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本文概述轻重量太阳电池阵系统的技术发展现状,并预估未来技术的发展趋势。空间站和早期的空间发电试验将继续沿用自动伸展的太阳电池系统。这些系统可作为独立的装置或星载系统发射到太空。需要面积大于4650平方米的太阳电池阵,这就得采用一种首次在轨道上组装的大型平面空间结构。因此,首先应当制造许多成套的太阳电池阵的电模件,经地面试验后,再送到轨道飞行的基板结构上,在那里铺设装配。为此,就要求研制支承大型太阳电池阵的空间结构,包括通常应用的石墨纤维一环氧树脂复合材料。此外,在太阳聚能的太阳电池装置的某些地方,以及近太阳轨道飞行的卫星,其温度范围有可能超过93℃(200℉),所以,聚酰亚胺树脂可作为这种要求的结构材料来使用。预计到1981年,可能应用比功率达到120—170瓦/公斤的自动伸展太阳电池阵系统,而比功率为170—240瓦/公斤的太阳电池阵系统,预计到1985年就可投入使用。如果这项研究在经济性方面确实是合算的,那么功率达5000—10,000兆瓦的大型组装式平面太阳电池阵到九十年代将可投入实际使用。
This article outlines the state of the art of light-weight solar array systems and forecasts future technology trends. Space stations and early space power generation tests will continue to use automatic stretching solar system. These systems can be launched into space as stand-alone devices or as spaceborne systems. Requires a solar cell area of more than 4,650 square meters, which necessitates the first large-scale planar space structure to be assembled on orbit. Therefore, first of all, many sets of solar modules should be made of electric modules, after the ground test, and then sent to the orbital flight of the substrate structure, where the laying of the assembly. To this end, it requires the development of space structure supporting large solar arrays, including the commonly used graphite fiber-epoxy composite material. In addition, polyimide resin can be used as a required structure in some parts of a solar concentrating solar cell device, and satellites flying near a solar orbit, which may have a temperature range exceeding 93 ° C (200 ° F) Material to use. It is estimated that by 1981 it is possible to use an auto-stretch solar array system with a specific power of 120-170 watts per kilogram, while a solar array system with a power of 170-240 watts per kilogram is expected to be operational by 1985. If this research is indeed economically viable, then large, assembled, planar solar arrays of 5,000-10,000 megawatts can be put into practical use by the nineties.