载人运载火箭惯性器件冗余管理中的精度控制技术  

Precision Control Technology in IMU Redundancy Management for Manned Launch Vehicle

作　　者：周涛[1] 施国兴[1] 胡海峰[1,2] 宁尧 Zhou Tao;Shi Guo-xing;Hu Hai-feng;Ning Yao(Beijing Aerospace Automatic Control Institute,Beijing,100854;National Key Laboratory of Aerospace Intelligent Control Technology,Beijing,100854)

机构地区：[1]北京航天自动控制研究所,北京100854 [2]宇航智能控制技术国家级重点实验室,北京100854

出　　处：《导弹与航天运载技术》2022年第1期59-64,共6页Missiles and Space Vehicles

摘　　要：运载火箭控制系统通过惯性器件冗余信息进行故障检测以提高系统可靠性,还可对惯组冗余信息采用信息融合技术以提高火箭入轨精度。以中国现役载人运载火箭控制系统双七表捷联惯组冗余设计为例,研究惯性器件冗余管理中的精度控制技术,提出了基于惯性冗余信息故障诊断和信息融合的精度控制技术,并以其他火箭实际飞行故障案例进行仿真分析。仿真结果表明,提出的惯性器件冗余管理中的精度控制技术能有效判别故障信息,提高火箭入轨精度。The redundancy information of IMU has been used to detect fault in order to improve system reliability for the launch vehicle control system.Information synthesis technology also can be used for the redundant information of IMU to improve orbital accuracy.The IMU redundant design based on dual seven-meter strapdown in manned launch vehicle control system is taken as an example,the precision control technology in IMU redundancy management and is researched a precision control technology based on IMU redundancy information fault diagnosis and information synthesis is proposed.This method is used to simulate and analyze other rocket actual flight failure cases.Simulation results show that this precision control technology in the redundancy management of IMU proposed can effectively distinguish the fault information and improve the orbit accuracy for the launch vehicle.

关 键 词：冗余管理 故障诊断 信息融合 入轨精度 

分 类 号：V448.131[航空宇航科学与技术—飞行器设计]