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

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. 作者： Author： Tao MENG  Hao WANG  Zhong-he JIN  Ke HAN 作者單位： Department of Information Science & Electronic Engineering, Zhejiang University, Hangzhou 310027, China 期 刊： 浙大學(xué)報(bào)（英文版）（A輯：應(yīng)用物理和工程）   ISTICEISCI Journal： JOURNAL OF ZHEJIANG UNIVERSITY SCIENCE A 年，卷(期)： 2009, 10(11) 分類(lèi)號(hào)： V448.22 Keywords： Pico-satellite    Attitude control    Magnetic coils    Momentum wheel    機(jī)標(biāo)分類(lèi)號(hào)： V44 V24 機(jī)標(biāo)關(guān)鍵詞： attitude control    magnetic coils    start up    Simulation results    launch vehicle    control method    axis    acquisition    Three    different    strategy    active    class    rest 基金項(xiàng)目： the Program for New Century Excellent Talents in University，the Postdoctoral Science Foundation of China

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