fly316/PX4-Autopilot
7
0
Fork 0
mirror of https://gitee.com/mirrors_PX4/PX4-Autopilot.git synced 2026-10-31 02:41:35 +08:00
Code Issues Packages Projects Releases Wiki Activity

param remove empty @unit

Browse Source
This commit is contained in:
Daniel Agar
2016-03-14 09:12:34 +01:00
committed by Lorenz Meier
parent 146cdf578a
commit 7a9427bc34
27 changed files with 0 additions and 195 deletions
Download Patch File Download Diff File Expand all files Collapse all files
src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c
-16
View File
@@ -63,7 +63,6 @@ PARAM_DEFINE_FLOAT(FW_L1_PERIOD, 20.0f);
*
* Damping factor for L1 control.
*
* @unit
* @min 0.6
* @max 0.9
* @group L1 Control
@@ -75,7 +74,6 @@ PARAM_DEFINE_FLOAT(FW_L1_DAMPING, 0.75f);
*
* This is the throttle setting required to achieve the desired cruise speed. Most airframes have a value of 0.5-0.7.
*
* @unit
* @min 0.0
* @max 1.0
* @group L1 Control
@@ -87,7 +85,6 @@ PARAM_DEFINE_FLOAT(FW_THR_CRUISE, 0.6f);
*
* Maximum slew rate for the commanded throttle
*
* @unit
* @min 0.0
* @max 1.0
* @group L1 Control
@@ -137,7 +134,6 @@ PARAM_DEFINE_FLOAT(FW_R_LIM, 50.0f);
* For overpowered aircraft, this should be reduced to a value that
* provides sufficient thrust to climb at the maximum pitch angle PTCH_MAX.
*
* @unit
* @min 0.0
* @max 1.0
* @group L1 Control
@@ -156,7 +152,6 @@ PARAM_DEFINE_FLOAT(FW_THR_MAX, 1.0f);
* For aircraft with internal combustion engine this parameter should be set
* for desired idle rpm.
*
* @unit
* @min 0.0
* @max 1.0
* @group L1 Control
@@ -171,7 +166,6 @@ PARAM_DEFINE_FLOAT(FW_THR_MIN, 0.0f);
* For aircraft with internal combustion engine this parameter should be set
* above desired idle rpm.
*
* @unit
* @min 0.0
* @max 0.4
* @group L1 Control
@@ -184,7 +178,6 @@ PARAM_DEFINE_FLOAT(FW_THR_IDLE, 0.15f);
* This throttle value will be set as throttle limit at FW_LND_TLALT,
* before arcraft will flare.
*
* @unit
* @min 0.0
* @max 1.0
* @group L1 Control
@@ -285,7 +278,6 @@ PARAM_DEFINE_FLOAT(FW_T_THRO_CONST, 8.0f);
* This is the damping gain for the throttle demand loop.
* Increase to add damping to correct for oscillations in speed and height.
*
* @unit
* @group Fixed Wing TECS
*/
PARAM_DEFINE_FLOAT(FW_T_THR_DAMP, 0.5f);
@@ -298,7 +290,6 @@ PARAM_DEFINE_FLOAT(FW_T_THR_DAMP, 0.5f);
* and height offsets are trimmed out, but reduces damping and
* increases overshoot.
*
* @unit
* @group Fixed Wing TECS
*/
PARAM_DEFINE_FLOAT(FW_T_INTEG_GAIN, 0.1f);
@@ -357,7 +348,6 @@ PARAM_DEFINE_FLOAT(FW_T_SPD_OMEGA, 2.0f);
* aircraft (eg powered sailplanes) can use a lower value, whereas
* inefficient low aspect-ratio models (eg delta wings) can use a higher value.
*
* @unit
* @group Fixed Wing TECS
*/
PARAM_DEFINE_FLOAT(FW_T_RLL2THR, 15.0f);
@@ -376,7 +366,6 @@ PARAM_DEFINE_FLOAT(FW_T_RLL2THR, 15.0f);
* Note to Glider Pilots - set this parameter to 2.0 (The glider will
* adjust its pitch angle to maintain airspeed, ignoring changes in height).
