Folding wing device of unmanned aerial vehicle
By adopting a combination of gears and springs in the folding wing device of the drone, the coaxial reversal and high consistency of the wing are achieved, and the problem of excessive rolling torque or axial torque after deployment is solved, ensuring the stability and safety of the wing.
Patent Information
- Application Number
- CN202322766358.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2023-10-15
- Publication Date
- 2025-03-28
- Estimated Expiration
- 2033-10-15
AI Technical Summary
After the existing drone folding wing device is deployed, the rolling torque or axial torque is too large, causing the wing to deform or stall and crash.
Two gears are connected by threads, and a compression spring is installed between the gears. After being deployed, it is self-locked by vertical threads to achieve coaxial reversal and ensure the consistency of the wing height.
It effectively solves the problem of excessive rolling torque or axial torque after the folding wings of the drone is expanded, ensuring that the wing does not deform during high-speed flight and avoids stalling and crashing.
Smart Images
Figure CN222682710U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of unmanned aerial vehicles, and in particular relates to a folding wing device for an unmanned aerial vehicle. Background Art
[0002] The development and application of drones have attracted great attention from all countries; however, small and medium-sized drones have limited load-bearing capacity, and their speed and range are restricted, and they are often unable to perform long-distance missions; in order to effectively utilize the characteristics of small drones, missiles or large transport aircraft can be used to remotely launch small double-wing drones. On the one hand, this can make up for the disadvantage of insufficient range and flight time of small drones, and on the other hand, the penetration capability of missiles or transport aircraft can be used to effectively transport drone clusters to enemy areas, greatly reducing the probability of being discovered and shot down.
[0003] The wing folding device is one of the key technologies of double-wing UAVs. The traditional variable-sweep wing folding solution is to fix the wing roots of the two wings on the axial shaft and arrange them up and down; after folding, the two wings are stacked together. The problem with this folding solution is that the two wings with inconsistent heights generate different lifts, which will produce a rolling moment. The ailerons need to separately allocate a part of the angle margin to balance the rolling moment, which reduces the adjustment ability of the ailerons.
[0004] The UAV wing folding device developed on the basis of the above divides the axial rotation axis into two and places them at the edge of the fuselage section, with the wings on both sides stacked side by side; this folding method can solve the problem of the wing folding cross-sectional area being too large, but the wing using this folding method causes a waste of the wing folding surface area, and does not have a self-locking function. When flying at high speed, the axial torque generated by the wing relative to the rotation axis is too large, which will cause the wing to deform or even stall and crash.
[0005] Therefore, there is an urgent need for a wing folding device that can quickly achieve coaxial reversal and maintain consistent wing height after unfolding, so as to solve the problem of excessive rolling moment or axial torque after the folding wings of the UAV are unfolded. Summary of the invention
[0006] The technical problem solved by the utility model is: in view of the shortcomings of the existing problems, a new unmanned aerial vehicle folding wing device is proposed; compared with the traditional folding device, before the folding device is unfolded, the two gears are connected by threads and a compression spring is installed between the two gears. After the folding device is unfolded, the vertical threads are used for self-locking, which solves the problem of excessive rolling moment or axial torque after the unmanned aerial vehicle folding wings are unfolded.
[0007] To achieve the above-mentioned purpose, the technical solution adopted by the utility model is as follows: a folding wing device for an unmanned aerial vehicle, characterized in that it includes a self-locking mechanism, a power mechanism, a transmission mechanism and a box body, two self-locking mechanisms are arranged on the right side of the box body, a power mechanism is arranged on the left side of the self-locking mechanism, and a transmission mechanism is arranged at the end of the power mechanism; the self-locking mechanism includes a first baffle, a second baffle, a third baffle, a fourth baffle, a first hook, a second hook, a first connecting shaft and a steering gear, the first baffle, the second baffle, the third baffle and the fourth baffle are respectively placed on both sides of the first hook and the second hook, and the first hook and The first connecting shaft and the servo are placed inside the second hook; the power mechanism includes a connecting plate, a first spring, a second spring, a first push rod, a second push rod, a pin and a positioning rod; the left side of the connecting plate is connected to the positioning rod, and the right side of the connecting plate is connected to the first push rod, the second push rod, the first spring and the second spring; the pins are installed in the inner holes of the first push rod and the second push rod; the transmission mechanism includes a first gear shaft, a second gear shaft, a gear sleeve, a nut, a circular rack and a third spring; the first gear shaft and the second gear shaft are arranged at the front end of the circular rack, and the first gear shaft is sequentially provided with a nut, a gear sleeve and a third spring from top to bottom.
