A wing rotation locking mechanism for tube-launched UAVs

Abstract

The present invention discloses a barrel-launched UAV wing rotation locking mechanism, which includes a base, a driving torsion spring, a locking pin, a locking pin compression spring, a shock-absorbing rubber pad, a rotating wing joint and a cover plate. The driving torsion spring is placed inside the driving torsion spring installation groove, the locking pin is arranged inside the locking pin limiting hole, the upper part of the locking pin is sleeved with the locking pin compression spring, the rotating wing joint is arranged on the upper surface of the base, the driving torsion spring installation groove is opened at the side of the top end of the rotating wing joint, and the locking pin limiting hole is opened at the side of the top end of the rotating cylinder sleeve. The present invention can realize the rapid deployment, accurate positioning and reliable locking of the wing, and the mechanism has reasonable design, simple and quick implementation, regular shape. The design concept of a single torsion spring effectively reduces the thickness of the entire rotation locking mechanism, increases the effective use space of the UAV, the limit locking mechanism occupies a small space, and the locking is firm. When the wing is fully deployed, the locking pin is pressed into the locking pin limiting hole by the locking pin compression spring to lock the wing.

Description

Technical Field

[0001] The present invention relates to a locking structure for an unmanned aerial vehicle, and particularly to a wing rotation locking mechanism for a tube-launched unmanned aerial vehicle, belonging to the technical field of unmanned aerial vehicles. Background Art

[0002] The tube-launched unmanned aerial vehicle is folded through a folding mechanism, effectively reducing the space size. Adopting the tube-launching method, it has the characteristics of low cost, high cost performance, and small size. Moreover, the flexible mobility and regional adaptability of the tube-launched unmanned aerial vehicle have attracted a large number of domestic and foreign experts to conduct in-depth research on it.

[0003] The wing folding mechanism generally includes two parts: a folding and unfolding mechanism and a limiting and locking mechanism. Divided by the driving method, the wing folding and unfolding mechanism can be roughly divided into an electric drive type and a spring drive type. Electric drive type: The motor is used as the power to drive the wing movement through a transmission mechanism, which is convenient for control and can be actively folded after unfolding. The disadvantages are slow unfolding speed, complex structure, and the need for an additional driving motor. Spring elastic force drive type: The energy is stored by the deformation of the spring, and the wing is driven by the spring. It has a fast unfolding speed, simple structure, and does not require an additional power device.

[0004] For the tube-launched unmanned aerial vehicle, the spring drive method is more suitable. At present, most of the research focuses on the independent driving form of two torsion springs for two wings, but there are generally problems such as complex structure, inconvenient installation, and large occupied space. The limiting and locking mechanisms of the folding mechanism include slider type, block type, ball head pin type, etc., and usually have disadvantages such as large structural volume and unstable locking. Summary of the Invention

[0005] The purpose of the present invention is to provide a wing rotation locking mechanism for a tube-launched unmanned aerial vehicle to solve the problems mentioned in the above background art, that is, the independent driving form of two torsion springs for two wings, but there are generally problems such as complex structure, inconvenient installation, and large occupied space. The limiting and locking mechanisms of the folding mechanism include slider type, block type, ball head pin type, etc., and usually have disadvantages such as large structural volume and unstable locking.

[0006] To achieve the above object, the present invention provides the following technical solution: A barrel-launched UAV wing rotation locking mechanism, including a base, a driving torsion spring, a locking pin, a locking pin compression spring, a shock-absorbing rubber pad, a rotating wing joint and a cover plate. A driving torsion spring installation groove is provided on the side of the top end of the base. A rotating shaft is fixedly installed in the middle of the top end of the base. Symmetrically arranged rotating convex block limiting grooves are provided on both sides of the rotating shaft. A base installation hole penetrating the base is provided at the bottom end of the driving torsion spring installation groove. The base is fixed on the UAV fuselage by threading and installing screws in the base installation hole. A driving torsion spring is placed inside the driving torsion spring installation groove. A locking pin limiting hole is provided on the side of the rotating shaft. A locking pin is provided inside the locking pin limiting hole. A locking pin compression spring is sleeved on the upper part of the locking pin. A rotating wing joint is provided on the upper surface of the base. A driving torsion spring installation groove is provided on the side of the top end of the rotating wing joint. A driving torsion spring horizontal limiting groove communicating with the driving torsion spring installation groove is provided on one side of the driving torsion spring installation groove. A rotating cylinder sleeve is fixedly installed in the middle of the driving torsion spring installation groove. Two symmetrically arranged rotating convex blocks are fixedly installed on both sides of the top end of the rotating cylinder sleeve. A locking pin limiting hole is provided on the side of the top end of the rotating cylinder sleeve. The driving torsion spring is placed in the driving torsion spring installation groove, and the driving torsion spring horizontal limiting end of the driving torsion spring is placed in the driving torsion spring horizontal limiting groove. The rotating convex block is placed in the rotating convex block limiting groove. The rotating shaft sleeve is sleeved on the rotating shaft. The upper end of the locking pin passes through the locking pin limiting hole.

