Research On Star/sins Integrated Navigation System

In modern navigation, the Strapdown Inertial Navigation System(SINS)was widely used for it's advantages such as independence,concealment , wide frequency band and all-around information. The disadvantage and deficiency of SINS is also obvious because as the drift errors of the inertial measurement component increase with time, the accumulated error make it unsuitable for long-time operating continuously. The star sensor wins general popularity in modern navigation for its high accuracy, intelligence and working without accumulate error. The SINS/CNS integrated navigation mode is formed in recent years to correct the navigation parameter, it gives priority to the strapdown inertial navigation system and it is complemented by the stars information. The integrated navigation system can improve aircraft's navigation accuracy obviously.This paper does research on the SINS/CNS Integrated Navigation System,it is mainly constituted by the following aspects:Fristly,this paper does the research on quaternion theory and coordinate system theory, It also analyses the basis principle of the strapdown inertial navigation system and its error propagation,it also analyses the basis knowledge of celestial navigation and makes the research of the astronomical navigation system.Secondly, the stateequtation of integrated navigation system is established.The observation equtation of integrated navigation system is established by attitude quaternion error defined by attitude quaternion of SINS and star sensor.Finally, the paper deduces the Kalman filter theory and uses the Kalman filter to the combine the two navigation systems and do a series of analysis about the Integrated Navigation System.