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TECS: allow for fast descend up to maximum airspeed. Use pitch control loop to control max airspeed while giving minimal throttle.
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@@ -129,6 +129,7 @@ FixedwingPositionControl::parameters_update()
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_tecs.set_speed_weight(_param_fw_t_spdweight.get());
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_tecs.set_equivalent_airspeed_trim(_performance_model.getCalibratedTrimAirspeed());
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_tecs.set_equivalent_airspeed_min(_performance_model.getMinimumCalibratedAirspeed());
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_tecs.set_equivalent_airspeed_max(_performance_model.getMaximumCalibratedAirspeed());
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_tecs.set_throttle_damp(_param_fw_t_thr_damping.get());
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_tecs.set_integrator_gain_throttle(_param_fw_t_thr_integ.get());
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_tecs.set_integrator_gain_pitch(_param_fw_t_I_gain_pit.get());
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@@ -137,6 +138,7 @@ FixedwingPositionControl::parameters_update()
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_tecs.set_roll_throttle_compensation(_param_fw_t_rll2thr.get());
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_tecs.set_pitch_damping(_param_fw_t_ptch_damp.get());
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_tecs.set_altitude_error_time_constant(_param_fw_t_h_error_tc.get());
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_tecs.set_fast_descend_altitude_error(_param_fw_t_fast_alt_err.get());
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_tecs.set_altitude_rate_ff(_param_fw_t_hrate_ff.get());
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_tecs.set_airspeed_error_time_constant(_param_fw_t_tas_error_tc.get());
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_tecs.set_ste_rate_time_const(_param_ste_rate_time_const.get());
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