平台式主惯导半实物模拟系统的研制  

Development of a Semi-Physical Simulation System for INS Platform

作　　者：徐剑芸[1,2] 鲁浩[2] 李群生[2] 庞秀枝[2] 

机构地区：[1]上海交通大学航空航天学院,上海200240 [2]中国空空导弹研究院,河南洛阳471009

出　　处：《电光与控制》2010年第1期61-64,96,共5页Electronics Optics & Control

摘　　要：为评估空空导弹捷联惯导系统对准和导航精度,研制平台式主惯导半实物模拟系统进行捷联惯导系统对准和导航性能试验。该模拟系统模拟两种国产平台式惯导系统的功能、性能、逻辑时序以及总线接口形式等,可接收外部按一定格式编排的飞行轨迹参数,或者系统自动生成飞行轨迹,包括飞机各种典型的机动动作。经过精确计算后,系统通过1553B/429总线输出各种导航参数、控制信息及状态信息。实现了惯导测试中模拟系统与实际平台式主惯导的可互换使用。In order to evaluate the alignment and navigation precision of Strap-down Inertial Navigation System（SINS） onboard air-to-air missiles, one type of semi-physical simulation system was developed for testing the alignment and navigation performance of the SINS. The system simulated the function, performance ,logic working procedure and bus interface of two types of domestic INS platforms. It can receive the flight trajectory parameters from outside, or generate a flight trajectory automatically, including all kinds of typical maneuvering actions. After calculation, the 1553B/429 bus was used for outputting all kinds of navigation parameters, control information and status information. The simulation system and real INS can be used interchangeably in testing.

关 键 词：空空导弹 平台式主惯导 半实物模拟系统 飞行轨迹 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计] TN956[电子电信—信号与信息处理]