类天宫航天器迎风面积建模及变化特性分析

Modeling of Cross Section Area for Tiangong-type Spacecraft and Analysis of its Variation Characteristics during Orbit Flight

针对类天宫航天器复杂结构外形迎风面积的精确计算问题,提出了一种在轨飞行期间迎风面积的计算模型。该模型考虑航天器姿态变化和帆板转动因素,在航天器本体系下建立经纬度网格,将三维的投影方向矢量转化为二维的经度、纬度;基于图形学几何投影方法,对投影经度、投影纬度、帆板转角模型参数按照一定颗粒度离线穷举,计算各种参数状态的迎风面积,离线建立航天器迎风面积模型;轨道计算过程中,根据航天器在轨飞行模式确定该时刻的姿态和帆板转动角度,通过迎风面积模型插值获得迎风面积。应用该方法计算天宫一号长期在轨飞行阶段的迎风面积,对不同时间尺度的变化规律进行了分析,验证了方法的有效性。

A calculation model for the cross section area of Tiangong-type spacecraft with complex geometric shape during orbit flight was proposed.The attitude changes and the solar array rotations were taken into account in this model.The three-dimensional projecting direction was translated into a two-dimensional vector as longitude and latitude in the body fixed coordination system of spacecraft.Based on the geometric projection method of computer graphics,the cross section areas of various parameter states by a certain step were exhaustively calculated offline,according to the three parameters including the projected longitude,projected latitude and solar arrays rotation angle.When the cross section area was needed during the orbit determination procession,the three parameters at this moment were determined according to the spacecraft′s orbital flight mode,and the area was obtained through interpolation.The method was applied to Tiangong-1 spacecraft in the long-term orbit flight phase,and the variation characteristics of different time scales were analyzed to verify the effectiveness of this method.