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 * modification, are permitted provided that the following conditions
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/**
 * @file mc_att_control_params.c
 * Parameters for multicopter attitude controller.
 *
 * @author Tobias Naegeli <naegelit@student.ethz.ch>
 * @author Lorenz Meier <lm@inf.ethz.ch>
 * @author Anton Babushkin <anton.babushkin@me.com>
 */

#include <px4_defines.h>
#include "mc_att_control_params.h"
#include <systemlib/param/param.h>

/**
 * Roll P gain
 *
 * Roll proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_ROLL_P);

/**
 * Roll rate P gain
 *
 * Roll rate proportional gain, i.e. control output for angular speed error 1 rad/s.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_ROLLRATE_P);

/**
 * Roll rate I gain
 *
 * Roll rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_ROLLRATE_I);

/**
 * Roll rate D gain
 *
 * Roll rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_ROLLRATE_D);

/**
 * Pitch P gain
 *
 * Pitch proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
 *
 * @unit 1/s
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_PITCH_P);

/**
 * Pitch rate P gain
 *
 * Pitch rate proportional gain, i.e. control output for angular speed error 1 rad/s.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_PITCHRATE_P);

/**
 * Pitch rate I gain
 *
 * Pitch rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_PITCHRATE_I);

/**
 * Pitch rate D gain
 *
 * Pitch rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_PITCHRATE_D);

/**
 * Yaw P gain
 *
 * Yaw proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
 *
 * @unit 1/s
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_YAW_P);

/**
 * Yaw rate P gain
 *
 * Yaw rate proportional gain, i.e. control output for angular speed error 1 rad/s.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_YAWRATE_P);

/**
 * Yaw rate I gain
 *
 * Yaw rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_YAWRATE_I);

/**
 * Yaw rate D gain
 *
 * Yaw rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
 *
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_YAWRATE_D);

/**
 * Yaw feed forward
 *
 * Feed forward weight for manual yaw control. 0 will give slow responce and no overshot, 1 - fast responce and big overshot.
 *
 * @min 0.0
 * @max 1.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_YAW_FF);

/**
 * Max yaw rate
 *
 * Limit for yaw rate, has effect for large rotations in autonomous mode, to avoid large control output and mixer saturation.
 *
 * @unit deg/s
 * @min 0.0
 * @max 360.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_YAWRATE_MAX);

/**
 * Max acro roll rate
 *
 * @unit deg/s
 * @min 0.0
 * @max 360.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_ACRO_R_MAX);

/**
 * Max acro pitch rate
 *
 * @unit deg/s
 * @min 0.0
 * @max 360.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_ACRO_P_MAX);

/**
 * Max acro yaw rate
 *
 * @unit deg/s
 * @min 0.0
 * @group Multicopter Attitude Control
 */
PX4_PARAM_DEFINE_FLOAT(MP_ACRO_Y_MAX);