A wing-blade structure and tail-seat vertical take-off and landing UAV

Abstract

The present invention relates to a wing-blade structure and a tail-seat vertical take-off and landing UAV. The wing-blade structure includes a wing-blade, which is an arc-shaped plate structure and has a notch extending from the middle of one end to a position close to the other end, and is equipped with a connecting mechanism for detachably connecting it to the UAV. The beneficial effects of the present invention are simple structure, reasonable design, and small occupied volume. The design of the wing-blade takes into account that the take-off and landing process of the tail-seat UAV is a multi-rotor state, and the control torque in the pitch and yaw directions is provided by the rudder. The magnitude of the control torque of the rudder is positively correlated with the magnitude of the propeller slipstream flowing thereon. Therefore, it is necessary to provide wing-blade rectification to increase the airflow flowing through the rudder, thereby increasing the rudder effect. In addition, the wing-blade can be detachably installed on the UAV through the connecting mechanism, which is convenient for disassembly and assembly, and convenient for subsequent maintenance, saving time and effort.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a wing-blade structure and a tail-seat type vertical take-off and landing UAV. Background Art

[0002] Existing tail-sitter drones experience large angles of attack during transitions between horizontal flight and vertical takeoff and landing (VTOL) operations, which can be detrimental to drone control. Currently, to mitigate wingtip flow separation in tail-sitter drones, winglets and other structures are typically installed at the wingtips. These structures can increase the available angle of attack during flight, hindering (e.g., blocking) airflow along the span of the wing, thereby improving the drone's maneuverability at reduced speeds (e.g., lower speeds during takeoff and / or landing operations, relative to the higher speeds during cruise operation). Conventional winglets are positioned and / or arranged along the top side of the aircraft's wing in a generally chordwise direction.

[0003] Traditional wing blades are usually welded directly to the wings of the drone, which makes them inconvenient to disassemble and assemble, inconvenient to maintain, and time-consuming and labor-intensive. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a wing-blade structure and a tail-seat vertical take-off and landing UAV, aiming to solve the problems in the prior art.

[0005] The technical solution of the present invention to solve the above technical problems is as follows:

[0006] A wing blade structure includes a wing blade in the form of an arc-shaped plate with a notch extending from the middle of one end to a position close to the other end, and is equipped with a connecting mechanism for detachably connecting the wing blade to a drone.

[0007] The beneficial effects of the present invention are: the present invention has a simple structure, a reasonable design, and occupies a small volume. The design of the wing blade is based on the consideration that the take-off and landing process of the tail-seat UAV is a multi-rotor state, and the control torque in the pitch and yaw directions is provided by the rudder surface, and the magnitude of the control torque of the rudder surface is positively correlated with the magnitude of the propeller slipstream flowing over it. Therefore, it is necessary to provide wing blade rectification to increase the airflow flowing through the rudder surface, thereby increasing the rudder effect; in addition, the wing blade can be detachably installed on the UAV through a connecting mechanism, which is easy to disassemble and assemble, convenient for subsequent maintenance, and saves time and effort.

[0008] On the basis of the above technical solution, the present invention can also be improved as follows.

[0009] Furthermore, the connecting mechanism includes two groups of snap-fit components, and the two groups of snap-fit components are distributed on the wing blades on both sides of the notch.

[0010] The beneficial effect of adopting the above further solution is that when disassembling and assembling, the wing blade is connected to the drone through two sets of clamping components, which makes disassembly and assembly convenient, saving time and effort.

[0011] Furthermore, each group of the snap-fit components includes a plurality of snap-fit blocks, which are evenly spaced and distributed on the wing blade on one side of the notch and are respectively used to snap into the snap-fit slots at corresponding parts of the drone.

[0012] The beneficial effect of adopting the above further solution is that when disassembling and assembling, the wing blades are respectively connected to the slots at the corresponding parts of the drone through multiple clamping blocks, so that the wing blades can be quickly disassembled and assembled, which is easy to operate and saves time and effort.

