CN117902074A

CN117902074A - Unmanned aircraft

Info

Publication number: CN117902074A
Application number: CN202410317057.8A
Authority: CN
Inventors: 张敏
Original assignee: Shenyang Xinyu Network Technology Co ltd
Current assignee: Shenyang Xinyu Network Technology Co ltd
Priority date: 2024-03-20
Filing date: 2024-03-20
Publication date: 2024-04-19
Anticipated expiration: 2044-03-20
Also published as: CN117902074B

Abstract

The invention discloses an unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises an aerial vehicle component, wherein the aerial vehicle component comprises a machine body, a power component is arranged in the machine body, protection components are arranged at the left side, the right side and the front end of the machine body, a first rotating shaft is arranged at the center position of a first connecting block, a rotating rod is sleeved on the outer surface of the first rotating shaft, a telescopic block is arranged on a supporting seat, a second connecting block is arranged on the front surface of the telescopic block, and a second rotating shaft is arranged at the center position of the second connecting block. According to the invention, the protection assembly is designed, so that the aircraft is effectively prevented from being collided with the aircraft in the flight process, the aircraft falls, the protection plate descends synchronously while the aircraft falls, the aircraft is better protected by supporting the aircraft when falling to the ground, the buffer assembly is designed, the aircraft is effectively buffered when falling to the ground, the contact area between the aircraft and the ground is increased, and the stabilizing effect is enhanced.

Description

Unmanned aircraft

Technical Field

The invention relates to the technical field of unmanned aircrafts, in particular to an unmanned aircraft.

Background

Unmanned aerial vehicles are simply referred to as "unmanned aerial vehicles" and are unmanned aerial vehicles that are operated by means of a radio remote control device and a self-contained program control device. Unmanned aircraft tend to be more suitable for tasks that are too "fooled, messy, or dangerous" than manned aircraft. Unmanned aerial vehicles can be classified into military and civilian applications according to the field of application. For military purposes, unmanned aerial vehicles are classified into reconnaissance and drones. In civil aspect, the unmanned aerial vehicle and the industrial application are really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer shooting, express delivery transportation, disaster relief, wild animal observation, infectious disease monitoring, mapping, news reporting, electric power inspection, disaster relief, video shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and the developed countries are also actively expanding the application of industries and developing unmanned aerial vehicle technologies.

The most widely used many rotor unmanned aerial vehicle among the civilian unmanned aerial vehicle, many rotor unmanned aerial vehicle fly time screw high-speed rotation, bump with the external world very easily and lead to out of control, crash or even hurt the people, especially under the comparatively narrow, complex circumstances of environment, unmanned aerial vehicle hardly gets into, even get into and receive the crashproof structure that bumps and crash extremely easily, there are some on the present market to be used for unmanned aerial vehicle, but this kind of structure is bulky, the weight is heavier, the mobility of unmanned aerial vehicle has been influenced, the operation is complicated when some crashproof structure installs to unmanned aerial vehicle, very inconvenient when leading to the use, simultaneously can not fine steady landing when unmanned aerial vehicle falls.

Disclosure of Invention

Based on this, it is an object of the present invention to provide an unmanned aerial vehicle to solve the technical problems set forth in the background above.

In order to achieve the above purpose, the present invention provides the following technical solutions: the unmanned aerial vehicle comprises an aerial vehicle component, wherein the aerial vehicle component comprises a machine body, a power component is arranged in the machine body, protection components are arranged at the left side, the right side and the front end of the machine body, and a buffer component is arranged at the top end of the protection components; the protection subassembly is including being fixed in the backup pad of fuselage left and right sides and front end, backup pad top partial right side is equipped with two sets of supporting shoe, the supporting shoe left side is equipped with the telescopic link, the telescopic link surface cover is equipped with a spring, and the telescopic link top is equipped with the guard plate, guard plate right side central point puts and is equipped with first line rope, and guard plate left side central point puts and be equipped with the second cotton rope, the guard plate bottom is equipped with the first pivot that changes second cotton rope extending direction, first pivot top is equipped with the second pivot that changes second cotton rope extending direction, first cotton rope and second cotton rope right side tip are equipped with the winding axle, the buffer unit is including being fixed in the fixed block on guard plate top, the fixed block top is equipped with the second spring, and the fixed block front surface is equipped with first connecting block, first connecting block central point puts and is equipped with a axis of rotation, first axis of rotation surface cover is equipped with the dwang, the second spring top is equipped with the supporting seat, inside being equipped with the telescopic block of supporting seat, the telescopic block front surface is equipped with the second connecting block, second connecting block central point put and is equipped with the axis of rotation.

