DocumentCode
3576033
Title
Attitude controller designed based on pole assignment theory for combined spacecraft
Author
Yan Qin ; Feng Wang ; Xibin Cao
Author_Institution
Res. Center of Satellite Technol., Harbin Inst. of Technol., Harbin, China
fYear
2014
Firstpage
1447
Lastpage
1451
Abstract
This paper investigates the attitude control problem of on-orbit servicing spacecraft which changes moment of inertia after the rendezvous and docking task. Considering in the small-angle circumstance and manipulating attitude dynamics model with linearization method, the attitude controller based on pole assignment is obtained. Finally, a numerical example is provided to illustrate the effectiveness of the proposed approach.
Keywords
attitude control; control system synthesis; linearisation techniques; matrix algebra; pole assignment; position control; space vehicles; stability; attitude control problem; attitude controller design; attitude dynamics model; combined spacecraft; docking task; linearization method; moment of inertia; on-orbit servicing spacecraft; pole assignment theory; rendezvous task; small-angle circumstance; stability; Aerodynamics; Angular velocity; Attitude control; Mathematical model; Quaternions; Space vehicles; Torque; attitude controller; combined spacecraft; on-orbit servicing; pole assignment;
fLanguage
English
Publisher
ieee
Conference_Titel
Mechatronics and Control (ICMC), 2014 International Conference on
Print_ISBN
978-1-4799-2537-7
Type
conf
DOI
10.1109/ICMC.2014.7231794
Filename
7231794
Link To Document