Cylinder shooting type unmanned aerial vehicle

Abstract

The utility model discloses a cylindrical unmanned aerial vehicle. The cylindrical unmanned aerial vehicle comprises a fuselage, a left wing assembly, a right wing assembly, a wing mounting base, a tilting mechanism and a wing rotating mechanism, the fuselage is fixedly connected with the wing mounting base; the left wing assembly and the right wing assembly are fixedly connected with the wing mounting base through the wing rotating mechanism; and the tilting mechanism is fixedly connected with the wing mounting base. When the left wing and the right wing are unfolded, the rocker arm of the left wing pushes away the locking plate through the extending part of the side edge, close to the clamping groove, of the locking plate, the tilting spring relieves constraint and pushes up the tilting bolt to drive the tilting limiting nut to move upwards, and a flash at the lower end of the tilting limiting nut drives the tilting seat to rotate so as to drive the wings to tilt. The unmanned aerial vehicle is small in occupied space in a folded state in the cylinder, and can automatically tilt and lock at the moment when the wings are unfolded, so that the mounting angle of the wings is changed, and the optimal lift-drag ratio flight state of the unmanned aerial vehicle is achieved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) design technology, and in particular to a tube-launched UAV. Background Technology

[0002] After rapid development in recent years, unmanned aerial vehicle (UAV) technology has gradually become an important part of national defense and military air power. In particular, cannon-launched UAVs, with their advantages of small size, portability, rapid response, and ability to launch in dense formations, have found widespread application in the military field. During the design of cannon-launched UAVs, the wings typically have an installation angle of 2° to 5° to ensure better lift-drag characteristics during flight. However, under normal circumstances, when the wings have a preset installation angle, the wing height space is significantly reduced when folded, resulting in insufficient longitudinal space and an excessive gap between the wings and the fuselage.

[0003] Taking a certain type of cannon-launched UAV as an example, the wing chord of the UAV is 100mm. After folding, the thickness of the four wings (top and bottom) and the gaps remain at 66mm. If the preset installation angle of the front wing is 4°, the longitudinal space occupied by the front wing will increase by about 14mm. Compared with the remaining longitudinal height of the fuselage itself, the proportion occupied is relatively high, and the space utilization rate is greatly reduced. Summary of the Invention

[0004] Purpose of the invention: In order to solve the problem of excessive longitudinal space when the wings of a tube-launched UAV are folded after the preset installation angle, a simple and reliable automatic wing tilting mechanism is designed. When the wings are folded, the wing can be pressed to reduce the space between the wing and the fuselage. When the wings are unfolded, they can automatically tilt and lock to ensure that the wings are in the optimal installation angle position, thereby ensuring the best cruise lift-drag characteristics of the entire aircraft.

[0005] This utility model discloses a tube-launched unmanned aerial vehicle, including a fuselage 10, left and right wing assemblies 21, a wing mounting base 17, a tilting mechanism 22, and a wing rotation mechanism;

[0006] The fuselage 10 is fixedly connected to the wing mounting base 17;

[0007] The left and right wing assemblies 21 are fixedly connected to the wing mounting base 17 via a wing rotation mechanism;

[0008] The tilting mechanism 22 is fixedly connected to the wing mounting base 17.

[0009] Including locking mechanisms;

[0010] The left and right wing assemblies 21 have locking holes adjacent to the wing rotation mechanism, and the locking mechanism is located in the locking holes;

[0011] There is a height difference surface between the fuselage 10 and the left and right wing assemblies 21. The buffer pad 8 covers the height difference surface and restricts the position of the wings after they are deployed.

[0012] The wing rotation mechanism includes an upper cover plate 1, a rotating shaft 6, and a lubrication pad 7;

[0013] The upper cover plate 1, the rotating shaft 6, and the lubricating pad 7 are stacked on top of each other in the vertical direction.

[0014] The left and right wing assemblies 21 include a left wing 20, a left wing rocker arm 2, a right wing 4, a right wing rocker arm 5, and a torsion spring 3;

[0015] The left wing 20 is fixedly connected to the left wing rocker arm 2;

[0016] The right wing 4 is fixedly connected to the right wing rocker arm 5;

[0017] The left wing rocker arm 2 and the right wing rocker arm 5 are stacked one on top of the other, with the left wing rocker arm 2 located on top.

[0018] The left and right wing assemblies 21 are deployed and folded around the rotation center of the wing rotation mechanism;

[0019] The exposed straight arms of the torsion spring 3 are inserted into the slots of the left wing rocker arm 2 and the right wing rocker arm 5, respectively, and connected to the left and right wing assemblies 21.

