Vertical take-off and landing aircraft

Abstract

The utility model relates to the technical field of aircrafts, and discloses a vertical take-off and landing aircraft which comprises an aircraft body, handle grooves are formed in the front side and the rear side of the aircraft body, a driving assembly is fixedly installed at the end, away from the aircraft body, of an aircraft arm, and wings are rotationally connected to the upper portion of the driving assembly. A first fixing plate is fixedly installed at the bottom of a driving assembly, a connecting shaft is rotationally connected into the first fixing plate, a fixing rod is fixedly installed at the bottom of the connecting shaft, a limiting plate is fixedly installed at the bottom of the fixing rod, and a damping rod and a first spring are fixedly installed at the bottom of the limiting plate. When the unmanned aerial vehicle needs to take off, a damping rod and a driving assembly are coaxial through the rotation effect of a connecting shaft and a first fixing plate, meanwhile, under the condition that the ground is uneven, the damping rod can stretch out and draw back, and meanwhile the damping rod is matched with a first spring to achieve the purpose that when the unmanned aerial vehicle faces different grounds, the damping rod can stretch out and draw back. The damping effect and the effect of keeping the overall stability of the fuselage are achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and more specifically, to a vertical take-off and landing aircraft. Background Art

[0002] Vertical take-off and landing aircraft refers to the technology that allows flying equipment or devices to take off and land without taxiing. Most of them are now used in the field of helicopters or drones. When taking off or landing, existing drones are placed on the ground for takeoff and landing. When they are located inside mountainous areas, the ground is not very flat, and the drone is likely to tilt during takeoff or landing, resulting in an unstable fuselage and even the risk of breaking. Utility Model Content

[0003] In order to overcome the deficiencies of the prior art, the utility model provides a vertical take-off and landing aircraft, which has the advantage of being able to adapt to different terrains for take-off and landing.

[0004] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a vertical take-off and landing aircraft, comprising a fuselage, handle grooves are provided on the front and rear sides of the fuselage, an anti-shake bracket is fixedly installed on the bottom of the fuselage, a camera is rotatably connected to the inside of the anti-shake bracket, the front and rear sides of the fuselage are rotatably connected to arms, a drive assembly is fixedly installed on one end of the arm away from the fuselage, and a wing is rotatably connected to the top of the drive assembly.

[0005] As a preferred technical solution of the utility model, a fixing plate 1 is fixedly installed on the bottom of the driving component, a connecting shaft is rotatably connected inside the fixing plate 1, a fixing rod is fixedly installed on the bottom of the connecting shaft, a limiting plate is fixedly installed on the bottom of the fixing rod, a damping rod is fixedly installed on the bottom of the limiting plate, and a spring 1 is sleeved on the outer side of the damping rod.

[0006] As a preferred technical solution of the utility model, a mounting sleeve is fixedly installed on the bottom of the damping rod, a connecting hole and a mounting hole are opened inside the mounting sleeve, a base support shaft is inserted into the inside of the mounting hole, a fixing plate 2 is fixedly installed above the base support shaft, a telescopic rod is fixedly installed on the outer side of the fixing plate 2, a spring 2 is sleeved on the outer side of the telescopic rod, and a clamping block is fixedly installed on the side of the spring 2 away from the fixing plate 2.

[0007] As a preferred technical solution of the utility model, a slide groove is opened inside the fuselage, a slider is slidably connected inside the slide groove, a button is fixedly installed on one side of the slider close to the central axis of the connecting hole, and the button is located inside the connecting hole.

[0008] As a preferred technical solution of the present utility model, a silica gel base is fixedly installed at the bottom of the base support shaft. The silica gel base has a relatively soft material and can be replaced with different shapes and different materials.

[0009] As a preferred technical solution of the present utility model, there are four driving components and four wings. The four wings are distributed at the four corners of the fuselage. There are multiple first fixing plates, and the multiple first fixing plates are respectively located below the four driving components. There are four connecting shafts, and the four connecting shafts are respectively rotatably connected to the multiple first fixing plates.

