Researching | Research on Attitude Maneuver Control of Thin-film Spacecraft Based on Nonlinear Variable Structure Sliding Mode Controller

AEROSPACE SHANGHAI, Volume. 41, Issue 6, 95(2024)

Research on Attitude Maneuver Control of Thin-film Spacecraft Based on Nonlinear Variable Structure Sliding Mode Controller

Yizhen YIN*... Guohua KANG, Junfeng WU, Jiaqi WU and Jindong YUAN |Show fewer author(s)

Author Affiliations

College of Astronautics，Nanjing University of Aeronautics and Astronautics，Nanjing211101，，China

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Figures&Tables (21)

References (10)

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Figures & Tables(21)

Fig. 1. Slider-sail mechanism of square thin-film sapcecraft

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Fig. 2. Working principle diagram of small sail

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Fig. 3. Fly wheel system of thin-film spacecraft

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Fig. 4. Diagram of atmospheric disturbance moment

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Fig. 5. Diagram of the attitude control system of thin-film spacecraft

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Fig. 6. Attitude response of thin-film spacecraft

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Fig. 7. Control torque $u$ outputed by the controller

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Fig. 8. Rotate speed of the flywheel system

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Fig. 9. Motion of the slider-sail mechanism

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Fig. 10. Change in the moment of inertia of thin-film spacecraft

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Fig. 11. Design of the on-ground attitude adjustment experiment system for thin-film spacecraft

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Fig. 12. Simulative module of thin-film spacecraft

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Fig. 13. Air-bearing platform

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Fig. 14. Experimental scene layout

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Fig. 15. Flow chart for the attitude maneuver experiment of thin-film spacecraft

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Fig. 16. Attitude information of the thin-film spacecraft

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Fig. 17. Rotate speed of the actuator flywheel

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Fig. 18. Steady-state error of the attitude maneuver experiment

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Table 1. Tab.1Parameters involved in the simulation process

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Table 1. Tab.1Parameters involved in the simulation process

参数类型	数值
转动惯量矩阵 $I_{0} / (k g \cdot m^{2})$	diag(62.5,31.25,31.25)
薄膜面积 $A / m^{2}$	100
航天器总质量 $M / k g$	10
固有压心质心偏距 $l_{0} / m$	[0,0.2,0.2]
单个滑块质量 $m / k g$	1
单个滑块滑动的幅值 $\|x_{m a x}\| / m$	6
单个滑块滑动速度的幅值 $\|{\dot{x}}_{m a x}\| / (m \cdot s^{- 1})$	0.1
单个小帆的面积A_s/m²	3
单个小帆转角的幅值 $\|λ_{m a x}\| / (°)$	30
单个小帆转动角速度的幅值 $\|{\dot{λ}}_{m a x}\| / [(°) \cdot s^{- 1}]$	1
小帆连接杆的长度 $l / m$	5
单个飞轮的主转动惯量 $J / (k g \cdot m^{2})$	0.006 061
单个飞轮的最大输出力矩 $/ (N \cdot m)$	0.09
单个飞轮的初始转速 $/ [r \cdot m i n^{- 1}]$	3 000
薄膜所受气动力的平均值 $\bar{f} / N$	0.006 9

Table 2. Tab.2Parameters of the simulative module of thin-film spacecraft
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Table 2. Tab.2Parameters of the simulative module of thin-film spacecraft
参数名称数值
总质量/ $k g$ 40
总转动惯量/（ $k g \cdot m^{2}$ ） 1.2
总有效面积/ $m^{2}$ 1
飞轮主惯量/（ $k g \cdot m^{2}$ ） 0.006

Table 3. Tab.3Parameters in the attitude maneuver experiment
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Table 3. Tab.3Parameters in the attitude maneuver experiment
参数类型数值
总质量/ $k g$ 40
总转动惯量/ $(k g \cdot m^{2})$ 1.2
总有效面积/ $m^{2}$ 1
风扇风速/ $(m \cdot s^{- 1})$ 0.3~1.0
目标姿态角/(°) 10
控制器参数 $a$ 0.075
控制器参数 $b$ 0.09
控制器参数 $c$ 0.01

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Yizhen YIN, Guohua KANG, Junfeng WU, Jiaqi WU, Jindong YUAN. Research on Attitude Maneuver Control of Thin-film Spacecraft Based on Nonlinear Variable Structure Sliding Mode Controller[J]. AEROSPACE SHANGHAI, 2024, 41(6): 95

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Paper Information

Category: Innovation and Exploration

Received: Feb. 1, 2024

Accepted: --

Published Online: Mar. 7, 2025

The Author Email:

DOI:10.19328/j.cnki.2096-8655.2024.06.012

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