基于锥形运动的制导火箭速度控制导引律设计

doi:10.7527/S1000-6893.2013.0407

Abstract

Abstract:

This paper develops a novel coning motion-based guidance method for a missile with impact velocity control. First, an ideal trajectory of a virtual target is designed based on the requirement of impact velocity, and the problem of velocity control for the missile is transformed into that of tracking the virtual target. Then, the locomotion models of the guided rocket and the virtual target are formulated. Furthermore, the information of the relative position and velocity between the rocket and the virtual target is used for the formula derivation of the coning motion-based guidance law. Based on the theory of dynamic inversion, the guidance parameters and commands are designed. Finally, the new guidance method is evaluated using a simulation of the typical terminal guidance for a guided rocket with velocity control. Simulation results demonstrate that the proposed guidance law has a good performance and can be applied to the guidance of missiles with impact velocity control in different impact angle constraints, which provides some significant reference for the technology of velocity control.

Key words: guided rocket, coning motion, velocity control, guidance law, dynamic inversion, virtual target

CLC Number:

LIU Pengyun, SUN Ruisheng, LI Weiming, MING Chao. A Coning Motion-based Guidance Law for Guided Rocket with Velocity Control[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(4): 933-941.

References

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A Coning Motion-based Guidance Law for Guided Rocket with Velocity Control

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