*
* @unit
* @min 0.0
* @max 2.0
* @group Fixed Wing TECS
@@ -391,7 +380,6 @@ PARAM_DEFINE_FLOAT(FW_T_SPDWEIGHT, 1.0f);
* will work well provided the pitch to servo controller has been tuned
* properly.
*
* @unit
* @group Fixed Wing TECS
*/
PARAM_DEFINE_FLOAT(FW_T_PTCH_DAMP, 0.0f);
@@ -399,7 +387,6 @@ PARAM_DEFINE_FLOAT(FW_T_PTCH_DAMP, 0.0f);
/**
* Height rate P factor
*
* @unit
* @group Fixed Wing TECS
*/
PARAM_DEFINE_FLOAT(FW_T_HRATE_P, 0.05f);
@@ -407,7 +394,6 @@ PARAM_DEFINE_FLOAT(FW_T_HRATE_P, 0.05f);
/**
* Height rate FF factor
*
* @unit
* @group Fixed Wing TECS
*/
PARAM_DEFINE_FLOAT(FW_T_HRATE_FF, 0.0f);
@@ -415,7 +401,6 @@ PARAM_DEFINE_FLOAT(FW_T_HRATE_FF, 0.0f);
/**
* Speed rate P factor
*
* @unit
* @group Fixed Wing TECS
*/
PARAM_DEFINE_FLOAT(FW_T_SRATE_P, 0.02f);
@@ -515,7 +500,6 @@ PARAM_DEFINE_FLOAT(FW_LND_FL_PMAX, 15.0f);
* Multiplying this factor with the minimum airspeed of the plane
* gives the target airspeed the landing approach.
*
* @unit
* @min 1.0
* @max 1.5
* @group L1 Control
src/modules/fw_pos_control_l1/mtecs/mTecs_params.c
-26
View File
@@ -57,7 +57,6 @@ PARAM_DEFINE_INT32(MT_ENABLED, 0);
* Total Energy Rate Control Feedforward
* Maps the total energy rate setpoint to the throttle setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -68,7 +67,6 @@ PARAM_DEFINE_FLOAT(MT_THR_FF, 0.7f);
* Total Energy Rate Control P
* Maps the total energy rate error to the throttle setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -79,7 +77,6 @@ PARAM_DEFINE_FLOAT(MT_THR_P, 0.1f);
* Total Energy Rate Control I
* Maps the integrated total energy rate to the throttle setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -89,7 +86,6 @@ PARAM_DEFINE_FLOAT(MT_THR_I, 0.25f);
/**
* Total Energy Rate Control Offset (Cruise throttle sp)
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -100,7 +96,6 @@ PARAM_DEFINE_FLOAT(MT_THR_OFF, 0.7f);
* Energy Distribution Rate Control Feedforward
* Maps the energy distribution rate setpoint to the pitch setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -111,7 +106,6 @@ PARAM_DEFINE_FLOAT(MT_PIT_FF, 0.4f);
* Energy Distribution Rate Control P
* Maps the energy distribution rate error to the pitch setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -122,7 +116,6 @@ PARAM_DEFINE_FLOAT(MT_PIT_P, 0.03f);
* Energy Distribution Rate Control I
* Maps the integrated energy distribution rate error to the pitch setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -133,7 +126,6 @@ PARAM_DEFINE_FLOAT(MT_PIT_I, 0.03f);
/**
* Total Energy Distribution Offset (Cruise pitch sp)
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -143,7 +135,6 @@ PARAM_DEFINE_FLOAT(MT_PIT_OFF, 0.0f);
/**
* Minimal Throttle Setpoint
*
* @unit
* @min 0.0
* @max 1.0
* @group mTECS
@@ -153,7 +144,6 @@ PARAM_DEFINE_FLOAT(MT_THR_MIN, 0.0f);
