Aircraft tail wing quick release structure and unmanned aerial vehicle tail wing

Abstract

The application provides an aircraft tail wing quick-release structure, which comprises a first connecting piece and a second connecting piece, the first connecting piece comprises a first bottom plate, a sliding assembly installed on the first bottom plate and a lock hook connected with the sliding assembly, the sliding assembly can move the lock hook in a first direction; the second connecting piece comprises a second bottom plate, a pressing assembly installed on the second bottom plate and a lock sleeve connected with the pressing assembly, the lock sleeve is matched with the lock hook, and the pressing assembly can move the lock sleeve in a second direction, the second direction is perpendicular to the first direction. The application also provides a UAV tail wing, which comprises an inverted V-shaped tail wing composed of a first tail wing and a second tail wing and the above-mentioned aircraft tail wing quick-release structure; wherein the first connecting piece and the second connecting piece of the aircraft tail wing quick-release structure are fixedly installed on the first tail wing and the second tail wing respectively. The application can quickly realize the installation and disassembly of the tail wing without tools, and meets the use requirements of flexible and quick disassembly of light and small UAVs in the field.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a quick-release structure for an aircraft tail fin and a tail fin for a drone. Background Technology

[0002] The inverted V-tail configuration is a common tail layout for aircraft. Compared to a conventional tail, the inverted V-tail offers advantages such as lower aerodynamic drag, better stealth performance, and lighter structural weight. Inverted V-tails are commonly found in small and medium-sized UAVs. These UAVs typically use rotating shafts or screw threads for their inverted V-tail connections.

[0003] However, if screw threads are used, a suitable torque wrench must be available on-site to ensure reliable connection. If a rotating hinge is used, it becomes inconvenient to rotate, fold, and disassemble the tail fin when it is too long, especially for medium-sized drones with tail fins reaching 1m on one side. Therefore, it is clear that disassembling and assembling an inverted V-shaped tail fin using either a rotating hinge or screw threads is inconvenient and cannot meet the requirements for flexible and rapid assembly and disassembly in the field for small and lightweight drones. Summary of the Invention

[0004] The features and advantages of the present invention are set forth in part in the description which follows, or may be apparent from the description, or may be learned by practicing the invention.

[0005] To overcome the problems of the prior art, the present invention provides a quick-release structure for an aircraft tail fin, comprising a first connector and a second connector, wherein:

[0006] The first connector includes a first base plate, a sliding assembly mounted on the first base plate, and a locking hook connected to the sliding assembly, wherein the sliding assembly enables the locking hook to move along a first direction;

[0007] The second connector includes a second base plate, a pressing assembly mounted on the second base plate, and a locking sleeve connected to the pressing assembly. The locking sleeve matches the locking hook, and the pressing assembly enables the locking sleeve to move along a second direction, which is perpendicular to the first direction.

[0008] In one embodiment of the present invention, the sliding assembly includes a guide plate and a sliding plate. A sliding cavity is provided on the first base plate, the guide plate covers the sliding cavity, the sliding plate is located inside the sliding cavity, and one end of the locking hook passes through the guide plate and is connected to the first end face of the sliding plate.

[0009] In one embodiment of the present invention, the sliding assembly further includes a pull ring, which is fixed to the second end face of the sliding plate, the second end face of the sliding plate being opposite to the first end face.

[0010] In one embodiment of the present invention, the sliding assembly further includes at least one positioning pin, the positioning pin being fixedly connected to the sliding plate, and the guide plate having a positioning pin hole through which the positioning pin passes.

[0011] In one embodiment of the present invention, the second base plate is provided with a positioning pin sleeve that matches the positioning pin.

[0012] In one embodiment of the present invention, the pressing assembly includes a lock sleeve receiving cavity for accommodating the lock sleeve, a cover plate matching the lock sleeve receiving cavity, and springs and unlocking buttons respectively disposed at two ends of the lock sleeve, wherein the springs are in contact with the bottom of the lock sleeve receiving cavity, and one end of the unlocking button passes through the top of the lock sleeve receiving cavity and is connected to the lock sleeve.

