6 files changed, 1285 insertions, 0 deletions
diff --git a/src/modules/fw_pos_control_l1/mtecs/limitoverride.cpp b/src/modules/fw_pos_control_l1/mtecs/limitoverride.cpp
new file mode 100644
index 000000000..58795edb6
--- /dev/null
+++ b/src/modules/fw_pos_control_l1/mtecs/limitoverride.cpp
@@ -0,0 +1,71 @@
+/****************************************************************************
+ *
+ *   Copyright (c) 2013 PX4 Development Team. All rights reserved.
+ *   Author: 	@author Thomas Gubler <thomasgubler@gmail.com>
+ *
+ * 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 limitoverride.cpp
+ *
+ * @author Thomas Gubler <thomasgubler@gmail.com>
+ */
+
+#include "limitoverride.h"
+
+namespace fwPosctrl {
+
+bool LimitOverride::applyOverride(BlockOutputLimiter &outputLimiterThrottle,
+		BlockOutputLimiter &outputLimiterPitch)
+{
+	bool ret = false;
+
+	if (overrideThrottleMinEnabled)	{
+		outputLimiterThrottle.setMin(overrideThrottleMin);
+		ret = true;
+	}
+	if (overrideThrottleMaxEnabled)	{
+		outputLimiterThrottle.setMax(overrideThrottleMax);
+		ret = true;
+	}
+	if (overridePitchMinEnabled)	{
+		outputLimiterPitch.setMin(overridePitchMin);
+		ret = true;
+	}
+	if (overridePitchMaxEnabled)	{
+		outputLimiterPitch.setMax(overridePitchMax);
+		ret = true;
+	}
+
+	return ret;
+}
+
+} /* namespace fwPosctrl */
diff --git a/src/modules/fw_pos_control_l1/mtecs/limitoverride.h b/src/modules/fw_pos_control_l1/mtecs/limitoverride.h
new file mode 100644
index 000000000..64c2e7bbd
--- /dev/null
+++ b/src/modules/fw_pos_control_l1/mtecs/limitoverride.h
@@ -0,0 +1,107 @@
+/****************************************************************************
+ *
+ *   Copyright (c) 2013 PX4 Development Team. All rights reserved.
+ *   Author: 	@author Thomas Gubler <thomasgubler@gmail.com>
+ *
+ * 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 limitoverride.h
+ *
+ * @author Thomas Gubler <thomasgubler@gmail.com>
+ */
+
+
+#ifndef LIMITOVERRIDE_H_
+#define LIMITOVERRIDE_H_
+
+#include "mTecs_blocks.h"
+
+namespace fwPosctrl
+{
+
+/* A small class which provides helper functions to override control output limits which are usually set by
+* parameters in special cases
+*/
+class LimitOverride
+{
+public:
+	LimitOverride() :
+		overrideThrottleMinEnabled(false),
+		overrideThrottleMaxEnabled(false),
+		overridePitchMinEnabled(false),
+		overridePitchMaxEnabled(false)
+	{};
+
+	~LimitOverride() {};
+
+	/*
+	* Override the limits of the outputlimiter instances given by the arguments with the limits saved in
+	* this class (if enabled)
+	* @return true if the limit was applied
+	*/
+	bool applyOverride(BlockOutputLimiter &outputLimiterThrottle,
+			BlockOutputLimiter &outputLimiterPitch);
+
+	/* Functions to enable or disable the override */
+	void enableThrottleMinOverride(float value) { enable(&overrideThrottleMinEnabled,
+			&overrideThrottleMin, value); }
+	void disableThrottleMinOverride() { disable(&overrideThrottleMinEnabled); }
+	void enableThrottleMaxOverride(float value) { enable(&overrideThrottleMaxEnabled,
+			&overrideThrottleMax, value); }
+	void disableThrottleMaxOverride() { disable(&overrideThrottleMaxEnabled); }
+	void enablePitchMinOverride(float value) { enable(&overridePitchMinEnabled,
+			&overridePitchMin, value); }
+	void disablePitchMinOverride() { disable(&overridePitchMinEnabled); }
+	void enablePitchMaxOverride(float value) { enable(&overridePitchMaxEnabled,
+			&overridePitchMax, value); }
+	void disablePitchMaxOverride() { disable(&overridePitchMaxEnabled); }
+
+protected:
+	bool overrideThrottleMinEnabled;
+	float overrideThrottleMin;
+	bool overrideThrottleMaxEnabled;
+	float overrideThrottleMax;
+	bool overridePitchMinEnabled;
+	float overridePitchMin; //in degrees (replaces param values)
+	bool overridePitchMaxEnabled;
+	float overridePitchMax; //in degrees (replaces param values)
+
+	/* Enable a specific limit override */
+	void enable(bool *flag, float *limit, float value) { *flag = true; *limit = value; };
+
+	/* Disable a specific limit override */
+	void disable(bool *flag) { *flag = false; };
+};
+
+} /* namespace fwPosctrl */
+
+#endif /* LIMITOVERRIDE_H_ */
diff --git a/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp b/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp
new file mode 100644
index 000000000..2e37d166e
--- /dev/null
+++ b/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp
@@ -0,0 +1,313 @@
+/****************************************************************************
+ *
+ *   Copyright (c) 2013 PX4 Development Team. All rights reserved.
