Wing blind hole connecting mechanism and unmanned aerial vehicle with same

Abstract

The invention provides a wing blind hole connecting mechanism and an unmanned aerial vehicle with the wing blind hole connecting mechanism, the wing blind hole connecting mechanism comprises a fastening unit, an elastic unit, a fixing unit and a pressing unit, the fastening unit is installed in a through hole formed in a wing, and the fastening unit and a blind hole are fixed through the fastening unit; the elastic unit has elastic force after being pressed and is installed between the fastening unit and the pressing unit, and after the pressing unit compresses the elastic unit, the elastic unit is fixed in the through hole through the fixing unit. Stable self-locking of the pressing unit is achieved, movement of the fastening unit is limited, and the connecting, fastening and anti-loosening performance and reliability of the wing mounting bolt blind hole are improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicle (UAV) design, and particularly relates to a wing blind hole connection mechanism and a UAV having the same. Background Art

[0002] In the field of UAV wing assembly, the wing bears most of the loads during UAV flight. The anti-loosening performance and reliability of wing fastening installation are particularly important, directly affecting the flight safety of the UAV. In UAV wing assembly, bolt connection is often used. When the wing bolt installation hole is a blind hole, there are two methods for bolt fastening and anti-loosening: one is to directly use a gasket for bolt anti-loosening, which is simple and fast to operate. However, when the UAV flight is severely bumpy or the flight load is large, the anti-loosening effect is not good, the anti-loosening reliability is poor, and the safety hazard is large; the other is to apply glue during the installation process of the wing bolt. After the glue is cured, the bolt and the threaded hole are bonded together. This method has a good anti-loosening effect, but it is difficult to disassemble the wing, and it affects the service life of the wing installation bolt and the threaded hole, and the maintenance cost is high. Moreover, in the above two methods, there is often a large step difference or gap between the position of the wing bolt installation hole and the wing shape, affecting the aerodynamic flight characteristics of the UAV. Summary of the Invention

[0003] The purpose of the present invention is to overcome the deficiencies in the prior art and provide a wing blind hole connection mechanism and a UAV having the same. The solution of the present invention can solve the problems existing in the above prior art.

[0004] The technical solution of the present invention:

[0005] According to the first aspect, a wing blind hole connection mechanism is provided, including a fastening unit, an elastic unit, a fixing unit, and a pressing unit. The fastening unit is installed in a through hole provided on the wing and is fixed to the blind hole through the fastening unit; the elastic unit has an elastic force after being pressed and is installed between the fastening unit and the pressing unit. After the pressing unit compresses the elastic unit, it is fixed in the through hole through the fixing unit.

[0006] Further, the fastening unit is a bolt, and a thread corresponding to the bolt is provided in the blind hole.

[0007] Further, the elastic unit is a spring, and the spring is installed with a pre-tightening force.

[0008] Further, the fixing unit is a pin shaft. One end of the pin shaft is installed in a blind hole inside the wing, and the other end is installed in a movement locking groove of the pressing unit. The movement locking groove is located on the outer side surface of the pressing unit. One end of the movement locking groove is open and the other end is closed. The open end provides an opening for the pin shaft to enter the movement locking groove, and the closed end is used to restrict the movement freedom of the pin shaft.

[0009] Further, two pin shafts are provided, and correspondingly, two movement locking grooves are provided.

[0010] Preferably, the pin shaft is provided with a large circular section, with a large diameter at one end and a small diameter at the other end, for fixed installation and limitation on the wing.

[0011] Further, the pressing unit is a pressing cap with an inner hole in a cylindrical structure. Movement locking grooves are symmetrically arranged on the outer circular surface, providing a path space for the movement and locking of the pin shaft. A slotted crosshead is arranged at the top, which cooperates with a slotted screwdriver to control the movement of the pressing cap. The inner hole at the bottom is used to place a spring.

[0012] Preferably, a switch mark is arranged at the top of the pressing cap to guide the movement of the pressing cap so as to achieve disassembly and locking.

[0013] Preferably, the inner hole of the pressing cap is a flat bottom hole.

