Publication: Air-breathing pulsed detonation thrust module: Numerical simulations and firing tests
Дата
2019
Авторы
Zangiev, A. E.
Frolov, S. M.
Aksenov, V. S.
Ivanov, V. S.
Shamshin, I. O.
Journal Title
Journal ISSN
Volume Title
Издатель
Аннотация
© 2019 Elsevier Masson SAS The air-breathing pulsed detonation thrust module (TM) for an aircraft designed for a subsonic flight at a speed of up to 120 m/s when operating on a standard aviation kerosene was developed using the analytical estimates and parametric multivariant three-dimensional (3D) calculations. The TM consists of an air intake with a check valve, a fuel supply system, a prechamber-jet ignition system and a combustion chamber with an attached detonation tube. An experimental sample of TM was fabricated, and its firing tests were carried out on a test rig with a thrust-measuring table. In firing tests, TM characteristics are obtained in the form of dependencies of effective thrust, aerodynamic drag and fuel-based specific impulse on fuel consumption at different speeds of the approaching air flow. It has been experimentally shown that the fuel-based specific impulse of the TM reaches 1000-1200 s, and the effective thrust developed by it reaches 180–200 N.
Описание
Ключевые слова
Цитирование
Air-breathing pulsed detonation thrust module: Numerical simulations and firing tests / Zangiev, A.E. [et al.] // Aerospace Science and Technology. - 2019. - 89. - P. 275-287. - 10.1016/j.ast.2019.04.005
URI
https://www.doi.org/10.1016/j.ast.2019.04.005
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https://openrepository.mephi.ru/handle/123456789/16871
https://www.scopus.com/record/display.uri?eid=2-s2.0-85064265736&origin=resultslist
http://gateway.webofknowledge.com/gateway/Gateway.cgi?GWVersion=2&SrcAuth=Alerting&SrcApp=Alerting&DestApp=WOS_CPL&DestLinkType=FullRecord&UT=WOS:000469896800023
https://openrepository.mephi.ru/handle/123456789/16871