Unmanned aerial vehicle with folding wing structure

Abstract

The invention discloses an unmanned aerial vehicle with a folding wing structure, and relates to the technical field of unmanned aerial vehicles. The two wings are symmetrically installed on the two sides of the unmanned aerial vehicle body, each wing comprises a main wing plate and an auxiliary wing plate, a connecting structure is arranged between each main wing plate and the corresponding auxiliary wing plate, and the main wing plates and the auxiliary wing plates are rotationally matched through the connecting structures; the linkage mechanism comprises sealing grooves, limiting grooves, ribs, sealing plugs, communicating grooves and driving assemblys.By arranging the connecting structure and the linkage mechanism, when the airfoil is not used, the multiple ribs are correspondingly folded in the multiple sealing grooves in the main airfoil plate, the auxiliary airfoil plate can conveniently rotate around the rotating shaft to be folded and coincide with the main airfoil plate, and therefore the airfoil can be conveniently folded and coincide with the main airfoil plate; the overall occupied area of the unmanned aerial vehicle is effectively reduced, a user can carry the unmanned aerial vehicle conveniently, and when the unmanned aerial vehicle is used, the main wing plate and the auxiliary wing plate form an overall wing through the linkage mechanism, and normal work can be conducted.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle with a folding wing structure. Background Art

[0002] Drones are a new type of aircraft that are remotely controlled by users through a control system. They are widely used in military and civilian fields. Existing drones are divided into rotary-wing drones and fixed-wing drones. Most fixed-wing drones cannot have foldable wings. In order to facilitate the carrying of drones, the fixed wings need to be separated from the main body of the drone for carrying. When using the drone, the fixed wings need to be installed on the main body of the drone, which is more troublesome.

[0003] Chinese invention application number CN202010979958.5 discloses a wing folding structure of a UAV, which connects and limits the main wing panel and the auxiliary wing panel through a separate outer cover shell. In this way, the separate outer cover shell is easy to be lost, and after the main wing panel and the auxiliary wing panel are connected through the outer cover shell, the outer cover shell will affect the overall shape structure of the wing, which is not conducive to improving the working performance of the wing. Summary of the invention

[0004] The invention proposes a UAV with a folding wing structure, the purpose of which is to solve the problem in the traditional technology that after the main wing panel and the auxiliary wing panel are connected by an outer cover shell, the outer cover shell will affect the overall appearance structure of the wing and is not conducive to improving the working performance of the wing.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A UAV with a folding wing structure, comprising:

[0007] The drone body;

[0008] Wings, two of which are symmetrically mounted on both sides of the drone body, the wings comprising a main wing panel and an auxiliary wing panel, a connecting structure being arranged between the main wing panel and the auxiliary wing panel, wherein the main wing panel and the auxiliary wing panel are rotatably matched through the connecting structure;

[0009] A linkage mechanism, the linkage mechanism includes a sealing groove, a limiting groove, a rib, a sealing plug, a connecting groove and a driving assembly. A plurality of sealing grooves are provided in the main wing panel, and a plurality of the sealing grooves are slidably connected with ribs. A plurality of limiting grooves are provided in the auxiliary wing panel, and a plurality of the ribs pass through the connecting structure at one end away from the drone body, and slide in cooperation with the plurality of limiting grooves in a one-to-one correspondence. A plurality of the ribs are fixedly connected with a sealing plug at one end away from the auxiliary wing panel, and the sealing plug is sealingly and slidably connected in the sealing groove. A plurality of the sealing grooves are connected with the same connecting groove at one end away from the auxiliary wing panel. The connecting groove is provided in the main wing panel, and a driving assembly is connected at one end of the connecting groove away from the sealing groove, and the driving assembly is arranged in the main wing panel.

[0010] Preferably, the connecting structure includes a connecting block, a connecting frame and a rotating shaft, the connecting block is fixedly connected to the main wing panel, and the two connecting frames are fixedly connected to the auxiliary wing panel, wherein the gaps between the two connecting frames are located at both ends of the connecting block, the connecting block is rotatably connected with a rotating shaft, and the two ends of the rotating shaft are fixedly connected to the two connecting frames in a one-to-one correspondence, a plurality of connecting holes are penetrated through the connecting block, and a plurality of radial holes are penetrated through the rotating shaft, and the plurality of connecting holes and the plurality of radial holes correspond one-to-one to cooperate with the coaxial gaps of the plurality of ribs.

