CN105704901B - A kind of honeycomb type dielectric barrier discharge plasma propulsion plant - Google Patents

Abstract

The invention provides a honeycomb dielectric barrier discharge plasma propulsion device, comprising: a casing, a high-voltage power supply and a honeycomb structure arranged in the casing, along the axial direction of the honeycomb structure, an M A layer of high-voltage electrodes, an M-layer ground electrode is provided at the position where the insulating medium wall intersects with the M-layer high-voltage electrodes, and two adjacent layers of high-voltage electrodes and ground electrodes form a dielectric barrier discharge plasma actuator. The main part of the invention is a honeycomb structure, which is simple in structure, light in weight, and low in manufacturing cost; without moving parts, it responds quickly and has high reliability; by controlling the voltage and frequency of the high-voltage power supply, the excitation intensity and power consumption can be flexibly set, and the thrust can be precisely controlled The direction of thrust can be adjusted by adjusting the direction of the axis of the honeycomb structure. When it is applied to an airship, it can realize precise control of the speed and direction of the airship. It does not need to carry fuel and can realize the long-term resident airship of the airship.

Description

A Honeycomb Dielectric Barrier Discharge Plasma Propulsion Device

technical field

The invention relates to the technical field of thrusters, in particular to a honeycomb dielectric barrier discharge plasma propulsion device, which is especially suitable for airships.

Background technique

The stratosphere generally refers to the airspace located 18 kilometers to 50 kilometers above the earth's surface. It is the upper hot and lower cold layer in the earth's atmosphere, and it is also the junction of the two systems of earth observation aviation and spaceflight. The stratosphere is the calmest part of the atmosphere, hardly affected by the weather, and almost never wet. At the same time, the stratosphere also has stable meteorological conditions and good electromagnetic characteristics, and there is currently no airspace restriction. Therefore, in view of the stratosphere With its own sports characteristics and unique advantages, it has become a new hot spot for developed countries to compete for space resources.

Due to its unique characteristics of long-term airborne, fixed-point maneuvering, low energy consumption, and high safety, the potential application prospects of stratospheric airships include: scientific research, communication relay, and military reconnaissance and other civilian and military fields. Since the stratospheric airship needs to stay in the air for a long time, if the traditional propulsion method with fuel is used, it will bring two problems: one is that the fuel carried cannot be supplied for a long time; the other is that with the consumption of fuel, the weight of the airship will change. This is detrimental to the trim and counterweight of the airship. Therefore, the traditional fuel-carrying engine propulsion system cannot be applied to stratospheric airships, and there is an urgent need for a propulsion device suitable for airships in this field.

Contents of the invention

(1) Technical problems to be solved

In order to solve the above-mentioned problems in the prior art, the present invention provides a honeycomb dielectric barrier discharge plasma propulsion device.

(2) Technical solution

The present invention provides a honeycomb dielectric barrier discharge plasma propulsion device, comprising: a housing 101, a high voltage power supply 107 and a honeycomb structure 102 arranged in the housing, wherein the honeycomb structure includes an insulating dielectric wall 103 and the The insulating medium wall 103 forms N honeycomb holes 104, and M layers of high-voltage electrodes 105 are arranged on the insulating medium walls in each honeycomb hole along the axial direction of the honeycomb structure, and the insulating medium walls are interlaced with the M layers of high-voltage electrodes M-layer ground electrodes 106 are arranged at the position, and high-voltage electrodes 105 and ground electrodes 106 are connected to the high-voltage power supply 107, wherein two adjacent layers of high-voltage electrodes 105 and ground electrodes 106 form a dielectric barrier discharge plasma actuator, and adjacent honeycomb holes 104 The ground electrodes 106 share their common insulating medium wall, where 1≤N≤1000, 1≤M≤1000.

Preferably, the M-layer ground electrode 106 is provided at the position where the insulating medium wall intersects with the M-layer high-voltage electrode, which specifically includes: the outermost edge of the honeycomb structure and the outermost edge of the insulating medium wall and the M-layer high-voltage electrode The M-layer ground electrodes 106 are arranged at the staggered positions, and the M-layer ground electrodes 106 are inlaid at the positions interlaced with the M-layer high-voltage electrodes inside the remaining insulating medium walls of the honeycomb structure, and the adjacent honeycomb holes 104 share The ground electrode 106 embedded in the common insulating medium wall.

