Moved all fixed wing controllers to new world

src/modules/fixedwing_att_control/fixedwing_att_control_att.c

@@ -0,0 +1,169 @@
+/****************************************************************************
+ *
+ *   Copyright (C) 2012 PX4 Development Team. All rights reserved.
+ *   Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
+ *
+ * Redistribution and use in source and binary forms, with or without
+ * modification, are permitted provided that the following conditions
+ * are met:
+ *
+ * 1. Redistributions of source code must retain the above copyright
+ *    notice, this list of conditions and the following disclaimer.
+ * 2. Redistributions in binary form must reproduce the above copyright
+ *    notice, this list of conditions and the following disclaimer in
+ *    the documentation and/or other materials provided with the
+ *    distribution.
+ * 3. Neither the name PX4 nor the names of its contributors may be
+ *    used to endorse or promote products derived from this software
+ *    without specific prior written permission.
+ *
+ * THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+ * "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+ * LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+ * FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+ * COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+ * INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+ * BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+ * OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+ * AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+ * LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+ * ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+ * POSSIBILITY OF SUCH DAMAGE.
+ *
+ ****************************************************************************/
+/**
+ * @file fixedwing_att_control_rate.c
+ * Implementation of a fixed wing attitude controller.
+ */
+
+#include <nuttx/config.h>
+#include <stdio.h>
+#include <stdlib.h>
+#include <string.h>
+#include <unistd.h>
+#include <fcntl.h>
+#include <errno.h>
+#include <math.h>
+#include <poll.h>
+#include <time.h>
+#include <drivers/drv_hrt.h>
+#include <arch/board/board.h>
+#include <uORB/uORB.h>
+
+#include <uORB/topics/vehicle_attitude.h>
+#include <uORB/topics/vehicle_attitude_setpoint.h>
+#include <uORB/topics/manual_control_setpoint.h>
+#include <systemlib/param/param.h>
+#include <systemlib/pid/pid.h>
+#include <systemlib/geo/geo.h>
+#include <systemlib/systemlib.h>
+
+#include "fixedwing_att_control_att.h"
+
+
+struct fw_att_control_params {
+	float roll_p;
+	float rollrate_lim;
+	float pitch_p;
+	float pitchrate_lim;
+	float yawrate_lim;
+	float pitch_roll_compensation_p;
+};
+
+struct fw_pos_control_param_handles {
+	param_t roll_p;
+	param_t rollrate_lim;
+	param_t pitch_p;
+	param_t pitchrate_lim;
+	param_t yawrate_lim;
+	param_t pitch_roll_compensation_p;
+};
+
+
+
+/* Internal Prototypes */
+static int parameters_init(struct fw_pos_control_param_handles *h);
+static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_att_control_params *p);
+
+static int parameters_init(struct fw_pos_control_param_handles *h)
+{
+	/* PID parameters */
+	h->roll_p 		=	param_find("FW_ROLL_P");
+	h->rollrate_lim =	param_find("FW_ROLLR_LIM");
+	h->pitch_p 		=	param_find("FW_PITCH_P");
+	h->pitchrate_lim =	param_find("FW_PITCHR_LIM");
+	h->yawrate_lim =	param_find("FW_YAWR_LIM");
+	h->pitch_roll_compensation_p = param_find("FW_PITCH_RCOMP");
+
+	return OK;
+}
+
+static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_att_control_params *p)
+{
+	param_get(h->roll_p, &(p->roll_p));
+	param_get(h->rollrate_lim, &(p->rollrate_lim));
+	param_get(h->pitch_p, &(p->pitch_p));
+	param_get(h->pitchrate_lim, &(p->pitchrate_lim));
+	param_get(h->yawrate_lim, &(p->yawrate_lim));
+	param_get(h->pitch_roll_compensation_p, &(p->pitch_roll_compensation_p));
+
+	return OK;
+}
+
+int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
+				   const struct vehicle_attitude_s *att,
+				   const float speed_body[],
+				   struct vehicle_rates_setpoint_s *rates_sp)
+{
+	static int counter = 0;
+	static bool initialized = false;
+
+	static struct fw_att_control_params p;
+	static struct fw_pos_control_param_handles h;
+
+	static PID_t roll_controller;
+	static PID_t pitch_controller;
+
+
+	if (!initialized) {
+		parameters_init(&h);
+		parameters_update(&h, &p);
+		pid_init(&roll_controller, p.roll_p, 0, 0, 0, p.rollrate_lim, PID_MODE_DERIVATIV_NONE); //P Controller
+		pid_init(&pitch_controller, p.pitch_p, 0, 0, 0, p.pitchrate_lim, PID_MODE_DERIVATIV_NONE); //P Controller
+		initialized = true;
+	}
+
+	/* load new parameters with lower rate */
+	if (counter % 100 == 0) {
+		/* update parameters from storage */
+		parameters_update(&h, &p);
+		pid_set_parameters(&roll_controller, p.roll_p, 0, 0, 0, p.rollrate_lim);
+		pid_set_parameters(&pitch_controller, p.pitch_p, 0, 0, 0, p.pitchrate_lim);
+	}
+
+	/* Roll (P) */
+	rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_body, att->roll, 0, 0);
+
+
+	/* Pitch (P) */
+
+	/* compensate feedforward for loss of lift due to non-horizontal angle of wing */
+	float pitch_sp_rollcompensation = p.pitch_roll_compensation_p * fabsf(sinf(att_sp->roll_body));
+	/* set pitch plus feedforward roll compensation */
+	rates_sp->pitch = pid_calculate(&pitch_controller,
+					att_sp->pitch_body + pitch_sp_rollcompensation,
+					att->pitch, 0, 0);
+
+	/* Yaw (from coordinated turn constraint or lateral force) */
+	rates_sp->yaw = (att->rollspeed * rates_sp->roll + 9.81f * sinf(att->roll) * cosf(att->pitch) + speed_body[0] * rates_sp->pitch * sinf(att->roll))
+			/ (speed_body[0] * cosf(att->roll) * cosf(att->pitch) + speed_body[2] * sinf(att->pitch));
+
+//	printf("rates_sp->yaw %.4f \n", (double)rates_sp->yaw);
+
+	counter++;
+
+	return 0;
+}
+
+
+

src/modules/fixedwing_att_control/fixedwing_att_control_att.h

@@ -0,0 +1,51 @@
+/****************************************************************************
+ *
+ *   Copyright (C) 2012 PX4 Development Team. All rights reserved.
+ *   Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
+ *
+ *
+ * Redistribution and use in source and binary forms, with or without
+ * modification, are permitted provided that the following conditions
+ * are met:
+ *
+ * 1. Redistributions of source code must retain the above copyright
+ *    notice, this list of conditions and the following disclaimer.
+ * 2. Redistributions in binary form must reproduce the above copyright
+ *    notice, this list of conditions and the following disclaimer in
+ *    the documentation and/or other materials provided with the
+ *    distribution.
+ * 3. Neither the name PX4 nor the names of its contributors may be
+ *    used to endorse or promote products derived from this software
+ *    without specific prior written permission.
+ *
+ * THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+ * "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+ * LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+ * FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+ * COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+ * INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+ * BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+ * OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+ * AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+ * LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+ * ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+ * POSSIBILITY OF SUCH DAMAGE.
+ *
+ ****************************************************************************/
+
+/* @file Fixed Wing Attitude Control */
+
+#ifndef FIXEDWING_ATT_CONTROL_ATT_H_
+#define FIXEDWING_ATT_CONTROL_ATT_H_
+
+#include <uORB/topics/vehicle_rates_setpoint.h>
+#include <uORB/topics/vehicle_attitude_setpoint.h>
+#include <uORB/topics/vehicle_attitude.h>
+#include <uORB/topics/vehicle_global_position.h>
+
+int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
+				   const struct vehicle_attitude_s *att,
+				   const float speed_body[],
+				   struct vehicle_rates_setpoint_s *rates_sp);
+
+#endif /* FIXEDWING_ATT_CONTROL_ATT_H_ */

