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author | Lorenz Meier <lm@inf.ethz.ch> | 2014-07-31 10:25:02 +0200 |
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committer | Lorenz Meier <lm@inf.ethz.ch> | 2014-07-31 10:25:02 +0200 |
commit | 3a32ffa90b83880c5df71d615cbcb3eba5a6124a (patch) | |
tree | 96c1def067904af3f21f2ab2f33d6114dac4be05 | |
parent | 391a5c82cbe6d02136e16528b472352e8461b02a (diff) | |
parent | 39aa9112baf0120538255cf44292ff8e1ff3387c (diff) | |
download | px4-firmware-3a32ffa90b83880c5df71d615cbcb3eba5a6124a.tar.gz px4-firmware-3a32ffa90b83880c5df71d615cbcb3eba5a6124a.tar.bz2 px4-firmware-3a32ffa90b83880c5df71d615cbcb3eba5a6124a.zip |
Merge pull request #1222 from PX4/asfilter
Airspeed filtering, reinstate TECS for testing
-rw-r--r-- | ROMFS/px4fmu_common/init.d/rc.fw_defaults | 4 | ||||
-rw-r--r-- | makefiles/config_aerocore_default.mk | 1 | ||||
-rw-r--r-- | makefiles/config_px4fmu-v1_default.mk | 1 | ||||
-rw-r--r-- | makefiles/config_px4fmu-v2_default.mk | 1 | ||||
-rw-r--r-- | src/drivers/meas_airspeed/meas_airspeed.cpp | 8 | ||||
-rw-r--r-- | src/lib/ecl/module.mk | 2 | ||||
-rw-r--r-- | src/lib/external_lgpl/module.mk | 2 | ||||
-rw-r--r-- | src/modules/controllib/blocks.cpp | 3 | ||||
-rw-r--r-- | src/modules/controllib/blocks.hpp | 2 | ||||
-rw-r--r-- | src/modules/fw_pos_control_l1/fw_pos_control_l1_main.cpp | 166 | ||||
-rw-r--r-- | src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c | 176 | ||||
-rw-r--r-- | src/modules/fw_pos_control_l1/mtecs/mTecs.cpp | 1 | ||||
-rw-r--r-- | src/modules/fw_pos_control_l1/mtecs/mTecs_params.c | 18 |
13 files changed, 339 insertions, 46 deletions
diff --git a/ROMFS/px4fmu_common/init.d/rc.fw_defaults b/ROMFS/px4fmu_common/init.d/rc.fw_defaults index 3a50fcf56..3c336f295 100644 --- a/ROMFS/px4fmu_common/init.d/rc.fw_defaults +++ b/ROMFS/px4fmu_common/init.d/rc.fw_defaults @@ -11,4 +11,8 @@ then param set NAV_RTL_ALT 100 param set NAV_RTL_LAND_T -1 param set NAV_ACCEPT_RAD 50 + 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
\ No newline at end of file diff --git a/makefiles/config_aerocore_default.mk b/makefiles/config_aerocore_default.mk index 53a2ad1ab..0d3934bd0 100644 --- a/makefiles/config_aerocore_default.mk +++ b/makefiles/config_aerocore_default.mk @@ -80,6 +80,7 @@ LIBRARIES += lib/mathlib/CMSIS MODULES += lib/mathlib MODULES += lib/mathlib/math/filter MODULES += lib/ecl +MODULES += lib/external_lgpl MODULES += lib/geo MODULES += lib/geo_lookup MODULES += lib/conversion diff --git a/makefiles/config_px4fmu-v1_default.mk b/makefiles/config_px4fmu-v1_default.mk index cc0958c29..a7c10f52f 100644 --- a/makefiles/config_px4fmu-v1_default.mk +++ b/makefiles/config_px4fmu-v1_default.mk @@ -108,6 +108,7 @@ LIBRARIES += lib/mathlib/CMSIS MODULES += lib/mathlib MODULES += lib/mathlib/math/filter MODULES += lib/ecl +MODULES += lib/external_lgpl MODULES += lib/geo MODULES += lib/geo_lookup MODULES += lib/conversion diff --git a/makefiles/config_px4fmu-v2_default.mk b/makefiles/config_px4fmu-v2_default.mk index a498a1b40..d0a40445d 100644 --- a/makefiles/config_px4fmu-v2_default.mk +++ b/makefiles/config_px4fmu-v2_default.mk @@ -121,6 +121,7 @@ LIBRARIES += lib/mathlib/CMSIS MODULES += lib/mathlib MODULES += lib/mathlib/math/filter MODULES += lib/ecl +MODULES += lib/external_lgpl MODULES += lib/geo MODULES += lib/geo_lookup MODULES += lib/conversion diff --git a/src/drivers/meas_airspeed/meas_airspeed.cpp b/src/drivers/meas_airspeed/meas_airspeed.cpp index 6ab437716..9cfa7f383 100644 --- a/src/drivers/meas_airspeed/meas_airspeed.cpp +++ b/src/drivers/meas_airspeed/meas_airspeed.cpp @@ -92,7 +92,7 @@ #include <drivers/airspeed/airspeed.h> /* I2C bus address is 1010001x */ -#define I2C_ADDRESS_MS4525DO 0x28 //0x51 /* 7-bit address. */ +#define I2C_ADDRESS_MS4525DO 0x28 /**< 7-bit address. Depends on the order code (this is for code "I") */ #define PATH_MS4525 "/dev/ms4525" /* The MS5525DSO address is 111011Cx, where C is the complementary value of the pin CSB */ #define I2C_ADDRESS_MS5525DSO 0x77 //0x77/* 7-bit address, addr. pin pulled low */ @@ -102,9 +102,9 @@ #define ADDR_READ_MR 0x00 /* write to this address to start conversion */ /* Measurement rate is 100Hz */ -#define MEAS_RATE 100.0f -#define MEAS_DRIVER_FILTER_FREQ 3.0f -#define CONVERSION_INTERVAL (1000000 / 100) /* microseconds */ +#define MEAS_RATE 100 +#define MEAS_DRIVER_FILTER_FREQ 1.5f +#define CONVERSION_INTERVAL (1000000 / MEAS_RATE) /* microseconds */ class MEASAirspeed : public Airspeed { diff --git a/src/lib/ecl/module.mk b/src/lib/ecl/module.mk index f2aa3db6a..93a5b511f 100644 --- a/src/lib/ecl/module.mk +++ b/src/lib/ecl/module.mk @@ -39,3 +39,5 @@ SRCS = attitude_fw/ecl_pitch_controller.cpp \ attitude_fw/ecl_roll_controller.cpp \ attitude_fw/ecl_yaw_controller.cpp \ l1/ecl_l1_pos_controller.cpp + +MAXOPTIMIZATION = -Os diff --git a/src/lib/external_lgpl/module.mk b/src/lib/external_lgpl/module.mk index 53f1629e3..29d3514f6 100644 --- a/src/lib/external_lgpl/module.mk +++ b/src/lib/external_lgpl/module.mk @@ -46,3 +46,5 @@ # SRCS = tecs/tecs.cpp + +MAXOPTIMIZATION = -Os diff --git a/src/modules/controllib/blocks.cpp b/src/modules/controllib/blocks.cpp index 0175acda9..f739446fa 100644 --- a/src/modules/controllib/blocks.cpp +++ b/src/modules/controllib/blocks.cpp @@ -121,6 +121,9 @@ int blockLimitSymTest() float BlockLowPass::update(float input) { + if (!isfinite(getState())) { + setState(input); + } float b = 2 * float(M_PI) * getFCut() * getDt(); float a = b / (1 + b); setState(a * input + (1 - a)*getState()); diff --git a/src/modules/controllib/blocks.hpp b/src/modules/controllib/blocks.hpp index 37d7832b3..bffc355a8 100644 --- a/src/modules/controllib/blocks.hpp +++ b/src/modules/controllib/blocks.hpp @@ -114,7 +114,7 @@ public: // methods BlockLowPass(SuperBlock *parent, const char *name) : Block(parent, name), - _state(0), + _state(0.0f/0.0f /* initialize to invalid val, force into is_finite() check on first call */), _fCut(this, "") // only one parameter, no need to name {}; virtual ~BlockLowPass() {}; diff --git a/src/modules/fw_pos_control_l1/fw_pos_control_l1_main.cpp b/src/modules/fw_pos_control_l1/fw_pos_control_l1_main.cpp index 0b111f7bd..eadb63f40 100644 --- a/src/modules/fw_pos_control_l1/fw_pos_control_l1_main.cpp +++ b/src/modules/fw_pos_control_l1/fw_pos_control_l1_main.cpp @@ -42,8 +42,8 @@ * Proceedings of the AIAA Guidance, Navigation and Control * Conference, Aug 2004. AIAA-2004-4900. * - * Implementation