[0013] Furthermore, the plurality of clamping blocks are respectively in an L-shaped block structure, one end of which is respectively fixedly connected to the edge of the wing blade, and the other end of which extends in the direction from the closed end to the open end of the wing blade.

[0014] The beneficial effects of adopting the above further solution are simple structure and reasonable design. When the wing knife is put on the wing of the drone, multiple card blocks can be connected to multiple card slots on the drone, which is convenient for connection and saves time and effort.

[0015] Furthermore, the plurality of clamping blocks in the two clamping groups are respectively located on the inner sides of both sides of the wing blade or the outer side of the wing blade or both the inner side and the outer side of the wing blade.

[0016] The beneficial effects of adopting the above further solution are simple structure, reasonable design, and further improved stability of the wing knife installation.

[0017] Furthermore, an adhesive layer is attached to the plurality of card blocks.

[0018] The beneficial effects of adopting the above further solution are simple structure, reasonable design, and further increased stability of the wing knife installation.

[0019] Furthermore, each group of the snap-fit components includes a plurality of positioning pins, which are respectively installed on the wing blade and positioned so as to move from one side of the wing blade to the other side, and are respectively used to snap into the positioning grooves of the corresponding parts of the drone.

[0020] The beneficial effect of adopting the above further solution is that when disassembling and assembling, the wing blades are respectively clamped in the positioning grooves at the corresponding parts of the drone through multiple positioning pins, so that the wing blades can be quickly disassembled and assembled, which is easy to operate and saves time and effort.

[0021] Furthermore, a plurality of grooves corresponding to the plurality of positioning pins are provided on the edge of the wing knife, and the plurality of positioning pins are movably installed in the plurality of grooves, one end of which is connected to the bottom of the plurality of grooves through a spring, and the other end extends outside the plurality of grooves.

[0022] The beneficial effect of adopting the above-mentioned further scheme is that during disassembly and assembly, multiple positioning pins can be respectively received in multiple positioning grooves under the action of external force. When the wing knife is put on the wing of the drone, the multiple positioning pins are released, and the multiple positioning pins are respectively engaged in the positioning grooves at the corresponding parts of the drone under the action of multiple spring forces, thereby realizing rapid disassembly and assembly of the wing knife, simple operation, saving time and effort.

[0023] Furthermore, the wing blade is an arc-shaped plate structure that is wide in the middle and narrow at both ends.

[0024] The beneficial effects of adopting the above further solution are simple structure, reasonable design, obstruction of airflow along the span direction of the wing, thereby improving the control of the UAV at a reduced speed and facilitating the flight of the UAV.

[0025] The present invention also relates to a tail-seat vertical take-off and landing UAV, comprising an airframe, two front wings being relatively fixedly mounted on both sides of the front end of the airframe, and two rear wings being relatively fixedly mounted on the rear end; and a plurality of wing blade structures as described above, wherein the plurality of wing blades are divided into two groups and are respectively and spaced apart and mounted on the front sides of the two rear wings.

[0026] The beneficial effect of adopting the above-mentioned further scheme is that the UAV has a simple structure and a reasonable design. The wing blades arranged on its wings are based on the consideration that the take-off and landing process of the tail-seat UAV is a multi-rotor state, and the control torque in the pitch and yaw directions is provided by the rudder. The magnitude of the control torque of the rudder is positively correlated with the magnitude of the propeller slipstream flowing over it. Therefore, it is necessary to provide wing blade straightening to increase the airflow flowing through the rudder, thereby increasing the rudder effect; in addition, the wing blades can be detachably installed on the UAV through a connecting mechanism, which is easy to disassemble and assemble, convenient for subsequent maintenance, and saves time and effort. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is one of the overall structural diagrams of the drone of the present invention;

[0028] Figure 2 This is the second schematic diagram of the overall structure of the drone of the present invention;

[0029] Figure 3 This is one of the structural schematic diagrams of the first embodiment of the wing blade of the present invention, in which two sets of clamping components are located on different sides of the wing blade;

[0030] Figure 4 This is the second structural diagram of the first embodiment of the wing blade of the present invention, in which the two sets of clamping components are located on different sides of the wing blade;

[0031] Figure 5 It is a structural schematic diagram of the second embodiment of the wing knife in the present invention.

