CN119683041A - Self-locking buckle, folding wing and barrel type folding wing unmanned aerial vehicle - Google Patents
Self-locking buckle, folding wing and barrel type folding wing unmanned aerial vehicle Download PDFInfo
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- CN119683041A CN119683041A CN202411913653.9A CN202411913653A CN119683041A CN 119683041 A CN119683041 A CN 119683041A CN 202411913653 A CN202411913653 A CN 202411913653A CN 119683041 A CN119683041 A CN 119683041A
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- wing
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- main wing
- folding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/50—Foldable or collapsible UAVs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/70—Transport or storage specially adapted for UAVs in containers
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Abstract
本发明公开了一种自锁卡扣、折叠机翼、筒式折叠翼无人机。包括弹性卡勾(401)和滑坡(402)，弹性卡勾(401)底面设有卡槽(403)，卡槽(403)深度沿弹性卡勾(401)长度方向递增，卡槽(403)底面的头端与弹性卡勾(401)底面连接，卡槽(403)底面的尾端经立直面A(404)与弹性卡勾(401)底面连接；滑坡(402)整体呈直角三角块，滑坡(402)顶面为直角三角块的斜面，尾端为直角三角块的立直面B(405)，底面为直角三角块的平直面(406)；自锁卡扣扣合时，卡槽(403)底面与滑坡(402)顶面对合，立直面A(404)与立直面B(405)对合。本发明具有收纳空间小、折叠机构简单、能有效改善机翼气动特性的特点。
The invention discloses a self-locking buckle, folding wing, and barrel-type folding wing UAV. The invention comprises an elastic hook (401) and a slide (402). The bottom surface of the elastic hook (401) is provided with a slot (403). The depth of the slot (403) increases along the length direction of the elastic hook (401). The head end of the bottom surface of the slot (403) is connected to the bottom surface of the elastic hook (401). The tail end of the bottom surface of the slot (403) is connected to the bottom surface of the elastic hook (401) via a vertical surface A (404). The slide (402) is a right-angled triangle block as a whole. The top surface of the slide (402) is the inclined surface of the right-angled triangle block, the tail end is the vertical surface B (405) of the right-angled triangle block, and the bottom surface is the flat surface (406) of the right-angled triangle block. When the self-locking buckle is buckled, the bottom surface of the slot (403) is matched with the top surface of the slide (402), and the vertical surface A (404) is matched with the vertical surface B (405). The present invention has the characteristics of small storage space, simple folding mechanism and effective improvement of the aerodynamic characteristics of the wing.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a self-locking buckle, a folding wing and a barrel type folding wing unmanned aerial vehicle.
Background
The barrel type folding wing unmanned aerial vehicle is provided with the wings which can be folded and unfolded, can be stored in the storage barrel in a folded state, is convenient to transport, and can be used for a single person to execute tasks. At present, a cylindrical folding wing unmanned aerial vehicle is folded in a unfolding direction, and therefore the problem that the chord-wise size of the wing is limited by a storage barrel is necessarily faced, on one hand, the chord length of the wing is smaller, the Reynolds number is limited, the aerodynamic characteristics of the unmanned aerial vehicle are poor, the aerodynamic efficiency is reduced, on the other hand, the main wing area of the wing is limited, the lifting space is limited, and the bearing capacity of the unmanned aerial vehicle is limited. Although some folding wing unmanned aerial vehicles choose to fold the trailing edge to obtain a larger wing size during storage, one of the problems is that more space cost is required in the height direction after the wings are folded, the storage effect is poor, and the other is that an active folding mechanism is usually adopted for the wings of the airplane, the folding mechanism is complex, the reliability is low, and additional weight is brought, as shown in fig. 9. In summary, the comprehensive performance of the unmanned aerial vehicle is not improved by folding only in the unfolding direction or by adopting a common trailing edge folding mode. Therefore, a trailing edge folding mechanism which has a small storage space and a simple folding mechanism and can effectively improve the aerodynamic characteristics of the wing is demanded, and the trailing edge folding mechanism becomes a serious difficulty in the field of the design of the current barrel type folding wing unmanned aerial vehicle.
