Integrated Optimization Design of Internal and External Ballistics for Low-altitude Cruise Target Missiles

WU Weixiao; SHAO Changxing; ZHU Mengcheng; ZHANG Xueqing; QIAN Long; ZHAO Mohan; YU Qi

doi:10.15892/j.cnki.djzdxb.2025.06.030

Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 6: 1202 - 1210

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.06.030

Academic article

Integrated Optimization Design of Internal and External Ballistics for Low-altitude Cruise Target Missiles

WU Weixiao ,
SHAO Changxing ,
ZHU Mengcheng ,
ZHANG Xueqing ,
QIAN Long ,
ZHAO Mohan ,
YU Qi

Expand

Shanghai Aerospace Precision Machinery Research Institute,Shanghai 201600,China

Received date: 2025-02-11

Online published: 2026-01-24

Fold

Abstract

The overall design of target missiles and their propulsion system design,as sequential steps,require multiple rounds of iterative optimization.Since the propulsion system design adheres to the engine optimization principle,it cannot directly derive optimal overall target missile performance from the input system parameters,leading to extended design cycles and increased costs.Specifically,a solid rocket motor performance analysis model and an external ballistic simulation model for target missiles were developed,achieving single-pass optimization of integrated internal-external ballistic design.A joint design optimization algorithm is established with the objective of maximizing cruise time under constraints including engine structural strength,propellant mechanical properties,overall layout of the missile body,and stability and control characteristics of the target missile.Compared with the initial scheme,the low-altitude supersonic cruise time of the target missile is increased by 27.4%,thereby verifying the rationality of the integrated optimization design scheme for internal and external ballistics.

Key words： Multi-stage thrust; Low-altitude supersonic cruise target missile; Optimization of integrated internal-external ballistic design; Cruise time

Cite this article

WU Weixiao , SHAO Changxing , ZHU Mengcheng , ZHANG Xueqing , QIAN Long , ZHAO Mohan , YU Qi . Integrated Optimization Design of Internal and External Ballistics for Low-altitude Cruise Target Missiles[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(6) : 1202 -1210 . DOI: 10.15892/j.cnki.djzdxb.2025.06.030

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within

[1]	王志健, 何国强, 魏祥庚, 等. 空空导弹多脉冲固体火箭发动机能量分配优化研究[J]. 弹箭与制导学报, 2010, 30(6):144-146. DOI WANG Z J, HE GQ, WEI X G, et al. An Investigation of Optimizing Energy Allocation on Multi-pulse Solid Rocket Motor in Airborne Missile[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2010, 30(6):144-146.

[2]	张翼, 郑哲. 空空导弹双脉冲固体火箭发动机能量分配研究[J]. 科技与创新, 2019,24:4-7. ZHANG Y, ZHENG Z. Research on Energy Distribution of Dual-Pulse Solid Rocket Motors for Air-to-Air Missiles[J]. Science and Technology&Innovation, 2019,24:4-7.

[3]	周梦琦, 薛林, 闫晓勇. 近程防空导弹发动机推力方案优化研究[J]. 现代防御技术, 2017, 45(5):42-47. ZHOU M Q, XUE L, YAN X Y. Optimizing Motor Propulsion Scheme in Short Range Antiaircraft Missiles[J]. Modern Defence Technology, 2017, 45(5):42-47.

[4]	张弫, 成楚之, 于本水. 多次点火固体火箭发动机在面空导弹上的应用研究[J]. 现代防御技术, 2001, 29(5):31-33. ZHANG Z, CHENG C Z, YU B S. Applications of Multiple Ignition Solid Rocket Motor to Surface to Air Missile[J]. Modern Defence Technology, 2001, 29(5):31-33.

[5]	翟艺云, 龙腾, 刘震宇, 等. 助推滑翔变体飞行器弹道方案多目标近似优化[J]. 上海航天(中英文), 2024,(3):110-120. ZHAI Y Y, LONG T, LIU Z Y, et al. Multi-objective Approximate Optimization for the Boost-glide Morphing Flight Vehicle Trajectory Scheme[J]. Aerospace Shanghai(Chinese&English), 2024,(3):110-120.

[6]	陈玉春, 崔高锋, 杨云恺, 等. 基于能量法的超声速飞航导弹/冲压发动机一体化研究[J]. 固体火箭技术, 2009, 32(2):119-122. CHEN Y C, CUI G F, YANG Y K, et al. Research of supersonic cruise missile and ramjet motor integration based on energy method[J]. Journal of Solid Rocket Technology, 2009, 32(2):119-122.

[7]	宋少倩, 陈永信, 任鹏飞, 等. 面向航程能力的固体火箭发动机方案设计优化[J]. 哈尔滨工业大学学报, 2022, 54(12):27-37. Song S Q, CHEN Y X, REN P F, et al. Conceptual design optimization of solid rocket motor for range capability[J]. Journal of Harbin Institute of Technology, 2022, 54(12):27-37.

