Attitude Protection Control for Side Stick-operated Aircraft

A control framework to limit aircraft Euler angles (pitch/rolling) under adverse side stick command adding is introduced. Attitude envelope of the aircraft pitch/rolling angle is discussed based on geometrical position of the aircraft relative to the ground. Control law of is established by using linearized predictive control strategy. The simulation test presents the performance of attitude protection restricting the Euler angles within the required envelop at 1,000m. Based on the test work discussed herein, the control work proposed in this paper is believed to be applicable.