Design and Simulation Analysis of Guidance Law for Boost Phase Interceptor Missile

doi:10.16182/j.issn1004731x.joss.23-1588

Abstract

Abstract:

The intercept time window in the boost phase is very short, which requires the missile to have high speed and high acceleration capability, at the same time, because the target ballistic missile is still accelerating in the boost phase, the guidance scheme of the interceptor missile needs to have the ability to cope with the characteristics of the booster phase interceptor missile. The trajectory simulation model is established, and the guidance law of the boost phase interceptor missile in the initial guidance, mid-guidance and final guidance stage are designed in detail according to the performance of the guidance mechanism required by the interceptor missile during the whole flight process. The influence of different guidance schemes on the interceptor performance is studied, and the interception effect of different maximum velocities of the missile is analyzed. Experimental results show that the guidance law of forecast point of impact can reduce the line-of-sight rate and make the trajectory flatter, and the modified proportional guidance law can reduce the required overload and improve the intercepting performance. At the same time, the higher the energy of the missile, the higher the speed characteristics, the higher the flight performance, and the shorter the interception time required, the better the interception effect.

Key words: ballistic missile defense, boost phase intercept, guidance law design, interception performance, trajectory simulation

CLC Number:

TP391.9

Zhang Xu, Zeng Peng, Li Xu, Zheng Xuehe, Xue Jianheng, Wang Chao. Design and Simulation Analysis of Guidance Law for Boost Phase Interceptor Missile[J]. Journal of System Simulation, 2025, 37(2): 335-344.

Figures/Tables 21

Fig. 1

Table 1

Comparison of ballistic parameters at the end of the first stage flight

弹道参数	$t m$ =4.0 s	$t m$ =4.3 s	$t m$ =4.5 s
最大调转攻角 $α m / (°)$	6.21	7.01	7.48
高度/km	28	28	28
速度/(m/s)	2 421.16	2 421.10	2 421.03
斜距/km	28.7	28.7	28.7
动压/Pa	72 285.37	72 387.16	72 423.95
弹道倾角 $/ (°)$	71.15	71.12	71.11

Table 1

Fig. 2

Fig. 3

Table 2

Initial guidance phase flight timing

起始时间/s	动作
0	拦截导弹点火发射，开启初制导
$t 1$	开始程序转弯
$t m$	导弹达到最大攻角
$t 2$	结束程序转弯，开始重力转弯
$t 3$	进入中制导

Table 2

Fig. 4

Fig. 5

Fig. 6

Table 3

Table 4

Table 5

Table 6

Fig. 7

Fig. 8

Fig. 9

Table 7

Interception performance of different guidance schemes

拦截性能	方案I	方案II	方案III
脱靶量/m	32	19	0.475
弹道变化情况	较为弯曲	较为弯曲	较为平直
最大需用法向过载×g	38.6	27.6	9.57
最大可用过载×g	20	20	20
拦截时间/s	85.8	85.1	84.6
初制导结束时间 $t 3$ /s	15	15	15