src/modules/fixedwing_att_control/fixedwing_att_control_main.c

@@ -0,0 +1,370 @@
+/****************************************************************************
+ *
+ *   Copyright (C) 2012 PX4 Development Team. All rights reserved.
+ *   Author: 	@author Thomas Gubler <thomasgubler@student.ethz.ch>
+ *   			@author Doug Weibel <douglas.weibel@colorado.edu>
+ *
+ * Redistribution and use in source and binary forms, with or without
+ * modification, are permitted provided that the following conditions
+ * are met:
+ *
+ * 1. Redistributions of source code must retain the above copyright
+ *    notice, this list of conditions and the following disclaimer.
+ * 2. Redistributions in binary form must reproduce the above copyright
+ *    notice, this list of conditions and the following disclaimer in
+ *    the documentation and/or other materials provided with the
+ *    distribution.
+ * 3. Neither the name PX4 nor the names of its contributors may be
+ *    used to endorse or promote products derived from this software
+ *    without specific prior written permission.
+ *
+ * THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+ * "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+ * LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+ * FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+ * COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+ * INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+ * BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+ * OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+ * AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+ * LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+ * ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+ * POSSIBILITY OF SUCH DAMAGE.
+ *
+ ****************************************************************************/
+/**
+ * @file fixedwing_att_control.c
+ * Implementation of a fixed wing attitude controller.
+ */
+
+#include <nuttx/config.h>
+#include <stdio.h>
+#include <stdlib.h>
+#include <string.h>
+#include <unistd.h>
+#include <fcntl.h>
+#include <errno.h>
+#include <math.h>
+#include <poll.h>
+#include <time.h>
+#include <drivers/drv_hrt.h>
+#include <arch/board/board.h>
+#include <uORB/uORB.h>
+#include <uORB/topics/vehicle_global_position.h>
+#include <uORB/topics/vehicle_global_position_setpoint.h>
+#include <uORB/topics/vehicle_attitude.h>
+#include <uORB/topics/vehicle_status.h>
+#include <uORB/topics/vehicle_attitude_setpoint.h>
+#include <uORB/topics/manual_control_setpoint.h>
+#include <uORB/topics/actuator_controls.h>
+#include <uORB/topics/vehicle_rates_setpoint.h>
+#include <uORB/topics/vehicle_global_position.h>
+#include <uORB/topics/debug_key_value.h>
+#include <systemlib/param/param.h>
+#include <systemlib/pid/pid.h>
+#include <systemlib/geo/geo.h>
+#include <systemlib/perf_counter.h>
+#include <systemlib/systemlib.h>
+
+#include "fixedwing_att_control_rate.h"
+#include "fixedwing_att_control_att.h"
+
+/* Prototypes */
+/**
+ * Deamon management function.
+ */
+__EXPORT int fixedwing_att_control_main(int argc, char *argv[]);
+
+/**
+ * Mainloop of deamon.
+ */
+int fixedwing_att_control_thread_main(int argc, char *argv[]);
+
+/**
+ * Print the correct usage.
+ */
+static void usage(const char *reason);
+
+/* Variables */
+static bool thread_should_exit = false;		/**< Deamon exit flag */
+static bool thread_running = false;		/**< Deamon status flag */
+static int deamon_task;				/**< Handle of deamon task / thread */
+
+/* Main Thread */
+int fixedwing_att_control_thread_main(int argc, char *argv[])
+{
+	/* read arguments */
+	bool verbose = false;
+
+	for (int i = 1; i < argc; i++) {
+		if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
+			verbose = true;
+		}
+	}
+
+	/* welcome user */
+	printf("[fixedwing att control] started\n");
+
+	/* declare and safely initialize all structs */
+	struct vehicle_attitude_s att;
+	memset(&att, 0, sizeof(att));
+	struct vehicle_attitude_setpoint_s att_sp;
+	memset(&att_sp, 0, sizeof(att_sp));
+	struct vehicle_rates_setpoint_s rates_sp;
+	memset(&rates_sp, 0, sizeof(rates_sp));
+	struct vehicle_global_position_s global_pos;
+	memset(&global_pos, 0, sizeof(global_pos));
+	struct manual_control_setpoint_s manual_sp;
+	memset(&manual_sp, 0, sizeof(manual_sp));
+	struct vehicle_status_s vstatus;
+	memset(&vstatus, 0, sizeof(vstatus));
+
+	/* output structs */
+	struct actuator_controls_s actuators;
+	memset(&actuators, 0, sizeof(actuators));
+
+
+	/* publish actuator controls */
+	for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++) {
+		actuators.control[i] = 0.0f;
+	}
+
+	orb_advert_t actuator_pub = orb_advertise(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, &actuators);
+	orb_advert_t rates_pub = orb_advertise(ORB_ID(vehicle_rates_setpoint), &rates_sp);
+
+	/* subscribe */
+	int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
+	int att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
+	int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
+	int manual_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
+	int vstatus_sub = orb_subscribe(ORB_ID(vehicle_status));
+
+	/* Setup of loop */
+	float gyro[3] = {0.0f, 0.0f, 0.0f};
+	float speed_body[3] = {0.0f, 0.0f, 0.0f};
+	struct pollfd fds = { .fd = att_sub, .events = POLLIN };
+
+	while (!thread_should_exit) {
+		/* wait for a sensor update, check for exit condition every 500 ms */
+		poll(&fds, 1, 500);
+
+		/* Check if there is a new position measurement or  attitude setpoint */
+		bool pos_updated;
+		orb_check(global_pos_sub, &pos_updated);
+		bool att_sp_updated;