Preferably, the four corners of the top end of the machine body are provided with shaft bodies, the top end of the shaft bodies is provided with wings, and the bottom end of the machine body is provided with a camera.

Preferably, the power component comprises a double-shaft motor, a first base rod is arranged on two sides of an output end of the double-shaft motor, two groups of first bevel gears are arranged on the left side of the double-shaft motor, a group of first bevel gears are arranged on the right side of the double-shaft motor, two identical bevel gears are arranged on the first bevel gears, and three groups of second bevel gears are fixedly connected to the winding shaft.

Preferably, the protection component is provided with three groups, the left side of the support plate is provided with a second base rod, the second base rod penetrates through the lower end of the front surface of the protection plate and is rotationally connected with the lower end of the front surface of the protection plate, and the left side of the protection plate is arc-shaped.

Preferably, the right side of the protection plate is in contact relation with the two groups of telescopic rods and the spring I, and the telescopic rods and the spring I are fixedly connected to the supporting blocks.

Preferably, the surface of the winding shaft is provided with a clamping groove which is matched with the first rope and the second rope, the end part of the first rope is fixedly connected to the right side of the protection plate, and the end part of the second rope is fixedly connected to the left side of the protection plate.

Preferably, one end of the rotating rod is rotationally connected with the first rotating shaft, the other end of the rotating rod is rotationally connected with the second rotating shaft, the length of the second connecting block is longer than that of the first connecting block, and the first rotating shaft and the second rotating shaft are both arranged at the central positions of the first connecting block and the second connecting block.

Preferably, the supporting seat is in sliding connection with the telescopic block, and the front surface of the telescopic block is provided with three groups of second connecting blocks which are fixedly connected with the telescopic block.

In summary, the invention has the following advantages:

according to the invention, the protection assembly is designed, and the supporting plate, the second base rod, the supporting block, the telescopic rod, the first spring, the protection plate, the first rope, the second rope, the first rotating shaft, the second rotating shaft and the winding shaft are matched with each other in the protection assembly, so that the aircraft is effectively prevented from being collided with the external objects in the flight process, and the aircraft is enabled to fall.

According to the invention, the buffer assembly is designed, and the fixed block, the first connecting block, the second connecting block, the first rotating shaft, the second spring, the rotating rod, the supporting seat, the telescopic block, the second connecting block and the second rotating shaft in the buffer assembly are mutually matched, so that the aircraft can play a role in buffering when falling to the ground, the contact area between the aircraft and the ground is increased, and the stabilizing effect is enhanced;

According to the invention, the protection assembly is designed, and the supporting plate, the second base rod, the supporting block, the telescopic rod, the first spring, the protection plate, the first rope, the second rope, the first rotating shaft, the second rotating shaft and the winding shaft are matched with each other in the protection assembly, so that the protection plate descends synchronously when the aircraft lands, the supporting effect is achieved on the aircraft during landing, and the aircraft is better protected.

Drawings

FIG. 1 is a schematic view of an aircraft assembly of the present invention;

FIG. 2 is a front view of an aircraft assembly of the present invention;

FIG. 3 is an enlarged view of a first shaft of the present invention;

FIG. 4 is a top view of the power assembly of the present invention;

FIG. 5 is a schematic view of a protective assembly according to the present invention;

FIG. 6 is a schematic diagram of a cushioning assembly according to the present invention.

