CAJ | 학술논문

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。
항천기태양익적수출공솔수도광조조건적영향,여태양광입사각θ（지태양광여태양익법선적협각,이하간칭θ）밀절상관（θ각취치0°～60°범위지간,수출공솔여θ적여현성정비）。위차건립료고정도적궤도수치계산모형、태양위치계산모형、광조지영모형화불동자태모식（항천기적비행모식화태양익정향모식적다충조합모식）하적태양광입사각계산모형。근거궤도화자태조건,추산항천기재궤운행과정중태양익적태양광입사각,분석태양광입사각수시간적변화。방진결과가용우계산태양익적발전공솔,병위항천기화태양익적자태공제제공삼고。
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.