+		orb_check(att_sp_sub, &att_sp_updated);
+
+		/* get a local copy of attitude */
+		orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
+
+		if (att_sp_updated)
+			orb_copy(ORB_ID(vehicle_attitude_setpoint), att_sp_sub, &att_sp);
+
+		if (pos_updated) {
+			orb_copy(ORB_ID(vehicle_global_position), global_pos_sub, &global_pos);
+
+			if (att.R_valid) {
+				speed_body[0] = att.R[0][0] * global_pos.vx + att.R[0][1] * global_pos.vy + att.R[0][2] * global_pos.vz;
+				speed_body[1] = att.R[1][0] * global_pos.vx + att.R[1][1] * global_pos.vy + att.R[1][2] * global_pos.vz;
+				speed_body[2] = att.R[2][0] * global_pos.vx + att.R[2][1] * global_pos.vy + att.R[2][2] * global_pos.vz;
+
+			} else {
+				speed_body[0] = 0;
+				speed_body[1] = 0;
+				speed_body[2] = 0;
+
+				printf("FW ATT CONTROL: Did not get a valid R\n");
+			}
+		}
+
+		orb_copy(ORB_ID(manual_control_setpoint), manual_sp_sub, &manual_sp);
+		orb_copy(ORB_ID(vehicle_status), vstatus_sub, &vstatus);
+
+		gyro[0] = att.rollspeed;
+		gyro[1] = att.pitchspeed;
+		gyro[2] = att.yawspeed;
+
+		/* control */
+
+		if (vstatus.state_machine == SYSTEM_STATE_AUTO ||
+		    vstatus.state_machine == SYSTEM_STATE_STABILIZED) {
+			/* attitude control */
+			fixedwing_att_control_attitude(&att_sp, &att, speed_body, &rates_sp);
+
+			/* angular rate control */
+			fixedwing_att_control_rates(&rates_sp, gyro, &actuators);
+
+			/* pass through throttle */
+			actuators.control[3] = att_sp.thrust;
+
+			/* set flaps to zero */
+			actuators.control[4] = 0.0f;
+
+		} else if (vstatus.state_machine == SYSTEM_STATE_MANUAL) {
+			if (vstatus.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_SAS) {
+
+				/* if the RC signal is lost, try to stay level and go slowly back down to ground */
+				if (vstatus.rc_signal_lost) {
+
+					/* put plane into loiter */
+					att_sp.roll_body = 0.3f;
+					att_sp.pitch_body = 0.0f;
+
+					/* limit throttle to 60 % of last value if sane */
+					if (isfinite(manual_sp.throttle) &&
+					    (manual_sp.throttle >= 0.0f) &&
+					    (manual_sp.throttle <= 1.0f)) {
+						att_sp.thrust = 0.6f * manual_sp.throttle;
+
+					} else {
+						att_sp.thrust = 0.0f;
+					}
+
+					att_sp.yaw_body = 0;
+
+					// XXX disable yaw control, loiter
+
+				} else {
+
+					att_sp.roll_body = manual_sp.roll;
+					att_sp.pitch_body = manual_sp.pitch;
+					att_sp.yaw_body = 0;
+					att_sp.thrust = manual_sp.throttle;
+				}
+
+				att_sp.timestamp = hrt_absolute_time();
+
+				/* attitude control */
+				fixedwing_att_control_attitude(&att_sp, &att, speed_body, &rates_sp);
+
+				/* angular rate control */
+				fixedwing_att_control_rates(&rates_sp, gyro, &actuators);
+
+				/* pass through throttle */
+				actuators.control[3] = att_sp.thrust;
+
+				/* pass through flaps */
+				if (isfinite(manual_sp.flaps)) {
+					actuators.control[4] = manual_sp.flaps;
+
+				} else {
+					actuators.control[4] = 0.0f;
+				}
+
+			} else if (vstatus.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_DIRECT) {
+				/* directly pass through values */
+				actuators.control[0] = manual_sp.roll;
+				/* positive pitch means negative actuator -> pull up */
+				actuators.control[1] = manual_sp.pitch;
+				actuators.control[2] = manual_sp.yaw;
+				actuators.control[3] = manual_sp.throttle;
+
+				if (isfinite(manual_sp.flaps)) {
+					actuators.control[4] = manual_sp.flaps;
+
+				} else {
+					actuators.control[4] = 0.0f;
+				}
+			}
+		}
+
+		/* publish rates */
+		orb_publish(ORB_ID(vehicle_rates_setpoint), rates_pub, &rates_sp);
+
+		/* sanity check and publish actuator outputs */
+		if (isfinite(actuators.control[0]) &&
+		    isfinite(actuators.control[1]) &&
+		    isfinite(actuators.control[2]) &&
+		    isfinite(actuators.control[3])) {
+			orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
+		}
+	}
+
+	printf("[fixedwing_att_control] exiting, stopping all motors.\n");
+	thread_running = false;
+
+	/* kill all outputs */
+	for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++)
+		actuators.control[i] = 0.0f;
+
+	orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
+
+
+
+	close(att_sub);
+	close(actuator_pub);
+	close(rates_pub);
+
+	fflush(stdout);
+	exit(0);
+
+	return 0;
+
+}
+
+/* Startup Functions */
+
+static void
+usage(const char *reason)
+{
+	if (reason)
+		fprintf(stderr, "%s\n", reason);
+
+	fprintf(stderr, "usage: fixedwing_att_control {start|stop|status}\n\n");
+	exit(1);
+}
+
+/**
+ * The deamon app only briefly exists to start
+ * the background job. The stack size assigned in the
+ * Makefile does only apply to this management task.
+ *
+ * The actual stack size should be set in the call
+ * to task_create().
+ */
+int fixedwing_att_control_main(int argc, char *argv[])
+{
+	if (argc < 1)
+		usage("missing command");
+
+	if (!strcmp(argv[1], "start")) {
+
+		if (thread_running) {
+			printf("fixedwing_att_control already running\n");
+			/* this is not an error */
+			exit(0);
+		}
+
+		thread_should_exit = false;
+		deamon_task = task_spawn("fixedwing_att_control",
+					 SCHED_DEFAULT,
+					 SCHED_PRIORITY_MAX - 20,
+					 2048,
+					 fixedwing_att_control_thread_main,
+					 (argv) ? (const char **)&argv[2] : (const char **)NULL);
+		thread_running = true;
+		exit(0);
+	}
+
+	if (!strcmp(argv[1], "stop")) {
+		thread_should_exit = true;
+		exit(0);
+	}
+
+	if (!strcmp(argv[1], "status")) {
+		if (thread_running) {
+			printf("\tfixedwing_att_control is running\n");
+
+		} else {
+			printf("\tfixedwing_att_control not started\n");
+		}
+
+		exit(0);
+	}
+
+	usage("unrecognized command");
+	exit(1);
+}
+
+
+