[0007] As a preferred technical solution of the present invention, a driving torsion spring vertical limiting hole is provided inside the driving torsion spring installation groove, and the vertical limiting end of the driving torsion spring is inserted into the driving torsion spring vertical limiting hole to limit the sway of the driving torsion spring.

[0008] As a preferred technical solution of the present invention, shock-absorbing rubber pads are symmetrically placed at the centers of both ends inside the rotating convex block limiting groove. When the wing is unfolded, the shock-absorbing rubber pads can effectively reduce the vibration caused by the collision between the rotating convex block and the rotating convex block limiting groove.

[0009] As a preferred technical solution of the present invention, a locking pin pulling hole is provided at the top of the locking pin, and a pull ring passes through the inside of the locking pin pulling hole. At this time, the locking pin compression spring presses the locking pin into the locking pin limiting hole.

[0010] As a preferred technical solution of the present invention, two wing installation limiting holes are provided at both ends of the rotating wing joint, and wings are fixedly installed inside the wing installation limiting holes.

[0011] As a preferred technical solution of the present invention, a cover plate is fixedly provided at the top of the rotating shaft sleeve and is fixed by cover plate installation holes and screws to prevent the rotating wing joint from loosening up and down.

[0012] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0013] A wing rotation locking mechanism for a tube-launched unmanned aerial vehicle according to the present invention can achieve rapid deployment, accurate positioning and reliable locking of the wing. Moreover, the mechanism is reasonably designed, simply and quickly implemented, and has a regular shape. The design concept of a single torsion spring effectively reduces the thickness of the entire rotation locking mechanism, increases the effective usable space of the unmanned aerial vehicle, the limit locking mechanism occupies a small space, and the locking is firm. When the wing is fully deployed, the locking pin is pressed into the locking pin limit hole by the locking pin compression spring to lock the wing. The shock-absorbing rubber pad provided inside the rotation locking mechanism effectively reduces the vibration caused by the collision during wing deployment. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is an exploded assembly schematic diagram of the present invention;

[0015] Figure 2 is an assembly schematic diagram of the present invention;

[0016] Figure 3 is a partial cross-sectional schematic diagram of the present invention;

[0017] Figure 4 is a rotation schematic diagram of the present invention;

[0018] Figure 5 is a schematic diagram of the base structure of the present invention;

[0019] Figure 6 is a schematic diagram of the driving torsion spring structure of the present invention;

[0020] Figure 7 is a schematic diagram of the locking structure of the present invention;

[0021] Figure 8 is a schematic diagram of the shock-absorbing rubber pad structure of the present invention;

[0022] Figure 9 is a schematic diagram of the upper surface structure of the rotating wing joint of the present invention;

[0023] Figure 10 is a schematic diagram of the lower surface structure of the rotating wing joint of the present invention;

[0024] Figure 11 is a schematic diagram of the cover plate.

[0025] In the figure: 1. Base; 1-1. Base mounting hole; 1-2. First cover plate mounting hole; 1-3. Driving torsion spring vertical limiting hole; 1-4. First locking pin limiting hole; 1-5. Rotating convex block limiting groove; 1-6. First driving torsion spring mounting groove; 1-7. Rotating shaft; 2. Driving torsion spring; 2-1. Driving torsion spring vertical limiting end; 2-2. Driving torsion spring horizontal limiting end; 3. Locking pin; 3-1. Locking pin pulling hole; 4. Locking pin compression spring; 5. Vibration damping rubber pad; 6. Rotating wing joint; 6-1. Second locking pin limiting hole; 6-2. Wing mounting limiting hole; 6-3. Wing joint; 6-4. Rotating convex block; 6-5. Driving torsion spring horizontal limiting groove; 6-6. Rotating shaft sleeve; 6-7. Second driving torsion spring mounting groove; 7. Cover plate; 7-1. Second cover plate mounting hole; 8. Airframe; 9. Wing. Detailed implementation manner

