Affiliation:
1. Beijing Institute of Technology
Abstract
Inertial navigation system’s position error and velocity error are accumulated over time, it certainly affect the end guidance accuracy of the air munitions. To solve this problem, the information which includes altitude angle, azimuth angle, their angle velocity and altitude provided by passive seeker and altimeter is used for amending INS error with UKF algorithm in end-guidance phase. Through computer simulation the feedback filter with altimeter is better than that without altimeter.
Publisher
Trans Tech Publications, Ltd.
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1 articles.
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