[0032] In the accompanying drawings, the components represented by the reference numerals are as follows:

[0033] 1. Wing blade; 2. Clamp block; 4. Fuselage; 5. Front wing; 6. Rear wing. DETAILED DESCRIPTION

[0034] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0035] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0036] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0037] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0038] Example 1

[0039] like Figures 1 to 5 As shown, this embodiment provides a wing blade structure, including a wing blade 1, which is an arc-shaped plate structure with a notch extending from the middle of one end to a position near the other end, and is equipped with a connecting mechanism for detachably connecting it to a drone.

[0040] Preferably, in this embodiment, two ends of the wing blade 1 are opposite to each other to form a U-shaped plate structure.

[0041] This embodiment has a simple structure, a reasonable design, and occupies a small volume. The design of the wing blade takes into account that the take-off and landing process of the tail-seat UAV is a multi-rotor state, and the control torque in the pitch and yaw directions is provided by the rudder. The magnitude of the control torque of the rudder is positively correlated with the speed of the propeller slipstream flowing over it. Therefore, it is necessary to provide wing blade rectification to increase the airflow flowing through the rudder, thereby increasing the rudder effect; in addition, the wing blade can be detachably installed on the UAV through a connecting mechanism, which is easy to disassemble and assemble, convenient for subsequent maintenance, and saves time and effort.

[0042] Example 2

[0043] On the basis of embodiment 1, in this embodiment, the connection mechanism includes two groups of clamping components, and the two groups of clamping components are distributed on the wing blades 1 on both sides of the notch.

[0044] During assembly and disassembly, the wing blade 1 is connected to the drone through two sets of snap-on components, which makes assembly and disassembly easy and saves time and effort.

[0045] Based on the above solution, the two groups of snap-fit components can be distributed on the same side of the wing blade 1 or on different sides of the wing blade 1. The latter is preferred, as the installation stability of the wing blade 1 is better.

[0046] When the two groups of clamping components are distributed on the same side of the wing blade, the two groups of clamping components can be distributed relative to each other or staggered.

[0047] It should be noted that the wing blade 1 is cut into two identical arc-shaped plates with the center plane of the two opening sides of the notch of the wing blade 1 as the cross section. At this time, the two sets of clamping components are respectively located on the two arc-shaped plates.

[0048] Example 3

[0049] Based on Example 2, in this embodiment, each group of card-connecting components includes multiple card blocks 2, and the multiple card blocks 2 are evenly spaced on the wing blade 1 on one side of the notch, that is, the multiple card blocks 2 are located on the edge of any one of the above-mentioned arc plates, and are respectively used to be connected to the card slots of the corresponding parts of the drone.

[0050] During assembly and disassembly, the wing blade 1 is respectively engaged in the slots at the corresponding parts of the UAV through a plurality of clamping blocks 2, so that the wing blade 1 can be quickly assembled and disassembled, which is easy to operate and saves time and effort.

[0051] Preferably, in this embodiment, each set of clamping components includes two clamping blocks 2 , and the two clamping blocks 2 are spaced apart and distributed along the edge of the wing blade 1 .

[0052] In addition to the above-mentioned implementation manner, the number of the card blocks 2 in each set of card connection components can also be reasonably designed according to the needs, and the design selection is specifically made according to the needs.

[0053] In addition, the multiple clamping blocks 2 in each set of clamping components can also be divided into two groups and distributed on the two side edges of the corresponding arc-shaped plate in pairs.

[0054] Example 4

[0055] On the basis of Example 3, in this embodiment, a plurality of blocks 2 are L-shaped block structures, one end of which is fixedly connected to the edge of the wing blade 1, and the other end extends in the direction from the closed end to the open end of the wing blade 1.

[0056] This solution has a simple structure and a reasonable design. When the wing knife 1 is put on the wing of the drone, the multiple card blocks 2 can be connected to the multiple card slots on the drone, which is convenient and saves time and effort.

