Unmanned aerial vehicle frame structure based on large-folding-ratio vehicle arms

Abstract

The invention discloses an unmanned aerial vehicle frame structure based on a large-folding-ratio vehicle arm. The unmanned aerial vehicle frame structure comprises a vehicle body and a power mechanism. Arm rods which are annularly distributed are installed at the side end of the vehicle body, the vehicle arms obliquely rotate relative to the single sides of the arm rods, and when the vehicle arms rotate and are folded relative to the arm rods, the vehicle arms and the adjacent arm rods are in an up-down staggered state to form an encircling folding structure. Fasteners are arranged between the machine arms and the arm rods in a matched mode, and when the machine arms rotate relative to the arm rods to be opened, the machine arms and the arm rods are locked through the fasteners. According to the unmanned aerial vehicle, due to the fact that the vehicle arms rotate in the single-side inclined direction relative to the arm rods, a user does not need to consider the rotating direction and the rotating sequence of the vehicle arms through a single-side rotating and folding mode, only one-by-one folding operation needs to be simply carried out, and compared with the prior art, operation is simpler and more efficient; compared with the prior art, the whole unmanned aerial vehicle is in a more compact folded state.

Description

Technical Field

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

[0002] At present, the continuous improvement of plant protection UAVs has played a huge role in the development of agricultural intelligence. In order to meet the continuous aerial operation of plant protection UAVs and have corresponding loading capacity, plant protection UAVs are getting bigger and bigger, and transportation is a point of increasing concern.

[0003] A drone frame with a high folding ratio can ensure the operating efficiency of a large frame while ensuring the convenience of transportation after folding, and the same transportation tool can transport more drones to improve operating efficiency. The enveloping folding method is currently a commonly used and mature method, but due to the influence of the structure, the folding often cannot reach the ideal size.

[0004] According to the application number: 202120262111.5, the drone that can be folded at an angle is used to solve the problem that existing drones take up a large amount of space when not in use by folding the front and rear arms diagonally and the middle arms vertically. However, due to the different rotation directions of the arms, the folding of the arms requires the user to operate in the corresponding direction according to the position of the arms. This operation method is cumbersome, and if the user operates the arms incorrectly, the arms are prone to be damaged. In addition, due to the vertical folding of the arms, the vertical height of the drone when not in use is limited by the folded arms, making it impossible to adjust, which is not conducive to further optimization of the size of the drone.

[0005] According to patent application number: 201920850543.0, a foldable agricultural spraying drone discloses a method in which the arms can be folded around, but because the arms cannot be rotated at an oblique angle, the rotation of the arms is easily interfered with by adjacent arms, resulting in a limited folding range and failure to reach an ideal size. In addition, the prior art does not have a structure for clamping multiple arms in an embracing folded state, resulting in the drone arms easily spreading out after folding, which is not conducive to the safe transportation of the drone.

[0006] Based on the above defects, a UAV frame structure based on a large folding ratio arm is provided. Summary of the invention

[0007] The purpose of the present invention is to solve the above-mentioned problem and to propose a UAV frame structure based on a large folding ratio arm.

[0008] In order to achieve the above-mentioned purpose, the present invention adopts the following technical solutions: a UAV frame structure based on a large folding ratio arm, including a body and a power mechanism; The side end of the machine body is provided with an arm rod distributed in a ring shape, and the arm rod is rotatably connected to a machine arm installed by a matching power mechanism at one side of the machine body through a hinge, and the machine arm is unilaterally obliquely rotated relative to the arm rod, and when the machine arm is rotated and folded relative to the arm rod, the machine arm and the adjacent arm rod are in an up-and-down staggered state, forming an embracing folding structure; The arm rod is provided with a clamping piece for cooperating with the machine arm to be folded and fixed; A fastener is provided between the machine arm and the arm rod. When the machine arm is rotated and opened relative to the arm rod, the machine arm and the arm rod are locked by the fastener.

