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学术文章

分导滑翔导弹双层架构时序协同轨迹优化

  • 骆盛 , 1, 2 ,
  • 李璇 , 1, * ,
  • 娄江 1 ,
  • 毛瑞 1 ,
  • 王鹏 1 ,
  • 谭一廷 1
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  • 1 西安现代控制技术研究所, 陕西 西安 710065
  • 2 西北工业大学, 陕西 西安 710065
李璇(2000—),男,硕士研究生,E-mail:

骆盛(1986—),男,正高级工程师,E-mail:

收稿日期: 2025-03-06

  网络出版日期: 2025-11-28

Two-layer Architecture Time-coordinated Trajectory Optimization for Distributed Glide Bombs

  • LUO Sheng , 1, 2 ,
  • LI Xuan , 1, * ,
  • LOU Jiang 1 ,
  • MAO Rui 1 ,
  • WANG Peng 1 ,
  • TAN Yi Ting 1
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  • 1 Xi’an Mordern Control Technology Research Institute, Xi’an 710065, Shaanxi, China
  • 2 Northwestern Polytechnical University, Xi’an 710065, Shaanxi, China

Received date: 2025-03-06

  Online published: 2025-11-28

摘要

分导协同攻击作为突破防空体系的有效手段,其技术核心在于多弹协同轨迹规划能力的优化。针对分导滑翔导弹集群协同打击任务中存在的多维度复杂约束问题,包括导弹分离后导致的初始高度差异、速度偏差与姿态角分散,以及三维空间中动态禁飞区的规避需求。提出一种融合高斯伪谱法与协调变量协同控制的新型轨迹规划方法。通过建立导弹三自由度运动学模型,深度耦合气动参数的非线性变化特性与多约束条件,构建了面向分导滑翔导弹集群协同的多目标轨迹优化模型。该方法采用自适应节点分布策略优化GPM的离散化过程,通过在禁飞区边界区域实施网格加密的方法,有效解决了传统方法在航迹拐点处约束违反率过高的问题。最后通过数值仿真验证,分别说明了该方法能够使分导滑翔导弹在初始高度、初始速度、初始姿态不同时,满足规避禁飞区约束,并以指定末速完成协同打击任务,验证了所提方法的有效性和优越性。

本文引用格式

骆盛 , 李璇 , 娄江 , 毛瑞 , 王鹏 , 谭一廷 . 分导滑翔导弹双层架构时序协同轨迹优化[J]. 弹箭与制导学报, 2025 , 45(5) : 827 -836 . DOI: 10.15892/j.cnki.djzdxb.2025.05.027

Abstract

As an effective approach to penetrate air defense systems, fractionated cooperative attack relies fundamentally on optimizing multi-projectile collaborative trajectory planning capabilities. This study addresses the multidimensional complex constraints in coordinated strikes by Distributed Glide Bomb (DGB) clusters, including initial condition disparities resulting from post-separation dynamics (altitude differences, velocity deviations, and attitude dispersion) and three-dimensional dynamic no-fly zone avoidance requirements. A novel trajectory planning methodology is proposed, integrating the Gauss Pseudo spectral Method (GPM) with coordinated-variable control. By establishing a three-degree-of-freedom (3DOF) kinematic model that deeply couples nonlinear aerodynamic parameter variations with multi-constraint conditions (including dynamic equations and geometric constraints), a multi-objective trajectory optimization framework is developed for DGB cluster coordination. The method innovatively employs an adaptive node distribution strategy to optimize the discretization process of the Gauss Pseudo spectral Method (GPM). By implementing mesh refinement in no-fly zone boundary regions, it effectively resolves the issue of high constraint violation rates at trajectory inflection points observed in conventional approaches. Numerical simulations demonstrate that under heterogeneous initial conditions (varying altitudes, velocities, and attitudes), all DGBs successfully generate collision-free 3D trajectories avoiding complex no-fly zones while achieving synchronized strikes with terminal velocities within specified tolerances. The results validate the method’s effectiveness in multi-constraint resolution and its superiority over conventional approaches in computational efficiency and mission adaptability.

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[1]
魏明英, 崔正达, 李运迁. 多弹协同拦截综述与展望[J]. 航空学报, 2020, DOI: 10.7527/S1000-6893.2019.23804.

WEI M Y, CUI Z D, LI Y Q, et al. Review and fueure development of multi-missile coordinated interception[J]. Acta Aeronautica et Astronautica Sinica, 2020, DOI: 10.7527/S1000-6893.2019.23804.