for total energy control class: - * Thomas Gubler + * Original implementation for total energy control class: + * Paul Riseborough and Andrew Tridgell, 2013 (code in lib/external_lgpl) * * More details and acknowledgements in the referenced library headers. * @@ -87,10 +87,13 @@ #include <mavlink/mavlink_log.h> #include <launchdetection/LaunchDetector.h> #include <ecl/l1/ecl_l1_pos_controller.h> +#include <external_lgpl/tecs/tecs.h> #include <drivers/drv_range_finder.h> #include "landingslope.h" #include "mtecs/mTecs.h" +static int _control_task = -1; /**< task handle for sensor task */ + /** * L1 control app start / stop handling function @@ -115,9 +118,9 @@ public: /** * Start the sensors task. * - * @return OK on success. + * @return OK on success. */ - int start(); + static int start(); /** * Task status @@ -131,7 +134,6 @@ private: bool _task_should_exit; /**< if true, sensor task should exit */ bool _task_running; /**< if true, task is running in its mainloop */ - int _control_task; /**< task handle for sensor task */ int _global_pos_sub; int _pos_sp_triplet_sub; @@ -192,6 +194,7 @@ private: math::Matrix<3, 3> _R_nb; ///< current attitude ECL_L1_Pos_Controller _l1_control; + TECS _tecs; fwPosctrl::mTecs _mTecs; bool _was_pos_control_mode; @@ -199,6 +202,21 @@ private: float l1_period; float l1_damping; + float time_const; + float min_sink_rate; + float max_sink_rate; + float max_climb_rate; + float heightrate_p; + float speedrate_p; + 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; @@ -226,6 +244,21 @@ 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 heightrate_p; + param_t speedrate_p; + 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; @@ -361,7 +394,6 @@ FixedwingPositionControl::FixedwingPositionControl() : _mavlink_fd(-1), _task_should_exit(false), _task_running(false), - _control_task(-1), /* subscriptions */ _global_pos_sub(-1), @@ -438,6 +470,21 @@ 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(); } @@ -488,6 +535,22 @@ 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)); + param_get(_parameter_handles.land_slope_angle, &(_parameters.land_slope_angle)); param_get(_parameter_handles.land_H1_virt, &(_parameters.land_H1_virt)); param_get(_parameter_handles.land_flare_alt_relative, &(_parameters.land_flare_alt_relative)); @@ -500,6 +563,23 @@ FixedwingPositionControl::parameters_update() _l1_control.set_l1_period(_parameters.l1_period); _l1_control.set_l1_roll_limit(math::radians(_parameters.roll_limit)); + _tecs.set_time_const(_parameters.time_const); + _tecs.set_min_sink_rate(_parameters.min_sink_rate); + _tecs.set_max_sink_rate(_parameters.max_sink_rate); + _tecs.set_throttle_damp(_parameters.throttle_damp); + _tecs.set_integrator_gain(_parameters.integrator_gain); + _tecs.set_vertical_accel_limit(_parameters.vertical_accel_limit); + _tecs.set_height_comp_filter_omega(_parameters.height_comp_filter_omega); + _tecs.set_speed_comp_filter_omega(_parameters.speed_comp_filter_omega); + _tecs.set_roll_throttle_compensation(_parameters.roll_throttle_compensation); + _tecs.set_speed_weight(_parameters.speed_weight); + _tecs.set_pitch_damping(_parameters.pitch_damping); + _tecs.set_indicated_airspeed_min(_parameters.airspeed_min); + _tecs.set_indicated_airspeed_max(_parameters.airspeed_max); + _tecs.set_max_climb_rate(_parameters.max_climb_rate); + _tecs.set_heightrate_p(_parameters.heightrate_p); + _tecs.set_speedrate_p(_parameters.speedrate_p); + /* sanity