[0026] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0027] Please refer to Figures 1-11, the present invention provides a technical solution for a wing rotation locking mechanism of a tube-launched unmanned aerial vehicle: A wing rotation locking mechanism of a tube-launched unmanned aerial vehicle includes a base 1, a driving torsion spring 2, a locking pin 3, a locking pin compression spring 4, a shock-absorbing rubber pad 5, a rotating wing joint 6, and a cover plate 7. A first driving torsion spring installation groove 1-6 is provided on the side of the top end of the base 1. A rotating shaft 1-7 is fixedly installed in the middle of the top end of the base 1. Symmetrically arranged rotating convex block limiting grooves 1-5 are provided on both sides of the rotating shaft 1-7. A base installation hole 1-1 penetrating the base 1 is provided at the bottom end of the first driving torsion spring installation groove 1-6. The base 1 is fixed on the unmanned aerial vehicle fuselage 8 by threadedly installing screws inside the base installation hole 1-1. A driving torsion spring 2 is placed inside the first driving torsion spring installation groove 1-6. A first locking pin limiting hole 1-4 is provided on the side of the rotating shaft 1-7. A locking pin 3 is provided inside the first locking pin limiting hole 1-4. A locking pin compression spring 4 is sleeved on the upper part of the locking pin 3. A rotating wing joint 6 is provided on the upper surface of the base 1. A second driving torsion spring installation groove 6-7 is provided on the side of the top end of the rotating wing joint 6. A driving torsion spring horizontal limiting groove 6-5 communicating with the second driving torsion spring installation groove 6-7 is provided on one side of the second driving torsion spring installation groove 6-7. A rotating cylinder sleeve 6-6 is fixedly installed in the middle of the second driving torsion spring installation groove 6-7. Two symmetrically arranged rotating convex blocks 6-4 are fixedly installed on both sides of the top end of the rotating cylinder sleeve 6-6. A second locking pin limiting hole 6-1 is provided on the side of the top end of the rotating cylinder sleeve 6-6. The driving torsion spring 2 is placed in the second driving torsion spring installation groove 6-7, and the driving torsion spring horizontal limiting end 2-2 of the driving torsion spring 2 is placed in the driving torsion spring horizontal limiting groove 6-5. The rotating convex block 6-4 is placed in the rotating convex block limiting groove 1-5. The rotating cylinder sleeve 6-6 is sleeved on the rotating shaft 1-7. The upper end of the locking pin 3 passes through the second locking pin limiting hole 6-1.

[0028] A driving torsion spring vertical limiting hole 1-3 is provided inside the first driving torsion spring installation groove 1-6, and the vertical limiting end 2-1 of the driving torsion spring 2 is inserted into the driving torsion spring vertical limiting hole 1-3 to limit the shaking of the driving torsion spring 2.

[0029] Shock-absorbing rubber pads 5 are symmetrically placed at both ends of the rotating convex block limiting groove 1-5. When the wing 9 is deployed, the shock-absorbing rubber pads 5 can effectively reduce the vibration caused by the collision between the rotating convex block 6-4 and the rotating convex block limiting groove 1-5.

[0030] A locking pin pulling hole 3-1 is provided at the top of the locking pin 3, and a pull ring passes through the inside of the locking pin pulling hole 3-1. At this time, the locking pin compression spring 4 presses the locking pin 3 into the first locking pin limiting hole 1-4.

[0031] Two wing installation limiting holes 6-2 are provided at both ends of the rotating wing joint 6, and a wing 9 is fixedly installed inside the wing installation limiting holes 6-2.

[0032] A cover plate 7 is fixedly provided at the top of the rotating shaft sleeve 6-6 and is fixed through the cover plate mounting holes 7-1, the first cover plate mounting holes 1-2 and screws to prevent the rotary wing joint 6 from loosening up and down.

[0033] According to Figures 1-3 As shown, specifically, the base 1, the locking pin 3, the rotary wing joint 6, and the cover plate 7 are all made of 7075 aviation aluminum alloy, which meets sufficient service strength and makes the mechanism lighter in weight, conducive to reducing the weight of the UAV. The driving torsion spring 2 and the locking pin compression spring 4 are made of SWPB spring steel, and the shock-absorbing rubber pad 5 is made of vulcanized rubber.

[0034] According to Figures 1-9 , specifically, the rotary locking mechanism can rotate the wing 9 by 90°. When the wing 9 is retracted, the wing 9 is parallel to the fuselage 8; the driving torsion spring 2 is a single torsion spring, and the driving torsion spring 2 is provided with limits in the vertical and horizontal directions.

