An aircraft wing adjustment mechanism

Abstract

This utility model discloses an aircraft wing adjustment mechanism, including a main unit. Connectors are located at each of the four corners of the main unit. Wing arms are rotatably fitted within each of the four connectors, and motors are installed within the wing arms, with fan blades mounted at the motor output ends. An adjusting rod is elastically fitted at one end of each wing arm rotatably fitted within a connector. A locking assembly is provided between the adjusting rod and the connector. A support rod is rotatably fitted at the end of the wing arm away from the connector. A protective rod is provided at one end of the support rod. A connecting rod is provided between the ends of every two adjacent protective rods. A landing gear is located at the bottom of the main unit. This utility model, through the adjustable rod, allows the locking assembly to be released by pressing the adjusting rod, enabling the wing arms to rotate and retract. Simultaneously, it allows the support rod to rotate, causing the protective rod to retract. This facilitates the adjustment and storage of the wing arms while simultaneously retracting the support and protective rods, reducing the overall space occupied by the aircraft and making it easier to store and store.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to an aircraft wing adjustment mechanism. Background Technology

[0002] With the development of technology, aircraft are widely used in various fields. Multirotor aircraft, compared to fixed-wing aircraft, have the advantage of vertical takeoff and landing, and are therefore widely used. Multirotor aircraft achieve attitude control by controlling the rotational speeds of different propellers.

[0003] Currently, for the safety of multi-rotor aircraft, anti-collision rings are usually used to protect multiple rotors, which also has the effect of protecting the aircraft. However, the fixed setting of the anti-collision rings results in a large overall space occupation of the aircraft, and the wings cannot be retracted, making it inconvenient to adjust and store the wings. There is an urgent need to design an aircraft wing adjustment mechanism to solve the above problems. Utility Model Content

[0004] The purpose of this invention is to provide an aircraft wing adjustment mechanism to address the aforementioned shortcomings in the prior art.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] An aircraft wing adjustment mechanism includes a main unit, with connectors at each of the four corners of the main unit, wing arms rotatably fitted within each of the four connectors, motors housed within the wing arms, and fan blades mounted at the output end of the motors.

[0007] The wing arm is rotatably fitted with an adjusting rod at one end within the connector. A snap-fit ​​assembly is provided between the adjusting rod and the connector. The end of the wing arm away from the connector is rotatably fitted with a support rod. A protective rod is provided at one end of the support rod. A connecting rod is provided between the ends of every two adjacent protective rods. A landing bracket is provided at the bottom of the main unit.

[0008] Furthermore, the landing gear includes two U-shaped rods rotatably fitted to the bottom of the main unit, and two U-shaped cylinders elastically fitted to the two U-shaped rods respectively. The two ends of the U-shaped rods are slidably fitted inside the two ends of the U-shaped cylinders and elastically fitted to the U-shaped cylinders. A torsion spring is provided between the periphery of the U-shaped rods and the bottom of the main unit.

[0009] Furthermore, the snap-fit ​​assembly includes multiple slots formed on the top of the inner wall of the connector, a snap block disposed on one side of the adjusting rod, and a sliding groove formed on one end of the wing arm. The snap block is slidably fitted in the sliding groove and snap-fitted with the slots.

[0010] Furthermore, a groove is provided at the bottom end of the adjusting rod, and a spring is provided between the groove and the interior of one end of the wing arm.

[0011] Furthermore, a block is slidably fitted at one end of the support rod, a through groove is provided at one end of the wing arm to engage with the block, a protrusion is provided at the top of the adjusting rod, the top of the protrusion is rounded, and a square groove corresponding to the protrusion is provided at the bottom of the block.

[0012] Furthermore, the protective rod is arc-shaped, and both ends of the protective rod are provided with connecting grooves, with one end of the connecting rod engaging with the connecting groove.

[0013] In the above technical solution, the aircraft wing adjustment mechanism provided by this utility model has the following beneficial effects:

[0014] The adjustable rods allow the locking components to be released by pressing them, enabling the wing arms to rotate and retract. Simultaneously, the support rods can be rotated to retract the protective rods, facilitating the adjustment and storage of the wing arms while simultaneously retracting the support and protective rods. This reduces the overall space occupied by the aircraft and makes storage easier. The connecting rods, after the four wing arms are deployed, connect the connecting rods to two protective rods, forming a collision protection ring with the four protective rods and four connecting rods. This facilitates quick deployment and assembly, and also makes storage more convenient. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings.

