基于模型预测控制的运载火箭轨迹优化方法
Model Predictive Control Based Launch Vehicle Trajectory Optimization Method
摘要: 本文针对运载火箭上升段的轨迹优化问题的高度不确定性和严格的飞行过程约束，利用了模型预测控控制(MPC)方法来构建最优控制问题，并将其采用多重打靶法转换为非线性规划(NLP)问题，最后采用内点法进行了在线求解。本文通过利用MPC的在线预测与优化能力减小不确定性影响，以及MPC的过程约束处理能力处理强约束条件，仿真结果表明该方法能有效适应不确定性及过程约束要求。
Abstract: A model predictive control (MPC) based trajectory optimization method is used in this paper for the high uncertainty and strict flight process constraints at the ascending stage of the launch vehicle. The model predictive control (MPC) method is used to construct the optimal control problem, and the multiple shooting method is used to convert it into a nonlinear planning (NLP) problem. At last, the interior point method was used to solve online. By using MPC's online prediction and optimi-zation capabilities to reduce the impact of uncertainty, and MPC's process constraint processing capabilities to deal with strong constraints, the simulation results show that the method can effec-tively adapt to uncertainties and process constraints.
文章引用：陈宜成, 李冬, 李海, 闵勇. 基于模型预测控制的运载火箭轨迹优化方法[J]. 国际航空航天科学, 2020, 8(3): 49-59. https://doi.org/10.12677/JAST.2020.83007

参考文献

[1] McHenry, R.L., Brand, T.J., Long, A.D., Cockrell, B.F. and Thribodeau, J.R. (1979) Space Shuttle Ascent Guidance, Navigation, and Control. Journal of the Astronuatical Science, 27, 1-38.
[2] Smith, I.E. (1966) General Formulation of the Iterative Guidance Mode. NASA TM X-53414.
[3] Hanson, J.M. (2002) A Plan for Advanced Guidance and Control Technology for 2nd Generation Reusable Launch Vehicles. AIAA Guidance, Navigation, and Control Conference and Exhibit, Monterey, 5-8 August 2002, 1. [Google Scholar] [CrossRef] 
[4] Bryson, A.E. and Ho, Y.C. (1975) Applied Optimal Control. Hemisphere Publishing Corporation, Washington DC.
[5] Marec, J.P. (1979) Optimal Space Trajectories. Elsevier, Ams-terdam.
[6] Betts, J.T. (2010) Practical Methods for Optimal Control and Estimation Using Nonlinear Programming. SIAM, Philadelphia. [Google Scholar] [CrossRef] 
[7] Topputo, F. and Zhang, C. (2014) Survey of Direct Transcription for Low-Thrust Space Trajectory Optimization with Applications. Abstract and Applied Analysis, 2014, Article ID: 851720. [Google Scholar] [CrossRef] 
[8] Dileep, M.V., Nair, V.G., Prahalad, K.R. and Kamath, S. (2014) Trajectory Optimization of Launch Vehicles Using Steepest Descent Method—A Novel Approach Ascent Optimization for a Heavy Space Launcher. International Journal of Engineering Research and Applications, 4, 116-121.
[9] Pontryagin, L., Boltyanskii, V., Gramkrelidze, R. and Mischenko, E. (1962) The Mathematical Theory of Optimal Processes. Wiley Interscience, Hoboken.
[10] Hull, D.G. (2003) Optimal Control Theory for Applications. Springer, Berlin. [Google Scholar] [CrossRef] 
[11] Betts, J.T. (1998) Survey of Numerical Methods for Trajectory Optimization. Journal of Guidance, Control, and Dynamics, 21, 193-207. [Google Scholar] [CrossRef] 
[12] Rao, A. (2009) A Survey of Numerical Methods for Optimal Control. Advances in the Astronautical Sciences, 135, 497-528.
[13] 孙丕忠, 夏志勋, 郭振云. 水平空中发射固体有翼运载火箭轨道设计与优化[J]. 固体火箭技术, 2004, 27(2): 87-90.
[14] 田蕾, 罗亚中, 唐国金. 面向系列化要求的运载火箭性能优化软件开发[J]. 系统仿真技术及其应用学术交流会, 2005: 620-625.
[15] 张洪倩. 基于高斯伪谱法的弹道优化设计与实现[D]: [硕士学位论文]. 南京: 南京理工大学, 2014.
[16] 胡凡, 杨希祥, 江振宇, 张为华. 固体运载火箭轨迹/总体参数一体化优化设计研究[J]. 固体火箭技术, 2010(6): 599.
[17] 罗亚中, 唐国金, 梁彦刚. 近地轨道运载火箭轨迹/总体参数一体化优化设计[J]. 中国空间科学技术, 2003, 23(4): 16-21.
[18] 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.
[19] 陈思远, 夏群利, 李然. 固体火箭助推段终端多约束能量管理制导研究[J]. 系统工程与电子技术, 2016, 38(8): 1860-1866.
[20] Xu, Z. and Zhang, Q. (2018) Multi-Constrained Ascent Guidance for Solid Propellant Launch Vehicles. Aerospace Science and Technology, 76, 260-271. [Google Scholar] [CrossRef] 

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