Novel plasma propulsion device
A plasma and propulsion device technology, applied in the field of ion plasma propulsion devices, can solve the problems of complex aero-engine design, high fuel consumption of aerospace engines, and can only be used for a single flight, so as to achieve simple structure, increased quantity, and improved The effect of thrust
Active Publication Date: 2018-12-28
郝江南
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Problems solved by technology
[0003] At present, the structural design of the aero-engine is complicated, and the blades of the engine fan have an impact on the safety of the engine. The aero-engine is used for flight in the atmosphere and cannot be used for space flight. The aero-engine consumes a lot of fuel. flight
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[0017] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on The embodiments of the present invention and all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0018] The present invention provides such Figure 1-2 A new type of plasma propulsion device shown includes the starting end of the inner wall 3 or the outer wall 4 of the spin body 1 and several groups of plasma actuators 2 arranged helically along the direction of rotation, and each group of plasma actuators 2 includes The upper electrode 5, the lower electrode 6 and the insulating layer 7, the insulating layer 7 is arranged between the upper...
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The invention discloses a novel plasma propulsion device, which comprises an inner wall or outer wall starting end of a spin-formed body and a plurality of sets of plasma exciters arranged spirally along a rotating direction; each set of the plasma exciter comprises an upper electrode, a lower electrode and an insulating layer; the insulating layer is disposed between the upper electrode and the lower electrode, and the insulating layer is wrapped around the outer surface of the lower electrode; the plasma actuator is spirally arranged on the inner wall or outer wall of the spin-formed body along the rotating direction; the second set of plasma exciter is arranged below the lower electrode of the first set of the plasma exciter along the axis direction of the spirally formed body; finally,the airflow on the whole surface of the spin-formed body is forwards accelerated; thrust is generated; when a concentric circle is adopted, the number of the plasma is increased, and the thrust is improved; the scheme can be applied to aircraft and spaceflight aircraft, the performance of the weapon is improved; and the plasma engineering is pushed.
Description
technical field [0001] In order to realize the application of plasma technology in the field of propulsion, the invention specifically relates to a novel plasma propulsion device. Background technique [0002] Plasma flow control technology is a flow control technology that has received attention in recent years. Many countries have extensively carried out flow separation control of plasma actuators, research on boundary layer flow control, reducing aerodynamic noise, controlling flow separation around cylinders, and multi-stage plasma flow control. Actuator design and other aspects are emerging research hotspots in the field of aerodynamics and aerothermodynamics in the world. The application of DBD plasma flow control technology may greatly improve the performance of aircraft and power plants, so that Jane's Defense Weekly commented on the research that plasma conducted abroad can drastically change the aerodynamic characteristics of aircraft as: We will look forward to a ...
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Login to View More IPC IPC(8): F03H1/00
CPCF03H1/0006F03H1/0087
Inventor 郝江南
Owner 郝江南