[0013] In one embodiment of the present invention, the locking sleeve receiving cavity is integrally formed with the second base plate.

[0014] The present invention also provides a tail fin for a drone, comprising an inverted V-shaped tail fin composed of a first tail fin and a second tail fin, and the aforementioned quick-release structure for the aircraft tail fin; wherein the first connector and the second connector in the quick-release structure for the aircraft tail fin are respectively fixedly installed on the first tail fin and the second tail fin.

[0015] In one embodiment of the present invention, the first tail fin is provided with a pull ring guide hole for the end of the sliding component in the quick-release structure of the aircraft tail fin to pass through.

[0016] In one embodiment of the present invention, the second tail fin is provided with a pressing hole for the end of the pressing component in the quick-release structure of the aircraft tail fin to pass through.

[0017] This invention provides a quick-release structure for aircraft tail fins and a tail fin for drones. The structure is simple and can quickly install and remove the tail fin, making the tail fin easy to transport after installation and removal.

[0018] By reading the instruction manual, those skilled in the art will gain a better understanding of the features and contents of these technical solutions. Attached Figure Description

[0019] The present invention will be described in detail below with reference to the accompanying drawings and examples. The advantages and implementation methods of the present invention will become more apparent from this description. The accompanying drawings are for illustrative purposes only and do not constitute any limitation on the present invention. In the accompanying drawings:

[0020] Figure 1 This is a schematic diagram of the quick-release structure of the aircraft tail fin according to an embodiment of the present invention.

[0021] Figure 2This is a schematic diagram of the structure of the first connector in an embodiment of the present invention.

[0022] Figure 3 This is a schematic diagram of the structure of the first base plate according to an embodiment of the present invention.

[0023] Figure 4 This is a schematic diagram of the structure of the second connector in an embodiment of the present invention.

[0024] Figure 5 This is a schematic diagram of the tail fin of a drone according to an embodiment of the present invention.

[0025] Figure 6 This is a schematic diagram of the tail fin structure of a drone according to an embodiment of the present invention. Figure 2 .

[0026] Figure 7 This is a schematic diagram of the tail fin structure of a drone according to an embodiment of the present invention. Figure 3 .

[0027] Figure 8 This is a schematic diagram of the tail fin structure of a drone according to an embodiment of the present invention. Figure 4 .

[0028] Figure label:

[0029] 10-First base plate, 11-Sliding cavity, 12-Step, 13-Bolt hole, 20-Locking hook, 30-Sliding assembly, 31-Guide plate, 32-Bolt, 33-Sliding plate, 34-Pull ring, 35-Positioning pin, 36-Bolt, 37-Locking hook hole, 38-Positioning pin hole, 40-First connector, 50-Second base plate, 51-Positioning pin sleeve, 52-Bolt, 53-Positioning pin sleeve mounting hole, 60-Pressing assembly 61-Lock sleeve receiving cavity, 62-Spring, 63-Unlock button, 64-Cover plate, 65-Lock hole, 66-Bolt, 70-Lock sleeve, 71-Lock beam, 72-Button beam, 73, 74-Spring mounting part, 80-Second connecting piece, 100-First tail wing, 110-Pull ring guide hole, 120-Pull ring guide buckle, 200-Second tail wing, 210-Pressing hole, 220-First groove, 230-Second groove. Detailed Implementation

[0030] In the description of this invention, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "inner," "outer," "top," "bottom," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0031] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0032] To facilitate understanding of this application, a more complete description will be provided below with reference to the accompanying drawings. Preferred embodiments of this application are shown in the drawings. However, this application can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the disclosure of this application.

[0033] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the specification of this application is for the purpose of describing particular embodiments only and is not intended to be limiting of this application.

[0034] like Figures 1 to 4 As shown, the present invention provides a quick-release structure for an aircraft tail fin, including a first connector 40 and a second connector 80. Wherein:

[0035] The first connecting member 40 includes a first base plate 10, a locking hook 20, and a sliding assembly 30. The first base plate 10 has a sliding cavity 11, and the sliding assembly 30 is installed within the sliding cavity 11 of the first base plate 10. The locking hook 20 is connected to the sliding assembly 30, and the sliding assembly 30 enables the locking hook 20 to move along a first direction, which can be a horizontal direction.

