A wing folding device for a drone

Abstract

The application discloses a kind of unmanned plane wing folding device, belong to unmanned plane wing technical field.It includes wing installation component, folding mechanism and multiple groups of wing components, folding mechanism includes two groups of rotating components, two groups of rotating components are respectively arranged on the length direction both ends of lower cover body, and two groups of rotating components are symmetrically arranged, drive assembly is also provided on lower cover body, and two ends of drive assembly are respectively connected with two groups of rotating components, to drive two groups of rotating components to rotate.By the drive assembly of being set drive two groups of rotating components synchronous motion, realize automation operation, and adopt mechanical locking, not rely on electromagnetic system locking, when circuit fault, voltage fluctuation or electromagnetic interference occurs, power-off unlocking situation does not occur, prevent the situation that wing loses constraint free rotation and thus crashes, by the locking component of being set fixed arm and contraction arm, the state that fixed arm and contraction arm are unfolded or contracted is locked, to complete the unfolding and contraction of wing.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) wing technology, and more specifically, to a UAV wing folding device. Background Technology

[0002] As the core component providing lift, the drone wing typically accounts for more than 60% of the overall fuselage size. Its large size in non-operational states is a key factor restricting the portability of drones. Traditional fixed-wing drones require dedicated transport cases or large storage spaces, making them unsuitable for scenarios such as individual soldier carrying or rapid vehicle deployment. Therefore, "foldable wings" have become a core optimization direction for drone structural design, and wing folding devices have become a crucial component ensuring the portability and operational flexibility of drones.

[0003] Currently, existing drone wing folding devices are mainly divided into two categories: manual folding and electric folding. However, they still have obvious defects in structural design, performance and safety, making it difficult to meet the comprehensive requirements of drones for "lightweight, high safety and convenient operation".

[0004] While electric folding devices achieve automated operation through motor drive and electromagnetic lock locking, they generally suffer from "single lock risk" and "high energy consumption and heavy weight" problems. Existing electric folding devices mostly use a single electromagnetic lock as the locking core, and its locking reliability depends entirely on the stability of the electromagnetic system's power supply. If a circuit failure, voltage fluctuation, or electromagnetic interference occurs during drone flight, the electromagnetic lock is prone to power failure and unlocking. Once the wings lose their fixed constraint, they will rotate freely around the axis of rotation, directly disrupting the drone's lift balance and causing a crash. Furthermore, to overcome the frictional resistance and aerodynamic preload during wing rotation, existing electric folding devices require a high-power drive motor (typically exceeding 50W). Combined with a reduction gear set, the overall weight can reach 400-600g, accounting for 15%-20% of the total weight of a small drone, significantly reducing the drone's endurance and payload.

[0005] In view of this, the present invention is proposed to solve the above-mentioned technical problems. Summary of the Invention

[0006] The purpose of this invention is to provide a wing folding device for unmanned aerial vehicles (UAVs) to solve the aforementioned technical problems.

[0007] To achieve the above objectives, the present invention provides the following technical solution: A drone wing folding device, comprising: The wing mounting assembly is mounted on the bottom of the UAV fuselage by fastening bolts. The wing mounting assembly includes a detachably connected lower cover and an upper cover. The folding mechanism includes two sets of rotating components, which are respectively arranged at both ends of the lower cover in the length direction and are symmetrically arranged. The lower cover is also provided with a drive component, which is connected to the two sets of rotating components at both ends to drive the two sets of rotating components to rotate. Multiple wing assemblies are respectively set at both ends of the rotating assembly. Each wing assembly includes a fixed arm and a retractable arm. The side wall of the fixed arm has a retractable groove. One end of the retractable arm is hinged to the end of the retractable groove away from the rotating assembly. The other end of the retractable arm is equipped with a rotor assembly. A slidable locking assembly is fitted on the fixed arm. The locking assembly is used to lock the position of the retractable arm.

[0008] Furthermore, the rotating assembly includes a drive shaft rotatably mounted on the lower cover via a bearing housing. Bevel gears are symmetrically arranged at both ends of the drive shaft, and a driven gear meshing with the bevel gear is arranged on one side of the bevel gear. The driven gear is mounted via a gear seat, and a fixed arm is fixedly mounted on the gear seat. The driven gear is fixedly connected to the gear seat.

[0009] Furthermore, the drive assembly includes a drive gear mounted on a drive shaft, a meshing rack at the bottom of the drive gear, the rack being slidably mounted on the lower cover, and end plates at the near ends of the two racks, with a bidirectional electric actuator positioned between the two end plates, the two output ends of the bidirectional electric actuator being fixedly connected to the two end plates respectively.