Disclosure of Invention
The invention aims to provide a self-locking buckle, a folding wing and a barrel type folding wing unmanned aerial vehicle. The invention has the characteristics of small storage space, simple folding mechanism and capability of effectively improving the aerodynamic characteristics of the wing.
The technical scheme is that the self-locking buckle comprises an elastic clamping hook and a landslide, wherein the bottom surface of the elastic clamping hook is provided with a clamping groove, the depth of the clamping groove increases gradually along the length direction of the elastic clamping hook, the head end of the bottom surface of the clamping groove is connected with the bottom surface of the elastic clamping hook, the tail end of the bottom surface of the clamping groove is connected with the bottom surface of the elastic clamping hook through a vertical surface A, the whole landslide is a right triangular block, the top surface of the landslide is an inclined surface of the right triangular block, the tail end of the landslide is a vertical surface B of the right triangular block, the bottom surface of the landslide is a flat surface of the right triangular block, and when the self-locking buckle is buckled, the bottom surface of the clamping groove is matched with the top surface of the landslide, and the vertical surface A is matched with the vertical surface B.
In the self-locking buckle, the top surface of the elastic clamping hook is streamline.
The folding wing with the self-locking buckle comprises a main wing, wherein the bottom surface of the tail end of the main wing is connected with an extension trailing edge through a semi-embedded hinge, an elastic clamping hook of the self-locking buckle is arranged on the top surface of the tail end of the main wing, a landslide is arranged on the top surface of the head end of the extension trailing edge through a flat surface, the head end of the bottom surface of a clamping groove is aligned with the end surface of the tail end of the main wing, and the head end of the landslide is aligned with the head end surface of the extension trailing edge.
In the folded wing, the ratio of the width of the extended trailing edge to the chord length of the wing profile is 30% ± 10%.
In the folded wing, in the unfolded state, the tail end face of the main wing is in butt joint with the head end face of the extended trailing edge, and the tail end profile of the main wing is in smooth transition with the head end profile of the extended trailing edge.
In the folding wing, the semi-embedded hinge is a sheet hinge and comprises a hinge piece A, a hinge piece B, a rotating shaft and a torsion spring, wherein the hinge piece A and the hinge piece B can rotate 180 degrees around the rotating shaft, the elasticity of the torsion spring can enable the two hinge pieces to be in an unfolding state in a free state, the hinge piece A is semi-embedded in the bottom surface of the tail end of the main wing, and the hinge piece B is semi-embedded in the bottom surface of the head end of the extended rear edge.
In the folding wing, the main wing and the extended trailing edge are connected through more than one semi-embedded hinge.
In the folding wing, the main wing and the extended trailing edge are locked by more than one self-locking buckle.
A barrel type folding wing unmanned aerial vehicle is provided with the folding wing.
The wing has the advantages that the wing is prolonged in a thin plate mode, the wing is unfolded by utilizing the moment of the spring, and the wing is locked by the self-locking buckle, so that the storage space is effectively saved, the folding mechanism is simplified, and the chord length and the main wing area of the wing are effectively improved. Specifically, the method has the following beneficial effects:
1. Compared with a folding wing unmanned aerial vehicle with folding unmanned aerial vehicle without a rear edge, the rear edge extension folding locking mechanism can respectively increase the wing chord length of the folding wing unmanned aerial vehicle by more than 30%, so that the main wing and the cruising Reynolds number of the folding wing unmanned aerial vehicle are respectively increased by more than 30%, the bearing capacity of the folding wing unmanned aerial vehicle is increased by more than 20%, the cruising lift-drag ratio is increased by more than 10%, and the flying performance is obviously enhanced.
