Unmanned aerial vehicle defense system

Abstract

The utility model discloses an unmanned aerial vehicle defense system which comprises a main body unit which comprises a fuselage, a buffer air bag is arranged on the fuselage, a protective cover is fixedly arranged at the upper end of the fuselage, and a supporting rod is arranged at the lower end of the fuselage; the working unit comprises a connector clamped on the fuselage, a starting component is arranged on the fuselage, an adjusting component is arranged on the starting component, a fixing component is arranged on the connector, and a rotor wing is arranged on the adjusting component. And then worm wheels on the two sides are driven to rotate, then a connecting rod is driven to rotate synchronously, then a second bevel gear is driven to rotate synchronously through a first bevel gear, then an adjusting rod can be driven to adjust the angle, and the unmanned aerial vehicle is prevented from colliding with a wall and the like.

Description

TECHNICAL FIELD

[0001] The utility model relates to an unmanned plane technical field especially relates to an unmanned plane defense system. BACKGROUND

[0002] The unmanned plane is called "unmanned plane" for short, and the English abbreviation is "UAV", which is a no -person plane controlled by radio remote control equipment and self -provided program control device or by on -board computer completely or intermittently.

[0003] The existing unmanned plane lacks the corresponding protective device when using, and the body is damaged due to accidents in actual use, and when flying in narrow places, improper operation can easily cause the wing to be damaged due to collision. UTILITY MODEL CONTENT

[0004] This part is to outline some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this part and the abstract of the specification and the utility model name to avoid obscuring the purpose of this part, the abstract of the specification and the utility model name, and such simplifications or omissions cannot be used to limit the scope of the utility model.

[0005] In view of the above problems existing in the prior art unmanned plane defense system, the utility model is proposed.

[0006] Therefore, the utility model aims at providing an unmanned plane defense system, which solves the problem that the existing unmanned plane lacks the corresponding protective device when using, and the body is damaged due to accidents in actual use, and when flying in narrow places, improper operation can easily cause the wing to be damaged due to collision.

[0007] To solve the above technical problems, the utility model provides the following technical scheme: an unmanned plane defense system, comprising:

[0008] The main unit comprises a fuselage, a buffer air bag is arranged on the fuselage, a protective cover is fixedly arranged on the upper end of the fuselage, and a supporting rod is arranged on the lower end of the fuselage.

[0009] The working unit comprises a connector clamped on the fuselage, a starting member is arranged on the fuselage, an adjusting member is arranged on the starting member, a fixing member is arranged on the connector, and a rotor is arranged on the adjusting member.

[0010] As a preferred scheme of the unmanned plane defense system, the starting member comprises a mounting groove arranged in the fuselage, a motor is fixedly arranged in the connector, a worm is fixedly arranged on the output end of the motor, a mount is fixedly arranged in the mounting groove, and a worm wheel is rotatably arranged on the mount.

[0011] As a preferred scheme of the unmanned aerial vehicle defense system, the worm is engaged with the worm wheel, and one end of the worm is rotationally connected with the fuselage.

[0012] As a preferred scheme of the unmanned aerial vehicle defense system, the fuselage is provided with a placing groove, a connecting rod is rotationally arranged on the mounting device, a first bevel gear is fixedly arranged at one end of the connecting rod, a second bevel gear is rotationally arranged on the placing groove, an adjusting rod is fixedly arranged at a lower end of the second bevel gear, and an adjusting groove is formed in the fuselage.

[0013] As a preferred scheme of the unmanned aerial vehicle defense system, the fixing member comprises a clamping groove formed in the fuselage, a rectangular block is fixedly arranged on the connector, a movement groove is formed in the rectangular block, a connecting spring is fixedly arranged on the movement groove, and a clamping block is fixedly arranged on the connecting spring.

[0014] As a preferred scheme of the unmanned aerial vehicle defense system, the first bevel gear is engaged with the second bevel gear, and the adjusting rod is slidably connected with the adjusting groove.

