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lightweightatnkagperoposeidnthecurrent This paper will first describe recent advances in systemw,hichwouldprovidehigherspecific energyIn.tegratinthgefuelcellsystemwithan electrolyspirsopulsiosnystemfurtherreducethse combinepdropulsioandpowesrystemweight duetocommocnomponenstusc,hasgastorage andtheelectrolyzer/cfueelll.Theenergdyensity of sucha unitizesdystemfor LEOapplications increasaensordeorfmagnitud(-e150W-hr/kg). Also,theweighatdvantaogfebothstandalone fuel cellsandunitizedsystemisncreasefosr missionwsitha longeernergcyharge-discharge cyclesT.hisresultfsromtheseparatiofnpower andenergyinsidetheURFCB.atteriescale linearlywith energystoragerequirement, whereafosrURFC'so,nlythestoragtaenkscale withenergystoragrequiremenTthse. reactor staciksscaleodnlyforpower. Perceivesdystemcomplexitcyanbea major obstaclteo in-flightuse.Theadditionof an electrolyzetor thepropulsiosnystemslightly increasecsomplexitoyvera gaspressurized systemH.owevethr,ecombinatiofnatenfolodr morereductioin combinepdropulsion/power systemasosverstate-of-thes-aysrtemansdthe cleannesosf propellantcsanfavora more complesxystem. Thefull advantaogfeelectrolyspisropulsioisn gainedwhenpossiblesynergiewsith other subsysteamresrealizedA. schemaotifcsucha proposeudnitizedsystemis shownin Fig. 1. Because most of the power for flight electronics isn't required during orbital transfer maneuvers, it will often be available to electrolyze water without adding additional capability and mass penalty. High performance gas storage tanks can provide some, if not most of the structure required by spacecraft that must function as stiff instrument platforms. A unitized propulsion and power system was proposed for a New Millennium Program spacecraft concept. 7 For the system proposed, a URFC was used to replace the baseline batteries for energy storage. The modest 30% increase in electrolyzer mass was more than offset by the savings in battery mass which accounted for as much as 10% of the wet mass. The projected benefits of such an integrated system were a weight savings of over component technologies which may make electrolysis propulsion a viable candidate for a variety of mission scenarios. This is followed by a description of a testbed built at NASA LeRC in a cooperative program partnering Lewis Research Center, Hamilton Standard and Lawrence Livermore National Laboratories, and results obtained from experiments in a high 50% for low-earth-orbit spacecraft, increasing permeable membranes which allow osmotic chamber. produce with analyses provide applications which require a large number of impulsive bums. water transport Because water is being propellants, a water gradient the water feed barrier and more water from the storage tank enters the cell. An electrochemical higher energy show that storage electrolysis needs. Missions systems also savings for into the hydrogen consumed NASA TM-113157 3 significant weight to is established across altitude simulation chamber. Component Technologies A schematic of a water electrolysis propulsion system which could propulsion functions application is shown primary thruster for cold gas thrusters for primary bums, and twelve cold gas thrusters for attitude control (ACS). This system is designed to replace two conventional (i.e. cold gas and NEH4) systems that would be needed to perform the same functions in a mission utilizing state-of- the-art technology. Key components of the water electrolysis system are discussed below. They are the etectrolyzer, gas dryers, the water and propellant tankage, the propellant feed system, and the thrusters. In addition, the technology to integrate propulsion and power is discussed. Electrolyzer A detailed description of the water vapor feed electrolyzer is given in Reference 7. This electrolyzer is based on Hamilton Standards' solid polymer electrolyte (SPE _) technology. The electrolyzer uses this sulfonic acid proton exchange membrane as the sole electrolyte. The membrane is fashioned into electrochemical cells by bonding catalyst electrodes to both faces. The single electrolysis cell consists of a water feed be thrust vector control during chamber, a water permeable membrane, hydrogen chamber, a SPE membrane, an oxygen chamber, an and electrical Hydrogen and oxygen are produced on side of the SPE membrane with the application of DC power. The water feed chamber is separated from the hydrogen gas chamber by water in used a to provide all small satellite in high AV maneuvers, four Fig. 2. It includes a electrochemical insulators on both end hydrogen pump, plates. either aPDF Image | Electrolysis Spacecraft Propulsion Applications
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