[0008] Preferably, the first baffle, the second baffle, the third baffle, the fourth baffle, the first hook and the second hook are all in contact with the fourth connecting shaft, and both ends of the fourth connecting shaft are connected to the guide grooves on the side of the box body.
[0009] Preferably, the first baffle, the second baffle and the first hook are connected via a second connecting shaft, and the third baffle, the fourth baffle and the second hook are connected via a third connecting shaft.
[0010] Preferably, the right side of the circular rack is inserted into the hole on the left side of the connecting plate and connected by a pin.
[0011] Preferably, the circular rack meshes with the gears at the lower ends of the first gear shaft and the second gear shaft, and the gear at the upper end of the second gear shaft meshes with the gear sleeve. The middle portion of the first gear shaft and the bottom portion of the gear sleeve are threadedly matched.
[0012] Preferably, the first gear shaft and the nut are threadedly connected, the nut cooperates with the upper wing, the lower wing is placed at the bottom of the upper wing, and the lower wing cooperates with the top of the gear sleeve.
[0013] The advantages of the utility model compared with the prior art are:
[0014] (1) The utility model adopts a spring as the power source, and a gear and a circular rack for transmission, so it can be deployed quickly and has high movement reliability;
[0015] (2) The utility model realizes the coaxial reversal of the wing by using the cooperation between three gears and a circular rack, thereby reducing the fuselage width of the folding UAV;
[0016] (3) The utility model adopts a gear shaft and a gear sleeve with threads and vertical threads, and installs a spring between the gear shaft and the gear sleeve, which solves the problem of up and down misalignment of the double-layer wings of the drone after unfolding;
[0017] (4) Except for the steering gear, all other parts in the present invention are purely mechanical parts with high reliability and no inflammable and explosive dangerous goods such as gunpowder and high-pressure gas. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 This is a schematic diagram of the mechanism of the double-layer UAV folding and unfolding device in the folded state.
[0019] Figure 2 This is a schematic diagram of the mechanism of the double-layer UAV folding and unfolding device in the unfolded state.
[0020] Figure 3 Schematic diagram of the explosion of the folding and unfolding device of a double-layer drone.
[0021] Figure 4 This is a partial cross-sectional view of the double-layer UAV folding and unfolding device in the folded state.
[0022] Figure 5 This is a schematic diagram of the double-layer UAV folding and unfolding device with wings in the folded state.
[0023] In the figure: 1. upper wing, 2. lower wing, 3. box, 4. self-locking mechanism, 5. power mechanism, 6. transmission mechanism, 401. first baffle, 402. first hook, 403. second baffle, 404. third baffle, 405. second hook, 406. fourth baffle, 407. second connecting shaft, 408. first connecting shaft, 409. third connecting shaft, 410. steering gear, 51. fourth connecting shaft, 52. first push rod, 53. first spring, 54. second push rod, 55. pin, 56. second spring, 57. connecting plate, 58. circular rack, 59. positioning rod, 61. first gear shaft, 62. second gear shaft, 63. third spring, 64. gear sleeve, 65. nut. Implementation
[0024] The utility model is described in detail below with reference to specific examples; the following description is helpful for those skilled in the art to further understand the utility model, but does not limit the utility model in any form; it should be pointed out that for those skilled in the art, several modifications and improvements can be made without departing from the concept of the utility model, which all belong to the protection scope of the utility model.