[0011] Preferably, the driving assembly includes a flat air cavity, an electric telescopic rod and a sealing block. The flat air cavity is opened inside the main engine wing panel, and the electric telescopic rod is installed in the flat air cavity. The output end of the electric telescopic rod is fixedly connected to the sealing block, and the sealing block is sealingly and slidably connected in the flat air cavity. The flat air cavity is connected to the connecting groove on the side away from the electric telescopic rod.

[0012] Preferably, the plurality of limit grooves are all arranged through one end away from the main wing plate, and are all threadedly connected with a blocking block.

[0013] Preferably, a buffer block is fixedly connected to one side of the blocking block close to the inner side of the limiting groove, the buffer block is made of elastic rubber, and the buffer block is extruded and matched with the end of the rib.

[0014] Preferably, a plurality of the ribs are connected with a buffer assembly, and the buffer assembly includes an installation groove, a solenoid valve, an axial groove, an inflation tube, an annular groove and an annular bag. The installation groove is opened through the middle of the sealing plug, and a solenoid valve is installed in the installation groove. One end of the installation groove is connected with the interior of the sealing groove, and the other end is connected with the axial groove. The axial groove is coaxially opened inside the rib, and an annular groove is coaxially opened on the outer peripheral side of the middle part of the rib. An annular bag is fixedly connected in the annular groove. The axial groove is connected with an inflation tube at one end away from the installation groove, and the inflation tube passes through the rib at one end away from the axial groove, and extends into the annular groove and is connected with the annular bag, wherein after the rib extends into the limiting groove, the annular bag is squeezed and contacted with the connecting hole and the radial hole in the connecting structure.

[0015] Preferably, a plurality of the sealing grooves are connected with a fixing ring, and a return spring is fixedly connected between the plurality of the fixing rings and the ends of the plurality of sealing plugs away from the ribs.

[0016] Preferably, the outer circumferences of the plurality of fixing rings are coaxially fixedly connected with annular clamping strips, the inner circumferences of the plurality of sealing grooves are connected with annular clamping grooves, and the plurality of annular clamping strips are snap-fitted with the plurality of annular clamping grooves in a one-to-one correspondence.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The present invention provides a connection structure and a linkage mechanism. When not in use, a plurality of ribs are correspondingly folded into a plurality of sealing grooves in the main wing panel, so that the auxiliary wing panel can rotate around the rotation axis and fold and overlap with the main wing panel, thereby effectively reducing the overall occupied area of ​​the UAV and making it convenient for users to carry it. When in use, the main wing panel and the auxiliary wing panel are formed into an integral wing through the linkage mechanism, so that normal operation can be performed.

[0019] 2. The present invention sets a linkage mechanism, and when the auxiliary wing panel is rotated to be flush with the main wing panel, the electric telescopic rod is controlled to work, and the output end of the electric telescopic rod is extended to push the sealing block to slide in the flat air cavity in a sealed manner. Under the action of air pressure, the sealing plug is pushed to drive the ribs to extend into the limiting grooves on the auxiliary wing panel, and then under the connection and limiting action of multiple ribs and the sealing grooves on the main wing panel and the limiting grooves on the auxiliary wing panel, the main wing panel and the auxiliary wing panel are connected into a whole, namely, the wing. Compared with the traditional technology of using external components to connect the main wing panel and the auxiliary wing panel, the linkage mechanism is located inside the main wing panel and the auxiliary wing panel, which effectively reduces the influence of external components on the external structural state of the wing and improves the working performance of the wing.

[0020] 3. The present invention sets a buffer component, and after the rib extends into the limit groove, controls multiple solenoid valves to be turned on. At this time, part of the high-pressure air in the sealing groove passes through the installation groove, the turned-on solenoid valve and the axial groove in the rib, and rushes into the annular bag through the inflation tube, so that the annular bag is inflated and expanded, and is pressed against the connecting hole of the connecting block and the radial hole of the rotating shaft, thereby further improving the connection tightness between the rib and the connecting structure, and at the same time forming a buffer protection and anti-bending effect on the rib, thereby improving the service life and use effect of the rib. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of the present invention;

[0022] Figure 2 It is a horizontal cross-sectional schematic diagram of the main wing panel, auxiliary wing panel and connection structure of the present invention;

[0023] Figure 3It is a horizontal cross-sectional schematic diagram of a wing of the present invention;

[0024] Figure 4 for Figure 3 The enlarged schematic diagram of part A in the middle;

[0025] Figure 5 for Figure 3 The enlarged schematic diagram of part B in the middle;

[0026] Figure 6 for Figure 3 Enlarged schematic diagram of part C in the middle.

