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In sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.c
float throttle_dif = v_ctl_auto_throttle_cruise_throttle - v_ctl_auto_throttle_nominal_cruise_throttle;
if (throttle_dif > 0) {
- float max_dif = Max(V_CTL_AUTO_THROTTLE_MAX_CRUISE_THROTTLE - v_ctl_auto_throttle_nominal_cruise_throttle, 0.1);
+ float max_dif = Max(v_ctl_auto_throttle_max_cruise_throttle - v_ctl_auto_throttle_nominal_cruise_throttle, 0.1);
elevator_trim = throttle_dif / max_dif * v_ctl_auto_throttle_dash_trim;
} else {
- float max_dif = Max(v_ctl_auto_throttle_nominal_cruise_throttle - V_CTL_AUTO_THROTTLE_MIN_CRUISE_THROTTLE, 0.1);
+ float max_dif = Max(v_ctl_auto_throttle_nominal_cruise_throttle - v_ctl_auto_throttle_min_cruise_throttle, 0.1);
elevator_trim = - throttle_dif / max_dif * v_ctl_auto_throttle_loiter_trim;
}
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