[0025] Figure 1-5As shown, a folding wing device of a drone of the utility model comprises a self-locking mechanism 4, a power mechanism 5, a transmission mechanism 6 and a box body 3, wherein the self-locking mechanism 4 is arranged on the right side of the box body 3, the power mechanism 5 is arranged on the left side of the self-locking mechanism 4, and the transmission mechanism 6 is arranged at the end of the power mechanism 5.
[0026] The self-locking mechanism 4 includes a first baffle 401, a second baffle 403, a third baffle 404, a fourth baffle 406, a first hook 402, a second hook 405, a first connecting shaft 408, a second connecting shaft 407 and a third connecting shaft 409. The first hook 402 is tightly attached to the first baffle 401 and the second baffle 403 on both sides and forms a clearance fit with the second connecting shaft 407. The second hook 405 is tightly attached to the third baffle 404 and the fourth baffle 406 on both sides and forms a clearance fit with the third connecting shaft 409. The first hook 402 and the second hook 405 form an interference fit with the first connecting shaft 408.
[0027] The power mechanism 5 includes a connecting plate 57, a first spring 53, a second spring 56, a first push rod 52, a second push rod 54, a fourth connecting shaft 51 and a positioning rod 59. The connecting plate 57 is connected to the positioning rod 59, the first push rod 52 and the second push rod 54 by epoxy resin. The first push rod 52 and the second push rod 54 pass through the first spring 53 and the second spring 56. The inner holes of the first push rod 52 and the second push rod 54 are installed in the fourth connecting shaft 51.
[0028] The transmission mechanism 6 includes a first gear shaft 61, a second gear shaft 62, a gear sleeve 64, a nut 65, a circular rack 58 and a third spring 63. The circular rack 58 is meshed with the first gear shaft 61 and the second gear shaft 62. The first gear shaft 61 is clearance-fitted with the third spring 63 and the gear sleeve 64. The first gear shaft 61 is threadedly connected with the nut 65.
[0029] Both ends of the fourth connecting shaft 51 are connected to the guide grooves on the side of the box body 3 . The guide grooves limit the moving distance of the fourth connecting shaft 51 . The fourth connecting shaft 51 limits the moving distance of the circular rack 58 .
[0030] The right side of the circular rack 58 is inserted into the hole on the left side of the connecting plate 57 and connected by the pin 55. The circular rack 58 meshes with the gears at the lower ends of the first gear shaft 61 and the second gear shaft 62, and the gear at the upper end of the second gear shaft 62 meshes with the gear sleeve 64. The middle part of the first gear shaft 61 and the bottom of the gear sleeve 64 are threadedly matched.
[0031] The first gear shaft 61 and the nut 65 are threadedly connected, the nut 65 is matched with the upper wing 1, the lower wing 2 is placed at the bottom of the upper wing, and the lower wing 2 is matched with the top of the gear sleeve 64.
[0032] The working process of the utility model is as follows: in the initial state, the fourth connecting shaft 51 of the power mechanism 5 is fixed by the first hook 402 and the second hook 405 of the self-locking mechanism 4, and the first gear shaft 61 and the gear sleeve 64 are connected by threads to prevent the wing from opening. At the same time, the first spring 53, the second spring 56 and the third spring 63 are all in a compressed state, such as Figure 1 As shown, after the rocker arm of the servo 410 rotates, the first hook 402 and the second hook 405 are lifted, the first spring 53 and the second spring 56 begin to release, the first spring 53 and the second spring 56 drive the circular rack 58 forward, the circular rack 58 drives the first gear shaft 61 and the second gear shaft 62 to rotate, the second gear shaft 62 drives the gear sleeve 64 to rotate, so that the threaded connection between the first gear shaft 61 and the gear sleeve 64 rotates and the upper wing 1 and the lower wing 2 are unfolded around the axis, and the threaded connection between the first gear shaft 61 and the gear sleeve 64 is unfolded while the upper wing 1 and the lower wing 2 are unfolded to a predetermined angle, the left end of the guide groove encounters the fourth connecting shaft 51 and the unfolding stops, the third spring 63 begins to release, the third spring 63 drives the gear sleeve 64 forward, the gear sleeve 64 is vertically connected with the first gear shaft 61, the gear sleeve 64 cooperates with the upper surface of the box body 3, the lower wing 2 rises to a predetermined height, the upper surface of the gear sleeve 64 and the lower surface of the nut 65 contact and move to stop, the whole unfolding process is completed, and the unfolding state is as shown in FIG. Figure 2 shown.
