The EOS-AM spacecraft is the first in a series of NASA remote Earth sensing spacecraft due for launch in 1998. The spacecraft requires a single solar array wing with an End of Life (5 years) power requirement of 5 kW. This paper discusses the technical issues which concluded that a flexible blanket with 5.5 mil thick GaAs/Ge solar cells was the optimum design at both array and spacecraft level. A relative cost study showed that there was only marginal cost impact in using GaAs/Ge cells as against Silicon cells on a flexible array. An overview of the proposed design (based on the TRW APSA design) is also given.
The EOS-AM solar array - a flexible GaAs/Ge array
Die EOS-AM-Solaranordnung - Eine flexible GaAs/Ge-Anordnung
IEEE Photovoltaic Specialists Conference, 23 ; 1375-1380
1993
6 Seiten, 6 Bilder, 4 Tabellen, 4 Quellen
Conference paper
English
British Library Conference Proceedings | 1993
|The Clementine GaAs/Ge Solar Array
British Library Conference Proceedings | 1994
|Rigid lightweight GaAs solar array design
Tema Archive | 1985
|The Clementine GaAs/Ge solar array
AIAA | 1994
|