Systems analysis for an operational EOTV

Miller, Todd

doi:10.2514/6.1991-2351

Cited by 5 publications

(1 citation statement)

References 3 publications

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“…For the LEO-to-GEO transfer, likely propellants include hydrogen and ammonia. 4,5,6 Helium has also been considered as a propellant for this application because of the potential for much higher efficiency with arcjets operating on helium.…”

Section: Introductionmentioning

confidence: 99%

Emission spectra of hydrogen-seeded helium arcjets

Welle

1997

33rd Joint Propulsion Conference and Exhibit

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Section: Introductionmentioning

confidence: 99%

Emission spectra of hydrogen-seeded helium arcjets

Welle

1997

33rd Joint Propulsion Conference and Exhibit

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A lightweight liquid hydrogen storage system for Electric Orbital Transfer Vehicle application

Miller¹,

Cady²

1991

27th Joint Propulsion Conference

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Krypton ion thruster performance

Patterson

Williams

1992

28th Joint Propulsion Conference and Exhibit

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Preliminary data were obtained from a 30 cm ion thruster operating on krypton propellant over the input power range of 0.4-5.5 kW. The data are presented, and compared and contrasted to those obtained with xenon propellant over the same input power envelope. Typical krypton thruster efficiency was 70 percent at a specific impulse of approximately 5000 s, with a maximum demonstrated thrust-to-power ratio of approximately 42 mN/kW at 2090 s specific impulse and 1580 watts input power. Critical thruster performance and component lifetime issues were evaluated. Order-of-magnitude power throttling was demonstrated using a simplified power-throttling strategy. parative assessment of overall thruster performance and lifetime expectations to that obtained with xenon propellant. Apparatus and Procedure A 30 cm diameter laboratory-model ion thruster was used to conduct the performance tests. The thruster, originally developed and optimized for xenon, 7 incorporated a segmented-anode geometry consisting of 3 stainless steel segments and has an exterior chamber of 0.76 mm thick cold rolled steel. The thruster uses a 'reverse-injection' propellant system for the main flow to reduce the neutral loss rate associated with the use of krypton propellant. A low-mass magnetic circuit design was employed using samarium-cobalt permanent magnets arranged to form a ring-cusp field boundary. 6's Conventional hollow cathodes, consisting of a molybdenumrhenium alloy tube and a thoriated tungsten orifice plate were employed in the discharge chamber and in the neutralizer. The orifice diameters of the discharge and the neutralizer cathodes were 1.52 mm and 0.51 mm, respectively. The cathodes utilize porous tungsten inserts impregnated with a low work function compound as the

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Systems analysis for an operational EOTV

Cited by 5 publications

References 3 publications

Emission spectra of hydrogen-seeded helium arcjets

Emission spectra of hydrogen-seeded helium arcjets

A lightweight liquid hydrogen storage system for Electric Orbital Transfer Vehicle application

Krypton ion thruster performance

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