src/modules/fixedwing_att_control/fixedwing_att_control_rate.c

@@ -0,0 +1,211 @@
+/****************************************************************************
+ *
+ *   Copyright (C) 2012 PX4 Development Team. All rights reserved.
+ *   Author: Thomas Gubler <thomasgubler@student.ethz.ch>
+ *
+ * Redistribution and use in source and binary forms, with or without
+ * modification, are permitted provided that the following conditions
+ * are met:
+ *
+ * 1. Redistributions of source code must retain the above copyright
+ *    notice, this list of conditions and the following disclaimer.
+ * 2. Redistributions in binary form must reproduce the above copyright
+ *    notice, this list of conditions and the following disclaimer in
+ *    the documentation and/or other materials provided with the
+ *    distribution.
+ * 3. Neither the name PX4 nor the names of its contributors may be
+ *    used to endorse or promote products derived from this software
+ *    without specific prior written permission.
+ *
+ * THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+ * "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+ * LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+ * FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+ * COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+ * INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+ * BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+ * OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+ * AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+ * LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+ * ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+ * POSSIBILITY OF SUCH DAMAGE.
+ *
+ ****************************************************************************/
+/**
+ * @file fixedwing_att_control_rate.c
+ * @author Thomas Gubler <thomasgubler@student.ethz.ch>
+ *
+ * Implementation of a fixed wing attitude controller.
+ *
+ */
+
+#include <nuttx/config.h>
+#include <stdio.h>
+#include <stdlib.h>
+#include <string.h>
+#include <unistd.h>
+#include <fcntl.h>
+#include <errno.h>
+#include <math.h>
+#include <poll.h>
+#include <time.h>
+#include <drivers/drv_hrt.h>
+#include <arch/board/board.h>
+#include <uORB/uORB.h>
+
+#include <uORB/topics/vehicle_attitude.h>
+#include <uORB/topics/vehicle_attitude_setpoint.h>
+#include <uORB/topics/manual_control_setpoint.h>
+#include <systemlib/param/param.h>
+#include <systemlib/pid/pid.h>
+#include <systemlib/geo/geo.h>
+#include <systemlib/systemlib.h>
+
+#include "fixedwing_att_control_rate.h"
+
+/*
+ * Controller parameters, accessible via MAVLink
+ *
+ */
+// Roll control parameters
+PARAM_DEFINE_FLOAT(FW_ROLLR_P, 0.9f);
+PARAM_DEFINE_FLOAT(FW_ROLLR_I, 0.2f);
+PARAM_DEFINE_FLOAT(FW_ROLLR_AWU, 0.9f);
+PARAM_DEFINE_FLOAT(FW_ROLLR_LIM, 0.7f);   // Roll rate limit in radians/sec, applies to the roll controller
+PARAM_DEFINE_FLOAT(FW_ROLL_P, 4.0f);
+PARAM_DEFINE_FLOAT(FW_PITCH_RCOMP, 0.1f);
+
+//Pitch control parameters
+PARAM_DEFINE_FLOAT(FW_PITCHR_P, 0.8f);
+PARAM_DEFINE_FLOAT(FW_PITCHR_I, 0.2f);
+PARAM_DEFINE_FLOAT(FW_PITCHR_AWU, 0.8f);
+PARAM_DEFINE_FLOAT(FW_PITCHR_LIM, 0.35f);   // Pitch rate limit in radians/sec, applies to the pitch controller
+PARAM_DEFINE_FLOAT(FW_PITCH_P, 8.0f);
+
+//Yaw control parameters					//XXX TODO this is copy paste, asign correct values
+PARAM_DEFINE_FLOAT(FW_YAWR_P, 0.3f);
+PARAM_DEFINE_FLOAT(FW_YAWR_I, 0.0f);
+PARAM_DEFINE_FLOAT(FW_YAWR_AWU, 0.0f);
+PARAM_DEFINE_FLOAT(FW_YAWR_LIM, 0.35f);   // Yaw rate limit in radians/sec
+
+/* feedforward compensation */
+PARAM_DEFINE_FLOAT(FW_PITCH_THR_P, 0.1f);	/**< throttle to pitch coupling feedforward */
+
+struct fw_rate_control_params {
+	float rollrate_p;
+	float rollrate_i;
+	float rollrate_awu;
+	float pitchrate_p;
+	float pitchrate_i;
+	float pitchrate_awu;
+	float yawrate_p;
+	float yawrate_i;
+	float yawrate_awu;
+	float pitch_thr_ff;
+};
+
+struct fw_rate_control_param_handles {
+	param_t rollrate_p;
+	param_t rollrate_i;
+	param_t rollrate_awu;
+	param_t pitchrate_p;
+	param_t pitchrate_i;
+	param_t pitchrate_awu;
+	param_t yawrate_p;
+	param_t yawrate_i;
+	param_t yawrate_awu;
+	param_t pitch_thr_ff;
+};
+
+
+
+/* Internal Prototypes */
+static int parameters_init(struct fw_rate_control_param_handles *h);
+static int parameters_update(const struct fw_rate_control_param_handles *h, struct fw_rate_control_params *p);
+
+static int parameters_init(struct fw_rate_control_param_handles *h)
+{
+	/* PID parameters */
+	h->rollrate_p 	 =	param_find("FW_ROLLR_P");   //TODO define rate params for fixed wing
+	h->rollrate_i 	 =	param_find("FW_ROLLR_I");
+	h->rollrate_awu  =	param_find("FW_ROLLR_AWU");
+
+	h->pitchrate_p 	 =	param_find("FW_PITCHR_P");
+	h->pitchrate_i 	 =	param_find("FW_PITCHR_I");
+	h->pitchrate_awu =	param_find("FW_PITCHR_AWU");
+
+	h->yawrate_p 	 =	param_find("FW_YAWR_P");
+	h->yawrate_i 	 =	param_find("FW_YAWR_I");
+	h->yawrate_awu   =	param_find("FW_YAWR_AWU");
+	h->pitch_thr_ff  =	param_find("FW_PITCH_THR_P");
+
+	return OK;
+}
+
+static int parameters_update(const struct fw_rate_control_param_handles *h, struct fw_rate_control_params *p)
+{
+	param_get(h->rollrate_p, &(p->rollrate_p));
+	param_get(h->rollrate_i, &(p->rollrate_i));
+	param_get(h->rollrate_awu, &(p->rollrate_awu));
+	param_get(h->pitchrate_p, &(p->pitchrate_p));
+	param_get(h->pitchrate_i, &(p->pitchrate_i));
+	param_get(h->pitchrate_awu, &(p->pitchrate_awu));
+	param_get(h->yawrate_p, &(p->yawrate_p));
+	param_get(h->yawrate_i, &(p->yawrate_i));
+	param_get(h->yawrate_awu, &(p->yawrate_awu));
+	param_get(h->pitch_thr_ff, &(p->pitch_thr_ff));
+
+	return OK;
+}
+
+int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
+				const float rates[],
+				struct actuator_controls_s *actuators)
+{
+	static int counter = 0;
+	static bool initialized = false;
+
+	static struct fw_rate_control_params p;
+	static struct fw_rate_control_param_handles h;
+
+	static PID_t roll_rate_controller;
+	static PID_t pitch_rate_controller;
+	static PID_t yaw_rate_controller;
+
+	static uint64_t last_run = 0;
+	const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
+	last_run = hrt_absolute_time();
+
+	if (!initialized) {
+		parameters_init(&h);
+		parameters_update(&h, &p);
+		pid_init(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0, p.rollrate_awu, 1, PID_MODE_DERIVATIV_NONE); // set D part to 0 because the controller layout is with a PI rate controller
+		pid_init(&pitch_rate_controller, p.pitchrate_p, p.pitchrate_i, 0, p.pitchrate_awu, 1, PID_MODE_DERIVATIV_NONE); // set D part to 0 because the contpitcher layout is with a PI rate contpitcher
+		pid_init(&yaw_rate_controller, p.yawrate_p, p.yawrate_i, 0, p.yawrate_awu, 1, PID_MODE_DERIVATIV_NONE); // set D part to 0 because the contpitcher layout is with a PI rate contpitcher
+		initialized = true;
+	}
+
+	/* load new parameters with lower rate */
+	if (counter % 100 == 0) {
+		/* update parameters from storage */
+		parameters_update(&h, &p);
+		pid_set_parameters(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0, p.rollrate_awu, 1);
+		pid_set_parameters(&pitch_rate_controller, p.pitchrate_p, p.pitchrate_i, 0, p.pitchrate_awu, 1);
+		pid_set_parameters(&yaw_rate_controller, p.yawrate_p, p.yawrate_i, 0, p.yawrate_awu, 1);
+	}
+
+
+	/* roll rate (PI) */
+	actuators->control[0] = pid_calculate(&roll_rate_controller, rate_sp->roll, rates[0], 0.0f, deltaT);
+	/* pitch rate (PI) */
+	actuators->control[1] = -pid_calculate(&pitch_rate_controller, rate_sp->pitch, rates[1], 0.0f, deltaT);
+	/* yaw rate (PI) */
+	actuators->control[2] = pid_calculate(&yaw_rate_controller, rate_sp->yaw, rates[2], 0.0f, deltaT);
+
+	counter++;
+
+	return 0;
+}
+
+
+

src/modules/fixedwing_att_control/fixedwing_att_control_rate.h

@@ -0,0 +1,48 @@
+/****************************************************************************
+ *
+ *   Copyright (C) 2012 PX4 Development Team. All rights reserved.
+ *   Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
+ *
+ *
+ * Redistribution and use in source and binary forms, with or without
+ * modification, are permitted provided that the following conditions
+ * are met:
+ *
+ * 1. Redistributions of source code must retain the above copyright
+ *    notice, this list of conditions and the following disclaimer.
+ * 2. Redistributions in binary form must reproduce the above copyright
+ *    notice, this list of conditions and the following disclaimer in
+ *    the documentation and/or other materials provided with the
+ *    distribution.
+ * 3. Neither the name PX4 nor the names of its contributors may be
+ *    used to endorse or promote products derived from this software
+ *    without specific prior written permission.
+ *
+ * THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+ * "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+ * LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+ * FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+ * COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+ * INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+ * BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+ * OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+ * AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+ * LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+ * ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+ * POSSIBILITY OF SUCH DAMAGE.
+ *
+ ****************************************************************************/
+
+/* @file Fixed Wing Attitude Rate Control */
+
+#ifndef FIXEDWING_ATT_CONTROL_RATE_H_
+#define FIXEDWING_ATT_CONTROL_RATE_H_
+
+#include <uORB/topics/vehicle_rates_setpoint.h>
+#include <uORB/topics/actuator_controls.h>
+
+int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
+				const float rates[],
+				struct actuator_controls_s *actuators);
+
+#endif /* FIXEDWING_ATT_CONTROL_RATE_H_ */