[0009] Preferably, a notch is formed on the side of the arm rod for the machine arm to penetrate and embed, and the outer tube diameter of the machine arm is matched with the inner tube diameter of the arm rod.

[0010] Preferably, the hinged member comprises a bracket fixedly mounted on the arm, a butt end is fixedly mounted on the machine arm, and an axle connection assembly is arranged between the bracket and the butt end.

[0011] Preferably, the shaft connection assembly comprises a rotating shaft penetrating the bracket and the butt end, and a nut is screwed and connected to the outer side of the rotating shaft.

[0012] Preferably, a stop block is formed at the end of the rotating shaft, and the two sides of the bracket are stopped by the stop block and the nut to limit the rotating shaft from being pulled out of the bracket.

[0013] Preferably, the clamping member comprises a sleeve fixedly arranged on the outside of the arm, and a buckle which is clamped to cooperate with the outer wall of the machine arm is fixedly arranged on the sleeve.

[0014] Preferably, the end surface where the jacket and the arm are fitted and fixed presents a matching rectangular anti-twist structure, and the groove where the snap-fit ​​arm is embedded and clamped presents a C-shaped closing structure.

[0015] Preferably, the fastener includes threads formed on the arm and the side wall of the machine arm, and a clamping assembly. When the machine arm is rotated and opened relative to the arm, the patterns of the two threads are merged and aligned, and the threads are tightened by the clamping assembly.

[0016] Preferably, the clamping assembly comprises a nut slidably sleeved on the outer side of the machine arm, a locking piece is screwed on the nut, and anti-slip grooves are formed on the side walls of the nut and the locking piece.

[0017] Preferably, a water pipe buckle is installed on the machine arm, and a buckle groove for matching the water pipe clamp is formed on the water pipe buckle, and the buckle groove is an Ω structure.

[0018] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are: 1. In the present application, a reference plane is formed by taking two adjacent arms as a reference, and the arms connected to the arms are rotated obliquely relative to the reference plane, so that when the arms are rotated and folded, they are staggered with the adjacent arms up and down, which is conducive to the arms being folded and retracted over a wider range, making the structure of the drone in the folded state more compact and convenient for users to carry.

[0019] 2. In the present application, by using a unilateral rotation and folding method, the user does not need to consider the rotation direction and rotation order of the arms, and only needs to simply perform the folding operations one by one. Compared with the prior art, the operation is simpler and more efficient. When the user folds the tripod of the drone, the overall height of the drone is lowered. Compared with the prior art, the entire drone is in a more compact folded state.

[0020] 3. In the present application, when the machine arm is rotated and folded to be buckled into the buckle, the buckle is first opened by the pressure of the machine arm. When the machine arm is buckled in, the buckle is deformed and the groove is tightened, thereby ensuring that the machine arm is in a stable clamping state after being folded.

[0021] 4. In the present application, the contact area among the nut, the arm and the arm rod is increased by setting the notch, thereby increasing the force strength between the arm rods and the arms, so that when the UAV is in flight, the connection between the arm and the arm rod will not be easily broken, thereby ensuring the safe flight of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A schematic diagram of the deployment of a drone frame according to an embodiment of the present invention is shown; Figure 2 A schematic diagram of folding a drone frame provided by an embodiment of the present invention is shown; Figure 3 A folding stereoscopic schematic diagram of a machine arm and an arm rod provided in an embodiment of the present invention is shown; Figure 4 A schematic front view of a folded machine arm and an arm rod provided in an embodiment of the present invention is shown; Figure 5 A schematic diagram of a folded top view of a machine arm and an arm rod provided in an embodiment of the present invention is shown; Figure 6 A schematic diagram of the exploded structure of a machine arm and an arm rod provided according to an embodiment of the present invention is shown.