Taking a cylinder type folding wing unmanned aerial vehicle with a cruising speed of 15m/s, a cruising lift coefficient of 0.86, a wingspan of 2m and a cylinder size of 0.25m as an example, the unmanned aerial vehicle is limited by the cylinder size, and the chord length of the aircraft wing is not more than 0.25m at maximum when no folding trailing edge exists. After the trailing edge folding scheme is adopted, the chord length of the aircraft wing can be increased to be more than 0.325m, the main wing area of the aircraft can be increased from 0.5m 2 to 0.65m 2, the cruising Reynolds number of the aircraft wing can be increased from 250000 to 330000, and the cruising lift-drag ratio of the aircraft is increased by 20%. The aircraft take-off weight can thus be increased from 6.04kg to 7.86kg, but the required thrust only has to be increased from 0.357kg to 0.393kg, see fig. 8.
2. The extension trailing edge is thin plate shape, and with the smooth transition of wing section afterbody, can effectively reduce the accommodation space of direction of height after folding.
3. The extension trailing edge is connected with the main wing through a semi-embedded hinge, the trailing edge is unfolded through the elastic force provided by the hinge torsion spring, and the semi-embedded design is simple and reliable, so that the resistance in the flight stage can be reduced.
4. After the trailing edge is unfolded, the main wing can be folded upwards further by aerodynamic force until the main wing is contacted with a separating surface of the extended trailing edge (the tail end surface of the main wing is extended to the head end surface of the trailing edge), so that a complex folding device is omitted.
5. The main wing is provided with the auto-lock buckle structure with extension trailing edge top, can realize the auto-lock when the laminating of both separation faces, and simple structure is reliable, only needs to break the trip with hands when unblock, convenient operation.
6. The self-locking buckle initial positions are all subjected to chamfering treatment, and the whole self-locking buckle is streamline, so that wing resistance during flying can be effectively reduced.
7. Compared with the conventional trailing edge folding mechanism, the simple trailing edge extension folding locking mechanism consisting of the sheet trailing edge, the torsion spring hinge and the self-locking buckle structure has the advantages of reducing the overall weight by more than 60%, reducing the cost by more than 80%, having the remarkable advantages of light weight, high reliability and low cost, and greatly improving the practicability.
Drawings
FIG. 1 is a schematic diagram of a self-locking snap lock locking mode;
FIG. 2 is a schematic diagram of a self-locking buckle unlocking mode;
Fig. 3 is a schematic view of a folding wing structure.
FIG. 4 is a schematic view of a connection structure of a self-locking buckle on a folding wing;
FIG. 5 is a schematic illustration of the connection of a semi-buried hinge to a folding wing;
FIG. 6 is a schematic illustration of a semi-buried hinge;
FIG. 7 is a schematic illustration of an unfolding process on a folding wing;
FIG. 8 is a plot of the effect of Reynolds number on lift-to-drag ratio for a folded-wing unmanned aerial vehicle;
Fig. 9 is a schematic diagram of a conventional trailing edge folding mechanism of boeing.
The novel self-locking hinge comprises a 1-main wing, a 101-main wing tail end face, a 2-prolonged trailing edge, a 201-prolonged trailing edge head end face, a 3-semi-embedded hinge, a 301-hinge piece, a 302-hinge piece, a 303-rotating shaft, a 304-torsion spring, a 4-self-locking buckle, a 401-hook, a 402-landslide, a 403-clamping groove, a 404-vertical face A, a 405-vertical face B and a 406-straight face.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.
Features and exemplary embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by showing examples of the invention. The present invention is in no way limited to any particular arrangement and method set forth below, but rather covers any adaptations, alternatives, and modifications of structure, method, and device without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques have not been shown in detail in order not to unnecessarily obscure the present invention.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other, and the embodiments may be referred to and cited with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
Example 1. 1-7, the self-locking buckle comprises an elastic clamping hook 401 and a sliding slope 402, wherein a clamping groove 403 is formed in the bottom surface of the elastic clamping hook 401, the depth of the clamping groove 403 increases gradually along the length direction of the elastic clamping hook 401, the head end of the bottom surface of the clamping groove 403 is connected with the bottom surface of the elastic clamping hook 401, the tail end of the bottom surface of the clamping groove 403 is connected with the bottom surface of the elastic clamping hook 401 through a vertical surface A404, the sliding slope 402 is integrally formed into a right triangular block, the top surface of the sliding slope 402 is an inclined surface of the right triangular block, the tail end of the sliding slope 402 is a vertical surface B405 of the right triangular block, the bottom surface of the sliding slope is a straight surface 406 of the right triangular block, and when the self-locking buckle is buckled, the bottom surface of the clamping groove 403 is matched with the top surface of the sliding slope 402, and the vertical surface A404 is matched with the vertical surface B405.