+ *   Author: 	@author Thomas Gubler <thomasgubler@gmail.com>
+ *
+ * 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 mTecs.cpp
+ *
+ * @author Thomas Gubler <thomasgubler@gmail.com>
+ */
+
+#include "mTecs.h"
+
+#include <lib/geo/geo.h>
+#include <stdio.h>
+
+namespace fwPosctrl {
+
+mTecs::mTecs() :
+	SuperBlock(NULL, "MT"),
+	/* Parameters */
+	_mTecsEnabled(this, "ENABLED"),
+	_airspeedMin(this, "FW_AIRSPD_MIN", false),
+	/* Publications */
+	_status(&getPublications(), ORB_ID(tecs_status)),
+	/* control blocks */
+	_controlTotalEnergy(this, "THR"),
+	_controlEnergyDistribution(this, "PIT", true),
+	_controlAltitude(this, "FPA", true),
+	_controlAirSpeed(this, "ACC"),
+	_flightPathAngleLowpass(this, "FPA_LP"),
+	_airspeedLowpass(this, "A_LP"),
+	_airspeedDerivative(this, "AD"),
+	_throttleSp(0.0f),
+	_pitchSp(0.0f),
+	_BlockOutputLimiterTakeoffThrottle(this, "TKF_THR"),
+	_BlockOutputLimiterTakeoffPitch(this, "TKF_PIT", true),
+	_BlockOutputLimiterUnderspeedThrottle(this, "USP_THR"),
+	_BlockOutputLimiterUnderspeedPitch(this, "USP_PIT", true),
+	_BlockOutputLimiterLandThrottle(this, "LND_THR"),
+	_BlockOutputLimiterLandPitch(this, "LND_PIT", true),
+	timestampLastIteration(hrt_absolute_time()),
+	_firstIterationAfterReset(true),
+	_dtCalculated(false),
+	_counter(0),
+	_debug(false)
+{
+}
+
+mTecs::~mTecs()
+{
+}
+
+int mTecs::updateAltitudeSpeed(float flightPathAngle, float altitude, float altitudeSp, float airspeed,
+		float airspeedSp, tecs_mode mode, LimitOverride limitOverride)
+{
+	/* check if all input arguments are numbers and abort if not so */
+	if (!isfinite(flightPathAngle) || !isfinite(altitude) ||
+			!isfinite(altitudeSp) || !isfinite(airspeed) || !isfinite(airspeedSp) || !isfinite(mode)) {
+		return -1;
+	}
+
+	/* time measurement */
+	updateTimeMeasurement();
+
+	/* calculate flight path angle setpoint from altitude setpoint */
+	float flightPathAngleSp = _controlAltitude.update(altitudeSp - altitude);
+
+	/* Debug output */
+	if (_counter % 10 == 0) {
+		debug("***");
+		debug("updateAltitudeSpeed: altitudeSp %.4f, altitude %.4f, flightPathAngleSp %.4f", (double)altitudeSp, (double)altitude, (double)flightPathAngleSp);
+	}
+
+	/* Write part of the status message */
+	_status.altitudeSp = altitudeSp;
+	_status.altitude = altitude;
+
+
+	/* use flightpath angle setpoint for total energy control */
+	return updateFlightPathAngleSpeed(flightPathAngle, flightPathAngleSp, airspeed,
+			airspeedSp, mode, limitOverride);
+}
+
+int mTecs::updateFlightPathAngleSpeed(float flightPathAngle, float flightPathAngleSp, float airspeed,
+		float airspeedSp, tecs_mode mode, LimitOverride limitOverride)
+{
+	/* check if all input arguments are numbers and abort if not so */
+	if (!isfinite(flightPathAngle) || !isfinite(flightPathAngleSp) ||
+			!isfinite(airspeed) || !isfinite(airspeedSp) || !isfinite(mode)) {
+		return -1;
+	}
+
+	/* time measurement */
+	updateTimeMeasurement();
+
+	/* Filter airspeed */
+	float airspeedFiltered = _airspeedLowpass.update(airspeed);
+
+	/* calculate longitudinal acceleration setpoint from airspeed setpoint*/
+	float accelerationLongitudinalSp = _controlAirSpeed.update(airspeedSp - airspeedFiltered);
+
+	/* Debug output */
+	if (_counter % 10 == 0) {
+		debug("updateFlightPathAngleSpeed airspeedSp %.4f, airspeed %.4f airspeedFiltered %.4f,"
+				"accelerationLongitudinalSp%.4f",
+				(double)airspeedSp, (double)airspeed,
+				(double)airspeedFiltered, (double)accelerationLongitudinalSp);
+	}
+
+	/* Write part of the status message */
+	_status.airspeedSp = airspeedSp;
