Plasma unmanned aerial vehicle device for 3D printing

Abstract

The utility model discloses a 3D printing plasma unmanned aerial vehicle device, which comprises an unmanned aerial vehicle main body and plasma propellers, four groups of plasma propellers are arranged and are distributed in a square array, the four groups of plasma propellers are pairwise positioned on two sides of the unmanned aerial vehicle main body, any two adjacent plasma propellers are connected through a first connecting rod, and a second connecting rod is arranged between the two adjacent plasma propellers. The unmanned aerial vehicle body is vertically and fixedly connected with the first connecting rods on the two opposite sides through second connecting rods, and each plasma propeller comprises a 3D-printed honeycomb discharging plate, a discharging guide head, a supporting column and a plasma supporting frame. The unmanned aerial vehicle has the advantages of being low in mechanical fatigue, small in flight noise and high in energy utilization efficiency, the problems of noise pollution and combustion emission pollution of a traditional power propulsion unmanned aerial vehicle can be solved when the unmanned aerial vehicle is put into use, and the unmanned aerial vehicle is more suitable for military low-altitude reconnaissance activities and civil low-altitude operation.

Description

Technical Field

[0001] The utility model belongs to the technical field of power-propelled UAVs, and in particular relates to a 3D-printed plasma UAV device. Background Art

[0002] With the rapid development of high-tech, the research and development of UAVs has achieved rapid development and has been widely used in military and civilian fields. As a member of modern air military forces, military UAVs have the characteristics of no casualties, few restrictions on use, good concealment and high cost-effectiveness. However, traditional power-propelled UAVs also have problems such as low energy efficiency, heavy weight, noise pollution and short endurance. Utility Model Content

[0003] The main technical problem solved by the utility model is to provide a 3D printed plasma UAV device, which has the advantages of low mechanical fatigue, low flight noise and high energy utilization efficiency. Putting it into use will solve the problems of noise pollution and combustion emission pollution of traditional power-propelled UAVs, and is more suitable for military low-altitude reconnaissance activities and civilian low-altitude operations.

[0004] In order to solve the above technical problems, a technical solution adopted by the utility model is: to provide a 3D printed plasma UAV device, including a UAV body and a plasma thruster, wherein the plasma thrusters are provided in 4 groups and distributed in a square array, and the four groups of plasma thrusters are located in pairs on both sides of the UAV body, and any two adjacent plasma thrusters are connected by a first connecting rod, and the UAV body is vertically fixedly connected to the first connecting rods on two opposite sides by a second connecting rod, and the plasma thruster includes a 3D printed honeycomb discharge plate, a discharge guide, a support column and a plasma support frame, and the honeycomb discharge plate is provided in two groups in a circular structure, including a first honeycomb discharge plate and a second honeycomb discharge plate with the same structure and symmetrically arranged up and down, and the discharge guide is fixed on the honeycomb hole at the bottom of the first honeycomb discharge plate and faces the honeycomb hole of the second honeycomb discharge plate, and the plasma support frame is provided between the first honeycomb discharge plate and the second honeycomb discharge plate in an annular structure, and the upper part of the plasma support frame is connected and fixed to the bottom edge of the first honeycomb discharge plate through the first supporting column, and the lower part of the plasma support frame is connected and fixed to the top edge of the second honeycomb discharge plate through the second supporting column.

[0005] In a preferred embodiment of the present invention, the honeycomb holes of the first honeycomb discharge plate are provided with a whole row of discharge conductors distributed at intervals in the row direction.

[0006] In a preferred embodiment of the present invention, the discharge conductor is arranged in a Y-shaped structure.

[0007] In a preferred embodiment of the present invention, the two forks of the discharge conductor are respectively connected and fixed to two opposite corners of the hexagonal structure of the honeycomb hole.

[0008] In a preferred embodiment of the present invention, a plurality of the first support columns and the second support columns are symmetrically arranged and distributed in an annular shape with equal intervals.

[0009] In a preferred embodiment of the present invention, the diameter of the plasma support frame is larger than the diameter of the honeycomb discharge plate.

[0010] The beneficial effects of the utility model are as follows: the 3D printed plasma UAV device pointed out by the utility model has the advantages of low mechanical fatigue, low flight noise and high energy utilization efficiency. Putting it into use will solve the problems of noise pollution and combustion emission pollution of traditional power-propelled UAVs, and is more suitable for military low-altitude reconnaissance activities and civilian low-altitude operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative work, among which:

[0012] Figure 1 This is a stereogram of a preferred embodiment of a 3D printed plasma drone device of the utility model;

[0013] Figure 2 yes Figure 1 A front view of

[0014] Figure 3 yes Figure 1 Top view of the . DETAILED DESCRIPTION

[0015] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0016] See also Figure 1 Combination Figure 2-Figure 3 As shown, the embodiment of the utility model includes:

[0017] A 3D printed plasma drone device comprises a drone body 1 and a plasma thruster.