[2]
梁晨, 王卫红, 赖超. 带攻击角度约束的深度强化元学习制导律[J]. 宇航学报, 2021, 42( 5) : 611-620.

LIANG C, WANG W H, LAI C. Deep reinforcement meta-learning guidance with impact angle constraint[J]. Journal of Astronautics, 2021, 42( 5) : 611-620.

[3]
董朝阳, 刘扬, 王青. 带攻角约束的高超声速飞行器自适应反步控制器设计[J]. 宇航学报, 2020, 41(2) : 174-181.

DONG C Y, LIU Y, WANG Q. Adaptive backstepping controller design for hypersonic vehicle with limited angle-ofvattack[J]. Journal of Astronautics, (2020). 41(2): 174-181.

[4]
MOON G, TAHK M, HAN D H, et al. Generalized polynomial guidance for terminal velocity control of tactical ballistic missiles[J]. International Journal of Aeronautical and Space Sciences, 2021, 22(1) : 163-175.

DOI

[5]
赵久奋, 史绍琨, 尤浩, 等. 视场角限制下导弹协同攻击导引律设计[J]. 国防科技大学学报, 2019, 41(04): 114-120.

Zhao J F, Shi S K, You H, et al. Missile cooperative attack guidance law with field-of-view limit[J]. Journal of National University of Defense Technology, 2019, 41(04): 114-120.

[6]
洪超, 夏群利, 阮聪. 带视场角约束的多弹三维协同制导律[J]. 战术导弹技术, 2020(06): 37-43.

Hong C., Xia Q L, Ruan C. Multi-missile threevdimensional cooperative guidance law with fieldvof-view constraints[J]. Tactical Missile Technology, 2020(06): 37-43.

[7]
Zhang Y, Tang S, et al. An adaptive fast fixed-time guidance law with an impact angle constraint for intercepting maneuvering targets[J]. Chinese Journal of Aeronautics, 2018, 31(147): 167-184.

[8]
Chen Z Y, Chen W C, et al. Three-dimensional fixed-time robust cooperative guidance law for simultaneous attack with impact angle constraint[J]. Aerospace Science and Technology, 2021(110): 1-16.

[9]
Qiao H, Sun P, Li X G. United Trajectory Design Method for Return to Launch Site of Suborbital Reusable Launch Vehicle[C]. 21st AIAA International Space Planes and Hypersonics Technologies Conference, Xiamen, China, 2017. (EI)

[10]
Shi J, Zhang L, Jiang B, et al. Aerodynamic force and heating optimization of HTV-2 typed vehicle[M]. American Institute of Aeronautics and Astronautics, 2017.

[11]
王晓海, 孟秀云, 周峰, 等. 基于偏置比例导引的落角约束滑模制导律[J]. 系统工程与电子技术, 2021, 43(05): 1295-1302.

WANG X H, MENG X Y, ZHOU F, et al. Sliding mode guidance law with impact angle constraint based on bias proportional navigation[J]. Systems Engineering and Electronics Technology, 2021, 43(05): 1295-1302.

[12]
Zhang R, Wang J, Li H, et al. Robust Finite-Time Guidance against Maneuverable Targets with Unpredictable Evasive Strategies[J]. Aerospace Science and Technology, 2018, 77(4): 534-544.

DOI

[13]
陈顺毅, 徐小平, 刘双喜, 等. 面向时间协同的高超声速滑翔飞行器集群再入轨迹规划[J/OL]. 国防科技大学学报,1-11[2025-2-27].http://kns.cnki.net/kcms/detail/43.1067.t.20250103.0931.002.html.

CHEN S Y, XU X P, LIU S X, et al. Time-coordinated reventry trajectory planning for hypersonic glide vehicles cluster[J/OL]. Journal of National University of Defense Technology, 1-11[2025-02-27].http://kns.cnki.net/kcms/detail/43.1067.t.20250103.0931.002.html.

[14]
张钰清, 陈长风, 张扬, 等. 带有时间约束的多飞行器协同轨迹规划[J]. 工程科学学报, 2024, 46(09):1554-1564.DOI:10.13374/J.ISSN2095-9389.2023.11.23.002.

ZHANG Y Q, CHEN C F, ZHANG Y., et al. Time-coordinated entry trajectory planning for multihypersonic vehicles[J]. Chinese Journal of Engineering, 2024, 46(09): 1554-1564. DOI: 10.13374/J.ISSN2095-9389.2023.11.23.002.

[15]
张振林, 张科, 郭正玉, 等. 一种新型领从式多弹协同制导律设计[J]. 航空兵器, 2020, 27(05): 33-38.

