Rapid ascent trajectory optimization of rocket⁃based combined cycle hypersonic vehicle

被引:0
作者
Yan X. [1 ]
Wang S. [2 ]
Wang P. [1 ]
Liu H. [1 ]
机构
[1] School of Astronautics, Northwestern Polytechnical University, Xi′an
[2] COMAC Flight Test Center, Shanghai
来源
Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University | 2023年 / 41卷 / 06期
关键词
ascent trajectory optimization; hypersonic vehicle; rocket⁃based combined cycle; second⁃order lag of control system; sequential convex op⁃ timization;
D O I
10.1051/jnwpu/20234161064
中图分类号
学科分类号
摘要
The ascent trajectory design of a rocket⁃based combined cycle (RBCC) hypersonic vehicle has many typical characteristics, including the complex working mode of the RBCC power system, strong coupling between thrust and flight state, strong nonlinear model and many complex constraints etc. This paper proposes a rapid trajec⁃ tory optimization method based on sequential convex optimization to optimize the complex ascent trajectory with the RBCC power system. Firstly, a mathematical model for optimizing the ascent trajectory of the RBCC hypersonic ve⁃ hicle is established to describe the angle of attack control system with and without the second⁃order lag. Then, the optimization model is made convex and discretized based on the convex optimization theory, and a trajectory optimi⁃ zation strategy is improved. Finally, taking the maximum terminal mechanical energy as optimization objective, the ascent trajectory optimization is simulated in cases with and without the second⁃order lag in the angle of attack con⁃ trol system. The simulation results show that the proposed mathematical model and the ascent trajectory optimization method are rapid and reliable and that the optimization results meet the characteristics of the RBCC power system and provide reference for the application of a RBCC power system and the design of an angle of attack control sys⁃ tem. ©2023 Journal of Northwestern Polytechnical University.
引用
收藏
页码:1064 / 1072
页数:8
相关论文
共 15 条
[1]  
GONG C, CHEN B, GU L., Design and optimization of RBCC powered suborbital reusable launch vehicle, Proceedings of AIAA International Space Planes & Hypersonic Systems & Technologies Conference, (2013)
[2]  
WANG Yajun, HE Guoqiang, QIN Fei, Et al., Research progress of rocket based combined cycle engines, Journal of Astro⁃ nautics, 40, 10, pp. 1126-1133, (2019)
[3]  
RUAN Jiangang, HE Guoqiang, LYU Xiang, Trajectory optimization method in two⁃stage⁃to⁃orbit RBCC⁃RKT launch vehicle, Acta Aeronautica et Astronautica Sinica, 35, 5, pp. 1284-1291, (2014)
[4]  
LYU Xiang, HE Guoqiang, LIU Peijin, Ascent trajectory design method for RBCC⁃powered vehicle, Acta Aeronautica et Astronautica Sinica, 31, 7, pp. 1332-1337, (2010)
[5]  
LI Huifeng, LI Zhaoying, Indirect method of optimal ascent guidance for hypersonic vehicle, Journal of Astronautics, 32, 2, (2011)
[6]  
DEREK J, DRISCOLL F., Minimum⁃fuel ascent of a hypersonic vehicle using surrogate optimization, Journal of Aircraft, 51, 6, (2014)
[7]  
WEI J L, TANG X J, YAN J., Costate estimation for a multiple⁃interval pseudospectral method using collocation at the flipped Legendre⁃Gauss⁃Radau points, IEEE/ CAA Journal of Automatica Sinica, 12, pp. 1-15, (2018)
[8]  
ZHOU H Y, WANG X G, BAI Y L, Et al., Ascent phase trajectory optimization for vehicle with multi⁃combined cycle engine based on improved particle swarm optimization, Acta Astronautica, 140, pp. 156-165, (2017)
[9]  
YANG S B, CUI T, HAO X Y, Et al., Trajectory optimization for a ramjet⁃powered vehicle in ascent phase via the Gauss pseudospectral method, Aerospace Science and Technology, 67, pp. 88-95, (2017)
[10]  
LU Ping, LIU Xinfu, Solving nonconvex optimal control problems by convex optimization, Journal of Guidance, Control, and Dynamics, 37, 3, pp. 750-765, (2014)