Retractable advanced rigid array (for solar space power)

Author

De Kam, J.

Author_Institution

Fokker Space & Syst., Amsterdam, Netherlands

fYear

1988

fDate

1988

Firstpage

860

Abstract

The design and development of a retractable, retrievable, and reusable advanced rigid array solar cell array is presented. The first application will be for EURECA in a 5 kW version. The array is designed for ten years in low earth orbit (LEO) and five shuttle launch-landing cycles. The design of new mechanisms to incorporate the retraction and relatching requirements is presented. The setup of a monitoring and electronic control system for the functional requirements is shown. A selection of materials and processes suitable for LEO missions regarding atomic oxygen erosion and thermal cycling is also shown. Rigorous fracture control measures to satisfy the reusability requirements, in view of shuttle safety regulations, are presented.

Keywords

design engineering; solar cell arrays; space vehicle power plants; 5 kW; control system; design; erosion; low earth orbit; safety; shuttle; solar cell array; space power; thermal cycling; Atomic measurements; Control systems; Costs; Economic indicators; Extraterrestrial measurements; Low earth orbit satellites; Monitoring; Observatories; Photovoltaic cells; Power generation economics; Qualifications; Safety; Space shuttles; Space stations; Space technology;

fLanguage

English

Publisher

ieee

Conference_Titel

Photovoltaic Specialists Conference, 1988., Conference Record of the Twentieth IEEE

Conference_Location

Las Vegas, NV, USA

Type

conf

DOI

10.1109/PVSC.1988.105826

Filename

105826