Three-dimensional Fixed-time Attack Proportional Guidance Law Based on Variable Power Sliding Mode for Multiple Missiles

doi:10.12382/bgxb.2024.0437

Abstract

Abstract:

Aiming at the problem of simultaneous attack of multiple missiles against the important targets,a three-dimensional fixed-time attack proportional guidance law based on variable power sliding mode is proposed for multiple missiles.A missile-target dynamics model in three-dimensional space is established.To reduce the complexity of designing a control method in three-dimensional space,a reference plane is determined in three-dimensional space,and the missile-target state vector in three-dimensional space is decomposed into two components parallel and perpendicular to the reference plane.Control methods are designed separately in the reference plane.The method parallel to the reference plane is based on the proportional guidance method,The tangential and normal accelerations are designed as the control inputs to drive the missile to reach the remaining flight time consistency before the desired attack moment.Additionally,for the component perpendicular to the reference plane,a guidance law is designed using an improved sliding mode control method based on variable power to achieve the rapid convergence in the early stage and the stable control in the terminal stage for the multi-missile system.When the consistent control of both components along the reference plane is realized in a preset attack time,the multi-missile system can complete the synchronized attack in the three-dimensional space.Furthermore,the synchronized attack on the target by the multi-missile system in the asynchronous launching scenario can be realized by compensating the launch delay of each missile in the guidance law.The performance of the proposed three-dimensional guidance law is verified by simulation,which is characterized by fast convergence and high stability.The guidance law is not only applicable to synchronous launching scenarios,but also adds only the launch delay of each missile to the input to complete the consistency control of attack time.

Key words: missile, variable power sliding mode control, proportional guidance law, fixed-time attack, three-dimensional attack scenarios

CLC Number:

TJ301

LI Jian, LIU Peng, YU Xiaohao, YU Hang, LI Changsheng, SHI Yunlei, ZHANG He. Three-dimensional Fixed-time Attack Proportional Guidance Law Based on Variable Power Sliding Mode for Multiple Missiles[J]. Acta Armamentarii, 2025, 46(7): 240437-.

Figures/Tables 7

Fig.1 Schematic diagram of a three-dimensional attack scenario

Fig.2 Schematic diagram of three-dimensional state vector decomposition of missile

Fig.3 Missile dynamics model on parallel reference plane

Table 1 Initial states of missiles

导弹与目标	位置信息/m	初始速度垂向分量/ (m·s^-1)	初始速度平行向分量/ (m·s^-1)	速度水平分量航向角/ rad
导弹1	(5000,5000,-50)	350	-35	0.09
导弹2	(4000,4500,80)	320	20	-0.10
导弹3	(3000,3000,-40)	270	-25	0.11
导弹4	(1000,4000,45)	400	22	-0.15
导弹5	(3500,2000,-60)	330	-35	0.12
目标	(15000,15000,0)

Fig.4 Three-dimensional spatial trajectory and missile-target distance

Fig.5 Motion parameters of missile on vertical reference plane

Fig.6 Motion parameters of missile on vertical reference plane

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