A Low Cost Approach to the Design of Autopilot for Hypersonic Glider

[摘要] This paper proposes a novel integrated guidance and control (IGC) approach to improve the autopilot design with low cost for hypersonic glider in dive and pull-up phase. The main objective is robust and adaptive tracking of flight path angle (FPA) under severe flight scenarios. Firstly, the nonlinear IGC model is developed with a second order actuator dynamics. Then the adaptive command filtered back-stepping control is implemented to deal with the large aerodynamics coefficient uncertainties, control surface uncertainties and unmatched time-varying disturbances. For the autopilot, a back-stepping sliding mode control is designed to track the control surface deflection, and a nonlinear differentiator is used to avoid direct differentiating the control input. Through a series of 6-DOF numerical simulations, it's shown that the proposed scheme successfully cancels out the large uncertainties and disturbances in tracking different kinds of FPA trajectory. The contribution of this paper lies in the application and determination of nonlinear integrated design of guidance and control system for hypersonic glider.

[发布机构] School of Aerospace Science and Engineering, National University of Defense Technology, Deya Road 109, Kaifu District, Changsha, China^1

[效力级别] 工业技术

[关键词] Back-stepping controls;Control surface deflection;Guidance and control system;Hypersonic gliders;Integrated designs;Integrated guidance and control (IGC);Second-order actuator dynamics;Time-varying disturbance