Trajectory multi-objective optimization for hypersonic telescopic wing morphing aircraft

被引：0

作者：

Peng W. ^{[1
]}

Yang T. ^{[1
]}

Wang C. ^{[2
]}

Feng Z. ^{[1
]}

Tu J. ^{[2
]}

机构：

[1] College of Aeronautics and Astronautics, National University of Defense Technology, Changsha

[2] China Academy of Launch Vehicle Technology, Beijing

来源：

Guofang Keji Daxue Xuebao/Journal of National University of Defense Technology | 2019年 / 41卷 / 01期

关键词：

Hypersonic; Morphing aircraft; Multi-objective optimization; Telescopic wing; Trajectory optimization;

D O I：

10.11887/j.cn.201901007

中图分类号：

学科分类号：

摘要：

In order to explore the application of morphing technology in hypersonic aircraft, a hypersonic morphing aircraft based on telescopic wing was proposed. Then the trajectory of glide phase was optimized through multi-objective optimization method. Firstly, the aerodynamic characteristics of different telescopic morphing phases were offered, the 3- degree of freedom dynamic model of free glide phase and the heat flux model of the leading edge of the wing were built. In the MOP (multi-objective optimization problem), the two optimization objectives were the range of trajectory, and the total heat of the leading edge of the wing. The optimization variables include the Mach numbers when the aircraft was morphing, and the angle of attack of different phases. MOP was solved by using the MOEA/D (multi-objective evolutionary algorithm based on decomposition). Numerical simulation results show that the proposed method can obtain the Pareto Front. Also, compared with the non-morphing aircraft, the aircraft can achieve a larger range and a smaller total heat of the leading edge of the wing. © 2019, NUDT Press. All right reserved.

引用

页码：41 / 47

页数：6

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