Attitude Control Law Design Based on LQR for a Compound High-speed Helicopter

A new configuration of high-speed helicopter is taken as the research object, and its nonlinear flight dynamics model is established. Based on the small disturbance theory, the nonlinear model is analytically linearized to obtain the state-space equations of the compound high-speed helicopter in hover state. A state feedback linear quadratic regulator(LQR) is used to design the attitude control law, and the closed-loop control simulation is conducted in the Matlab/Simulink simulation environment. The simulation results show that the attitude control law designed in this paper can realize rapid and reliable tracking of the attitude angles, and meet the hover requirements of the compound high-speed helicopter.