Integrated Protection Control for Unstart of the Wide Speed Range Hypersonic Vehicle Inlet

被引：0
|
作者：
Li J. [1 ]
Li D. [2 ]
Liu K. [3 ]
Wu G. [3 ]
Wu Z. [1 ]
机构：
[1] School of Aeronautics and Aslnmautic, Sun Yat-sen University, Shenzhen
[2] Shenyang Aircraft Design & Research Institute, Shenyang
[3] School of Aeronautics and Astronautic, Dalian University of Technology, Dalian
来源：
Yuhang Xuebao/Journal of Astronautics | 2023年 / 44卷 / 07期
关键词：
Inlet unstart; Integrated control; Mow Fields Optimization; Wide speed range vehicle;
D O I：
10.3873/j.issn.1000-1328.2023.07.007
中图分类号：
学科分类号：
摘要：
The inlet unstart problem of the wide speed range hypersonic vehicle during maneuvering flight is a key problem that must be considered in flight control design. An integrated flight/propulsion protection and control method based on optimal inlet optimization is developed in this paper. The method can optimize? the angle of attack of the inlet flow field in real-time according to the flight condition, and the joint adjustment of the angle of attack and the expansion ratio of the combustion chamber is completed by the pole placement strategy. The simulation results show that compared with the traditional unstart protection control method, the integrated protection control method can improve the unstart stability margin of the inlet under the same design premise, reduce the unstart risk of the inlet, and avoid the adverse effects of the unstart of the inlet on the flight mission of the wide speed range hypersonic vehicle. © 2023 China Spaceflight Society. All rights reserved.
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页码：1034 / 1041
页数：7
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