[0020] When the torsion spring 3 is twisted to its maximum angle, the left and right wings fold. When the torsion spring 3 returns to its minimum angle, the left and right wings unfold. The torsion spring has a certain pre-rotation angle to ensure that the left and right wings can unfold in place.

[0021] The locking mechanism includes a locking pin 23, an unfolding locking spring 24, and an unfolding locking bottom nut 25;

[0022] The unfolding locking pin 23, unfolding locking spring 24, and unfolding locking bottom nut 25 are fixedly connected from top to bottom.

[0023] The tilting mechanism 22 includes a right bolt 9, a locking plate 11, a left bolt 12, a tilting spring 13, a tilting bolt 14, a tilting limiting nut 15, an adjusting pad 16, a tilting seat 18, and a tilting shaft 19;

[0024] The right bolt 9 passes through the through hole at the right end of the locking piece 11 and is fixedly connected to the wing mounting base 17;

[0025] The left bolt 12 passes through the left end slot of the locking piece 11 and is fixedly connected to the wing mounting base 17.

[0026] The tilting seat 18 is fixedly connected to the adjusting pad 16;

[0027] The tilting spring 13 is sleeved on the tilting bolt 14 and is located below the middle of the locking piece 11;

[0028] The tilting limiting nut 15 is fitted onto the tilting bolt 14 and is located below the tilting seat 18. The lower end of the tilting limiting nut 15 has a flash.

[0029] The locking piece 11 extends outward from the side near the slot;

[0030] The tilting seat 18 is connected to the mounting base 17 via the tilting shaft 19 and can rotate around the tilting shaft 19.

[0031] When the left wing 20 and right wing 4 are folded, press down on the tilt bolt 14 and push the locking plate 11 towards the tilt bolt 14, so that the lower surface of the locking plate 11 presses against the bolt head of the tilt bolt 14, thereby locking the left bolt 12 into the slot of the locking plate 11. The tilt bolt 14 is constrained downward by the locking plate 11, and the tilt spring 13 is compressed. Manually pressing down on the folded left and right wing assemblies 21 moves the tilt seat 18 downward, thereby causing the left and right wings to fit against the fuselage 10.

[0032] The thickness of the adjusting pad 16 affects the fit between the left and right wings and the fuselage 10. If the thickness is too small, the distance between the wings and the fuselage will be too small, and the left and right wings will not be able to fold in. If the thickness is too large, the distance between the wings and the fuselage will be too high, and folding and retraction will waste space. Therefore, by selecting an adjusting pad of appropriate thickness, space can be fully utilized.

[0033] When the left wing 20 and the right wing 4 are deployed, the left wing rocker arm 2 pushes open the locking plate 11 through the side extension of the locking plate 11 near the slot. The tilt spring 13 is released from its constraint and pushes up the tilt bolt 14, which drives the tilt limiting nut 15 upward. The flash at the lower end of the tilt limiting nut 15 drives the tilt seat 18 to rotate, thereby causing the left and right wings to tilt.

[0034] The tilt limiting nut 15 is fitted onto the tilt bolt 14. When screwed in relative to the tilt spring 13, the tilt of the left and right wings decreases; when screwed out relative to the tilt spring 13, the tilt of the left and right wings increases.

[0035] When the left wing 20 and the right wing 4 are folded, the slots of the left wing 20 and the right wing 4 are 180° out of phase with their centers, the deployment locking spring 24 is compressed, and the upper part of the deployment locking pin 23 is limited by the lower surface of the left wing rocker arm 2; when the left wing 20 and the right wing 4 are deployed, the left wing 20 and the right wing 4 are each rotated 90°, and the slots are in the same phase, the deployment locking pin 23 is aligned with the slot hole 27 of the left wing and the small hole 26 of the upper cover plate, and the deployment locking pin 23 is pushed out by the deployment locking spring 24 and inserted into the slot hole 27 of the left wing, thereby locking the left and right wings after they are deployed.

[0036] In the vertical direction, the upper cover plate 1, the rotating shaft 6, the adjusting pad 16 and the tilting seat 18 are fixedly connected through the hollow part of the wing mounting base 17. They are fixed by screws through the six corresponding screw holes on the upper cover plate 1, the rotating shaft 6, the lubricating pad 7, the adjusting pad 16 and the tilting seat 18. The size of the hollow part of the wing mounting base 17 is slightly larger than that of the adjusting pad 16 so that the adjusting pad 16 has room to move up and down. The side of the adjusting pad 16 closest to the buffer pad 8 is thicker than the other side, so that when the wing is folded, the left and right wing assemblies 21 can remain horizontal.