[0057] Preferably, in this embodiment, each L-shaped block 2 includes block one and block two, and block one and block two are respectively in a strip-shaped structure; block one extends from one side of the wing blade 1 to the other side, and one end thereof is fixedly connected to the edge of the wing blade 1; block two is distributed perpendicular to block one, and one end thereof is fixedly connected to the other end of block one, and the other end extends from the closed end to the open end of the wing blade 1.

[0058] In addition to the above embodiments, each block 2 may also adopt other suitable shapes, such as an arc-shaped structure or a triangular structure, with the groove thereof facing the open end of the wing blade 1 .

[0059] It should be noted that the closed end of the wing blade 1 refers to one end of the wing blade 1 , and the open end refers to the other end of the wing blade 1 .

[0060] Example 5

[0061] Based on any one of Examples 3 to 4, in this embodiment, the multiple clamping blocks 2 in the two groups of clamping groups are respectively located on the inner side of both sides of the wing blade 1 or the outer side of the wing blade 1 or the inner and outer sides of the wing blade 1, that is, the multiple clamping blocks 2 are respectively located on the inner side of the above-mentioned two curved plates or the outside of the two curved plates or the inner side of one of the curved plates and the outer side of the other curved plate.

[0062] This solution has a simple structure and a reasonable design. When the wing knife 1 is put on the wing of the drone, the multiple card blocks 2 can be connected to the multiple card slots on the drone, which is convenient and saves time and effort.

[0063] When the multiple clamping blocks 2 in the two sets of clamping components are respectively located on the inner and outer sides of the wing blade 1 on both sides of the gap, the stability of the installation of the wing blade 1 can be further improved (see Figure 3 and Figure 4 ).

[0064] It should be noted that the inner side of the above-mentioned wing blade 1 refers to the side close to the body 4 of the drone when the wing blade 1 is installed on the wing, and the outer side of the wing blade 1 refers to the side away from the body 4 of the drone when the blade 1 is installed on the wing.

[0065] Example 6

[0066] On the basis of any one of Embodiments 3 to 5, in this embodiment, an adhesive layer is attached to the plurality of card blocks 2 .

[0067] This solution has a simple structure and a reasonable design, and can further increase the stability of the installation of the wing knife 1.

[0068] During use, the adhesive layer can be formed by manually applying adhesive to the card block 2 during installation, or an adhesive layer can be pre-set on the card block 2, and a release paper can be pasted on the adhesive layer, and the release paper can be manually torn off during installation.

[0069] Example 7

[0070] Based on Example 2, in this embodiment, each set of snap-fit components includes multiple positioning pins, and the multiple positioning pins are installed on the wing blade 1 and positioned along the direction from one side to the other side of the wing blade 1, that is, the multiple positioning pins are moved and positioned along the direction from one side to the other side of the corresponding arc plate, and are respectively used to snap into the positioning grooves of the corresponding parts of the drone.

[0071] During assembly and disassembly, the wing blade 1 is respectively engaged in the locating grooves at the corresponding parts of the UAV through a plurality of locating pins, so that the wing blade 1 can be quickly assembled and disassembled, which is easy to operate and saves time and effort.

[0072] Preferably, in this embodiment, the multiple positioning pins in the two groups of clamping assemblies can be distributed on the same side of both ends of the wing blade 1. In this case, the multiple positioning pins in the two groups of clamping assemblies can be distributed opposite to each other in pairs or alternately spaced in sequence.

[0073] Alternatively, the multiple positioning pins in the two groups of clamping assemblies can be distributed on different sides of both ends of the wing blade 1, which can further improve the installation stability of the wing blade 1.

[0074] The above-mentioned embodiment 7 and embodiment 3 are parallel solutions.

[0075] In addition to the above-mentioned embodiments, the wing blade 1 can also be installed on the wing of the drone in other ways. For example, the wing blade 1 can be directly and detachably installed on the wing of the drone through bolts. In this case, screw holes that cooperate with the bolts are respectively provided on the wing of the drone and the wing blade 1.

