[{"data":1,"prerenderedAt":-1},["ShallowReactive",2],{"doc-seo-294257-105":3,"detail-sidebar-cat-0-en-105":81,"doc-detail-294257-en":131},{"code":4,"msg":5,"data":6},0,"ok",{"site_id":7,"language":8,"slug":9,"title":10,"keywords":11,"description":12,"schema_data":13,"social_meta":74,"head_meta":76,"extra_data":78,"updated_unix":80},105,"en","external-pulsed-plasma-propulsion-eppp-analysis-maturation","EXTERNAL PULSED PLASMA PROPULSION (EPPP) ANALYSIS MATURATION","","External Pulsed Plasma Propulsion (EPPP) systems are described as being in an early engineering stage, with shifting paradigms for application, performance, and general characteristics. Recent work emphasizes using existing technologies for near-term EPPP development for interplanetary exploration and asteroid/comet deflection. The inherent advantages of EPPP are discussed alongside applications to energy sources, and a Mars mission scenario demonstrates capability. A technology roadmap outlines mutual benefits across space propulsion research areas.",{"@graph":14,"@context":73},[15,34,56],{"@type":16,"itemListElement":17},"BreadcrumbList",[18,23,27,31],{"item":19,"name":20,"@type":21,"position":22},"https://docshare.wps.com","Home","ListItem",1,{"item":24,"name":25,"@type":21,"position":26},"https://docshare.wps.com/document/","Document",2,{"item":28,"name":29,"@type":21,"position":30},"https://docshare.wps.com/document/research-report/","Research & Report",3,{"item":32,"name":10,"@type":21,"position":33},"https://docshare.wps.com/document/external-pulsed-plasma-propulsion-eppp-analysis-maturation/294257/",4,{"url":32,"name":10,"@type":35,"image":36,"author":41,"headline":10,"publisher":44,"fileFormat":47,"inLanguage":8,"description":12,"dateModified":48,"datePublished":49,"encodingFormat":47,"isAccessibleForFree":50,"interactionStatistic":51},"DigitalDocument",{"url":37,"@type":38,"width":39,"height":40},"https://docshare.wps.com/thumbnails/external-pulsed-plasma-propulsion-eppp-analysis-maturation/294257.png","ImageObject",300,407,{"name":42,"@type":43},"WPS_1786070896","Person",{"url":19,"name":45,"@type":46},"DocShare","Organization","application/pdf","2026-11-06","2026-09-17",true,{"@type":52,"interactionType":53,"userInteractionCount":55},"InteractionCounter",{"@type":54},"ViewAction",12,{"@type":57,"mainEntity":58},"FAQPage",[59,65,69],{"name":60,"@type":61,"acceptedAnswer":62},"What stage are EPPP systems in, according to the abstract?","Question",{"text":63,"@type":64},"EPPP systems are at the engineering infancy stage, with evolving paradigms for application, performance, and general characteristics.","Answer",{"name":66,"@type":61,"acceptedAnswer":67},"What near-term applications are highlighted for EPPP development?",{"text":68,"@type":64},"Near-term EPPP development is focused on interplanetary exploration and asteroid/comet deflection.",{"name":70,"@type":61,"acceptedAnswer":71},"Why does EPPP claim to reduce a key limitation of conventional thermal rocket engines?",{"text":72,"@type":64},"EPPP reduces the material temperature constraint inherent in conventional thermal engines by operating the hottest part of the engine externally to the confinement walls and using pulsed energy 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Morton  \nNASA Marshall Space Flight CenterPropulsion Research Center.TD-40Huntsville.Alabama 35812(256)544-4019 and (256)544-4613  \n## ABSTRACT\n\nExternal Pulsed Plasma Propulsion(EPPP)systems are atthe stage of engineering infancy with evolving paradigms forapplication.performance and general characteristics.Recentefforts have focused on an approach that employs existingtechnologies with near term EPPP development for usage ininterplanetary exploration and asteroid/comet deflection.ifmandated.The inherent advantages of EPPP are discussed andits application to a variety of propulsion concepts is explored.These include,but are not limited to.utilizing energy sourcessuch as fission.fusion and antimatter.as well as.improvedchemical explosives.A mars mission scenario is presented as ademonstration of its capability using existing technologies.Asuggested alternate means to improve EPPP efficiencies couldalso lead to a heavy lift(non-nuclear)launch vehicle capability.Conceivably,true low-cost,access to space is possible usingadvanced explosive propellants and/or coupling the EPPPvehicle to a \"beam propellant\"concept.EPPP systems appearto offer an approach that can potentially cover ETO throughinterstellar transportation capability.A technology roadmap ispresented that shows mutual benefits pertaining to a substantialnumber of existing space propulsion and research areas.  \n## INTRODUCTION\n\nExternal Pulsed Plasma Propulsion(EPPP)is a highlyefficient method of propulsion.No matter what energy sourceis used to generate the plasma burst,there are inherentadvantages to its operation.EPPPs primary advantage is thatit reduces the material temperature constraint innate in all  \nconventional thermal rocket engines.In most liquid chemicalengines,using a combustion chamber and an exhaust nozzle.alarge amount of fuel is used to convectively cool the chamberwalls.Without which.the walls would quickly reach theirmelting temperature.The same is true for nuclear thermalconcepts(solid core)where the fuel temperature must bmaintained below its melting point.   In practice.thetemperature is further curbed by lower material yield strengthsat higher temperatures and practical engineering safety margins.Even in a gas core nuclear reactor.the fuel temperature cannotbe left unchecked as the containment walls.operating in steadystate must be actively cooled to avoid exceeding practicalmaterial limitations.  \nThe material limit paradox is that an arbitrary hot centralcore must be separated by a physical barrier.If the barrier is asolid.it will conduct the energy when the core is in contactwith it.If the core is not in contact(e.g.by some high-speedflow effect or electromagnetic effects)then the core's radiativeenergy is still absorbed or transmitted by the wall.In thetransmitted case,there must be a second nontransparent wall orthe hot core will be radiating into space(a 4 Kelvin heat sink).In these radiative cases,the core temperature to the fourthpower dominates the heat loss from the system.'Assumingmaterial temperatures are limited to roughly 3.000 Kelvin,theneven a 5,000 Kelvin gas temperature generates a huge 30MW/m^2 of waste heat(through radiation alone)that must berejected.Depending on the particular configuration and gasproperties,that is the same order-of-magnitude as the energyneeded to heat the gas(i.e.approximately 5 MW/kg to ideallyheat a gas from 300 Kelvin to 5.000 Kelvin.which even for apressure of 1,000 atmospheres is about 15 MWkg to reject).Obviously.the actual temperature,pressure and heat fluxeswould be different at equilibrium in a real engine.Nevertheless.the equilibrium performance is only furtherdegraded.  \nAnother discouraging fact is that even an ideal radiatorrequires an order-of-magnitude greater surface area to radiantlyreject the heat into space.Both these problems become worstas the gas temperature rises.In all realistic cases.known  ","cbCaiiuSJXZkp2jk","https://ap.wps.com/l/cbCaiiuSJXZkp2jk","pdf",721781,"English","# ABSTRACT\n# INTRODUCTION\n# BACKGROUND","[{\"question\":\"What stage are EPPP systems in, according to the abstract?\",\"answer\":\"EPPP systems are at the engineering infancy stage, with evolving paradigms for application, performance, and general characteristics.\"},{\"question\":\"What near-term applications are highlighted for EPPP development?\",\"answer\":\"Near-term EPPP development is focused on interplanetary exploration and asteroid/comet deflection.\"},{\"question\":\"Why does EPPP claim to reduce a key limitation of conventional thermal rocket engines?\",\"answer\":\"EPPP reduces the material temperature constraint inherent in conventional thermal engines by operating the hottest part of the engine externally to the confinement walls and using pulsed energy release.\"}]","EXTERNAL PULSED PLASMA PROPULSION (EPPP) ANALYSIS MATURATION | PDF",1789680763,18]