw_sp;
				control_input.airspeed_min = _parameters.airspeed_min;
				control_input.airspeed_max = _parameters.airspeed_max;
				control_input.airspeed = airspeed;
				control_input.scaler = airspeed_scaling;
				control_input.lock_integrator = lock_integrator;
				control_input.groundspeed = groundspeed;
				control_input.groundspeed_scaler = groundspeed_scaler;

				/* Run attitude controllers */
				if (_vcontrol_mode.flag_control_attitude_enabled) {
					if (PX4_ISFINITE(roll_sp) && PX4_ISFINITE(pitch_sp)) {
						_roll_ctrl.control_attitude(control_input);
						_pitch_ctrl.control_attitude(control_input);
						_yaw_ctrl.control_attitude(control_input); //runs last, because is depending on output of roll and pitch attitude
						_wheel_ctrl.control_attitude(control_input);

						/* Update input data for rate controllers */
						control_input.roll_rate_setpoint = _roll_ctrl.get_desired_rate();
						control_input.pitch_rate_setpoint = _pitch_ctrl.get_desired_rate();
						control_input.yaw_rate_setpoint = _yaw_ctrl.get_desired_rate();

						/* Run attitude RATE controllers which need the desired attitudes from above, add trim */
						float roll_u = _roll_ctrl.control_euler_rate(control_input);
						_actuators.control[actuator_controls_s::INDEX_ROLL] = (PX4_ISFINITE(roll_u)) ? roll_u + _parameters.trim_roll :
								_parameters.trim_roll;

						if (!PX4_ISFINITE(roll_u)) {
							_roll_ctrl.reset_integrator();
							perf_count(_nonfinite_output_perf);

							if (_debug && loop_counter % 10 == 0) {
								warnx("roll_u %.4f", (double)roll_u);
							}
						}

						float pitch_u = _pitch_ctrl.control_euler_rate(control_input);
						_actuators.control[actuator_controls_s::INDEX_PITCH] = (PX4_ISFINITE(pitch_u)) ? pitch_u + _parameters.trim_pitch :
								_parameters.trim_pitch;

						if (!PX4_ISFINITE(pitch_u)) {
							_pitch_ctrl.reset_integrator();
							perf_count(_nonfinite_output_perf);

							if (_debug && loop_counter % 10 == 0) {
								warnx("pitch_u %.4f, _yaw_ctrl.get_desired_rate() %.4f,"
								      " airspeed %.4f, airspeed_scaling %.4f,"
								      " roll_sp %.4f, pitch_sp %.4f,"
								      " _roll_ctrl.get_desired_rate() %.4f,"
								      " _pitch_ctrl.get_desired_rate() %.4f"
								      " att_sp.roll_body %.4f",
								      (double)pitch_u, (double)_yaw_ctrl.get_desired_rate(),
								      (double)airspeed, (double)airspeed_scaling,
								      (double)roll_sp, (double)pitch_sp,
								      (double)_roll_ctrl.get_desired_rate(),
								      (double)_pitch_ctrl.get_desired_rate(),
								      (double)_att_sp.roll_body);
							}
						}

						float yaw_u = 0.0f;

						if (_parameters.w_en && _att_sp.fw_control_yaw) {
							yaw_u = _wheel_ctrl.control_bodyrate(control_input);

						} else {
							yaw_u = _yaw_ctrl.control_euler_rate(control_input);
						}

						_actuators.control[actuator_controls_s::INDEX_YAW] = (PX4_ISFINITE(yaw_u)) ? yaw_u + _parameters.trim_yaw :
								_parameters.trim_yaw;

						/* add in manual rudder control in manual modes */
						if (_vcontrol_mode.flag_control_manual_enabled) {
							_actuators.control[actuator_controls_s::INDEX_YAW] += _manual.r;
						}

						if (!PX4_ISFINITE(yaw_u)) {
							_yaw_ctrl.reset_integrator();
							_wheel_ctrl.reset_integrator();
							perf_count(_nonfinite_output_perf);

							if (_debug && loop_counter % 10 == 0) {
								warnx("yaw_u %.4f", (double)yaw_u);
							}
						}

						/* throttle passed through if it is finite and if no engine failure was detected */
						_actuators.control[actuator_controls_s::INDEX_THROTTLE] = (PX4_ISFINITE(throttle_sp)
								&& !_vehicle_status.engine_failure) ? throttle_sp : 0.0f;

