Connecting structure for wings of unmanned aerial vehicle

Abstract

The connecting structure comprises a nose body, a fuselage body and a plurality of side wings, the nose body is arranged at the front end of the nose body, the side wings are circumferentially distributed on the outer wall of the fuselage body, one ends of the side wings are hinged to the outer wall of the fuselage body, and the other ends of the side wings are hinged to the outer wall of the fuselage body. The side wings incline towards the tail end of the fuselage body, a plurality of connecting parts are hinged to the tail of the fuselage body, the connecting parts incline towards the nose body, the connecting parts correspond to the side wings in a one-to-one mode, and the connecting parts and the corresponding side wings are arranged in a staggered mode; when the side wings are in an unfolded state, the side wings and the connecting parts are far away from the fuselage body; when the side wings are in the folded state, the side wings and the connecting parts are close to the fuselage body, and locking pieces are arranged between the connecting parts and the corresponding side wings. The unmanned aerial vehicle has the effect that the unmanned aerial vehicle can be folded and stored conveniently.

Description

Technical Field

[0001] The present application relates to the field of unmanned aerial vehicles, and in particular to a connection structure of a wing of a unmanned aerial vehicle. Background Art

[0002] At present, in modern military operations, rapid and accurate strikes are the key to victory. Currently, most bomb-carrying drones have bombs hanging under the fuselage. In addition, the fuselage is equipped with multiple propellers with vertically set rotating shafts. The propellers are rotated by the fuselage's own motor to provide power for transporting ammunition.

[0003] During the drone transportation process, due to the structural characteristics of drones, they cannot be folded and stored, and they occupy a large space, which limits the number of drones that can be transported by a transport vehicle at a time. Therefore, there is still room for improvement. Summary of the invention

[0004] In order to facilitate the folding and storage of a drone, the present application provides a connection structure for the wings of a drone.

[0005] The connection structure of the drone wing provided in this application adopts the following technical solution:

[0006] A connection structure of unmanned aerial vehicle wings comprises a nose body, a fuselage body and a plurality of side wings, wherein the nose body is arranged at the front end of the nose body, the plurality of side wings are circumferentially distributed on the outer wall of the fuselage body, one end of the side wing is hinged to the outer wall of the fuselage body, the side wing is inclined toward the tail end of the fuselage body, the tail of the fuselage body is hinged with a plurality of connecting parts, the connecting parts are inclined toward the nose body, the plurality of connecting parts correspond to the plurality of side wings one by one, and the connecting parts are staggered with the corresponding side wings; when the side wings are in an unfolded state, the side wings and the connecting parts are both away from the fuselage body; when the side wings are in a retracted state, the side wings and the connecting parts are both close to the fuselage body, and locking members are arranged between the connecting parts and the corresponding side wings.

[0007] By adopting the above technical solution, the side wings are hinged to the outer wall of the fuselage body, and the connecting part is cooperatively connected to the side wings and locked by a locking piece to improve the stability in the unfolded state. By bringing the side wings and the connecting part close to the fuselage body at the same time, the side wings can be stored, which facilitates the folding and storage of the drone, and helps to reduce the space occupied by the drone during transportation.

[0008] Preferably, a slide groove is provided on one side of the side wing facing the connecting part, the connecting part is provided with a slider slidably connected to the slide groove, the locking member is provided through the slider in the direction of the side wing, the bottom wall of the slide groove is provided with a first threaded locking hole and a second threaded locking hole, when the slider moves to the first threaded locking hole, the side wing is in an unfolded state. The locking member is threadedly connected to the first threaded locking hole; when the slider moves to the second threaded locking hole, the side wing is in a retracted state, and the locking member is threadedly connected to the second threaded locking hole.

[0009] By adopting the above technical solution, the synchronous storage of the connecting part and the side wing is realized under the sliding cooperation of the slider and the slide groove, and the first threaded locking hole and the second threaded locking hole are opened in the slide groove as switching nodes between the storage state and the deployment state of the side wing. The threaded cooperation of the locking piece is conducive to achieving the stability effect of the storage state and the deployment state of the drone.

[0010] Preferably, a fixing rod is provided between the connecting portion and the corresponding side wing, a fastener is provided between the fixing rod and the side wing, and when the side wing is in an unfolded state, the length direction of the fixing rod is parallel to the length direction of the fuselage body.