/**
* Maximal Throttle Setpoint
*
* @unit
* @min 0.0
* @max 1.0
* @group mTECS
@@ -200,7 +190,6 @@ PARAM_DEFINE_FLOAT(MT_FPA_LP, 1.0f);
* P gain for the altitude control
* Maps the altitude error to the flight path angle setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -211,7 +200,6 @@ 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
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -221,7 +209,6 @@ PARAM_DEFINE_FLOAT(MT_FPA_D, 0.0f);
/**
* Lowpass for FPA error derivative calculation (see MT_FPA_D)
*
* @unit
* @group mTECS
*/
PARAM_DEFINE_FLOAT(MT_FPA_D_LP, 1.0f);
@@ -250,7 +237,6 @@ PARAM_DEFINE_FLOAT(MT_FPA_MAX, 30.0f);
/**
* Lowpass (cutoff freq.) for airspeed
*
* @unit
* @group mTECS
*/
PARAM_DEFINE_FLOAT(MT_A_LP, 0.5f);
@@ -258,7 +244,6 @@ PARAM_DEFINE_FLOAT(MT_A_LP, 0.5f);
/**
* Airspeed derivative calculation lowpass
*
* @unit
* @group mTECS
*/
PARAM_DEFINE_FLOAT(MT_AD_LP, 0.5f);
@@ -267,7 +252,6 @@ PARAM_DEFINE_FLOAT(MT_AD_LP, 0.5f);
* P gain for the airspeed control
* Maps the airspeed error to the acceleration setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -278,7 +262,6 @@ PARAM_DEFINE_FLOAT(MT_ACC_P, 0.3f);
* D gain for the airspeed control
* Maps the change of airspeed error to the acceleration setpoint
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -288,7 +271,6 @@ PARAM_DEFINE_FLOAT(MT_ACC_D, 0.0f);
/**
* Lowpass for ACC error derivative calculation (see MT_ACC_D)
*
* @unit
* @group mTECS
*/
PARAM_DEFINE_FLOAT(MT_ACC_D_LP, 0.5f);
@@ -312,7 +294,6 @@ PARAM_DEFINE_FLOAT(MT_ACC_MAX, 40.0f);
/**
* Minimal throttle during takeoff
*
* @unit
* @min 0.0
* @max 1.0
* @group mTECS
@@ -322,7 +303,6 @@ PARAM_DEFINE_FLOAT(MT_TKF_THR_MIN, 1.0f);
/**
* Maximal throttle during takeoff
*
* @unit
* @min 0.0
* @max 1.0
* @group mTECS
@@ -352,7 +332,6 @@ PARAM_DEFINE_FLOAT(MT_TKF_PIT_MAX, 45.0f);
/**
* Minimal throttle in underspeed mode
*
* @unit
* @min 0.0
* @max 1.0
* @group mTECS
@@ -362,7 +341,6 @@ PARAM_DEFINE_FLOAT(MT_USP_THR_MIN, 1.0f);
/**
* Maximal throttle in underspeed mode
*
* @unit
* @min 0.0
* @max 1.0
* @group mTECS
@@ -392,7 +370,6 @@ PARAM_DEFINE_FLOAT(MT_USP_PIT_MAX, 0.0f);
/**
* Minimal throttle in landing mode (only last phase of landing)
*
* @unit
* @min 0.0
* @max 1.0
* @group mTECS
@@ -402,7 +379,6 @@ PARAM_DEFINE_FLOAT(MT_LND_THR_MIN, 0.0f);
/**
* Maximal throttle in landing mode (only last phase of landing)
*
* @unit
* @min 0.0
* @max 1.0
* @group mTECS
@@ -432,7 +408,6 @@ PARAM_DEFINE_FLOAT(MT_LND_PIT_MAX, 15.0f);
/**
* Integrator Limit for Total Energy Rate Control
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS
@@ -442,7 +417,6 @@ PARAM_DEFINE_FLOAT(MT_THR_I_MAX, 10.0f);
/**
* Integrator Limit for Energy Distribution Rate Control
*
* @unit
* @min 0.0
* @max 10.0
* @group mTECS