助推-滑翔导弹分段总体参数优化方法研究

罗炜; 雷刚; 郑晓龙

doi:10.15892/j.cnki.djzdxb.2023.05.012

弹箭与制导学报 >

2023 , Vol. 43 >Issue 5: 73 - 79

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2023.05.012

助推-滑翔导弹分段总体参数优化方法研究

罗炜 ,
雷刚 ,
郑晓龙

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火箭军工程大学,陕西西安 710025

雷刚(1978—),男,副教授,博士,研究方向:飞行力学与飞行器任务规划。

罗炜(2000—),男,硕士研究生,研究方向:飞行力学与飞行器任务规划。

收稿日期: 2022-10-26

网络出版日期: 2024-12-30

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Research on Multi-Stage Overall Parameter Optimization Method for Boost-glide Missile

LUO Wei ,
LEI Gang ,
ZHENG Xiaolong

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Rock Force University of Engineering,Xi’an 710025,Shaanxi, China

Received date: 2022-10-26

Online published: 2024-12-30

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摘要

为发挥助推-滑翔式导弹最大作战效能,需在一定的飞行条件约束下,对其总体参数进行优化设计。首先分析直接起滑式滑翔弹道下各类参数对飞行弹道的影响,并将整个优化过程划分为独立的两个阶段;而后采用自适应遗传算法对各阶段进行优化,得到了满足文中约束条件下的最佳导弹总体方案;最后采用蒙特卡洛模拟对该方法进行验证。结果表明,文中设计方法能够在5.5 s内完成总体参数优化,并在±0.7%的精度范围内使得导弹进行直接起滑式飞行。

关键词： 助推-滑翔式导弹; 总体参数设计; 分段优化方法; 自适应遗传算法

本文引用格式

罗炜 , 雷刚 , 郑晓龙 . 助推-滑翔导弹分段总体参数优化方法研究[J]. 弹箭与制导学报, 2023 , 43(5) : 73 -79 . DOI: 10.15892/j.cnki.djzdxb.2023.05.012

Abstract

In order to give full play to the maximum combat effectiveness of the booster-glide missile, its overall parameters are optimized under certain flight conditions. Firstly, after analyzing the influence of various parameters on the flight trajectory under the direct takeoff and gliding trajectory, the entire optimization process is divided into two relatively independent sub-stages; then the sub-stages are optimized by adaptive genetic algorithm respectively, and the results satisfying each The optimal missile overall design scheme under the class constraints; finally, the method is verified based on the Monka simulation. The results show that the design method can complete the overall parameter optimization within 5.5 seconds, and make the missile fly with the accuracy of ±0.7%.

Key words： booster-glide missile; overall parameter design; segmentation optimization method; adaptive genetic algorithm

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参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序

[1]	赵吉松, 谷良贤, 龚春林. 高超声速飞行器起飞质量的解析估算[J]. 固体火箭技术, 2008, 31(6): 548-551. ZHAO J S, GU L X, GONG C L. Analytical evaluation of takeoff mass for hypersonic vehicles[J]. Journal of Solid Rocket Technology, 2008, 31(6): 548-551.

[2]	LI J, QI W, GONG H R, et al. Study on the optimization of missile take off mass and its influence on aerodynamic parameters[J]. Journal of Physics Conference Series, 2020, 1600: 012054.

[3]	蒋明明, 袁庆航, 赵长见, 等. 助推-滑翔式导弹总体参数设计方法初探[J]. 导弹与航天运载技术, 2016(4): 5-7. JIANG M M, YUAN Q H, ZHAO C J, et al. Preliminary investigation of parameter design method for boost-glide missile[J]. Missiles and Space Vehicles, 2016(4): 5-7.

[4]	周伟, 罗建军, 强洪夫, 等. 变权TOPSIS评价的导弹总体参数粒子群优化设计方法[J]. 固体火箭技术, 2018, 41 (3): 388-394. ZHOU W, LUO J J, QIANG H F, et al. Variable weight TOPSIS evaluation combined with particle swarm method for missile overall parameters optimization design[J]. Journal of Solid Rocket Technology, 2018, 41(3): 388-394.

[5]	孙乐园, 贾如岩, 杨枝山, 等. 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, 2016, 34(6): 1101-1107. SUN L Y, JIA R Y, YANG Z S, et al. An integrated optimization method of trajectory/system parameters for heavy launch vehicles[J]. Journal of Northwestern Poly-technical University, 2016, 34(6): 1101-1107.

[6]	施雨阳, 万自明, 徐敏. 基于混合遗传算法的冲压发动机导弹总体参数优化[J]. 科学技术与工程, 2013, 13(30): 9144-9148. SHI Y Y, WAN Z M, XU M. Ramjet powered missile overall parameter optimization based on hybrid adaptive genetic algorithm[J]. Science Technology and Engineering, 2013, 13(30): 9144-9148.

[7]	陈江宁, 王和平. 弹道导弹总体参数的混合遗传算法全局优化[J]. 飞行力学, 2011, 29(3): 44-47. CHEN J N, WANG H P. Hybrid genetic algorithm global optimization of configuration design for ballistic missiles[J]. Flight dynamic, 2011, 29(3): 44-47.

[8]	胥涯杰, 鲜勇, 李邦杰. 基于BP神经网络改进遗传算法的导弹总体参数快速优化方法[J]. 电光与控制, 2022, 29(2): 20-24. XU Y J, XIAN Y, LI B J. Rapid optimization of missile’s overall parameters based on BP neural network improved genetic algorithm[J]. Electronics Optics & Control, 2022, 29(2): 20-24.

[9]	李广华, 张洪波, 汤国建. 高超声速滑翔飞行器典型弹道特性分析[J]. 宇航学报, 2015, 36(4): 397-403. LI G H, ZHANG H B, TANG G J. Typical Trajectory characteristics of hypersonic glide vehicle[J]. Journal of Astronautics, 2015, 36(4): 397-403.

[10]	RICHIE G. The common aero vehicle-space delivery system of the future: AIAA 1999-4435[R]. Reston: AIAA, 1999.

[11]	何睿智. 高超声速助推滑翔飞行器全程弹道规划方法研究[D]. 长沙: 国防科技大学, 2017. HE R Z. Study of all-course trajectory planning approach for hypersonic boost-glide vehicles[D]. Changsha: National University of Defense Technology, 2017.

[12]	赵汉元. 飞行器再入动力学和制导[M]. 长沙: 国防科技大学出版社, 1997. ZHAO H Y. Vehicle re-entry dynamics and guidance[M]. Changsha: National University of Defense Technology Press, 1997.

[13]	冯智莉, 易国洪, 李普山, 等. 并行化遗传算法研究综述[J]. 计算机应用与软件, 2018, 35(11): 1-7. FENG Z L, YI G H, LI P S, et al. Review of parallel genetic algorithm[J]. Computer Applications and Software, 2018, 35(11): 1-7.

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