[0011] By adopting the above technical solution, the fixed rod plays a role in reinforcing the connecting part and the side wing, thereby improving the stability of the connection between the two and further improving the flight stability of the UAV. At the same time, the fixed rod is parallel to the fuselage body, which is beneficial to reducing the area of ​​the windward surface of the fixed rod and reducing wind resistance.

[0012] Preferably, one end of the connecting portion away from the fuselage body is hinged to one end of the fixed rod, the side wing is provided with a first guide groove, and the end of the fixed rod away from the connecting portion is provided with a moving block, the moving block is slidably connected to the first guide groove, when the moving block is located at the starting end of the first guide groove, the fixed rod is parallel to the fuselage body, and when the moving block is located at the end of the first guide groove, the fixed rod is parallel to the connecting portion.

[0013] By adopting the above technical solution, a first guide groove is added to the side wing, and the first guide groove and the movable block are slidably matched so as to swing the fixed rod to be parallel to the connecting part, thereby assembling the fixed rod and the connecting part into a whole, which is convenient for the subsequent overall storage of the fixed rod and the connecting part.

[0014] Preferably, the wing side wall is provided with a second guide groove, the starting end of the first guide groove is connected to the end of the second guide groove, and when the connecting part and the fixing rod are approached toward the fuselage body, the moving block moves from the starting end of the second guide groove to the end of the second guide groove.

[0015] By adopting the above technical solution, it is convenient to store the fixing rod and the connecting part as a whole.

[0016] Preferably, the outer wall of the fuselage body is provided with a plurality of accommodating grooves, the plurality of accommodating grooves correspond one-to-one to a plurality of side wings, the length direction of the accommodating grooves is consistent with the length direction of the fuselage body, and when the side wings are in a stowed state, the side wings are embedded in the accommodating grooves.

[0017] By adopting the above technical solution, the receiving groove plays a storage role to store the opposite wing, which is beneficial to further reduce the space occupancy rate of the drone in the stored state.

[0018] Preferably, a front propeller is provided at one end of the fixing rod away from the side wing.

[0019] By adopting the above technical solution, the front propeller improves the wind-breaking ability of the UAV, which is beneficial to increasing the flight speed of the UAV.

[0020] Preferably, a tail propeller is provided at one end of the fuselage body away from the nose body.

[0021] By adopting the above technical solution, a tail propeller is installed at the end of the fuselage body, and the propeller has a boosting effect on the flight of the UAV, which is beneficial to increasing the flight speed of the UAV.

[0022] In summary, the present application includes at least one of the following beneficial technical effects:

[0023] The side wings are hinged to the outer wall of the fuselage body, and the connecting part is connected with the side wings and locked by a locking member to improve the stability in the unfolded state. The side wings and the connecting part are simultaneously placed close to the fuselage body to achieve the purpose of storing the side wings, which is convenient for folding and storing the drone, and is conducive to reducing the space occupied by the drone during transportation;

[0024] By slidingly cooperating between the slider and the slide groove, the connection part and the side wing are synchronously stored, and the first threaded locking hole and the second threaded locking hole are provided in the slide groove as switching nodes between the stored state and the deployed state of the side wing. The threaded cooperation of the locking member is conducive to achieving the stable effect of the stored state and the deployed state of the drone.

[0025] By arranging a fixing rod between the connecting part and the corresponding side wing, the fixing rod plays the role of reinforcing the connecting part and the side wing, thereby improving the stability of the connection between the two and further improving the flight stability of the UAV. At the same time, the fixing rod is parallel to the fuselage body, which is beneficial to reducing the area of ​​the windward surface of the fixing rod and reducing wind resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1This is a schematic diagram of the unfolded state of the side wing in the connection structure of the wing of a drone in an embodiment of the present application.

[0027] Figure 2 yes Figure 1 A magnified schematic diagram of center A.

[0028] Figure 3 It is a schematic diagram of the state when the connecting part and the fixed rod are close to each other in the connecting structure of the wing of a drone in an embodiment of the present application.

[0029] Figure 4 This is a schematic diagram of the stowed state of the side wing in the connection structure of the wing of a drone in an embodiment of the present application.

[0030] Figure 5 It is a schematic diagram of the internal structure of a connection structure of a drone wing according to an embodiment of the present application.

