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Furthermoreth,e waterpropellangtreatly simplifiesgroundloadingand servicing requiremenatsndeliminatesmanyof the handlincgompatibilictyoncernosf toxicearth storablperopellantTsh.erealattractiveneosfs electrolyspisropulsiomnightbetheabilityto serveintheduarloleofpropulsioandpower generatioTnh.etankagien thisunitizedsystem canalsoprovidesomei,f notmostof the structurerequiredby spacecratfhtat must functioansastiffinstrumepnlattformA.unitized electrolysis/fucell unit wouldprovidehigh performancperopellantfsor propulsionand generapteowerT.hismighbteacriticaflunction fordeeplanetamryissionws,heresolaprower willbecommeorescarcaesthemissiopnroceeds andwhereloadlevelingcanbe animportant asset. References Thestateof the of a flight-type 4Newman, control D. system," electrolysis propulsion series of generation subsequent demonstrated Hydrogen electrolysis cycles Symposium, Agency Publ. 5Stechman, Electrolysis Marquardt TR-72-132, November 125220 and 7McElroy, cell storage applications," Rept. BD94-02, system breadboard were Liquid by means hot-fire on and process were tests was system. produced stored inside small, AFRPL- A.H., oxygen during the the components discussed and a system was assembled. A with alternate propellant of water electrolysis and "Water 7 th Chemical Propulsion 72, ppl05-114, Oct. technology for thruster this breadboard "Water System," The high pressure tanks. The thruster used was ahigh temperature, oxidation resistant, rhenium- attached to a workhorse 6Mitlitsky, "Lightweight F., Myers, B., and iridium, injector section. 1 N chamber, by means of unitized Oxygen between 7.5 and 9.5, with highest C* efficiency at the lowest proof-of-concept and optimized for C* efficiency of design will performance bipropellents. to hydrogen mixture ratios varied than those of state concept. propulsion worked tests and 16-19, Judd, 1996, D.C., Logan, UT "Long Life a water-cooled adapter mixture ratio as expected. The test bed that was not designed performance had a maximum 79%. generate Optimization significantly of of thruster better the art SMitlitsky, F., de Groot, W.A., Butler, L., and McElroy, J.F., "Integrated Modular Propulsion The tests fundamental and power electrolysis the system functional featuring a water vapor feed URFC is needed to Regenerative (IMPRESS)for AIAA/USU September Electro-Energy Small Satellites," Conference on Storage 10th Small described feasibility in this paper of the unitized URFC cycle showed the propulsion demonstrate the great advancements that can made using this technology. be NASA TM-113157 10 tests demonstrated as anticipated. that A fully system 9Fanciullo, Reaction Aerospace 0964, Irvine, T.J., Control Design CA, and unitized propulsion and power System Design," AIAA Paper 92- 1Wilson, A., Jane's 1996-1997, Jane's Space Directory, 12 Ih Ed. Ltd., 1994, Sentinel House, pp.334. 2Myers, R.M., Schneider, Propulsion Proceedings University 29- Sept. 1, 1994. 3Sutherland, G. Surrey, England, Review Thrust," 8, August of Microrocket Oieson, S.J., "Chemical Options for of the Conference State Aug. M. 10 -6 to 1 lbf J. Spacecraft 1966. and Rockets, Vol. 3, No. reaction P., R.C., Satellite Company, January, S., and Maes, Technology: E.: "A Information Group UK, 8 th on AIAA Utah Small Satellites, pressure vessels regenerative fuel cells," 1996 Fuel Cell Seminar, and System annual Satellites, 84322. 17-20, 1996, Orlando, UCRL-MI- 125220. J.F., system UTC March regenerative for aircraft and Hamilton Standard 1994. fuel orbital div., "Unitized S.R., Curran, and Small F.M., and Campbell, Propulsion Technical 1973. J.G. Conference, February 16-19, 1993. Electrical Satellites," Propulsion Information 1965. Report Weisberg, and FL; UCRL-JC- AIAAPDF Image | Electrolysis Spacecraft Propulsion Applications
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