Table 7

Table 8

Fig. 10

Fig. 11

Fig. 12

Fig. 13

References 22

1	Corbett C M, Zarchan P. The Role of Airpower in Active Missile Defense[J]. Air and Space Power Journal, 2010, 24(2): 57-71.
2	周皓, 冯占林, 张怀天. 美国弹道导弹防御武器系统研究[J]. 中国航天, 2018(6): 62-65.
	Zhou Hao, Feng Zhanlin, Zhang Huaitian. Study on US Ballistic Missile Defense System[J]. Aerospace China, 2018(6): 62-65.
3	朱枫, 韩晓明, 何小九. 助推段反导作战发展现状综述[J]. 飞航导弹, 2017(1): 29-33.
4	刘永兰, 李为民, 谢鑫, 等. 国外助推段反导的研究现状及发展趋势分析[J]. 飞航导弹, 2014(3): 34-41.
5	荆武兴, 杨彪, 高长生. 空基反助推段导弹制导技术综述[J]. 哈尔滨工业大学学报, 2021, 53(6): 1-12.
	Jing Wuxing, Yang Biao, Gao Changsheng. Review on Guidance Technology of Air-based Missiles for Boost Phase Interception[J]. Journal of Harbin Institute of Technology, 2021, 53(6): 1-12.
6	李宪强, 刘莹莹, 葛致磊, 等. 空基助推段拦截中制导律设计[J]. 飞行力学, 2012, 30(5): 436-439.
	Li Xianqiang, Liu Yingying, Ge Zhilei, et al. Guidance Law Designing for Air-based Interception of Ballistic Missiles in the Boost Phase[J]. Flight Dynamics, 2012, 30(5): 436-439.
7	王森, 杨建军. 战术弹道导弹助推段拦截方法研究[J]. 飞航导弹, 2009(5): 54-57.
8	Barton D K, Falcone R, Kleppner D, et al. Report of the American Physical Society Study Group on Boost-phase Intercept Systems for National Missile Defense: Scientific and Technical Issues[J]. Reviews of Modern Physics, 2004, 76(3).
9	石磊, 张占月. 海基拦截导弹弹道建模与仿真[J]. 系统仿真学报, 2009, 21(增2): 89-91, 96.
	Shi Lei, Zhang Zhanyue. Modeling and Simulation for Sea-based Intercept Missile Trajectory[J]. Journal of System Simulation, 2009, 21(S2): 89-91, 96.
10	董杰, 张正成, 刘宗福. 助推段反导的动能拦截弹导引律设计[J]. 指挥控制与仿真, 2016, 38(5): 119-122.
	Dong Jie, Zhang Zhengcheng, Liu Zongfu. Guidance Law Design for Kinetic Interceptor for Antimissile in Boost Phase[J]. Command Control & Simulation, 2016, 38(5): 119-122.
11	孙佳玥. 反助推段导弹的末制导仿真研究[D]. 哈尔滨: 哈尔滨工业大学, 2015.
	Sun Jiayue. Terminal Guidance Simulation of the Interception of Boost Phase Missile[D]. Harbin: Harbin Institute of Technology, 2015.
12	孟逸东. "标准-3"拦截弹制导律设计与攻防对抗仿真[D]. 哈尔滨: 哈尔滨工业大学, 2022.
	Meng Yidong. The Design of Guidance Law and Attack Defense Confrontation Simulation of "Standard-3" Missile[D]. Harbin: Harbin Institute of Technology, 2022.
13	李大壮. 基于强化学习的导弹拦截制导律设计[D]. 哈尔滨: 哈尔滨工业大学, 2022.
	Li Dazhuang. Design of Missle Interception Guidance Law Based on Reinforcement Learning[D]. Harbin: Harbin Institute of Technology, 2022.
14	孙旭涛, 郭小威, 王志佳. 舰空导弹拦截目标中制导律设计研究[J]. 弹箭与制导学报, 2018, 38(3): 29-32.
	Sun Xutao, Guo Xiaowei, Wang Zhijia. The Design Research on the Midcourse Guidance Law of Ship-to-air Missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018, 38(3): 29-32.
15	束川良, 朱迪, 钟永建, 等. 防空导弹拦截高速大俯冲机动目标中制导律设计[J]. 空天防御, 2019, 2(1): 29-32.
	Shu Chuanliang, Zhu Di, Zhong Yongjian, et al. Design of Midcourse Guidance Law of Air Defence Missile Intercepting High Speed Maneuvering Target with Big Diving Angle[J]. Air & Space Defense, 2019, 2(1): 29-32.
16	孟克子. 拦截高速机动目标的导弹导引规律研究[D]. 哈尔滨: 哈尔滨工业大学, 2017.
	Meng Kezi. Missile Guidance Laws for Intercepting High-speed Maneuvering Targets[D]. Harbin: Harbin Institute of Technology, 2017.
17	王健权, 王韬, 尹中杰, 等. 面向高速目标的临近空间飞机拦截平台制导方法[J]. 宇航学报, 2023, 44(10): 1575-1585.
	Wang Jianquan, Wang Tao, Yin Zhongjie, et al. Guidance Method of Near Space Aircraft Interceptor Platform for High Speed Target[J]. Journal of Astronautics, 2023, 44(10): 1575-1585.
18	胡志恒. 临近空间拦截导弹制导方法及其轨迹预报方法研究[D]. 哈尔滨: 哈尔滨工业大学, 2020.
	Hu Zhiheng. Guidance and Trajectory Prediction of Near Space Interceptor Missiles[D]. Harbin: Harbin Institute of Technology, 2020.
19	陈宏旭, 于江龙, 陈扬, 等. 拦截机动目标的三维协同中末一体化制导律[J]. 飞控与探测, 2023, 6(3): 86-94.
	Chen Hongxu, Yu Jianglong, Chen Yang, et al. Three-dimensional Cooperative Mid-terminal Guidance Law for Intercepting Maneuvering Targets[J]. Flight Control & Detection, 2023, 6(3): 86-94.
20	胡志恒, 周荻, 邹昕光. 拦截导弹的制导律辨识与弹道预报[J]. 系统工程与电子技术, 2018, 40(3): 609-614.
	Hu Zhiheng, Zhou Di, Zou Xinguang. Guidance Law Estimation and Trajectory Prediction of Interceptor Missile[J]. Systems Engineering and Electronics, 2018, 40(3): 609-614.
21	潘翔宇, 胡小敏, 刘琨. 基于预测命中点的微分几何制导律[J]. 电光与控制, 2021, 28(7): 41-47.
	Pan Xiangyu, Hu Xiaomin, Liu Kun. Differential Geometric Guidance Law for Predicting Hit Points[J]. Electronics Optics & Control, 2021, 28(7): 41-47.
22	尹中杰, 刘凯, 朱柏羊, 等. 面向临近空间目标拦截的预测命中点设计方法[J]. 宇航学报, 2020, 41(9): 1184-1194.
	Yin Zhongjie, Liu Kai, Zhu Baiyang, et al. Method of Predicted Impact Point Planning for Near-space Target Interception[J]. Journal of Astronautics, 2020, 41(9): 1184-1194.