[0033] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A folding wing device for an unmanned aerial vehicle, characterized in that: The invention comprises a box body (3), a self-locking mechanism (4), a power mechanism (5) and a transmission mechanism (6); the self-locking mechanism (4) is arranged on the right side of the box body (3), the power mechanism (5) is arranged on the left side of the self-locking mechanism (4), and the transmission mechanism (6) is arranged at the end of the power mechanism (5); the self-locking mechanism comprises a first baffle (401), a second baffle (403), a third baffle (404), a fourth baffle (406), a first hook (402), a second hook (405), a first connecting shaft (408) and a steering gear (410); the first baffle (401), the second baffle (403), the third baffle (404) and the fourth baffle (406) are respectively arranged on both sides of the first hook (402) and the second hook (405); the first connecting shaft (408) and the steering gear (410) are arranged inside the first hook (402) and the second hook (405); the power mechanism The invention comprises a connecting plate (57), a first spring (53), a second spring (56), a first push rod (52), a second push rod (54), a pin (55) and a positioning rod (59). The left side of the connecting plate (57) is connected to the positioning rod (59), and the right side of the connecting plate (57) is connected to the first push rod (52), the second push rod (54), the first spring (53) and the second spring (56). The inner holes of the first push rod (52) and the second push rod (54) are filled with the pin (55). The transmission mechanism comprises a first gear shaft (61), a second gear shaft (62), a gear sleeve (64), a nut (65), a circular rack (58) and a third spring (63). The front end of the circular rack (58) is provided with the first gear shaft (61) and the second gear shaft (62). The first gear shaft (61) is provided with a nut (65), a gear sleeve (64) and a third spring (63) in sequence from top to bottom.
2. The folding wing device of a drone according to claim 1, characterized in that: The first baffle (401), the second baffle (403), the third baffle (404), the fourth baffle (406), the first hook (402), and the second hook (405) are all in contact with the fourth connecting shaft (51), and both ends of the fourth connecting shaft (51) are connected to the guide grooves on the side of the box body (3).
3. The folding wing device of a drone according to claim 1, characterized in that: The first baffle (401), the second baffle (403) and the first hook (402) are connected via a second connecting shaft (407), and the third baffle (404), the fourth baffle (406) and the second hook (405) are connected via a third connecting shaft (409).
4. The folding wing device for an unmanned aerial vehicle according to claim 1, characterized in that: The right side of the circular rack (58) is inserted into the hole on the left side of the connecting plate (57) and connected via a pin (55).
5. The folding wing device for a drone according to claim 1, characterized in that: The circular rack (58) meshes with the gears at the lower ends of the first gear shaft (61) and the second gear shaft (62), the gear at the upper end of the second gear shaft (62) meshes with the gear sleeve (64), and the middle portion of the first gear shaft (61) and the bottom portion of the gear sleeve (64) are threadedly matched.
6. The folding wing device for a drone according to claim 1, characterized in that: The first gear shaft (61) and the nut (65) are threadedly connected, the nut (65) cooperates with the upper wing (1), the lower wing (2) is placed at the bottom of the upper wing (1), and the lower wing (2) cooperates with the top of the gear sleeve (64).