src/modules/fixedwing_att_control/module.mk

@@ -0,0 +1,42 @@
+############################################################################
+#
+#   Copyright (c) 2012, 2013 PX4 Development Team. All rights reserved.
+#
+# Redistribution and use in source and binary forms, with or without
+# modification, are permitted provided that the following conditions
+# are met:
+#
+# 1. Redistributions of source code must retain the above copyright
+#    notice, this list of conditions and the following disclaimer.
+# 2. Redistributions in binary form must reproduce the above copyright
+#    notice, this list of conditions and the following disclaimer in
+#    the documentation and/or other materials provided with the
+#    distribution.
+# 3. Neither the name PX4 nor the names of its contributors may be
+#    used to endorse or promote products derived from this software
+#    without specific prior written permission.
+#
+# THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+# "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+# LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+# FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+# COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+# INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+# BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+# OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+# AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+# LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+# ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+# POSSIBILITY OF SUCH DAMAGE.
+#
+############################################################################
+
+#
+# Fixedwing Attitude Control application
+#
+
+MODULE_COMMAND	= fixedwing_att_control
+
+SRCS		= fixedwing_att_control_main.c \
+		  fixedwing_att_control_att.c \
+		  fixedwing_att_control_rate.c

src/modules/fixedwing_backside/fixedwing_backside_main.cpp

@@ -0,0 +1,170 @@
+/****************************************************************************
+ *
+ *   Copyright (c) 2012, 2013 PX4 Development Team. All rights reserved.
+ *   Author: James Goppert
+ *
+ * Redistribution and use in source and binary forms, with or without
+ * modification, are permitted provided that the following conditions
+ * are met:
+ *
+ * 1. Redistributions of source code must retain the above copyright
+ *    notice, this list of conditions and the following disclaimer.
+ * 2. Redistributions in binary form must reproduce the above copyright
+ *    notice, this list of conditions and the following disclaimer in
+ *    the documentation and/or other materials provided with the
+ *    distribution.
+ * 3. Neither the name PX4 nor the names of its contributors may be
+ *    used to endorse or promote products derived from this software
+ *    without specific prior written permission.
+ *
+ * THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+ * "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+ * LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+ * FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+ * COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+ * INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+ * BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+ * OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+ * AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+ * LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+ * ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+ * POSSIBILITY OF SUCH DAMAGE.
+ *
+ ****************************************************************************/
+
+/**
+ * @file fixedwing_backside_main.cpp
+ * @author James Goppert
+ *
+ * Fixedwing backside controller using control library
+ */
+
+#include <nuttx/config.h>
+#include <unistd.h>
+#include <stdio.h>
+#include <stdlib.h>
+#include <string.h>
+#include <systemlib/systemlib.h>
+#include <controllib/fixedwing.hpp>
+#include <systemlib/param/param.h>
+#include <drivers/drv_hrt.h>
+#include <math.h>
+
+static bool thread_should_exit = false;     /**< Deamon exit flag */
+static bool thread_running = false;     /**< Deamon status flag */
+static int deamon_task;             /**< Handle of deamon task / thread */
+
+/**
+ * Deamon management function.
+ */
+extern "C" __EXPORT int fixedwing_backside_main(int argc, char *argv[]);
+
+/**
+ * Mainloop of deamon.
+ */
+int control_demo_thread_main(int argc, char *argv[]);
+
+/**
+ * Test function
+ */
+void test();
+
+/**
+ * Print the correct usage.
+ */
+static void usage(const char *reason);
+
+static void
+usage(const char *reason)
+{
+	if (reason)
+		fprintf(stderr, "%s\n", reason);
+
+	fprintf(stderr, "usage: control_demo {start|stop|status} [-p <additional params>]\n\n");
+	exit(1);
+}
+
+/**
+ * The deamon app only briefly exists to start
+ * the background job. The stack size assigned in the
+ * Makefile does only apply to this management task.
+ *
+ * The actual stack size should be set in the call
+ * to task_create().
+ */
+int fixedwing_backside_main(int argc, char *argv[])
+{
+
+	if (argc < 1)
+		usage("missing command");
+
+	if (!strcmp(argv[1], "start")) {
+
+		if (thread_running) {
+			printf("control_demo already running\n");
+			/* this is not an error */
+			exit(0);
+		}
+
+		thread_should_exit = false;
+		deamon_task = task_spawn("control_demo",
+					 SCHED_DEFAULT,
+					 SCHED_PRIORITY_MAX - 10,
+					 5120,
+					 control_demo_thread_main,
+					 (argv) ? (const char **)&argv[2] : (const char **)NULL);
+		exit(0);
+	}
+
+	if (!strcmp(argv[1], "test")) {
+		test();
+		exit(0);
+	}
+
+	if (!strcmp(argv[1], "stop")) {
+		thread_should_exit = true;
+		exit(0);
+	}
+
+	if (!strcmp(argv[1], "status")) {
+		if (thread_running) {
+			printf("\tcontrol_demo app is running\n");
+
+		} else {
+			printf("\tcontrol_demo app not started\n");
+		}
+
+		exit(0);
+	}
+
+	usage("unrecognized command");
+	exit(1);
+}
+
+int control_demo_thread_main(int argc, char *argv[])
+{
+
+	printf("[control_Demo] starting\n");
+
+	using namespace control;
+
+	fixedwing::BlockMultiModeBacksideAutopilot autopilot(NULL, "FWB");
+
+	thread_running = true;
+
+	while (!thread_should_exit) {
+		autopilot.update();
+	}
+
+	printf("[control_demo] exiting.\n");
+
+	thread_running = false;
+
+	return 0;
+}
+
+void test()
+{
+	printf("beginning control lib test\n");
+	control::basicBlocksTest();
+}

src/modules/fixedwing_backside/module.mk

@@ -0,0 +1,40 @@
+############################################################################
+#
+#   Copyright (c) 2012, 2013 PX4 Development Team. All rights reserved.
+#
+# Redistribution and use in source and binary forms, with or without
+# modification, are permitted provided that the following conditions
+# are met:
+#
+# 1. Redistributions of source code must retain the above copyright
+#    notice, this list of conditions and the following disclaimer.
+# 2. Redistributions in binary form must reproduce the above copyright
+#    notice, this list of conditions and the following disclaimer in
+#    the documentation and/or other materials provided with the
+#    distribution.
+# 3. Neither the name PX4 nor the names of its contributors may be
+#    used to endorse or promote products derived from this software
+#    without specific prior written permission.
+#
+# THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+# "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+# LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+# FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+# COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+# INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+# BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+# OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+# AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+# LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+# ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+# POSSIBILITY OF SUCH DAMAGE.
+#
+############################################################################
+
+#
+# Fixedwing backside controller
+#
+
+MODULE_COMMAND	= fixedwing_backside
+
+SRCS		= fixedwing_backside_main.cpp

