| タイトル | Thermal Hydraulics Design and Analysis Methodology for a Solid-Core Nuclear Thermal Rocket Engine Thrust Chamber |
| 本文（外部サイト） | http://hdl.handle.net/2060/20130001802 |
| 著者（英） | Wang, Ten-See; Ito, Yasushi; Canabal, Francisco; Cheng, Gary; Chen, Yen-Sen |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2013-01-01 |
| 言語 | eng |
| 内容記述 | Nuclear thermal propulsion is a leading candidate for in-space propulsion for human Mars missions. This chapter describes a thermal hydraulics design and analysis methodology developed at the NASA Marshall Space Flight Center, in support of the nuclear thermal propulsion development effort. The objective of this campaign is to bridge the design methods in the Rover/NERVA era, with a modern computational fluid dynamics and heat transfer methodology, to predict thermal, fluid, and hydrogen environments of a hypothetical solid-core, nuclear thermal engine the Small Engine, designed in the 1960s. The computational methodology is based on an unstructured-grid, pressure-based, all speeds, chemically reacting, computational fluid dynamics and heat transfer platform, while formulations of flow and heat transfer through porous and solid media were implemented to describe those of hydrogen flow channels inside the solid24 core. Design analyses of a single flow element and the entire solid-core thrust chamber of the Small Engine were performed and the results are presented herein |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | M12-1927 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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