Trajectory optimization for satellite fast attitude maneuver based on collocation method

Jiang Bingqiang; Ye Dong; Sun Zhaowei

doi:10.1109/ICMC.2014.7231761

Trajectory optimization for satellite fast attitude maneuver based on collocation method

Jiang Bingqiang
, Ye Dong
, Sun Zhaowei

School of Astronautics, Harbin Institute of Technology

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

2 Scopus citations

Abstract

Aircraft trajectory optimization is the key to overall aircraft design, it plays an important role in modern aircraft design. In this paper, agile satellite attitude maneuver problem, is studied based on Time-Optimal and direct collocation method to get the agile satellite maneuvering trajectory optimization and simulation verification. The results is bang-bang mode, and the size of the deviation affect the accuracy of the result, the control torque change times will depends on the manuvering.

Original language	English
Title of host publication	Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	1294-1298
Number of pages	5
ISBN (Electronic)	9781479925384
DOIs	https://doi.org/10.1109/ICMC.2014.7231761
State	Published - 31 Aug 2015
Externally published	Yes
Event	International Conference on Mechatronics and Control, ICMC 2014 - Jinzhou, China Duration: 3 Jul 2014 → 5 Jul 2014

Publication series

Name	Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014

Conference

Conference	International Conference on Mechatronics and Control, ICMC 2014
Country/Territory	China
City	Jinzhou
Period	3/07/14 → 5/07/14

Keywords

Agile satellite
Direct collocation method
Optimal-time Attitude maneuver

Access to Document

10.1109/ICMC.2014.7231761

Cite this

Bingqiang, J., Dong, Y., & Zhaowei, S. (2015). Trajectory optimization for satellite fast attitude maneuver based on collocation method. In Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014 (pp. 1294-1298). Article 7231761 (Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ICMC.2014.7231761

Bingqiang, Jiang ; Dong, Ye ; Zhaowei, Sun. / Trajectory optimization for satellite fast attitude maneuver based on collocation method. Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014. Institute of Electrical and Electronics Engineers Inc., 2015. pp. 1294-1298 (Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014).

@inproceedings{e57f7094a58d4216a892b9397b338398,

title = "Trajectory optimization for satellite fast attitude maneuver based on collocation method",

abstract = "Aircraft trajectory optimization is the key to overall aircraft design, it plays an important role in modern aircraft design. In this paper, agile satellite attitude maneuver problem, is studied based on Time-Optimal and direct collocation method to get the agile satellite maneuvering trajectory optimization and simulation verification. The results is bang-bang mode, and the size of the deviation affect the accuracy of the result, the control torque change times will depends on the manuvering.",

keywords = "Agile satellite, Direct collocation method, Optimal-time Attitude maneuver",

author = "Jiang Bingqiang and Ye Dong and Sun Zhaowei",

note = "Publisher Copyright: {\textcopyright} 2014 IEEE.; International Conference on Mechatronics and Control, ICMC 2014 ; Conference date: 03-07-2014 Through 05-07-2014",

year = "2015",

month = aug,

day = "31",

doi = "10.1109/ICMC.2014.7231761",

language = "英语",

series = "Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014",

publisher = "Institute of Electrical and Electronics Engineers Inc.",

pages = "1294--1298",

booktitle = "Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014",

address = "美国",

}

Bingqiang, J, Dong, Y & Zhaowei, S 2015, Trajectory optimization for satellite fast attitude maneuver based on collocation method. in Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014., 7231761, Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014, Institute of Electrical and Electronics Engineers Inc., pp. 1294-1298, International Conference on Mechatronics and Control, ICMC 2014, Jinzhou, China, 3/07/14. https://doi.org/10.1109/ICMC.2014.7231761

Trajectory optimization for satellite fast attitude maneuver based on collocation method. / Bingqiang, Jiang; Dong, Ye ; Zhaowei, Sun.
Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014. Institute of Electrical and Electronics Engineers Inc., 2015. p. 1294-1298 7231761 (Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014).

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

TY - GEN

T1 - Trajectory optimization for satellite fast attitude maneuver based on collocation method

AU - Bingqiang, Jiang

AU - Dong, Ye

AU - Zhaowei, Sun

PY - 2015/8/31

Y1 - 2015/8/31

N2 - Aircraft trajectory optimization is the key to overall aircraft design, it plays an important role in modern aircraft design. In this paper, agile satellite attitude maneuver problem, is studied based on Time-Optimal and direct collocation method to get the agile satellite maneuvering trajectory optimization and simulation verification. The results is bang-bang mode, and the size of the deviation affect the accuracy of the result, the control torque change times will depends on the manuvering.

AB - Aircraft trajectory optimization is the key to overall aircraft design, it plays an important role in modern aircraft design. In this paper, agile satellite attitude maneuver problem, is studied based on Time-Optimal and direct collocation method to get the agile satellite maneuvering trajectory optimization and simulation verification. The results is bang-bang mode, and the size of the deviation affect the accuracy of the result, the control torque change times will depends on the manuvering.

KW - Agile satellite

KW - Direct collocation method

KW - Optimal-time Attitude maneuver

UR - https://www.scopus.com/pages/publications/84953709429

U2 - 10.1109/ICMC.2014.7231761

DO - 10.1109/ICMC.2014.7231761

M3 - 会议稿件

AN - SCOPUS:84953709429

T3 - Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014

SP - 1294

EP - 1298

BT - Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014

PB - Institute of Electrical and Electronics Engineers Inc.

T2 - International Conference on Mechatronics and Control, ICMC 2014

Y2 - 3 July 2014 through 5 July 2014

ER -

Bingqiang J, Dong Y , Zhaowei S. Trajectory optimization for satellite fast attitude maneuver based on collocation method. In Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014. Institute of Electrical and Electronics Engineers Inc. 2015. p. 1294-1298. 7231761. (Proceedings - 2014 International Conference on Mechatronics and Control, ICMC 2014). doi: 10.1109/ICMC.2014.7231761

Trajectory optimization for satellite fast attitude maneuver based on collocation method

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