Electro-deformation driver and flapping wing air vehicle

Abstract

The utility model discloses an electro-deformation driver which comprises an angle frame, the angle frame comprises a C-shaped frame and a connecting frame, the connecting frame is installed on the rear end face of the C-shaped frame, the connecting frame is fixedly connected with the C-shaped frame, parallel plate electric field sets are symmetrically installed on the two sides of the C-shaped frame, and the parallel plate electric field sets are fixedly connected with the C-shaped frame in an inserted mode. The two parallel plate electric field groups are symmetrically mounted on the aircraft through the angle frame, and the flapping wings of the aircraft are arranged between the parallel plate electric field groups; the flapping wings can be driven to flap between the top electric field polar plate and the bottom electric field polar plate in a reciprocating manner through the interaction of the conductive film parts of the flapping wings and the electric field force on the parallel plate electric field group, the flapping deformation of the flapping wings is completely formed by the driving of the electric field force, and a mechanical transmission structure is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of an electrodeformation driver and a flapping-wing aircraft, in particular to an electrodeformation driver and a flapping-wing aircraft. Background Art

[0002] Flapping-wing aircraft refers to an aircraft that flaps its wings up and down like a bird to generate a reaction force in the air as lift and forward force. Flapping-wing aircraft have the advantages of moderate size, easy to carry, strong flexibility, and the ability to take off and land vertically, so they have very important and wide applications in both civil and defense fields.

[0003] The existing Chinese patent with announcement number CN212313871U discloses a flapping-wing aircraft, including an aircraft body and a flexible adjustment structure, wherein the flexible adjustment structure has a first end and a second end relative to each other, the first end is connected to the aircraft body, and the second end is a free end, and the center of gravity of the flexible adjustment structure is located behind the center of gravity of the aircraft body.

[0004] With regard to the above-mentioned related technologies, it is found that most of the existing flapping-wing aircraft use mechanical transmission to drive the flapping wings to flap, and then achieve flight operations by flapping the wings to beat the air. However, in order to reduce the overall weight of the aircraft, a more sturdy mechanical transmission structure is often not adopted. After long-term use, wear and deformation may easily occur, affecting the normal use of the aircraft. Utility Model Content

[0005] The present application provides an electrodeformable actuator and a flapping-wing aircraft, which are used to solve the problems raised in the background technology.

[0006] The utility model is achieved in this way:

[0007] An electrodeformation actuator comprises an angle frame, wherein the angle frame comprises a C-shaped frame and a connecting frame, wherein the connecting frame is mounted on the rear end surface of the C-shaped frame and is fixedly connected to the C-shaped frame, and parallel plate electric field groups are symmetrically mounted on both sides of the C-shaped frame and are plugged and fixed to the C-shaped frame.

[0008] Furthermore, the C-shaped frame includes a top seat, a middle pole and a bottom seat, wherein the top seat and the bottom seat are respectively arranged at the upper and lower ends of the middle pole, and the rear ends of the top seat and the bottom seat are fixedly connected to the middle pole.

[0009] Furthermore, the parallel plate electric field group includes a top electric field plate and a bottom electric field plate, and the bottom electric field plate is arranged in parallel at the lower end of the top electric field plate.

[0010] A flapping-wing aircraft comprises a light frame, a movable swing arm and a flapping wing, wherein the movable swing arm is symmetrically mounted on the head of the light frame, and the lower end of the movable swing arm is rotatably connected to the light frame, and the flapping wing is mounted on the head of the movable swing arm, and the flapping wing is fixedly connected to the movable swing arm

[0011] Furthermore, the lightweight frame includes a horizontal bracket and a head frame for mounting a movable rocker arm, the head frame is mounted on the head of the horizontal bracket, and the head frame is fixedly connected to the horizontal bracket.

[0012] Furthermore, the flapping wing includes a conductive film portion and an extended wing, one end of the conductive film portion is fixed on the movable rocker, and the extended wing is fixedly mounted on the other end of the conductive film portion.

[0013] Furthermore, a tail wing is fixedly mounted on the end of the horizontal bracket, and a bracket is also fixedly mounted on the middle of the horizontal bracket.

[0014] Compared with the prior art, the beneficial effects of the utility model are as follows: the utility model uses an angle frame to symmetrically install two sets of parallel plate electric field groups on the aircraft, and sets the flapping wings of the aircraft between the parallel plate electric field groups, and drives the flapping wings to flap back and forth between the top electric field plate and the bottom electric field plate through the interaction between the conductive film part of the flapping wings and the electric field force on the parallel plate electric field groups. The flapping deformation of the flapping wings is completely driven by the electric field force, which reduces the mechanical transmission structure and increases the overall durability of the aircraft. In addition, the electrodeformation driver is used as the power of the aircraft, which has the advantages of rapid driving and stable flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solution of the implementation mode of the utility model, the drawings required for use in the implementation mode will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is a schematic diagram of the overall structure in an embodiment of the utility model;

[0017] Figure 2 yes Figure 1 A top view of the device shown without the angle bracket and parallel plate electric field assembly installed;

[0018] Figure 3 yes Figure 1 A three-dimensional diagram of the angle frame and the parallel plate shown in FIG.