[0031] Explanation of the reference numerals: 1. nose body; 11. warhead chamber; 12. annular protrusion; 2. fuselage body; 21. warhead chamber; 22. groove; 23. accommodating groove; 3. side wing; 31. slide groove; 32. first guide groove; 33. second guide groove; 4. connecting part; 41. slider; 42. locking piece; 5. fixing rod; 51. moving block; 52. fastener; 6. front propeller; 7. anti-loosening washer; 8. tail propeller. DETAILED DESCRIPTION

[0032] The following is combined with Figure 1-5 This application is described in further detail.

[0033] The present application embodiment discloses a connection structure of a drone wing. Figure 1 and Figure 2 A connection structure of a drone wing includes a nose body 1, a fuselage body 2 and a plurality of side wings 3. The nose body 1 is arranged at the front end of the nose body 1. In this embodiment, there are 4 side wings 3, and the four side wings 33 work together to balance the heading and stabilize the drone during flight. The side wings 3 are circumferentially distributed on the outer wall of the fuselage body 2, one end of the side wing 3 is hinged to the outer wall of the fuselage body 2, and the side wing 3 is inclined toward the tail end of the fuselage body 2. The tail of the fuselage body 2 is hinged with a plurality of connecting parts 4, and the connecting parts 4 are inclined toward the direction of the nose body 1, and the plurality of connecting parts 4 correspond to the plurality of side wings 3 one by one.

[0034] In this embodiment, when the side wing 3 is in the unfolded state, the connecting portion 4 is staggered with the corresponding side wing 3, and the side wing 3 and the connecting portion 4 are both far away from the fuselage body 2, and the connecting portion 4 is staggered with the corresponding side wing 3. Among them, the angle between the connecting portion 4 and the fuselage body 2 is 15°, and the angle between the side wing 3 and the fuselage body 2 is 60°.

[0035] When the side wing 3 is in the stowed state, the side wing 3 and the connecting portion 4 are both close to the fuselage body 2, and a locking member 42 is provided between the connecting portion 4 and the corresponding side wing 3. The locking member 42 realizes a stable state of the side wing 3 and the connecting portion 4.

[0036] Specifically, a slide groove 31 is provided on one side of the side wing 3 facing the connecting part 4, and a slider 41 is fixed in the middle of the connecting part 4 and is slidably connected to the slide groove 31. The slider 41 is cylindrical. A locking member 42 is arranged through the slider 41 in the direction of the side wing 3. The locking member 42 is a screw. A first threaded locking hole (not shown in the figure) and a second threaded locking hole (not shown in the figure) are provided on the bottom wall of the slide groove 31. The first threaded locking hole and the second threaded locking hole are respectively arranged at the starting end and the end of the slide groove 31. When the slider 41 moves to the first threaded locking hole, the side wing 3 is in an unfolded state, and is threadedly connected to the first threaded locking hole through the locking member 42 to achieve the stability of the side wing 3 in the unfolded state; when the slider 41 moves to the second threaded locking hole, the side wing 3 is in a retracted state, and is threadedly connected to the second threaded locking hole through the locking member 42 to achieve the stability of the side wing 3 in the retracted state.

[0037] In addition, in order to strengthen the connection stability between the connection part 4 and the side wing 3, a fixing rod 5 is connected between the connection part 4 and the corresponding side wing 3, wherein a fastener 52 is provided between the fixing rod 5 and the side wing 3. The fastener 52 is a screw. When the side wing 3 is in the unfolded state, the length direction of the fixing rod 5 is parallel to the length direction of the fuselage body 2. The fixing rod 5 plays the role of strengthening the connection part 4 and the side wing 3. In addition, the length direction of the fixing rod 5 is parallel to the length direction of the fuselage body 2, which is conducive to reducing the area of ​​the windward surface of the fixing rod 5, thereby reducing wind resistance.

[0038] Reference Figure 2 and Figure 3 In this embodiment, one end of the connecting part 4 away from the fuselage body 2 is hinged to one end of the fixing rod 5, the side wing 3 is provided with a first guide groove 32, and one end of the fixing rod 5 away from the connecting part 4 is provided with a cylindrical moving block 51, and the moving block 51 is slidably connected with the first guide groove 32. When the moving block 51 is located at the starting end of the first guide groove 32, the fixing rod 5 is parallel to the fuselage body 2, and the fastener 52 passes through the moving block 51 and is threadedly fixed to the bottom of the first guide groove 32. When the moving block 51 is located at the end of the first guide groove 32, the fixing rod 5 is parallel to the connecting part 4. Through the sliding cooperation between the first guide groove 32 and the moving block 51, the fixing rod 5 is swung to be parallel to the connecting part 4, so that the fixing rod 5 and the connecting part 4 are assembled into a whole, which is convenient for the subsequent storage of the fixing rod 5 and the connecting part 4 as a whole.

