Aircraft Controlled by Pneumatic Vortex Generator and Plasma Synthetic Jet

Abstract

The invention discloses an aircraft controlled by a combination of a pneumatic vortex generator and a plasma synthetic jet, which comprises a projectile body, an embedded air inlet, a pneumatic vortex generator located on the projectile body, and a jet on the guide surface of the air inlet. Plasma synthetic jet actuator. Among them, part of the incoming boundary layer is blown off by a pneumatic vortex generator, so that the entrainment vortex sucks the fluid with higher energy. A new vortex is induced to force the high-energy flow at the bottom to flow to the center of the pipe while keeping the vortex intensity small, thereby further reducing the total pressure distortion of the outlet section of the inlet. The invention makes full use of the advantages of the two control methods, the control effect is better than that of the single control, the air consumption is less than 0.5% of the engine flow, and the flow control state can be adaptively adjusted according to the flight state, which has broad engineering and practical prospects.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a buried air intake. Background technique [0002] The air intake is one of the important aerodynamic components of the air-breathing propulsion system. The design of the advanced air intake must pay attention to its electromagnetic stealth, structural length and weight, external resistance, and integration with the aircraft while tapping its own aerodynamic potential. And other integration factors, embedded air intake came into being. [0003] The buried air intake has a unique integration advantage because it does not present any protruding parts on the fuselage: first, the inlet is completely integrated with the surface of the fuselage, so it can significantly reduce the windward resistance of the aircraft and greatly reduce the air intake. Secondly, it effectively reduces the electromagnetic echo in the inlet cavity and the corner area between the outer surface of the inlet an...

AI Technical Summary

Problems solved by technology

There has been a lot of research work at home and abroad to realize the effective control of the internal swirl flow and its induced separation in the buried inlet. Among them, the active control method mainly uses the jet vortex generator, but the jet vortex generator alone requires In order to achieve a better control effect, it is often necessary to divert the airflow exceeding 1% of the mainstream flow from the high-pressure compressor, which has a great impact on the thrust and stable working boundary of the engine, while the passive flow control method is mainly aerodynamic vortex generation The protruding blades not only have the risk of falling off but also cannot be adjusted according to the flight state. Therefore, it is necessary to develop a flow control method that consumes less energy and can actively adapt to the state of the aircraft.

Images