Preferably, each layer of high-voltage electrodes in each of the honeycomb holes is connected as a whole to form a ring-shaped high-voltage electrode with the same shape as the honeycomb hole in the M layer, and the ground electrodes arranged adjacent to the insulating medium wall are connected to form an M layer. The integrated ground electrode with N honeycomb holes corresponds to the ring-shaped high-voltage electrode whose M layers in the N honeycomb holes have the same shape as the honeycomb holes.

Preferably, an insulating material 109 is provided outside the insulating medium wall at the outermost edge of the honeycomb structure, and the insulating material 109 covers the ground electrode provided outside the insulating medium wall at the outermost edge.

Preferably, it also includes: a high-voltage electrode wire, a ground electrode wire, and N high-voltage electrode connection posts 110 and a ground electrode connection post 111 respectively located at both ends of the honeycomb structure; wherein, the high-voltage electrode wire connects the The M-layer high-voltage electrodes in each honeycomb hole are connected together, and connected to the high-voltage electrode connection post 110, and then connected to the high-voltage power supply high-voltage terminal 112, and the ground electrode wire connects the M layer with N honeycomb holes The integrated ground electrodes are connected together and connected to the ground electrode connection post 111 , and then connected to the ground terminal 113 of the high voltage power supply.

Preferably, it also includes: a solar battery connected to the high voltage power supply 107 and providing electric energy for the high voltage power supply 107 .

Preferably, the cross section of the shell is hexagonal, circular, quadrangular or other polygonal; and/or the shape of the honeycomb holes is hexagonal, triangular, quadrilateral or other polygonal.

Preferably, the insulating dielectric wall and the insulating material are polytetrafluoroethylene, quartz glass or ceramic materials.

Preferably, the output waveform of the high voltage power supply is a sine wave, a square wave or a sawtooth wave.

Preferably, the materials of the high voltage electrode and the ground electrode are copper, tungsten, molybdenum or stainless steel.

(3) Beneficial effects

It can be seen from the above technical solutions that the honeycomb dielectric barrier discharge plasma propulsion device of the present invention has the following beneficial effects:

(1) Its main components are honeycomb structure, simple and compact structure, low manufacturing cost; no moving parts, quick response and high reliability;

(2) The honeycomb structure has good strength and can be processed with thinner materials, which is conducive to reducing the weight of the device. The grounding electrodes of the adjacent honeycomb holes sharing the insulating medium wall and the integrated grounding electrode structure further reduce the weight and simplify the structure;

(3) The high-voltage power supply is connected to the high-voltage electrode and the ground electrode. By controlling the voltage and frequency of the high-voltage power supply, the intensity and power consumption of the plasma excitation can be flexibly set, and the generated thrust can be precisely controlled. When it is applied to the airship, the airship can be realized. Precise control of movement speed;

(4) The direction of thrust can be adjusted by adjusting the direction of the axis of the honeycomb structure. When it is applied to an airship, it can realize flexible and precise control of the direction of motion of the airship;

(5) The electric energy consumed is provided by the solar cell, and when used in an airship, it does not need to carry fuel, which can realize the long-term resident airship of the airship;

(6) The grounding electrode is embedded in the insulating medium wall or covered by insulating material to prevent the grounding electrode from ionizing the air near it, saving electric energy and improving energy utilization efficiency;

(7) By setting high-voltage electrode wires, grounding electrode wires, high-voltage electrode connection posts, and ground electrode connection posts, the lines can be simplified, the overall structure can be optimized, and the stability and reliability of operation can be improved.

Description of drawings

Fig. 1 is the working principle diagram of dielectric barrier discharge plasma excitation structure;

Fig. 2 is a three-dimensional schematic diagram of an embodiment of the present invention;

Fig. 3 is a side view of an embodiment of the present invention;

Fig. 4 is the top view of the embodiment of the present invention;

Fig. 5 is the split plan view of position A-A in Fig. 4;

Fig. 6 is a schematic diagram of the thrust direction generated by the embodiment of the present invention;

7 is a schematic structural view of an integrated ground electrode;

FIG. 8 is a schematic structural diagram of a multilayer integrated ground electrode.

【Symbol Description】

101-shell; 102-honeycomb structure; 103-insulating medium wall;

104-honeycomb hole; 105-high voltage electrode; 106-ground electrode;

107-high voltage power supply; 108-insulation medium wall on the outermost edge; 109-insulation material;

110-high-voltage electrode connection column; 111-ground electrode connection column; 112-high-voltage power supply high-voltage end;

113-high voltage power supply grounding terminal; 114-insulation medium; 115-induced flow direction;

116-reaction force direction; 117-thrust direction; 118-plasma.