						/* scale effort by battery status */
						if (_parameters.bat_scale_en && _battery_status.scale > 0.0f &&
						    _actuators.control[actuator_controls_s::INDEX_THROTTLE] > 0.1f) {
							_actuators.control[actuator_controls_s::INDEX_THROTTLE] *= _battery_status.scale;
						}


						if (!PX4_ISFINITE(throttle_sp)) {
							if (_debug && loop_counter % 10 == 0) {
								warnx("throttle_sp %.4f", (double)throttle_sp);
							}
						}

					} else {
						perf_count(_nonfinite_input_perf);

						if (_debug && loop_counter % 10 == 0) {
							warnx("Non-finite setpoint roll_sp: %.4f, pitch_sp %.4f", (double)roll_sp, (double)pitch_sp);
						}
					}

				} else {
					// pure rate control
					_roll_ctrl.set_bodyrate_setpoint(_manual.y * _parameters.acro_max_x_rate_rad);
					_pitch_ctrl.set_bodyrate_setpoint(-_manual.x * _parameters.acro_max_y_rate_rad);
					_yaw_ctrl.set_bodyrate_setpoint(_manual.r * _parameters.acro_max_z_rate_rad);

					float roll_u = _roll_ctrl.control_bodyrate(control_input);
					_actuators.control[actuator_controls_s::INDEX_ROLL] = (PX4_ISFINITE(roll_u)) ? roll_u + _parameters.trim_roll :
							_parameters.trim_roll;

					float pitch_u = _pitch_ctrl.control_bodyrate(control_input);
					_actuators.control[actuator_controls_s::INDEX_PITCH] = (PX4_ISFINITE(pitch_u)) ? pitch_u + _parameters.trim_pitch :
							_parameters.trim_pitch;

					float yaw_u = _yaw_ctrl.control_bodyrate(control_input);
					_actuators.control[actuator_controls_s::INDEX_YAW] = (PX4_ISFINITE(yaw_u)) ? yaw_u + _parameters.trim_yaw :
							_parameters.trim_yaw;

					_actuators.control[actuator_controls_s::INDEX_THROTTLE] = PX4_ISFINITE(throttle_sp) ? throttle_sp : 0.0f;
				}

				/*
				 * Lazily publish the rate setpoint (for analysis, the actuators are published below)
				 * only once available
				 */
				_rates_sp.roll = _roll_ctrl.get_desired_bodyrate();
				_rates_sp.pitch = _pitch_ctrl.get_desired_bodyrate();
				_rates_sp.yaw = _yaw_ctrl.get_desired_bodyrate();

				_rates_sp.timestamp = hrt_absolute_time();

				if (_rate_sp_pub != nullptr) {
					/* publish the attitude rates setpoint */
					orb_publish(_rates_sp_id, _rate_sp_pub, &_rates_sp);

				} else if (_rates_sp_id) {
					/* advertise the attitude rates setpoint */
					_rate_sp_pub = orb_advertise(_rates_sp_id, &_rates_sp);
				}

				rate_ctrl_status_s rate_ctrl_status;
				rate_ctrl_status.timestamp = hrt_absolute_time();
				rate_ctrl_status.rollspeed = _att.rollspeed;
				rate_ctrl_status.pitchspeed = _att.pitchspeed;
				rate_ctrl_status.yawspeed = _att.yawspeed;
				rate_ctrl_status.rollspeed_integ = _roll_ctrl.get_integrator();
				rate_ctrl_status.pitchspeed_integ = _pitch_ctrl.get_integrator();
				rate_ctrl_status.yawspeed_integ = _yaw_ctrl.get_integrator();
				rate_ctrl_status.additional_integ1 = _wheel_ctrl.get_integrator();

				int instance;
				orb_publish_auto(ORB_ID(rate_ctrl_status), &_rate_ctrl_status_pub, &rate_ctrl_status, &instance, ORB_PRIO_DEFAULT);

			} else {
				/* manual/direct control */
				_actuators.control[actuator_controls_s::INDEX_ROLL] = _manual.y * _parameters.man_roll_scale + _parameters.trim_roll;
				_actuators.control[actuator_controls_s::INDEX_PITCH] = -_manual.x * _parameters.man_pitch_scale +
						_parameters.trim_pitch;
				_actuators.control[actuator_controls_s::INDEX_YAW] = _manual.r * _parameters.man_yaw_scale + _parameters.trim_yaw;
				_actuators.control[actuator_controls_s::INDEX_THROTTLE] = _manual.z;
			}