[0036] In this embodiment, the sliding assembly 30 includes a guide plate 31 and a sliding plate 33. The guide plate 31 covers the sliding cavity 11, and the sliding plate 33 is located inside the sliding cavity 11 and moves in a direction away from or towards the guide plate 31. The first end of the locking hook 20 passes through the guide plate 31 and is connected to the first end face of the sliding plate 33. More specifically, the guide plate 31 is provided with a locking hook hole 37, through which the first end of the locking hook 20 can pass, while the second end of the locking hook 20 cannot pass through the locking hook hole 37. In specific implementation, the first end of the locking hook 20 can be fixed to the sliding plate 33 by bolts, and the guide plate 31 can also be fixed to the first base plate 10 by bolts 32. The sliding cavity 11 on the first base plate 10 can be either a bottom cavity or a bottomless cavity; the present invention does not limit this.

[0037] To ensure that the first base plate 10 has a flat end face, steps 12 can be provided on the two opposite inner side walls of the sliding cavity 11. Bolt holes 13 are provided on the steps 12. The guide plate 31 is placed on the steps 12 and fixed to the steps 12 by bolts 32. At this time, the upper end face of the guide plate 31 is flush with the upper end face of the first base plate 10.

[0038] The sliding assembly 30 also includes a pull ring 34, which is fixed to the second end face of the sliding plate 33, with the second end face of the sliding plate 33 facing the first end face. Thus, when it is necessary to move the sliding plate 33 and thereby move the locking hook 20, it is only necessary to pull the pull ring 34.

[0039] The second connecting member 80 includes a second base plate 50, a pressing assembly 60, and a locking sleeve 70. The pressing assembly 60 is mounted on the second base plate 50, and the locking sleeve 70 is connected to the pressing assembly 60. The pressing assembly 60 allows the locking sleeve 70 to move along a second direction, which is perpendicular to the first direction. When the first direction is horizontal, the second direction is vertical. The locking sleeve 70 matches the locking hook 20 in the first connecting member. When the locking hook 20 and the locking sleeve 70 are connected, the first connecting member 40 and the second connecting member 80 are connected together.

[0040] In this embodiment, the pressing assembly 60 includes a locking sleeve receiving cavity 61, a cover plate 64, a spring 62, and an unlocking button 63. The locking sleeve receiving cavity 61 is disposed on the second base plate 50. In specific implementation, the opening of the locking sleeve receiving cavity 61 is flush with the first end face of the second base plate 50, which is used to contact the first connecting member 40. The locking sleeve receiving cavity 61 can be integrally formed with the second base plate 50. The cover plate 64 matches the locking sleeve receiving cavity 61 and is bolted to the opening of the locking sleeve receiving cavity 61. To maintain the flatness of the first end face of the second base plate 50, a step can be provided inside the locking sleeve receiving cavity 61 for placing the cover plate 64, and the cover plate 64 is fixed to the step by bolts 66. At this time, the end face of the cover plate 64 is flush with the first end face of the second base plate 50. The cover plate 64 also has a locking hole 65 for the locking hook 20 to pass through.

[0041] The locking sleeve 70 is located inside the locking sleeve receiving cavity 61. The lower end of the locking sleeve 70 is fixed to the bottom of the locking sleeve receiving cavity 61 by a spring 62, and the upper end of the locking sleeve 70 is connected to the unlocking button 63. That is, one end of the unlocking button 63 passes through the top of the locking sleeve receiving cavity 61 and is connected to the upper end of the locking sleeve 70.

[0042] In this embodiment, the lock sleeve 70 includes a lock beam 71, a button beam 72, and spring mounting portions 73 and 74. The lock beam 71 and button beam 72 are arranged in parallel. The two ends of the spring mounting portion 73 are connected to the first ends of the lock beam 71 and the button beam 72, respectively. The two ends of the spring mounting portion 74 are connected to the second ends of the lock beam 71 and the button beam 72, respectively. The spring mounting portions 73 and 74 are connected to the spring 62 and contact the bottom of the lock sleeve receiving cavity 61. The lock beam 71 is used to cooperate with the lock hook 20. The unlocking button 63 is mounted on the button beam 72. In specific implementations, the unlocking button 63 may have a notch that matches the button beam 72. Furthermore, to further strengthen the connection between the unlocking button and the lock sleeve 70, the unlocking button 63 can be further fixed to the button beam 72 using a set screw.