[0016] Figure 1 This is a schematic diagram of the overall structure of an embodiment of an aircraft wing adjustment mechanism according to the present invention.

[0017] Figure 2 This is a schematic diagram of a protective rod structure provided for an embodiment of an aircraft wing adjustment mechanism according to the present invention.

[0018] Figure 3 This is a schematic diagram of the landing gear structure provided for an embodiment of an aircraft wing adjustment mechanism according to the present invention.

[0019] Figure 4 This is a schematic diagram of the wing arm structure provided for an embodiment of an aircraft wing adjustment mechanism according to the present invention.

[0020] 1. Main unit; 2. Connecting parts; 3. Wing arm; 4. Motor; 5. Fan blade; 6. Adjusting rod; 7. Support rod; 8. Protective rod; 9. Connecting rod; 10. Landing bracket; 11. U-shaped rod; 12. U-shaped cylinder; 13. Torsion spring; 14. Slot; 15. Locking block; 16. Slide groove; 17. Spring; 18. Square block; 19. Through groove; 20. Protrusion; 21. Square groove; 22. Connecting groove. Detailed Implementation

[0021] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings.

[0022] like Figure 1-4 As shown in the figure, this utility model provides an aircraft wing adjustment mechanism.

[0023] Includes a main unit 1, with connectors 2 at each of the four corners of the main unit 1, and wing arms 3 rotatably fitted inside each of the four connectors 2, with motors 4 installed inside the wing arms 3, and fan blades 5 installed at the output end of the motors 4;

[0024] One end of the wing arm 3 is rotatably fitted with an adjusting rod 6 within the connector 2. A snap-fit ​​assembly is provided between the adjusting rod 6 and the connector 2. The end of the wing arm 3 away from the connector 2 is rotatably fitted with a support rod 7. One end of the support rod 7 is provided with a protective rod 8. A connecting rod 9 is provided between the ends of every two adjacent protective rods 8. A landing bracket 10 is provided at the bottom of the main unit 1.

[0025] Reference Figure 3 In this embodiment, the landing gear 10 includes two U-shaped rods 11 rotatably fitted to the bottom of the main unit 1, and two U-shaped cylinders 12 elastically fitted to the two U-shaped rods 11 respectively. The two ends of the U-shaped rods 11 are slidably fitted inside the two ends of the U-shaped cylinders 12 and elastically fitted to the U-shaped cylinders 12. A torsion spring 13 is provided between the periphery of the U-shaped rods 11 and the bottom of the main unit 1. Through the U-shaped cylinders 12, when the aircraft lands, the U-shaped cylinders 12 contact the ground, so that there is elastic cushioning between the U-shaped cylinders 12 and the U-shaped rods 11, and at the same time, the rotation of the U-shaped rods 11 drives the torsion springs 13.

[0026] Reference Figure 3 , Figure 4The snap-fit ​​assembly of this embodiment includes multiple slots 14 formed on the top of the inner wall of the connector 2, a snap-fit ​​block 15 disposed on one side of the adjusting rod 6, and a sliding groove 16 formed on one end of the wing arm 3. The snap-fit ​​block 15 is slidably fitted in the sliding groove 16 and snap-fitted with the slot 14. By pressing the adjusting rod 6 through the slot 14, the snap-fit ​​block 15 will move and move out of the slot 14 along the sliding groove 16, releasing the fixation between the connector 2 and the wing arm 3. After the adjusting rod 6 is released, the elastic force will move the adjusting rod 6 upward, causing the adjusting rod 6 to move the snap-fit ​​block 15 into the slot 14 for snap-fit ​​fixation.

[0027] Reference Figure 4 In this embodiment, the bottom end of the adjusting rod 6 is provided with a groove, and a spring 17 is provided between the groove and the interior of one end of the wing arm 3. Through the groove, when the adjusting rod 6 is pressed, the spring 17 can be squeezed into the groove, without affecting the up and down movement of the adjusting rod 6.

[0028] Reference Figure 4 In this embodiment, a block 18 is slidably fitted into one end of the support rod 7, and a through groove 19 is provided at one end of the wing arm 3 to engage with the block 18. A protrusion 20 is provided at the top of the adjusting rod 6, and the top of the protrusion 20 is rounded. A square groove 21 corresponding to the protrusion 20 is provided at the bottom of the block 18. By pressing the block 18 into the through groove 19, the support rod 7 can be fixed. When stored, the protrusion 20 can pass through the through groove 19 and enter the square groove 21, reducing accidental contact with the adjusting rod 6 and making storage more stable. The rounded corner at the top of the protrusion 20 can smoothly enter and exit the square groove 21.

