High performance silicon solar arrays employing advanced structuresSpecific design features to reduce cell mass, lower panel operating temperatures, and improve power to mass ratios for silicon solar cell arrays in space applications are presented. Because mass constraints limit payload capacity for launch into GEO, graphite/epoxy structures combined with high performance Si cells are needed to deliver a power/mass ratio of 265 W/kg, notably for Solar Electric Propulsion systems, compared with existing level of 65 W/kg. Shallow diffusion and back surface field cell technology have raised cell efficiencies to 15%, with a back emissivity of 1.64. Structural design requirements comprise Shuttle interface compatibility, full ground test capability, low mass, and high stiffness. Three array alternatives are discussed, and the STACBEAM configuration, which consists of a triangular truss and a piston deployer with folding accomplished on simple hinges, provides 0.2 Hz stiffness and achieves the design power/mass goals.
Document ID
19820028223
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Rockey, D. E. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)
Hedgepeth, J. M. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Adams, L. (Astro Research Corp. Carpinteria, CA, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1981
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: In: Intersociety Energy Conversion Engineering Conference