摘要
航天器太阳翼的输出功率受到光照条件的影响,与太阳光入射角θ(指太阳光与太阳翼法线的夹角,以下简称θ)密切相关(θ角取值0°～60°范围之间,输出功率与θ的余弦成正比)。为此建立了高精度的轨道数值计算模型、太阳位置计算模型、光照地影模型和不同姿态模式(航天器的飞行模式和太阳翼定向模式的多种组合模式)下的太阳光入射角计算模型。根据轨道和姿态条件,推算航天器在轨运行过程中太阳翼的太阳光入射角,分析太阳光入射角随时间的变化。仿真结果可用于计算太阳翼的发电功率,并为航天器和太阳翼的姿态控制提供参考。
The electrical output of solar wing is affected by the illuminated condition.It is closely related to the sunlight incidence angle θ and can be a direct ratio to the cosine of the incidence angle of sunlight when it is between 0 and 60 degrees. Orbit calculation model,solar position computation model, earth eclipse model and sunlight incidence angle computation model for various attitudes（different combinations of spacecraft flying mode and solar wing orientating pattern） are built at first.With the different orbit and attitude of the spacecraft,the incidence angle of sunlight is computed.Finally,the changing rate of the incidence angle of sunlight is simulated,and the result can be used to compute the electric output of the solar wing and can offer reference to the attitude control.
出处
《航天器工程》
2012年第1期37-42,共6页
Spacecraft Engineering
基金
国家高技术研究发展计划(863计划)课题<新一代导航卫星自主定轨和管理技术研究>
2007AA12Z308
关键词
太阳翼
地影
飞行模式
定向模式
太阳光入射角
solar wing
earth eclipse
flying mode
orientating pattern
sunlight incidence angle