src/modules/fixedwing_backside/params.c

@@ -0,0 +1,71 @@
+#include <systemlib/param/param.h>
+
+// currently tuned for easystar from arkhangar in HIL
+//https://github.com/arktools/arkhangar
+
+// 16 is max name length
+
+// gyro low pass filter
+PARAM_DEFINE_FLOAT(FWB_P_LP, 300.0f); // roll rate low pass cut freq
+PARAM_DEFINE_FLOAT(FWB_Q_LP, 300.0f); // pitch rate low pass cut freq
+PARAM_DEFINE_FLOAT(FWB_R_LP, 300.0f); // yaw rate low pass cut freq
+
+// yaw washout
+PARAM_DEFINE_FLOAT(FWB_R_HP, 1.0f); // yaw rate high pass
+
+// stabilization mode
+PARAM_DEFINE_FLOAT(FWB_P2AIL, 0.3f); // roll rate 2 aileron
+PARAM_DEFINE_FLOAT(FWB_Q2ELV, 0.1f); // pitch rate 2 elevator
+PARAM_DEFINE_FLOAT(FWB_R2RDR, 0.1f); // yaw rate 2 rudder
+
+//  psi -> phi -> p
+PARAM_DEFINE_FLOAT(FWB_PSI2PHI, 0.5f);      // heading 2 roll
+PARAM_DEFINE_FLOAT(FWB_PHI2P, 1.0f);        // roll to roll rate
+PARAM_DEFINE_FLOAT(FWB_PHI_LIM_MAX, 0.3f);  // roll limit, 28 deg
+
+// velocity -> theta
+PARAM_DEFINE_FLOAT(FWB_V2THE_P, 1.0f);      // velocity to pitch angle PID, prop gain
+PARAM_DEFINE_FLOAT(FWB_V2THE_I, 0.0f);      // integral gain
+PARAM_DEFINE_FLOAT(FWB_V2THE_D, 0.0f);      // derivative gain
+PARAM_DEFINE_FLOAT(FWB_V2THE_D_LP, 0.0f);   // derivative low-pass
+PARAM_DEFINE_FLOAT(FWB_V2THE_I_MAX, 0.0f);  // integrator wind up guard
+PARAM_DEFINE_FLOAT(FWB_THE_MIN, -0.5f);     // the max commanded pitch angle
+PARAM_DEFINE_FLOAT(FWB_THE_MAX, 0.5f);      // the min commanded pitch angle
+
+
+// theta -> q
+PARAM_DEFINE_FLOAT(FWB_THE2Q_P, 1.0f);      // pitch angle to pitch-rate PID
+PARAM_DEFINE_FLOAT(FWB_THE2Q_I, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_THE2Q_D, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_THE2Q_D_LP, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_THE2Q_I_MAX, 0.0f);
+
+//  h -> thr
+PARAM_DEFINE_FLOAT(FWB_H2THR_P, 0.01f);     // altitude to throttle PID
+PARAM_DEFINE_FLOAT(FWB_H2THR_I, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_H2THR_D, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_H2THR_D_LP, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_H2THR_I_MAX, 0.0f);
+
+// crosstrack
+PARAM_DEFINE_FLOAT(FWB_XT2YAW_MAX, 1.57f);  // cross-track to yaw angle limit 90 deg
+PARAM_DEFINE_FLOAT(FWB_XT2YAW, 0.005f);     // cross-track to yaw angle gain
+
+// speed command
+PARAM_DEFINE_FLOAT(FWB_V_MIN, 10.0f);       // minimum commanded velocity
+PARAM_DEFINE_FLOAT(FWB_V_CMD, 12.0f);       // commanded velocity
+PARAM_DEFINE_FLOAT(FWB_V_MAX, 16.0f);       // maximum commanded velocity
+
+// rate of climb
+// this is what rate of climb is commanded (in m/s) 
+// when the pitch stick is fully defelcted in simple mode
+PARAM_DEFINE_FLOAT(FWB_ROC_MAX, 1.0f);
+
+//  rate of climb -> thr
+PARAM_DEFINE_FLOAT(FWB_ROC2THR_P, 0.01f);   // rate of climb to throttle PID
+PARAM_DEFINE_FLOAT(FWB_ROC2THR_I, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_ROC2THR_D, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_ROC2THR_D_LP, 0.0f);
+PARAM_DEFINE_FLOAT(FWB_ROC2THR_I_MAX, 0.0f);
+
+PARAM_DEFINE_FLOAT(FWB_TRIM_THR, 0.8f);     // trim throttle (0,1)

