Vertical take-off and landing aircraft capable of rapidly replacing rotor wings

Abstract

The utility model relates to the technical field of aircrafts, and discloses a vertical take-off and landing aircraft capable of quickly replacing rotor wings, which comprises an aircraft body, a plurality of wings are fixedly connected outside the aircraft body, the tops of the wings are rotatably connected with connecting blocks I, two rotating shafts I are rotatably connected inside the connecting blocks I, and the two rotating shafts I are rotatably connected inside the aircraft body. A threaded block is fixedly connected to the exterior of the first rotating shaft, two clamping blocks are slidably connected to the interior of the first connecting block, threaded shafts are connected to the interiors of the two clamping blocks in a threaded mode, and telescopic rods are fixedly connected to the sides, close to each other, of the two clamping blocks. When the connecting shaft is subjected to external force, the connecting shaft moves downwards to enable the groove and the threaded shaft to move, when the connecting column moves, the groove rotates, the threaded shaft linearly moves, and the first spring correspondingly stretches out and draws back along with the movement of the threaded shaft, so that elastic support is provided; therefore, the effect of quickly replacing the rotor wing is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a vertical take-off and landing aircraft with rapidly replaceable rotors. Background Art

[0002] A vertical take-off and landing aircraft is an aircraft that can take off and land in a vertical direction. This type of aircraft usually does not rely on long runways or take-off and landing ramps like traditional aircraft, but can operate in confined spaces or places without fixed runways by taking off and landing directly in the air. It refers to the process of replacing or replacing the original rotor system in an aircraft for various reasons.

[0003] In the prior art, some devices cannot quickly replace the rotor, which makes it more difficult to repair the damaged rotor and cannot be quickly replaced, resulting in increased maintenance time and cost, and increased design and manufacturing complexity and cost. Utility Model Content

[0004] The utility model provides a vertical take-off and landing aircraft with rapidly replaceable rotors, aiming to improve the problem of difficulty in replacing rotors of the aircraft.

[0005] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0006] A vertical take-off and landing aircraft with quickly replaceable rotors comprises a fuselage, a plurality of wings being fixedly connected to the outside of the fuselage, a connecting block being rotatably connected to the top of the wing, two rotating shafts being rotatably connected to the inside of the connecting block, a threaded block being fixedly connected to the outside of the rotating shaft, two clamping blocks being slidably connected to the inside of the connecting block, a threaded shaft being connected to the internal threads of the two clamping blocks, a telescopic rod being fixedly connected to adjacent sides of the two clamping blocks, an elastic component for providing static friction being sleeved on the outside of the telescopic rod, a clamping block being detachably connected to adjacent sides of the two clamping blocks, a connecting shaft being fixedly connected to the top of the clamping block, and a blade being fixedly connected to the top of the connecting shaft.

[0007] Furthermore, the elastic component includes a spring 1, and the spring is arranged on the outside of the telescopic rod. The two ends of the spring 1 are respectively fixedly connected to the inside of the two clamping blocks.

[0008] Furthermore, a plurality of fixing blocks are fixedly connected to the bottom of the fuselage, a fixing rod is fixedly connected to adjacent sides of two fixing blocks on the same side, and a sliding block is slidably connected to the outside of the fixing rod.

[0009] Furthermore, two springs are sleeved on the outside of the fixing rod, a groove is provided on one side of the outside of the threaded shaft, and two searchlights are fixedly connected to the front side of the outside of the fuselage.

[0010] Furthermore, the sliding block is internally rotatably connected to a second rotating shaft, the second rotating shaft is externally rotatably connected to a rotating plate, and the two rotating plates are internally rotatably connected to a third rotating shaft.

[0011] Furthermore, the outside of the rotating shaft three is fixedly connected with a connecting block two, and the outside of the connecting block two is fixedly connected with an arc plate.

[0012] Furthermore, one end of the second spring is fixedly connected to one side of the outside of the fixed block, and the other end of the second spring is fixedly connected to one side of the outside of the sliding block.

[0013] Furthermore, the external thread of the threaded block is connected to the inside of the connecting block 1, and the external thread of the threaded block is connected to the top of the clamping block.

[0014] The utility model has the following beneficial effects:

[0015] 1. In the utility model, when the connecting shaft is subjected to external force, it moves downward so that the groove and the threaded shaft move. When the connecting shaft moves, the groove rotates and the threaded shaft moves linearly. The spring 1 also expands and contracts accordingly with the movement of the threaded shaft to provide elastic support, thereby achieving the effect of quickly replacing the rotor.