[0027] In the figure: 1 UAV body, 2 main wing panel, 3 auxiliary wing panel, 4 connecting block, 5 connecting frame, 6 rotating shaft, 7 sealing groove, 8 connecting hole, 9 radial hole, 10 limiting groove, 11 rib, 12 sealing plug, 13 connecting groove, 14 flat air cavity, 15 electric telescopic rod, 16 sealing block, 17 blocking block, 18 buffer block, 19 mounting groove, 20 solenoid valve, 21 axial groove, 22 inflation tube, 23 annular groove, 24 annular capsule, 25 fixing ring, 26 reset spring, 27 annular clamping strip, 28 annular clamping groove. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0029] Reference Figure 1-Figure 6 , a UAV with a folding wing structure, comprising:

[0030] Drone body 1.

[0031] Wings, two wings are symmetrically installed on both sides of the drone body 1, and the wings include a main wing panel 2 and an auxiliary wing panel 3. A connecting structure is provided between the main wing panel 2 and the auxiliary wing panel 3, wherein the main wing panel 2 and the auxiliary wing panel 3 are rotatably matched through the connecting structure.

[0032] The connection structure includes a connection block 4, a connection frame 5 and a rotating shaft 6. The connection block 4 is fixedly connected to the main wing panel 2. The two connection frames 5 are fixedly connected to the auxiliary wing panel 3. The gap between the two connection frames 5 is located at both ends of the connection block 4. The connection block 4 is rotatably connected with the rotating shaft 6. The two ends of the rotating shaft 6 are fixedly connected to the two connection frames 5 in a one-to-one correspondence.

[0033] The linkage mechanism includes a sealing groove 7, a limiting groove 10, a rib 11, a sealing plug 12, a connecting groove 13 and a driving assembly. A plurality of sealing grooves 7 are provided in the main wing panel 2, and the plurality of sealing grooves 7 are all slidably connected with ribs 11. A plurality of limiting grooves 10 are provided in the auxiliary wing panel 3. The plurality of ribs 11 all penetrate the connecting structure at one end away from the drone body 1, and slide in cooperation with the plurality of limiting grooves 10 in a one-to-one correspondence. The plurality of ribs 11 are all fixedly connected at one end away from the auxiliary wing panel 3 with a sealing plug 12, and the sealing plug 12 is sealingly and slidably connected in the sealing groove 7. The plurality of sealing grooves 7 are connected at one end away from the auxiliary wing panel 3 with the same connecting groove 13, and the connecting groove 13 is provided in the main wing panel 2. The connecting groove 13 is connected at one end away from the sealing groove 7 with a driving assembly, and the driving assembly is arranged in the main wing panel 2.

[0034] A plurality of connecting holes 8 are formed through the connecting block 4 , and a plurality of radial holes 9 are formed through the rotating shaft 6 . The plurality of connecting holes 8 and the plurality of radial holes 9 are coaxially matched with the plurality of ribs 11 in a one-to-one correspondence.

[0035] The driving assembly includes a flat air cavity 14, an electric telescopic rod 15 and a sealing block 16. The flat air cavity 14 is opened inside the main wing panel 2. The electric telescopic rod 15 is installed in the flat air cavity 14. The output end of the electric telescopic rod 15 is fixedly connected to the sealing block 16. The sealing block 16 is sealingly and slidably connected in the flat air cavity 14. The flat air cavity 14 is connected to the connecting groove 13 on the side away from the electric telescopic rod 15.

[0036] A plurality of limiting grooves 10 are all provided through one end away from the main wing plate 2 , and are all threadedly connected with a blocking block 17 . By removing the blocking block 17 , it is convenient to extract the rib 11 through the limiting groove 10 .

[0037] A buffer block 18 is fixedly connected to one side of the blocking block 17 close to the inner side of the limiting groove 10 . The buffer block 18 is made of elastic rubber and is pressed and matched with the end of the rib 11 .

[0038] A buffer assembly is connected to multiple ribs 11, and the buffer assembly includes a mounting groove 19, a solenoid valve 20, an axial groove 21, an inflation tube 22, an annular groove 23 and an annular capsule 24. The mounting groove 19 is opened through the middle of the sealing plug 12, and the solenoid valve 20 is installed in the mounting groove 19. One end of the mounting groove 19 is connected to the inside of the sealing groove 7, and the other end is connected to the axial groove 21. The axial groove 21 is coaxially opened in the rib 11, and an annular groove 23 is coaxially opened on the outer peripheral side of the middle part of the rib 11. An annular capsule 24 is fixedly connected in the annular groove 23. The end of the axial groove 21 away from the mounting groove 19 is connected to the inflation tube 22, and the end of the inflation tube 22 away from the axial groove 21 passes through the rib 11, and extends into the annular groove 23, and is connected to the annular capsule 24. After the rib 11 extends into the limiting groove 10, the annular capsule 24 is squeezed and contacted with the connecting hole 8 and the radial hole 9 in the connecting structure.

