Modular, ion-propelled, orbit-transfer vehicle

Hermel, J.; Meese, R.; Rogers, W. P.; Kushida, R.; Beattie, J. R.

doi:10.2514/3.26014

Cited by 16 publications

(3 citation statements)

References 5 publications

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“…The effects of eclipse and drag were not explicitly included in this study. Hermel et al 55 found that approximately 9% of a low thrust LEO -GEO transfer would be spent in eclipse resulting in a corresponding increase in trip time. While drag was not explicitly included in this study, the 370 km initial altitude did not significantly penalize a 30 kW SEOTV studied by General Dynamics.…”

Section: Propulsion System Comparisonmentioning

confidence: 99%

Low power pulsed MPD thruster system analysis and applications

Myers

Domonkos²,

Gilland

1993

29th Joint Propulsion Conference and Exhibit

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Section: Propulsion System Comparisonmentioning

confidence: 99%

Low power pulsed MPD thruster system analysis and applications

Myers

Domonkos²,

Gilland

1993

29th Joint Propulsion Conference and Exhibit

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“…Therefore, although ∆v delivered may be impressive (1.31 km for double-strength UHMWPE rope), most of the delivered ∆v is over the ∆v required for LEO orbit insertion. It must be stressed that all ∆v beyond minimal-altitude (185 km approximately) circular LEO delivered by bolo system is simpler (and cheaper) to deliver using onboard ion motors or inter-orbital ion tug, for example, the ion tug designed by Jaffe [48] or Hermel [49]. Ion tug will clearly be more efficient in the absence of the heavy, damage-prone tether.…”

Section: Example Missions Designsmentioning

confidence: 99%

The Space Mission Design Example Using LEO Bolos

Nizhnik¹

2013

Aerospace

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Four sample space launch missions were designed using rotating momentum transfer tethers (bolos) within low Earth orbit and a previously unknown phenomenon of -aerospinning‖ was identified and simulated. The momentum transfer tethers were found to be only marginally more efficient than the use of chemical rocket boosters. Insufficient power density of modern spacecrafts was identified as the principal inhibitory factor for tether usage as a means of launch-assistance, with power densities at least 10 W/kg required for effective bolos operation.

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“…26,30,34,[79][80][81] Liquid storage of inert gases at cryogenic temperatures has also been suggested, especially for argon. 22 As a gas, xenon tankage fractions of 0.1 to 0.2 have been estimated.…”

Section: Propellant Storage and Distributionmentioning

confidence: 99%

Xenon ion propulsion for orbit transfer

Rawlin

Patterson

Gruber

1990

21st International Electric Propulsion Conference

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For more than 30 years, NASA has conducted an ion propulsion program which has resulted in several experimental space flight demonstrations and the development of many supporting technologies. Technologies appropriate for geosynchronous stationkeeping, Earth-orbit transfer missions, and interplanetary missions have been defined and evaluated. The status of critical ion propulsion system elements is reviewed in this paper. Electron bombardment ion thrusters for primary propulsion have evolved to operate on xenon in the 5-10 kW power range. Thruster efficiencies of 0.7 and specific impulse values of 4000 s have been documented. The baseline thruster currently under development by NASA LeRC includes ring-cusp magnetic field plasma containment and dished two-grid ion optics. Based on past experience and demonstrated simplifications, power processors for these thrusters should have approximately 500 parts, a mass of 40 kg, and an efficiency near 0.94. Thrust vector control, via individual thruster gimbals, is a mature technology. High pressure, gaseous xenon propellant storage and control schemes, using flight qualified hardware, result in propellant tankage fractions between 0.1 and 0.2.In-space and ground integration testing has demonstrated that ion propulsion systems can be successfully integrated with their host spacecraft. Ion propulsion system technologies are mature and can significantly enhance and/or enable a variety of missions in the nation's space propulsion program.

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Modular, ion-propelled, orbit-transfer vehicle

Cited by 16 publications

References 5 publications

Low power pulsed MPD thruster system analysis and applications

Low power pulsed MPD thruster system analysis and applications

The Space Mission Design Example Using LEO Bolos

Xenon ion propulsion for orbit transfer

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