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
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Издатель
Научные группы
Организационные подразделения
Организационная единица
Институт лазерных и плазменных технологий
Стратегическая цель Института ЛаПлаз – стать ведущей научной школой и ядром развития инноваций по лазерным, плазменным, радиационным и ускорительным технологиям, с уникальными образовательными программами, востребованными на российском и мировом рынке образовательных услуг.
Выпуск журнала
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.
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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
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