[0016] 2. In the utility model, when the aircraft lands, the fixed block is fixed as the impact force is transmitted, so that the spring 2 supports the fixed block. During the support of the spring 2, the rotating shaft 2 is connected to the rotating plate, and the rotating plate 3 is connected to the connecting block 2, so that very little impact is transmitted to the support plate, so as to solve the impact problem when the aircraft lands. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A three-dimensional diagram of a vertical take-off and landing aircraft with rapidly replaceable rotors proposed in the utility model;

[0018] Figure 2 This is a cross-sectional view of the connection block of the vertical take-off and landing aircraft with rapidly replaceable rotors proposed in the utility model;

[0019] Figure 3 This is a schematic diagram of the fixed block structure of a vertical take-off and landing aircraft with quickly replaceable rotors proposed by the utility model.

[0020] Legend:

[0021] 1. Fuselage; 2. Wing; 3. Connecting block 1; 4. Rotating shaft 1; 5. Threaded block; 6. Clamping block; 7. Threaded shaft; 8. Groove; 9. Telescopic rod; 10. Spring 1; 11. Connecting shaft; 12. Engaging block; 13. Blade; 14. Fixed rod; 15. Spring 2; 16. Fixed block; 17. Rotating shaft 2; 18. Sliding block; 19. Rotating plate; 20. Rotating shaft 3; 21. Connecting block 2; 22. Curved plate; 23. Searchlight. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only 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.

[0023] Reference Figure 1 , Figure 2 The utility model provides an embodiment: a vertical take-off and landing aircraft with a rapidly replaceable rotor, comprising a fuselage 1, a plurality of wings 2 are fixedly connected to the outside of the fuselage 1, and the purpose is to maintain stability during the flight of the aircraft. The top of the wing 2 is rotatably connected to a connecting block 13, the inside of the connecting block 13 is rotatably connected to two rotating shafts 14, the outside of the rotating shaft 4 is fixedly connected to a threaded block 5, the inside of the connecting block 13 is slidably connected to two clamping blocks 6, the inside of the two clamping blocks 6 is threadedly connected to a threaded shaft 7, the adjacent sides of the two clamping blocks 6 are fixedly connected to a telescopic rod 9, the telescopic rod 9 is used to support the movement of a spring 10, the outer sleeve of the telescopic rod 9 is provided with an elastic component for providing static friction, the adjacent sides of the two clamping blocks 6 are detachably connected to a clamping block 12, the top of the clamping block 12 is fixedly connected to a connecting shaft 11, the top of the connecting shaft 11 is fixedly connected to a blade 13, and the blade 13 can reduce resistance and improve efficiency.

[0024] Reference Figure 1-Figure 3 The elastic component includes a spring 10, which is sleeved on the outside of the telescopic rod 9, and the two ends of the spring 10 are respectively fixedly connected to the inside of the two clamping blocks 6. The bottom of the fuselage 1 is fixedly connected with a plurality of fixed blocks 16, and the fixed blocks 16 are used to fix the two springs for relative movement. The adjacent side of the two fixed blocks 16 on the same side is fixedly connected with a fixed rod 14, which connects the two springs 15 for fixing. The outside of the fixed rod 14 is slidably connected with a sliding block 18. The outside of the fixed rod 14 is sleeved with two springs 15, which can reduce resistance when the aircraft lands. A groove 8 is provided on the outer side of the threaded shaft 7. Two searchlights 23 are fixedly connected to the outer front side of the fuselage 1, and the searchlights 23 provide safety protection in bad weather.

[0025] Reference Figure 1-Figure 3 The sliding block 18 is internally rotatably connected to a rotating shaft 2 17, and the rotating shaft 2 17 is externally rotatably connected to a rotating plate 19, and the two rotating plates 19 are internally rotatably connected to a rotating shaft 3 20. The rotating shaft 3 20 is externally fixedly connected to a connecting block 21, and the connecting block 21 is externally fixedly connected to an arc plate 22. In order to allow the aircraft to land smoothly, one end of the spring 2 15 is fixedly connected to the external side of the fixed block 16, and the other end of the spring 2 15 is fixedly connected to the external side of the sliding block 18. The sliding block 18 is connected to the rotating shaft for sliding. The external thread of the threaded block 5 is connected to the inside of the connecting block 1 3, in order to connect the blades 13 so that the rotor can be quickly replaced for the aircraft. The external thread of the threaded block 5 is connected to the top of the clamping block 6.