check parameters */ if (_parameters.airspeed_max < _parameters.airspeed_min || _parameters.airspeed_max < 5.0f || @@ -561,6 +641,9 @@ FixedwingPositionControl::vehicle_airspeed_poll() } } + /* update TECS state */ + _tecs.enable_airspeed(_airspeed_valid); + return airspeed_updated; } @@ -621,7 +704,17 @@ FixedwingPositionControl::vehicle_setpoint_poll() void FixedwingPositionControl::task_main_trampoline(int argc, char *argv[]) { + l1_control::g_control = new FixedwingPositionControl(); + + if (l1_control::g_control == nullptr) { + warnx("OUT OF MEM"); + return; + } + + /* only returns on exit */ l1_control::g_control->task_main(); + delete l1_control::g_control; + l1_control::g_control = nullptr; } float @@ -733,6 +826,14 @@ FixedwingPositionControl::control_position(const math::Vector<2> ¤t_positi float eas2tas = 1.0f; // XXX calculate actual number based on current measurements + /* filter speed and altitude for controller */ + math::Vector<3> accel_body(_sensor_combined.accelerometer_m_s2); + math::Vector<3> accel_earth = _R_nb * accel_body; + + if (!_mTecs.getEnabled()) { + _tecs.update_50hz(_global_pos.alt /* XXX might switch to alt err here */, _airspeed.indicated_airspeed_m_s, _R_nb, accel_body, accel_earth); + } + /* define altitude error */ float altitude_error = _pos_sp_triplet.current.alt - _global_pos.alt; @@ -758,6 +859,9 @@ FixedwingPositionControl::control_position(const math::Vector<2> ¤t_positi /* get circle mode */ bool was_circle_mode = _l1_control.circle_mode(); + /* restore speed weight, in case changed intermittently (e.g. in landing handling) */ + _tecs.set_speed_weight(_parameters.speed_weight); + /* current waypoint (the one currently heading for) */ math::Vector<2> next_wp((float)pos_sp_triplet.current.lat, (float)pos_sp_triplet.current.lon); @@ -1066,9 +1170,9 @@ FixedwingPositionControl::control_position(const math::Vector<2> ¤t_positi _att_sp.thrust = launchDetector.getThrottlePreTakeoff(); } else { - _att_sp.thrust = math::min(_mTecs.getThrottleSetpoint(), throttle_max); + _att_sp.thrust = math::min(_mTecs.getEnabled() ? _mTecs.getThrottleSetpoint() : _tecs.get_throttle_demand(), throttle_max); } - _att_sp.pitch_body = _mTecs.getPitchSetpoint(); + _att_sp.pitch_body = _mTecs.getEnabled() ? _mTecs.getPitchSetpoint() : _tecs.get_pitch_demand(); if (_control_mode.flag_control_position_enabled) { last_manual = false; @@ -1084,10 +1188,6 @@ void FixedwingPositionControl::task_main() { - /* inform about start */ - warnx("Initializing.."); - fflush(stdout); - /* * do subscriptions */ @@ -1248,20 +1348,29 @@ void FixedwingPositionControl::tecs_update_pitch_throttle(float alt_sp, float v_ const math::Vector<3> &ground_speed, tecs_mode mode) { - /* Using mtecs library: prepare arguments for mtecs call */ - float flightPathAngle = 0.0f; - float ground_speed_length = ground_speed.length(); - if (ground_speed_length > FLT_EPSILON) { - flightPathAngle = -asinf(ground_speed(2)/ground_speed_length); - } - fwPosctrl::LimitOverride limitOverride; - if (climbout_mode) { - limitOverride.enablePitchMinOverride(M_RAD_TO_DEG_F * climbout_pitch_min_rad); + if (_mTecs.getEnabled()) { + /* Using mtecs library: prepare arguments for mtecs call */ + float flightPathAngle = 0.0f; + float ground_speed_length = ground_speed.length(); + if (ground_speed_length > FLT_EPSILON) { + flightPathAngle = -asinf(ground_speed(2)/ground_speed_length); + } + fwPosctrl::LimitOverride limitOverride; + if (climbout_mode) { + limitOverride.enablePitchMinOverride(M_RAD_TO_DEG_F * climbout_pitch_min_rad); + } else { + limitOverride.disablePitchMinOverride(); + } + _mTecs.updateAltitudeSpeed(flightPathAngle, altitude, alt_sp, _airspeed.true_airspeed_m_s, v_sp, mode, + limitOverride); } else { - limitOverride.disablePitchMinOverride(); + /* Using tecs library */ + _tecs.update_pitch_throttle(_R_nb, _att.pitch, altitude, alt_sp, v_sp, + _airspeed.indicated_airspeed_m_s, eas2tas, + climbout_mode, climbout_pitch_min_rad, + throttle_min, throttle_max, throttle_cruise, + pitch_min_rad, pitch_max_rad); } - _mTecs.updateAltitudeSpeed(flightPathAngle, altitude, alt_sp, _airspeed.true_airspeed_m_s, v_sp, mode, - limitOverride); } int @@ -1295,14 +1404,7 @@ int fw_pos_control_l1_main(int argc, char *argv[]) if (l1_control::g_control != nullptr) errx(1, "already running"); - l1_control::g_control = new FixedwingPositionControl; - - if (l1_control::g_control == nullptr) - errx(1, "alloc failed"); - - if (OK != l1_control::g_control->start()) { - delete l1_control::g_control; - l1_control::g_control = nullptr; + if (OK != FixedwingPositionControl::start()) { err(1, "start failed"); } 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 27039ff51..52128e1b7 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 @@ -155,6 +155,182 @@ 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 * * @group L1 Control diff --git a/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp b/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp index 749f57a2b..afc411a60 100644 --- a/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp +++ b/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp @@ -76,6 +76,7 @@ mTecs::mTecs() : _counter(0), _debug(false) { + warnx("starting"); } mTecs::~mTecs() diff --git a/src/modules/fw_pos_control_l1/mtecs/mTecs_params.c b/src/modules/fw_pos_control_l1/mtecs/mTecs_params.c index 4ca31fe20..7cfe63fbc 100644 --- a/src/modules/fw_pos_control_l1/mtecs/mTecs_params.c +++ b/src/modules/fw_pos_control_l1/mtecs/mTecs_params.c @@ -241,7 +241,14 @@ PARAM_DEFINE_FLOAT(MT_FPA_MAX, 30.0f); * * @group mTECS */ -PARAM_DEFINE_FLOAT(MT_A_LP, 1.0f); +PARAM_DEFINE_FLOAT(MT_A_LP, 0.5f); + +/** + * Airspeed derivative calculation lowpass + * + * @group mTECS + */ +PARAM_DEFINE_FLOAT(MT_AD_LP, 0.5f); /** * P gain for the airspeed control @@ -268,7 +275,7 @@ PARAM_DEFINE_FLOAT(MT_ACC_D, 0.0f); * * @group mTECS */ -PARAM_DEFINE_FLOAT(MT_ACC_D_LP, 1.0f); +PARAM_DEFINE_FLOAT(MT_ACC_D_LP, 0.5f); /** * Minimal acceleration (air) @@ -287,13 +294,6 @@ PARAM_DEFINE_FLOAT(MT_ACC_MIN, -40.0f); PARAM_DEFINE_FLOAT(MT_ACC_MAX, 40.0f); /** - * Airspeed derivative calculation lowpass - * - * @group mTECS - */ -PARAM_DEFINE_FLOAT(MT_AD_LP, 1.0f); - -/** * Minimal throttle during takeoff * * @min 0.0f |