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TsAGI Science Journal

ISSN Imprimir: 1948-2590
ISSN On-line: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.2018026652
pages 683-698

NEW TYPE OF PULSED THERMAL ACTUATOR

Aleksandr Vladimirovich Voevodin
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Anton Andreevich Kornyakov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Aleksander Sergeevich Petrov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region
D. A. Petrov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Georgiy Grigoryevich Soudakov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky Str. 1, Zhukovsky 140180, Russia

RESUMO

Methods to control the gas flow around an aircraft by pulsed thermal actuators of various types are considered. The operation principles and flight modes in which they can be effectively used are discussed. It is argued that the known types of plasma actuators can be effective only at low flight velocities of unmanned aerial vehicles. To extend the range of flight velocities, a new type of actuator is considered, namely, a pulsed thermal actuator. The calculations show that this actuator has a serious disadvantage, which is active zone overheating at high pulse repetition frequencies. Several types of pulsed thermal actuators are proposed and studied. One of which (an open-ended actuator) is designed for operation at high repetition frequencies and transonic flow velocities. Its potential capability of operation at frequencies on the order of 1 kHz is demonstrated, which is sufficient to control the majority of aerodynamic processes at high subsonic velocities. It is shown that the use of such actuators in applications with tangential jet flows is much less effective from the energy point of view compared to boundary layer suction. A new type of actuator (an ejector-type pulsed thermal actuator) is proposed for the suction regime. This actuator provides simultaneous suction of the boundary layer from the upper surface of the wing and gas ejection in the trailing edge region. The suction velocity ensured by the operating model of the actuator is determined in experiments by hot wire anemometry.


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