Spacecraft charging for microsatellite KITSAT-3
Spacecraft charging for microsatellite KITSAT-3
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为微型卫星 KITSAT-3 航天器充电
DOI：
10.2514/2.7052
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发表时间：
2003
影响因子：
1.6
通讯作者：
S. Park
中科院分区：
文献类型：
--
作者：
H. Kim;J. Lee;J. Rhee;E. S. Lee;K. Min;D. Sung;J. Seon;Y. Jung;S. Park
用电子温度探针测量了KITSAT-3微型卫星的浮动电位。该卫星的轨道高度为730公里，与太阳同步，固定当地时间的下降交点接近当地时间1200小时。卫星的尺寸约为495 × 614 × 852毫米3。卫星的重量为112公斤。在昼侧，执行一系列姿态机动以旋转卫星。发现太阳能电池阵列产生的电流与浮置电位之间存在显著的相关性，当太阳能电池阵列朝向太阳时，初始浮置电位基本为负（<−10 V），当航天器旋转使太阳能电池阵列接近垂直于太阳时，初始浮置电位增加到100 V − 3 V。利用NASCAP/LEO软件进行了数值模拟，验证了电势变化的结果。目前的调查发现，微型卫星KITSAT-3的浮动电位是由卫星由于太阳能电池阵列的存在而负电荷决定的。标称AC =卫星主体的导电面积，m 2 AS =卫星的表面积，m 2 AW =互连件的导电面积，m 2 B =磁场，nT e =电子电荷，1.60 × 10 −19 C I =电流，A ISC =由卫星轨道运动在撞击方向收集的电流，A ITH =由于卫星电势收集的电流，Ak =玻尔兹曼常数q=电荷，CVp =卫星电势，VVpp =峰间电压，VVsc =卫星轨道速度，m/s α =轨道速度与导电表面法向矢量之间的夹角，-=太阳能电池之间的电势差，V θ =卫星方位相对于轨道速度的角度，度
Floating potentials for a microsatellite KITSAT-3 are measured with an electron temperature probe. The orbit of the satellite is 730-km altitude, sun-synchronous, with a fixed local time of descending node near 1200 hrs local time. The dimension of the satellite in stowed configuration is approximately 495 × × 614 × 852 mm 3 . The weight of the satellite is 112 kg. In the dayside, a series of attitude maneuvering is performed to rotate the satellite. Significant correlation between the currents generated from the solar arrays and the floating potentials is found. The initial floating potentials that are largely negative (<−10 V) when the solar arrays are directed toward the sun are found to increase up to ∼ ∼− 3V as the rotation of the spacecraft brings the solar arrays nearly perpendicular to the sunlight. The result of the potential variation is verified by a numerical simulation with NASCAP/LEO. The present investigation finds that the floating potentials for a microsatellite KITSAT-3 are determined by the negative charging of the satellite due to the presence of solar arrays. Nomenclature AC = conductive area of the satellite body, m 2 AS = surface area of the satellite, m 2 AW = conductive area of interconnectors, m 2 B = magnetic field, nT e = electron charge, 1.60 × 10 −19 C I = current, A ISC = current collected in the ram direction by the orbital motion of the satellite, A ITH = current collected due to the satellite potential, A k = Boltzmann constant q= charge, C Vp = satellite potential, V Vpp = peak-to-peak voltage, V Vsc = orbital speed of satellite, m/s α = angle between the orbital velocity and the normal vector of the conductive surface �� = potential difference between the solar cells, V θ = angle of satellite orientation relative to the orbital velocity, deg