Patent ID: 8583293
Filing Date: 2013-11-12
Classification: B64C

Abstract:
1. A flight control surface actuation system, comprising: a plurality of differential pressure (DP) sensors, each DP sensor configured to sense a differential fluid pressure across a hydraulically-operated actuator and supply a differential pressure signal representative of the sensed differential fluid pressure; a plurality of user interface sensors, each user interface sensor configured to sense movement of a user interface and supply a position command signal representative of the sensed movement; a position sensor configured to sense flight control surface position and supply a flight control surface position signal representative of the sensed flight control surface position; a flight control module coupled to receive the differential pressure signals, the position command signals, and the flight control surface position signal, the flight control module configured to process these signals and generate a plurality of force fight command signals; and a plurality of actuator controls, each actuator control coupled to receive one of the force fight command signals and one of the position command signals and configured, in response to these signals, to supply a plurality of substantially equal actuator commands, wherein the flight control module comprises a force fight mitigation function that comprises: