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

被引：0
作者：
Liu K. [1 ,2 ]
Guo J. [3 ]
Zhou W.-Y. [1 ,2 ]
She Z.-Y. [3 ]
机构：
[1] School of Aeronautics and Astronautics, Dalian University of Technology, Dalian
[2] Key Laboratory of Advanced Technology for Aerospace Vehicles of Liaoning Province, Dalian
[3] Beijing Institute of Aerospace Technology, Beijing
来源：
Yuhang Xuebao/Journal of Astronautics | 2020年 / 41卷 / 08期
关键词：
Ascent guidance; Hypersonic vehicle; Trajectory linearization control; Trajectory optimization;
D O I：
10.3873/j.issn.1000-1328.2020.08.005
中图分类号：
学科分类号：
摘要：
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. © 2020, Editorial Dept. of JA. All right reserved.
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页码：1023 / 1031
页数：8
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