[0043] As can be seen, when the first connector 40 and the second connector 80 are connected, the locking hook 20 extends into the lock sleeve receiving cavity 61 and hooks the locking beam 71 of the lock sleeve 70. At this time, the locking hook 20 is locked and cannot be removed under the action of the spring 62. If the unlocking button 63 is pressed, the spring 62 is compressed, and the locking beam 71 moves closer to the bottom of the lock sleeve receiving cavity 61. At this time, pulling the pull ring can disengage the locking hook 20 from the lock sleeve 70 and remove it from the lock sleeve receiving cavity.

[0044] In one embodiment of the present invention, in order to make the movement of the locking hook 20 smoother and prevent deviation, the sliding assembly 30 further includes at least one positioning pin 35. The positioning pin 35 is fixedly connected to the first end face of the sliding plate 33 by bolts 36, and the guide plate 31 is provided with positioning pin holes 38 for the positioning pin 35 to pass through. Generally, there are two positioning pins 35, and in this case, the corresponding positioning pin holes 38 are located at both ends of the locking hook hole 37.

[0045] The second base plate 50 is provided with a positioning pin sleeve 51 that matches the positioning pin 35. More specifically, the second base plate 50 is provided with a positioning pin sleeve mounting hole 53, the positioning pin sleeve 51 is disposed in the positioning pin sleeve mounting hole 53 and fixed to the second base plate 50 by bolts 52. In this way, when the pull ring 34 is pulled, the sliding plate 33 can be moved back and forth along the axial direction of the positioning pin on the guide plate 31.

[0046] The locating pins can also be used for force transmission and positioning, thereby achieving greater structural strength.

[0047] The quick-release tail fin structure provided by this invention is suitable for compound-wing UAVs with inverted V-shaped tail fins. In practical use, the first connector and the second connector can be fixed to the right and left structures of the tail fin, respectively. This eliminates the need for users to use tools for assembly, enabling quick installation and removal of the tail fin, and facilitating transportation after disassembly and assembly.

[0048] like Figures 5 to 8 As shown, the present invention also provides a UAV tail fin, including an inverted V-shaped tail fin composed of a first tail fin 100 and a second tail fin 200, and a quick-release structure for the aircraft tail fin provided in any embodiment of the present invention; wherein the first connector 40 and the second connector 80 in the quick-release structure for the aircraft tail fin are respectively fixedly installed on the first tail fin 100 and the second tail fin 200. More specifically, the first tail fin 100 has a first contact end face, and the second tail fin 200 has a second contact end face, the first contact end face and the second contact end face are connected by the quick-release structure for the aircraft tail fin.

[0049] In specific implementation, the first base plate 10 in the first connector 40 can be fixedly connected to the first contact surface of the first tail fin 100 by means of adhesive bonding or other methods. The first tail fin 100 is also provided with a pull ring guide hole 110, which penetrates from the first contact surface to the second end face of the first tail fin, the second end face of the first tail fin being adjacent to the first contact surface. The pull ring guide hole 110 allows the end of the sliding component 30 in the quick-release structure of the aircraft tail fin to pass through; the end of the sliding component 30 refers to the pull ring 34. Generally, a pull ring guide buckle 120 can also be provided on the second end face of the first tail fin 100, the pull ring guide buckle 120 being located at the edge of the pull ring guide hole 110.

[0050] On the second contact surface of the second tail fin 200, there are a first groove 220 and a second groove 230, wherein the first groove 220 matches the locking sleeve receiving cavity, and the second groove 230 matches the pin sleeve. The first end face of the second tail fin 200 adjacent to the second contact surface is also provided with a pressing hole 210, which communicates with the first groove 220. The pressing hole 210 is used for the end of the pressing component in the quick-release structure of the aircraft tail fin, i.e., the unlocking button 63, to pass through.