[0023] Legend: 1. Machine body; 2. Arm; 3. Jacket; 4. Buckle; 5. Notch; 6. Bracket; 7. Machine arm; 8. Butt end; 9. Thread; 10. Rotating shaft; 11. Nut; 12. Nut; 13. Locking piece; 14. Water pipe buckle; 15. Buckle groove; 16. Power mechanism. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] See also Figure 1-6 , the present invention provides a technical solution: a UAV frame structure based on a large folding ratio arm, including a body 1 and a power mechanism 16; A ring-shaped arm 2 is installed at the side end of the body 1. The arm 2 is away from the side of the body 1 and is rotatably connected to an arm 7 installed in conjunction with a power mechanism 16 through a hinge. The arm 7 rotates obliquely relative to the arm 2. When the arm 7 is rotated and folded relative to the arm 2, the arm 7 and the adjacent arm 2 are staggered up and down to form an embracing folding structure.

[0026] The power mechanism 16 is a prior art and is a key part of the UAV's flight performance. It includes main components such as motors, electric regulators, and propellers. The arm 2 and the arm 7 are both hollow structures, which are used to connect the power lines and control lines in the body 1 to the power mechanism 16, thereby realizing power supply and function control of the power mechanism 16.

[0027] A reference plane is formed by taking two adjacent arms 2 as a reference, and the arm 7 connected to the arm 2 is rotated obliquely relative to the reference plane, so that when the arm 7 is rotated and folded, it is staggered with the adjacent arm 2 up and down, which is conducive to the arm 7 to fold and retract over a larger range, making the structure of the drone in the folded state more compact and convenient for users to carry.

[0028] Since the arm 7 is unilaterally rotated obliquely relative to the arm rod 2, the arm 7 is in a folded state after folding. Through the unilateral rotation and folding method, the user does not need to consider the rotation direction and rotation order of the arm 7, and only needs to simply perform the folding operations one by one. Compared with the existing technology, the operation is simpler and more efficient. When the user folds the tripod of the drone, the overall height of the drone is lowered. Compared with the existing technology, the entire drone is in a more compact folded state.

[0029] In order to minimize the overall height of the drone, the oblique rotation angle of the arm 7 relative to the reference plane should be controlled so that the arm 7 can just stagger the adjacent arm rods 2 after being folded. The setting of this oblique angle is related to the diameter of the arm 7 and the arm rod 2, and is also related to the circumferential distribution angle of the arm rod 2 relative to the body 1. According to the current product structure size arrangement, the adapted oblique rotation angle is 9.5 degrees.

[0030] The arm 2 is provided with a clamping piece for cooperating with the machine arm 7 to be folded and fixed.

[0031] When the user folds the arm 7, the arm 7 remains fixed relative to the arm rod 2 under the action of the clamping piece, which helps the frame as a whole to maintain a stable folded state, plays a role in protecting the UAV, and avoids the frame from spreading apart due to external forces during the carrying of the UAV, which can easily cause damage to the power mechanism.

[0032] A fastener is provided between the machine arm 7 and the arm rod 2. When the machine arm 7 is rotated and opened relative to the arm rod 2, the machine arm 7 and the arm rod 2 are locked by the fastener.

[0033] When the arm 7 is unfolded relative to the arm 2 and is distributed in the same straight line as the arm 2, the arm 7 and the arm 2 are tightened by fasteners to ensure that the arm 7 remains in a stable open state during the flight of the UAV, thereby facilitating the stable flight of the UAV.

[0034] Specifically, Figure 3-6 As shown, the hinged member includes a bracket 6 fixedly mounted on the arm 2, a butt end 8 fixedly mounted on the machine arm 7, and an axle connection assembly disposed between the bracket 6 and the butt end 8.

[0035] The bracket 6 and the arm 2 are integrally formed, and the arm 7 and the docking end 8 are integrally formed, so as to reduce the number of parts and solve the problem of complicated screw installation operation.

