Data-Driven-Based Impact Time Control Guidance Law Independent of Time-to-Go

doi:10.12382/bgxb.2022.0324

Abstract

Abstract:

To solve the problem of missile impact time control, a two-stage impact time control guidance law is designed based on proportional navigation guidance and the data-driven method, which is independent of time-to-go information. The first stage is the impact time control stage. The relationship data set between the flight path angle and the flight state of the missile is constructed by simulation under the framework of proportional navigation guidance method, and then the corresponding mapping network model is trained offline by using the neural network method. According to the mapping network, the ideal flight path angle corresponding to the impact time can be calculated in real time during missile flight, and the guidance command will control the actual flight path angle converging to the ideal one. In the second stage, the proportional navigation guidance law is directly applied, and the missile impact time control is finally realized. The simulation results under different conditions verify the feasibility and effectiveness of the proposed guidance law. Compared with the existing similar guidance laws, the proposed one can control the impact time with higher precision and less control energy. In addition, the theoretical analysis shows that the guidance law can be extended to impact angle control by changing the mapping network.

Key words: data-driven method, proportional navigation guidance, ideal flight path angle, impact time control, impact angle control

CLC Number:

TJ765.3

HUANG Jia, CHANG Sijiang, CHEN Qi, ZHANG Haiyang. Data-Driven-Based Impact Time Control Guidance Law Independent of Time-to-Go[J]. Acta Armamentarii, 2023, 44(8): 2299-2309.

Figures/Tables 11

Fig.1 Relationship of missile-target engagement

Fig.2 Structure diagram of neural network

Fig.3 Error variation during training

Fig.4 Simulation results of different desired impact time

Fig.5 Simulation results of errors in flight state variables

Table 1 Errors of impact time corresponding to different desired impact time

序号	R、γ是否存在误差	期望攻击时间/s	实际攻击时间与期望值之差/s
1	否	45	0.013
2	否	50	0.021
3	否	55	0.022
4	否	60	0.012
5	否	65	0.005
6	是	65	0.005

Fig.6 Simulation results compared with Ref.[10]

Table 2 Comparison of performance between the proposed guidance law and the one in Ref. [10]

序号	导引律	初始前置角/ (°)	攻击时间误差/s	加速度极值绝对值/ (m·s^-2)	总控制能量/ (m²·s^-3)
1	本文	15	0.002	22.59	7.69×10³
2	文献[10]	15	0.039	98.00	1.08×10⁴
3	本文	45	0.005	20.97	5.43×10³
4	文献[10]	45	0.041	42.41	5.72×10³

Fig.7 Simulation results of cooperative attack

Table 3 Simulation parameters and results of cooperative attack

仿真对象	位置/m	初始前置角/(°)	攻击时间误差/s
导弹1	(-5000,-7000)	30	0.032
导弹2	(-10000,0)	40	0.012
导弹3	(-10392.3,6000)	20	0.025
目标	(0,0)	0	0

Fig.8 Simulation results of different desired impact angles

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