[0015] The beneficial effects of the present application are as follows:

[0016] When the flight space is relatively small, the motor is turned on, the motor drives the worm to rotate, and then drives the two side worm wheels to rotate, and then drives the connecting rod to rotate synchronously, and then drives the second bevel gear to rotate synchronously through the first bevel gear, and then drives the adjusting rod to adjust the angle, so as to avoid the collision between the unmanned aerial vehicle and the wall. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical scheme of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiment description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor. Among them:

[0018] Figure 1 It is a front overall structure schematic diagram of the unmanned aerial vehicle defense system proposed by the present application;

[0019] Figure 2 It is a starting member structure schematic diagram;

[0020] Figure 3 It is an adjusting member structure schematic diagram;

[0021] Figure 4 It is a fuselage cross-section structure schematic diagram;

[0022] Figure 5 For Figure 4 The enlarged structure schematic view is shown at A in the figure.

[0023] In the figure: 100, main unit; 101, fuselage; 102, buffer air bag; 103, protective cover; 104, support rod; 200, working unit; 201, connector; 202, starting component; 202a, mounting groove; 202b, motor; 202c, mount; 202d, worm; 202e, worm wheel; 203, adjusting component; 203a, placing groove; 203b, connecting rod; 203c, first bevel gear; 203d, second bevel gear; 203e, adjusting rod; 203f, adjusting groove; 204, fixing component; 204a, clamping groove; 204b, rectangular block; 204c, movement groove; 204d, connecting spring; 204e, clamping block; 205, rotor. DETAILED DESCRIPTION

[0024] In order to make the above-mentioned purposes, features and advantages of the present application more apparent and understandable, the specific embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0025] In the following description, a large number of specific details are set forth in order to facilitate a full understanding of the present application, but the present application can also be implemented in other ways different from those described herein, and those skilled in the art can make similar generalizations without departing from the connotation of the present application, therefore the present application is not limited by the specific embodiments disclosed below.

[0026] Secondly, the "one embodiment" or "embodiment" referred to herein means that the specific features, structures or characteristics can be included in at least one implementation of the present application. In different places in this specification, "in one embodiment" does not mean the same embodiment, nor is it an independent or alternative embodiment that excludes other embodiments.

[0027] Thirdly, the present application is described in detail in conjunction with the schematic diagram, and in order to facilitate the description, the cross-sectional view of the device structure will be partially enlarged without the general proportion, and the schematic diagram is only an example, which should not limit the scope of protection of the present application. In addition, the three-dimensional spatial dimensions of length, width and depth should be included in actual production.

[0028] With reference to Figure 1 -5, the present application provides a kind of unmanned aerial vehicle defense system, comprising:

[0029] The main unit 100 comprises a machine body 101, a buffer air bag 102 is arranged on the machine body 101, a protective cover 103 is fixedly arranged on the upper end of the machine body 101, and a supporting rod 104 is arranged on the lower end of the machine body 101;

[0030] The working unit 200 comprises a connector 201 clamped on the machine body 101, a starting member 202 is arranged on the machine body 101, an adjusting member 203 is arranged on the starting member 202, a fixing member 204 is arranged on the connector 201, a rotor 205 is arranged on the adjusting member 203, the adjusting member 203 can be adjusted through the starting member 202, so that the unmanned aerial vehicle is prevented from colliding with the wall.

[0031] The starting member 202 comprises an installation groove 202a arranged in the machine body 101, a motor 202b is fixedly arranged in the connector 201, a worm 202d is fixedly arranged at the output end of the motor 202b, an installer 202c is fixedly arranged in the installation groove 202a, a worm wheel 202e is rotatably arranged on the installer 202c, the motor 202b is turned on, the motor 202b drives the worm 202d to rotate, and then the worm wheels 202e on the two sides are rotated.

[0032] Further, the worm 202d is engaged with the worm wheel 202e, and one end of the worm 202d is rotatably connected with the machine body 101.