[0036] The shaft connection assembly includes a rotating shaft 10 that passes through the bracket 6 and the butt end 8, and a nut 11 is screwed on the outer side of the rotating shaft 10. The bracket 6 and the butt end 8 are both formed with a hole groove that fits the rotating shaft 10 to pass through, and the inner side of the bracket 6 is formed with a groove that fits the butt end 8 to rotate and embed. When the machine arm 7 is folded or unfolded relative to the arm rod 2, the bracket 6 rotates along the rotating shaft 10 in the groove.

[0037] A stop block is formed at the end of the rotating shaft 10 , and the stop block and the nut 11 are used to stop both sides of the bracket 6 , thereby limiting the rotating shaft 10 from being pulled away from the bracket 6 .

[0038] The end of the rotating shaft 10 away from the stop block passes through the bracket 6 and the docking end 8, and the nut 11 is screwed into the rotating shaft 10 from this end. The position of the rotating shaft 10 relative to the bracket 6 is limited by the nut 11 and the stop block, which is conducive to maintaining a stable articulated state between the arm 7 and the arm rod 2.

[0039] Specifically, Figure 1-6 As shown, the clamping member includes a jacket 3 fixedly arranged on the outside of the arm 2, and a buckle 4 is fixedly arranged on the jacket 3 for clamping with the outer wall of the machine arm 7.

[0040] The end surfaces of the jacket 3 and the arm 2 that are fitted and fixed together present a matching rectangular anti-twist structure, and the buckle 4 cooperates with the machine arm 7 to be embedded in the clamping groove to present a C-shaped closing structure.

[0041] The buckle 4 has a certain elastic closing ability. When the arm 7 is rotated and buckled into the buckle 4, the buckle 4 is first opened by the pressure of the arm 7. When the arm 7 is buckled in, the buckle 4 deforms and recovers to tighten the groove, thereby ensuring that the arm 7 is in a stable clamping state after being folded.

[0042] The hook of the buckle 4 is hollow, which is conducive to elastic deformation within a certain range, and support ribs are distributed in the hollow structure of the buckle 4 to stabilize its shape.

[0043] Specifically, Figure 3-6 As shown, a notch 5 is formed on the side of the arm 2 for the arm 7 to penetrate and embed. The outer diameter of the arm 7 is matched with the inner diameter of the arm 2. The fastener includes a thread 9 formed on the side walls of the arm 2 and the arm 7, and a clamping assembly. When the arm 7 is rotated and opened relative to the arm 2, the textures of the two threads 9 are merged and aligned, and the thread 9 is tightened by the clamping assembly.

[0044] The notch 5 is provided so that when the arm 7 is rotated and opened relative to the arm rod 2, part of the tube body thereof is embedded in the arm rod 2, so that the side end of the arm 7 is in contact with the inner wall of the arm rod 2. At this time, the threads 9 on the arm rod 2 and the arm 7 are merged to form a complete spiral pattern.

[0045] The clamping assembly includes a nut 12 slidably sleeved on the outer side of the machine arm 7, a locking piece 13 is screwed on the nut 12, and anti-slip grooves are formed on the side walls of the nut 12 and the locking piece 13.

[0046] When the nut 12 is screwed together with the thread 9, the nut 12 is wrapped around the outside of the arm 2 and the arm 7. Through the setting of this structure, the contact area among the nut 12, the arm 7 and the arm 2 is increased, thereby increasing the force strength between the arm 2 and the arm 7, so that when the UAV is in flight, the connection between the arm 7 and the arm 2 will not easily break, thereby ensuring the safe flight of the UAV.

[0047] Specifically, Figure 1 and Figure 5 As shown, a water pipe buckle 14 is installed on the machine arm 7, and a buckle groove 15 for fitting the water pipe is formed on the water pipe buckle 14, and the buckle groove 15 is in an Ω structure.

