载人航天器体装太阳电池阵有效发电面积计算方法

航天器的发电能力与太阳电池阵有效发电面积成正比。针对圆柱形载人航天器，提出了一种体装太阳电池阵有效发电面积计算方法。首先，将太阳电池阵沿圆周方向划分为多个子阵，通过坐标变换，计算太阳矢量与每个子阵法线的夹角（即太阳入射角）；然后，将每个子阵面积与对应太阳入射角的余弦相乘并求和，得到体装太阳电池阵的有效发电面积。对不同轨道日照角、不同飞行姿态下体装太阳电池阵有效发电面积进行仿真分析，仿真结果表明:三轴对地姿态下平均有效发电面积为安装面积的25%~32%，通过固定角度偏航可将有效发电面积提高至安装面积的30%~44%。 

A calculation method for effective power supply area of manned spacecraft with body mou nted solar array

The power supply capability is proportional to the effective area of spacecraft solar array. For cylindrical manned spacecraft, a calculation method for effective area of body mounted solar array is proposed. First, the mounted solar array was divided into n parts along the circumference. The angle between the sun vector and the normal of each part (incidence angle) was calculated by coordinate transform. Then, the effective area of body mounted solar array was obtained by summing up the products of the area of each part and the cosine of incidence angle. Finally, the proposed method was verified by effective area simulation under different orbit sunlight angles and different flight attitudes for manned spacecraft with body mounted solar array. The simulation results show that the average effective area can reach 25%-32% of the mounted area under earth-oriented three-axis stabilized attitude the flight attitude of orientating the earth. By yawing the manned spacecraft with fixed angle, the ratio of effective area to mounted area can be expanded to 30%-44%.