src/modules/fixedwing_pos_control/fixedwing_pos_control_main.c

@@ -0,0 +1,479 @@
+/****************************************************************************
+ *
+ *   Copyright (C) 2012 PX4 Development Team. All rights reserved.
+ *   Author: 	@author Thomas Gubler <thomasgubler@student.ethz.ch>
+ *   			@author Doug Weibel <douglas.weibel@colorado.edu>
+ *
+ * Redistribution and use in source and binary forms, with or without
+ * modification, are permitted provided that the following conditions
+ * are met:
+ *
+ * 1. Redistributions of source code must retain the above copyright
+ *    notice, this list of conditions and the following disclaimer.
+ * 2. Redistributions in binary form must reproduce the above copyright
+ *    notice, this list of conditions and the following disclaimer in
+ *    the documentation and/or other materials provided with the
+ *    distribution.
+ * 3. Neither the name PX4 nor the names of its contributors may be
+ *    used to endorse or promote products derived from this software
+ *    without specific prior written permission.
+ *
+ * THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+ * "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+ * LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+ * FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+ * COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+ * INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+ * BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+ * OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+ * AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+ * LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+ * ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+ * POSSIBILITY OF SUCH DAMAGE.
+ *
+ ****************************************************************************/
+/**
+ * @file fixedwing_pos_control.c
+ * Implementation of a fixed wing attitude controller.
+ */
+
+#include <nuttx/config.h>
+#include <stdio.h>
+#include <stdlib.h>
+#include <string.h>
+#include <unistd.h>
+#include <fcntl.h>
+#include <errno.h>
+#include <math.h>
+#include <poll.h>
+#include <time.h>
+#include <drivers/drv_hrt.h>
+#include <arch/board/board.h>
+#include <uORB/uORB.h>
+#include <uORB/topics/vehicle_global_position.h>
+#include <uORB/topics/vehicle_global_position_setpoint.h>
+#include <uORB/topics/vehicle_attitude_setpoint.h>
+#include <uORB/topics/manual_control_setpoint.h>
+#include <uORB/topics/actuator_controls.h>
+#include <uORB/topics/vehicle_rates_setpoint.h>
+#include <uORB/topics/vehicle_attitude.h>
+#include <uORB/topics/parameter_update.h>
+#include <systemlib/param/param.h>
+#include <systemlib/pid/pid.h>
+#include <systemlib/geo/geo.h>
+#include <systemlib/perf_counter.h>
+#include <systemlib/systemlib.h>
+
+/*
+ * Controller parameters, accessible via MAVLink
+ *
+ */
+PARAM_DEFINE_FLOAT(FW_HEAD_P, 0.1f);
+PARAM_DEFINE_FLOAT(FW_HEADR_I, 0.1f);
+PARAM_DEFINE_FLOAT(FW_HEADR_LIM, 1.5f); //TODO: think about reasonable value
+PARAM_DEFINE_FLOAT(FW_XTRACK_P, 0.01745f);		// Radians per meter off track
+PARAM_DEFINE_FLOAT(FW_ALT_P, 0.1f);
+PARAM_DEFINE_FLOAT(FW_ROLL_LIM, 0.7f);	// Roll angle limit in radians
+PARAM_DEFINE_FLOAT(FW_HEADR_P, 0.1f);
+PARAM_DEFINE_FLOAT(FW_PITCH_LIM, 0.35f);	/**< Pitch angle limit in radians per second */
+
+struct fw_pos_control_params {
+	float heading_p;
+	float headingr_p;
+	float headingr_i;
+	float headingr_lim;
+	float xtrack_p;
+	float altitude_p;
+	float roll_lim;
+	float pitch_lim;
+};
+
+struct fw_pos_control_param_handles {
+	param_t heading_p;
+	param_t headingr_p;
+	param_t headingr_i;
+	param_t headingr_lim;
+	param_t xtrack_p;
+	param_t altitude_p;
+	param_t roll_lim;
+	param_t pitch_lim;
+};
+
+
+struct planned_path_segments_s {
+	bool segment_type;
+	double start_lat;			// Start of line or center of arc
+	double start_lon;
+	double end_lat;
+	double end_lon;
+	float radius;				// Radius of arc
+	float arc_start_bearing;		// Bearing from center to start of arc
+	float arc_sweep;				// Angle (radians) swept out by arc around center.
+	// Positive for clockwise, negative for counter-clockwise
+};
+
+
+/* Prototypes */
+/* Internal Prototypes */
+static int parameters_init(struct fw_pos_control_param_handles *h);
+static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_pos_control_params *p);
+
+/**
+ * Deamon management function.
+ */
+__EXPORT int fixedwing_pos_control_main(int argc, char *argv[]);
+
+/**
+ * Mainloop of deamon.
+ */
+int fixedwing_pos_control_thread_main(int argc, char *argv[]);
+
+/**
+ * Print the correct usage.
+ */
+static void usage(const char *reason);
+
+/* Variables */
+static bool thread_should_exit = false;		/**< Deamon exit flag */
+static bool thread_running = false;		/**< Deamon status flag */
+static int deamon_task;				/**< Handle of deamon task / thread */
+
+
+/**
+ * Parameter management
+ */
+static int parameters_init(struct fw_pos_control_param_handles *h)
+{
+	/* PID parameters */
+	h->heading_p 		=	param_find("FW_HEAD_P");
+	h->headingr_p 		=	param_find("FW_HEADR_P");
+	h->headingr_i 		=	param_find("FW_HEADR_I");
+	h->headingr_lim 	=	param_find("FW_HEADR_LIM");
+	h->xtrack_p 		=	param_find("FW_XTRACK_P");
+	h->altitude_p 		=	param_find("FW_ALT_P");
+	h->roll_lim 		=	param_find("FW_ROLL_LIM");
+	h->pitch_lim 		=	param_find("FW_PITCH_LIM");
+
+	return OK;
+}
+
+static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_pos_control_params *p)
+{
+	param_get(h->heading_p, &(p->heading_p));
+	param_get(h->headingr_p, &(p->headingr_p));
+	param_get(h->headingr_i, &(p->headingr_i));
+	param_get(h->headingr_lim, &(p->headingr_lim));
+	param_get(h->xtrack_p, &(p->xtrack_p));
+	param_get(h->altitude_p, &(p->altitude_p));
+	param_get(h->roll_lim, &(p->roll_lim));
+	param_get(h->pitch_lim, &(p->pitch_lim));
+
+	return OK;
+}
+
+
+/* Main Thread */
+int fixedwing_pos_control_thread_main(int argc, char *argv[])
+{
+	/* read arguments */
+	bool verbose = false;
+
+	for (int i = 1; i < argc; i++) {
+		if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
+			verbose = true;
+		}
+	}
+
+	/* welcome user */
+	printf("[fixedwing pos control] started\n");
+
+	/* declare and safely initialize all structs */
+	struct vehicle_global_position_s global_pos;
+	memset(&global_pos, 0, sizeof(global_pos));
+	struct vehicle_global_position_s start_pos;		// Temporary variable, replace with
+	memset(&start_pos, 0, sizeof(start_pos));		// previous waypoint when available
+	struct vehicle_global_position_setpoint_s global_setpoint;
+	memset(&global_setpoint, 0, sizeof(global_setpoint));
+	struct vehicle_attitude_s att;
+	memset(&att, 0, sizeof(att));
+	struct crosstrack_error_s xtrack_err;
+	memset(&xtrack_err, 0, sizeof(xtrack_err));
+	struct parameter_update_s param_update;
+	memset(&param_update, 0, sizeof(param_update));
+
+	/* output structs */
+	struct vehicle_attitude_setpoint_s attitude_setpoint;
+	memset(&attitude_setpoint, 0, sizeof(attitude_setpoint));
+
+	/* publish attitude setpoint */
+	attitude_setpoint.roll_body = 0.0f;
+	attitude_setpoint.pitch_body = 0.0f;
+	attitude_setpoint.yaw_body = 0.0f;
+	attitude_setpoint.thrust = 0.0f;
+	orb_advert_t attitude_setpoint_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &attitude_setpoint);
+
+	/* subscribe */
+	int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
+	int global_setpoint_sub = orb_subscribe(ORB_ID(vehicle_global_position_setpoint));
+	int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
+	int param_sub = orb_subscribe(ORB_ID(parameter_update));
+
+	/* Setup of loop */
+	struct pollfd fds[2] = {
+		{ .fd = param_sub, .events = POLLIN },
+		{ .fd = att_sub, .events = POLLIN }
+	};
+	bool global_sp_updated_set_once = false;
+
+	float psi_track = 0.0f;
+
+	int counter = 0;
+
+	struct fw_pos_control_params p;
+	struct fw_pos_control_param_handles h;
+
+	PID_t heading_controller;
+	PID_t heading_rate_controller;
+	PID_t offtrack_controller;
+	PID_t altitude_controller;
+
+	parameters_init(&h);
+	parameters_update(&h, &p);
+	pid_init(&heading_controller, p.heading_p, 0.0f, 0.0f, 0.0f, 10000.0f, PID_MODE_DERIVATIV_NONE); //arbitrary high limit
+	pid_init(&heading_rate_controller, p.headingr_p, p.headingr_i, 0.0f, 0.0f, p.roll_lim, PID_MODE_DERIVATIV_NONE);
+	pid_init(&altitude_controller, p.altitude_p, 0.0f, 0.0f, 0.0f, p.pitch_lim, PID_MODE_DERIVATIV_NONE);
+	pid_init(&offtrack_controller, p.xtrack_p, 0.0f, 0.0f, 0.0f , 60.0f * M_DEG_TO_RAD, PID_MODE_DERIVATIV_NONE); //TODO: remove hardcoded value
+
+	/* error and performance monitoring */
+	perf_counter_t fw_interval_perf = perf_alloc(PC_INTERVAL, "fixedwing_pos_control_interval");
+	perf_counter_t fw_err_perf = perf_alloc(PC_COUNT, "fixedwing_pos_control_err");
+
+	while (!thread_should_exit) {
+		/* wait for a sensor update, check for exit condition every 500 ms */
+		int ret = poll(fds, 2, 500);
+
+		if (ret < 0) {
