Nuclear Thermal Rocket/Stage Technology Options for NASA's Future Human Exploration Missions to the Moon and Mars

Borowski, Stanley K.; Corban, Robert R.; McGuire, Melissa L.; Beke, Erik G.

doi:10.1063/1.2950265

AIP Conference Proceedings 1994

DOI: 10.1063/1.2950265

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Nuclear Thermal Rocket/Stage Technology Options for NASA's Future Human Exploration Missions to the Moon and Mars

Stanley K. Borowski¹,

Robert R. Corban²,

Melissa L. McGuire³

et al.

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Cited by 2 publications

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“…4 shows the magnitude of the axial (top) and radial (bottom) velocity components. The axial velocity increases downstream as the plume expands and becomes negative in the backflow region.…”

mentioning

confidence: 99%

Nuclear thermal rocket plume interactions with spacecraft. Final report

Mauk¹,

Gatsonis²,

Buzby³

et al. 1997

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This report was prepared as an account of work sponsored by an agency of the United States Government. Neither the United States Government nor any agency thereof, nor any of their employees, make any warranty, express or implied, or assumes any legal liability or responsibiKty for the accuracy, completeness, or usefulness of any information, apparatus, product, or process disclosed, or represents that its use would not infringe privately owned rights. Reference herein to any specific commerud product, p m e s , or service by trade name, trademark, manufacturer, or otherwise does not necessarily comtitute or imply its endorsement, recommendation, or favoring by the United States Government or any agency thereof. The views and opinions of authors expressed herein do not necessarily state or reflect those of the United States Government or any agency thereof. Nuclear Thermal Rocket Plume Interactions with Spacecraft Summary of Accomplishments This is the first study that has treated the Nuclear Thermal Rocket (NTR) effluent problem in its entirety, beginning with the reactor core, through the nozzle flow, to the plume backflow. The summary of major accomplishments is given below: Including a chemically reacting Navier-Stokes code for the Applying the full capabilities of the developed DSMC-PIC

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“…4 shows the magnitude of the axial (top) and radial (bottom) velocity components. The axial velocity increases downstream as the plume expands and becomes negative in the backflow region.…”

mentioning

confidence: 99%

Nuclear thermal rocket plume interactions with spacecraft. Final report

Mauk¹,

Gatsonis²,

Buzby³

et al. 1997

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show abstract

Modeling nuclear thermal rocket plume effluents

Gatsonis

Buzby

Yin

et al. 1996

31st Thermophysics Conference

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Nuclear Thermal Rocket/Stage Technology Options for NASA's Future Human Exploration Missions to the Moon and Mars

Cited by 2 publications

References 2 publications

Nuclear thermal rocket plume interactions with spacecraft. Final report

Nuclear thermal rocket plume interactions with spacecraft. Final report

Modeling nuclear thermal rocket plume effluents

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