[0039] A fixing ring 25 is connected to each of the sealing grooves 7 , and a return spring 26 is fixedly connected between each of the fixing rings 25 and one end of the sealing plugs 12 away from the rib 11 , so that the rib 11 can return to its original position after moving.

[0040] The outer circumferences of the multiple fixing rings 25 are coaxially fixedly connected with annular clamping strips 27, and the inner circumferences of the multiple sealing grooves 7 are connected with annular clamping grooves 28. The multiple annular clamping strips 27 are snap-fitted with the multiple annular clamping grooves 28 in a one-to-one correspondence, and the annular clamping strips 27 are elastic. During installation, the fixing rings 25 are directly pushed into the sealing groove 7 so that the annular clamping strips 27 are snapped into the annular clamping grooves 28.

[0041] When not in use, the plurality of ribs 11 are correspondingly folded into the plurality of sealing grooves 7 in the main wing panel 2, so that the auxiliary wing panel 3 can be rotated around the rotation axis 6 and folded to overlap with the main wing panel 2, which effectively reduces the overall occupied area of ​​the drone and makes it convenient for users to carry it;

[0042] When in use, the auxiliary wing plate 3 is rotated and flattened, so that the multiple limit grooves 10 on the auxiliary wing plate 3 and the multiple radial holes 9 on the rotating shaft 6 are coaxially connected with the multiple sealing grooves 7 on the main wing plate 2 and the multiple connecting holes 8 on the connecting block 4;

[0043] At this time, the electric telescopic rod 15 in the control driving assembly works, and the output end of the electric telescopic rod 15 extends, pushing the sealing block 16 to slide in the flat air cavity 14, compressing the space on one side of the flat air cavity 14, so that the air in the flat air cavity 14 is squeezed and enters the multiple sealing grooves 7 through the connecting groove 13, increasing the air pressure in the sealing groove 7. Under the pushing action of the air pressure, the elastic force of the return spring 26 is overcome to stretch the return spring 26, pushing one end of the sealing plug 12 in the sealing groove 7, so that the sealing plug 12 drives the rib 11 to move out of the sealing groove 7. One end of the rib 11 extends out of the sealing groove 7 and extends into the limiting groove 10 on the auxiliary wing panel 3 through the connecting hole 8 and the radial hole 9. Then, under the connection and limiting action of the plurality of ribs 11, the sealing groove 7 on the main wing panel 2 and the limiting groove 10 on the auxiliary wing panel 3, the main wing panel 2 and the auxiliary wing panel 3 are connected into a whole, i.e., a wing, so that the wing can work normally. Compared with the conventional technology of connecting the main wing panel 2 and the auxiliary wing panel 3 with external components, the influence of external components on the structural state of the wing is effectively reduced, and the working performance of the wing is improved.

[0044] When the rib 11 extends into the limiting groove 10, the elastic action of the buffer block 18 forms a buffer protection effect on the rib 11. At the same time, by providing the blocking block 17, it is convenient to pull the rib 11 out through the limiting groove 10, so as to facilitate the maintenance or replacement of the rib 11.

[0045] After the rib 11 extends into the limit groove 10, multiple solenoid valves 20 are controlled to be turned on. At this time, part of the high-pressure air in the sealing groove 7 passes through the installation groove 19, the turned-on solenoid valve 20 and the axial groove 21 in the rib 11, and rushes into the annular bag 24 through the inflation tube 22, so that the annular bag 24 is inflated and expanded, and is pressed against the connecting hole 8 of the connecting block 4 and the radial hole 9 of the rotating shaft 6, thereby further improving the connection tightness between the rib 11 and the connecting structure, and at the same time forming a buffer protection and anti-bending effect on the rib 11, thereby improving the service life and use effect of the rib 11.