[0039] Reference Figure 2 and Figure 4A second guide groove 33 is provided on the side wall of the wing, and the starting end of the first guide groove 32 is connected to the end of the second guide groove 33. When the connecting portion 4 and the fixing rod 5 approach toward the fuselage body 2, the moving block 51 moves from the starting end of the second guide groove 33 to the end of the second guide groove 33, and the fastener 52 passes through the moving block 51 and is threadedly fixed to the bottom wall of the second guide groove 33.

[0040] The outer wall of the fuselage body 2 is provided with a plurality of accommodating grooves 23, and the plurality of accommodating grooves 23 correspond one-to-one to the plurality of side wings 3. The length direction of the accommodating grooves 23 is consistent with the length direction of the fuselage body 2. When the side wings 3 are in the storage state, the side wings 3 are embedded in the accommodating grooves 23. The accommodating grooves 23 play a storage role to store the side wings 3, which is beneficial to further reduce the space occupancy rate of the drone in the storage state.

[0041] A front propeller 6 is installed at one end of the fixed rod 5 away from the side wing 3, and a front motor for driving the front propeller 6 to rotate is installed at the end of the fixed rod 5. The front propeller 6 improves the wind-breaking ability of the drone and is conducive to increasing the flight speed of the drone.

[0042] In this embodiment, a tail propeller 8 is installed at one end of the fuselage body 2 away from the nose body 1, and a tail motor for driving the tail propeller 8 to rotate is embedded in the tail of the fuselage body 2. The tail propeller 8 boosts the flight of the UAV, which is beneficial to increasing the flight speed of the UAV.

[0043] Reference Figure 5 In this embodiment, the nose body 1 is detachably connected to the fuselage body 2, and the sides of the nose body 1 and the fuselage body 2 facing each other are their respective joint surfaces. A warhead chamber 11 is arranged inside the nose body 1, and the opening position of the warhead chamber 11 is arranged at the joint surface of the nose body 1, and the shape of the warhead chamber 11 is adapted to the shape of the warhead of the missile, and is used to accommodate the warhead of the missile. A body chamber 21 is arranged inside the fuselage body 2, and the opening position of the body chamber 21 is arranged at the joint surface of the fuselage body 2, and the shape of the body chamber 21 is adapted to the shape of the body of the missile, and is used to accommodate the warhead of the missile. The warhead chamber 11 is connected to the body chamber 21 to form a cavity for accommodating the missile. By completely hiding the missile inside the drone, instead of the traditional missile external missile loading method, it is beneficial to reduce the wind resistance of the drone during flight, and it is convenient to improve the flight speed and flight stability of the drone.

[0044] In this embodiment, the nose body 1 is in a bullet shape, the body body 2 is in a cylindrical shape, and the outer wall of the nose body 1 and the outer wall of the body body 2 are smoothly transitioned. The cylindrical body and the nose in the shape of a bullet improve the wind-breaking ability of the nose and help reduce wind resistance.

[0045] In order to improve the connection stability between the nose body 1 and the fuselage body 2, an annular protrusion 12 is provided on the joint surface of the nose body 1, and an external thread is provided on the outer peripheral surface of the annular protrusion 12. A groove 22 is provided on the joint surface of the fuselage body 2, and an internal thread is provided on the inner peripheral wall of the groove 22. The nose body 1 and the fuselage body 2 are threadedly connected through the annular protrusion 12 and the groove 22. And the outer sleeve of the annular protrusion 12 is provided with an anti-loosening washer 7. When the nose body 1 and the fuselage body 2 are assembled, the anti-loosening washer 7 is sandwiched between the nose body 1 and the fuselage. Reduce the looseness of the drone during flight, thereby improving the flight stability of the drone.

[0046] The implementation principle of the connection structure of the drone wing in the embodiment of the present application is:

[0047] When switching the drone from the deployed state to the stored state, first remove the fastener 52 to unlock the movement restriction of the moving block 51, and then slide the moving block 51 until the moving block 51 moves to the end of the first guide groove 32, so that the fixed rod 5 and the connecting part 4 are parallel and close to each other, and then swing the fixed rod 5 and the connecting part 4 together toward the fuselage body 2, so that the fixed rod 5 and the connecting part 4 are close to the drone fuselage body 2, at this time, the slider 41 moves along the length direction of the slide groove 31, and the moving block 51 moves along the length direction of the second guide groove 33, while driving the side wing 3 to swing toward the fuselage body 2, until the side wing 3 is partially stored in the accommodating groove 23, and then the moving block 51 and the slider 41 are locked at the same time.