The top surface of the elastic hook 401 is streamline. Therefore, in the cruising state, the airflow on the clamping hook cannot be obviously separated, and the flight resistance is effectively reduced.
A folding wing provided with the self-locking buckle comprises a main wing 1, wherein the bottom surface of the tail end of the main wing 1 is connected with an extension trailing edge 2 through a semi-embedded hinge 3, an elastic clamping hook 401 of the self-locking buckle 4 is arranged on the top surface of the tail end of the main wing 1, a landslide 402 is arranged on the top surface of the head end of the extension trailing edge 2 through a flat surface 406, the head end of the bottom surface of a clamping groove 403 is aligned with the tail end face 101 of the main wing, and the head end of the landslide 402 is aligned with the head end face 201 of the head end of the extension trailing edge.
The aforementioned ratio of the width of the extended trailing edge 2 to the chord length of the airfoil is 30% ± 10%.
In the unfolded state, the tail end face 101 of the main wing is matched with the head end face 201 of the extension trailing edge, and the tail end profile of the main wing 1 is in smooth transition with the head end profile of the extension trailing edge 2.
The semi-embedded hinge 3 is a sheet hinge and comprises a hinge piece A301, a hinge piece B302, a rotating shaft 303 and a torsion spring 304, wherein the hinge piece A301 and the hinge piece B302 can rotate 180 degrees around the rotating shaft 303, the elasticity of the torsion spring 304 can enable the two hinge pieces to be in an unfolding state in a free state, the hinge piece A301 is embedded in the bottom surface of the tail end of the main wing 1, and the hinge piece B302 is embedded in the bottom surface of the head end of the extended rear edge 2. Thereby reducing the windward area and the flight resistance.
The main wing 1 and the extended trailing edge 2 are connected by one or more semi-embedded hinges 3.
The main wing 1 and the extended trailing edge 2 are locked by more than one self-locking buckles 4.
A barrel type folding wing unmanned aerial vehicle is provided with the folding wing.
When the extended trailing edge 2 is unfolded, the elastic force provided by the torsion spring 304 built in the semi-embedded hinge 3 is firstly utilized to release, then the folding is realized by means of upward aerodynamic force on a control surface, when the tail end face 101 of the main wing is attached to the head end face 201 of the extended trailing edge, the inclined face of the sliding slope 402 moves along the bottom face of the clamping groove 403, when the sliding slope 402 is attached to the bottom face of the clamping groove 403, the inclined face of the sliding slope 402 is attached to the bottom face of the clamping groove 403, and meanwhile, the vertical face A404 and the vertical face B405 attach to enable the whole sliding slope 402 to be wedged into the clamping groove 403, self-locking is realized, when the extended trailing edge 2 is folded, the elastic clamping hook 401 is firstly upwards broken, after the sliding slope 402 is withdrawn from the clamping groove 403 to be unlocked, the extended trailing edge 2 is downwards folded for about 180 degrees, and the barrel type folding wing unmanned aerial vehicle is stored in a storage barrel.
The folding rear edge is different from a traditional barrel type folding wing unmanned aerial vehicle without a folding rear edge, on one hand, the folding rear edge can effectively reduce the storage space of the unmanned aerial vehicle in the height direction under a folding state, so that the size of a transmitting barrel or a storage barrel can be obviously reduced, on the other hand, the folding rear edge can effectively increase the main wing area and the chord length of the folding wing unmanned aerial vehicle under an unfolding state, and the flying Reynolds number of the unmanned aerial vehicle is improved, so that the effective bearing capacity and the cruising pneumatic efficiency of the barrel type folding wing unmanned aerial vehicle can be effectively improved, and the unmanned aerial vehicle has stronger flying performance. The unmanned aerial vehicle is driven by the torsion spring and aerodynamic force to realize the unfolding of the extension trailing edge after leaving the transmitting barrel or the receiving barrel, and the self-locking buckle is utilized to realize the locking, so that the unmanned aerial vehicle wing is simple in structure and high in reliability, when the wing is folded, the quick unlocking and the receiving can be realized through the breaking-off of the clamping hooks, the operation is convenient, the hinge with the torsion spring is of a semi-embedded design, the self-locking buckle is of a streamline design, the resistance in the flight stage can be effectively reduced, the main wing and the extension trailing edge are integrally designed, and the processing difficulty is low.