[0026] Compared with some devices in the prior art, the above content is that when the connecting shaft 11 is subjected to external force, it moves downward to cause the groove 8 and the threaded shaft 7 to rotate. When the connecting column moves, the groove 8 rotates, and the threaded shaft 7 moves linearly. The spring 10 also expands and contracts accordingly with the movement of the threaded shaft 7. Secondly, as the impact force is transmitted, the fixed block 16 is fixed to allow the spring 2 15 to support the fixed block 16. When the spring 2 15 is supporting, the rotating shaft 2 17 is connected to the rotating plate 19, and the rotating plate 19 is connected to the connecting block 2 21, so that very little impact is transmitted to the arc plate 22 to solve the impact problem when the aircraft lands.

[0027] Working principle: When the connecting shaft 11 is acted upon by an external force, it moves downward to make the clamping block 6 perform horizontal reciprocating motion. When the clamping block moves, the groove 8 and the threaded block 5 perform reciprocating motion. The purpose of this is to make the connecting column move up and down. When the clamping plate 6 moves, it will drive the threaded block 5 to move, and the fuselage 1 will also move accordingly. When the clamping block 6 moves, it will drive the spring 10 to contract and provide elastic support to solve the problem of the aircraft being able to quickly replace the rotor. Secondly, when the aircraft is landing, the connecting shaft 11 fixes the fixed rod 14, and one end of the spring 2 15 is fixedly connected to the fixed block 16. The spring 2 15 is used to fix the fixed block 16. In the process of the clamping block 12 supporting, the fixed rod 14 connects the two sliding blocks 18. When the sliding block 18 slides, it is connected to the rotating plate 19 through the rotating shaft 2 17, and the rotating plate 19 is connected to the connecting block 2 21, thereby reducing the impact force transmitted to the arc plate 22 to solve the problem of impact when the aircraft lands.

[0028] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A vertical take-off and landing aircraft with rapidly replaceable rotors, comprising a fuselage (1), characterized in that: The fuselage (1) is fixedly connected to a plurality of wings (2) on the outside, the top of the wing (2) is rotatably connected to a connecting block (3), the inside of the connecting block (3) is rotatably connected to two rotating shafts (4), the outside of the rotating shaft (4) is fixedly connected to a threaded block (5), the inside of the connecting block (3) is slidably connected to two clamping blocks (6), the insides of the two clamping blocks (6) are threadedly connected to a threaded shaft (7), the adjacent sides of the two clamping blocks (6) are fixedly connected to a telescopic rod (9), the outside of the telescopic rod (9) is sleeved with an elastic component for providing static friction, the adjacent sides of the two clamping blocks (6) are detachably connected to a clamping block (12), the top of the clamping block (12) is fixedly connected to a connecting shaft (11), and the top of the connecting shaft (11) is fixedly connected to a blade (13).

2. The vertical take-off and landing aircraft with rapidly replaceable rotors according to claim 1, characterized in that: The elastic component comprises a spring 1 (10), wherein the spring 1 (10) is sleeved on the outside of the telescopic rod (9), and the two ends of the spring 1 (10) are respectively fixedly connected to the inside of the two clamping blocks (6).

3. The vertical take-off and landing aircraft with rapidly replaceable rotors according to claim 1, characterized in that: A plurality of fixed blocks (16) are fixedly connected to the bottom of the fuselage (1), a fixed rod (14) is fixedly connected to adjacent sides of two fixed blocks (16) on the same side, and a sliding block (18) is slidably connected to the outside of the fixed rod (14).

4. The vertical take-off and landing aircraft with rapidly replaceable rotors according to claim 3, characterized in that: The fixing rod (14) is sleeved with two springs (15) on its exterior, a groove (8) is provided on one side of the exterior of the threaded shaft (7), and two searchlights (23) are fixedly connected to the exterior front side of the fuselage (1).

5. The vertical take-off and landing aircraft with rapidly replaceable rotors according to claim 3, characterized in that: The sliding block (18) is internally rotatably connected to a second rotating shaft (17), the second rotating shaft (17) is externally rotatably connected to a rotating plate (19), and the two rotating plates (19) are internally rotatably connected to a third rotating shaft (20).

6. The vertical take-off and landing aircraft with rapidly replaceable rotors according to claim 5, characterized in that: The outside of the rotating shaft three (20) is fixedly connected to a connecting block two (21), and the outside of the connecting block two (21) is fixedly connected to an arc-shaped plate (22).

7. The vertical take-off and landing aircraft with rapidly replaceable rotors according to claim 4, characterized in that: One end of the second spring (15) is fixedly connected to an outer side of the fixed block (16), and the other end of the second spring (15) is fixedly connected to an outer side of the sliding block (18).

8. The vertical take-off and landing aircraft with rapidly replaceable rotors according to claim 1, characterized in that: The external thread of the threaded block (5) is connected to the inside of the connecting block (3), and the external thread of the threaded block (5) is connected to the top of the clamping block (6).

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