[0046] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A UAV with a folding wing structure, characterized in that: include: UAV body (1); Wings, two of the wings are symmetrically mounted on both sides of the drone body (1), the wings comprising a main wing panel (2) and an auxiliary wing panel (3), a connecting structure is provided between the main wing panel (2) and the auxiliary wing panel (3), wherein the main wing panel (2) and the auxiliary wing panel (3) are rotationally matched via the connecting structure; A linkage mechanism, the linkage mechanism comprising a sealing groove (7), a limiting groove (10), a rib (11), a sealing plug (12), a connecting groove (13) and a driving assembly, wherein a plurality of sealing grooves (7) are provided in the main wing panel (2), the plurality of sealing grooves (7) are all slidably connected with ribs (11), a plurality of limiting grooves (10) are provided in the auxiliary wing panel (3), the plurality of ribs (11) at one end away from the drone body (1) all penetrate the connecting structure, and are connected to the plurality of limiting grooves (10) One corresponding sliding fit, the ends of the plurality of ribs (11) away from the auxiliary wing panel (3) are all fixedly connected with a sealing plug (12), the sealing plug (12) is sealingly and slidingly connected in the sealing groove (7), the ends of the plurality of sealing grooves (7) away from the auxiliary wing panel (3) are connected with the same connecting groove (13), the connecting groove (13) is arranged in the main wing panel (2), the ends of the connecting groove (13) away from the sealing groove (7) are connected with a driving component, and the driving component is arranged in the main wing panel (2).

2. The UAV with folding wing structure according to claim 1, characterized in that: in: The connection structure comprises a connection block (4), a connection frame (5) and a rotating shaft (6); the connection block (4) is fixedly connected to the main wing panel (2); the two connection frames (5) are fixedly connected to the auxiliary wing panel (3); the gap between the two connection frames (5) is located at two ends of the connection block (4); the connection block (4) is rotatably connected to the rotating shaft (6); the two ends of the rotating shaft (6) are fixedly connected to the two connection frames (5) in a one-to-one correspondence; a plurality of connecting holes (8) are penetrated through the connection block (4); a plurality of radial holes (9) are penetrated through the rotating shaft (6); the plurality of connecting holes (8) and the plurality of radial holes (9) are coaxially gap-matched with the plurality of ribs (11) in a one-to-one correspondence.

3. The UAV with folding wing structure according to claim 1, characterized in that: in: The driving assembly comprises a flat air cavity (14), an electric telescopic rod (15) and a sealing block (16); the flat air cavity (14) is arranged inside the main engine wing plate (2); the electric telescopic rod (15) is installed inside the flat air cavity (14); the output end of the electric telescopic rod (15) is fixedly connected to the sealing block (16); the sealing block (16) is sealingly and slidably connected inside the flat air cavity (14); and the side of the flat air cavity (14) away from the electric telescopic rod (15) is connected to the connecting groove (13).

4. The UAV with folding wing structure according to claim 1, characterized in that: in: The plurality of limit grooves (10) are all arranged through one end away from the main wing plate (2), and are all threadedly connected with a blocking block (17).

5. The UAV with folding wing structure according to claim 4, characterized in that: in: A buffer block (18) is fixedly connected to one side of the blocking block (17) close to the inside of the limiting groove (10); the buffer block (18) is made of elastic rubber, and the buffer block (18) is extruded and matched with the end of the rib (11).

6. The UAV with folding wing structure according to claim 2, characterized in that: in: A plurality of the ribs (11) are connected to a buffer assembly, the buffer assembly comprising a mounting groove (19), a solenoid valve (20), an axial groove (21), an air filling tube (22), an annular groove (23) and an annular bag (24); the mounting groove (19) is opened through the middle of the sealing plug (12); a solenoid valve (20) is installed in the mounting groove (19); one end of the mounting groove (19) is connected to the inside of the sealing groove (7), and the other end is connected to the axial groove (21); the axial groove (21) is coaxially opened inside the rib (11); An annular groove (23) is coaxially formed on the outer peripheral side of the middle part of the rib (11), an annular capsule (24) is fixedly connected in the annular groove (23), an end of the axial groove (21) away from the mounting groove (19) is connected to an inflation tube (22), an end of the inflation tube (22) away from the axial groove (21) passes through the rib (11), extends into the annular groove (23), and is connected to the annular capsule (24), wherein after the rib (11) extends into the limiting groove (10), the annular capsule (24) is in mutual compression contact with the connecting hole (8) and the radial hole (9) in the connecting structure.

7. The UAV with folding wing structure according to claim 1, characterized in that: in: A fixing ring (25) is connected to each of the plurality of sealing grooves (7), and a return spring (26) is fixedly connected between each of the plurality of fixing rings (25) and the ends of the plurality of sealing plugs (12) away from the ribs (11).

8. The UAV with folding wing structure according to claim 7, characterized in that: in: The outer circumferences of the plurality of fixing rings (25) are coaxially fixedly connected with an annular clamping strip (27), the inner circumferences of the plurality of sealing grooves (7) are connected with an annular clamping groove (28), and the plurality of annular clamping strips (27) are snap-fitted with the plurality of annular clamping grooves (28) in a one-to-one corresponding manner.

Images