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Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering)  2009, Vol. 10 Issue (11): 1617-1623    DOI: 10.1631/jzus.A0820425
Aerospace Science and Technology     
Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils
Tao MENG, Hao WANG, Zhong-he JIN, Ke HAN
Department of Information Science & Electronic Engineering, Zhejiang University, Hangzhou 310027, China
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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.

Key wordsPico-satellite      Attitude control      Magnetic coils      Momentum wheel     
Received: 06 June 2008     
CLC:  V448.22  
Cite this article:

Tao MENG, Hao WANG, Zhong-he JIN, Ke HAN. Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 2009, 10(11): 1617-1623.

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http://www.zjujournals.com/xueshu/zjus-a/10.1631/jzus.A0820425     OR     http://www.zjujournals.com/xueshu/zjus-a/Y2009/V10/I11/1617

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