倾斜轨道小卫星太阳高度角分析与机动方案设计

doi:10.3969/j.issn.1674-1579.2016.03.006

Abstract

Abstract: Abstract：Considering the optic attitude sensor of inclinedorbit small satellite interfered by sunlight, the variation law of solar height angle is analyzed. For computing and analyzing easily, a handy experience formula of solar height angle is proposed. Based on the formula, a yawaxis attitude maneuver scheme is presented, which can avoid sunlight interferer and make thermal control design and solar array drive law design conveniently.

Key words: Keywords：inclinedorbit, solar height angle, attitude maneuver

CLC Number:

V448

FENG Bao-Min, CHEN Zhan-Sheng, YE Li-Jun, JI Cheng-Sheng, ZHU Hong. Solar Height Angle Analysis and Attitude Maneuver Design of InclinedOrbit Small Satellite[J]., 2016, 42(3): 33-37.

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URL: http://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/10.3969/j.issn.1674-1579.2016.03.006

http://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/Y2016/V42/I3/33

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Solar Height Angle Analysis and Attitude Maneuver Design of InclinedOrbit Small Satellite

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