期刊文献+

多防御弹主动防御系统协同一致拦截

Simultaneous and cooperative interception with multiple defense missiles for active defense system
原文传递
导出
摘要 针对目标-攻击弹-防御弹群(TAD)系统中防御弹群需协同目标进行主动防御并实现同时拦截攻击弹目标的问题,对TAD系统在二维平面下的协同主动防御模型进行了研究,并提出了包括虚拟领弹、目标以及防御弹群的两层协同制导策略,问题采用基于非线性模型预测控制(NMPC)的一致性协议算法进行求解。两层制导策略分别是第一层中的虚拟防御弹领弹协同目标进行主动防御并得到攻击弹位置信息,第二层是真实防御弹群针对确定位置的攻击弹采用基于模型预测控制的一致性算法,实现同时到达并拦截攻击弹。第一层协同制导主要考虑保护目标在安全范围内,以及目标和虚拟防御弹的加速度约束,第二层协同制导主要考虑防御弹群的加速度约束。两层制导均通过基于NMPC的方法优化,计算出目标和防御弹群的协同控制量。仿真结果表明,提出的多防御弹主动防御系统协同一致拦截制导算法能够实现TAD系统中目标和防御弹群的协同主动防御。 Aiming to solve the challenge of cooperation between the defending missiles and the target in a target-attacker-defenders(TAD) system, a cooperative active defense model for the TAD system in the planar scenario is explored. The proposed solution is a two-level cooperative guidance strategy that involves a virtual leader, the target and the defending missile group. The strategy utilizes a consistency protocol algorithm based on Nonlinear Model Predictive Control(NMPC) to achieve simultaneous interception for the attacking missile.The first layer of the guidance strategy involves the cooperation between the virtual defending missile and the target to actively defend and gather the position information of the attacking missile. The second layer involves the use of a consistency algorithm based on Model Predictive Control by the real defending missiles to simultaneously arrive and intercept the attacking missile at a determined position. The first layer of guidance focuses on considering the acceleration constraints of the target and virtual defender within a safe range, while the second layer focuses on the acceleration constraints of the defending missile group. Both layers use the NMPC-based method to calculate the cooperative control of the target and defending missiles. Simulation results indicate that the cooperative and consistent interception guidance algorithm for the multi-defending missiles in the active defense system is effective in achieving the cooperative active defense between the target and defending missiles in the TAD system.
作者 杨登峰 闫晓东 Yang Dengfeng;Yan Xiaodong(School of Astronautics,Northwestern Polytechnical University,Xi'an 710000,China)
出处 《战术导弹技术》 北大核心 2023年第5期73-82,共10页 Tactical Missile Technology
关键词 主动防御 目标-攻击弹-防御弹群系统 非线性模型预测控制 一致性到达 虚拟领弹 协同拦截 两层制导 active defense target-attacker-defenders system nonlinear model predictive control si-multaneous arrival virtual leading missile cooperative interception two-layer guidance
  • 相关文献

参考文献4

二级参考文献24

  • 1任远,崔平远,栾恩杰.基于不变流形的小推力Halo轨道转移方法研究[J].宇航学报,2007,28(5):1113-1118. 被引量:8
  • 2冯小荣,樊秋林.对外大气层动能杀伤拦截器EKV的突防方法研究[J].红外与激光工程,2006,35(z1):52-55. 被引量:4
  • 3Koon W S, Lo M W, Marsden J E, et al. Dynamical system, the three-body problem and space mission design [ M ]. Springer, Heidelberg, 2006.
  • 4Howell K, Kakoi M. Transfers between the Earth-Moon and Sun- Earth systems using manifolds and transit orbits [ J ]. Acta. Astronautica, 2005, 56: 652- 669.
  • 5Gomez G, Jorba A, Masdemont J, et al. Study of the transfer between halo orbits[ J]. Aeta Astronautica, 1998, 43 (9 - 10) : 493 - 520.
  • 6Peng H J, Zhao J, Gao Q, et al. Nonlinear optimal control of the continuous low-thrust transfer between Halo orbits[ C ]. The 3rdInternational Symposium on Systems and Control in Aeronautics and Astronautics, China, 2010 : 616 - 620.
  • 7Gao Y. Linear feedback guidance for low-thrust many-revolution earth-orbit transfers [ J ]. Journal of Spacecraft and Rockets, 2009, 46(6) : 1320 - 1325.
  • 8Tian B L, Zong Q. Optimal guidance for reentry vehicles based on indirect Legendre pseudospectral method [ J ]. Acta Astronautica, 2011,68(7 -8) : 1176 -1184.
  • 9Lu P. Regulation about time-varying trajectories precision entry guidance illustrated [ J ]. Journal of Guidance, Control, and Dynanfics, 1999, 22(6) : 784 -790.
  • 10Ohtsuka T. Quasi-newton-type continuation method for nonlinear receding horizon control[ J ]. Journal of Guidance, Control, and Dynamics, 2002, 25 (4) : 685 - 692.

共引文献22

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部