一种航天器有效迎风面积的求解方法

An algorithm for solving the effective front face area of spacecraft

有效迎风面积在复杂外形航天器姿态变化过程中很难精确得到,成为影响大气阻力建模精度的关键因素之一。基于微元划分思想提出分块建模方法建立航天器网格模型,并将Graham’s Scan法和射击线扫描法有效结合以求解有效迎风面积。该方法可避免航天器姿态变化时各部分之间的遮挡及太阳能帆板旋转引起的迎风面积重叠计算,实现有效迎风面积的准确求解。通过计算值与参考值的比较,表明该方法具有较好的精度,可为航天器精细模型的建立提供参考。

The front face area is very important to the accuracy of atmospheric drag model, but it is verydifficult to accurately estimate the front face area of a complex outline spacecraft during its attitude chan-ging. In this paper, we try to solve this problem and propose a new method to calculate the front face area.First, based on infinitesimal theory, we put forward part-modeling method to build spacecraft grid model.And then we combine Graham＇ s Scan method with shot-line-scanning method to solve the front face area.The advantage of this method is that we can effectively avoid the overlap of front face caused by spacecraftself-shadow and the sail＇ s rotation, so the solution is more accuracy. Comparing the computed value withthe theory value, we proved above conclusion.