[0019] Figure 4 yes Figure 3 a front view of the device shown;

[0020] Figure 5 yes Figure 3 A top view of the device shown.

[0021] In the figure: 1. Angle frame; 11. C-shaped frame; 111. Top seat; 112. Middle pole; 113. Bottom seat; 12. Connecting frame; 2. Parallel plate electric field group; 21. Top electric field plate; 22. Bottom electric field plate; 3. Lightweight frame; 31. Horizontal bracket; 311. Tail wing; 312. Bracket; 32. Head frame; 4. Movable rocker arm; 5. Flapping wing; 51. Conductive film part; 52. Extended wing. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model. Therefore, the following detailed description of the embodiments of the utility model provided in the drawings is not intended to limit the scope of the utility model for which protection is claimed, but merely represents selected embodiments of the utility model.

[0023] Reference Figure 2 , Figure 3 and Figure 4 As shown, an electrodeformation actuator includes an angle frame 1, the angle frame 1 includes a C-shaped frame 11 and a connecting frame 12, the connecting frame 12 is installed on the rear end surface of the C-shaped frame 11, and the connecting frame 12 is fixedly connected to the C-shaped frame 11, and parallel plate electric field groups 2 are symmetrically installed on both sides of the C-shaped frame 11, and the parallel plate electric field group 2 is plugged and fixed to the C-shaped frame 11. The parallel plate electric field group 2 includes a top electric field plate 21 and a bottom electric field plate 22, and the bottom electric field plate 22 is arranged in parallel at the lower end of the top electric field plate 21. The structural setting of the angle frame 1 ensures that the parallel plate electric field group 2 can be installed through the C-shaped frame 11 for use. At the same time, by fixing the connecting frame 12 on the C-shaped frame 11, it is convenient to connect with the outside through the connecting frame 12 to ensure the stable use of the angle frame 1. At the same time, through the structural setting of the parallel plate electric field group 2, when it is convenient to use, an external power supply can be used through a pair of parallel top electric field plates 21 and bottom electric field plates 22 to provide an electric field (the top electric field plate 21 and the bottom electric field plate 22 are used as a positive plate and a negative plate respectively), thereby providing an electric field force to a conductive object placed between the top electric field plate 21 and the bottom electric field plate 22.

[0024] Reference Figure 2 , Figure 3 and Figure 4 As shown, the C-shaped frame 11 includes a top seat 111, a middle rod 112 and a bottom seat 113. The top seat 111 and the bottom seat 113 are respectively arranged at the upper and lower ends of the middle rod 112, and the rear ends of the top seat 111 and the bottom seat 113 are fixedly connected to the middle rod 112. The structural setting of the C-shaped frame 11 ensures that the top seat 111 and the bottom seat 113 can be connected and fixed to each other through the middle rod 112, so that the electric field plates can be installed respectively through the top seat 111 and the bottom seat 113, ensuring that the electric field plates installed on the top seat 111 and the bottom seat 113 can remain in a parallel state.

[0025] Reference Figure 1 and Figure 2 As shown, a flapping-wing aircraft comprises a lightweight frame 3, a movable swing arm 4 and a flapping wing 5. The movable swing arm 4 is symmetrically mounted on the head of the lightweight frame 3, and the lower end of the movable swing arm 4 is rotatably connected to the lightweight frame 3. The flapping wing 5 is mounted on the head of the movable swing arm 4, and the flapping wing 5 is fixedly connected to the movable swing arm 4. The lightweight frame 3 is provided as the overall frame structure of the aircraft, and the movable swing arm 4 is installed on the lightweight frame 3, so that the flapping wing 5 can be supported and installed by the movable swing arm 4, and the flapping wing 5 can be flapped on the lightweight frame 3 by the movable swing arm 4 during easy use.

[0026] Reference Figure 1 and Figure 2 As shown, the lightweight frame 3 includes a horizontal bracket 31 and a head frame 32 for mounting the movable swing arm 4, the head frame 32 is mounted at the head of the horizontal bracket 31, and the head frame 32 is fixedly connected to the horizontal bracket 31. A tail 311 is fixedly mounted at the end of the horizontal bracket 31, and a bracket 312 is also fixedly mounted in the middle of the horizontal bracket 31. The structural setting of the lightweight frame 3 ensures that the head frame 32 is fixedly mounted on the horizontal bracket 31, and the movable swing arm 4 is conveniently positioned and mounted through the head frame 32, so that the movable swing arm 4 can be easily swung on the head frame 32 for use. At the same time, the setting of the tail 311 assists in increasing the stability during flight, and the setting of the bracket 312 facilitates the fixed installation of the angle frame 1.

