Research on Reentry Trajectory of Powered Hypersonic Vehicle with Discontinuous Ignition

doi:10.3969/j.issn.1000-1093.2020.07.007

Abstract

Abstract: Discontinuous ignition boost for powered hypersonic vehicle could effectively improve the flexibility and maneuverability of reentry vehicle. To analyze the influences of ignition time and boost time on the reentry trajectory, the modified Gaussian pseudo-spectral method was used to optimize the reentry trajectory with different ignition time and boost duration. When the engine is off, the Gauss pseudospectral method is used to generate the optimal reentry trajectory that meets multi-constraints. After the engine is ignited, the reentry trajectory is calculated and generated by numerical integration according to the given control input. Additional constraint conditions are added to ensure the continuity of vehicle states between each pair of phases. Four typical moments (A, B, C, D) in the reentry process were selected to perform the first and second ignitions of the engine, and the simulations were designed with the target of maximum lateral range. The results show that the improved Gauss pseudospectral method could effectively solve the reentry trajectory optimization for powered hypersonic vehicle with discontinuous ignition. When the total impulse of the engine is given, the ignition timing has a significant effect on the reentry trajectory. Key

Key words: poweredhypersonicvehicle, reentrytrajectoryoptimization, discontinuousignition, multi-phaseGausspseudospectralmethod

CLC Number:

V412.4⁺4

LIN Jun, HE Yingzi, HUANG Panxing. Research on Reentry Trajectory of Powered Hypersonic Vehicle with Discontinuous Ignition[J]. Acta Armamentarii, 2020, 41(7): 1307-1316.

References

［1］金涛.高超声速飞行器轨迹优化研究[D].南京:南京航空航天大学, 2014.
JIN T.Research on trajectory optimization of hypersonic vehicle[D].Nanjing: Nanjing University of Aeronautics and Astronautics, 2014. (in Chinese)
[2］ ELNAGAR G L, KAZEMI M A. Pseudospectral Chebyshev optimal control of constrained nonlinear dynamical systems [J].Computational Optimization and Applications,1998,11(2): 195-217.
[3］雍恩米, 唐国金, 陈磊. 基于Gauss伪谱方法的高超声速飞行器再入轨迹快速优化[J]. 宇航学报, 2008, 29(6): 1766-1772.
YONG E M, TANG G J, CHEN L. Rapid trajectory optimization for hypersonic reentry vehicle via gauss pseudospectral method [J]. Journal of Astronautics, 2008, 29(6): 1766-1772. (in Chinese)
[4］ BENSON D.A Gauss pseudospectral transcription for optimal control[D].Cambridge, MA，US:MIT, 2005.
[5］ HUNTINGTON G T. Advancement and analysis of a Gauss pseudospectral transcription for optimal control problems[D]. Cambridge, MA, US: MIT, 2007.
[6］李沐淋. 货运飞船和制品返回舱返回轨道设计[D]. 长沙: 国防科学技术大学, 2013.
LI M L. Return trajectory design of cargo spacecraft and sample return capsule [D]. Changsha: National University of Defense Technology, 2013. (in Chinese)
[7］杨希祥, 张为华. 基于Gauss伪谱法的固体运载火箭上升段轨迹快速优化研究[J]. 宇航学报, 2011, 32(1): 15-21.
YANG X X, ZHANG W H. Rapid optimization of ascent trajectory for solid launch vehicles based on Gauss pseudosepctral method [J]. Journal of Astronautics, 2011, 32(1): 15-21. (in Chinese)
[8］刘超越, 张成. 基于高斯伪谱法的二级助推战术火箭多阶段轨迹优化[J]. 兵工学报, 2019, 40(2): 292-302.
LIU C Y, ZHANG C. Multi-stage trajectory optimization of tactical two-stage booster rocket based on Gauss pseudospectral method[J]. Acta Armamentarii, 2019, 40(2): 292-302. (in Chinese)
[9］张志国, 余梦伦, 耿光有, 等. 应用伪谱法的运载火箭在线制导方法研究[J]. 宇航学报, 2017, 38(3): 262-269.
ZHANG Z G, YU M L, GENG G Y, et al. Research on application of pseudo-spectral method in online guidance method for a launch vehicle[J]. Journal of Astronautics, 2017, 38(3): 262-269. (in Chinese)