[0010] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0011] 1. In the present utility model, a first fixing plate is fixedly installed at the bottom of the driving component, a connecting shaft is rotatably connected inside the first fixing plate, a fixing rod is fixedly installed at the bottom of the connecting shaft, and a limiting plate is fixedly installed at the bottom of the fixing rod. A damping rod and a first spring are fixedly installed at the bottom of the limiting plate. When the drone needs to take off, through the rotational action of the connecting shaft and the first fixing plate, the damping rod is coaxially aligned with the driving component. At the same time, when facing uneven ground, the damping rod will expand and contract, and cooperate with the first spring to achieve the effects of shock absorption and maintaining the overall stability of the fuselage when facing different ground conditions.

[0012] 2. In the present utility model, a connecting hole, an installation hole and a chute are provided inside the installation sleeve. When the base support shaft with the silica gel base needs to be installed, the block is pressed towards the second fixing plate, so that the telescopic rod contracts, and the base support shaft with the block enters the inside of the connecting hole together. At this time, the base support shaft is rotated. When the block rotates and aligns with the connecting hole, the second spring will provide elastic force to pop the block into the inside of the connecting hole, so as to be clamped inside the connecting hole to fix the base support shaft as a whole. At the same time, when the silica gel base needs to be disassembled, since the block is in contact with the button, the button is pressed inward. Through the sliding action of the slider and the chute, the block drives the telescopic rod and the second spring to contract, and then the base support shaft is pulled downward, so as to achieve the effects of convenient installation and disassembly. Description of the Drawings

[0013] Figure 1 It is a schematic diagram of the overall structure of the present utility model;

[0014] Figure 2 It is for the present utility model Figure 1 Enlarged schematic diagram of the structure at A;

[0015] Figure 3 It is for the present utility model Figure 1 Enlarged schematic diagram of the structure at B;

[0016] Figure 4 This is an exploded view of a partial structure of the present utility model;

[0017] Figure 5 This is the present utility model Figure 4 A schematic enlarged view of the structure at position C of the present utility model.

[0018] In the figure: 1, fuselage; 2, handle groove; 3, anti-shake bracket; 4, camera; 5, arm; 6, drive assembly; 7, wing; 8, first fixing plate; 9, connecting shaft; 10, fixing rod; 11, limiting plate; 12, damping rod; 13, first spring; 14, mounting sleeve; 15, connecting hole; 16, mounting hole; 17, sliding groove; 18, slider; 19, button; 20, base support shaft; 21, second fixing plate; 22, telescopic rod; 23, second spring; 24, clamping block; 25, silicone base. Specific embodiments

[0019] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without making creative efforts belong to the scope of protection of the present utility model.

[0020] As Figures 1 to 5 shown, the present utility model provides a vertical takeoff and landing aircraft, including a fuselage 1. Handle grooves 2 are provided on both the front and rear sides of the fuselage 1. An anti-shake bracket 3 is fixedly installed at the bottom of the fuselage 1. A camera 4 is rotatably connected inside the anti-shake bracket 3. Arms 5 are rotatably connected to both the front and rear sides of the fuselage 1. A drive assembly 6 is fixedly installed at one end of the arm 5 away from the fuselage 1. A wing 7 is rotatably connected above the drive assembly 6.

[0021] A power assembly is provided inside the drive assembly 6, which can drive the wing 7 to rotate at high speed, so that the fuselage 1 is lifted by an upward force to achieve the effect of vertical takeoff. At the same time, after the fuselage 1 is lifted, the camera 4 will take pictures of the bottom of the ground to facilitate the observation of the nearby terrain.

