Parametric Study of Dual-Expander Aerospike Nozzle Upper-Stage Rocket Engine-Reference-Cited by-同舟云学术

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Parametric Study of Dual-Expander Aerospike Nozzle Upper-Stage Rocket Engine

Published:2011-03 Issue:2 Volume:48 Page:355-367
ISSN:0022-4650
Container-title:Journal of Spacecraft and Rockets
language:en
Short-container-title:Journal of Spacecraft and Rockets

Author:

Simmons J.¹,Branam Richard¹

Affiliation:

1. Air Force Institute of Technology, Wright-Patterson Air Force Base, Ohio 45433

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Space and Planetary Science,Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/1.51534

Reference9 articles.

1. Martin, D. F. "Computational Design of Upperstage Chamber, Aerospike, and Cooling Jacket of Dual-Expander Rocket Engine," M.S. Thesis, Air Force Inst. of Technology, Wright-Patterson, AFB,OH, 2008.

2. Design and development of an advanced liquid hydrogen turbopump

3. Strain, W. S. "Design of an Oxygen Turbopump for a Dual Expander Cycle Rocket Engine," M.S. Thesis, Air Force Inst. of Technology, Wright-Patterson, AFB,OH, 2008.

Cited by 2 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Computational Analysis of Dual Expander Aerospike Nozzle;Advances in Mechanical Engineering;2020-06-30

2. Assessment of Aerospike Nozzle for Single-Stage to Orbit Flight;51st AIAA/SAE/ASEE Joint Propulsion Conference;2015-07-23

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