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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 作者单位: Department of Information Science & Electronic Engineering, Zhejiang University, Hangzhou 310027, China 期 刊: 浙大学报(英文版)(A辑:应用物理和工程) ISTICEISCI Journal: JOURNAL OF ZHEJIANG UNIVERSITY SCIENCE A 年,卷(期): 2009, 10(11) 分类号: V448.22 Keywords: Pico-satellite Attitude control Magnetic coils Momentum wheel 机标分类号: V44 V24 机标关键词: attitude control magnetic coils start up Simulation results launch vehicle control method axis acquisition Three different strategy active class rest 基金项目: the Program for New Century Excellent Talents in University,the Postdoctoral Science Foundation of China【Attitude stabilization of a pico-sat】相关文章:
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