+	_status.airspeed = airspeed;
+	_status.airspeedFiltered = airspeedFiltered;
+
+
+	/* use longitudinal acceleration setpoint for total energy control */
+	return updateFlightPathAngleAcceleration(flightPathAngle, flightPathAngleSp, airspeedFiltered,
+			accelerationLongitudinalSp, mode, limitOverride);
+}
+
+int mTecs::updateFlightPathAngleAcceleration(float flightPathAngle, float flightPathAngleSp, float airspeedFiltered,
+		float accelerationLongitudinalSp, tecs_mode mode, LimitOverride limitOverride)
+{
+	/* check if all input arguments are numbers and abort if not so */
+	if (!isfinite(flightPathAngle) || !isfinite(flightPathAngleSp) ||
+			!isfinite(airspeedFiltered) || !isfinite(accelerationLongitudinalSp) || !isfinite(mode)) {
+		return -1;
+	}
+	/* time measurement */
+	updateTimeMeasurement();
+
+	/* update parameters first */
+	updateParams();
+
+	/* Filter flightpathangle */
+	float flightPathAngleFiltered = _flightPathAngleLowpass.update(flightPathAngle);
+
+	/* calculate values (energies) */
+	float flightPathAngleError = flightPathAngleSp - flightPathAngleFiltered;
+	float airspeedDerivative = 0.0f;
+	if(_airspeedDerivative.getDt() > 0.0f) {
+		airspeedDerivative = _airspeedDerivative.update(airspeedFiltered);
+	}
+	float airspeedDerivativeNorm = airspeedDerivative / CONSTANTS_ONE_G;
+	float airspeedDerivativeSp = accelerationLongitudinalSp;
+	float airspeedDerivativeNormSp = airspeedDerivativeSp / CONSTANTS_ONE_G;
+	float airspeedDerivativeNormError = airspeedDerivativeNormSp - airspeedDerivativeNorm;
+
+	float totalEnergyRate = flightPathAngleFiltered + airspeedDerivativeNorm;
+	float totalEnergyRateError = flightPathAngleError + airspeedDerivativeNormError;
+	float totalEnergyRateSp = flightPathAngleSp + airspeedDerivativeNormSp;
+	float totalEnergyRateError2 = totalEnergyRateSp - totalEnergyRate;
+
+	float energyDistributionRate = flightPathAngleFiltered - airspeedDerivativeNorm;
+	float energyDistributionRateError = flightPathAngleError - airspeedDerivativeNormError;
+	float energyDistributionRateSp = flightPathAngleSp - airspeedDerivativeNormSp;
+	float energyDistributionRateError2 = energyDistributionRateSp - energyDistributionRate;
+
+	/* Debug output */
+	if (_counter % 10 == 0) {
+		debug("totalEnergyRateSp %.2f, totalEnergyRate %.2f, totalEnergyRateError %.2f totalEnergyRateError2 %.2f airspeedDerivativeNorm %.4f",
+				(double)totalEnergyRateSp, (double)totalEnergyRate, (double)totalEnergyRateError, (double)totalEnergyRateError2, (double)airspeedDerivativeNorm);
+		debug("energyDistributionRateSp %.2f, energyDistributionRate %.2f, energyDistributionRateError %.2f energyDistributionRateError2 %.2f",
+				(double)energyDistributionRateSp, (double)energyDistributionRate, (double)energyDistributionRateError, (double)energyDistributionRateError2);
+	}
+
+	/* Check airspeed: if below safe value switch to underspeed mode (if not in land or takeoff mode) */
+	if (mode != TECS_MODE_LAND && mode != TECS_MODE_TAKEOFF && airspeedFiltered < _airspeedMin.get()) {
+		mode = TECS_MODE_UNDERSPEED;
+	}
+
+	/* Set special ouput limiters if we are not in TECS_MODE_NORMAL */
+	BlockOutputLimiter *outputLimiterThrottle = &_controlTotalEnergy.getOutputLimiter();
+	BlockOutputLimiter *outputLimiterPitch = &_controlEnergyDistribution.getOutputLimiter();
+	if (mode == TECS_MODE_TAKEOFF) {
+		outputLimiterThrottle = &_BlockOutputLimiterTakeoffThrottle;
+		outputLimiterPitch = &_BlockOutputLimiterTakeoffPitch;
+	} else if (mode == TECS_MODE_LAND) {
+		// only limit pitch but do not limit throttle
