Affiliation:
1. University Politehnica of Bucharest
Abstract
This paper presents a design approach for the automatic flight control system of a launch vehicle using a linear quadratic integral technique together with a fixed gain Kalman filter. Its purpose is to analyse the stability and tracking robustness performances of the control system designed via this approach when atmospheric disturbances, modeling uncertainties and structural flexible modes of the launcher are taken into account.
Publisher
Trans Tech Publications, Ltd.
Reference16 articles.
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2 articles.
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