Patent ID: 8016243
Filing Date: 2011-09-13
Classification: B63C,B64D,G05D

Abstract:
1. A method for controlling an aircraft, the method comprising: processing a pilot short-period pitch control command through a fly-by-wire control system to provide corresponding short-period pitch control fly-by-wire computer gains; re-scaling the short-period pitch control computer gains to provide re-scaled short-period pitch control computer gains; commanding a full-authority digital engine control system (FADEC) with the re-scaled short-period pitch control computer gains such that the FADEC modulates engine thrust to control a short period pitch response for the aircraft; processing a pilot airspeed command through a FADEC auto-throttle to provide corresponding FADEC autothrottle control gains; re-scaling the FADEC autothrottle control gains to provide re-scaled FADEC autothrottle gains; and actuating an electric stabilizer for the aircraft according to the re-scaled FADEC autothrottle control gains to control an airspeed for the aircraft.