Отправить статью по E-mail Thrust characteristics of an airbreathing pulse detonation engine in flight at mach numbers of 0.4 to 5.0
- Авторы: Zangiev A.E.1,2,3, Ivanov V.S.1,2,3, Frolov S.M.1,2,3
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Учреждения:
- Semenov Institute of Chemical Physics
- Center of Pulse Detonation Combustion
- National Nuclear Research University “MEPhI,”
- Выпуск: Том 10, № 2 (2016)
- Страницы: 272-283
- Раздел: Combustion, Explosion, and Shock Waves
- URL: https://journals.rcsi.science/1990-7931/article/view/197453
- DOI: https://doi.org/10.1134/S1990793116020135
- ID: 197453
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Аннотация
Multidimensional calculations are performed to demonstrate that, by its characteristics, the pulse detonation engine (PDE) is a unique type of ramjet propulsion system, which can be used in both subsonic and supersonic aircraft. By a number of examples, it is shown that, in various thrust characteristics, such as the specific impulse, specific fuel consumption, and specific thrust, the PDE substantially exceeds ramjet engines.
Об авторах
A. Zangiev
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Email: smfrol@chph.ras.ru
Россия, Moscow; Moscow; Moscow
V. Ivanov
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Email: smfrol@chph.ras.ru
Россия, Moscow; Moscow; Moscow
S. Frolov
Semenov Institute of Chemical Physics; Center of Pulse Detonation Combustion; National Nuclear Research University “MEPhI,”
Автор, ответственный за переписку.
Email: smfrol@chph.ras.ru
Россия, Moscow; Moscow; Moscow
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