Design of Aircraft Center of Gravity Control Law Based on Sliding Mode Control

A sliding mode based active center of gravity control law is designed for the aircraft with center of gravity varying during flight. As the basis, the general scheme of the active center of gravity control system is proposed, and the mathematic model of aircraft center of gravity varying with fuel transfer is established. Then, the center of gravity control law based on sliding mode control theory is designed, which can guarantee the control error converges to zero in finite time. Finally, simulations are carried out to verify the proposed method. Simulation results show that the sliding mode based center of gravity control law can accurately and rapidly track the given command for various different fuel transfer conditions.