高超声速飞行器制导控制及一体化设计方法

Review of Integrated Guidance and Control Schemes for Hypersonic Vehicles

针对高超声速飞行器制导与姿态控制问题,从慢回路质心制导、快回路绕质心姿控、制导控制联合设计和制导控制一体化设计四个层面对高超声速飞行器制导控制方法进行了总结综述。基于当前各国高超声速飞行器的发展脉络和高超声速飞行器典型飞行特点归纳总结制导与姿态控制方法的重难点;以飞行阶段为准则分别阐述了高超声速飞行器助推段、滑翔段和俯冲段的制导策略及其内涵,结合现代控制理论剖析了已成功用于高超声速飞行器姿态控制的非线性控制过程;基于已公开的有限数目的文献,对高超声速飞行器制导控制联合设计和制导控制一体化设计方法进行了分析。最后,对高超声速飞行器制导控制一体化全集成设计的思路和趋势进行了探索总结。

Aiming at the design of guidance and attitude control systems of hypersonic vehicles,the current design approaches with respect to the translational guidance strategy,rotational attitude controller design,guidance and control（GC） system design and integrated guidance and control（IGC） of hypersonic vehicles are summarized and reviewed. The emphasis and difficulty of the GC system design of hypersonic vehicles are described based on the progress of representative hypersonic vehicles all over the world and the flight characteristics of hypersonic vehicles. The gliding guidance methods and diving guidance approaches of the hypersonic vehicles are denoted,the modern control theories and attitude control techniques having been successfully employed on the hypersonic vehicles are proposed. By analyzing the public literatures with respect to the six-degree-of-freedom（6 Do F） GC system design of hypersonic vehicles,the separated GC system design approaches and IGC schemes are anatomized. Finally,the principium and trend of integrated guidance and control design of hypersonic vehicles are discussed.