[0027] Reference Figure 1 and Figure 2As shown, the flapping wing 5 includes a conductive film portion 51 and an extended wing 52 . One end of the conductive film portion 51 is fixed on the movable swing rod 4 , and the extended wing 52 is fixedly mounted on the other end of the conductive film portion 51 . The structure of the flapping wing 5 is set to ensure that the extended wing 52 is installed through the conductive film part 51. When in use, the conductive film part 51 is set between the top electric field plate 21 and the bottom electric field plate 22. When the top electric field plate 21 and the bottom electric field plate 22 are energized, they will bend under the action of the electric field force. If the conductive film part 51 itself carries a positive charge, it will be attracted by the negative plate in the electric field and deflect toward the negative plate. When it contacts the negative plate, the charge exchange will be completed. At this time, it will change from carrying a positive charge to carrying a negative charge, so it will be attracted by the positive plate and deflect toward the positive plate again, and then the charge exchange will be carried out. Such reciprocating movement will form a fanning form of mechanical deformation, which can ensure that the conductive film part 51 can flap back and forth between the top electric field plate 21 and the bottom electric field plate 22, and the area of ​​the conductive film part 51 flapping the air is increased by setting the extended wing 52, thereby increasing the flight ability.

[0028] Working principle: When installing the aircraft, first combine the angle frame and the parallel plate electric field group together. After fixing the parallel plate electric field group on the angle frame, the C-shaped frame can be installed on the head frame of the lightweight frame, and then the connecting frame is placed on the bracket of the lightweight frame. Finally, the connecting frame and the bracket are fixed to each other by bolts. When it is needed to fly, it is necessary to install a power supply battery and a corresponding control system on the lightweight frame to power the parallel plate electric field group to ensure that the flapping wings can be flapped under the action of the electric field force of the parallel plate electric field group.

[0029] The above description is only the preferred implementation of the utility model, and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. An electrodeformation actuator, comprising an angle frame (1), characterized in that: The angle frame (1) comprises a C-shaped frame (11) and a connecting frame (12); the connecting frame (12) is mounted on the rear end surface of the C-shaped frame (11), and the connecting frame (12) is fixedly connected to the C-shaped frame (11); parallel plate electric field groups (2) are symmetrically mounted on both sides of the C-shaped frame (11), and the parallel plate electric field groups (2) are plugged and fixed to the C-shaped frame (11).

2. The electrodeformable actuator according to claim 1, characterized in that: The C-shaped frame (11) comprises a top seat (111), a middle rod (112) and a bottom seat (113); the top seat (111) and the bottom seat (113) are respectively arranged at the upper and lower ends of the middle rod (112); and the rear ends of the top seat (111) and the bottom seat (113) are fixedly connected to the middle rod (112).

3. The electrodeformable actuator according to claim 2, characterized in that: The parallel plate electric field group (2) comprises a top electric field plate (21) and a bottom electric field plate (22), wherein the bottom electric field plate (22) is arranged in parallel at the lower end of the top electric field plate (21).

4. A flapping-wing aircraft, comprising the electrodeformable actuator according to any one of claims 1 to 3, characterized in that: The invention also comprises a lightweight frame (3), a movable swing arm (4) and a flapping wing (5), wherein the movable swing arm (4) is symmetrically mounted on the head of the lightweight frame (3), and the lower end of the movable swing arm (4) is rotatably connected to the lightweight frame (3), and the flapping wing (5) is mounted on the head of the movable swing arm (4), and the flapping wing (5) is fixedly connected to the movable swing arm (4).

5. A flapping-wing aircraft according to claim 4, characterized in that: The lightweight frame (3) comprises a horizontal support (31) and a head frame (32) for mounting a movable swing arm (4); the head frame (32) is mounted on the head of the horizontal support (31), and the head frame (32) is fixedly connected to the horizontal support (31).

6. A flapping-wing aircraft according to claim 5, characterized in that: The flapping wing (5) comprises a conductive film portion (51) and an extended wing (52); one end of the conductive film portion (51) is fixed on the movable swing rod (4), and the extended wing (52) is fixedly mounted on the other end of the conductive film portion (51).

7. A flapping-wing aircraft according to claim 6, characterized in that: A tail wing (311) is fixedly mounted at the end of the horizontal support (31), and a bracket (312) is also fixedly mounted at the middle of the horizontal support (31).

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