[8]	范健, 杨春, 佟明曦, 等. 基于内外弹道联合仿真的固体火箭发动机优化设计[J]. 弹箭与制导学报, 2018, 38(2):56-60. DOI FAN J, YANG C, TONG M X, et al. Optimization of Solid Rocket Motor Based on Joint-simulation of Internal and External Ballistic Design[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2018, 38(2):56-60.

[9]	王鹏, 李旭昌, 徐颖军, 等. 固体火箭发动机总体优化设计[J]. 火箭推进, 2007, 33(4):16-19. WANG P, LI X C, XU Y J, et al. The optimal design of solid rocket motors[J]. Journal of Rocket Propulsion, 2007, 33(4):16-19.

[10]	刘宝华, 杨志菊. 固体火箭发动机内弹道性能的仿真研究[J]. 电子测试, 2009,(10):17-20. LIU B H, YANG Z J. Simulate research of solid rocket engine inside trajectory characteristic[J]. Electronic Test, 2009,(10):17-20.

[11]	吴蜀豫, 吴晓中, 王新平. 某小型固体火箭发动机内弹道数值仿真探究[J]. 电子测试, 2014(3):9-11. WU S Y, WU X Z, WANG X P. Research of interior ballistics numerical simulation for a small solid rocket engine[J]. Electronic Test, 2014(3):9-11.

[12]	曹任刚. 无喷管固体火箭发动机内弹道计算[J]. 航空兵器, 2006,1:57-60. CAO R G. Analysis of Nozzle less Solid Propellant Rocket Motor Performance[J]. Aero Weaponry, 2006,1:57-60.

[13]	程谋森, 李小康, 杨雄, 等. 火箭发动机原理[M]. 北京: 科学出版社, 2021. CHENG M S, LI X K, YANG X, et al. Principles of Rocket Engines[M]. Beijing: Science Press, 2021.

[14]	宁超, 田干. 火箭发动机理论基础[M]. 西安: 西北工业大学出版社, 2016. NING C, TIAN G. The Fundamentals of Rocket Engine Theory[M]. Xi’an: Northwestern Polytechnical University Press, 2016.

[15]	王元有. 固体火箭发动机设计[M]. 北京: 国防工业出版社,1984. WANG Y Y. Design of Solid Rocket Motors[M]. Beijing: Defense Industry Press,1984.

[16]	WILLCOS M A, BREWSTER M Q, TANG K C, et al. Solid propellant grain design and burnback simulation using a minimum distance function[J]. Journal of Propulsion and Power, 2007, 23(2):465. DOI

[17]	刘震国. 某空空导弹固体火箭发动机改进设计及试验研究[D]. 南京: 南京理工大学, 2012. LIU Z G. The Modified Design and Experimental Study of the Solid Rocket Motor of the Missile[D]. Nanjing: Nanjing University of Science&Technology, 2012.

[18]	孙善春, 谭泽荣, 董元发. 基于改进粒子群算法的固体火箭发动机总体设计优化方法[J]. 机械工程师, 2022,(2):138-140. SUN S C, TAN Z R, DONG Y F. Overall Design Optimization Method of Solid Rocket English Based on Improved Particle Swarm Algorithm[J]. Mechanical Engineer, 2022,(2):138-140.

[19]	张久云, 杜国秀, 齐子凤. 中小型固体火箭发动机喷管扩张比寻优算法[J]. 弹箭与制导学报, 2012, 32(6):106-111. DOI ZHANG J Y, DU G X, QI Z F. Optimization Algorithm of Small and Medium-sized Solid Rocket Motors Nozzle Optimal Divergence Ratio[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2012, 32(6):106-111.

[20]	户艳, 刘思濛, 刘焕玲, 等. 固体火箭发动机喷管的结构设计与性能仿真[J]. 计算机技术与发展, 2015, 25(8):188-193. HU Y, LIU S M, LIU H L, et al. Design and Performance Simulation of Solid Rocket Motor Nozzle[J]. Computer Technology and Development, 2015, 25 (8):188-193.

[21]	何景轩, 甘晓松, 乐发仁, 等. 固体火箭发动机燃烧室压强及喷管扩张比优化设计[J]. 固体火箭技术, 2003, 26(4):12-13. HE J X, GAN X S, LE F R, et al. Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors[J]. Journal of Solid Rocket Technology, 2003, 26(4):12-13.

[22]	范晓星, 王宇, 王曦珠, 等. 小型拉瓦尔喷管的参数设计和模拟[J]. 辽宁大学学报, 2023, 50(2):146-153. FAN X X, WANG Y, WANG X Z, et al. Design of Small Size Laval Nozzle and Simulation[J]. Journal of Liaoning University, 2023, 50(2):146-153.

Options

Outlines