Detailed ways

In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be described in further detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

Referring to FIG. 1 , FIG. 1 is a working schematic diagram of a dielectric barrier discharge plasma excitation structure. Among them, the high-voltage electrodes 105 and the ground electrodes 106 are alternately arranged on both sides of the insulating medium 114, and the high-voltage alternating current is provided by the high-voltage power supply 107. After the high-voltage electrodes 105 and the ground electrodes 106 are connected to the high-voltage electricity, the fluid in the vicinity is ionized to generate plasma 118. 118 can induce flow, and at the same time generate a thrust opposite to the induced flow direction 115, so as to realize the excitation of the reaction force direction 116. At the same time, the ground electrode 106 can be covered by insulating material 109, so as to prevent the ground electrode 106 from ionizing the nearby air and consuming unnecessary power .

Please refer to Fig. 2-Fig. 8, the honeycomb type dielectric barrier discharge plasma propulsion device of the first embodiment of the present invention, it comprises: shell 101, the honeycomb structure 102 that is arranged in shell 101 and high-voltage power source 107, the insulation of this honeycomb structure The dielectric wall 103 forms N honeycomb holes 104, and along the axial direction of the honeycomb structure, M-layer high-voltage electrodes 105 are arranged on the insulating dielectric wall 103 in each honeycomb hole. M-layer ground electrode 106, high-voltage electrode 105 and ground electrode 106 are all connected to high-voltage power supply 107, wherein adjacent two layers of high-voltage electrode 105 and ground electrode 106 form a dielectric barrier discharge plasma exciter, and adjacent honeycomb holes 104 share its common insulation The ground electrode 106 of the dielectric wall, where 1≤N≤1000, 1≤M≤1000. In FIG. 2 and FIG. 4, the N is 7, and in FIG. 5 and FIG. 6, the M is 6.

Wherein, the outer side of the insulating medium wall 108 on the outermost edge of the honeycomb structure is provided with an M-layer grounding electrode 106 at a position intersecting with the M-layer high-voltage electrode, and an M-layer grounding electrode is inlaid at a position intersecting with the M-layer high-voltage electrode inside the other insulating medium walls 106, the adjacent honeycomb holes 104 share the ground electrode 106 embedded in the common insulating medium wall.

Preferably, the cross section of the shell can be hexagonal, circular, quadrangular or polygonal; the shape of the honeycomb holes can be hexagonal, triangular, quadrilateral or polygonal.

Preferably, the material of the insulating medium wall is polytetrafluoroethylene, quartz glass or ceramics; the output voltage of the high-voltage power supply is 500V-100kV, the frequency is 100Hz-100kHz, and the waveform is sine wave, square wave or sawtooth wave; Materials are copper, tungsten, molybdenum or stainless steel.

Preferably, each layer of high-voltage electrodes in each honeycomb hole is connected as a whole, so that an annular high-voltage electrode with the same shape as the M layer and the shape of the honeycomb hole is formed in each honeycomb hole, and the ground electrodes arranged on the adjacent insulating medium wall are connected as a whole to form a M layer. As shown in Figure 7, the integrated ground electrode with N honeycomb holes corresponds to the ring-shaped high-voltage electrode with M layers in the N honeycomb holes having the same shape as the honeycomb holes.

In the honeycomb dielectric barrier discharge plasma propulsion device of the first embodiment of the present invention, after the dielectric barrier discharge plasma actuator is connected to high voltage, the high voltage electrode and the ground electrode of the dielectric barrier discharge plasma actuator are connected to ionize the fluid in the vicinity Plasma is generated, the plasma induces flow along the axial direction of the honeycomb structure, and generates a thrust opposite to the direction of the induced flow, all dielectric barrier discharge plasma actuators generate thrust in the same direction, and the resultant force of all these thrusts forms a thrust along the axial direction of the honeycomb structure. It can be seen from FIG. 6 that the thrust direction 117 generated by the honeycomb dielectric barrier discharge plasma propulsion device according to the first embodiment of the present invention is along the axial direction of the honeycomb structure.

It can be seen that the honeycomb dielectric barrier discharge plasma propulsion device of the first embodiment of the present invention has a simple and compact structure and low manufacturing cost; there are no moving parts, and the response is fast and the reliability is high; by controlling the voltage and frequency of the high-voltage power supply, The intensity and power consumption of the plasma excitation can be flexibly set, and the generated thrust can be precisely controlled. When it is applied to an airship, it can realize the precise control of the airship's movement speed; the direction of the thrust can be adjusted by adjusting the direction of the axis of the honeycomb structure. When it is applied to an airship, it can realize the flexible and precise control of the airship's movement direction; the honeycomb structure has good strength and can be processed with thinner materials, which is conducive to reducing the weight of the device; adjacent honeycomb holes share the ground electrode of the insulating medium wall, and adopt The integrated ground electrode structure can reduce weight and simplify the structure; the ground electrode is embedded in the insulating medium wall to prevent the ground electrode from ionizing the air near it, thereby saving electric energy and improving energy utilization efficiency.

