小视场下巡航导弹天文制导设计与仿真  

Celestial technology based guidance design and simulation for cruise missile under small field of view

作　　者：李伟[1] 王安国[1] 唐君[1] 

机构地区：[1]海军大连舰艇学院航海系,辽宁大连116018

出　　处：《红外与激光工程》2014年第10期3457-3461,共5页Infrared and Laser Engineering

基　　金：国家科技支撑计划课题(2012BAH36B03)

摘　　要：为了提高远程反舰导弹的巡航制导能力,增大有效射程,在对未来海战场特点和相关技术背景进行客观分析的基础上,结合小视场天文导航技术的特点,提出了以天文测角导航技术作为中远程导弹巡航阶段主要制导手段的制导方法,提出了"制导角"的概念,给出了系统设计,列举了系统的技术优势。制导系统分为三个阶段,即初始参数装订与计算、制导角修正和末制导确认,分别给出了计算公式和相关推导,并用数学计算工具对一个想定情况进行了仿真计算。仿真结果表明,制导角连续可用,系统误差在可控范围之内,系统可以有效进行巡航制导。In order to improve the cruising guidance ability of the remote anti-ship missile and to increase the effctive range, based on the objective analysis for the future sea battlefield and the features of the celestial navigation about small field of view, a celestial angle measurement based guidance way was put forward which will serve as the main method for the guidance of remote missile on it′s cruise phase , gave out the system analysis for feasibility and listed the superiorities. With the new concept of ＂guidance angle＂, the guidance system can be divided into three stages, namely initial parameters′s binding and calculation, guidance angle′s correction and terminal guidance confirmation, their respective calculation formula and related derivation were given, a specific example was used to carry out computer simulation. The simulation results show that guidance system can serve as an effective cruise guidance method, it witnesses a successive guidance angle and a permitted error, which bears important significance for the overal design of modern missile.

关 键 词：小视场 巡航导弹 巡航制导 天文测角 制导角 海上大目标 

分 类 号：P128.4[天文地球—天体测量]