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

Siqi Wang; Bifeng Song; Lei He

doi:10.1007/978-981-13-3305-7_190

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

Siqi Wang
, Bifeng Song
, Lei He

School of Aeronautics

Northwestern Polytechnical University Xian

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

4 Scopus citations

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.

Original language	English
Title of host publication	The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018
Editors	Xinguo Zhang
Publisher	Springer Verlag
Pages	2368-2387
Number of pages	20
ISBN (Print)	9789811333040
DOIs	https://doi.org/10.1007/978-981-13-3305-7_190
State	Published - 2019
Event	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 - Chengdu, China Duration: 16 Oct 2018 → 18 Oct 2018

Publication series

Name	Lecture Notes in Electrical Engineering
Volume	459
ISSN (Print)	1876-1100
ISSN (Electronic)	1876-1119

Conference

Conference	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018
Country/Territory	China
City	Chengdu
Period	16/10/18 → 18/10/18

Keywords

Flight state transition
Optimal control allocation
Robust control
Tilt-wing

Access to Document

10.1007/978-981-13-3305-7_190

Cite this

Wang, S., Song, B., & He, L. (2019). Robust Attitude Control System Design for a Distributed Propulsion Tilt-Wing UAV in Flight State Transition. In X. Zhang (Ed.), The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 (pp. 2368-2387). (Lecture Notes in Electrical Engineering; Vol. 459). Springer Verlag. https://doi.org/10.1007/978-981-13-3305-7_190

@inproceedings{9e20793d8dca44f590397b2321713ed3,

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

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 \$\$ \textbackslash{}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.",

keywords = "Flight state transition, Optimal control allocation, Robust control, Tilt-wing",

author = "Siqi Wang and Bifeng Song and Lei He",

note = "Publisher Copyright: {\textcopyright} 2019, Springer Nature Singapore Pte Ltd.; Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 ; Conference date: 16-10-2018 Through 18-10-2018",

year = "2019",

doi = "10.1007/978-981-13-3305-7\_190",

language = "英语",

isbn = "9789811333040",

series = "Lecture Notes in Electrical Engineering",

publisher = "Springer Verlag",

pages = "2368--2387",

editor = "Xinguo Zhang",

booktitle = "The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018",

}

Wang, S, Song, B & He, L 2019, Robust Attitude Control System Design for a Distributed Propulsion Tilt-Wing UAV in Flight State Transition. in X Zhang (ed.), The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018. Lecture Notes in Electrical Engineering, vol. 459, Springer Verlag, pp. 2368-2387, Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018, Chengdu, China, 16/10/18. https://doi.org/10.1007/978-981-13-3305-7_190

Robust Attitude Control System Design for a Distributed Propulsion Tilt-Wing UAV in Flight State Transition. / Wang, Siqi; Song, Bifeng; He, Lei.
The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018. ed. / Xinguo Zhang. Springer Verlag, 2019. p. 2368-2387 (Lecture Notes in Electrical Engineering; Vol. 459).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

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N2 - 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.

AB - 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.

KW - Flight state transition

KW - Optimal control allocation

KW - Robust control

KW - Tilt-wing

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

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