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

摘要

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