			// Add feed-forward from roll control output to yaw control output
			// This can be used to counteract the adverse yaw effect when rolling the plane
			_actuators.control[actuator_controls_s::INDEX_YAW] += _parameters.roll_to_yaw_ff * math::constrain(
						_actuators.control[actuator_controls_s::INDEX_ROLL], -1.0f, 1.0f);

			_actuators.control[actuator_controls_s::INDEX_FLAPS] = _flaps_applied;
			_actuators.control[5] = _manual.aux1;
			_actuators.control[actuator_controls_s::INDEX_AIRBRAKES] = _flaperons_applied;
			// FIXME: this should use _vcontrol_mode.landing_gear_pos in the future
			_actuators.control[7] = _manual.aux3;

			/* lazily publish the setpoint only once available */
			_actuators.timestamp = hrt_absolute_time();
			_actuators.timestamp_sample = _att.timestamp;
			_actuators_airframe.timestamp = hrt_absolute_time();
			_actuators_airframe.timestamp_sample = _att.timestamp;

			/* Only publish if any of the proper modes are enabled */
			if (_vcontrol_mode.flag_control_rates_enabled ||
			    _vcontrol_mode.flag_control_attitude_enabled ||
			    _vcontrol_mode.flag_control_manual_enabled) {
				/* publish the actuator controls */
				if (_actuators_0_pub != nullptr) {
					orb_publish(_actuators_id, _actuators_0_pub, &_actuators);

				} else if (_actuators_id) {
					_actuators_0_pub = orb_advertise(_actuators_id, &_actuators);
				}

				if (_actuators_2_pub != nullptr) {
					/* publish the actuator controls*/
					orb_publish(ORB_ID(actuator_controls_2), _actuators_2_pub, &_actuators_airframe);

				} else {
					/* advertise and publish */
					_actuators_2_pub = orb_advertise(ORB_ID(actuator_controls_2), &_actuators_airframe);
				}
			}
		}

		loop_counter++;
		perf_end(_loop_perf);
	}

	warnx("exiting.\n");

	_control_task = -1;
	_task_running = false;
}
コード例 #2
0
void
FixedwingAttitudeControl::task_main()
{
	/*
	 * do subscriptions
	 */
	_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
	_ctrl_state_sub = orb_subscribe(ORB_ID(control_state));
	_accel_sub = orb_subscribe_multi(ORB_ID(sensor_accel), 0);
	_vcontrol_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));
	_global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
	_vehicle_status_sub = orb_subscribe(ORB_ID(vehicle_status));
	_vehicle_land_detected_sub = orb_subscribe(ORB_ID(vehicle_land_detected));

	parameters_update();

	/* get an initial update for all sensor and status data */
	vehicle_setpoint_poll();
	vehicle_accel_poll();
	vehicle_control_mode_poll();
	vehicle_manual_poll();
	vehicle_status_poll();
	vehicle_land_detected_poll();

	/* wakeup source */
	px4_pollfd_struct_t fds[2];

	/* Setup of loop */
	fds[0].fd = _params_sub;
	fds[0].events = POLLIN;
	fds[1].fd = _ctrl_state_sub;
	fds[1].events = POLLIN;

	_task_running = true;

	while (!_task_should_exit) {
		static int loop_counter = 0;

		/* wait for up to 500ms for data */
		int pret = px4_poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 100);

		/* timed out - periodic check for _task_should_exit, etc. */
		if (pret == 0) {
			continue;
		}

		/* 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;
		}

		perf_begin(_loop_perf);

		/* only update parameters if they changed */
		if (fds[0].revents & POLLIN) {
			/* read from param to clear updated flag */
			struct parameter_update_s update;
			orb_copy(ORB_ID(parameter_update), _params_sub, &update);

			/* update parameters from storage */
			parameters_update();
		}

		/* only run controller if attitude changed */
		if (fds[1].revents & POLLIN) {
			static uint64_t last_run = 0;
			float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
			last_run = hrt_absolute_time();

			/* guard against too large deltaT's */
			if (deltaT > 1.0f) {
				deltaT = 0.01f;
			}

			/* load local copies */
			orb_copy(ORB_ID(control_state), _ctrl_state_sub, &_ctrl_state);