[0022] Among them, a first fixing plate 8 is fixedly installed at the bottom of the drive assembly 6. A connecting shaft 9 is rotatably connected inside the first fixing plate 8. A fixing rod 10 is fixedly installed at the bottom of the connecting shaft 9. A limiting plate 11 is fixedly installed at the bottom of the fixing rod 10. A damping rod 12 is fixedly installed at the bottom of the limiting plate 11. A first spring 13 is sleeved outside the damping rod 12.

[0023] When taking off facing an uneven position, the spring 13 rotates through the connecting shaft 9 and the fixing plate 8 to coaxialize the damping rod 12 with the driving assembly 6. At the same time, when facing uneven positions, the damping rod 12 can expand and contract, thereby improving the balance effect and stability of the fuselage 1.

[0024] Among them, a mounting sleeve 14 is fixedly installed at the bottom of the damping rod 12. A connecting hole 15 and a mounting hole 16 are opened inside the mounting sleeve 14. A base support shaft 20 is inserted into the mounting hole 16. Above the base support shaft 20, a fixing plate 21 is fixedly installed. On the outside of the fixing plate 21, a telescopic rod 22 is fixedly installed. A spring 23 is sleeved outside the telescopic rod 22. On the side of the spring 23 away from the fixing plate 21, a clamping block 24 is fixedly installed.

[0025] When the base support shaft 20 needs to be installed, the clamping block 24 is pressed towards the fixing plate 21 to contract the telescopic rod 22, so that the base support shaft 20 and the clamping block 24 enter the inside of the connecting hole 15 together. At this time, the base support shaft 20 is rotated. When the clamping block 24 rotates and aligns with the connecting hole 15, the spring 23 will provide elastic force to pop the clamping block 24 into the inside of the connecting hole 15, so as to enter the inside of the connecting hole 15 and the whole base support shaft 20 is clamped, achieving a fixing effect.

[0026] Among them, a sliding groove 17 is opened inside the fuselage 1. A slider 18 is slidably connected inside the sliding groove 17. On the side of the slider 18 close to the central axis of the connecting hole 15, a button 19 is fixedly installed. The button 19 is located inside the connecting hole 15.

[0027] When the base support shaft 20 needs to be disassembled, the button 19 is pressed inward. Through the sliding action of the slider 18 and the sliding groove 17, the clamping block 24 drives the telescopic rod 22 and the spring 23 to contract, and then the base support shaft 20 is pulled downward, thus achieving the effect of convenient disassembly.

[0028] Among them, a silicone base 25 is fixedly installed at the bottom of the base support shaft 20. The material of the silicone base 25 is relatively soft, and the silicone base 25 can be replaced with different shapes and different materials.

[0029] When facing a hard ground, the relatively soft silicone base 25 can play a role in shock absorption and anti-collision. When facing a soft ground, the silicone base 25 can be replaced with a harder conical material to slightly insert the silicone base 25 into the ground, thereby improving the overall stability of the fuselage 1.

[0030] Among them, there are four driving components 6 and four wings 7. The four wings 7 are distributed at the four corners of the fuselage 1. There are multiple first fixing plates 8, and the multiple first fixing plates 8 are respectively located below the four driving components 6. There are four connecting shafts 9, and the four connecting shafts 9 are respectively rotatably connected to the multiple first fixing plates 8.

[0031] When takeoff is not required, the four connecting shafts 9 are folded through rotational action with the multiple first fixing plates 8, so as to achieve the effect of convenient storage.

[0032] The working principle and usage process of the present utility model are as follows:

[0033] First, the arm 5 is pulled away from the fuselage 1 to extend the arm 5 to the maximum. Secondly, the connecting shaft 9 is rotated through rotation with the first fixing plate 8 so that the damping rod 12 and the driving component 6 are coaxial and fixed.

[0034] At this time, the block 24 is pressed towards the second fixing plate 21 to contract the telescopic rod 22, so that the base support shaft 20 carries the block 24 into the inside of the connection hole 15 together. At this time, the base support shaft 20 is rotated. When the block 24 rotates and aligns with the connection hole 15, the spring two 23 will provide elastic force to spring the block 24 into the inside of the connection hole 15, so as to achieve the effect that the whole base support shaft 20 is clamped into the inside of the connection hole 15 to install the silica gel base 25.