[0033] Further, a placing groove 203a is arranged in the machine body 101, a connecting rod 203b is rotatably arranged on the installer 202c, a first bevel gear 203c is fixedly arranged at one end of the connecting rod 203b, a second bevel gear 203d is rotatably arranged on the placing groove 203a, an adjusting rod 203e is fixedly arranged at the lower end of the second bevel gear 203d, and an adjusting groove 203f is arranged on the machine body 101, and the connecting rod 203b is rotated under the action of the worm wheel 202e.

[0034] Further, the fixing member 204 comprises a clamping groove 204a arranged on the machine body 101, a rectangular block 204b is fixedly arranged on the connector 201, a movement groove 204c is arranged in the rectangular block 204b, a connecting spring 204d is fixedly arranged on the movement groove 204c, and a clamping block 204e is fixedly arranged on the connecting spring 204d.

[0035] Further, the first bevel gear 203c is engaged with the second bevel gear 203d, and the adjusting rod 203e is slidably connected with the adjusting groove 203f.

[0036] During use, the clamping block 204e is pressed so that the clamping block 204e is retracted into the movement groove 204c, then the connector 201 is removed, a camera or other device can be installed on the connector 201, or the corresponding motor 202b is replaced according to the actual endurance requirement; when in a relatively narrow flight space, the motor 202b is turned on, the motor 202b drives the worm 202d to rotate, then the worm gears 202e on both sides are driven to rotate, then the connecting rod 203b is synchronously rotated, then the first bevel gear 203c drives the second bevel gear 203d to synchronously rotate, then the adjusting rod 203e can be driven to adjust the angle, so that the unmanned aerial vehicle is prevented from colliding with a wall or the like.

[0037] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, not to limit it. Although the present application has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the technical solutions of the present application can be modified or replaced equivalently without departing from the spirit and scope of the technical solutions of the present application, which should be covered in the scope of the claims of the present application.

Claims

1. A drone defense system, characterized by: Include: The main unit (100) includes the fuselage (101), the fuselage (101) is provided with a buffer air bag (102), the fuselage (101) upper end is fixedly provided with a protective cover (103), the fuselage (101) lower end is provided with a support rod (104); The working unit (200) includes a connector (201) clamped on the fuselage (101), the fuselage (101) is provided with a starting member (202), the starting member (202) is provided with an adjusting member (203), the connector (201) is provided with a fixing member (204), the adjusting member (203) is provided with a rotor (205).

2. The drone defense system of claim 1, wherein: The starting member (202) includes a mounting groove (202a) opened in the fuselage (101), the connector (201) is fixedly provided with a motor (202b), the motor (202b) output end is fixedly provided with a worm (202d), the mounting groove (202a) is fixedly provided with a mounting device (202c), the mounting device (202c) is rotatably provided with a worm wheel (202e).

3. The drone defense system of claim 2, wherein: The worm (202d) is engaged with the worm wheel (202e), and one end of the worm (202d) is rotatably connected with the fuselage (101).

4. The drone defense system of claim 2, wherein: The fuselage (101) is provided with a placing groove (203a), the mounting device (202c) is rotatably provided with a connecting rod (203b), one end of the connecting rod (203b) is fixedly provided with a first bevel gear (203c), the placing groove (203a) is rotatably provided with a second bevel gear (203d), the second bevel gear (203d) lower end is fixedly provided with an adjusting rod (203e), the fuselage (101) is provided with an adjusting groove (203f).

5. The drone defense system of claim 1, wherein: The fixing member (204) includes a clamping groove (204a) opened in the fuselage (101), the connector (201) is fixedly provided with a rectangular block (204b), the rectangular block (204b) is provided with a movement groove (204c), the movement groove (204c) is fixedly provided with a connecting spring (204d), the connecting spring (204d) is fixedly provided with a clamping block (204e).

6. The drone defense system of claim 4, wherein: The first bevel gear (203c) is engaged with the second bevel gear (203d), and the adjusting rod (203e) is slidably connected with the adjusting groove (203f).

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