Objectives of the solar array orbital flight test were to demonstrate the readiness of large-area, lightweight photovoltaic technology, to demonstrate the deployment, retraction, and restowage of the array; and to study dynamic behaviour of large, flexible space structure. In parallel with the various hardware development activities there was, of course, extensive effort expended in supporting analytical tools—chiefly deployed dynamics and thermal models. These models were also validated by the SAFE experiment, resulting in an established set of flight test-validated design tools for structures of this type, such as space station. Flight data correlated extremely well with the outputs of both models (Fig. 7). In addition to providing technical data, the SAFE also served as a demonstration which provided confidence to other Lockheed programs to employ these types of systems, and indeed two programs are now in production. These programs continue to provide further technology input to the Space Station Freedom Program. In addition, the Industrial Space Facility, a commercial space lab venture, adopted this design as their baseline and funded design efforts, atomic oxygen testing of cell assemblies, and an important flat-pack bypass diode development. Also, as the problem of Kapton erosion by atomic oxygen became apparent from JSC shuttle flight data, Lewis Research Center began working on an SiO2 coating method to combat the problem. This led to the Photovoltaic Array Environmental Protection (PAEP) program which is directed at evaluating various coatings for use on
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