Development of advanced technologies for future cryogenic thrust chamber applications-Reference-Cited by-同舟云学术

Development of advanced technologies for future cryogenic thrust chamber applications

Published:1997-07-06 Issue: Volume: Page:
ISSN:
Container-title:33rd Joint Propulsion Conference and Exhibit
language:
Short-container-title:

Author:

Zinner W.¹,Haeseler D.¹,Maeding C.¹,Rubinskij V.²,Gorochov V.²,Hrisanfov S.²,Nikulin G.³,Zinner W.¹,Haeseler D.¹,Maeding C.¹,Rubinskij V.²,Gorochov V.²,Hrisanfov S.²,Nikulin G.³

Affiliation:

1. Daimler-Benz Aerospace AG, Munich, Germany

2. Chemiautomatics Design Bureau, Voronezh, Russia

3. Keldysh Research Center, Moscow, Russia

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1997-3312

Reference7 articles.

1. H. Immich, Dasa-M. Caporicci, ESA FESTIP Technology Development in Liquid Rocket PropulsionforReusableLaunchVehicles AIAA-96-3113

2. R.J.Quentmeyer Rocket Combustion Chamber Life Enhancing Design Concepts AIAA-90-2116

Cited by 4 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. Investigation of full-scale porous injector plate transpiration cooling coupled with combustion in high-thrust H2/O2 rocket engines;Applied Thermal Engineering;2023-07

2. Injector Head Transpiration Cooling Coupled with Combustion in H2/O2 Subscale Thrust Chamber;Journal of Thermophysics and Heat Transfer;2013-01

3. Experimental investigation of transpiration cooled hydrogen-oxygen subscale chambers;34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit;1998-07-13

4. Numerical prediction of flow separation for advanced nozzle concepts;34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit;1998-07-13