In the figure: 100. an aircraft assembly; 110. a body; 120. a shaft body; 130. a wing; 140. a camera;

200. a power assembly; 210. a biaxial motor; 220. a first base rod; 230. a first helical gear; 240. a helical gear II;

300. A protective assembly; 310. a support plate; 311. a second base rod; 320. a support block; 330. a telescopic rod; 340. a first spring; 350. a protection plate; 360. a first cord; 370. a second cord; 371. a first rotating shaft; 372. a second rotating shaft; 380. a winding shaft;

400. a buffer assembly; 410. a fixed block; 411. a first connection block; 412. a first rotating shaft; 420. a second spring; 430. a rotating lever; 440. a support base; 450. a telescopic block; 451. a second connection block; 452. and a second rotating shaft.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.

Hereinafter, an embodiment of the present invention will be described in accordance with its entire structure.

1-6, The unmanned aerial vehicle comprises an aerial vehicle component 100, wherein the aerial vehicle component 100 comprises a machine body 110, a power component 200 is arranged in the machine body 110, protective components 300 are arranged on the left side, the right side and the front end of the machine body 110, and a buffer component 400 is arranged at the top end of the protective components 300; the protection component 300 comprises a supporting plate 310 fixed on the left and right sides and the front end of the machine body 110, two groups of supporting blocks 320 are arranged on the right side of the top end of the supporting plate 310, a telescopic rod 330 is arranged on the left side of the supporting block 320, a first spring 340 is sleeved on the outer surface of the telescopic rod 330, a protection plate 350 is arranged on the top end of the telescopic rod 330, a first rope 360 is arranged at the center position of the right side of the protection plate 350, a second rope 370 is arranged at the center position of the left side of the protection plate 350, a first rotating shaft 371 for changing the extending direction of the second rope 370 is arranged at the bottom end of the protection plate 350, a second rotating shaft 372 for changing the extending direction of the second rope 370 is arranged above the first rotating shaft 371, the right side end of first cotton rope 360 and second cotton rope 370 is equipped with take-up spool 380, buffer module 400 is including being fixed in fixed block 410 on guard plate 350 top, fixed block 410 top is equipped with second spring 420, and fixed block 410 front surface is equipped with first connecting block 411, first connecting block 411 central point puts and is equipped with rotation axis 412, rotation axis 412 surface cover is equipped with dwang 430, second spring 420 top is equipped with supporting seat 440, the inside telescopic block 450 that is equipped with of supporting seat 440, telescopic block 450 front surface is equipped with second connecting block 451, second connecting block 451 central point put and is equipped with No. two rotation axis 452.

Through starting the aircraft, make wing 130 high-speed rotation, drive the aircraft flight, through starting biax motor 210, drive first basic pole 220 rotation, first basic pole 220 drives first helical gear 230 rotation, first helical gear 230 drives No. two helical gear 240 rotations, no. two helical gear 240 drives the receipts spool 380 rotation, make the shrink of first cotton rope 360 pull guard plate 350 laminate in spring 340, when in the flight, the foreign matter bumps guard plate 350, through the effect of spring 340 and telescopic link 330 down, effectually with the power buffering, prevent the aircraft roll over, thereby make it fall, when the aircraft drops, wing 130 rotational speed becomes low, biax motor 210 reversal makes second cotton rope 370 atress, through first pivot 371 and second pivot 372 pulling guard plate 350, make guard plate 350 rotate through No. two basic poles 311, keep the vertical state, play the effect of support to the aircraft when falling to the ground, better protection aircraft, make support seat 440 atress compress second spring 420 simultaneously, through the effect of rolling shaft 412 and second number rotation axis 452 pull down, the effect of rolling link 430 and the effective floor area of the aircraft is increased when the telescopic link 430 is fallen.

Referring to fig. 1 and 2, the top end of the body 110 is provided with a shaft 120 at four corners, the top end of the shaft 120 is provided with a wing 130, and the bottom end of the body 110 is provided with a camera 140.

The high-speed rotation of the wing 130 can effectively drive the aircraft assembly 100 to fly, and the camera 140 can better observe the surrounding conditions of the aircraft in the flying process, so that the aircraft can be better controlled.