ZHANG Z L, ZHANG K, GUO Z Y, et al. Design of a New Leader-Follower Collaborative Guidance Law for Multiple Missiles[J]. Aero Weaponry, 2020, 27(05): 33-38.

[16]
欧阳权, 徐罗旻, 杨继阳, 等. 基于能耗优化的四旋翼无人机航迹规划:分段式高斯伪谱法[J]. 电光与控制, 2025, 32(01):1-7.

OU Y Q, XU L M, YANG J Y, et al. Energy-efficient trajectory planning for quadrotor UAVs: a segmented Gaussian pseudo spectral method[J]. Electronics Optics & Control, 2025, 32(1): 1-7.

[17]
张佩俊, 许宏涛, 姚保江, 等. 滑翔飞行器速度约束条件下制导律设计[J]. 上海航天(中英文), 2024, 41(04):141-147.DOI:10.19328/j.cnki.2096-8655.2024.04.017.

ZHANG P J, XU H T, YAO B J, et al. Guidance Law Design for Glide Vehicles Under Velocity Constraint. AEROSPACE SHANGHAI(CHINESE& ENGLISH), 2024, 41(04):141-147.DOI:10.19328/j.cnki.2096-8655.2024.04.017.

[18]
肖明昊, 韩治国, 弋可行, 等. 带速度及视线角约束的大机动目标协同制导律[J]. 宇航学报, 2024, 45(12):1974-1986.

XIAO M H, HAN Z G, YI K X, et al. Cooperative Guidance Law for Large Maneuvering Targets withVelocity and Line-of-sight Angle Constraints[J]. Journal of Astronautics, 2024, 45(12):1974-1986.

[19]
赵在强, 杨召, 杨添琦. 基于目标分配的多弹协同分层拦截制导策略[J/OL]. 系统工程与电子技术,1-11[2025-03-07].http://kns.cnki.net/kcms/detail/11.2422.TN.20241206.1421.047.html.

ZHAO Z Q, YANG Z, YANG T Q. Multi-missile cooperative layered interception guidance scheme based ontarget assignment[J/OL]. Systems Engineering and Electronics, 1-11[2025-03-07]. http://kns.cnki.net/kcms/detail/11.2422.TN.20241206.1421.047.html.

[20]
夏侯超, 周浩, 陈万春. 考虑时变速度和信息共享的协同最优解析制导方法[J/OL]. 北京航空航天大学学报,1-20[2025-03-07].https://doi.org/10.13700/j.bh.1001-5965.2024.0707.

XIAHOU C, ZHOU H, CHEN W C. Cooperative optimal analytical guidance method considering time-varying velocity and information sharing[J/OL]. Journal of Beijing University of Aeronautics and Astronautics, 1-20[2025-03-07]. https://doi.org/10.13700/j.bh.1001-5965.2024.0707.

[21]
尤浩, 常新龙, 赵久奋, 等. 带落角约束的新型领弹-从弹固定时间协同制导律[J]. 国防科技大学学报, 2024, 46(06):64-76.

YOU H, CHANG X L, ZHAO J F, et al. Novel leader-following missiles fixed-time cooperative guidance law with impact angle constraints[J]. Journal of National University of Defense Technology, 2024, 46(06): 64-76.

[22]
黄绍洧, 都延丽, 刘燕斌, 等. 有限时间收敛的自适应滑模协同末制导[J/OL]. 系统工程与电子技术,1-11[2025-03-07].http://kns.cnki.net/kcms/detail/11.2422.TN.20241119.2338.018.html.

HUANG S W, DU Y L, LIU Y B, et al. Adaptive sliding cooperative terminal guidance with finite time convergence[J/OL]. Systems Engineering and Electronics, 1-11[2025-03-07]. http://kns.cnki.net/kcms/detail/11.2422.TN.20241119.2338.018.html.

[23]
刘双喜, 徐小平, 黄伟, 等. 国外多弹协同项目发展及关键技术展望[J]. 航空兵器, 2024, 31(06):1-13.

LIU S X, XU X P, HUANG W, et al. Development and Key Technologies Outlook of Foreign Multi-Missile Collaborative Projects[J]. Aero Weaponry, 2024, 31(06): 1-13.

[24]
詹译傲, 李思远, 周荻, 等. 基于协同估计的三维多导弹博弈制导律[J]. 宇航学报, 2024, 45(09):1467-1480.

ZHAN Y A, LI S Y, ZHOU D, et al. Three-dimensional multi-missile game guidance law based on cooperative estimation[J]. Journal of Astronautics, 2024, 45(09): 1467-1480.

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