[0018] Among them, the plasma thrusters are provided in four groups and distributed in a square array, and the four groups of plasma thrusters are located in pairs on both sides of the UAV body 1, and any two adjacent plasma thrusters are connected by a first connecting rod 2. The UAV body 1 and the first connecting rods 2 on two opposite sides are vertically fixedly connected by a second connecting rod 3 to realize the overall layout of the UAV structure.

[0019] The plasma thruster comprises a 3D printed honeycomb discharge plate, a discharge guide 4, a support column and a plasma support frame 5. The weight of the structure itself can be optimized according to 3D printing.

[0020] The honeycomb discharge plate is provided in two groups in a circular structure, including a first honeycomb discharge plate 6 and a second honeycomb discharge plate 7 having the same structure and symmetrically arranged up and down. The honeycomb structure design is adopted, so that the plasma thruster can provide greater thrust.

[0021] The honeycomb holes of the first honeycomb discharge plate 6 are provided with a whole row of discharge conductors 4 at intervals in the column direction. The discharge conductors 4 are fixed on the honeycomb holes at the lower part of the first honeycomb discharge plate 6 and face the honeycomb holes of the second honeycomb discharge plate 7. Specifically, the discharge conductors 4 are arranged in a Y-shaped structure, and the two forks of the discharge conductors 4 are respectively connected and fixed to the two opposite corners of the hexagonal structure of the honeycomb holes. Air ionization is achieved by corona discharge of an asymmetric high-voltage electrode group, and ion acceleration is achieved by a high-voltage electric field, and momentum exchange occurs with air molecules, thereby generating lift for the vertical take-off and landing of the drone. This structural design can enhance its discharge capability and generate more powerful thrust.

[0022] The plasma support frame 5 is annularly arranged between the first honeycomb discharge plate 6 and the second honeycomb discharge plate 7. The diameter of the plasma support frame 5 is larger than the diameter of the honeycomb discharge plate to avoid affecting the middle discharge. Specifically, the first connecting rod 2 is connected and fixed to the side of the plasma support frame 5.

[0023] The upper part of the plasma support frame 5 is connected and fixed to the bottom edge of the first honeycomb discharge plate 6 through the first support column 8, and the lower part of the plasma support frame 5 is connected and fixed to the top edge of the second honeycomb discharge plate 7 through the second support column 9. The first support column 8 and the second support column 9 are symmetrically arranged in multiple and equally spaced annular distributions to ensure stable support.

[0024] The honeycomb structure itself has strong stability and can provide relatively stable support when the drone is working.

[0025] In summary, the 3D printed plasma UAV device pointed out in the utility model has the advantages of low mechanical fatigue, low flight noise and high energy utilization efficiency. Putting it into use will solve the problems of noise pollution and combustion emission pollution of traditional power-propelled UAVs, and is more suitable for military low-altitude reconnaissance activities and civilian low-altitude operations.

[0026] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the present invention specification, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A 3D printed plasma drone device, characterized in that: It comprises a drone body and a plasma thruster, wherein the plasma thrusters are provided in four groups and are distributed in a square array, and the four groups of plasma thrusters are located in pairs on both sides of the drone body, and any two adjacent plasma thrusters are connected by a first connecting rod, and the drone body is vertically fixedly connected to the first connecting rods on two opposite sides by a second connecting rod, and the plasma thruster comprises a 3D-printed honeycomb discharge plate, a discharge guide, a support column and a plasma support frame, and the honeycomb discharge plate is provided in two groups in a circular structure, including a first honeycomb discharge plate and a second honeycomb discharge plate with the same structure and symmetrically arranged up and down, the discharge guide is fixed on the honeycomb hole at the bottom of the first honeycomb discharge plate and faces the honeycomb hole of the second honeycomb discharge plate, and the plasma support frame is provided between the first honeycomb discharge plate and the second honeycomb discharge plate in an annular structure, and the upper part of the plasma support frame is connected and fixed to the bottom edge of the first honeycomb discharge plate by a first supporting column, and the lower part of the plasma support frame is connected and fixed to the top edge of the second honeycomb discharge plate by a second supporting column.

2. The 3D printed plasma drone device according to claim 1, characterized in that: The honeycomb holes of the first honeycomb discharge plate are provided with a whole row of discharge guides distributed at intervals in the row direction.

3. The 3D printed plasma drone device according to claim 2, characterized in that: The discharge guide head is arranged in a Y-shaped structure.

4. The 3D printed plasma drone device according to claim 3, characterized in that: The two forks of the discharge conductor are respectively connected and fixed to two opposite corners of the hexagonal structure of the honeycomb hole.

5. The 3D printed plasma drone device according to claim 1, characterized in that: The first supporting columns and the second supporting columns are symmetrically arranged in a plurality and are distributed in an annular shape with equal intervals.

6. The 3D printed plasma drone device according to claim 1, characterized in that: The diameter of the plasma support frame is larger than the diameter of the honeycomb discharge plate.

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