重型运载火箭轨迹/总体参数一体化优化方法 -- 西北工业大学学报,2016,34(6):1101-1107
论文:2016,Vol:34,Issue(6):1101-1107
引用本文:
孙乐园, 贾如岩, 杨枝山, 江振宇. 重型运载火箭轨迹/总体参数一体化优化方法[J]. 西北工业大学学报
Sun Leyuan, Jia Ruyan, Yang Zhishan, Jiang Zhenyu. An Integrated Optimization Method of Trajectory/System Parameters for Heavy Launch Vehicles[J]. Northwestern polytechnical university

重型运载火箭轨迹/总体参数一体化优化方法
孙乐园, 贾如岩, 杨枝山, 江振宇
国防科学技术大学 航天科学与工程学院, 湖南 长沙 410073
摘要:
研究了重型运载火箭轨迹/总体参数一体化优化问题。建立了一体化参数优化模型,设计了一种双环迭代优化算法,外环采用遗传算法进行参数优化,内环通过带自适应松弛因子的改进牛顿迭代法进行参数迭代。针对牛顿迭代法对模型本身及迭代初值敏感的问题,提出了一种模型变量筛选方法和迭代初值生成方法。基于Morris参数全局灵敏度分析法筛选出对终端等式约束影响最大的参数作为牛顿迭代变量,以历史迭代收敛值作为当前迭代初值。并通过迭代误差监控,保证了算法的鲁棒性。以三级液体重型运载火箭为对象,进行了一体化优化仿真。仿真结果显示起飞总质量减少了4.09%,表明设计的双环迭代优化算法能在复杂约束下完成重型运载火箭轨迹/总体参数一体化优化。
关键词:    重型运载火箭    一体化优化    改进牛顿迭代法    全局灵敏度分析    迭代初值   
An Integrated Optimization Method of Trajectory/System Parameters for Heavy Launch Vehicles
Sun Leyuan, Jia Ruyan, Yang Zhishan, Jiang Zhenyu
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
Abstract:
The integrated optimization of trajectory/system parameters for heavy launch vehicles was investigated. A model of integrated optimization was set up. An iterative optimization algorithm with double loops was designed. The genetic algorithm was used to optimize parameters in outer loop, and the improved Newton iteration method with an adaptive relaxation factor was used to iterate parameters in inner loop. Aiming at the susceptibility of Newton iteration method to the model and initial values, a method of model variable screening and initial iteration values generation were proposed. Based on the Morris method of global sensitivity analysis, the parameters with the biggest influence on the terminal equality constraints were taken as the Newton iteration variables. And the historic convergent iteration values were set as the current initial iteration values. And the robustness of the algorithm was ensured by monitoring of the iterative error. A liquid heavy launch vehicle with 3 levels was set as an example for integrated optimization simulation. The results showed that initial mass decreases by 4.09% and demonstrate that the iterative optimization algorithm with double loops can complete the integrated optimization of trajectory/system parameters for heavy launch vehicles with complex constraints.