[0010] Furthermore, a groove is provided on the fixed arm along its length, and a locking frame is fitted on the fixed arm. The bottom of the locking frame is slidably disposed in the groove through a protrusion. The locking frame is equipped with a detachable locking knob, and both ends of the retractable arm are provided with a front fixing hole and a rear fixing hole. The fixed arm is provided with a mating hole at the end near the gear seat. When the fixed arm and the retractable arm are extended, the locking knob is threadedly connected to the front fixed hole. When the fixed arm and the retractable arm are retracted, the rear fixed hole and the mating hole are coaxially connected, and the locking knob extends into the mating hole and is threadedly connected to the rear fixed hole.

[0011] Furthermore, baffles are symmetrically arranged on the lower cover, with the baffles arranged along the length of the lower cover. A partition plate is vertically arranged in the middle of the baffle to form multiple receiving cavities, which are used to accommodate the fixed arm and the retractable arm.

[0012] Furthermore, the lower cover is provided with rotatable support shafts on all four sides, and the driven gear is fixedly mounted on the support shafts.

[0013] Furthermore, limit baffles are provided at both ends of the lower cover and the upper cover in the width direction, and the two limit baffles at the same end are connected by fastening bolts.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: The lower and upper covers are used to install and protect the folding mechanism. The drive components drive the two sets of rotating components to move synchronously, thereby expanding or contracting the wing assembly. This achieves automated operation and uses mechanical locking, not relying on an electromagnetic system. In the event of circuit failure, voltage fluctuation, or electromagnetic interference, there will be no power failure and unlocking, preventing the wing from losing restraint and rotating freely, thus preventing a crash. When expanding or contracting the rotor assembly, the locking components lock the fixed arm and the retracting arm, and lock their expanded or contracted states, thereby completing the expansion and contraction of the wing. The operation is simple and convenient for various emergency rescues. Attached Figure Description

[0015] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention, but do not constitute an undue limitation of the invention. Obviously, the drawings described below are merely some embodiments, and those skilled in the art can obtain other drawings based on these drawings without creative effort. In the drawings: Figure 1 This is a schematic diagram of the structure of the UAV wing folding device provided in this embodiment of the application; Figure 2 for Figure 1 A structural diagram without the drone's fuselage; Figure 3 for Figure 2 A schematic diagram of the structure after removing the top cover; Figure 4 for Figure 3 Enlarged view of point A in the middle; Figure 5 This is a schematic diagram of the wing mounting assembly of the UAV wing folding device provided in this embodiment of the application.

[0016] Reference numerals: 1. UAV fuselage; 2. Wing mounting assembly; 3. Folding mechanism; 4. Wing assembly; 5. Rotor assembly; 21. Lower cover; 22. Upper cover; 23. Baffle; 24. Limiting baffle; 25. Support shaft; 31. Drive shaft; 32. Bevel gear; 33. Driven gear; 34. Drive gear; 35. Rack; 36. Bidirectional electric actuator; 37. Gear seat; 41. Fixed arm; 42. Retractable arm; 43. Rear fixing hole; 44. Slide groove; 45. Mating hole; 46. Locking frame; 47. Locking knob. Detailed Implementation

[0017] The technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0018] See Figures 1 to 5 As shown, a drone wing folding device includes: a wing mounting assembly 2, a folding mechanism 3, and multiple sets of wing assemblies 4. The wing mounting assembly 2 is installed on the bottom of the drone fuselage 1 by fastening bolts. The wing mounting assembly 2 includes a detachably connected lower cover 21 and an upper cover 22. The folding mechanism 3 includes two sets of rotating assemblies, which are respectively arranged at both ends of the lower cover 21 along its length and are symmetrically arranged. The lower cover 21 is also provided with a drive assembly, which is connected at both ends to the two sets of rotating assemblies to drive the two sets of rotating assemblies to rotate. Multiple sets of wing assemblies 4 are respectively arranged at both ends of the rotating assemblies. The wing assembly 4 includes a fixed arm 41 and a retractable arm 42. The fixed arm 41 has a retractable groove on its side wall. One end of the retractable arm 42 is hinged in the retractable groove at the end away from the rotating assembly. The other end of the retractable arm 42 is provided with a rotor assembly 5. A slidable locking assembly is fitted on the fixed arm 41 to lock the position of the retractable arm 42.

[0019] It should be noted that the drone fuselage 1 directly adopts existing technology. This application does not provide a detailed description of the specific structure of the drone fuselage 1, which includes a battery assembly and a flight control module. The drive assembly is electrically connected to the flight control module. The rotor assembly 5 includes a rotor motor and a rotor. The rotor is mounted on the output shaft of the rotor motor. The rotation of the output shaft of the rotor motor drives the rotor to rotate.

