Design of Inter-satellite Separation of China’s First All-electric Communication Satellite

doi:10.12382/bgxb.2024.0880

Abstract

Abstract:

AP-6E satellite is the first domestic all-electric communication satellite,which is also the first communication satellite in the world to realize the autonomous orbit transfer from low earth orbit to geosynchronous orbit.The separable propulsion segment is utilized to realize the rapid orbit transfer via the chemical propulsion system,then the segment is separated and de-orbited,finally the remaining tasks of the satellite are preformed solely by the electric propulsion system.Therefore,the inter-satellite separation is the key to the success of this mission.The design of the connection and separation mechanism of AP-6E is introduced,and the stress margin of connection and the near-field and far-field safeties of separation process analyzed in order to systematically expound the experience of the engineering practice of the all-electric propulsion platform carried by the low-cost launch vehicle,which is of certain significance for the subsequent projects.

Key words: communication satellite, separation safety, combination, all-electric propulsion, chemical propulsion, inter-satellite separation

PAN Yuqian, FANG Yaopeng, WEI Qiang, WANG Min, SUN Guopeng, LIU Cuicui, LIANG Xingang. Design of Inter-satellite Separation of China’s First All-electric Communication Satellite[J]. Acta Armamentarii, 2024, 45(S2): 146-152.

Figures/Tables 9

References 17

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工程参数	偏差范围
卫星质量	±1%
独立推进舱质量	±5%
卫星X轴方向质心偏差/mm	[-5,5]
卫星Y轴方向质心偏差/mm	[-5,5]
卫星Z轴方向质心偏差/mm	[-5,5]
独立推进舱X轴方向质心偏差/mm	[-5,5]
独立推进舱Y轴方向质心偏差/mm	[-5,5]
独立推进舱Z轴方向质心偏差/mm	[-5,5]
卫星绕X轴转动惯量	±5%
卫星绕Y轴转动惯量	±5%
卫星绕Z轴转动惯量	±5%
独立推进舱绕X轴转动惯量	±5%
独立推进舱绕Y轴转动惯量	±5%
独立推进舱绕Z轴转动惯量	±5%
组合体分离前绕X轴初始角速度/((°)·s^-1)	[-0.01,0.01]
组合体分离前绕Y轴初始角速度/((°)·s^-1)	[-0.01,0.01]
组合体分离前绕Z轴初始角速度/((°)·s^-1)	[-0.01,0.01]
分离弹簧1初始分离力	±4%
分离弹簧2初始分离力	±4%
分离弹簧…初始分离力	±4%
分离弹簧X初始分离力	±4%

工程参数	偏差范围
卫星质量	±1%
独立推进舱质量	±5%
卫星X轴方向质心偏差/mm	[-5,5]
卫星Y轴方向质心偏差/mm	[-5,5]
卫星Z轴方向质心偏差/mm	[-5,5]
独立推进舱X轴方向质心偏差/mm	[-5,5]
独立推进舱Y轴方向质心偏差/mm	[-5,5]
独立推进舱Z轴方向质心偏差/mm	[-5,5]
卫星绕X轴转动惯量	±5%
卫星绕Y轴转动惯量	±5%
卫星绕Z轴转动惯量	±5%
独立推进舱绕X轴转动惯量	±5%
独立推进舱绕Y轴转动惯量	±5%
独立推进舱绕Z轴转动惯量	±5%
组合体分离前绕X轴初始角速度/((°)·s^-1)	[-0.01,0.01]
组合体分离前绕Y轴初始角速度/((°)·s^-1)	[-0.01,0.01]
组合体分离前绕Z轴初始角速度/((°)·s^-1)	[-0.01,0.01]
分离弹簧1初始分离力	±4%
分离弹簧2初始分离力	±4%
分离弹簧…初始分离力	±4%
分离弹簧X初始分离力	±4%

关键工程参数	偏差范围	敏感度
卫星X轴方向质心偏差/mm	[-5,5]	5.1%
卫星Y轴方向质心偏差/mm	[-5,5]	6.2%
独立推进舱X轴方向质心偏差/mm	[-5,5]	8.2%
独立推进舱Y轴方向质心偏差/mm	[-5,5]	15.3%
分离弹簧1分离力	±4%	14.4%
分离弹簧2分离力	±4%	17.6%
分离弹簧…分离力	±4%	14.4%
分离弹簧X分离力	±4%	17.6%

关键工程参数	偏差范围	敏感度
卫星X轴方向质心偏差/mm	[-5,5]	5.1%
卫星Y轴方向质心偏差/mm	[-5,5]	6.2%
独立推进舱X轴方向质心偏差/mm	[-5,5]	8.2%
独立推进舱Y轴方向质心偏差/mm	[-5,5]	15.3%
分离弹簧1分离力	±4%	14.4%
分离弹簧2分离力	±4%	17.6%
分离弹簧…分离力	±4%	14.4%
分离弹簧X分离力	±4%	17.6%