			/* get current rotation matrix and euler angles from control state quaternions */
			math::Quaternion q_att(_ctrl_state.q[0], _ctrl_state.q[1], _ctrl_state.q[2], _ctrl_state.q[3]);
			_R = q_att.to_dcm();

			math::Vector<3> euler_angles;
			euler_angles = _R.to_euler();
			_roll    = euler_angles(0);
			_pitch   = euler_angles(1);
			_yaw     = euler_angles(2);

			if (_vehicle_status.is_vtol && _parameters.vtol_type == 0) {
				/* vehicle is a tailsitter, we need to modify the estimated attitude for fw mode
				 *
				 * Since the VTOL airframe is initialized as a multicopter we need to
				 * modify the estimated attitude for the fixed wing operation.
				 * Since the neutral position of the vehicle in fixed wing mode is -90 degrees rotated around
				 * the pitch axis compared to the neutral position of the vehicle in multicopter mode
				 * we need to swap the roll and the yaw axis (1st and 3rd column) in the rotation matrix.
				 * Additionally, in order to get the correct sign of the pitch, we need to multiply
				 * the new x axis of the rotation matrix with -1
				 *
				 * original:			modified:
				 *
				 * Rxx  Ryx  Rzx		-Rzx  Ryx  Rxx
				 * Rxy	Ryy  Rzy		-Rzy  Ryy  Rxy
				 * Rxz	Ryz  Rzz		-Rzz  Ryz  Rxz
				 * */
				math::Matrix<3, 3> R_adapted = _R;		//modified rotation matrix

				/* move z to x */
				R_adapted(0, 0) = _R(0, 2);
				R_adapted(1, 0) = _R(1, 2);
				R_adapted(2, 0) = _R(2, 2);

				/* move x to z */
				R_adapted(0, 2) = _R(0, 0);
				R_adapted(1, 2) = _R(1, 0);
				R_adapted(2, 2) = _R(2, 0);

				/* change direction of pitch (convert to right handed system) */
				R_adapted(0, 0) = -R_adapted(0, 0);
				R_adapted(1, 0) = -R_adapted(1, 0);
				R_adapted(2, 0) = -R_adapted(2, 0);
				euler_angles = R_adapted.to_euler();  //adapted euler angles for fixed wing operation

				/* fill in new attitude data */
				_R = R_adapted;
				_roll    = euler_angles(0);
				_pitch   = euler_angles(1);
				_yaw     = euler_angles(2);

				/* lastly, roll- and yawspeed have to be swaped */
				float helper = _ctrl_state.roll_rate;
				_ctrl_state.roll_rate = -_ctrl_state.yaw_rate;
				_ctrl_state.yaw_rate = helper;
			}

			vehicle_setpoint_poll();

			vehicle_accel_poll();

			vehicle_control_mode_poll();

			vehicle_manual_poll();

			global_pos_poll();

			vehicle_status_poll();

			vehicle_land_detected_poll();

			// the position controller will not emit attitude setpoints in some modes
			// we need to make sure that this flag is reset
			_att_sp.fw_control_yaw = _att_sp.fw_control_yaw && _vcontrol_mode.flag_control_auto_enabled;

			/* lock integrator until control is started */
			bool lock_integrator;

			if (_vcontrol_mode.flag_control_attitude_enabled && !_vehicle_status.is_rotary_wing) {
				lock_integrator = false;

			} else {
				lock_integrator = true;
			}

			/* Simple handling of failsafe: deploy parachute if failsafe is on */
			if (_vcontrol_mode.flag_control_termination_enabled) {
				_actuators_airframe.control[7] = 1.0f;
				//warnx("_actuators_airframe.control[1] = 1.0f;");

			} else {
				_actuators_airframe.control[7] = 0.0f;
				//warnx("_actuators_airframe.control[1] = -1.0f;");
			}

			/* if we are in rotary wing mode, do nothing */
			if (_vehicle_status.is_rotary_wing && !_vehicle_status.is_vtol) {
				continue;
			}

			/* default flaps to center */
			float flaps_control = 0.0f;

			static float delta_flaps = 0;

			/* map flaps by default to manual if valid */
			if (PX4_ISFINITE(_manual.flaps) && _vcontrol_mode.flag_control_manual_enabled) {
				flaps_control = 0.5f * (_manual.flaps + 1.0f) * _parameters.flaps_scale;

			} else if (_vcontrol_mode.flag_control_auto_enabled) {
				flaps_control = _att_sp.apply_flaps ? 1.0f * _parameters.flaps_scale : 0.0f;
			}