[0020] In the above scheme, the lower cover 21 and upper cover 22 are used to install and protect the folding mechanism 3. The driving component drives the two sets of rotating components to move synchronously, thereby driving the wing assembly 4 to unfold or retract, realizing automated operation. It adopts mechanical locking and does not rely on electromagnetic system locking. In the event of circuit failure, voltage fluctuation or electromagnetic interference, there will be no power failure unlocking, preventing the wing from losing restraint and rotating freely, thus preventing the aircraft from crashing. When unfolding and retracting the rotor assembly 5, the locking component locks the fixed arm 41 and the retracting arm 42, and locks the unfolded or retracted state of the fixed arm 41 and the retracting arm 42, thereby completing the unfolding and retraction of the wing. The operation is simple and convenient for various emergency rescues.

[0021] See some possible implementations. Figure 3 As shown, the rotating assembly includes a drive shaft 31 rotatably mounted on the lower cover 21 via a bearing seat. Bevel gears 32 are symmetrically arranged at both ends of the drive shaft 31. A driven gear 33 meshes with the bevel gear 32 on one side. The driven gear 33 is mounted via a gear seat 37. A fixed arm 41 is fixedly mounted on the gear seat 37. The driven gear 33 is fixedly connected to the gear seat 37.

[0022] In the above scheme, the drive shaft 31 is rotatably mounted on the lower cover 21 through the bearing seat. When the wing assembly 4 is deployed or retracted, the two drive shafts 31 are controlled to rotate synchronously so that the drive shaft 31 rotates and drives the bevel gear 32 to rotate. The rotation of the bevel gear 32 drives the gear seat 37 to rotate through meshing with the driven gear 33, thereby driving the wing assembly 4 to deploy or retract.

[0023] See some possible implementations. Figure 3 As shown, the drive assembly includes a drive gear 34 mounted on a drive shaft 31. A meshing rack 35 is provided at the bottom of the drive gear 34. The rack 35 is slidably mounted on the lower cover 21. Each of the two racks 35 has an end plate at one end close to each other. A bidirectional electric actuator 36 is provided between the two end plates. The two output ends of the bidirectional electric actuator 36 are fixedly connected to the two end plates respectively.

[0024] In the above scheme, when the control drive component is started, the bidirectional electric push rod 36 is first started by the flight control module of the UAV body 1, so that the output end of the bidirectional electric push rod 36 extends or retracts. The extension or retraction of the output end of the bidirectional electric push rod 36 drives the two racks 35 to move towards or relative to each other through the end plate. The two racks 35 move towards or relative to each other and drive the two drive shafts 31 to rotate in opposite directions by meshing with the drive gear 34.

[0025] See some possible implementations. Figure 4 As shown, a groove 44 is provided on the fixed arm 41 along its length direction. A locking frame 46 is fitted on the fixed arm 41. The bottom of the locking frame 46 is slidably disposed in the groove 44 through a protrusion. A detachable locking knob 47 is provided on the locking frame 46. Both ends of the retractable arm 42 are provided with a front fixing hole and a rear fixing hole 43. A mating hole 45 is provided on the end of the fixed arm 41 near the gear seat 37. When the fixed arm 41 and the retractable arm 42 are extended, the locking knob 47 is threadedly connected to the front fixing hole. When the fixed arm 41 and the retractable arm 42 are retracted, the rear fixing hole 43 is coaxially connected to the mating hole 45. The locking knob 47 extends into the mating hole 45 and is threadedly connected to the rear fixing hole 43. The bottom of the locking knob 47 has a threaded rod that mates with the front fixing hole, the rear fixing hole 43, or the mating hole 45.

[0026] In the above scheme, when unfolding the retractable arm 42, the retractable arm 42 is rotated around the hinge axis so that the retractable arm 42 is parallel to the fixed arm 41. Then, the locking frame 46 is slid so that the protrusion at the bottom of the locking frame 46 slides to the outermost end of the slide groove 44. At this time, the threaded rod at the bottom of the locking knob 47 is coaxial with the front fixing hole. Rotating the locking knob 47 causes the threaded rod to screw into the front fixing hole, completing the unfolding and fixing of the retractable arm 42. When retracting the retractable arm 42, the locking knob 47 is released, and the locking frame 46 is slid so that the protrusion at the bottom of the locking frame 46 slides to the innermost end of the slide groove 44. At this time, the retractable arm 42 is rotated around the hinge axis so that the retractable arm 42 retracts into the retractable groove, and the rear fixing hole 43 and the mating hole 45 are coaxial. Then, the locking knob 47 is rotated again, and the threaded rod at the bottom of the locking knob 47 passes through the mating hole 45 and is threadedly connected to the rear fixing hole 43, completing the retraction and fixing of the retractable arm 42.