For the purpose of brief description of the honeycomb dielectric barrier discharge plasma propulsion device in the second embodiment of the present invention, any technical features described in the above-mentioned first embodiment that can be used in the same way are incorporated here, and there is no need to repeat the same description.

Wherein, an insulating material 109 is provided outside the insulating medium wall 108 at the outermost edge of the honeycomb structure, and the insulating material 109 covers the ground electrode provided outside the insulating medium wall 108 at the outermost edge of the honeycomb structure.

Preferably, the insulating material is polytetrafluoroethylene, quartz glass or ceramics.

In the honeycomb-type dielectric barrier discharge plasma propulsion device of the second embodiment of the present invention, the ground electrode is covered by insulating material, which prevents the ground electrode from ionizing the air near it, further saves electric energy, and improves energy utilization efficiency.

For the purpose of brief description of the honeycomb dielectric barrier discharge plasma propulsion device according to the third embodiment of the present invention, any technical features described in any of the above embodiments that can be used for the same application are incorporated here, and the same description does not need to be repeated.

Referring to Fig. 2, Fig. 3, Fig. 5 and Fig. 8, it also includes high-voltage electrode wires, ground electrode wires, and N high-voltage electrode connecting posts 110 and a grounding electrode connecting post 111 respectively located at both ends of the honeycomb structure. The wire connects the M-layer high-voltage electrodes in each honeycomb hole together, and connects to the high-voltage electrode connection post 110, and then connects to the high-voltage power supply high-voltage terminal 112; the ground electrode wire connects the M-layer integrated ground electrodes together, And connected to the ground electrode connection column 111, and then connected to the ground terminal 113 of the high voltage power supply.

The honeycomb dielectric barrier discharge plasma propulsion device according to the third embodiment of the present invention can simplify the circuit, optimize the whole structure, and improve the efficiency of operation by setting the high-voltage electrode wire, the ground electrode wire, the high-voltage electrode connection post, and the ground electrode connection post. stability and reliability.

For the purpose of brief description of the honeycomb dielectric barrier discharge plasma propulsion device according to the fourth embodiment of the present invention, any technical features described in any of the above-mentioned embodiments that can be used in the same way are all described here, and the same description does not need to be repeated.

It also includes a solar cell, which is connected to the high voltage power supply 107 and provides electric energy for the high voltage power supply 107 .

The honeycomb dielectric barrier discharge plasma propulsion device according to the fourth embodiment of the present invention, when used in an airship, uses solar cells to provide power consumption, does not need to carry fuel, and can realize the long-term resident airship of the airship.

So far, the present embodiment has been described in detail with reference to the drawings. Based on the above description, those skilled in the art should have a clear understanding of the honeycomb dielectric barrier discharge plasma propulsion device of the present invention.

It should be noted that, in the accompanying drawings or in the text of the specification, implementations that are not shown or described are forms known to those of ordinary skill in the art, and are not described in detail. In addition, the above definition of each element is not limited to the various specific structures, shapes or methods mentioned in the embodiments, and those skilled in the art can easily modify or replace them, for example:

(1) The cylindrical structure can also choose other shapes;

(2) The directional terms mentioned in the embodiments, such as "up", "down", "front", "back", "left", "right", etc., are only referring to the directions of the drawings, and are not used to limit The protection scope of the present invention;

(3) The above embodiments can be mixed and matched with each other or with other embodiments based on design and reliability considerations, that is, technical features in different embodiments can be freely combined to form more embodiments.

In summary, a honeycomb dielectric barrier discharge plasma propulsion device of the present invention has a simple and compact structure, low manufacturing cost; no moving parts, rapid response and high reliability; by controlling the voltage and frequency of the high-voltage power supply, it can Flexibly set the intensity and power consumption of the plasma excitation, and precisely control the magnitude of the generated thrust. When it is applied to an airship, it can realize precise control of the airship's movement speed; the direction of the thrust can be adjusted by adjusting the direction of the axis of the honeycomb structure. When applied to an airship, it can realize flexible and precise control of the airship's movement direction; the honeycomb structure has good strength and can be processed with thinner materials, which is conducive to reducing the weight of the device; adjacent honeycomb holes share the ground electrode of the insulating medium wall, and adopt an integrated The ground electrode structure can reduce weight and simplify the structure; the ground electrode is embedded in the insulating medium wall or covered by insulating material, so as to prevent the ground electrode from ionizing the air near it, thereby saving electric energy and improving energy utilization efficiency; by solar cells Provide the consumed electric energy without carrying fuel, and can realize the long-term resident airship of the airship.