Example 2. As shown in fig. 3-5, a folding wing for a barrel folding wing unmanned aerial vehicle comprises a main wing 1, an extended trailing edge 2, a semi-embedded hinge 3 and a self-locking buckle 4.
As shown in fig. 6, the semi-embedded hinge 3 is a sheet hinge, and is composed of a hinge piece a301, a hinge piece B302, a rotating shaft 303 and a torsion spring 304, wherein the hinge piece a301 and the hinge piece B302 can rotate 180 ° around the rotating shaft 303, and the elasticity of the torsion spring 304 can enable the two hinge pieces to be in an unfolding state in a free state. The semi-embedded hinges 3 are distributed on the lower surface of the main wing 1 along the spanwise direction, wherein one half of the hinge piece A301 is embedded in the skin surface of the main wing 1 along the thickness direction, and one half of the hinge piece B302 is embedded in the extension trailing edge 2 along the thickness direction, so that the windward area is reduced, and the flight resistance is reduced.
As shown in fig. 1 and 2, the self-locking buckle 4 is composed of an elastic hook 401 and a landslide 402, and is made of carbon fiber composite material or aluminum alloy. The elastic hook 401 and the outer skin of the main wing 1 are integrally formed, the landslide 402 and the extended trailing edge 2 are integrally formed, and the integrally formed areas are chamfered, so that the flight resistance is reduced. When the extension trailing edge is in an unfolding state, the elastic clamping hook and the landslide can be completely matched without a gap, and meanwhile, the extension trailing edge and the main wing can be effectively prevented from being separated.
A folding wing for a barrel type folding wing unmanned aerial vehicle has the following specific working principle:
when the unmanned aerial vehicle 1 is positioned in the transmitting cylinder, the extension rear edge 2 is folded and hidden below the main wing 1, and the storage volume can be effectively reduced because the extension rear edge 2 is smaller in relative thickness, the semi-embedded hinge 3 is in a compression state and resists the elastic force of the torsion spring 304 by virtue of the outer wall of the transmitting cylinder;
2, after the unmanned aerial vehicle is out of the cylinder, under the action of the elasticity of the torsion spring 304, the hinge piece A301 and the hinge piece B302 are unfolded to drive the extension rear edge 2 to be unfolded backwards around the rotating shaft 304, and the unfolding process is shown in fig. 7;
3, after the extended trailing edge 2 rotates about 180 degrees around the rotating shaft 304, the elastic clamping hook 401 contacts and slides with the landslide 402, when the extended trailing edge 2 is completely tightly attached to the main wing 1, the hook-shaped structure of the elastic clamping hook 401 is just clamped on the rear wall surface of the landslide 402, the self-locking buckle 4 is in a locking state, and the relative positions of the extended trailing edge 2 and the main wing 1 are relatively locked and cannot be separated in a flying state;
Under the flying state 4, the semi-embedded hinge 3 has smaller windward area, and the self-locking buckle 4 is streamline, so that the flying resistance can be effectively reduced;
5, when the wing is stored after the flying, the elastic clamping hook 401 is manually lifted upwards, the hook-shaped structure is separated from the rear wall surface of the landslide 402, the self-locking buckle 4 is unlocked, then the rear edge 2 is downwardly pressed to be prolonged, the rear edge is rotated 180 degrees around the rotating shaft 304, the wing is folded and hidden below the main wing 1, the aircraft is retracted into the launching barrel, then the hand is loosened, and the rear edge is prevented from being unfolded by utilizing the restraint of the wall surface of the launching barrel.
