CLC number: V448.22
On-line Access:
Received: 2008-06-06
Revision Accepted: 2009-02-25
Crosschecked: 2009-09-10
Cited: 6
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Tao MENG, Hao WANG, Zhong-he JIN, Ke HAN. Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils[J]. Journal of Zhejiang University Science A, 2009, 10(11): 1617-1623.
@article{title="Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils",
author="Tao MENG, Hao WANG, Zhong-he JIN, Ke HAN",
journal="Journal of Zhejiang University Science A",
volume="10",
number="11",
pages="1617-1623",
year="2009",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A0820425"
}
%0 Journal Article
%T Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils
%A Tao MENG
%A Hao WANG
%A Zhong-he JIN
%A Ke HAN
%J Journal of Zhejiang University SCIENCE A
%V 10
%N 11
%P 1617-1623
%@ 1673-565X
%D 2009
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A0820425
TY - JOUR
T1 - Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils
A1 - Tao MENG
A1 - Hao WANG
A1 - Zhong-he JIN
A1 - Ke HAN
J0 - Journal of Zhejiang University Science A
VL - 10
IS - 11
SP - 1617
EP - 1623
%@ 1673-565X
Y1 - 2009
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A0820425
Abstract: The three-axis active attitude control method with a momentum wheel and magnetic coils for a pico-satellite is considered. The designed satellite is a 2.5 kg class satellite stabilized to nadir pointing. The momentum wheel performs a pitch-axis momentum bias, nominally spinning at a particular rate. Three magnetic coils are mounted perpendicularly along the body axis for precise attitude control through the switch control mechanism. momentum wheel start up control, damping control and attitude acquisition control are considered. Simulation results show that the proposed combined control laws for the pico-satellite is reliable and has an appropriate accuracy under different separation conditions. The proposed strategy to start up the wheel after separation from the launch vehicle shows that its pitch momentum wheel can start up successfully to its nominal speed from rest, and the attitude convergence can be completed within several orbits, depending on separation conditions.
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