[0051] like Figure 7 As shown, when it is necessary to combine the first tail fin and the second tail fin, the pull ring 34 is pushed horizontally, causing the positioning pin 35 to align and enter the pin sleeve 51. At the same time, the locking hook 20 is locked by the locking sleeve 70 under the action of the spring and cannot be disengaged. When it is necessary to separate the first tail fin and the second tail fin, as shown... Figure 8 As shown, pressing the unlock button 63 simultaneously pulls the pull ring 34, causing the sliding plate 33 and the positioning pin 35 and locking hook 20 fixed on the sliding plate 33 to disengage from the lock sleeve and positioning pin sleeve, thus removing the second tail fin.

[0052] The present invention provides a quick-release structure for aircraft tail fins and a tail fin for drones. The structure is simple and can quickly install and remove the tail fin without tools, meeting the requirements of flexible and rapid assembly and disassembly for small and light drones in the field.

[0053] The preferred embodiments of the present invention have been described above with reference to the accompanying drawings. Those skilled in the art can implement the present invention in various modifications without departing from its scope and spirit. For example, a feature shown or described in one embodiment can be used in another embodiment to obtain yet another embodiment. The above are merely preferred embodiments of the present invention and do not limit the scope of the present invention. All equivalent changes made based on the description and drawings of the present invention are included within the scope of the present invention.

Claims

1. A quick-release structure for an aircraft tail fin, characterized in that... It includes a first connector and a second connector, wherein: The first connector includes a first base plate, a sliding assembly mounted on the first base plate, and a locking hook connected to the sliding assembly, wherein the sliding assembly enables the locking hook to move along a first direction; The second connector includes a second base plate, a pressing assembly mounted on the second base plate, and a locking sleeve connected to the pressing assembly. The locking sleeve matches the locking hook, and the pressing assembly enables the locking sleeve to move along a second direction, which is perpendicular to the first direction. The sliding assembly includes a guide plate and a sliding plate. A sliding cavity is provided on the first base plate. The guide plate covers the sliding cavity and the sliding plate is located inside the sliding cavity. One end of the locking hook passes through the guide plate and is connected to the first end face of the sliding plate. The sliding assembly also includes a pull ring, which is fixed to the second end face of the sliding plate, and the second end face of the sliding plate is opposite to the first end face.

2. The quick-release structure for the tail fin of an aircraft according to claim 1, characterized in that... The sliding assembly further includes at least one positioning pin, which is fixedly connected to the sliding plate, and the guide plate is provided with a positioning pin hole through which the positioning pin passes.

3. The quick-release structure for the aircraft tail fin according to claim 2, characterized in that... The second base plate is provided with a positioning pin sleeve that matches the positioning pin.

4. The quick-release structure for the tail fin of an aircraft according to claim 1, characterized in that... The pressing assembly includes a lock housing cavity for accommodating the lock housing, a cover plate that matches the lock housing cavity, and springs and unlocking buttons respectively disposed at both ends of the lock housing. The springs are in contact with the bottom of the lock housing cavity, and one end of the unlocking button passes through the top of the lock housing cavity and is connected to the lock housing.

5. The quick-release structure for the aircraft tail fin according to claim 4, characterized in that... The locking sleeve receiving cavity is integrally formed with the second base plate.

6. A tail fin for an unmanned aerial vehicle, characterized in that... It includes an inverted V-shaped tail fin composed of a first tail fin and a second tail fin, and a quick-release tail fin structure for an aircraft as described in any one of claims 1 to 5; wherein the first connector and the second connector in the quick-release tail fin structure are respectively fixedly installed on the first tail fin and the second tail fin.

7. The UAV tail fin according to claim 6, characterized in that, The first tail fin is provided with a pull ring guide hole for the end of the sliding component in the quick-release structure of the aircraft tail fin to pass through.

8. The UAV tail fin according to claim 6, characterized in that, The second tail fin is provided with a pressing hole for the end of the pressing component in the quick-release structure of the aircraft tail fin to pass through.

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