Continued increases in spacecraft power requirements and launch vehicle payload capability have rapidly reached the point where body-mounted or single flat panel solar arrays are unable to provide the required power output and still be retained within the physical confines of a spacecraft launch configuration. Therefore, some form of extendible solar array is necessary to meet the many constraints of the spacecraft designer. A 2 year research and development program was conducted to acquire the technology to design and fabricate flexible deployable solar cell arrays that advance the power-to-weight ratio of present arrays. Large area Flexible Integrated Solar Cell Arrays (FISCA) are capable of compact stowage and positive deployment and retraction. This report presents the FISCA development program including the subsystem design and mechanical system test certification to the Atlas/Centaur and Titan III-C launch environment. (Author)
Flexible Integrated Solar Cell Array
1967
160 pages
Report
Keine Angabe
Englisch
Electric Power Production , Spacecraft components , Solar cells , Solar panels , Flexible structures , Launching , Packaging , Test methods , Aerodynamics , Vibration , Stresses , Halocarbon plastics , Glass textiles , Gravity , Deflection , Configuration , Manufacturing methods , FISCA(Flexible integrated solar cell arrays) , Titan 3 , Centaur , Atlas
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