+		outputLimiterPitch = &_BlockOutputLimiterLandPitch;
+	} else if (mode == TECS_MODE_LAND_THROTTLELIM) {
+		outputLimiterThrottle = &_BlockOutputLimiterLandThrottle;
+		outputLimiterPitch = &_BlockOutputLimiterLandPitch;
+	} else if (mode == TECS_MODE_UNDERSPEED) {
+		outputLimiterThrottle = &_BlockOutputLimiterUnderspeedThrottle;
+		outputLimiterPitch = &_BlockOutputLimiterUnderspeedPitch;
+	}
+
+	/* Apply overrride given by the limitOverride argument (this is used for limits which are not given by
+	 * parameters such as pitch limits with takeoff waypoints or throttle limits when the launchdetector
+	 * is running) */
+	limitOverride.applyOverride(*outputLimiterThrottle, *outputLimiterPitch);
+
+	/* Write part of the status message */
+	_status.flightPathAngleSp = flightPathAngleSp;
+	_status.flightPathAngle = flightPathAngle;
+	_status.flightPathAngleFiltered = flightPathAngleFiltered;
+	_status.airspeedDerivativeSp = airspeedDerivativeSp;
+	_status.airspeedDerivative = airspeedDerivative;
+	_status.totalEnergyRateSp = totalEnergyRateSp;
+	_status.totalEnergyRate = totalEnergyRate;
+	_status.energyDistributionRateSp = energyDistributionRateSp;
+	_status.energyDistributionRate = energyDistributionRate;
+	_status.mode = mode;
+
+	/** update control blocks **/
+	/* update total energy rate control block */
+	_throttleSp = _controlTotalEnergy.update(totalEnergyRateSp, totalEnergyRateError, outputLimiterThrottle);
+
+	/* update energy distribution rate control block */
+	_pitchSp = _controlEnergyDistribution.update(energyDistributionRateSp, energyDistributionRateError, outputLimiterPitch);
+
+
+	if (_counter % 10 == 0) {
+		debug("_throttleSp %.1f, _pitchSp %.1f, flightPathAngleSp %.1f, flightPathAngle %.1f accelerationLongitudinalSp %.1f, airspeedDerivative %.1f",
+				(double)_throttleSp, (double)_pitchSp,
+				(double)flightPathAngleSp, (double)flightPathAngle,
+				(double)accelerationLongitudinalSp, (double)airspeedDerivative);
+	}
+
+	/* publish status messge */
+	_status.update();
+
+	/* clean up */
+	_firstIterationAfterReset = false;
+	_dtCalculated = false;
+
+	_counter++;
+
+	return 0;
+}
+
+void mTecs::resetIntegrators()
+{
+	_controlTotalEnergy.getIntegral().setY(0.0f);
+	_controlEnergyDistribution.getIntegral().setY(0.0f);
+	timestampLastIteration = hrt_absolute_time();
+	_firstIterationAfterReset = true;
+}
+
+void mTecs::resetDerivatives(float airspeed)
+{
+	_airspeedDerivative.setU(airspeed);
+}
+
+
+void mTecs::updateTimeMeasurement()
+{
+	if (!_dtCalculated) {
+		float deltaTSeconds = 0.0f;
+		if (!_firstIterationAfterReset) {
+			hrt_abstime timestampNow = hrt_absolute_time();
+			deltaTSeconds = (float)(timestampNow - timestampLastIteration) * 1e-6f;
+			timestampLastIteration = timestampNow;
+		}
+		setDt(deltaTSeconds);
+
+		_dtCalculated = true;
+	}
+}
+
+void mTecs::debug_print(const char *fmt, va_list args)
+{
+	fprintf(stderr, "%s: ", "[mtecs]");
+	vfprintf(stderr, fmt, args);
+
+	fprintf(stderr, "\n");
+}
+
+void mTecs::debug(const char *fmt, ...) {
+
+	if (!_debug) {
+		return;
+	}
+
+	va_list args;
+
+	va_start(args, fmt);
+	debug_print(fmt, args);
+}
+
+} /* namespace fwPosctrl */
diff --git a/src/modules/fw_pos_control_l1/mtecs/mTecs.h b/src/modules/fw_pos_control_l1/mtecs/mTecs.h
new file mode 100644
index 000000000..efa89a5d3
--- /dev/null
+++ b/src/modules/fw_pos_control_l1/mtecs/mTecs.h
@@ -0,0 +1,155 @@
+/****************************************************************************
+ *
+ *   Copyright (c) 2013 PX4 Development Team. All rights reserved.