[0029] Reference Figure 4 In this embodiment, the protective rod 8 is arc-shaped, and both ends of the protective rod 8 are provided with connecting grooves 22. One end of the connecting rod 9 is engaged with the connecting groove 22. Through the connecting grooves 22, after the protective rod 8 is unfolded, the connecting rod 9 is used to connect two protective rods 8, so that both ends of the connecting rod 9 are engaged with the connecting grooves 22 at one end of the two protective rods 8 respectively, so that the four protective rods 8 and the four connecting rods 9 form a protective ring.

[0030] Working principle: In use, first press the block 18 to push the protrusion 20, which in turn pushes the adjusting rod 6. This allows the adjusting rod 6 and the protrusion 20 to move smoothly out of the through groove 19. At the same time, the adjusting rod 6 releases the fixing of the snap-fit ​​assembly, allowing the wing arm 3 to rotate. Then, rotate and unfold the four wing arms 3. After the wing arms 3 rotate out, the adjusting rod 6 uses its elasticity to re-engage the snap-fit ​​assembly, fixing the wing arms 3. Then, rotate out the support rod 7, press the block 18 to enter the through groove 19 for fixing, so that the protective rod 8 protects the aircraft. Then, snap the connecting rod 9 between one end of each pair of adjacent protective rods 8, so that the four protective rods 8 and the four connecting rods 9 form a protective ring. Then, control the main unit 1 to start the motor 4. The motor 4 will drive the fan blade 5 to rotate. To retract, adjust the adjusting rod 6 to release the fixing of the snap-fit ​​assembly, and then rotate to retract the wing arms 3 and support rod 7. The protrusion 20 on the adjusting rod 6 can pass through the through groove 19 and enter the square groove 21 to simply fix the support rod 7.

[0031] The foregoing description only illustrates certain exemplary embodiments of the present invention. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An aircraft wing adjustment mechanism, comprising a main unit (1), characterized in that, The host (1) is provided with connectors (2) at each of its four corners. Each of the four connectors (2) is fitted with a wing arm (3). A motor (4) is provided inside the wing arm (3). A fan blade (5) is installed at the output end of the motor (4). The wing arm (3) is rotatably fitted with an adjusting rod (6) in one end of the connector (2). A snap-fit ​​assembly is provided between the adjusting rod (6) and the connector (2). The end of the wing arm (3) away from the connector (2) is rotatably fitted with a support rod (7). A protective rod (8) is provided at one end of the support rod (7). A connecting rod (9) is provided between the ends of every two adjacent protective rods (8). A landing bracket (10) is provided at the bottom of the main unit (1).

2. The aircraft wing adjustment mechanism according to claim 1, characterized in that, The landing support (10) includes two U-shaped rods (11) rotatably fitted at the bottom of the main unit (1) and two U-shaped cylinders (12) elastically fitted with the two U-shaped rods (11) respectively. The two ends of the U-shaped rods (11) are slidably fitted inside the two ends of the U-shaped cylinders (12) and elastically fitted with the U-shaped cylinders (12). A torsion spring (13) is provided between the periphery of the U-shaped rods (11) and the bottom of the main unit (1).

3. The aircraft wing adjustment mechanism according to claim 1, characterized in that, The snap-fit ​​assembly includes multiple slots (14) formed on the top of the inner wall of the connector (2), a snap block (15) set on one side of the adjusting rod (6), and a sliding groove (16) formed on one end of the wing arm (3). The snap block (15) slides in the sliding groove (16) and snaps into the slots (14).

4. The aircraft wing adjustment mechanism according to claim 1, characterized in that, The bottom end of the adjusting rod (6) is provided with a groove, and a spring (17) is provided between the groove and the interior of one end of the wing arm (3).

5. The aircraft wing adjustment mechanism according to claim 1, characterized in that, One end of the support rod (7) is slidably fitted with a block (18), one end of the wing arm (3) is provided with a through groove (19) that engages with the block (18), the top of the adjusting rod (6) is provided with a protrusion (20), the top of the protrusion (20) is provided with a rounded corner, and the bottom of the block (18) is provided with a square groove (21) corresponding to the protrusion (20).

6. The aircraft wing adjustment mechanism according to claim 1, characterized in that, The protective rod (8) is arc-shaped, and both ends of the protective rod (8) are provided with connecting grooves (22). One end of the connecting rod (9) is engaged with the connecting groove (22).

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