Spacecraft reorientation control with attitude and velocity constrains

Qiang Shen; Cher Hiang Goh; Chengfei Yue; Baolin Wu

doi:10.1109/AERO.2017.7943957

Spacecraft reorientation control with attitude and velocity constrains

Qiang Shen
, Cher Hiang Goh
, Chengfei Yue
, Baolin Wu

National University of Singapore
School of Astronautics, Harbin Institute of Technology

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

1 Scopus citations

Abstract

This paper investigates rest-to-rest attitude reorientation problem for a rigid spacecraft in the presence of attitude and angular velocity constraints. Based on a potential function, a nonlinear attitude controller is developed to avoid the un-desired celestial objects autonomously and limit the spacecraft rotation speed while achieving asymptotic attitude stabilization. To improve the agility of spacecraft, control moment gyro (CMG) is considered as torque-generating actuators for attitude control. General singular robust (GSR) steering logic is employed to determine the CMG gimbal rate commands. The proposed attitude control scheme has simple structure, which is of great interest for aerospace industry when onboard computing power is limited. Finally, simulation results for a CMG-based spacecraft are presented to show the effectiveness of the proposed attitude control systems.

Original language	English
Title of host publication	2017 IEEE Aerospace Conference
Publisher	IEEE Computer Society
ISBN (Electronic)	9781509016136
DOIs	https://doi.org/10.1109/AERO.2017.7943957
State	Published - 7 Jun 2017
Externally published	Yes
Event	2017 IEEE Aerospace Conference, AERO 2017 - Big Sky, United States Duration: 4 Mar 2017 → 11 Mar 2017

Publication series

Name	IEEE Aerospace Conference Proceedings
ISSN (Print)	1095-323X

Conference

Conference	2017 IEEE Aerospace Conference, AERO 2017
Country/Territory	United States
City	Big Sky
Period	4/03/17 → 11/03/17

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10.1109/AERO.2017.7943957

Cite this

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title = "Spacecraft reorientation control with attitude and velocity constrains",

abstract = "This paper investigates rest-to-rest attitude reorientation problem for a rigid spacecraft in the presence of attitude and angular velocity constraints. Based on a potential function, a nonlinear attitude controller is developed to avoid the un-desired celestial objects autonomously and limit the spacecraft rotation speed while achieving asymptotic attitude stabilization. To improve the agility of spacecraft, control moment gyro (CMG) is considered as torque-generating actuators for attitude control. General singular robust (GSR) steering logic is employed to determine the CMG gimbal rate commands. The proposed attitude control scheme has simple structure, which is of great interest for aerospace industry when onboard computing power is limited. Finally, simulation results for a CMG-based spacecraft are presented to show the effectiveness of the proposed attitude control systems.",

author = "Qiang Shen and Goh, \{Cher Hiang\} and Chengfei Yue and Baolin Wu",

note = "Publisher Copyright: {\textcopyright} 2017 IEEE.; 2017 IEEE Aerospace Conference, AERO 2017 ; Conference date: 04-03-2017 Through 11-03-2017",

year = "2017",

month = jun,

day = "7",

doi = "10.1109/AERO.2017.7943957",

language = "英语",

series = "IEEE Aerospace Conference Proceedings",

publisher = "IEEE Computer Society",

booktitle = "2017 IEEE Aerospace Conference",

address = "美国",

}

TY - GEN

T1 - Spacecraft reorientation control with attitude and velocity constrains

AU - Shen, Qiang

AU - Goh, Cher Hiang

AU - Yue, Chengfei

AU - Wu, Baolin

PY - 2017/6/7

Y1 - 2017/6/7

N2 - This paper investigates rest-to-rest attitude reorientation problem for a rigid spacecraft in the presence of attitude and angular velocity constraints. Based on a potential function, a nonlinear attitude controller is developed to avoid the un-desired celestial objects autonomously and limit the spacecraft rotation speed while achieving asymptotic attitude stabilization. To improve the agility of spacecraft, control moment gyro (CMG) is considered as torque-generating actuators for attitude control. General singular robust (GSR) steering logic is employed to determine the CMG gimbal rate commands. The proposed attitude control scheme has simple structure, which is of great interest for aerospace industry when onboard computing power is limited. Finally, simulation results for a CMG-based spacecraft are presented to show the effectiveness of the proposed attitude control systems.

AB - This paper investigates rest-to-rest attitude reorientation problem for a rigid spacecraft in the presence of attitude and angular velocity constraints. Based on a potential function, a nonlinear attitude controller is developed to avoid the un-desired celestial objects autonomously and limit the spacecraft rotation speed while achieving asymptotic attitude stabilization. To improve the agility of spacecraft, control moment gyro (CMG) is considered as torque-generating actuators for attitude control. General singular robust (GSR) steering logic is employed to determine the CMG gimbal rate commands. The proposed attitude control scheme has simple structure, which is of great interest for aerospace industry when onboard computing power is limited. Finally, simulation results for a CMG-based spacecraft are presented to show the effectiveness of the proposed attitude control systems.

UR - https://www.scopus.com/pages/publications/85021185857

U2 - 10.1109/AERO.2017.7943957

DO - 10.1109/AERO.2017.7943957

M3 - 会议稿件

AN - SCOPUS:85021185857

T3 - IEEE Aerospace Conference Proceedings

BT - 2017 IEEE Aerospace Conference

PB - IEEE Computer Society

T2 - 2017 IEEE Aerospace Conference, AERO 2017

Y2 - 4 March 2017 through 11 March 2017

ER -

Spacecraft reorientation control with attitude and velocity constrains

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