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Study on strapdown stellar-inertial integrated guidance system for launch vehicle

ZHANG Li-jun1,ZHANG Shi-feng1,QIAN Shan2 1.College of Aerospace and Material Engineering,National University of Defence Technology,Changsha 410073,China; 2.China Xi'an Satellite Control Center,Xi'an 710043,China)  
In this paper,a strapdown stellar-inertial integrated guidance system was presented to satisfy the requirement of space rapid reaction for launch vehicle.The major errors derived from initial localization and orientation,initial attitude alignment and the drift of inertial sensors were analyzed.Both error angle model of digital platform and navigation error model were established,and a dual star correction scheme was presented subsequently.Numerical examples were given for the analysis of the influence of each error factor on the strapdown inertial navigation system,and the feasibility and validity of the integrated guidance scheme were verified.
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