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Merge pull request #1204 from PX4/tecs-cleanup

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Remove all unused TECS parameters
This commit is contained in:
Thomas Gubler
2014-07-18 09:30:55 +02:00
parent 4b6192f0bc 81f60329e4
commit a1a921d152
9 changed files with 2 additions and 269 deletions
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ROMFS/px4fmu_common/init.d/1005_rc_fw_Malolo1.hil
-9
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@@ -26,15 +26,6 @@ then
param set FW_RR_P 0.1
param set FW_R_LIM 45
param set FW_R_RMAX 0
param set FW_T_CLMB_MAX 5
param set FW_T_HRATE_P 0.02
param set FW_T_PTCH_DAMP 0
param set FW_T_RLL2THR 15
param set FW_T_SINK_MAX 5
param set FW_T_SINK_MIN 2
param set FW_T_SRATE_P 0.01
param set FW_T_TIME_CONST 3
param set FW_T_VERT_ACC 7
param set FW_YR_FF 0.0
param set FW_YR_I 0
param set FW_YR_IMAX 0.2
ROMFS/px4fmu_common/init.d/3031_phantom
-4
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@@ -30,10 +30,6 @@ then
param set FW_RR_P 0.08
param set FW_R_LIM 50
param set FW_R_RMAX 0
param set FW_T_HRATE_P 0.01
param set FW_T_RLL2THR 15
param set FW_T_SRATE_P 0.01
param set FW_T_TIME_CONST 5
fi
set MIXER phantom
ROMFS/px4fmu_common/init.d/3032_skywalker_x5
-4
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@@ -30,10 +30,6 @@ then
param set FW_RR_P 0.03
param set FW_R_LIM 60
param set FW_R_RMAX 0
param set FW_T_HRATE_P 0.01
param set FW_T_RLL2THR 15
param set FW_T_SRATE_P 0.01
param set FW_T_TIME_CONST 5
fi
set MIXER FMU_X5
ROMFS/px4fmu_common/init.d/3100_tbs_caipirinha
-4
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@@ -33,10 +33,6 @@ then
param set FW_RR_P 0.03
param set FW_R_LIM 60
param set FW_R_RMAX 0
param set FW_T_HRATE_P 0.01
param set FW_T_RLL2THR 15
param set FW_T_SRATE_P 0.01
param set FW_T_TIME_CONST 5
fi
set MIXER FMU_Q
src/modules/fw_pos_control_l1/fw_pos_control_l1_main.cpp
+2 -58
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@@ -199,19 +199,6 @@ private:
float l1_period;
float l1_damping;
float time_const;
float min_sink_rate;
float max_sink_rate;
float max_climb_rate;
float throttle_damp;
float integrator_gain;
float vertical_accel_limit;
float height_comp_filter_omega;
float speed_comp_filter_omega;
float roll_throttle_compensation;
float speed_weight;
float pitch_damping;
float airspeed_min;
float airspeed_trim;
float airspeed_max;
@@ -242,19 +229,6 @@ private:
param_t l1_period;
param_t l1_damping;
param_t time_const;
param_t min_sink_rate;
param_t max_sink_rate;
param_t max_climb_rate;
param_t throttle_damp;
param_t integrator_gain;
param_t vertical_accel_limit;
param_t height_comp_filter_omega;
param_t speed_comp_filter_omega;
param_t roll_throttle_compensation;
param_t speed_weight;
param_t pitch_damping;
param_t airspeed_min;
param_t airspeed_trim;
param_t airspeed_max;
@@ -470,21 +444,6 @@ FixedwingPositionControl::FixedwingPositionControl() :
_parameter_handles.land_heading_hold_horizontal_distance = param_find("FW_LND_HHDIST");
_parameter_handles.range_finder_rel_alt = param_find("FW_LND_RFRALT");
_parameter_handles.time_const = param_find("FW_T_TIME_CONST");
_parameter_handles.min_sink_rate = param_find("FW_T_SINK_MIN");
_parameter_handles.max_sink_rate = param_find("FW_T_SINK_MAX");
_parameter_handles.max_climb_rate = param_find("FW_T_CLMB_MAX");
_parameter_handles.throttle_damp = param_find("FW_T_THR_DAMP");
_parameter_handles.integrator_gain = param_find("FW_T_INTEG_GAIN");
_parameter_handles.vertical_accel_limit = param_find("FW_T_VERT_ACC");
_parameter_handles.height_comp_filter_omega = param_find("FW_T_HGT_OMEGA");