			// move the actual control value continuous with time
			static hrt_abstime t_flaps_changed = 0;

			if (fabsf(flaps_control - _flaps_cmd_last) > 0.01f) {
				t_flaps_changed = hrt_absolute_time();
				delta_flaps = flaps_control - _flaps_cmd_last;
				_flaps_cmd_last = flaps_control;
			}

			static float flaps_applied = 0.0f;

			if (fabsf(flaps_applied - flaps_control) > 0.01f) {
				flaps_applied = (flaps_control - delta_flaps) + (float)hrt_elapsed_time(&t_flaps_changed) * (delta_flaps) / 1000000;
			}

			/* default flaperon to center */
			float flaperon = 0.0f;

			static float delta_flaperon = 0.0f;

			/* map flaperons by default to manual if valid */
			if (PX4_ISFINITE(_manual.aux2) && _vcontrol_mode.flag_control_manual_enabled) {
				flaperon = 0.5f * (_manual.aux2 + 1.0f) * _parameters.flaperon_scale;

			} else if (_vcontrol_mode.flag_control_auto_enabled) {
				flaperon = _att_sp.apply_flaps ? 1.0f * _parameters.flaperon_scale : 0.0f;
			}

			// move the actual control value continuous with time
			static hrt_abstime t_flaperons_changed = 0;

			if (fabsf(flaperon - _flaperons_cmd_last) > 0.01f) {
				t_flaperons_changed = hrt_absolute_time();
				delta_flaperon = flaperon - _flaperons_cmd_last;
				_flaperons_cmd_last = flaperon;
			}

			static float flaperon_applied = 0.0f;

			if (fabsf(flaperon_applied - flaperon) > 0.01f) {
				flaperon_applied = (flaperon - delta_flaperon) + (float)hrt_elapsed_time(&t_flaperons_changed) *
						   (delta_flaperon) / 1000000;
			}

			/* decide if in stabilized or full manual control */
			if (_vcontrol_mode.flag_control_attitude_enabled) {
				/* scale around tuning airspeed */
				float airspeed;

				/* if airspeed is not updating, we assume the normal average speed */
				if (bool nonfinite = !PX4_ISFINITE(_ctrl_state.airspeed) || !_ctrl_state.airspeed_valid) {
					airspeed = _parameters.airspeed_trim;

					if (nonfinite) {
						perf_count(_nonfinite_input_perf);
					}

				} else {
					/* prevent numerical drama by requiring 0.5 m/s minimal speed */
					airspeed = math::max(0.5f, _ctrl_state.airspeed);
				}

				/*
				 * For scaling our actuators using anything less than the min (close to stall)
				 * speed doesn't make any sense - its the strongest reasonable deflection we
				 * want to do in flight and its the baseline a human pilot would choose.
				 *
				 * Forcing the scaling to this value allows reasonable handheld tests.
				 */
				float airspeed_scaling = _parameters.airspeed_trim / ((airspeed < _parameters.airspeed_min) ? _parameters.airspeed_min :
							 airspeed);

				/* Use min airspeed to calculate ground speed scaling region.
				 * Don't scale below gspd_scaling_trim
				 */
				float groundspeed = sqrtf(_global_pos.vel_n * _global_pos.vel_n +
							  _global_pos.vel_e * _global_pos.vel_e);
				float gspd_scaling_trim = (_parameters.airspeed_min * 0.6f);
				float groundspeed_scaler = gspd_scaling_trim / ((groundspeed < gspd_scaling_trim) ? gspd_scaling_trim : groundspeed);

				float roll_sp = _parameters.rollsp_offset_rad;
				float pitch_sp = _parameters.pitchsp_offset_rad;
				float yaw_sp = 0.0f;
				float yaw_manual = 0.0f;
				float throttle_sp = 0.0f;

				/* Read attitude setpoint from uorb if
				 * - velocity control or position control is enabled (pos controller is running)
				 * - manual control is disabled (another app may send the setpoint, but it should
				 *   for sure not be set from the remote control values)
				 */
				if (_vcontrol_mode.flag_control_auto_enabled ||
				    !_vcontrol_mode.flag_control_manual_enabled) {
					/* read in attitude setpoint from attitude setpoint uorb topic */
					roll_sp = _att_sp.roll_body + _parameters.rollsp_offset_rad;
					pitch_sp = _att_sp.pitch_body + _parameters.pitchsp_offset_rad;
					yaw_sp = _att_sp.yaw_body;
					throttle_sp = _att_sp.thrust;