+ *   Author: 	@author Thomas Gubler <thomasgubler@gmail.com>
+ *
+ * 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 mTecs.h
+ *
+ * @author Thomas Gubler <thomasgubler@gmail.com>
+ */
+
+
+#ifndef MTECS_H_
+#define MTECS_H_
+
+#include "mTecs_blocks.h"
+#include "limitoverride.h"
+
+#include <controllib/block/BlockParam.hpp>
+#include <drivers/drv_hrt.h>
+#include <uORB/Publication.hpp>
+#include <uORB/topics/tecs_status.h>
+
+namespace fwPosctrl
+{
+
+/* Main class of the mTecs */
+class mTecs : public control::SuperBlock
+{
+public:
+	mTecs();
+	virtual ~mTecs();
+
+	/*
+	 * Control in altitude setpoint and speed mode
+	 */
+	int updateAltitudeSpeed(float flightPathAngle, float altitude, float altitudeSp, float airspeed,
+			float airspeedSp, tecs_mode mode, LimitOverride limitOverride);
+
+	/*
+	 * Control in flightPathAngle setpoint (flollow a slope etc.) and speed mode
+	 */
+	int updateFlightPathAngleSpeed(float flightPathAngle, float flightPathAngleSp, float airspeed,
+			float airspeedSp, tecs_mode mode, LimitOverride limitOverride);
+
+	/*
+	 * Control in flightPathAngle setpoint (flollow a slope etc.) and acceleration mode (base case)
+	 */
+	int updateFlightPathAngleAcceleration(float flightPathAngle, float flightPathAngleSp, float airspeedFiltered,
+			float accelerationLongitudinalSp, tecs_mode mode, LimitOverride limitOverride);
+
+	/*
+	 * Reset all integrators
+	 */
+	void resetIntegrators();
+
+	/*
+	 * Reset all derivative calculations
+	 */
+	void resetDerivatives(float airspeed);
+
+	/* Accessors */
+	bool getEnabled() { return _mTecsEnabled.get() > 0; }
+	float getThrottleSetpoint() { return _throttleSp; }
+	float getPitchSetpoint() { return _pitchSp; }
+	float airspeedLowpassUpdate(float input) { return _airspeedLowpass.update(input); }
+
+protected:
+	/* parameters */
+	control::BlockParamInt _mTecsEnabled;		/**< 1 if mTecs is enabled */
+	control::BlockParamFloat _airspeedMin;		/**< minimal airspeed */
+
+	/* Publications */
+	uORB::Publication<tecs_status_s> _status;	/**< publish internal values for logging */
+
+	/* control blocks */
+	BlockFFPILimitedCustom _controlTotalEnergy;		/**< FFPI controller for total energy control: output
+								  is throttle */
+	BlockFFPILimitedCustom _controlEnergyDistribution;	/**< FFPI controller for energy distribution control:
+								  output is pitch */
+	BlockPDLimited	_controlAltitude;			/**< PD controller for altitude: output is the flight
+								  path angle setpoint */
+	BlockPDLimited	_controlAirSpeed;			/**< PD controller for airspeed: output is acceleration
+								  setpoint */
+
+	/* Other calculation Blocks */
+	control::BlockLowPass _flightPathAngleLowpass;	/**< low pass filter for the flight path angle */
+	control::BlockLowPass _airspeedLowpass;		/**< low pass filter for airspeed */
+	control::BlockDerivative _airspeedDerivative;	/**< airspeed derivative calulation */
+
+	/* Output setpoints */
+	float _throttleSp;				/**< Throttle Setpoint from 0 to 1 */
+	float _pitchSp;					/**< Pitch Setpoint from -pi to pi */
+
+	/* Output Limits in special modes */
+	BlockOutputLimiter _BlockOutputLimiterTakeoffThrottle;	    /**< Throttle Limits during takeoff */
+	BlockOutputLimiter _BlockOutputLimiterTakeoffPitch;	    /**< Pitch Limit during takeoff */
+	BlockOutputLimiter _BlockOutputLimiterUnderspeedThrottle;   /**< Throttle Limits when underspeed is detected */
+	BlockOutputLimiter _BlockOutputLimiterUnderspeedPitch;	    /**< Pitch Limit when underspeed is detected */
+	BlockOutputLimiter _BlockOutputLimiterLandThrottle;	    /**< Throttle Limits during landing (only in
+								      last phase)*/
+	BlockOutputLimiter _BlockOutputLimiterLandPitch;	    /**< Pitch Limit during landing */
+
+	/* Time measurements */
+	hrt_abstime timestampLastIteration;	/**< Saves the result of hrt_absolute_time() of the last iteration */
+
+	bool _firstIterationAfterReset;		/**< True during the first iteration after a reset */
+	bool _dtCalculated;			/**< True if dt has been calculated in this iteration */
+
+	int _counter;
+	bool _debug;				///< Set true to enable debug output
+
+
+	static void	debug_print(const char *fmt, va_list args);
+	void		debug(const char *fmt, ...);
+
+	/*
+	 * Measure and update the time step dt if this was not already done in the current iteration
+	 */
+	void updateTimeMeasurement();
+};
+
+} /* namespace fwPosctrl */
+
+#endif /* MTECS_H_ */
diff --git a/src/modules/fw_pos_control_l1/mtecs/mTecs_blocks.h b/src/modules/fw_pos_control_l1/mtecs/mTecs_blocks.h
new file mode 100644
index 000000000..c22e60ae0
--- /dev/null
+++ b/src/modules/fw_pos_control_l1/mtecs/mTecs_blocks.h
@@ -0,0 +1,220 @@
+/****************************************************************************
+ *
+ *   Copyright (c) 2013 PX4 Development Team. All rights reserved.