[10］彭祺擘, 李海阳, 沈红新, 等. 基于Gauss伪谱法和直接打靶法结合的月球定点着陆轨道优化[J]. 国防科技大学学报, 2012, 34(2): 119-124.
PENG Q B, LI H Y, SHEN H X, et al. Lunar exact-landing trajectory optimization via the method combining GPM with direct shooting method [J]. Journal of National University of Defense Technology, 2012, 34(2): 119-124. (in Chinese)
[11］袁宴波, 张科, 薛晓东. 基于Radau伪谱法的制导炸弹最优滑翔弹道研究[J]. 兵工学报, 2014, 35(8): 1179-1186.
YUAN Y B, ZHANG K, XUE X D. Optimization of glide trajectory of guided bombs using a Radau pseudo-spectral method [J]. Acta Armamentarii, 2014, 35(8): 1179-1186. (in Chinese)
[12］ JORRIS T R, COBB R G. Three-dimensional trajectory optimization satisfying waypoint and no-fly zone constraints [J]. Journal of Guidance Control and Dynamics, 2009, 32(2): 551-571.
[13］ ZHAO J, ZHOU R. Reentry trajectory optimization for hypersonic vehicle satisfying complex constraints [J]. Chinese Journal of Aeronautics, 2013, 26(6): 1544-1553.
[14］张合新, 宫梓丰, 蔡光斌, 等. 复杂约束条件下的高超声速飞行器再入轨迹优化[J]. 兵器装备工程学报, 2019, 40(1): 1-6.
ZHANG H X, GONG Z F, CAI G B, et al. Reentry tracking control of hypersonic vehicle with complicated constraints[J]. Journal of Ordnance Equipment Engineering, 2019, 40(1):1-6. (in Chinese)
[15］ MAO Y F, ZHANG D L, WANG L. Reentry trajectory optimization for hypersonic vehicle based on improved Gauss pseudospectral method [J]. Soft Computing, 2017, 21(16): 4583-4592.
[16］ ZHANG Y L, LIU L H, TANG G J, et al. Trajectory generation of heat load test based on Gauss pseudospectral method [J]. Science China (Technological Sciences), 2018, 61(2): 273-284.
[17］王劲博, 崔乃刚, 郭继锋, 等. 火箭返回着陆问题高精度快速轨迹优化算法[J]. 控制理论与应用, 2018, 35(3): 389-398.
WANG J B, CUI N G, GUO J F, et al. High precision rapid trajectory optimization algorithm for launch vehicle landing[J]. Control Theory and Application, 2018, 35(3): 389-398. (in Chinese)
[18］ D′SOUZA N S, SARIGUL-KLIJIN N. Survey of planetary entry guidance algorithms [J]. Process in Aerospace Sciences, 2014, 68: 64-74.
[19］ BENSON D A, HUNTINGTON G T, THORVALDSEN T P, et al. Direct trajectory optimization and costate estimation via an orthogonal collocation method[J]. Journal of Guidance, Control and Dynamics, 2006, 29(6): 1435-1440.
[20］蔺君, 何英姿, 黄盘兴. 基于改进分段Gauss伪谱法的带推力高超声速飞行器再入轨迹规划[J]. 控制理论与应用, 2019, 36(10): 1662-1671.
LIN J, HE Y Z, HUANG P X. Powered hypersonic vehicle reentry trajectory optimization based on improved multi-phase pseudospectral method [J]. Control Theory and Application, 2019, 36(10): 1662-1671. (in Chinese)
[21］ PHILLIPS T H. A common aero vehicle (CAV) model, description, and employment guide[R]. New York, NY，US: Schafer Corporation for AFRL and AFSPC, 2003.
[22］赵吉松, 龚春林, 谷良贤. 有动力空间再入打击飞行器航迹优化[J]. 飞行力学, 2008, 26(4): 39-42,46.
ZHAO J S, GONG C L, GU L X. Trajectory optimization of prompt space reentry strike vehicle[J]. Flight Dynamics,2008, 26(4): 39-42,46. (in Chinese)

第41卷第7期2020 年7月
兵工学报ACTA ARMAMENTARII
Vol.41No.7Jul.2020