Vehicle configuration options using nuclear propulsion for Mars missions

Conference · Wed Jan 20 04:00:00 EST 1993 · AIP Conference Proceedings (American Institute of Physics); (United States)

DOI:https://doi.org/10.1063/1.43032· OSTI ID:5460512

Emrich, Jr, W J ^[1]

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1. NASA-Marshall Space Flight Center, Huntsville, Alabama 35812 (United States)

The solid core nuclear thermal rocket (NTR) provides an attractive means of providing the propulsive force needed to accomplish a wide array of space missions. With its factor of two or more advantage in Isp over chemical engines, nuclear propulsion provides the opportunity to accomplish space missions which are impractical by other means. This paper focuses on the use of a nuclear thermal rocket to accomplish a variety of space missions with emphasis on the manned Mars mission. The particle bed reactor (PBR) type nuclear engine was chosen as the baseline engine used to conduct the present study because of its perceived versatility over other nuclear propulsion systems in conducting a wide variety of tasks. This study baselines a particle bed reactor engine with an engine thrust-to-weight ratio ([similar to]11.5) and a specific impulse of [similar to]950 s. It is shown that a PBR engine of this type will offer distinct advantages over the larger and heavier NERVA type nuclear engines.

• OSTI ID: 5460512
• Report Number(s): CONF-930103--
• Conference Information: Journal Name: AIP Conference Proceedings (American Institute of Physics); (United States) Journal Volume: 271:3
• Country of Publication: United States
• Language: English

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