[0035] Secondly, the driving component 6 is started to drive the wing 7 to rotate at a high speed, so that the wing 7 has an upward lifting force after rotation, thereby driving the fuselage 1 to vertically rise, and then observing and photographing the nearby terrain through the camera 4.

[0036] Finally, when it is necessary to land on an uneven ground after the end, since the connecting shaft 9 is rotatably connected inside the first fixing plate 8, a fixing rod 10 is fixedly installed at the bottom of the connecting shaft 9, and a limiting plate 11 is fixedly installed at the bottom of the fixing rod 10. A damping rod 12 and a spring one 13 are fixedly installed at the bottom of the limiting plate 11. After landing, the damping rod 12 will contract, combined with the elasticity of the spring one 13 to play a role in shock absorption and stability, so as to achieve the effect of landing on an uneven place.

[0037] It should be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprising", "including" or any other variant thereof are intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements not only includes those elements but also includes other elements not expressly listed, or elements inherent to such process, method, article or device.

[0038] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A vertical take-off and landing aircraft, comprising a fuselage (1), characterized in that: The front and rear sides of the fuselage (1) are both provided with handle grooves (2); an anti-shake bracket (3) is fixedly mounted on the bottom of the fuselage (1); a camera (4) is rotatably connected to the interior of the anti-shake bracket (3); the front and rear sides of the fuselage (1) are both rotatably connected to arms (5); a drive assembly (6) is fixedly mounted on one end of the arm (5) away from the fuselage (1); and a wing (7) is rotatably connected to the top of the drive assembly (6).

2. A vertical take-off and landing aircraft according to claim 1, characterized in that: A fixing plate (8) is fixedly mounted on the bottom of the driving component (6); a connecting shaft (9) is rotatably connected to the inside of the fixing plate (8); a fixing rod (10) is fixedly mounted on the bottom of the connecting shaft (9); a limiting plate (11) is fixedly mounted on the bottom of the fixing rod (10); a damping rod (12) is fixedly mounted on the bottom of the limiting plate (11); and a spring (13) is sleeved on the outer side of the damping rod (12).

3. A vertical take-off and landing aircraft according to claim 2, characterized in that: A mounting sleeve (14) is fixedly mounted on the bottom of the damping rod (12); a connecting hole (15) and a mounting hole (16) are provided inside the mounting sleeve (14); a base support shaft (20) is inserted into the inside of the mounting hole (16); a second fixing plate (21) is fixedly mounted above the base support shaft (20); a telescopic rod (22) is fixedly mounted on the outer side of the second fixing plate (21); a second spring (23) is sleeved on the outer side of the telescopic rod (22); and a clamping block (24) is fixedly mounted on the side of the second spring (23) away from the second fixing plate (21).

4. A vertical take-off and landing aircraft according to claim 1, characterized in that: A slide groove (17) is provided inside the body (1), a slider (18) is slidably connected inside the slide groove (17), a button (19) is fixedly mounted on one side of the slider (18) close to the central axis of the connecting hole (15), and the button (19) is located inside the connecting hole (15).

5. A vertical take-off and landing aircraft according to claim 3, characterized in that: A silicone base (25) is fixedly mounted on the bottom of the base support shaft (20); the material of the silicone base (25) is relatively soft, and the silicone base (25) can be replaced with different shapes and different materials.

6. A vertical take-off and landing aircraft according to claim 2, characterized in that: There are four drive assemblies (6) and four wings (7), and the four wings (7) are distributed at the four corners of the fuselage (1). There are multiple fixing plates (8), and the multiple fixing plates (8) are respectively located below the four drive assemblies (6). There are four connecting shafts (9), and the four connecting shafts (9) are respectively rotatably connected to the multiple fixing plates (8).

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