					/* reset integrals where needed */
					if (_att_sp.roll_reset_integral) {
						_roll_ctrl.reset_integrator();
					}

					if (_att_sp.pitch_reset_integral) {
						_pitch_ctrl.reset_integrator();
					}

					if (_att_sp.yaw_reset_integral) {
						_yaw_ctrl.reset_integrator();
						_wheel_ctrl.reset_integrator();
					}

				} else if (_vcontrol_mode.flag_control_velocity_enabled) {

					/* the pilot does not want to change direction,
					 * take straight attitude setpoint from position controller
					 */
					if (fabsf(_manual.y) < 0.01f && fabsf(_roll) < 0.2f) {
						roll_sp = _att_sp.roll_body + _parameters.rollsp_offset_rad;

					} else {
						roll_sp = (_manual.y * _parameters.man_roll_max)
							  + _parameters.rollsp_offset_rad;
					}

					pitch_sp = _att_sp.pitch_body + _parameters.pitchsp_offset_rad;
					throttle_sp = _att_sp.thrust;

					/* reset integrals where needed */
					if (_att_sp.roll_reset_integral) {
						_roll_ctrl.reset_integrator();
					}

					if (_att_sp.pitch_reset_integral) {
						_pitch_ctrl.reset_integrator();
					}

					if (_att_sp.yaw_reset_integral) {
						_yaw_ctrl.reset_integrator();
						_wheel_ctrl.reset_integrator();
					}

				} else if (_vcontrol_mode.flag_control_altitude_enabled) {
					/*
					 * Velocity should be controlled and manual is enabled.
					*/
					roll_sp = (_manual.y * _parameters.man_roll_max) + _parameters.rollsp_offset_rad;
					pitch_sp = _att_sp.pitch_body + _parameters.pitchsp_offset_rad;
					throttle_sp = _att_sp.thrust;

					/* reset integrals where needed */
					if (_att_sp.roll_reset_integral) {
						_roll_ctrl.reset_integrator();
					}

					if (_att_sp.pitch_reset_integral) {
						_pitch_ctrl.reset_integrator();
					}

					if (_att_sp.yaw_reset_integral) {
						_yaw_ctrl.reset_integrator();
						_wheel_ctrl.reset_integrator();
					}

				} else {
					/*
					 * Scale down roll and pitch as the setpoints are radians
					 * and a typical remote can only do around 45 degrees, the mapping is
					 * -1..+1 to -man_roll_max rad..+man_roll_max rad (equivalent for pitch)
					 *
					 * With this mapping the stick angle is a 1:1 representation of
					 * the commanded attitude.
					 *
					 * The trim gets subtracted here from the manual setpoint to get
					 * the intended attitude setpoint. Later, after the rate control step the
					 * trim is added again to the control signal.
					 */
					roll_sp = (_manual.y * _parameters.man_roll_max) + _parameters.rollsp_offset_rad;
					pitch_sp = -(_manual.x * _parameters.man_pitch_max) + _parameters.pitchsp_offset_rad;
					/* allow manual control of rudder deflection */
					yaw_manual = _manual.r;
					throttle_sp = _manual.z;

					/*
					 * in manual mode no external source should / does emit attitude setpoints.
					 * emit the manual setpoint here to allow attitude controller tuning
					 * in attitude control mode.
					 */
					struct vehicle_attitude_setpoint_s att_sp;
					att_sp.timestamp = hrt_absolute_time();
					att_sp.roll_body = roll_sp;
					att_sp.pitch_body = pitch_sp;
					att_sp.yaw_body = 0.0f - _parameters.trim_yaw;
					att_sp.thrust = throttle_sp;

					/* lazily publish the setpoint only once available */
					if (_attitude_sp_pub != nullptr) {
						/* publish the attitude setpoint */
						orb_publish(_attitude_setpoint_id, _attitude_sp_pub, &att_sp);

					} else if (_attitude_setpoint_id) {
						/* advertise and publish */
						_attitude_sp_pub = orb_advertise(_attitude_setpoint_id, &att_sp);
					}
				}

				/* If the aircraft is on ground reset the integrators */
				if (_vehicle_land_detected.landed || _vehicle_status.is_rotary_wing) {
					_roll_ctrl.reset_integrator();
					_pitch_ctrl.reset_integrator();
					_yaw_ctrl.reset_integrator();
					_wheel_ctrl.reset_integrator();
				}