[0076] Example 8

[0077] Based on Example 7, in this embodiment, a plurality of grooves corresponding to a plurality of positioning pins are provided on the edge of the wing blade 1, and the plurality of positioning pins are respectively installed in the plurality of grooves, one end of which is respectively connected to the bottom of the plurality of grooves through a spring, and the other end extends outside the plurality of grooves.

[0078] During disassembly and assembly, multiple positioning pins can be respectively received in multiple positioning grooves under the action of external force. When the wing knife 1 is put on the wing of the drone, the multiple positioning pins are released, and the multiple positioning pins are respectively engaged in the positioning grooves at the corresponding parts of the drone under the action of multiple spring forces, thereby realizing rapid disassembly and assembly of the wing knife, easy operation, and saving time and effort.

[0079] It should be noted that, when the spring is in a naturally extended state, the other end of each positioning pin extends out of the corresponding groove.

[0080] In addition to the above embodiment, multiple positioning pins can be movably installed in multiple grooves, with one end of each pin located in the multiple grooves and the other end extending outside the multiple grooves. The positioning method of the multiple positioning pins can be: each positioning pin is provided with a socket, and the edge of the wing blade 1 corresponding to the multiple groove notches is provided with a through hole connected to the interior thereof, and each through hole is inserted into a pin. When in use, the multiple pins are first manually moved until they exit the multiple sockets, and then the multiple positioning pins are manually moved to insert into the multiple slots on the drone, and then the multiple pins are manually inserted into the multiple sockets to position the multiple positioning pins.

[0081] Example 9

[0082] On the basis of the above embodiments, in this embodiment, the wing blade 1 is an arc-shaped plate structure that is wide in the middle and narrow at both ends.

[0083] The solution has a simple structure and a reasonable design, and blocks the airflow along the span direction of the wing, thereby improving the maneuverability of the UAV at a reduced speed and facilitating the flight of the UAV.

[0084] Preferably, in this embodiment, both ends of the wing blade 1 are in a pointed cone structure.

[0085] In addition to the above embodiments, the two ends of the wing blade 1 may have other shapes. For example, the two ends of the wing blade 1 may have a certain width, but the width is smaller than the width of the middle part of the wing blade 1 to ensure the flow blocking effect of the wing blade 1.

[0086] Example 10

[0087] Based on the above embodiments, this embodiment also provides a tail-seat vertical take-off and landing UAV, including a body 4, two front wings 5 are relatively fixedly installed on both sides of the front end of the body 4, and two rear wings 6 are relatively fixedly installed at the rear end; it also includes multiple wing blade structures as described above, and the multiple wing blades 1 are divided into two groups and are respectively installed at intervals on the front sides of the two rear wings 6.

[0088] The UAV has a simple structure and a reasonable design. The wing blades 1 arranged on the wings are designed to take into account that the take-off and landing process of the tail-seat UAV is in a multi-rotor state. The control torque in the pitch and yaw directions is provided by the rudder surface, and the magnitude of the control torque of the rudder surface is positively correlated with the magnitude of the propeller slipstream flowing over it. Therefore, it is necessary to provide wing blade rectification to increase the airflow flowing through the rudder surface, thereby increasing the steering effect. In addition, the wing blades 1 can be detachably installed on the UAV through a connecting mechanism, which is easy to disassemble and assemble, convenient for subsequent maintenance, and saves time and effort.

[0089] Preferably, in this embodiment, the two front wings 5 are respectively in a structure with one end being thick and the other end being thin, and the thick ends thereof are respectively fixedly connected to both sides of the front end of the body 4 .

[0090] In addition, the two rear wings 6 are respectively in a structure with one end being thick and the other end being thin, and the thick ends thereof are respectively fixedly connected to both sides of the rear end of the body 4 .

[0091] Preferably, in this embodiment, two wing blades 1 are provided on each rear wing 6 at intervals, and the two wing blades 1 are located on the front side of the rear wing 6 respectively.

