中文摘要：

针对制导火箭落点速度的约束要求，提出了一种采用锥形运动控制导弹飞行速度的导引方法。该方法首先设计了满足速度约束的虚拟目标理想运动轨迹，将导弹减速控制问题转化为对虚拟目标的追踪导引问题，通过建立制导火箭与虚拟目标的相对运动模型，分析了弹目相对位置和相对速度的关系，推导了具有速度控制的导引律一般形式，并采用动态逆控制理论设计了锥形运动控制指令和导引参数。通过数字仿真对比了不同落角约束条件下导弹锥形运动的速度控制效果，结果表明该方法设计的导引律能够满足制导火箭速度约束要求，且制导精度高、控制效果好，为导弹锥形运动速度控制技术提供了参考。

英文摘要：

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 ve- locity 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.