+ *   Author: 	@author Thomas Gubler <thomasgubler@gmail.com>
+ *
+ * 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 mTecs_blocks.h
+ *
+ * Custom blocks for the mTecs
+ *
+ * @author Thomas Gubler <thomasgubler@gmail.com>
+ */
+
+#pragma once
+
+#include <controllib/blocks.hpp>
+#include <systemlib/err.h>
+
+namespace fwPosctrl
+{
+
+using namespace control;
+
+/* An block which can be used to limit the output */
+class BlockOutputLimiter: public SuperBlock
+{
+public:
+// methods
+	BlockOutputLimiter(SuperBlock *parent, const char *name, bool fAngularLimit = false) :
+		SuperBlock(parent, name),
+		_isAngularLimit(fAngularLimit),
+		_min(this, "MIN"),
+		_max(this, "MAX")
+	{};
+	virtual ~BlockOutputLimiter() {};
+	/*
+	 * Imposes the limits given by _min and _max on value
+	 *
+	 * @param value is changed to be on the interval _min to _max
+	 * @param difference if the value is changed this corresponds to the change of value * (-1)
+     * otherwise unchanged
+	 * @return: true if the limit is applied, false otherwise
+	 */
+	bool limit(float& value, float& difference) {
+		float minimum = isAngularLimit() ? getMin() * M_DEG_TO_RAD_F : getMin();
+		float maximum = isAngularLimit() ? getMax() * M_DEG_TO_RAD_F : getMax();
+		if (value < minimum) {
+			difference = value - minimum;
+			value = minimum;
+			return true;
+		} else if (value > maximum) {
+			difference = value - maximum;
+			value = maximum;
+			return true;
+		}
+		return false;
+	}
+//accessor:
+	bool isAngularLimit() {return _isAngularLimit ;}
+	float getMin() { return _min.get(); }
+	float getMax() { return _max.get(); }
+	void setMin(float value) { _min.set(value); }
+	void setMax(float value) { _max.set(value); }
+protected:
+//attributes
+	bool _isAngularLimit;
+	control::BlockParamFloat _min;
+	control::BlockParamFloat _max;
+};
+
+
+/* A combination of feed forward, P and I gain using the output limiter*/
+class BlockFFPILimited: public SuperBlock
+{
+public:
+// methods
+	BlockFFPILimited(SuperBlock *parent, const char *name, bool isAngularLimit = false) :
+		SuperBlock(parent, name),
+		_outputLimiter(this, "", isAngularLimit),
+		_integral(this, "I"),
+		_kFF(this, "FF"),
+		_kP(this, "P"),
+		_kI(this, "I"),
+		_offset(this, "OFF")
+	{};
+	virtual ~BlockFFPILimited() {};
+	float update(float inputValue, float inputError) { return calcLimitedOutput(inputValue, inputError, _outputLimiter); }
+// accessors
+	BlockIntegral &getIntegral() { return _integral; }
+	float getKFF() { return _kFF.get(); }
+	float getKP() { return _kP.get(); }
+	float getKI() { return _kI.get(); }
+	float getOffset() { return _offset.get(); }
+	BlockOutputLimiter &getOutputLimiter() { return _outputLimiter; };
+protected:
+	BlockOutputLimiter _outputLimiter;
+
+	float calcUnlimitedOutput(float inputValue, float inputError) {return getOffset() + getKFF() * inputValue + getKP() * inputError + getKI() * getIntegral().update(inputError);}
+	float calcLimitedOutput(float inputValue, float inputError, BlockOutputLimiter &outputLimiter) {
+		float difference = 0.0f;
+		float integralYPrevious = _integral.getY();
+		float output = calcUnlimitedOutput(inputValue, inputError);
+		if(outputLimiter.limit(output, difference) &&
+			(((difference < 0) && (getKI() * getIntegral().getY() < 0)) ||
+			((difference > 0) && (getKI() * getIntegral().getY() > 0)))) {
+				getIntegral().setY(integralYPrevious);
+		}
+		return output;
+	}
+private:
+	BlockIntegral _integral;
+	BlockParamFloat _kFF;
+	BlockParamFloat _kP;
+	BlockParamFloat _kI;
+	BlockParamFloat _offset;
+};
+
+/* A combination of feed forward, P and I gain using the output limiter with the option to provide a special output limiter (for example for takeoff)*/
+class BlockFFPILimitedCustom: public BlockFFPILimited
+{
+public:
+// methods
+	BlockFFPILimitedCustom(SuperBlock *parent, const char *name, bool isAngularLimit = false) :
+		BlockFFPILimited(parent, name, isAngularLimit)
+		{};
+	virtual ~BlockFFPILimitedCustom() {};
+	float update(float inputValue, float inputError, BlockOutputLimiter *outputLimiter = NULL) {
+		return calcLimitedOutput(inputValue, inputError, outputLimiter == NULL ? _outputLimiter : *outputLimiter);
+	}
+};
+
+/* A combination of P gain and output limiter */
+class BlockPLimited: public SuperBlock
