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Analysis of nonstationary thermal state of low-thrust liquid rocket engine with high-concentration hydrogen peroxide and kerosene propellant with film cooling
- Authors: Vorobiev A.G.1, Borovik I.N.1, Ha S.2
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Affiliations:
- Moscow Aviation Institute (National Research University)
- KARI - Korea Aerospace Research Institute
- Issue: Vol 13, No 1 (2014)
- Pages: 30-40
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/1695
- DOI: https://doi.org/10.18287/1998-6629-2014-0-1(43)-30-40
- ID: 1695
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Abstract
The paper presents an analysis of the nonstationary thermal state of a low-thrust liquid rocket engine with HTHP (high-test hydrogen peroxide) and kerosene propellant with film cooling. A mathematical model was developed with internal convective and radiant heat fluxes. The model takes into account the heat flux pass through the wall. The results of the calculations show that in order to provide long working life of the combustion chamber wall it is necessary to use either 96% of HPK at the level of 20% of HTHP or 20% of kerosene needed for film cooling.
About the authors
A. G. Vorobiev
Moscow Aviation Institute (National Research University)
Author for correspondence.
Email: formula1_av@mail.ru
Candidate of Science (Engineering), Associate Professor
Russian FederationI. N. Borovik
Moscow Aviation Institute (National Research University)
Email: borra2000@mail.ru
Candidate of Science (Engineering), Associate Professor
Russian FederationSong-Up Ha
KARI - Korea Aerospace Research Institute
Email: mars_hadius@hotmail.com
Senior Research Engineer
Advanced Rocket Research Team
Korea, Republic ofReferences
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- Kozlov A.A., Abashev V.M. Raschet i proektirovanie zhidkostnogo raketnogo dvigatelja maloj tjagi [Calculation and design of a low-thrust liquid-propellant engine]. Moscow: MAI Publ., 2003.
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