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CLC number: V448.22

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Received: 2008-06-06

Revision Accepted: 2009-02-25

Crosschecked: 2009-09-10

Cited: 6

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Journal of Zhejiang University SCIENCE A 2009 Vol.10 No.11 P.1617~1623

http://doi.org/10.1631/jzus.A0820425


Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils


Author(s):  Tao MENG, Hao WANG, Zhong-he JIN, Ke HAN

Affiliation(s):  Department of Information Science & Electronic Engineering, Zhejiang University, Hangzhou 310027, China

Corresponding email(s):   mengtao@zju.edu.cn

Key Words:  Pico-satellite, Attitude control, Magnetic coils, Momentum wheel


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.

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author="Tao MENG, Hao WANG, Zhong-he JIN, Ke HAN",
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T1 - Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils
A1 - Tao MENG
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PB - Zhejiang University Press & Springer
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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.

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

Reference

[1] Bushenkov, V.A., Ovchinnikov, M.Y., Smirnov, G.V., 2002. Attitude stabilization of a satellite by magnetic coils. Acta Astronautica, 50(12):721-728.

[2] Chang, Y.K., Lee, B.H., Kim, S.J., 2006. Momentum wheel start-up method for HAUSAT-2 ultra-small satellite. Aerospace Science and Technology, 10(2):168-174.

[3] Ergin, E.I., Wheeler, P.C., 1965. Magnetic attitude control of a spinning satellite. Journal Spacecraft and Rockets, 2(6):846-850.

[4] Guelman, M., Waller, R., Shiryaev, A., Psiaki, M., 2005. Design and testing of magnetic controllers for satellite stabilization. Acta Astronautica, 56(1-2):231-239.

[5] Jan, Y.W., Tsai, J.R., 2005. Active control for initial attitude acquisition using magnetic torquers. Acta Astronautica, 57(9):754-759.

[6] Schilling, K., 2006. Design of pico-satellites for education in systems engineering. IEEE Aerospace and Electronic System Magazine, 21(7):S9-S14.

[7] Silani, E., Lovera, M., 2005. Magnetic spacecraft attitude control: a survey and some new results. Control Engineering Practice, 13(3):357-371.

[8] Smirnov, G.V., 2001. Attitude determination and stabilisation of a spherically symmetric rigid body in a magnetic field. International Journal of Control, 74(4):341-347.

[9] Wang, P., Shtessel, Y.B., 1998. Satellite Attitude Control Using only Magnetorquers. American Control Conference, Philadelphia, PA, USA, p.222-226.

[10] Wisniewski, R., Blanke, M., 1999. Fully magnetic attitude control for spacecraft subject to gravity gradient. Automatica, 35(7):1201-1214.

[11] Yu, F.X., Meng, T., Han, K., Zhuang, R., Jin, Z.H., 2007. Design and error analysis of pico-satellite sun sensor. Acta Energiae Solaris Sinica, 28(12):1295-1299 (in Chinese).

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