运载火箭摄动制导导引系数实时计算方法

对于新型运载火箭,没有相近型号导引系数数据供参考,采用传统试探法计算量大,在制导方案初期论证中不能满足多方案快速计算的需求。在引入理想弹道剩余飞行速度概念的基础上,提出导引系数实时计算方法。本方法对当前实时状态参数和后续飞行段弹道进行了综合考虑,通过数字仿真表明导引精度高于传统常系数导引方法。由于本方法对导引能力进行了预估,因而制导指令不会剧烈变化,易于姿态控制系统的设计实现。同时,由于采用完全解析法,对箭载计算机计算能力要求几乎没有增加,易于工程实现。

Research on the real-time calculation of perturbation guidance coefficients for the launch vehicle

The guidance precision of the launch vehicle during the flight stage within the atmosphere is greatly affected by the guidance coefficients of perturbation guidance. However, there are no comparable database for the guidance coefficients selection in the argumentation of a new launch vehicle. It cannot meet the demand for rapid calculation using the traditional test method. A real-time calculation method for the guidance coefficient which considers both the real-time status and the follow-up flight trajectory is proposed in this paper based on introducing the concept of remaining flight speed in the standard trajectory. Through the numerical simulation, it is proved that higher guidance precision is achieved by the proposed method in comparison with the traditional method with constant coefficients. Since the guide capacity is predicted by this method, the guidance instruction do not change dramatically, which contributes to easy design for the attitude control system. Meanwhile, a fully analytical method is developed, so there is no additional calculation requirement for the rocket-born computer, giving rise to convenient engineering realization.