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Journal of System Simulation

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, midguidance 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.

First Page

335

Last Page

344

CLC

TP391.9; TJ765.4

Recommended Citation

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

Corresponding Author

Li Xu

DOI

10.16182/j.issn1004731x.joss.23-1588

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