Patent ID: 8068943
Filing Date: 2011-11-29
Classification: G05D

Abstract:
1. A flight control system, the system comprising: a reference system including a first set of gyroscopes and accelerometers configured to provide a first output of a first set of inertial signals and a second output of 3-axis body rate signals based on the gyroscopes of the first set; a flight control module coupled to the reference system and receiving the first output of inertial signals, the flight control module processing the first set of inertial signals into normal mode flight control signals; actuator control electronics having a first input receiving the normal mode flight control signals and a second input receiving the second output of 3-axis body rate signals; and flight control actuators coupled to the actuator control electronics, wherein the actuator control electronics selects the normal mode flight control signals to control the flight control actuators while operating in a normal flight mode, and wherein the actuator control electronics selects the 3-axis body rate signals to control the flight control actuators while operating in a backup flight mode.