Solar array technology for solar electric propulsion missions

Abstract

Development of 66 W/kg and 200 W/kg solar arrays for solar electric propulsion is discussed along with two basic concentrator solar array design concepts. Considerable testing was performed to demonstrate the availability and capability of the technology used for these arrays. To provide complete demonstration of 66 W/kg technology, a full-scale wing was built and tested and NASA decided to fly it as an experiment on one of the early Shuttle flights. Performance of the concentrator array system was demonstrated by model testing in a thermal-vacuum chamber.