The specific embodiments described above have further described the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above descriptions are only specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims (9)

1. A honeycomb dielectric barrier discharge plasma propulsion device, characterized in that it comprises: a housing (101), a high-voltage power supply (107) and a honeycomb structure (102) arranged in the housing, wherein, The honeycomb structure includes an insulating medium wall (103) and the insulating medium wall (103) forms N honeycomb holes (104), and the insulating medium wall in each honeycomb hole is provided with M layer high-voltage electrode (105), the position where the insulating medium wall intersects with the M-layer high-voltage electrode is provided with an M-layer ground electrode (106), and the high-voltage electrode (105) and the ground electrode (106) are connected to the high-voltage power supply (107 ), wherein adjacent two layers of high-voltage electrodes (105) and ground electrodes (106) form a dielectric barrier discharge plasma actuator, and adjacent honeycomb holes (104) share the ground electrodes (106) of their common insulating dielectric walls, wherein, 1≤N≤1000, 1≤M≤1000; The M-layer ground electrode (106) is provided at a position where the insulating medium wall intersects with the M-layer high-voltage electrode, specifically including: The M-layer ground electrode (106) is arranged at a position where the insulating medium wall outside the outermost edge of the honeycomb structure intersects with the M-layer high-voltage electrode, and The M-layer ground electrode (106) is inlaid in the position interlaced with the M-layer high-voltage electrode inside the rest of the insulating medium wall of the honeycomb structure, and the adjacent honeycomb holes (104) share the grounding embedded in the insulating medium wall. Electrodes (106). 2. The honeycomb dielectric barrier discharge plasma propulsion device as claimed in claim 1, characterized in that: Each layer of high-voltage electrodes in each of the honeycomb holes is connected as a whole to form a ring-shaped high-voltage electrode with the same shape as the M layer and the honeycomb hole, and the ground electrodes arranged on the adjacent insulating medium wall are connected into one body to form an M layer with N The integrated ground electrode of the honeycomb hole corresponds to the ring-shaped high-voltage electrode of the M layer in the N honeycomb holes having the same shape as the honeycomb hole. 3. The honeycomb dielectric barrier discharge plasma propulsion device as claimed in claim 1, characterized in that: An insulating material (109) is arranged outside the insulating medium wall at the outermost edge of the honeycomb structure, and the insulating material (109) covers the ground electrode arranged outside the insulating medium wall at the outermost edge. 4. The honeycomb dielectric barrier discharge plasma propulsion device as claimed in claim 2, further comprising: high-voltage electrode wires, ground electrode wires and N high-voltage electrode connection posts respectively located at two ends of the honeycomb structure (110) and a ground electrode connection post (111); Wherein, the high-voltage electrode wire connects the M-layer high-voltage electrodes in each honeycomb hole together, and connects to the high-voltage electrode connection column (110), and then connects to the high-voltage power supply high-voltage terminal (112) , the ground electrode wire connects the integrated ground electrodes with N honeycomb holes on the M layer together, and connects to the ground electrode connection post (111), and then connects to the high voltage power supply ground terminal (113). 5. The honeycomb dielectric barrier discharge plasma propulsion device according to claim 1, further comprising: a solar cell connected to the high voltage power supply (107) and providing electric energy for the high voltage power supply (107). 6. The honeycomb dielectric barrier discharge plasma propulsion device according to claim 1, characterized in that: the cross section of the housing is hexagonal, circular, quadrilateral or other polygonal; and/or the honeycomb hole The shape is hexagon, triangle, quadrilateral or other polygons. 7. The honeycomb dielectric barrier discharge plasma propulsion device according to claim 1, characterized in that the insulating dielectric wall and insulating material are polytetrafluoroethylene, quartz glass or ceramic materials. 8. The honeycomb dielectric barrier discharge plasma propulsion device according to claim 1, wherein the output waveform of the high voltage power supply is a sine wave, a square wave or a sawtooth wave. 9. The honeycomb dielectric barrier discharge plasma propulsion device according to claim 1, characterized in that, the materials of the high voltage electrode and the ground electrode are copper, tungsten, molybdenum or stainless steel.