适合于机动弹道导弹的星光—惯性组合制导系统研究  

Study on Stellar-Inertial Integrated Guidance System for Mobile Ballistic Missile

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：《航空学报》2005年第2期168-172,共5页Acta Aeronautica et Astronautica Sinica

基　　金：国防基础研究项目资助

摘　　要：机动弹道导弹通常会带来较大的初始定位定向误差,星光 惯性组合制导系统能有效地修正初始定位定向误差,提高惯导系统的精度。本文详细介绍了基于一种随动平台的星光 惯性组合制导系统的原理;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。仿真结果表明了该方案的有效性。Mobile ballistic missile is associated with poor initial attitude alignment of the inertial platform and poor initial position data. Stellar-inertial integrated guidance system can update the initial errors and overcome the shortcomings of the inertial platform. A kind of stellar-inertial integrated guidance system based on followup platform is introduced in detail. The computing formulae are deduced required for controlling the follow-up platform to rotate; the principle of the follow-up platform＇s tracking star is researched; the measurement process of stellar-tracker to the platform＇s error angles is discussed; and the relationship between the output of stellar-tracker and the error angle of inertial platform is deduced. The simulating results show that the scheme is valid.

关 键 词：随动平台 星体跟踪器 组合制导 平台误差 

分 类 号：V44[航空宇航科学与技术—飞行器设计]