吸气式组合动力高超声速飞行器上升段制导方法研究  

Investigation on Ascent Guidance Law for Air-Breathing Combined-Cycle Hypersonic Vehicle

作　　者：刘凯 郭健 周文雅[1,2] 佘智勇 LIU Kai;GUO Jian;ZHOU Wen-ya;SHE Zhi-yong(School of Aeronautics and Astronautics,Dalian University of Technology,Dalian 116024,China;Key Laboratory of Advanced Technology for Aerospace Vehicles of Liaoning Province,Dalian 116024,China;Beijing Institute of Aerospace Technology,Beijing 100074,China)

机构地区：[1]大连理工大学航空航天学院,大连116024 [2]辽宁省空天飞行器前沿技术重点实验室,大连116024 [3]北京空天技术研究所,北京100074

出　　处：《宇航学报》2020年第8期1023-1031,共9页Journal of Astronautics

基　　金：国家自然科学基金(61603363,61703383,61603056)。

摘　　要：针对涡轮/冲压/火箭三组合动力水平起降高超声速飞行器爬升段飞行轨迹设计和制导律设计问题,首先考虑宽速域组合动力发动机多模态特性和高低速气动特性差异,分别开展了涡轮段、引射段、纯冲压段及冲压火箭段的飞行策略研究,提出了不同阶段的飞行攻角剖面构型和火箭流量剖面构型,将无穷维轨迹优化问题转化为有限维参数规划问题,进而完成了组合动力上升段飞行轨迹的优化设计;在此基础上,结合轨迹线性化控制方法,开展了组合动力上升段轨迹跟踪制导律设计研究,给出了保证闭环稳定性和控制品质的制导律参数设计准则,最后通过开展仿真分析说明了提出轨迹设计及制导方法的有效性。The ascent trajectory design problem of air-breathing combined-cycle hypersonic vehicle is studied in this paper. By considering the different characteristics of the combined-cycle engine and aerodynamics within the flight envelope, the flight strategy for turbo mode, ejecting mode, scram mode and scram-rocket mode is proposed respectively. Then, by constructing the proper attack angle profile and rocket flow profile, the infinity dimension optimization problem is simplified as the finite dimension parameters optimization problem, which can be solved effectively via the sequence quadratic program algorithm. Moreover, by using the trajectory linearization control approach, the tracking guidance law for the combined-cycle ascent phase is designed, and the principle for choosing the controller parameters to guarantee the stability and performance is also provided. In the end, the simulation is carried out and the results demonstrate the efficacy of the proposed design approach.

关 键 词：高超声速飞行器 轨迹优化 上升制导 轨迹线性化控制 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]