_parameter_handles.speed_comp_filter_omega = param_find("FW_T_SPD_OMEGA");
_parameter_handles.roll_throttle_compensation = param_find("FW_T_RLL2THR");
_parameter_handles.speed_weight = param_find("FW_T_SPDWEIGHT");
_parameter_handles.pitch_damping = param_find("FW_T_PTCH_DAMP");
_parameter_handles.heightrate_p = param_find("FW_T_HRATE_P");
_parameter_handles.speedrate_p = param_find("FW_T_SRATE_P");
/* fetch initial parameter values */
parameters_update();
}
@@ -535,19 +494,6 @@ FixedwingPositionControl::parameters_update()
param_get(_parameter_handles.throttle_land_max, &(_parameters.throttle_land_max));
param_get(_parameter_handles.time_const, &(_parameters.time_const));
param_get(_parameter_handles.min_sink_rate, &(_parameters.min_sink_rate));
param_get(_parameter_handles.max_sink_rate, &(_parameters.max_sink_rate));
param_get(_parameter_handles.throttle_damp, &(_parameters.throttle_damp));
param_get(_parameter_handles.integrator_gain, &(_parameters.integrator_gain));
param_get(_parameter_handles.vertical_accel_limit, &(_parameters.vertical_accel_limit));
param_get(_parameter_handles.height_comp_filter_omega, &(_parameters.height_comp_filter_omega));
param_get(_parameter_handles.speed_comp_filter_omega, &(_parameters.speed_comp_filter_omega));
param_get(_parameter_handles.roll_throttle_compensation, &(_parameters.roll_throttle_compensation));
param_get(_parameter_handles.speed_weight, &(_parameters.speed_weight));
param_get(_parameter_handles.pitch_damping, &(_parameters.pitch_damping));
param_get(_parameter_handles.max_climb_rate, &(_parameters.max_climb_rate));
param_get(_parameter_handles.heightrate_p, &(_parameters.heightrate_p));
param_get(_parameter_handles.speedrate_p, &(_parameters.speedrate_p));
@@ -810,10 +756,8 @@ FixedwingPositionControl::control_position(const math::Vector<2> &current_positi
if (!_was_pos_control_mode) {
/* reset integrators */
if (_mTecs.getEnabled()) {
_mTecs.resetIntegrators();
_mTecs.resetDerivatives(_airspeed.true_airspeed_m_s);
}
_mTecs.resetIntegrators();
_mTecs.resetDerivatives(_airspeed.true_airspeed_m_s);
}
_was_pos_control_mode = true;
src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c
-176
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@@ -154,182 +154,6 @@ PARAM_DEFINE_FLOAT(FW_THR_MIN, 0.0f);
*/
PARAM_DEFINE_FLOAT(FW_THR_LND_MAX, 1.0f);
/**
* Maximum climb rate
*
* This is the best climb rate that the aircraft can achieve with
* the throttle set to THR_MAX and the airspeed set to the
* default value. For electric aircraft make sure this number can be
* achieved towards the end of flight when the battery voltage has reduced.
* The setting of this parameter can be checked by commanding a positive
* altitude change of 100m in loiter, RTL or guided mode. If the throttle
* required to climb is close to THR_MAX and the aircraft is maintaining
* airspeed, then this parameter is set correctly. If the airspeed starts
* to reduce, then the parameter is set to high, and if the throttle
* demand required to climb and maintain speed is noticeably less than
* FW_THR_MAX, then either FW_T_CLMB_MAX should be increased or
* FW_THR_MAX reduced.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_CLMB_MAX, 5.0f);
/**
* Minimum descent rate
*
* This is the sink rate of the aircraft with the throttle
* set to THR_MIN and flown at the same airspeed as used
* to measure FW_T_CLMB_MAX.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SINK_MIN, 2.0f);
/**
* Maximum descent rate
*
* This sets the maximum descent rate that the controller will use.
* If this value is too large, the aircraft can over-speed on descent.
