Damping device to reduce the risk of injection-coupled combustion instabilities in liquid propellant rocket engines-Reference-Cited by-同舟云学术

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Damping device to reduce the risk of injection-coupled combustion instabilities in liquid propellant rocket engines

Published:2020-04 Issue: Volume:169 Page:170-179
ISSN:0094-5765
Container-title:Acta Astronautica
language:en
Short-container-title:Acta Astronautica

Author:

Armbruster Wolfgang^ORCID,Hardi Justin S.,Miene Yannik^ORCID,Suslov Dmitry,Oschwald Michael

Funder

DFG

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference30 articles.

1. Liquid Propellant Rocket Combustion Instability,1972

2. Comprehensive review of liquid-propellant combustion instabilities in F-1 engines;Oefelein;J. Propuls. Power,1993

3. Combustion stability improvement of LE-9 engine for booster stage of H3 launch vehicle;Watanabe;Mitsubishi Heavy Ind. Tech. Rev.,2016

4. Development status of LE-7A and LE-5B engines for H-IIA familiy;Fukushima;Acta Astronaut.,2002

5. On triggering and suppresion of combustion instabilities in LOX/RP-1 LREs;Wang,2016

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