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2019 | OriginalPaper | Buchkapitel

Robust Attitude Control System Design for a Distributed Propulsion Tilt-Wing UAV in Flight State Transition

verfasst von : Siqi Wang, Bifeng Song, Lei He

Erschienen in: The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018)

Verlag: Springer Singapore

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Abstract

This paper describes the establishment and analysis of a robust attitude control system for a distributed tilt-wing UAV in the flight state transition procedure. Firstly, a complete nonlinear dynamic model of the target UAV was developed. Secondly, a selection of the transition strategy and a unified nonlinear control allocation model were determined, based on which, an optimal linearized control allocation method towards four deflect angles was developed. Thirdly, robust attitude controllers towards four deflect angles were designed through \( \mu \) synthesis method and D-K iteration. In the end, a scheduling model is involved to simulate the whole procedure of the flight state transition and the results of the simulation reach the requirement of performance.

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Vorheriges Kapitel Cooperative Formation Control Technology for Manned/Unmanned Aerial Vehicles

Nächstes Kapitel Safety Envelope Determination for Impaired Aircraft During Landing Phase Based on Reachability Analysis

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Titel: Robust Attitude Control System Design for a Distributed Propulsion Tilt-Wing UAV in Flight State Transition
verfasst von: Siqi Wang
Bifeng Song
Lei He
Verlag: Springer Singapore
Buch: The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018)
Print ISBN: 978-981-13-3304-0

Electronic ISBN: 978-981-13-3305-7

Copyright-Jahr: 2019
DOI: https://doi.org/10.1007/978-981-13-3305-7_190

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