Key words:    Heavy launch vehicles    Integrated optimization    Improved Newton iteration method    Global sensitivity analysis    Initial iteration values   
收稿日期: 2016-04-14     修回日期:
DOI:
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作者简介: 孙乐园(1991-),国防科学技术大学硕士研究生,主要从事飞行器总体设计与系统仿真研究。
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参考文献:
[1] 马志滨, 何麟书. 国外重型运载火箭发展趋势述评[J]. 固体火箭技术, 2012, 35(1):1-4 Ma Zhibin, He Linshu. Development Trend Review of Foreign Heavy-Lift Launch Vehicle[J]. Journal of Solid Rocket Technology, 2012, 35(1):1-4(in Chinese)
[2] 何巍, 刘伟, 龙乐豪. 重型运载火箭及其应用探讨[J]. 导弹与航天运载技术, 2011(1):1-5 He Wei, Liu Wei, Long Lehao. Heavy Launch Vehicle and Its Application[J]. Missiles and Space Vehicles, 2011(1):1-5(in Chinese)
[3] 胡凡, 杨希祥, 江振宇, 等. 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, 33(6):599-602 Hu Fan, Yang Xixiang, Jiang Zhenyu, et al. Integrated Optimization Design of Trajectory/System Parameters for Solid Launch Vehicle[J]. Journal of Solid Rocket Technology, 2010, 33(6):599-602(in Chinese)
[4] 肖飞, 向敏, 张为华. 多级固体运载火箭总体/弹道/轨道一体化设计与优化[J]. 空军工程大学学报, 2008, 9(5):19-13 Xiao Fei, Xiang Min, Zhang Weihua. Orbit Trajectory and System Integrated Design and Optimization of Multi-Stage Solid Rocket[J]. Journal of Air Force Engineering University, 2008, 9(5):19-13(in Chinese)
[5] 马加庆, 孙丕忠, 夏智勋, 等. 大型捆绑助推器总体/动力/轨道一体化设计与优化[J]. 国防科技大学学报, 2006, 28(1):1-4 Ma Jiaqing, Sun Pizhong, Xia Zhixun, et al. Trajectory Solid Rocket and System Integration Design and Optimization on Rocket with Two Boosters[J]. Journal of National University of Defense Technology, 2006, 28(1):1-4(in Chinese)
[6] Anderson M, Burkhalter J, Jenkins R. Multi-Disciplinary Intelligent System Approach to Solid Rocket Motor Design Part I, Single and Dual Goal Optimization[R]. AIAA-2001-3599
[7] 罗亚中, 唐国金, 周黎妮, 等. 运载火箭性能计算一体化优化设计系统分析与设计[J]. 宇航学报, 2003, 24(3):314-317 Luo Yazhong, Tang Guojin, Zhou Lini, et al. The Analysis and Design of Launch Vehicle Performance-Calculation Integrated Optimization Design System[J]. Journal of Astronautics, 2003, 24(3):314-317(in Chinese)
[8] 张宁宁, 闵昌万, 刘辉, 等. 临近空间直接入轨运载火箭级间比/弹道一体化优化设计[J]. 飞行力学, 2014, 32(3):258-261 Zhang Ningning, Min Changwan, Liu Hui, et al. Integrated Optimization Design for Mass Distribution/Trajectory of Near Space Directly Injecting Carrier Rocket[J]. Flight Dynamics, 2014, 32(3):258-261(in Chinese)
[9] 徐玮, 孙丕忠, 夏智勋. 助推-滑翔导弹总体一体化优化设计[J]. 固体火箭技术, 2008, 32(4):317-319 Xu Wei, Sun Pizhong, Xia Zhixun. Integrated Design and Optimization for Boost-Glider Missile[J]. Journal of Solid Rocket Technology, 2008, 32(4):317-319(in Chinese)
[10] 熊伟, 张耐民, 张艳玲. 基于组合算法的固体运载火箭快速运载能力优化[J]. 系统仿真学报, 2013, 25(11):2552-2556 Xiong Wei, Zhang Naimin, Zhang Yanling. Quick Launch Ability Optimization for Solid Rocket Using Combinatorial Optimization Algorithm[J]. Journal of System Simulation, 2013, 25(11):2552-2556(in Chinese)
[11] Morris M D. Factorial Sampling Plans for Preliminary Computational Experiments[J]. Technometrics, 1991, 33:161-174
[12] 陈克俊, 刘鲁华, 孟云鹤. 远程火箭飞行动力学与制导[M]. 北京:国防工业出版社, 2014 Chen Kejun, Liu Luhua, Meng Yunhe. Launch Vehicle Flight Dynamics and Guidance[M]. Beijing, National Defense Industry Press, 2014(in Chinese)
[13] Lu P, Sun H, Tsai B. Closed-Loop Endo-Atmospheric Ascent Guidance[J]. Journal of Guidance, Control, and Dynamics, 2003, 26(2):283-294
[14] 何坚勇. 最优化方法[M]. 北京:清华大学出版社, 2014 He Jianyong. Optimization Method[M]. Beijing, Tsinghua University Press, 2014(in Chinese)
[15] 贾如岩, 王涛, 江振宇, 等. 导弹尾罩分离运动不确定性分析[J]. 国防科技大学学报, 2014, 36(6):88-92 Jia Ruyan, Wang Tao, Jiang Zhenyu, et al. Uncertainly Analysis of the Rocket Trail Cover Separation[J]. Journal of National University of Defense Technology, 2014, 36(6):88-92(in Chinese)