[0037] In this utility model, preferably, the body 10 is made of carbon fiber.

[0038] Beneficial effects: 1. This utility model provides a novel tilt wing design for a cannon-launched UAV. When folded inside the cannon, it occupies less space. When the wing is unfolded, it can automatically tilt and lock, realizing the change of the wing installation angle to achieve the UAV's optimal lift-to-drag ratio flight state.

[0039] 2. The design is compact, simple in structure, small in size, lightweight, and highly reliable. It can be extended to be used in the wing design of various folding drones. Attached Figure Description

[0040] Figure 1 A schematic diagram of the wing mechanism of a cannon-launched UAV that can automatically tilt.

[0041] Figure 2 A diagram showing the unfolded wing mechanism of a cannon-launched UAV that can automatically tilt.

[0042] Figure 3 A schematic diagram of the folded state of the wing mechanism of an automatically tilting tube-fired UAV;

[0043] Figure 4 A schematic diagram of the wing mechanism of an automatically tilting, tube-launched UAV in its deployed state;

[0044] Figure 5 This is a schematic diagram of the internal structure of the wing of a cannon-launched UAV that can automatically tilt.

[0045] Figure 6 A horizontal cross-sectional view of the wing mechanism of a cannon-launched UAV that can automatically tilt.

[0046] Figure 7 A cross-sectional view of the wing mechanism of an automatically tilting, tube-launched UAV in its folded state;

[0047] Figure 8 This is a cross-sectional view of the wing mechanism of an automatically tilting, tube-launched UAV in its deployed state. Detailed Implementation

[0048] The automatically tilting tube-launched drone wing proposed in this invention occupies less longitudinal space when folded, and the drone's wing installation angle can be preset when unfolded, so that the wing can ensure sufficient cruising efficiency and occupy as little folding space as possible when folded.

[0049] In the attached diagram: 1. Top cover plate; 2. Left wing rocker arm; 3. Torsion spring; 4. Right wing; 5. Right wing rocker arm; 6. Rotary shaft; 7. Lubricating pad; 8. Buffer pad; 9. Right bolt; 10. Fuselage; 11. Locking plate; 12. Left bolt; 13. Tilting spring; 14. Tilting bolt; 15. Tilting limit nut; 16. Adjusting pad; 17. Wing mounting base; 18. Tilting seat; 19. Tilting shaft; 20. Left wing; 21. Left and right wing assemblies; 22. Tilting mechanism; 23. Deployment locking pin; 24. Deployment locking spring; 25. Deployment locking bottom nut; 26. Top cover plate hole; 27. Left wing slot.

[0050] like Figure 1 As shown, a tube-launched unmanned aerial vehicle includes a fuselage 10, left and right wing assemblies 21, a wing mounting base 17, a tilting mechanism 22, and a small hole 26 on the edge of the upper cover plate.

[0051] like Figure 2 As shown, in the vertical direction, the upper cover plate 1, the rotating shaft 6, the adjusting pad 16 and the tilting seat 18 are fixedly connected through the hollow part of the wing mounting base 17. They are fixed by screws through the six corresponding screw holes on the upper cover plate 1, the rotating shaft 6, the lubricating pad 7, the adjusting pad 16 and the tilting seat 18. The size of the hollow part of the wing mounting base 17 is slightly larger than that of the adjusting pad 16 so that the adjusting pad 16 has room to move up and down.

[0052] The rotating shaft 6 is located in the hole at the symmetrical center of the left and right wing assemblies 21;

[0053] The torsion spring 3 is located in the slot of the left and right wing assemblies 21;

[0054] The fuselage 10 is fixedly connected to the wing mounting base 17;

[0055] The buffer pad 8 covers the height difference surface between the fuselage 10 and the left and right wing assemblies 21.

[0056] The left and right wing assemblies 21 include a left wing 20, a left wing rocker arm 2, a right wing 4, and a right wing rocker arm 5.

[0057] The left wing 20 is fixedly connected to the left wing rocker arm 2;

[0058] The right wing 4 is fixedly connected to the right wing rocker arm 5;

[0059] The left wing rocker arm 2 and the right wing rocker arm 5 are stacked one on top of the other, with the left wing rocker arm 2 located on top.