The power assembly 200 comprises a double-shaft motor 210, wherein a first base rod 220 is arranged on two sides of an output end of the double-shaft motor 210, two groups of first bevel gears 230 are arranged on the left side of the double-shaft motor 210, a group of first bevel gears 230 are arranged on the right side of the double-shaft motor 210, a second bevel gear 240 which is matched with the first bevel gears 230 is arranged on the first bevel gears 230, and three groups of second bevel gears 240 are arranged and fixedly connected to a winding shaft 380.

The three groups of protection components 300 are driven to synchronously operate by the double-shaft motor 210, so that the aircraft can be better protected from falling caused by unexpected collision in the flight process.

Referring to fig. 1 and 5, the protection assembly 300 is provided with three groups, the left side of the support plate 310 is provided with a second base rod 311, the second base rod 311 penetrates through the lower end of the front surface of the protection plate 350 and is rotatably connected with the lower end of the front surface of the protection plate 350, the left side of the protection plate 350 is arc-shaped, and the right side of the protection plate 350 is in contact relation with two groups of telescopic rods 330 and a first spring 340, and the telescopic rods 330 and the first spring 340 are fixedly connected with the support block 320.

By setting the surface of the shield 350 to be arc-shaped, drag of the aircraft during flight can be reduced better.

Referring to fig. 5, a clamping groove matching with the first cord 360 and the second cord 370 is formed on the surface of the winding shaft 380, the end of the first cord 360 is fixedly connected to the right side of the protection plate 350, and the end of the second cord 370 is fixedly connected to the left side of the protection plate 350.

The protection plate 350 is acted by the first rope 360 and the second rope 370, so that the aircraft can protect the aircraft during flying, and the aircraft can be supported during landing.

Referring to fig. 6, one end of the rotating rod 430 is rotatably connected to the first rotating shaft 412, the other end of the rotating rod 430 is rotatably connected to the second rotating shaft 452, the length of the second connecting block 451 is longer than that of the first connecting block 411, the first rotating shaft 412 and the second rotating shaft 452 are both disposed at the central positions of the first connecting block 411 and the second connecting block 451, the supporting seat 440 is slidably connected to the telescopic block 450, and three groups of second connecting blocks 451 are disposed on the front surface of the telescopic block 450 and fixedly connected to the first connecting block 411.

The second spring 420 is stressed and compressed through the supporting seat 440 when the aircraft lands, and the telescopic block 450 is pulled by the rotating rod 430 under the action of the first rotating shaft 412 and the second rotating shaft 452, so that the contact area between the telescopic block and the ground is increased, and the stabilizing effect of the aircraft during landing is effectively enhanced.

During use, the wing 130 rotates at a high speed to drive the aircraft to fly, the double-shaft motor 210 is started to drive the first base rod 220 to rotate, the first base rod 220 drives the first bevel gear 230 to rotate, the first bevel gear 230 drives the second bevel gear 240 to rotate, the second bevel gear 240 drives the winding shaft 380 to rotate, the first rope 360 contracts and pulls the protection plate 350 to be attached to the first spring 340, when the foreign object collides with the protection plate 350 in the flying process, the force is effectively buffered off under the action of the first spring 340 and the telescopic rod 330 to prevent the aircraft from turning on one's side, so that the aircraft falls, when the aircraft falls, the wing 130 rotates at a low speed, the double-shaft motor 210 reverses to enable the second rope 370 to bear force, the protection plate 350 is pulled by the first rotating shaft 371 and the second rotating shaft 372 to enable the protection plate 350 to rotate by the second base rod 311, the vertical state is kept, the aircraft is supported during landing, the aircraft is better protected, the supporting seat 440 compresses the second spring 420 during landing, the force is effectively buffered under the action of the first rotating shaft 412 and the second rotating shaft 452, and the ground is effectively increased in contact with the ground, and the ground is effectively contacted with the telescopic rod 430.

Although embodiments of the invention have been shown and described, the detailed description is to be construed as exemplary only and is not limiting of the invention as the particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples, and modifications, substitutions, variations, etc. may be made in the embodiments as desired by those skilled in the art without departing from the principles and spirit of the invention, provided that such modifications are within the scope of the appended claims.

