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- Title
Rocket Engine with Continuous Detonation Combustion of the Natural Gas--Oxygen Propellant System.
- Authors
Frolov, S. M.; Aksenov, V. S.; Ivanov, V. S.; Medvedev, S. N.; Shamshin, O.; Yakovlev, N. N.; Kostenko, I. I.
- Abstract
In a demonstrator of a detonation rocket engine (DRE) using the natural gas--oxygen propellant system, a high (270 s) specific impulse at sea level at a low (32 atm) mean combustor pressure was experimentally obtained for the first time. Comparison of these characteristics with the respective ones (263 s and 61 atm) of the well-known Russian RD 170-A liquid-propellant rocket engine using deflagration combustion of the kerosene--oxygen propellant system showed that the specific impulse at sea level in the DRE is close to that in the deflagration-combustion engine but is produced at half as high a mean combustor pressure. This indicates that the energy efficiency of detonation combustion exceeds that of deflagration combustion, and that there is room to improve the weight--size characteristics of the turbopump unit in the DRE.
- Subjects
ROCKET engines; COMBUSTION; NATURAL gas; PROPELLANTS; KEROSENE
- Publication
Doklady Physical Chemistry, 2018, Vol 478, Issue 2, p31
- ISSN
0012-5016
- Publication type
Article
- DOI
10.1134/S001250161802001X