弹道导弹捷联惯性/星光复合制导系统模型研究  

A Study on Model of Strapdown Inertial/Starlight Integrated Guidance System for Ballistic Missiles

作　　者：王新龙[1] 谢佳[1] 郭隆华[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《弹道学报》2008年第3期87-91,共5页Journal of Ballistics

基　　金：航天创新基金及航天支撑资金项目(044.107)

摘　　要：推导了星光制导量测信息修正捷联惯性制导系统姿态角误差的机理,讨论了复合制导系统的主要误差,建立了全捷联工作模式的惯性/星光复合制导系统误差模型.针对捷联惯性制导系统的初始位置误差、对准误差及惯性元器件漂移所造成的制导误差,提出了一种适用于弹道导弹的星光修正捷联惯性的复合制导方案.仿真结果表明,当弹道导弹飞出大气层后,利用星体跟踪器获得的精确弹体三轴姿态信息调正捷联惯性制导系统的方案是合理、可行的,这种自主复合制导系统能够满足弹道导弹高精度的制导要求.The principle of using the measurement information of starlight guidance system to adjust the errors of pose angles of strapdown inertial guidance was deduced. The major errors of intergrated guidance system were discussed, and the error model of strapdown inertial/starlight integrated guidance system was founded. Aiming at the guidance errors caused by the errors of initial position, attitude alignment and inertia sensors, a novel scheme was proposed to use the starlight guidance to update the strapdown inertial guidance system. The simulation results show that the plan of using the precise pose measurement value of stellar-trackers to adjust the strapdown inertial guidance system is reasonable and feasible, and the characteristics of this independ- ent integrated guidance system can satisfy high precise guidance demand of ballistic missiles.

关 键 词：惯性制导 星光制导 复合制导 星体跟踪器 

分 类 号：TP319.9[自动化与计算机技术—计算机软件与理论]