[0060] The left and right wing assemblies 21 are sandwiched between the upper cover plate 1 and the adjusting pad 16, and are unfolded and folded with the rotating shaft 6 as the rotation center;

[0061] like Figure 6 As shown, the two exposed straight arms of the torsion spring 3 are respectively inserted into the slots of the left wing rocker arm 2 and the right wing rocker arm 5 and connected to the left and right wing assemblies 21.

[0062] The buffer pad 8 restricts the position of the left and right wings after they are deployed.

[0063] Example 1:

[0064] like Figure 3 as well as Figure 7 As shown, in the folded state, the left end of the locking plate 11 is fully inserted into the left bolt 12, the top of the tilt bolt 14 is abutted by the middle part of the locking plate 11, and the tilt limiting nut 15 is offset downwards. At this time, the tilt seat 18 is disengaged from the limit of the tilt limiting nut 15 and can rotate around the tilt axis 19. The tilt spring 13 on the tilt bolt 14 is in a compressed state and does not exert force on the tilt seat 18. The lower part of the left and right wing assemblies 21 is connected to the adjusting pad 16, and the lower part of the adjusting pad 16 is connected to the tilt seat 18. Thus, at this time, applying downward pressure to the left and right wings or relying on the size constraint of the launch tube wall can make the left and right wings fit against the fuselage wall, reducing the longitudinal height of the UAV in the folded state.

[0065] When the left and right wings are folded, the left and right wing slots are 180° out of phase with their centers apart. The deployment locking spring 24 inside the slot is compressed, and the deployment locking pin 23 is limited above the lower surface of the left wing rocker arm 2.

[0066] Example 2:

[0067] like Figure 4 as well as Figure 8 As shown, during the deployment of the left and right wings, the left wing rocker arm 2 pushes open the protruding part at the left end of the locking plate 11, causing the locking plate 11 to rotate around the right bolt 9. At the same time, the middle part of the locking plate 11 also moves open.

[0068] At this time, its interior, such as Figure 5 As shown, without the obstruction of the locking plate 11, the tilt bolt 14 is pushed upward by the tilt spring 13, while the tilt limiting nut 15 at the bottom of the tilt bolt 14 is blocked by the tilt seat 18. Thus, the elastic force released by the tilt spring 13 drives the tilt seat 18 to rotate, and the left and right wings also rotate with the tilt seat 18 until they reach the limited position. At the same time, the deployment of the left and right wings stops after impacting the buffer pad 8, reaching the final deployment position.

[0069] like Figure 5 As shown, when the left and right wings also rotate with the tilt seat 18 until they reach the specified position, the tilt angle of the wings depends on the rotation angle of the tilt seat. By screwing the tilt limiting nut 15 into the tilt spring 13, the rotation angle of the tilt seat can be reduced, thereby causing the tilt of the left and right wings to decrease; by screwing the tilt limiting nut 15 out of the tilt spring 13, the rotation angle of the tilt seat can be increased, thereby causing the tilt of the left and right wings to increase.

[0070] When the left and right wings are deployed, each wing rotates 90° and the slots are on the same phase. The deployment locking pin 23 aligns with the slot 27 of the left wing and is pushed out by the deployment locking spring 24 and inserted into the slot 27 of the left wing, thereby locking the left and right wings after deployment.

[0071] When the wings need to be folded, the locking pin 23 is unfolded by using the small hole reserved in the cover plate to compress the unfolding locking spring 24 and release it from the screw hole to unlock it.

[0072] This utility model provides a tube-launched unmanned aerial vehicle (UAV). There are many methods and approaches to implement this technical solution. The above description is only a preferred embodiment of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model. All components not explicitly stated in this embodiment can be implemented using existing technology.

