The invention provides an overall optimization design method based on inclined orbit satellite illumination conditions, which comprises the following steps: a calculation step: obtaining a solar vector by on-board orbit parameter recursion or sun sensor measurement, calculating to obtain a solar altitude angle, and representing the energy supply change and heat dissipation surface change of the whole satellite by taking the solar altitude angle as a parameter; determining a flight scheme, wherein a satellite U-turn flight scheme considering whole satellite energy and fixed heat dissipation surface design is adopted; determining satellite flight polarity: determining the satellite flight polarity according to the sun vector change direction; an applicability determination step: adaptabilityof a shadow area judgment method and a shadow area turning-around flight scheme; and a basis selection step: selecting a basis for the turn-around flight time. Starting from the perspective of overall optimization design of the whole satellite, thermal control design of the whole satellite is facilitated; enough illumination time is ensured, so that the energy of the whole satellite is balanced;and the constraint of sensor and load layout design is also solved by the fixed illumination surface.
本发明提供了一种基于倾斜轨道卫星光照条件的总体优化设计方法,包括:计算步骤:由星上轨道参数递推或太阳敏感器测量得到太阳矢量,计算得到太阳高度角,以太阳高度角为参数表征整星能源供应变化和散热面变化;确定飞行方案步骤:兼顾整星能源和固定散热面设计的卫星掉头飞行方案;确定卫星飞行极性步骤:根据太阳矢量变化方向确定卫星飞行极性;确定适用性步骤:阴影区判断方法及阴影区掉头飞行方案的适应性;依据选择步骤:掉头飞行时间选择依据。本发明从整星总体优化设计角度出发,有利于整星热控设计;保证了足够光照时间,使整星能源得到平衡;固定光照面也解决了敏感器及载荷布局设计的约束。
Overall optimization design method based on inclined orbit satellite illumination conditions
基于倾斜轨道卫星光照条件的总体优化设计方法
2020-06-05
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
Europäisches Patentamt | 2022
|Europäisches Patentamt | 2023
|