[0048] The water pipe buckle 14 is used to guide and buckle the water pipe when the drone is spraying, so that the water pipe is in close contact with the arm 7, to prevent the water pipe from shaking back and forth when the drone is flying, thereby affecting the stable flight of the drone. The buckle groove 15 in the Ω structure has the same principle as the C-type closing of the buckle 4, and is used to ensure the buckling state of the water pipe.

[0049] The above description of the embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A drone frame structure based on a large folding ratio arm, comprising a body (1) and a power mechanism (16), characterized in that: An arm (2) distributed in a ring shape is installed at the side end of the machine body (1); the arm (2) is rotatably connected to a machine arm (7) mounted and installed by a matching power mechanism (16) at a side away from the machine body (1) through a hinge; the machine arm (7) is unilaterally obliquely rotated relative to the arm (2); when the machine arm (7) is rotated and folded relative to the arm (2), the machine arm (7) and the adjacent arm (2) are in an up-and-down staggered state, forming an enveloping folding structure; The arm rod (2) is provided with a clamping piece for cooperating with the machine arm (7) to be folded and fixed; A fastener is provided between the machine arm (7) and the arm rod (2); when the machine arm (7) is rotated and opened relative to the arm rod (2), the machine arm (7) and the arm rod (2) are locked by the fastener.

2. The UAV frame structure based on a large folding ratio arm according to claim 1 is characterized in that: A notch (5) is formed on the side of the arm (2) for the machine arm (7) to penetrate and embed into, and the outer diameter of the machine arm (7) is matched with the inner diameter of the arm (2).

3. The UAV frame structure based on a large folding ratio arm according to claim 1 is characterized in that: The hinged member comprises a bracket (6) fixedly mounted on the arm (2); a butt end (8) is fixedly mounted on the machine arm (7); and a shaft connection assembly is arranged between the bracket (6) and the butt end (8).

4. The UAV frame structure based on a large folding ratio arm according to claim 3 is characterized in that: The shaft connection assembly comprises a rotating shaft (10) penetrating the bracket (6) and the butt end (8), and a nut (11) is screwed and connected to the outer side of the rotating shaft (10).

5. The UAV frame structure based on a large folding ratio arm according to claim 4, characterized in that: A stop block is formed at the end of the rotating shaft (10), and the stop block and the nut (11) are used to stop both sides of the bracket (6), thereby limiting the rotating shaft (10) from being pulled away from the bracket (6).

6. The UAV frame structure based on a large folding ratio arm according to claim 1, characterized in that: The clamping member comprises a jacket (3) fixedly arranged on the outside of the arm (2), and a buckle (4) is fixedly arranged on the jacket (3) for clamping with the outer wall of the machine arm (7).

7. The UAV frame structure based on a large folding ratio arm according to claim 6, characterized in that: The end surfaces of the clamping sleeve (3) and the arm (2) that are fitted and fixed together present a matching rectangular anti-twist structure, and the buckle (4) cooperates with the machine arm (7) to embed into the clamping groove to present a C-shaped closing structure.

8. The UAV frame structure based on a large folding ratio arm according to claim 1, characterized in that: The fastener comprises threads (9) formed on the side walls of the arm (2) and the machine arm (7), and a clamping assembly. When the machine arm (7) is rotated and opened relative to the arm (2), the patterns of the two threads (9) are merged and aligned, and the threads (9) are tightened by the clamping assembly.

9. The UAV frame structure based on a large folding ratio arm according to claim 8, characterized in that: The clamping assembly comprises a nut (12) slidably mounted on the outside of the machine arm (7), a locking piece (13) being screwed on the nut (12), and anti-slip grooves are formed on the side walls of the nut (12) and the locking piece (13).

10. The UAV frame structure based on a large folding ratio arm according to claim 1, characterized in that: A water pipe buckle (14) is mounted on the machine arm (7), and a buckle groove (15) for cooperating with the water pipe clamp is formed on the water pipe buckle (14), and the buckle groove (15) is in an Ω structure.

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