* This should be set to a value that can be achieved without
* exceeding the lower pitch angle limit and without over-speeding
* the aircraft.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SINK_MAX, 5.0f);
/**
* TECS time constant
*
* This is the time constant of the TECS control algorithm (in seconds).
* Smaller values make it faster to respond, larger values make it slower
* to respond.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_TIME_CONST, 5.0f);
/**
* Throttle damping factor
*
* This is the damping gain for the throttle demand loop.
* Increase to add damping to correct for oscillations in speed and height.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_THR_DAMP, 0.5f);
/**
* Integrator gain
*
* This is the integrator gain on the control loop.
* Increasing this gain increases the speed at which speed
* and height offsets are trimmed out, but reduces damping and
* increases overshoot.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_INTEG_GAIN, 0.1f);
/**
* Maximum vertical acceleration
*
* This is the maximum vertical acceleration (in metres/second square)
* either up or down that the controller will use to correct speed
* or height errors. The default value of 7 m/s/s (equivalent to +- 0.7 g)
* allows for reasonably aggressive pitch changes if required to recover
* from under-speed conditions.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_VERT_ACC, 7.0f);
/**
* Complementary filter "omega" parameter for height
*
* This is the cross-over frequency (in radians/second) of the complementary
* filter used to fuse vertical acceleration and barometric height to obtain
* an estimate of height rate and height. Increasing this frequency weights
* the solution more towards use of the barometer, whilst reducing it weights
* the solution more towards use of the accelerometer data.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_HGT_OMEGA, 3.0f);
/**
* Complementary filter "omega" parameter for speed
*
* This is the cross-over frequency (in radians/second) of the complementary
* filter used to fuse longitudinal acceleration and airspeed to obtain an
* improved airspeed estimate. Increasing this frequency weights the solution
* more towards use of the arispeed sensor, whilst reducing it weights the
* solution more towards use of the accelerometer data.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SPD_OMEGA, 2.0f);
/**
* Roll -> Throttle feedforward
*
* Increasing this gain turn increases the amount of throttle that will
* be used to compensate for the additional drag created by turning.
* Ideally this should be set to approximately 10 x the extra sink rate
* in m/s created by a 45 degree bank turn. Increase this gain if
* the aircraft initially loses energy in turns and reduce if the
* aircraft initially gains energy in turns. Efficient high aspect-ratio
* aircraft (eg powered sailplanes) can use a lower value, whereas
* inefficient low aspect-ratio models (eg delta wings) can use a higher value.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_RLL2THR, 10.0f);
/**
* Speed <--> Altitude priority
*
* This parameter adjusts the amount of weighting that the pitch control
* applies to speed vs height errors. Setting it to 0.0 will cause the
* pitch control to control height and ignore speed errors. This will
* normally improve height accuracy but give larger airspeed errors.
* Setting it to 2.0 will cause the pitch control loop to control speed
* and ignore height errors. This will normally reduce airspeed errors,
* but give larger height errors. The default value of 1.0 allows the pitch
* control to simultaneously control height and speed.
* Note to Glider Pilots - set this parameter to 2.0 (The glider will
* adjust its pitch angle to maintain airspeed, ignoring changes in height).
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SPDWEIGHT, 1.0f);
/**
* Pitch damping factor
*
* This is the damping gain for the pitch demand loop. Increase to add
* damping to correct for oscillations in height. The default value of 0.0
* will work well provided the pitch to servo controller has been tuned
* properly.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_PTCH_DAMP, 0.0f);
/**
* Height rate P factor
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_HRATE_P, 0.05f);
/**
* Speed rate P factor
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SRATE_P, 0.05f);
/**
* Landing slope angle
*
src/modules/fw_pos_control_l1/mtecs/mTecs.cpp
-1
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@@ -49,7 +49,6 @@ namespace fwPosctrl {
mTecs::mTecs() :
SuperBlock(NULL, "MT"),
/* Parameters */
_mTecsEnabled(this, "ENABLED"),
_airspeedMin(this, "FW_AIRSPD_MIN", false),
/* Publications */
_status(&getPublications(), ORB_ID(tecs_status)),
src/modules/fw_pos_control_l1/mtecs/mTecs.h
-2
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@@ -90,14 +90,12 @@ public:
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 */
src/modules/fw_pos_control_l1/mtecs/mTecs_params.c
-11
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@@ -46,17 +46,6 @@
* 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