[0048] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A connection structure for the wings of a drone, characterized in that: The invention comprises a nose body (1), a fuselage body (2) and a plurality of side wings (3), wherein the nose body (1) is arranged at the front end of the nose body (1), the plurality of side wings (3) are circumferentially distributed on the outer wall of the fuselage body (2), one end of the side wing (3) is hinged to the outer wall of the fuselage body (2), the side wing (3) is inclined toward the tail end of the fuselage body (2), the tail of the fuselage body (2) is hinged with a plurality of connecting parts (4), the connecting parts (4) are inclined toward the nose body (1), and the connecting parts (4) are inclined toward the tail end of the fuselage body (2). The side wings (3) are inclined in the direction of rotation, and a plurality of connecting parts (4) correspond to a plurality of side wings (3) one by one; when the side wings (3) are in an unfolded state, the side wings (3) and the connecting parts (4) are both away from the fuselage body (2), and the connecting parts (4) and the corresponding side wings (3) are arranged in a staggered manner; when the side wings (3) are in a retracted state, the side wings (3) and the connecting parts (4) are both close to the fuselage body (2), and a locking member (42) is arranged between the connecting parts (4) and the corresponding side wings (3).

2. The connection structure of a drone wing according to claim 1, characterized in that: The side wing (3) is provided with a slide groove (31) on one side facing the connecting portion (4); the connecting portion (4) is provided with a slider (41) slidably connected to the slide groove (31); the locking member (42) is arranged to penetrate the slider (41) in the direction of the side wing (3); a first threaded locking hole and a second threaded locking hole are provided on the bottom wall of the slide groove (31); when the slider (41) moves to the first threaded locking hole, the side wing (3) is in an unfolded state, and the locking member (42) is threadedly connected to the first threaded locking hole; when the slider (41) moves to the second threaded locking hole, the side wing (3) is in a retracted state, and the locking member (42) is threadedly connected to the second threaded locking hole.

3. The connection structure of the drone wing according to claim 2, characterized in that: A fixing rod (5) is provided between the connecting portion (4) and the corresponding side wing (3), and a fastener (52) is provided between the fixing rod (5) and the side wing (3). When the side wing (3) is in an unfolded state, the length direction of the fixing rod (5) is parallel to the length direction of the fuselage body (2).

4. The connection structure of the drone wing according to claim 3 is characterized in that: One end of the connecting portion (4) away from the fuselage body (2) is hinged to one end of the fixing rod (5); the side wing (3) is provided with a first guide groove (32); one end of the fixing rod (5) away from the connecting portion (4) is provided with a moving block (51); the moving block (51) is slidably connected to the first guide groove (32); when the moving block (51) is located at the starting end of the first guide groove (32), the fixing rod (5) is parallel to the fuselage body (2); when the moving block (51) is located at the end of the first guide groove (32), the fixing rod (5) is parallel to the connecting portion (4).

5. The connection structure of the drone wing according to claim 4, characterized in that: The wing side wall is provided with a second guide groove (33), the starting end of the first guide groove (32) is connected to the end of the second guide groove (33), and when the connecting portion (4) and the fixing rod (5) are moved toward the fuselage body (2), the moving block (51) moves from the starting end of the second guide groove (33) to the end of the second guide groove (33).

6. The connection structure of the drone wing according to claim 5, characterized in that: The outer wall of the fuselage body (2) is provided with a plurality of accommodating grooves (23), the plurality of accommodating grooves (23) correspond to the plurality of side wings (3) one by one, the length direction of the accommodating grooves (23) is consistent with the length direction of the fuselage body (2), and when the side wings (3) are in a stored state, the side wings (3) are embedded in the accommodating grooves (23).

7. The connection structure of the drone wing according to claim 3, characterized in that: A front propeller (6) is provided at one end of the fixing rod (5) away from the side wing (3).

8. The connection structure of a drone wing according to claim 1, characterized in that: A tail propeller (8) is provided at one end of the fuselage body (2) away from the nose body (1).

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