Design Options for a Versatile Nuclear Thermal Propulsion (NTP) Stage

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Design Options for a Versatile Nuclear Thermal Propulsion (NTP) Stage

Houts, Michael G. / Joyner, Claude R.; II / Kokan, Timothy S. / Reynolds, Britton / Abrams, John / Beale, Dani / Denbrock, Chad / Easley, Jacob

Abstract

A study was initiated to investigate propulsion stage and mission architecture options potentially enabled by fission energy. One initial concept is a versatile Nuclear Thermal Propulsion (NTP) system with a maximum specific impulse of 900 s and a maximum thrust (per engine) of 15 klbf. The system assumes a monopropellant stage (hydrogen), and is designed to also provide 300 lbf of thrust (potentially split between multiple thrusters) at an Isp > 500 s. Boost pumps are used to assist with engine decay heat removal and low thrust engine burns, and to compensate for partial tank depressurization during full thrust engine burns. Potential stage assembly orbits that take full advantage of launch vehicle payload mass and volume capabilities are being assessed. The potential for using NTP engines to also generate a small to moderate amount of electrical power is also being evaluated.

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Document information

Title :

Design Options for a Versatile Nuclear Thermal Propulsion (NTP) Stage

Contributors:

Houts, Michael G. (author) / Joyner, Claude R.; II (author) / Kokan, Timothy S. (author) / Reynolds, Britton (author) / Abrams, John (author) / Beale, Dani (author) / Denbrock, Chad (author) / Easley, Jacob (author)

Conference:

AIAA Space Forum ; 2018 ; Orlando, FL, United States

Publication date :

2018-09-17

Type of media :

Conference paper

Type of material :

No indication

Language :

English

Keywords :

Spacecraft Propulsion And Power , Fission Power Propulsion