				/* Prepare speed_body_u and speed_body_w */
				float speed_body_u = _R(0, 0) * _global_pos.vel_n + _R(1, 0) * _global_pos.vel_e + _R(2, 0) * _global_pos.vel_d;
				float speed_body_v = _R(0, 1) * _global_pos.vel_n + _R(1, 1) * _global_pos.vel_e + _R(2, 1) * _global_pos.vel_d;
				float speed_body_w = _R(0, 2) * _global_pos.vel_n + _R(1, 2) * _global_pos.vel_e + _R(2, 2) * _global_pos.vel_d;

				/* Prepare data for attitude controllers */
				struct ECL_ControlData control_input = {};
				control_input.roll = _roll;
				control_input.pitch = _pitch;
				control_input.yaw = _yaw;
				control_input.roll_rate = _ctrl_state.roll_rate;
				control_input.pitch_rate = _ctrl_state.pitch_rate;
				control_input.yaw_rate = _ctrl_state.yaw_rate;
				control_input.speed_body_u = speed_body_u;
				control_input.speed_body_v = speed_body_v;
				control_input.speed_body_w = speed_body_w;
				control_input.acc_body_x = _accel.x;
				control_input.acc_body_y = _accel.y;
				control_input.acc_body_z = _accel.z;
				control_input.roll_setpoint = roll_sp;
				control_input.pitch_setpoint = pitch_sp;
				control_input.yaw_setpoint = yaw_sp;
				control_input.airspeed_min = _parameters.airspeed_min;
				control_input.airspeed_max = _parameters.airspeed_max;
				control_input.airspeed = airspeed;
				control_input.scaler = airspeed_scaling;
				control_input.lock_integrator = lock_integrator;
				control_input.groundspeed = groundspeed;
				control_input.groundspeed_scaler = groundspeed_scaler;

				_yaw_ctrl.set_coordinated_method(_parameters.y_coordinated_method);

				/* Run attitude controllers */
				if (PX4_ISFINITE(roll_sp) && PX4_ISFINITE(pitch_sp)) {
					_roll_ctrl.control_attitude(control_input);
					_pitch_ctrl.control_attitude(control_input);
					_yaw_ctrl.control_attitude(control_input); //runs last, because is depending on output of roll and pitch attitude
					_wheel_ctrl.control_attitude(control_input);

					/* Update input data for rate controllers */
					control_input.roll_rate_setpoint = _roll_ctrl.get_desired_rate();
					control_input.pitch_rate_setpoint = _pitch_ctrl.get_desired_rate();
					control_input.yaw_rate_setpoint = _yaw_ctrl.get_desired_rate();

					/* Run attitude RATE controllers which need the desired attitudes from above, add trim */
					float roll_u = _roll_ctrl.control_bodyrate(control_input);
					_actuators.control[0] = (PX4_ISFINITE(roll_u)) ? roll_u + _parameters.trim_roll : _parameters.trim_roll;

					if (!PX4_ISFINITE(roll_u)) {
						_roll_ctrl.reset_integrator();
						perf_count(_nonfinite_output_perf);

						if (_debug && loop_counter % 10 == 0) {
							warnx("roll_u %.4f", (double)roll_u);
						}
					}

					float pitch_u = _pitch_ctrl.control_bodyrate(control_input);
					_actuators.control[1] = (PX4_ISFINITE(pitch_u)) ? pitch_u + _parameters.trim_pitch : _parameters.trim_pitch;

					if (!PX4_ISFINITE(pitch_u)) {
						_pitch_ctrl.reset_integrator();
						perf_count(_nonfinite_output_perf);

						if (_debug && loop_counter % 10 == 0) {
							warnx("pitch_u %.4f, _yaw_ctrl.get_desired_rate() %.4f,"
							      " airspeed %.4f, airspeed_scaling %.4f,"
							      " roll_sp %.4f, pitch_sp %.4f,"
							      " _roll_ctrl.get_desired_rate() %.4f,"
							      " _pitch_ctrl.get_desired_rate() %.4f"
							      " att_sp.roll_body %.4f",
							      (double)pitch_u, (double)_yaw_ctrl.get_desired_rate(),
							      (double)airspeed, (double)airspeed_scaling,
							      (double)roll_sp, (double)pitch_sp,
							      (double)_roll_ctrl.get_desired_rate(),
							      (double)_pitch_ctrl.get_desired_rate(),
							      (double)_att_sp.roll_body);
						}
					}

					float yaw_u = 0.0f;

					if (_att_sp.fw_control_yaw == true) {
						yaw_u = _wheel_ctrl.control_bodyrate(control_input);
					}

					else {
						yaw_u = _yaw_ctrl.control_bodyrate(control_input);
					}

					_actuators.control[2] = (PX4_ISFINITE(yaw_u)) ? yaw_u + _parameters.trim_yaw : _parameters.trim_yaw;

