Patent ID: 6450456
Filing Date: 2002-09-17
Classification: G05D

Abstract:
An airborne safe landing power control system for an aircraft including an autothrottle system with a landing mode and a minimum airspeed program as a function of altitude during a landing maneuver, a radio altimeter for sensing the instantaneous altitude of an aircraft, means for sensing the aircraft's airspeed and comparator means for comparing the programmed airspeed with the actual airspeed at a given altitude and throttle retard means for decreasing the engine thrust when the actual airspeed exceeds the programmed airspeed at any given altitude, and first inhibiting means for inhibiting the throttle retard means when the aircraft's altitude as determined by said radio altimeter indicates that the aircraft is above a preselected altitude for the start of a landing maneuver and second inhibiting means for inhibiting the throttle retard means if the airspeed drops below the programmed airspeed.