It should be noted that the above embodiments are only for illustrating the technical solution of the present invention, but the scope of the present invention is not limited thereto, and any equivalent modifications or substitutions can be easily made by those skilled in the art within the technical scope of the present invention, and these modifications or substitutions should be included in the scope of the present invention.
Claims (9)
1. A self-locking buckle is characterized by comprising an elastic clamping hook (401) and a landslide (402), wherein a clamping groove (403) is formed in the bottom surface of the elastic clamping hook (401), the depth of the clamping groove (403) is gradually increased along the length direction of the elastic clamping hook (401), the head end of the bottom surface of the clamping groove (403) is connected with the bottom surface of the elastic clamping hook (401), the tail end of the bottom surface of the clamping groove (403) is connected with the bottom surface of the elastic clamping hook (401) through a vertical surface A (404), the whole landslide (402) is a right triangular block, the top surface of the landslide (402) is an inclined surface of the right triangular block, the tail end of the landslide (402) is a vertical surface B (405) of the right triangular block, the bottom surface of the sliding slope is a flat surface (406) of the right triangular block, and when the self-locking buckle is buckled, the bottom surface of the clamping groove (403) is buckled with the top surface of the landslide (402), and the vertical surface A (404) is buckled with the vertical surface B (405).
2. The self-locking buckle according to claim 1, wherein the top surface of the elastic hook (401) is streamlined.
3. A folding wing provided with the self-locking buckle as claimed in claim 1 or 2, which is characterized by comprising a main wing (1), wherein the bottom surface of the tail end of the main wing (1) is connected with an extended trailing edge (2) through a semi-embedded hinge (3), an elastic clamping hook (401) of the self-locking buckle (4) is arranged on the top surface of the tail end of the main wing (1), a landslide (402) is arranged on the top surface of the head end of the extended trailing edge (2) through a flat surface (406), the head end of the bottom surface of a clamping groove (403) is aligned with the tail end surface (101) of the main wing, and the head end of the landslide (402) is aligned with the head end surface (201) of the head end of the extended trailing edge.
4. A folded wing according to claim 3, characterized in that the ratio of the width of the extended trailing edge (2) to the chord length of the wing profile is 30% ± 10%.
5. A folded wing according to claim 3, characterized in that in the unfolded state the main wing trailing end face (101) is in apposition with the extended trailing edge leading end face (201), the main wing (1) trailing end face smoothly transitions with the extended trailing edge (2) leading end face.
6. The folding wing according to claim 3, wherein the semi-embedded hinge (3) is a sheet hinge and comprises a hinge piece A (301), a hinge piece B (302), a rotating shaft (303) and a torsion spring (304), wherein the hinge piece A (301) and the hinge piece B (302) can rotate 180 degrees around the rotating shaft (303), the elasticity of the torsion spring (304) can enable the two hinge pieces to be in an unfolding state in a free state, the hinge piece A (301) is embedded in the bottom surface of the tail end of the main wing (1) in a half mode, and the hinge piece B (302) is embedded in the bottom surface of the head end of the extended rear edge (2) in a half mode.
7. A folding wing according to claim 3, characterized in that the main wing (1) is connected to the extended trailing edge (2) via one or more semi-buried hinges (3).
8. A folding wing according to claim 3, characterized in that the main wing (1) and the extended trailing edge (2) are locked by means of more than one self-locking catch (4).
9. A folding wing drone of the barrel type, characterised in that a folding wing according to any one of claims 3 to 8 is fitted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411913653.9A CN119683041A (en) | 2024-12-24 | 2024-12-24 | Self-locking buckle, folding wing and barrel type folding wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411913653.9A CN119683041A (en) | 2024-12-24 | 2024-12-24 | Self-locking buckle, folding wing and barrel type folding wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN119683041A true CN119683041A (en) | 2025-03-25 |
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| CN202411913653.9A Pending CN119683041A (en) | 2024-12-24 | 2024-12-24 | Self-locking buckle, folding wing and barrel type folding wing unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN119683041A (en) |
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- 2024-12-24 CN CN202411913653.9A patent/CN119683041A/en active Pending
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