[0014] Further, the top end face of the pressing cap conforms to the shape of the drone wing.

[0015] According to a second aspect, a drone is provided, which has the wing blind hole connection mechanism described in this application.

[0016] Advantages of the present invention compared with the prior art:

[0017] (1) Through the pre-tightening force provided by the pressing unit to the elastic unit, the fastening unit is pressed through the pre-tightening force of the elastic unit, and the pressing unit is fixed through the fixing unit, thereby restricting the movement of the pressing unit, achieving stable self-locking of the pressing unit, restricting the movement of the fastening unit, and improving the fastening and anti-loosening performance and reliability of the wing installation bolt blind hole connection;

[0018] (2) The present invention solves the problem that the gluing of the bolt blind hole connection restricts the disassembly of the wing. It is installed using a screwdriver, and the operation is simple and practical;

[0019] (3) By conformally designing the outer shape of the pressing unit with the outer shape of the wing and designing the outer diameter of the pressing unit to conform to the shape of the wing bolt installation hole, the present invention reduces the influence of the wing bolt installation hole on the aerodynamic shape of the drone and ensures the aerodynamic performance during the flight of the drone. Description of the Drawings

[0020] The included drawings are used to provide a further understanding of the embodiments of the present invention. They form a part of the specification, are used to illustrate the embodiments of the present invention, and are used to explain the principles of the present invention together with the written description. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0021] Figure 1 Shows an exploded view of the wing blind hole connection mechanism provided according to an embodiment of the present invention;

[0022] Figure 2 Shows a cross-sectional view of the wing blind hole connection mechanism provided according to an embodiment of the present invention;

[0023] Figure 3 Shows a schematic diagram of a bolt provided according to an embodiment of the present invention;

[0024] Figure 4 Shows a schematic diagram of a spring provided according to an embodiment of the present invention;

[0025] Figure 5 Shows a schematic diagram of a pin shaft provided according to an embodiment of the present invention;

[0026] Figure 6 Shows a front view of a compression cap provided according to an embodiment of the present invention;

[0027] Figure 7 Shows an axonometric schematic diagram of a compression cap provided according to an embodiment of the present invention.

[0028] The above-mentioned drawings include the following reference numerals:

[0029] 1. Bolt; 11. Hexagon socket; 2. Spring; 3. Pin shaft; 31. Large round end; 4. Compression cap; 41. Movement locking groove; 41a. Open end; 41b. Closed end; 42. Slotted screwdriver slot; 43. Switch mark; 44. Inner hole; 45. Outer circle; 5. Wing; 51. Wing bolt mounting hole; 6. Airframe. Detailed implementation manners

[0030] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. The description of at least one exemplary embodiment below is actually only illustrative and in no way restrictive of the present invention and its application or use. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0031] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, they specify the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0032] Unless otherwise specifically stated, the relative arrangements of components and steps, numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present invention. At the same time, it should be understood that for the convenience of description, the dimensions of the various parts shown in the drawings are not drawn in actual proportional relationships. Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the said technologies, methods, and devices should be regarded as part of the authorized specification. In all the examples shown and discussed here, any specific value should be construed as merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that like reference numerals and letters denote like items in the following drawings, and thus, once an item is defined in one drawing, it does not require further discussion in subsequent drawings.

[0033] As Figure 1 shown, according to an embodiment of the first aspect of the present invention, a wing blind hole connection mechanism is provided, which includes a fastening unit, an elastic unit, a fixing unit, and a pressing unit. The fastening unit is installed in a through hole provided on the wing and is fixed to the blind hole through the fastening unit; the elastic unit has elastic force after being pressed and is installed between the fastening unit and the pressing unit. After the pressing unit compresses the elastic unit, it is fixed in the through hole through the fixing unit.

[0034] Through the above settings, the pre-tightening force provided by the pressing unit to the elastic unit, through the pre-tightening force of the elastic unit, presses the fastening unit, and the pressing unit is fixed through the fixing unit, thereby restricting the movement of the pressing unit, realizing the stable self-locking of the pressing cap, restricting the movement of the fastening unit, and achieving the effect of preventing loosening of the connection.