					/* add in manual rudder control */
					_actuators.control[2] += yaw_manual;

					if (!PX4_ISFINITE(yaw_u)) {
						_yaw_ctrl.reset_integrator();
						_wheel_ctrl.reset_integrator();
						perf_count(_nonfinite_output_perf);

						if (_debug && loop_counter % 10 == 0) {
							warnx("yaw_u %.4f", (double)yaw_u);
						}
					}

					/* throttle passed through if it is finite and if no engine failure was
					 * detected */
					_actuators.control[3] = (PX4_ISFINITE(throttle_sp) &&
								 !(_vehicle_status.engine_failure ||
								   _vehicle_status.engine_failure_cmd)) ?
								throttle_sp : 0.0f;

					if (!PX4_ISFINITE(throttle_sp)) {
						if (_debug && loop_counter % 10 == 0) {
							warnx("throttle_sp %.4f", (double)throttle_sp);
						}
					}

				} else {
					perf_count(_nonfinite_input_perf);

					if (_debug && loop_counter % 10 == 0) {
						warnx("Non-finite setpoint roll_sp: %.4f, pitch_sp %.4f", (double)roll_sp, (double)pitch_sp);
					}
				}

				/*
				 * Lazily publish the rate setpoint (for analysis, the actuators are published below)
				 * only once available
				 */
				_rates_sp.roll = _roll_ctrl.get_desired_rate();
				_rates_sp.pitch = _pitch_ctrl.get_desired_rate();
				_rates_sp.yaw = _yaw_ctrl.get_desired_rate();

				_rates_sp.timestamp = hrt_absolute_time();

				if (_rate_sp_pub != nullptr) {
					/* publish the attitude rates setpoint */
					orb_publish(_rates_sp_id, _rate_sp_pub, &_rates_sp);

				} else if (_rates_sp_id) {
					/* advertise the attitude rates setpoint */
					_rate_sp_pub = orb_advertise(_rates_sp_id, &_rates_sp);
				}

			} else {
				/* manual/direct control */
				_actuators.control[actuator_controls_s::INDEX_ROLL] = _manual.y + _parameters.trim_roll;
				_actuators.control[actuator_controls_s::INDEX_PITCH] = -_manual.x + _parameters.trim_pitch;
				_actuators.control[actuator_controls_s::INDEX_YAW] = _manual.r + _parameters.trim_yaw;
				_actuators.control[actuator_controls_s::INDEX_THROTTLE] = _manual.z;
			}

			_actuators.control[actuator_controls_s::INDEX_FLAPS] = flaps_applied;
			_actuators.control[5] = _manual.aux1;
			_actuators.control[actuator_controls_s::INDEX_AIRBRAKES] = flaperon_applied;
			_actuators.control[7] = _manual.aux3;

			/* lazily publish the setpoint only once available */
			_actuators.timestamp = hrt_absolute_time();
			_actuators.timestamp_sample = _ctrl_state.timestamp;
			_actuators_airframe.timestamp = hrt_absolute_time();
			_actuators_airframe.timestamp_sample = _ctrl_state.timestamp;

			/* Only publish if any of the proper modes are enabled */
			if (_vcontrol_mode.flag_control_rates_enabled ||
			    _vcontrol_mode.flag_control_attitude_enabled ||
			    _vcontrol_mode.flag_control_manual_enabled) {
				/* publish the actuator controls */
				if (_actuators_0_pub != nullptr) {
					orb_publish(_actuators_id, _actuators_0_pub, &_actuators);

				} else if (_actuators_id) {
					_actuators_0_pub = orb_advertise(_actuators_id, &_actuators);
				}

				if (_actuators_2_pub != nullptr) {
					/* publish the actuator controls*/
					orb_publish(ORB_ID(actuator_controls_2), _actuators_2_pub, &_actuators_airframe);

				} else {
					/* advertise and publish */
					_actuators_2_pub = orb_advertise(ORB_ID(actuator_controls_2), &_actuators_airframe);
				}
			}
		}

		loop_counter++;
		perf_end(_loop_perf);
	}

	warnx("exiting.\n");

	_control_task = -1;
	_task_running = false;
}