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6.

immune to radiation damage function as the electric utility for a series of Shuttle experiments with high power demands but it could also function as a fuel production depot. However, all of these concepts depend upon the success of the new absorber if the expense, weight and radiation degradation problems of solar cells are to be avoided.

References

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Space Power Systems, Part I, AGAR Dograph 123, p. 39,
November 1969.

Preprototype Solar Collector, 15 KW Solar Mechanical
Power Generation; Quarterly Progress Report, Feb. 1964 ·
May 1964, Goodyear Aerospace Corporation.

Feasibility of Large-Scale Orbital Solar/Thermal Power
Generation, Path, J. T., and Woodcock, G. R., The Boeing
Company, Paper #739085, pp. 312-319, IECEC 1973.

THE JOHNS HOPKINS UNIVERSITY

APPLIED PHYSICS LABORATORY

LAUREL MARYLAND

APPENDIX A

All of the figures in Appendix A are taken from Section 4 of "Interim Summary Report Investigation of a 15 KW Solar Dynamic Power System for Space Application," which is available in its entirety from The Defense Documentation Control Center under AD 432202. These figures reflect the previously developed state-of-the-art in "Space Deployable" solar concentrating mirrors. They are arranged in their original order. Note that the reradiation versus absorber size dilemma is specifically recognized in the original text under Figure IV.2-20. Note also that some of the figures are of poor quality in the original microfilm from which they have been reproduced. They are reproduced for the reader's convenience due to the current unavailability of hard copies.

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