diff options
Diffstat (limited to 'src')
-rw-r--r-- | src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c | 153 |
1 files changed, 91 insertions, 62 deletions
diff --git a/src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c b/src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c index e0b8d8771..416a6fcfc 100644 --- a/src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c +++ b/src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c @@ -40,12 +40,10 @@ */ #include <nuttx/config.h> - #include <systemlib/param/param.h> /* * Controller parameters, accessible via MAVLink - * */ /** @@ -119,7 +117,6 @@ PARAM_DEFINE_FLOAT(FW_P_LIM_MIN, -45.0f); */ PARAM_DEFINE_FLOAT(FW_P_LIM_MAX, 45.0f); - /** * Controller roll limit * @@ -131,17 +128,18 @@ PARAM_DEFINE_FLOAT(FW_P_LIM_MAX, 45.0f); */ PARAM_DEFINE_FLOAT(FW_R_LIM, 45.0f); -/* +/** * Throttle limit max * * This is the maximum throttle % that can be used by the controller. * For overpowered aircraft, this should be reduced to a value that * provides sufficient thrust to climb at the maximum pitch angle PTCH_MAX. * -*/ + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_THR_MAX, 1.0f); -/* +/** * Throttle limit min * * This is the minimum throttle % that can be used by the controller. @@ -152,19 +150,22 @@ PARAM_DEFINE_FLOAT(FW_THR_MAX, 1.0f); * * For aircraft with internal combustion engine this parameter should be set * for desired idle rpm. -*/ + * + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_THR_MIN, 0.0f); -/* +/** * Throttle limit value before flare * * This throttle value will be set as throttle limit at FW_LND_TLALT, * before arcraft will flare. -*/ + * + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_THR_LND_MAX, 1.0f); - -/* +/** * Maximum climb rate * * This is the best climb rate that the aircraft can achieve with @@ -179,21 +180,23 @@ PARAM_DEFINE_FLOAT(FW_THR_LND_MAX, 1.0f); * 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. @@ -201,41 +204,45 @@ PARAM_DEFINE_FLOAT(FW_T_SINK_MIN, 2.0f); * 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^2) @@ -243,11 +250,12 @@ PARAM_DEFINE_FLOAT(FW_T_INTEG_GAIN, 0.1f); * 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 @@ -255,12 +263,12 @@ PARAM_DEFINE_FLOAT(FW_T_VERT_ACC, 7.0f); * 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 @@ -268,11 +276,12 @@ PARAM_DEFINE_FLOAT(FW_T_HGT_OMEGA, 3.0f); * 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 @@ -283,11 +292,12 @@ PARAM_DEFINE_FLOAT(FW_T_SPD_OMEGA, 2.0f); * 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 @@ -300,56 +310,75 @@ PARAM_DEFINE_FLOAT(FW_T_RLL2THR, 10.0f); * 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 -*/ + * + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_LND_ANG, 5.0f); -/* +/** * Landing slope length -*/ + * + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_LND_SLLR, 0.9f); -/* +/** * -*/ + * + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_LND_HVIRT, 10.0f); -/* +/** * Landing flare altitude (relative) -*/ + * + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_LND_FLALT, 15.0f); -/* +/** * Landing throttle limit altitude (relative) -*/ + * + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_LND_TLALT, 5.0f); -/* +/** * Landing heading hold horizontal distance -*/ + * + * @group L1 Control + */ PARAM_DEFINE_FLOAT(FW_LND_HHDIST, 15.0f); |