Claims

1. A tube-launched unmanned aerial vehicle, characterized in that: It includes the fuselage (10), left and right wing assemblies (21), wing mounting base (17), tilting mechanism (22) and wing rotation mechanism; The fuselage (10) is fixedly connected to the wing mounting base (17); The left and right wing assemblies (21) are fixedly connected to the wing mounting base (17) via a wing rotation mechanism; The tilting mechanism (22) is fixedly connected to the wing mounting base (17); The tilting mechanism (22) includes a right bolt (9), a locking plate (11), a left bolt (12), a tilting spring (13), a tilting bolt (14), a tilting limiting nut (15), an adjusting pad (16), a tilting seat (18), and a tilting shaft (19); The right bolt (9) passes through the through hole at the right end of the locking piece (11) and is fixedly connected to the wing mounting base (17); The left bolt (12) passes through the left end slot of the locking piece (11) and is fixedly connected to the wing mounting base (17). The tilting seat (18) is fixedly connected to the adjusting pad (16); The tilting spring (13) is sleeved on the tilting bolt (14) and located below the middle of the locking piece (11); The tilting limiting nut (15) is fitted onto the tilting bolt (14) and located below the tilting seat (18). The lower end of the tilting limiting nut (15) has a flash. The locking piece (11) extends outward from the side near the slot; The tilting seat (18) is connected to the mounting base (17) via the tilting shaft (19) and can rotate around the tilting shaft (19); The left and right wing assemblies (21) include a left wing (20), a left wing rocker arm (2), a right wing (4), a right wing rocker arm (5), and a torsion spring (3); The left wing (20) is fixedly connected to the left wing rocker arm (2); The right wing (4) is fixedly connected to the right wing rocker arm (5); The left wing rocker arm (2) and the right wing rocker arm (5) are stacked one on top of the other, with the left wing rocker arm (2) located on top. The left and right wing assemblies (21) are deployed and folded around the rotation center of the wing rotation mechanism; When the left wing (20) and right wing (4) are folded, press the tilt bolt (14) and push the locking plate (11) toward the tilt bolt (14), so that the lower surface of the locking plate (11) presses against the bolt head of the tilt bolt (14), thereby the left bolt (12) is locked in the slot of the locking plate (11), the tilt bolt (14) is constrained downward by the locking plate (11), the tilt spring (13) is compressed, and manually press down the folded left and right wing assemblies to drive the tilt seat (18) downward, thereby driving the left and right wings to fit against the fuselage.

2. The tube-launched UAV according to claim 1, characterized in that: Including locking mechanisms; The left and right wing assemblies (21) have locking holes adjacent to the wing rotation mechanism, and the locking mechanism is located in the locking holes.

3. The tube-launched UAV according to claim 2, characterized in that: The wing rotation mechanism includes an upper cover plate (1), a rotating shaft (6), and a lubrication pad (7); The upper cover plate (1), the rotating shaft (6) and the lubricating pad (7) are stacked on top of each other in the vertical direction.

4. A cannon-launched UAV according to claim 3, characterized in that: The exposed straight arms of the torsion spring (3) are inserted into the slots of the left wing rocker arm (2) and the right wing rocker arm (5) respectively, and connected to the left and right wing assemblies (21); There is a height difference surface between the left and right wing assemblies (21) and the fuselage (10), and the buffer pad (8) covers the height difference surface.

5. A cannon-launched UAV according to claim 4, characterized in that: The locking mechanism includes an unfolding locking pin (23), an unfolding locking spring (24), and an unfolding locking bottom nut (25); The unfolding locking pin (23), unfolding locking spring (24), and unfolding locking bottom nut (25) are fixedly connected from top to bottom.

6. A cannon-launched UAV according to claim 5, characterized in that: When the left wing (20) and the right wing (4) are deployed, the left wing rocker arm (2) pushes open the locking plate (11) through the side extension of the locking plate (11) near the slot. The tilt spring (13) releases the constraint and pushes up the tilt bolt (14), which drives the tilt limit nut (15) upward. The lower end of the tilt limit nut (15) drives the tilt seat (18) to rotate, thereby driving the wing to tilt.

7. A cannon-launched UAV according to claim 6, characterized in that: The tilt limiting nut (15) is fitted onto the tilt bolt (14). When it is screwed in relative to the tilt spring (13), the tilt of the wing decreases; when it is screwed out relative to the tilt spring (13), the tilt of the left and right wings increases.

8. A cannon-launched UAV according to claim 7, characterized in that: When the left wing (20) and right wing (4) are folded, the slots of the left wing (20) and right wing (4) are 180° out of phase with their centers, the deployment locking spring (24) is compressed, and the deployment locking pin (23) is limited above the lower surface of the left wing rocker arm (2); when the left wing (20) and right wing (4) are unfolded, the left wing (20) and right wing (4) are each rotated 90°, the slots are in the same phase, the deployment locking pin (23) is aligned with the slot hole (27) of the left wing and the small hole (26) of the upper cover plate, the deployment locking pin (23) is pushed out by the deployment locking spring (24) and inserted into the slot hole (27) of the left wing, thereby locking the left wing (20) and right wing (4) after unfolding.

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