[0027] See some possible implementations. Figure 5 As shown, baffles 23 are symmetrically arranged on the lower cover 21. The baffles 23 are arranged along the length of the lower cover 21. A partition plate is vertically arranged in the middle of the baffle 23 to form multiple receiving cavities. The receiving cavities are used to receive the fixed arm 41 and the retractable arm 42.

[0028] In the above scheme, the cavity formed by the baffle 23 and the partition plate is used to retract the fixed arm 41 and the retractable arm 42. When the lower cover 21 and the upper cover 22 are fixed, the baffle 23 also plays a role in enhancing the structural stability of the lower cover 21 and the upper cover 22.

[0029] See some possible implementations. Figure 5 As shown, the lower cover 21 is provided with rotatable support shafts 25 on all four sides, and the driven gear 33 is fixedly mounted on the support shafts 25. The support shafts 25 are used to install the driven gear 33.

[0030] See some possible implementations. Figure 5 As shown, both ends of the lower cover 21 and the upper cover 22 in the width direction are provided with limit baffles 24, and the two limit baffles 24 at the same end are connected by fastening bolts. The limit baffles 24 play a protective role for the folding mechanism 3. At the same time, when the rack 35 abuts against the limit baffles 24, the fixed arm 41 and the retractable arm 42 are extended to the maximum angle.

[0031] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A wing folding device for unmanned aerial vehicles (UAVs), characterized in that, include: The wing mounting assembly (2) is mounted on the bottom of the UAV fuselage (1) by fastening bolts. The wing mounting assembly (2) includes a detachably connected lower cover (21) and an upper cover (22). Folding mechanism (3), the folding mechanism (3) includes two sets of rotating components, the two sets of rotating components are respectively arranged at both ends of the length direction on the lower cover (21), and the two sets of rotating components are symmetrically arranged. The lower cover (21) is also provided with a driving component, the two ends of the driving component are respectively connected to the two sets of rotating components to drive the two sets of rotating components to rotate. Multiple sets of wing assemblies (4) are respectively disposed at both ends of the rotating assembly. Each wing assembly (4) includes a fixed arm (41) and a retractable arm (42). The fixed arm (41) has a retractable groove on its side wall. One end of the retractable arm (42) is hinged to the retractable groove at the end away from the rotating assembly. A rotor assembly (5) is disposed on the other end of the retractable arm (42). A slidable locking assembly is fitted on the fixed arm (41). The locking assembly is used to lock the position of the retractable arm (42). The rotating assembly includes a drive shaft (31) rotatably mounted on the lower cover (21) via a bearing seat. The drive shaft (31) has bevel gears (32) symmetrically arranged at both ends. A driven gear (33) meshes with the bevel gear (32) on one side. The driven gear (33) is mounted via a gear seat (37). The fixed arm (41) is fixedly mounted on the gear seat (37). The driven gear (33) is fixedly connected to the gear seat (37). The drive assembly includes a drive gear (34) mounted on a drive shaft (31), and a meshing rack (35) is provided at the bottom of the drive gear (34). The rack (35) is slidably mounted on the lower cover (21). Each of the two racks (35) has an end plate at one end close to each other. A bidirectional electric actuator (36) is provided between the two end plates. The two output ends of the bidirectional electric actuator (36) are fixedly connected to the two end plates respectively. The fixed arm (41) has a sliding groove (44) along its length direction, and a locking frame (46) is fitted on the fixed arm (41). The bottom of the locking frame (46) is slidably disposed in the sliding groove (44) through a protrusion. The locking frame (46) is provided with a detachable locking knob (47), and both ends of the retractable arm (42) are provided with a front fixing hole and a rear fixing hole (43). The fixed arm (41) is provided with a mating hole (45) at the end near the gear seat (37). When the fixed arm (41) and the retractable arm (42) are extended, the locking knob (47) is threadedly connected to the front fixed hole. When the fixed arm (41) and the retractable arm (42) are retracted, the rear fixed hole (43) and the mating hole (45) are coaxially connected. The locking knob (47) extends into the mating hole (45) and is threadedly connected to the rear fixed hole (43).

2. The UAV wing folding device according to claim 1, characterized in that, The lower cover (21) is symmetrically provided with baffles (23), which are arranged along the length of the lower cover (21). A partition plate is vertically arranged in the middle of the baffle (23) to form multiple accommodating cavities. The accommodating cavities are used to accommodate the fixed arm (41) and the retractable arm (42).

3. The UAV wing folding device according to claim 2, characterized in that, The lower cover (21) is provided with rotatable support shafts (25) on all four sides, and the driven gear (33) is fixedly mounted on the support shafts (25).

4. The UAV wing folding device according to claim 3, characterized in that, Both ends of the lower cover (21) and the upper cover (22) in the width direction are provided with limit baffles (24), and the two limit baffles (24) at the same end are connected by fastening bolts.

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