Aircraft Control Method Based on Attitude Feedback for Overload Tracking

doi:10.12382/bgxb.2021.0111

Abstract

Abstract: For aircraft whose control forces and moments are provided by aerodynamic rudder, a method of the control system considering the maneuverability and attitude stability is proposed depending on the nonlinear mathematical model of the pitch and yaw channel. First, based on the equivalent conversion between the overload and attitude of aircraft, the accurate attitude angle command is obtained according to the overload command calculated by the guidance law. And then, using attitude feedback as the main control loop and overload compensation as the auxiliary, this control strategy enables the overload command to be tracked accurately. The six-degree-of-freedom simulation results demonstrate that the proposed method not only meets the requirements of overload tracking accuracy for guidance, but also achieves the purpose of robust stability control for aircraft attitude. This method is simple and reliable, and has been verified by engineering application.

Key words: vehicle, aerodynamicforce, overload, attitude, maneuverability

CLC Number:

V448.222

JIANG Limin， LIU Hailiang， CHEN Shuxuan. Aircraft Control Method Based on Attitude Feedback for Overload Tracking[J]. Acta Armamentarii, 2022, 43(8): 1835-1844.

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