SINS/CNS组合导航半实物仿真系统及其实验研究  

Realization and Experimental Research for Hybrid Simulation System of SINS/CNS Integrated Navigation

作　　者：全伟[1] 房建成[1] 

机构地区：[1]北京航空航天大学仪器与光电工程学院,北京100083

出　　处：《系统仿真学报》2007年第15期3414-3418,共5页Journal of System Simulation

基　　金：国家自然科学基金(60574086)

摘　　要：因航天实验费用大,组合导航系统的性能及算法很难都通过飞行实验进行测试,为此提出了一种高性能捷联惯性/天文组合导航半实物仿真系统。该系统遵循硬件功能模块化和软件流程一体化的设计思想;利用轨迹发生终端生成标称轨迹数据,作为信息处理统一参考源;采用时间软同步并行采集惯、性、天文系统真实误差数据;通过平滑处理,结合标称轨迹数据完成性能测试。它具有强的灵活性和可扩展性,利用其可有效地降低组合导航系统的实验成本,缩短研制周期;这对研究组合导航系统的算法性能、系统特性和工程应用等具有重要理论和实践意义。To validate and corroborate a designed Strapdown inertial navigation system （SINS） / celestial navigation system （CNS）, spacecraft＇s actual flight will involve a lot of efforts as well as a heavy financial budget. At design stage, it is impossible for debugging performance and testing algorithms of integrated navigation system on the ground to take real time flight experiment. To the problem, a high performance hybrid simulation system of SINS/CNS integrated navigation was proposed. The system adopted the design of hardware-functional modularization and software-flow integration, and made use of trajectory generator to produce nominal trajectory data which was a uniform reference to signal process, and employed time soft-synchronization technique to collect actual errors data of inertial, celestial system. Combining with nominal trajectory data and through the data smoothing, this system accomplished the performance testing. It has the feature of flexibility and extensibility and can be used to reduce effectively the experimental expense and shorten the developing period of integrated navigation system, which is significant for studying algorithm performance, system speciality and project application of integrated navigation system.

关 键 词：捷联惯性导航 天文导航 SINS/CNS组合导航 半实物仿真 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]