参数类别	参数名称	参数信息
目标初始参数	关机点时间/s	135
	关机点高度/km	198.8
	关机点速度/(km/s)	4.85
	可拦弧段时间	T~235 s
拦截导弹初始参数	发弹时间	T
	关机点时间	T+60 s
	关机点速度/(km/s)	约6

起始时间	动作
T	拦截导弹点火发射，开启初制导
T+2.6 s	开始程序转弯
T+6 s	结束程序转弯，依靠重力转弯
T+15 s	进入中制导(经典比例导引)
T+76.9 s	进入末制导(经典比例导引)
T+85 s	拦截目标

起始时间	动作
T	拦截导弹点火发射，开启初制导
T+2.6 s	开始程序转弯
T+6 s	结束程序转弯，依靠重力转弯
T+15 s	进入中制导(修正比例导引)
T+76.4 s	进入末制导(修正比例导引)
T+85.1 s	拦截目标

起始时间	动作
T	拦截导弹点火发射，开启初制导
T+2.6 s	开始程序转弯
T+6 s	结束程序转弯，依靠重力转弯
T+15 s	进入中制导(预测命中点导引)
T+75.7 s	进入末制导(修正比例导引)
T+84.6 s	拦截目标

[1]	Shao Cheng, Sun Hongyuan, Zhang Lin. Simulation of Anti-ship Missile Automatic Control Section Trajectory Based on PSO-LSSVM [J]. Journal of System Simulation, 2021, 33(4): 918-926.
[2]	Sun Shuguang, Cheng Peng. 3D Flight Trajectory Simulation Generator Based on Track Constraints [J]. Journal of System Simulation, 2019, 31(2): 275-283.
[3]	Li Longyue, Liu Fuxian, Zhao Huizhen. Modeling and Simulation of Missile Defense M/M/N Queueing System [J]. Journal of System Simulation, 2018, 30(4): 1260-1271.
[4]	Zhang Guoqiang, Liu Xiaohe, Jiang Fangting, Li Zhiping. Research on Development and Integration Method of BMDS Integrated Test and Training Environment [J]. Journal of System Simulation, 2016, 28(4): 898-906.
[5]	Mo Cuiqiong, Li Jiahai, Dai Huanyao, Chen Qiuju, Zhao Jing. Velocity Deception Jamming Analysis of Coherent Video Simulation of Anti-ship PD Seeker [J]. Journal of System Simulation, 2015, 27(5): 1024-1029.