+{
+public:
+// methods
+	BlockPLimited(SuperBlock *parent, const char *name, bool isAngularLimit = false) :
+		SuperBlock(parent, name),
+		_kP(this, "P"),
+		_outputLimiter(this, "", isAngularLimit)
+	{};
+	virtual ~BlockPLimited() {};
+	float update(float input) {
+		float difference = 0.0f;
+		float output = getKP() * input;
+		getOutputLimiter().limit(output, difference);
+		return output;
+	}
+// accessors
+	BlockOutputLimiter &getOutputLimiter() { return _outputLimiter; };
+	float getKP() { return _kP.get(); }
+private:
+	control::BlockParamFloat _kP;
+	BlockOutputLimiter _outputLimiter;
+};
+
+/* A combination of P, D gains and output limiter */
+class BlockPDLimited: public SuperBlock
+{
+public:
+// methods
+	BlockPDLimited(SuperBlock *parent, const char *name, bool isAngularLimit = false) :
+		SuperBlock(parent, name),
+		_kP(this, "P"),
+		_kD(this, "D"),
+		_derivative(this, "D"),
+		_outputLimiter(this, "", isAngularLimit)
+	{};
+	virtual ~BlockPDLimited() {};
+	float update(float input) {
+		float difference = 0.0f;
+		float output = getKP() * input + (getDerivative().getDt() > 0.0f ? getKD() * getDerivative().update(input) : 0.0f);
+		getOutputLimiter().limit(output, difference);
+
+		return output;
+	}
+// accessors
+	float getKP() { return _kP.get(); }
+	float getKD() { return _kD.get(); }
+	BlockDerivative &getDerivative() { return _derivative; }
+	BlockOutputLimiter &getOutputLimiter() { return _outputLimiter; };
+private:
+	control::BlockParamFloat _kP;
+	control::BlockParamFloat _kD;
+	BlockDerivative _derivative;
+	BlockOutputLimiter _outputLimiter;
+};
+
+}
+
diff --git a/src/modules/fw_pos_control_l1/mtecs/mTecs_params.c b/src/modules/fw_pos_control_l1/mtecs/mTecs_params.c
new file mode 100644
index 000000000..5b9238780
--- /dev/null
+++ b/src/modules/fw_pos_control_l1/mtecs/mTecs_params.c
@@ -0,0 +1,419 @@
+/****************************************************************************
+ *
+ *   Copyright (c) 2013 PX4 Development Team. All rights reserved.
+ *   Author: 	@author Thomas Gubler <thomasgubler@gmail.com>
+ *
+ * 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 mTecs_params.c
+ *
+ * @author Thomas Gubler <thomasgubler@gmail.com>
+ */
+
+#include <nuttx/config.h>
+#include <systemlib/param/param.h>
+
+/*
+ * Controller parameters, accessible via MAVLink
+ */
+
+/**
+ * mTECS enabled
+ *
+ * Set to 1 to enable mTECS
+ *
+ * @min 0
+ * @max 1
+ * @group mTECS
+ */
+PARAM_DEFINE_INT32(MT_ENABLED, 1);
+
+/**
+ * Total Energy Rate Control Feedforward
+ * Maps the total energy rate setpoint to the throttle setpoint
+ *
+ * @min 0.0
+ * @max 10.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_THR_FF, 0.7f);
+
+/**
+ * Total Energy Rate Control P
+ * Maps the total energy rate error to the throttle setpoint
+ *
+ * @min 0.0
+ * @max 10.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_THR_P, 0.1f);
+
+/**
+ * Total Energy Rate Control I
+ * Maps the integrated total energy rate to the throttle setpoint
+ *
+ * @min 0.0
+ * @max 10.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_THR_I, 0.25f);
+
+/**
+ * Total Energy Rate Control Offset (Cruise throttle sp)
+ *
+ * @min 0.0
+ * @max 10.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_THR_OFF, 0.7f);
+
+/**
+ * Energy Distribution Rate Control Feedforward
+ * Maps the energy distribution rate setpoint to the pitch setpoint
+ *
+ * @min 0.0
+ * @max 10.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_PIT_FF, 0.4f);
+
+/**
+ * Energy Distribution Rate Control P
+ * Maps the energy distribution rate error to the pitch setpoint
+ *
+ * @min 0.0
+ * @max 10.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_PIT_P, 0.03f);
+
+/**
+ * Energy Distribution Rate Control I
+ * Maps the integrated energy distribution rate error to the pitch setpoint
+ *
+ * @min 0.0
+ * @max 10.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_PIT_I, 0.03f);
+
+
+/**
+ * Total Energy Distribution Offset (Cruise pitch sp)
+ *
+ * @min 0.0
+ * @max 10.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_PIT_OFF, 0.0f);
+
+/**
+ * Minimal Throttle Setpoint
+ *
+ * @min 0.0
+ * @max 1.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_THR_MIN, 0.0f);
+
+/**
+ * Maximal Throttle Setpoint
+ *
+ * @min 0.0
+ * @max 1.0