Claims

1. An unmanned aerial vehicle comprising an aircraft assembly (100), characterized in that: the aircraft assembly (100) comprises a machine body (110), wherein a power assembly (200) is arranged in the machine body (110), protective assemblies (300) are arranged at the left side, the right side and the front end of the machine body (110), and a buffer assembly (400) is arranged at the top end of each protective assembly (300);

The protection component (300) comprises a supporting plate (310) fixed on the left side and the right side of a machine body (110) and at the front end, two groups of supporting blocks (320) are arranged on the right side of the top end of the supporting plate (310), a telescopic rod (330) is arranged on the left side of the supporting block (320), a first spring (340) is sleeved on the right side of the outer surface of the telescopic rod (330), a protection plate (350) is arranged on the top end of the telescopic rod (330), a first wire rope (360) is arranged at the center position of the right side of the protection plate (350), a second wire rope (370) is arranged at the center position of the left side of the protection plate (350), a first rotating shaft (371) for changing the extending direction of the second wire rope (370) is arranged at the bottom end of the protection plate (350), a second rotating shaft (372) for changing the extending direction of the second wire rope (370) is arranged above the first rotating shaft (371), a retracting shaft (380) is arranged at the right side end of the first wire rope (360) and the second wire rope (370), the buffer component (400) comprises a fixed block (410) fixed on the top end of the protection plate (350), a second spring (420) is arranged at the top end of the fixed block (411), a second spring (420), a first rotating shaft (412) is arranged at the top end of the protection plate, a first connecting block (412) and a first rotating shaft (412), the top of the second spring (420) is provided with a supporting seat (440), a telescopic block (450) is arranged inside the supporting seat (440), a second connecting block (451) is arranged on the front surface of the telescopic block (450), and a second rotating shaft (452) is arranged at the center of the second connecting block (451).

2. An unmanned aerial vehicle according to claim 1, wherein: the novel wing-mounted aircraft is characterized in that shaft bodies (120) are arranged at four corners of the top end of the aircraft body (110), wings (130) are arranged at the top end of the shaft bodies (120), and a camera (140) is arranged at the bottom end of the aircraft body (110).

3. An unmanned aerial vehicle according to claim 1, wherein: the power assembly (200) comprises a double-shaft motor (210), a base rod (220) is arranged on two sides of the output end of the double-shaft motor (210), two groups of helical gears (230) are arranged on the left side of the double-shaft motor (210), a group of helical gears (230) are arranged on the right side of the double-shaft motor (210), two identical helical gears (240) are arranged on the helical gears (230), and the helical gears (240) are provided with three groups and are fixedly connected to a winding shaft (380).

4. An unmanned aerial vehicle according to claim 1, wherein: the protection assembly (300) is provided with three groups, the left side of the support plate (310) is provided with a second base rod (311), the second base rod (311) penetrates through the lower end of the front surface of the protection plate (350) and is rotationally connected with the lower end of the front surface of the protection plate, and the left side of the protection plate (350) is arc-shaped.

5. An unmanned aerial vehicle according to claim 1, wherein: the right side of the protection plate (350) is in contact relation with the two groups of telescopic rods (330) and the first spring (340), and the telescopic rods (330) and the first spring (340) are fixedly connected to the supporting block (320).

6. An unmanned aerial vehicle according to claim 1, wherein: the winding shaft (380) is provided with clamping grooves matched with the first rope (360) and the second rope (370), the end part of the first rope (360) is fixedly connected to the right side of the protection plate (350), and the end part of the second rope (370) is fixedly connected to the left side of the protection plate (350).

7. An unmanned aerial vehicle according to claim 1, wherein: the utility model discloses a rotary rod, including pivoted lever (430), pivoted lever (430) one end is connected with pivoted lever (412), and pivoted lever (430) other end is connected with pivoted lever (452) No. two, the length of second connecting block (451) is longer than first connecting block (411), pivoted lever (412) and pivoted lever (452) all locate the central point of first connecting block (411) and second connecting block (451).

8. An unmanned aerial vehicle according to claim 1, wherein: the supporting seat (440) is in sliding connection with the telescopic block (450), and three groups of second connecting blocks (451) are arranged on the front surface of the telescopic block (450) and are fixedly connected with the telescopic block.