[0035] During specific use, for a wing rotary locking mechanism of a tube-launched UAV according to the present invention, when the wing 9 is deployed, the wing 9 is perpendicular to the fuselage 8, and the locking pin compression spring 4 presses the locking pin 3 into the first locking pin limiting hole 1-4 to complete the locking of the wing 9. By pulling the thin string or metal ring passing through the locking pin pulling hole 3-1, the locking pin 3 is pulled up to make it leave the first locking pin limiting hole 1-4, and the wing 9 can be rotated and folded clockwise.

[0036] In the description of the present invention, it should be understood that the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0037] In the present invention, unless otherwise clearly specified and limited, for example, it can be fixedly connected, detachably connected, or integrated; it can be mechanically connected, electrically connected; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the internal communication of two elements or the interaction relationship between two elements. Unless otherwise clearly limited, for those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

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

Claims

1. A barrel-launched UAV wing rotation locking mechanism, comprising a base (1), a driving torsion spring (2), a locking pin (3), a locking pin compression spring (4), a shock-absorbing rubber pad (5), a rotating wing joint (6), and a cover plate (7). It is characterized in that: On the side of the top end of the base (1), a first driving torsion spring installation groove (1-6) is provided. In the middle of the top end of the base (1), a rotating shaft (1-7) is fixedly installed. On both sides of the rotating shaft (1-7), symmetrically arranged rotating convex block limiting grooves (1-5) are provided. At the bottom end of the first driving torsion spring installation groove (1-6), a base installation hole (1-1) penetrating the base (1) is provided. The base (1) is fixed on the UAV fuselage (8) by threading and installing screws in the base installation hole (1-1). Inside the first driving torsion spring installation groove (1-6), a driving torsion spring (2) is placed. On the side of the rotating shaft (1-7), a first locking pin limiting hole (1-4) is provided. Inside the first locking pin limiting hole (1-4), a locking pin (3) is provided. On the upper part of the locking pin (3), a locking pin compression spring (4) is sleeved. On the top of the locking pin (3), a locking pin pulling hole (3-1) is provided. On the upper surface of the base (1), a rotating wing joint (6) is provided. On the side of the top end of the rotating wing joint (6), a second driving torsion spring installation groove (6-7) is provided. On one side of the second driving torsion spring installation groove (6-7), a driving torsion spring horizontal limiting groove (6-5) communicating with the second driving torsion spring installation groove (6-7) is provided. In the middle of the second driving torsion spring installation groove (6-7), a rotating shaft sleeve (6-6) is fixedly installed. On both sides of the top end of the rotating shaft sleeve (6-6), two symmetrically arranged rotating convex blocks (6-4) are fixedly installed. On the side of the top end of the rotating shaft sleeve (6-6), a second locking pin limiting hole (6-1) is provided. The driving torsion spring (2) is placed in the second driving torsion spring installation groove (6-7), and the driving torsion spring horizontal limiting end (2-2) of the driving torsion spring (2) is placed in the driving torsion spring horizontal limiting groove (6-5). The rotating convex block (6-4) is placed in the rotating convex block limiting groove (1-5). The rotating shaft sleeve (6-6) is sleeved on the rotating shaft (1-7). The upper end of the locking pin (3) passes through the second locking pin limiting hole (6-1). Inside the first driving torsion spring installation groove (1-6), a driving torsion spring vertical limiting hole (1-3) is provided, and the vertical limiting end (2-1) of the driving torsion spring (2) is inserted into the driving torsion spring vertical limiting hole (1-3) to limit the shaking of the driving torsion spring (2). At the two ends of the rotating convex block limiting groove (1-5), shock-absorbing rubber pads (5) are symmetrically placed at the center. When the wing (9) is unfolded, the shock-absorbing rubber pads (5) can effectively reduce the vibration caused by the collision between the rotating convex block (6-4) and the rotating convex block limiting groove (1-5).

2. A barrel-launched UAV wing rotation locking mechanism according to claim 1, It is characterized in that: The inside of the locking pin pulling hole (3-1) passes through the pull ring, and at this time, the locking pin compression spring (4) presses the locking pin (3) into the first locking pin limiting hole (1-4).

3. A wing rotation locking mechanism for a tube-launched unmanned aerial vehicle according to claim 1, characterized in that: Both ends of the rotating wing joint (6) are provided with two wing installation limiting holes (6-2), and the wing (9) is fixedly installed inside the wing installation limiting hole (6-2).

4. A wing rotation locking mechanism for a tube-launched unmanned aerial vehicle according to claim 1, characterized in that: A cover plate (7) is fixedly provided at the top of the rotating shaft sleeve (6-6), and is fixed by the second cover plate installation hole (7-1), the first cover plate installation hole (1-2) and screws, so as to prevent the rotating wing joint (6) from loosening up and down.

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