Flight control system design for a flying-wing aircraft

Mingxing Xu; Xiaoping Zhu; Zhou Zhou; Bo Zhang

doi:10.1109/TENCON.2013.6718805

Flight control system design for a flying-wing aircraft

Mingxing Xu
, Xiaoping Zhu
, Zhou Zhou
, Bo Zhang

航空学院

Northwestern Polytechnical University Xian

科研成果: 书/报告/会议事项章节 › 会议稿件 › 同行评审

4 引用（Scopus）

摘要

In this paper, the flight control system of a flying-wing aircraft is designed. Significant dynamic nonlinearity and control redundancy are main problems for a flying-wing aircraft. As the over-actuated system and dynamic nonlinearity, the flight control system is divided into two parts: control laws and control allocation. Nonlinear dynamic inversion is used to design the control laws to generate control moments as the commands of control allocator. Because the relationship between moment and effector deflection is nonlinear, the nonlinear control allocation based on SQP is designed. The nonlinear control allocation can reduce the errors between commands and responses of control moments.

源语言	英语
主期刊名	2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013 - Conference Proceedings
DOI	https://doi.org/10.1109/TENCON.2013.6718805
出版状态	已出版 - 2013
活动	2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013 - Xi'an, Shaanxi, 中国期限: 22 10月 2013 → 25 10月 2013

出版系列

姓名	IEEE Region 10 Annual International Conference, Proceedings/TENCON
ISSN（印刷版）	2159-3442
ISSN（电子版）	2159-3450

会议

会议	2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013
国家/地区	中国
市	Xi'an, Shaanxi
时期	22/10/13 → 25/10/13

访问文件

10.1109/TENCON.2013.6718805

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引用此

@inproceedings{a9d19944ec034af9b7298cb9d893c33a,

title = "Flight control system design for a flying-wing aircraft",

abstract = "In this paper, the flight control system of a flying-wing aircraft is designed. Significant dynamic nonlinearity and control redundancy are main problems for a flying-wing aircraft. As the over-actuated system and dynamic nonlinearity, the flight control system is divided into two parts: control laws and control allocation. Nonlinear dynamic inversion is used to design the control laws to generate control moments as the commands of control allocator. Because the relationship between moment and effector deflection is nonlinear, the nonlinear control allocation based on SQP is designed. The nonlinear control allocation can reduce the errors between commands and responses of control moments.",

keywords = "flying-wing aircraft, nonlinear control allocation, nonlinear dynamic inversion, sequential quadratic programming",

author = "Mingxing Xu and Xiaoping Zhu and Zhou Zhou and Bo Zhang",

year = "2013",

doi = "10.1109/TENCON.2013.6718805",

language = "英语",

isbn = "9781479928262",

series = "IEEE Region 10 Annual International Conference, Proceedings/TENCON",

booktitle = "2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013 - Conference Proceedings",

note = "2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013 ; Conference date: 22-10-2013 Through 25-10-2013",

}

Xu, M, Zhu, X, Zhou, Z & Zhang, B 2013, Flight control system design for a flying-wing aircraft. 在 2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013 - Conference Proceedings., 6718805, IEEE Region 10 Annual International Conference, Proceedings/TENCON, 2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013, Xi'an, Shaanxi, 中国, 22/10/13. https://doi.org/10.1109/TENCON.2013.6718805

TY - GEN

T1 - Flight control system design for a flying-wing aircraft

AU - Xu, Mingxing

AU - Zhu, Xiaoping

AU - Zhou, Zhou

AU - Zhang, Bo

PY - 2013

Y1 - 2013

N2 - In this paper, the flight control system of a flying-wing aircraft is designed. Significant dynamic nonlinearity and control redundancy are main problems for a flying-wing aircraft. As the over-actuated system and dynamic nonlinearity, the flight control system is divided into two parts: control laws and control allocation. Nonlinear dynamic inversion is used to design the control laws to generate control moments as the commands of control allocator. Because the relationship between moment and effector deflection is nonlinear, the nonlinear control allocation based on SQP is designed. The nonlinear control allocation can reduce the errors between commands and responses of control moments.

AB - In this paper, the flight control system of a flying-wing aircraft is designed. Significant dynamic nonlinearity and control redundancy are main problems for a flying-wing aircraft. As the over-actuated system and dynamic nonlinearity, the flight control system is divided into two parts: control laws and control allocation. Nonlinear dynamic inversion is used to design the control laws to generate control moments as the commands of control allocator. Because the relationship between moment and effector deflection is nonlinear, the nonlinear control allocation based on SQP is designed. The nonlinear control allocation can reduce the errors between commands and responses of control moments.

KW - flying-wing aircraft

KW - nonlinear control allocation

KW - nonlinear dynamic inversion

KW - sequential quadratic programming

UR - https://www.scopus.com/pages/publications/84894292059

U2 - 10.1109/TENCON.2013.6718805

DO - 10.1109/TENCON.2013.6718805

M3 - 会议稿件

AN - SCOPUS:84894292059

SN - 9781479928262

T3 - IEEE Region 10 Annual International Conference, Proceedings/TENCON

BT - 2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013 - Conference Proceedings

T2 - 2013 IEEE International Conference of IEEE Region 10, IEEE TENCON 2013

Y2 - 22 October 2013 through 25 October 2013

ER -

Flight control system design for a flying-wing aircraft

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