+			/* poll error, count it in perf */
+			perf_count(fw_err_perf);
+
+		} else if (ret == 0) {
+			/* no return value, ignore */
+		} else {
+
+			/* 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), param_sub, &update);
+
+				/* update parameters from storage */
+				parameters_update(&h, &p);
+				pid_set_parameters(&heading_controller, p.heading_p, 0, 0, 0, 10000.0f); //arbitrary high limit
+				pid_set_parameters(&heading_rate_controller, p.headingr_p, p.headingr_i, 0, 0, p.roll_lim);
+				pid_set_parameters(&altitude_controller, p.altitude_p, 0, 0, 0, p.pitch_lim);
+				pid_set_parameters(&offtrack_controller, p.xtrack_p, 0, 0, 0, 60.0f * M_DEG_TO_RAD); //TODO: remove hardcoded value
+			}
+
+			/* only run controller if attitude changed */
+			if (fds[1].revents & POLLIN) {
+
+
+				static uint64_t last_run = 0;
+				const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
+				last_run = hrt_absolute_time();
+
+				/* check if there is a new position or setpoint */
+				bool pos_updated;
+				orb_check(global_pos_sub, &pos_updated);
+				bool global_sp_updated;
+				orb_check(global_setpoint_sub, &global_sp_updated);
+
+				/* load local copies */
+				orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
+
+				if (pos_updated) {
+					orb_copy(ORB_ID(vehicle_global_position), global_pos_sub, &global_pos);
+				}
+
+				if (global_sp_updated) {
+					orb_copy(ORB_ID(vehicle_global_position_setpoint), global_setpoint_sub, &global_setpoint);
+					start_pos = global_pos; //for now using the current position as the startpoint (= approx. last waypoint because the setpoint switch occurs at the waypoint)
+					global_sp_updated_set_once = true;
+					psi_track = get_bearing_to_next_waypoint((double)global_pos.lat / (double)1e7d, (double)global_pos.lon / (double)1e7d,
+							(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
+
+					printf("next wp direction: %0.4f\n", (double)psi_track);
+				}
+
+				/* Simple Horizontal Control */
+				if (global_sp_updated_set_once) {
+					//				if (counter % 100 == 0)
+					//					printf("lat_sp %d, ln_sp %d, lat: %d, lon: %d\n", global_setpoint.lat, global_setpoint.lon, global_pos.lat, global_pos.lon);
+
+					/* calculate crosstrack error */
+					// Only the case of a straight line track following handled so far
+					int distance_res = get_distance_to_line(&xtrack_err, (double)global_pos.lat / (double)1e7d, (double)global_pos.lon / (double)1e7d,
+										(double)start_pos.lat / (double)1e7d, (double)start_pos.lon / (double)1e7d,
+										(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
+
+					// XXX what is xtrack_err.past_end?
+					if (distance_res == OK /*&& !xtrack_err.past_end*/) {
+
+						float delta_psi_c = pid_calculate(&offtrack_controller, 0, xtrack_err.distance, 0.0f, 0.0f); //p.xtrack_p * xtrack_err.distance
+
+						float psi_c = psi_track + delta_psi_c;
+						float psi_e = psi_c - att.yaw;
+
+						/* wrap difference back onto -pi..pi range */
+						psi_e = _wrap_pi(psi_e);
+
+						if (verbose) {
+							printf("xtrack_err.distance %.4f ", (double)xtrack_err.distance);
+							printf("delta_psi_c %.4f ", (double)delta_psi_c);
+							printf("psi_c %.4f ", (double)psi_c);
+							printf("att.yaw %.4f ", (double)att.yaw);
+							printf("psi_e %.4f ", (double)psi_e);
+						}
+
+						/* calculate roll setpoint, do this artificially around zero */
+						float delta_psi_rate_c = pid_calculate(&heading_controller, psi_e, 0.0f, 0.0f, 0.0f);
+						float psi_rate_track = 0; //=V_gr/r_track , this will be needed for implementation of arc following
+						float psi_rate_c = delta_psi_rate_c + psi_rate_track;
+
+						/* limit turn rate */
+						if (psi_rate_c > p.headingr_lim) {
+							psi_rate_c = p.headingr_lim;
+
+						} else if (psi_rate_c < -p.headingr_lim) {
+							psi_rate_c = -p.headingr_lim;
+						}
+
+						float psi_rate_e = psi_rate_c - att.yawspeed;
+
+						// XXX sanity check: Assume 10 m/s stall speed and no stall condition
+						float ground_speed = sqrtf(global_pos.vx * global_pos.vx + global_pos.vy * global_pos.vy);
+
+						if (ground_speed < 10.0f) {
+							ground_speed = 10.0f;
+						}
+
+						float psi_rate_e_scaled = psi_rate_e * ground_speed / 9.81f; //* V_gr / g
+
+						attitude_setpoint.roll_body = pid_calculate(&heading_rate_controller, psi_rate_e_scaled, 0.0f, 0.0f, deltaT);
+
+						if (verbose) {
+							printf("psi_rate_c %.4f ", (double)psi_rate_c);
+							printf("psi_rate_e_scaled %.4f ", (double)psi_rate_e_scaled);
+							printf("rollbody %.4f\n", (double)attitude_setpoint.roll_body);
+						}
+
+						if (verbose && counter % 100 == 0)
+							printf("xtrack_err.distance: %0.4f, delta_psi_c: %0.4f\n", xtrack_err.distance, delta_psi_c);
+
+					} else {
+						if (verbose && counter % 100 == 0)
+							printf("distance_res: %d, past_end %d\n", distance_res, xtrack_err.past_end);
+					}
+
+					/* Very simple Altitude Control */
+					if (pos_updated) {
+
+						//TODO: take care of relative vs. ab. altitude
+						attitude_setpoint.pitch_body = pid_calculate(&altitude_controller, global_setpoint.altitude, global_pos.alt, 0.0f, 0.0f);
+
+					}
+
+					// XXX need speed control
+					attitude_setpoint.thrust = 0.7f;
+
+					/* publish the attitude setpoint */
+					orb_publish(ORB_ID(vehicle_attitude_setpoint), attitude_setpoint_pub, &attitude_setpoint);
+
+					/* measure in what intervals the controller runs */
+					perf_count(fw_interval_perf);
+
+					counter++;
+
+				} else {
+					// XXX no setpoint, decent default needed (loiter?)
+				}
+			}
+		}
+	}
+
+	printf("[fixedwing_pos_control] exiting.\n");
+	thread_running = false;
+
+
+	close(attitude_setpoint_pub);
+
+	fflush(stdout);
+	exit(0);
+
+	return 0;
+
+}
+
+/* Startup Functions */
+
+static void
+usage(const char *reason)
+{
+	if (reason)
+		fprintf(stderr, "%s\n", reason);
+
+	fprintf(stderr, "usage: fixedwing_pos_control {start|stop|status}\n\n");
+	exit(1);
+}
+
+/**
+ * The deamon app only briefly exists to start
+ * the background job. The stack size assigned in the
+ * Makefile does only apply to this management task.
+ *
+ * The actual stack size should be set in the call
+ * to task_create().
+ */
+int fixedwing_pos_control_main(int argc, char *argv[])
+{
+	if (argc < 1)
+		usage("missing command");
+
+	if (!strcmp(argv[1], "start")) {
+
+		if (thread_running) {
+			printf("fixedwing_pos_control already running\n");
+			/* this is not an error */
+			exit(0);
+		}
+
+		thread_should_exit = false;
+		deamon_task = task_spawn("fixedwing_pos_control",
+					 SCHED_DEFAULT,
+					 SCHED_PRIORITY_MAX - 20,
+					 2048,
+					 fixedwing_pos_control_thread_main,
+					 (argv) ? (const char **)&argv[2] : (const char **)NULL);
+		thread_running = true;
+		exit(0);
+	}
+
+	if (!strcmp(argv[1], "stop")) {
+		thread_should_exit = true;
+		exit(0);
+	}
+
+	if (!strcmp(argv[1], "status")) {
+		if (thread_running) {
+			printf("\tfixedwing_pos_control is running\n");
+
+		} else {
+			printf("\tfixedwing_pos_control not started\n");
+		}
+
+		exit(0);
+	}
+
+	usage("unrecognized command");
+	exit(1);
+}

src/modules/fixedwing_pos_control/module.mk

@@ -0,0 +1,40 @@
+############################################################################
+#
+#   Copyright (c) 2012, 2013 PX4 Development Team. All rights reserved.
+#
+# Redistribution and use in source and binary forms, with or without
+# modification, are permitted provided that the following conditions
+# are met:
+#
+# 1. Redistributions of source code must retain the above copyright
+#    notice, this list of conditions and the following disclaimer.
+# 2. Redistributions in binary form must reproduce the above copyright
+#    notice, this list of conditions and the following disclaimer in
+#    the documentation and/or other materials provided with the
+#    distribution.
+# 3. Neither the name PX4 nor the names of its contributors may be
+#    used to endorse or promote products derived from this software
+#    without specific prior written permission.
+#
+# THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
+# "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
+# LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
+# FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
+# COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
+# INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
+# BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
+# OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
+# AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
+# LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
+# ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
+# POSSIBILITY OF SUCH DAMAGE.
+#
+############################################################################
+
+#
+# Fixedwing PositionControl application
+#
+
+MODULE_COMMAND	= fixedwing_pos_control
+
+SRCS		= fixedwing_pos_control_main.c