基于随动平台的天文-惯性复合制导系统在弹道导弹上的应用研究  

On Celestial-Inertial Compound Guidance System Based on Follow-up Platform

作　　者：金振山[1] 申功勋[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《宇航学报》2005年第B10期50-54,共5页Journal of Astronautics

基　　金：国防基础研究项目

摘　　要：详细介绍了基于随动平台的天文-惯性复合制导系统的原理。研究了随动平台跟踪星体的机理;推导了控制随动平台转动所需的计算公式;讨论了星体跟踪器对平台误差角的观测过程;导出了星体跟踪器的测量输出与平台误差角之间的数学方程。仿真结果表明,天文-惯性复合制导系统可以有效地修正导弹的初始定位定向误差及初始对准误差。该系统精度高,可行性强,特别适合在机动发射的弹道导弹上使用。Celestial-inertial compound guidance system based on follow-up platform was introduced in detail. The computing formulae were deduced required for controlling the follow-up platform; the principle of the follow-up platform＇ s tracking star was researched; the measurement process of stellar-tracker to the platform＇ s error angles was discussed; the relationship between the output of stellar-tracker and the error angles of inertial guidance platform was deduced. Simulating results show that the celestialinertial compound guidance system based on follow-up platform can measure the initial launch position errors and initial misalignments efficiently. With the advantages of high accuracy and high feasibility, it applies to mobile ballistic missiles particularly.

关 键 词：随动平台 星体跟踪器 复合制导 制导精度 

分 类 号：V448[航空宇航科学与技术—飞行器设计]