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_THR_MAX, 1.0f);
+
+/**
+ * Minimal Pitch Setpoint in Degrees
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_PIT_MIN, -45.0f);
+
+/**
+ * Maximal Pitch Setpoint in Degrees
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_PIT_MAX, 20.0f);
+
+/**
+ * Lowpass (cutoff freq.) for the flight path angle
+ *
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_FPA_LP, 1.0f);
+
+/**
+ * P gain for the altitude control
+ * Maps the altitude error to the flight path angle setpoint
+ *
+ * @min 0.0f
+ * @max 10.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_FPA_P, 0.3f);
+
+/**
+ * D gain for the altitude control
+ * Maps the change of altitude error to the flight path angle setpoint
+ *
+ * @min 0.0f
+ * @max 10.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_FPA_D, 0.0f);
+
+/**
+ * Lowpass for FPA error derivative calculation (see MT_FPA_D)
+ *
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_FPA_D_LP, 1.0f);
+
+
+/**
+ * Minimal flight path angle setpoint
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_FPA_MIN, -20.0f);
+
+/**
+ * Maximal flight path angle setpoint
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_FPA_MAX, 30.0f);
+
+/**
+ * Lowpass (cutoff freq.) for airspeed
+ *
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_A_LP, 1.0f);
+
+/**
+ * P gain for the airspeed control
+ * Maps the airspeed error to the acceleration setpoint
+ *
+ * @min 0.0f
+ * @max 10.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_ACC_P, 0.3f);
+
+/**
+ * D gain for the airspeed control
+ * Maps the change of airspeed error to the acceleration setpoint
+ *
+ * @min 0.0f
+ * @max 10.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_ACC_D, 0.0f);
+
+/**
+ * Lowpass for ACC error derivative calculation (see MT_ACC_D)
+ *
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_ACC_D_LP, 1.0f);
+
+/**
+ * Minimal acceleration (air)
+ *
+ * @unit m/s^2
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_ACC_MIN, -40.0f);
+
+/**
+ * Maximal acceleration (air)
+ *
+* @unit m/s^2
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_ACC_MAX, 40.0f);
+
+/**
+ * Airspeed derivative calculation lowpass
+ *
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_AD_LP, 1.0f);
+
+/**
+ * Minimal throttle during takeoff
+ *
+ * @min 0.0f
+ * @max 1.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_TKF_THR_MIN, 1.0f);
+
+/**
+ * Maximal throttle during takeoff
+ *
+ * @min 0.0f
+ * @max 1.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_TKF_THR_MAX, 1.0f);
+
+/**
+ * Minimal pitch during takeoff
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_TKF_PIT_MIN, 0.0f);
+
+/**
+ * Maximal pitch during takeoff
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_TKF_PIT_MAX, 45.0f);
+
+/**
+ * Minimal throttle in underspeed mode
+ *
+ * @min 0.0f
+ * @max 1.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_USP_THR_MIN, 1.0f);
+
+/**
+ * Maximal throttle in underspeed mode
+ *
+ * @min 0.0f
+ * @max 1.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_USP_THR_MAX, 1.0f);
+
+/**
+ * Minimal pitch in underspeed mode
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_USP_PIT_MIN, -45.0f);
+
+/**
+ * Maximal pitch in underspeed mode
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_USP_PIT_MAX, 0.0f);
+
+/**
+ * Minimal throttle in landing mode (only last phase of landing)
+ *
+ * @min 0.0f
+ * @max 1.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_LND_THR_MIN, 0.0f);
+
+/**
+ * Maximal throttle in landing mode (only last phase of landing)
+ *
+ * @min 0.0f
+ * @max 1.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_LND_THR_MAX, 0.0f);
+
+/**
+ * Minimal pitch in landing mode
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_LND_PIT_MIN, -5.0f);
+
+/**
+ * Maximal pitch in landing mode
+ *
+ * @min -90.0f
+ * @max 90.0f
+ * @unit deg
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_LND_PIT_MAX, 15.0f);
+
+/**
+ * Integrator Limit for Total Energy Rate Control
+ *
+ * @min 0.0f
+ * @max 10.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_THR_I_MAX, 10.0f);
+
+/**
+ * Integrator Limit for Energy Distribution Rate Control
+ *
+ * @min 0.0f
+ * @max 10.0f
+ * @group mTECS
+ */
+PARAM_DEFINE_FLOAT(MT_PIT_I_MAX, 10.0f);