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smalsllotsonthebackofahydrogesnplitterring providedradial injectionof the "igniter hydrogenw",hilesixelemenctsantedinward temperatuArleld.atawererecordewdithastand- alonedataacquisitiosnystemandstoredin a personcaolmputer. providehdydrogeinjectiofnurthedrownstream. Nofilm coolingwasemployeAd.5-cmlong water-cooleadapterw,ithastainlessteel boundarlyayertrip ring,providedadditional mixingandwasusetdomounthtechambteorthe inletpressuretse,mperaturaen,dcalibration. injector. TwochambewrseretestewdiththeinjectorA. coppehreat-sinckhambwerasusedforcheckout ofthesystema,ndanIr/Rechambwerasthen installefdorthemajorityoftestingT.heIr/Re chambedre,signefodrI-Nthrustc,onsisteodfa 8.98-mmdiametecrhambearnda 2.41-mm diametethrroaTt.henozzlexpansiorantiowas 23.3I.t hadpreviousulyndergolnifetestinagnd hadanaccumulatesdtimeof 11.5hoursata mixtureratioof 5. Thecoppecrhambehrada similardiametecrhambear,2.43mmdiameter throat,butaslightlyshortecrhamberand differenctonvergisnegction. Thermocouplaensd pressurteransducearst selectelodcationseatrheelectrolysuinsit,the storagteanksa,ndthethrustewr,ereusedto monitotremperatuarnedpressurceonditions. Particlfeiltersdownstreaomf thestoragteanks removepdarticleslargerthan15 micronto protecvtalveseatsandinjectorports.Relief valversatedat1.0MPaneatrheelectrolysuinsit protectethdeunitfromoverpressurizatiniotnhe caseofcomponemnatlfunction. Experimental Approach The breadboard system was installed and tested inside the high altitude simulation test facility described in Reference 20. Figure 5 is a photograph of the test configuration. Ambient pressure in the altitude chamber during the test Both the theoreticaland experimental characterisvteiclocitCy*,whichisameasuoref combustieofnficienccyo,uldbedeterminwedith standamrdethodasndusingtheCEC(chemical equilibriumcode2)1for thegivenpropellant mixturreatio.TheC*efficiencdye,finedasthe ratio of experimentavlersustheoretical characterisvteiclocityw,asalsodetermined. In preparation for a series of tests, all air from the electrolysis unit, storage tanks, and propellant lines was evacuated by means of opening the valves to the high altitude environment. After propellant system evacuation, the thruster valves were closed, the supply valves opened, and was maintained two-stage ejector. the testing of the both during the during the hot-fire test with the thruster. simultaneously. Combustion chamber at propellant using a during system, well as approximately 1 kPa Key data breadboard were obtained propulsion generation as pressures test from decreased during a typical 190 to 138 kPa. This Key parameters, measured and recorded the electrolysis fill cycle, were tank pressures and temperatures, electrolysis pressure and temperature, ambient pressure and temperature, and electrolysis current and voltage. The last two variables were power. Parameters were the pressures combustion chamber, tanks in 0.1 s increments, venturi inlet pressures and temperatures, and ambient pressure and NASA TM-113157 7 determined recorded during hot-fire temperatures tests in the in the and wall the pressure drop during by the available In additionto themeasurepdarametesrso,me additionqaulantitiewserecalculatePdr.opellant flowratescouldbecalculatefrdomtheventuri power Hydrogen was supplied and oxygen to the were generated and unit. the storage pressure ofaround 1MPa. Different power levels were applied at a number of electrolysis cycles in order to establish conversion efficiency variations for varying propellant generation rates. The duration of the propellant fill was between twenty minutes and several hours, depending on the power level. Data were taken at five minute intervals. A rocket firing followed each tank fill. Thruster- valve opening and spark ignition initiated combustion. The lead time between the spark ignition and the thruster valves opening was pre- set. For most of the tests reported in this paper, spark ignition and thruster valve opening tanks were filled to a predetermined occurred selected the present electrolysis system. Hot-fire tests were terminated after the chamber pressure dropped below a pre-set value, which was selected to provide an acceptable combustion efficiency during this blowdown test. During hot- fire tests, data were taken at 100 ms intervals. Test conditions varied during a sequence of hot- fire tests as the result of changing system conditions. The volume occupied by hydrogen blowdown range was point of the chamber (170 kPa). A typical test duration was 3-4 s, which was limited by the volume of the tanks and the maximum pressure allowed with as it bounds the design electrolysisPDF Image | Electrolysis Spacecraft Propulsion Applications
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