SEP solar array technology developmentA technology development program is in progress to define a detail design of a lightweight 25 KW solar array for Solar Electric Propulsion (SEP) and to demonstrate technology readiness for fabrication, testing and flight of the large area solar array system. The requirements and baseline design for the 66 W/kg are discussed. The requirement for operation at 0.3 to 6.0 AU heliocentric distance presents a wide range of temperature environments as well as severe combined thermal/vacuum/UV radiation environments. The specific technology deficient areas are defined and the technology development program is presented. The program includes design and design evaluation testing on a component level followed by the fabrication and test of a developmental full-scale solar array wing. The results of the design studies and test program underway are presented. The test program covers the areas of fabrication testing, design support evaluation testing, zero-gravity array fold-up testing, full-scale array wing testing, and NDT development testing.
Document ID
19770029973
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Elms, R. V., Jr. (Lockheed Missiles and Space Co., Inc. Sunnyvale, Calif., United States)
Young, L. E. (NASA Marshall Space Flight Center Huntsville, Ala., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Conference on Intersociety Energy Conversion Engineering