Roll-Pitch-Yaw Integrated Robust Autopilot Design for a High Angle-of-Attack Missile

This paper explores the feasibility of roll–pitch–yaw integrated autopilots for a high angle-of-attack missile. Investigation of the aerodynamic characteristics indicates strong cross-coupling effects between the motions in longitudinal and lateral directions. Robust control techniques based on H1 synthesis are employed to design roll– pitch–yaw integrated autopilots. The performance of the proposed roll–pitch–yaw integrated controller is tested in high-fidelity nonlinear 5-degree-of-freedom simulations. The proposed controllers are scheduled as a function of total angle of attack in a linear parameter varying framework with proportional navigation guidance laws. The integrated controller demonstrates satisfactory performance that cannot be achieved by the controller designed in a decoupled manner.