[0092] In addition, of the two wing blades 1 on each rear wing 6 , one wing blade 1 is located at the thick end of the rear wing 6 , and the other wing blade 1 is close to the middle of the rear wing 6 .

[0093] Preferably, in this embodiment, both side surfaces of each wing blade 1 are respectively in an arc-shaped surface structure matching the outer shape of the rear wing 6 , which is reasonably designed and further improves the flow resistance effect of the wing blade 1 .

[0094] The disassembly and assembly process of the present invention is as follows:

[0095] During installation, each wing blade 1 is put on the corresponding part of the rear wing 6 from the front side of the corresponding rear wing 6 and is installed on the corresponding rear wing 6 through any one of the above-mentioned connecting mechanisms.

[0096] The drone provided by the present invention has a simple structure and a reasonable design. The wing blades 1 arranged on the wings are designed to take into account that the take-off and landing process of the tail-seat drone is in a multi-rotor state, and the control torque in the pitch and yaw directions is provided by the rudder surface. The magnitude of the control torque of the rudder surface is positively correlated with the speed of the propeller slipstream flowing over it. Therefore, it is necessary to provide wing blade rectification to increase the airflow flowing through the rudder surface, thereby increasing the steering effect. In addition, the wing blades 1 can be detachably installed on the drone through a connecting mechanism, which is convenient for disassembly and assembly, and facilitates subsequent maintenance, saving time and effort.

[0097] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the invention can be embodied in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be included therein. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

[0098] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

[0099] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A tail-seat vertical take-off and landing UAV, comprising a body (4), two front wings (5) relatively fixedly mounted on both sides of the front end of the body (4), and two rear wings (6) relatively fixedly mounted on the rear end of the body (4); characterized in that: It also includes a plurality of wing blades (1), each of which is an arc-shaped plate structure that is wide in the middle and narrow at both ends, and has a notch extending from the middle of one end to a position close to the other end, and is equipped with a connecting mechanism for detachably connecting it to the drone; the plurality of wing blades (1) are divided into two groups and are installed at intervals on the front sides of the two rear wings (6).

2. The tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The connecting mechanism comprises two groups of snap-fit components, and the two groups of snap-fit components are distributed on the wing blades (1) on both sides of the notch.

3. The tail-seat vertical take-off and landing UAV according to claim 2, characterized in that: Each group of the snap-fit components comprises a plurality of snap-fit blocks (2), and the plurality of snap-fit blocks (2) are evenly spaced and distributed on the wing blade (1) on one side of the notch, and are respectively used for snapping into the snap-fit slots at corresponding parts of the drone.

4. The tail-seat vertical take-off and landing UAV according to claim 3, characterized in that: The plurality of clamping blocks (2) are respectively in an L-shaped block structure, one end of which is respectively fixedly connected to the edge of the wing knife (1), and the other end of which extends in the direction from the closed end to the open end of the wing knife (1).

5. The tail-seat vertical take-off and landing UAV according to claim 3, characterized in that: The plurality of clamping blocks (2) in the two clamping groups are respectively located on the inner side of the wing knife (1) or the outer side of the wing knife (1) or both the inner side and the outer side of the wing knife (1) on both sides of the notch.

6. The tail-seat vertical take-off and landing UAV according to claim 3, characterized in that: An adhesive layer is attached to the plurality of card blocks (2).

7. The tail-seat vertical take-off and landing UAV according to claim 2, characterized in that: Each group of the clamping components includes a plurality of positioning pins, and the plurality of positioning pins are respectively installed on the wing blade (1) and positioned in a direction that moves from one side of the wing blade (1) to the other side, and are respectively used to clamp into the positioning grooves of corresponding parts of the drone.

8. The tail-seat vertical take-off and landing UAV according to claim 7, characterized in that: A plurality of grooves corresponding to the plurality of positioning pins are provided on the edge of the wing blade (1), and the plurality of positioning pins are respectively installed in the plurality of grooves, one end of each of the positioning pins is connected to the bottom of the plurality of grooves through a spring, and the other end of each of the positioning pins is respectively extended outside the plurality of grooves.

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