diff options
Diffstat (limited to 'src/modules/fw_att_control')
-rw-r--r-- | src/modules/fw_att_control/fw_att_control_main.cpp | 75 |
1 files changed, 47 insertions, 28 deletions
diff --git a/src/modules/fw_att_control/fw_att_control_main.cpp b/src/modules/fw_att_control/fw_att_control_main.cpp index 78952cb8d..ffad69135 100644 --- a/src/modules/fw_att_control/fw_att_control_main.cpp +++ b/src/modules/fw_att_control/fw_att_control_main.cpp @@ -619,7 +619,8 @@ FixedwingAttitudeControl::task_main() float airspeed_scaling = _parameters.airspeed_trim / airspeed; //warnx("aspd scale: %6.2f act scale: %6.2f", airspeed_scaling, actuator_scaling); - float roll_sp, pitch_sp; + float roll_sp = 0.0f; + float pitch_sp = 0.0f; float throttle_sp = 0.0f; if (_vcontrol_mode.flag_control_velocity_enabled || _vcontrol_mode.flag_control_position_enabled) { @@ -643,6 +644,7 @@ FixedwingAttitudeControl::task_main() */ roll_sp = _manual.roll * 0.75f; pitch_sp = _manual.pitch * 0.75f; + warnx("copy(2) _att_sp.roll_body %.4f", _att_sp.roll_body); throttle_sp = _manual.throttle; _actuators.control[4] = _manual.flaps; @@ -681,33 +683,50 @@ FixedwingAttitudeControl::task_main() } /* Run attitude controllers */ - _roll_ctrl.control_attitude(roll_sp, _att.roll); - _pitch_ctrl.control_attitude(pitch_sp, _att.roll, _att.pitch, airspeed); - _yaw_ctrl.control_attitude(_att.roll, _att.pitch, - speed_body_u,speed_body_w, - _roll_ctrl.get_desired_rate(), _pitch_ctrl.get_desired_rate()); //runs last, because is depending on output of roll and pitch attitude - - /* Run attitude RATE controllers which need the desired attitudes from above */ - float roll_u = _roll_ctrl.control_bodyrate(_att.pitch, - _att.rollspeed, _att.yawspeed, - _yaw_ctrl.get_desired_rate(), - _parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator); - _actuators.control[0] = (isfinite(roll_u)) ? roll_u : 0.0f; - - float pitch_u = _pitch_ctrl.control_bodyrate(_att.roll, _att.pitch, - _att.pitchspeed, _att.yawspeed, - _yaw_ctrl.get_desired_rate(), - _parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator); - _actuators.control[1] = (isfinite(pitch_u)) ? pitch_u : 0.0f; - - float yaw_u = _yaw_ctrl.control_bodyrate( _att.roll, _att.pitch, - _att.pitchspeed, _att.yawspeed, - _pitch_ctrl.get_desired_rate(), - _parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator); - _actuators.control[2] = (isfinite(yaw_u)) ? yaw_u : 0.0f; - - /* throttle passed through */ - _actuators.control[3] = (isfinite(throttle_sp)) ? throttle_sp : 0.0f; + if (isfinite(roll_sp) && isfinite(pitch_sp)) { + _roll_ctrl.control_attitude(roll_sp, _att.roll); + _pitch_ctrl.control_attitude(pitch_sp, _att.roll, _att.pitch, airspeed); + _yaw_ctrl.control_attitude(_att.roll, _att.pitch, + speed_body_u,speed_body_w, + _roll_ctrl.get_desired_rate(), _pitch_ctrl.get_desired_rate()); //runs last, because is depending on output of roll and pitch attitude + + /* Run attitude RATE controllers which need the desired attitudes from above */ + float roll_u = _roll_ctrl.control_bodyrate(_att.pitch, + _att.rollspeed, _att.yawspeed, + _yaw_ctrl.get_desired_rate(), + _parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator); + _actuators.control[0] = (isfinite(roll_u)) ? roll_u : 0.0f; + if (!isfinite(roll_u)) { + warnx("roll_u %.4f", roll_u); + } + + float pitch_u = _pitch_ctrl.control_bodyrate(_att.roll, _att.pitch, + _att.pitchspeed, _att.yawspeed, + _yaw_ctrl.get_desired_rate(), + _parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator); + _actuators.control[1] = (isfinite(pitch_u)) ? pitch_u : 0.0f; + if (!isfinite(pitch_u)) { + warnx("pitch_u %.4f, _yaw_ctrl.get_desired_rate() %.4f, airspeed %.4f, airspeed_scaling %.4f, roll_sp %.4f, pitch_sp %.4f, _roll_ctrl.get_desired_rate() %.4f, _pitch_ctrl.get_desired_rate() %.4f att_sp.roll_body %.4f", + pitch_u, _yaw_ctrl.get_desired_rate(), airspeed, airspeed_scaling, roll_sp, pitch_sp, _roll_ctrl.get_desired_rate(), _pitch_ctrl.get_desired_rate(), _att_sp.roll_body); + } + + float yaw_u = _yaw_ctrl.control_bodyrate( _att.roll, _att.pitch, + _att.pitchspeed, _att.yawspeed, + _pitch_ctrl.get_desired_rate(), + _parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator); + _actuators.control[2] = (isfinite(yaw_u)) ? yaw_u : 0.0f; + if (!isfinite(yaw_u)) { + warnx("yaw_u %.4f", yaw_u); + } + + /* throttle passed through */ + _actuators.control[3] = (isfinite(throttle_sp)) ? throttle_sp : 0.0f; + if (!isfinite(throttle_sp)) { + warnx("throttle_sp %.4f", throttle_sp); + } + } else { + warnx("Non-finite setpoint roll_sp: %.4f, pitch_sp %.4f", roll_sp, pitch_sp); + } // warnx("aspd: %s: %6.2f, aspd scaling: %6.2f, controls: %5.2f %5.2f %5.2f %5.2f", (_airspeed_valid) ? "valid" : "unknown", // airspeed, airspeed_scaling, _actuators.control[0], _actuators.control[1], |