REFERENCES & FOOTNOTES FOR PART I (1) Various concepts are described in the previous Eurospace Powersat Final Study Report. December 1990. Others are discussed in the Proceedings from the SPS *91 Power from Space. Second International Symposium. Paris/Gif-Sur- Yvette. 27 to 30. August 1991. (2) Nagatomo. M.. et al.. “Engineering Aspects of The Microwave Ionosphere Nonlinear Interaction Experiment (MINIX) With a Sounding Rocket." Acta Astronautica, Vol. 13. No. 1, 1986, p.23. (3) In the mid-1970s NASA proposed development of a “25 kW Power System" that the Shuttle would dock to in order to provide power for 30 missions. This program was not funded, however. Instead, NASA decided in the late 1980s to develop a small cryo-pack that would insert in the payload bay. This pack would supply sufficient additional liquid hydrogen and liquid oxygen for the fuel cells and thereby enable 14-day Shuttle missions. (4) Little. F.. Kennedy, M.. “ Commercialization of Strategies for Space Power Technology." IAF-90-617 41st International Astronautical Congress, Dresden. Germany. October 1990, p. 12. (5) Data supplied by Mark Saunders (via fax) of the Space Station Freedom Project Office in Reston. Virginia. (6) Freedom is not re-fuelled as such, but the spent propellant modules are replaced by fully-loaded modules. (7) Ibid. (8) Eurospace Powersat Final Study Report, p. 87. (9) A description of the RIT ion thruster, for example, can be found in ESA ESTEC Publication F-26. 1991. (10) An overview of the options for SDG systems was presented by Ansaldo in Appendix D to the Eurospace Powersat Final Study Report. (11) Eshuis. D., "Survey of Solar-Dynamic Space Power - The Stirling Option." ESA Journal. Vol. 10. 4/1986, p. 361. (12) Carre. F.. Proust. E.. Keirle. P.. “CNES CEA Comparative Evaluation
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