Two-phase flow characteristics of cryogenic propellant in filling the head cavity of liquid rocket engine-Reference-Cited by-同舟云学术

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Two-phase flow characteristics of cryogenic propellant in filling the head cavity of liquid rocket engine

Published:2024-06 Issue: Volume:246 Page:122976
ISSN:1359-4311
Container-title:Applied Thermal Engineering
language:en
Short-container-title:Applied Thermal Engineering

Author:

Liu Jiaxun,Zhou Wenyuan,Dou Suyi,Zhang Miao,Yang Qingchun,Xu Xu

Publisher

Elsevier BV

Reference40 articles.

1. D.K. Huzel, D.H. Huang, Design of liquid propellant rocket engines, 1967.

2. History of liquid propellant rocket engines;Sutton,2006

3. A review of cryogenic rocket engine;Thakur;Int. Res. J. Eng. Technol.,2017

4. An RL10A-3-3A rocket engine model using the rocket engine transient simulator (ROCETS) software;Binder;29th Joint Propulsion Conference and Exhibit.,1993

5. Two-phase flow characteristics of liquid oxygen flow in low pressure liquid rocket engine;Cho;Cryogenics,2004

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1. Analysis and optimization of LN2 two-phase flow in CRAFT NNBI cryopump;Nuclear Engineering and Technology;2024-08

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