diff options
Diffstat (limited to 'src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c')
| -rw-r--r-- | src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c | 60 |
1 files changed, 47 insertions, 13 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 52128e1b7..41c374407 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 @@ -83,6 +83,17 @@ PARAM_DEFINE_FLOAT(FW_L1_DAMPING, 0.75f); PARAM_DEFINE_FLOAT(FW_THR_CRUISE, 0.7f); /** + * Throttle max slew rate + * + * Maximum slew rate for the commanded throttle + * + * @min 0.0 + * @max 1.0 + * @group L1 Control + */ +PARAM_DEFINE_FLOAT(FW_THR_SLEW_MAX, 0.0f); + +/** * Negative pitch limit * * The minimum negative pitch the controller will output. @@ -155,6 +166,18 @@ PARAM_DEFINE_FLOAT(FW_THR_MIN, 0.0f); PARAM_DEFINE_FLOAT(FW_THR_LND_MAX, 1.0f); /** + * Climbout Altitude difference + * + * If the altitude error exceeds this parameter, the system will climb out + * with maximum throttle and minimum airspeed until it is closer than this + * distance to the desired altitude. Mostly used for takeoff waypoints / modes. + * Set to zero to disable climbout mode (not recommended). + * + * @group L1 Control + */ +PARAM_DEFINE_FLOAT(FW_CLMBOUT_DIFF, 25.0f); + +/** * Maximum climb rate * * This is the best climb rate that the aircraft can achieve with @@ -181,7 +204,7 @@ PARAM_DEFINE_FLOAT(FW_T_CLMB_MAX, 5.0f); * set to THR_MIN and flown at the same airspeed as used * to measure FW_T_CLMB_MAX. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_SINK_MIN, 2.0f); @@ -194,7 +217,7 @@ PARAM_DEFINE_FLOAT(FW_T_SINK_MIN, 2.0f); * exceeding the lower pitch angle limit and without over-speeding * the aircraft. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_SINK_MAX, 5.0f); @@ -205,17 +228,28 @@ PARAM_DEFINE_FLOAT(FW_T_SINK_MAX, 5.0f); * Smaller values make it faster to respond, larger values make it slower * to respond. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_TIME_CONST, 5.0f); /** + * TECS Throttle time constant + * + * This is the time constant of the TECS throttle control algorithm (in seconds). + * Smaller values make it faster to respond, larger values make it slower + * to respond. + * + * @group Fixed Wing TECS + */ +PARAM_DEFINE_FLOAT(FW_T_THRO_CONST, 8.0f); + +/** * 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 + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_THR_DAMP, 0.5f); @@ -227,7 +261,7 @@ PARAM_DEFINE_FLOAT(FW_T_THR_DAMP, 0.5f); * and height offsets are trimmed out, but reduces damping and * increases overshoot. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_INTEG_GAIN, 0.1f); @@ -240,7 +274,7 @@ PARAM_DEFINE_FLOAT(FW_T_INTEG_GAIN, 0.1f); * allows for reasonably aggressive pitch changes if required to recover * from under-speed conditions. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_VERT_ACC, 7.0f); @@ -253,7 +287,7 @@ PARAM_DEFINE_FLOAT(FW_T_VERT_ACC, 7.0f); * the solution more towards use of the barometer, whilst reducing it weights * the solution more towards use of the accelerometer data. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_HGT_OMEGA, 3.0f); @@ -266,7 +300,7 @@ PARAM_DEFINE_FLOAT(FW_T_HGT_OMEGA, 3.0f); * more towards use of the arispeed sensor, whilst reducing it weights the * solution more towards use of the accelerometer data. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_SPD_OMEGA, 2.0f); @@ -282,7 +316,7 @@ 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. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_RLL2THR, 10.0f); @@ -300,7 +334,7 @@ PARAM_DEFINE_FLOAT(FW_T_RLL2THR, 10.0f); * Note to Glider Pilots - set this parameter to 2.0 (The glider will * adjust its pitch angle to maintain airspeed, ignoring changes in height). * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_SPDWEIGHT, 1.0f); @@ -312,21 +346,21 @@ PARAM_DEFINE_FLOAT(FW_T_SPDWEIGHT, 1.0f); * will work well provided the pitch to servo controller has been tuned * properly. * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_PTCH_DAMP, 0.0f); /** * Height rate P factor * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_HRATE_P, 0.05f); /** * Speed rate P factor * - * @group L1 Control + * @group Fixed Wing TECS */ PARAM_DEFINE_FLOAT(FW_T_SRATE_P, 0.05f); |