[0035] Further, in one embodiment, the fastening unit is a bolt, and a thread corresponding to the bolt is provided in the blind hole. In other embodiments, other fastening methods may be used for fastening.

[0036] Further, in one embodiment, the elastic unit is a spring, and the spring is installed with pre-tightening force. In other embodiments, other elastic components may be used to provide elastic force.

[0037] Further, in one embodiment, the fixing unit is a pin shaft. One end of the pin shaft is installed in a blind hole in the wing, and the other end is installed in the moving locking groove of the pressing unit. The moving locking groove is located on the outer side surface of the pressing unit. One end of the moving locking groove is open and the other end is closed. The open end provides an opening for the pin shaft to enter the moving locking groove, and the closed end is used to restrict the degree of freedom of movement of the pin shaft. Through the above settings, it is convenient to disassemble and lock the pressing unit, thus providing convenience for maintenance.

[0038] Further, in one embodiment, two pin shafts are provided, and correspondingly, two moving locking grooves are provided.

[0039] Preferably, in one embodiment, the pin shaft is provided with a large circular section, with a large diameter at one end and a small diameter at the other end, for fixed installation and limitation on the wing.

[0040] Further, in one embodiment, the pressing unit is a compression cap with a cylindrical inner hole structure. Moving locking grooves are symmetrically arranged on the outer cylindrical surface, providing a path space for the movement and locking of the pin shaft. A slotted crosshead is provided at the top, which cooperates with a slotted screwdriver to control the movement of the compression cap. The inner hole at the bottom is used to place a spring.

[0041] Preferably, in one embodiment, a switch mark is provided at the top of the compression cap to guide the movement of the compression cap to achieve disassembly and locking.

[0042] Preferably, in one embodiment, the inner hole of the compression cap is a flat-bottomed hole.

[0043] Further, in one embodiment, the top end face of the compression cap conforms to the shape of the UAV wing. This reduces the influence of the wing bolt mounting hole on the aerodynamic shape of the UAV and ensures the aerodynamic performance during the flight of the UAV.

[0044] According to the embodiment of the second aspect, a UAV is provided, which has the wing blind hole connection mechanism described in the present application.

[0045] To further understand a wing blind hole connection mechanism provided by the present invention, the following will be described in detail with specific examples and drawings.

[0046] As Figures 1 to 7 shown, according to one aspect of the present invention, a wing blind hole connection mechanism is provided. The mechanism includes: bolt 1, spring 2, pin shaft 3, compression cap 4.

[0047] As Figure 3 shown, the top of the bolt 1 is provided with an internal hexagonal socket 11. The bolt 1 is used for wing installation. The internal hexagonal socket 11, on the one hand, cooperates with a wrench to tighten the bolt 1; on the other hand, it is used to place the spring 2 and provide a placement space for the spring 2.

[0048] As Figure 4The spring 2 connects the compression cap and the bolt. One end is placed in the hexagon socket 11, and the other end is placed in the inner hole 44, providing a pressing force for the bolt 1.

[0049] As Figure 5 The pin shaft 3 is installed and fixed in the wing 5 and is provided with a large round end 31, and the large round end 31 cooperates with the movement locking groove 41 of the compression cap 4.

[0050] As Figure 6 and Figure 7 The compression cap 4 is an integral structure with a cylindrical inner hole, conforming to the aerodynamic shape of the wing 5. Its diameter depends on the wing bolt mounting hole 51. Movement locking grooves 41 are symmetrically arranged on the outer cylindrical surface 45, providing a path space for the movement and locking of the pin shaft. A slotted cross recess 42 is provided at the top, and an inner hole 44 is provided at the bottom for placing the spring.

[0051] The present invention also provides a drone with a wing blind hole connection mechanism, and the drone includes the wing bolt blind hole connection anti-loosening mechanism described in the above embodiment.

[0052] The working principle of the present invention:

[0053] During the wing installation process, the bolt 1 is tightened, the spring 2 is placed in the hexagon socket 11 of the bolt 1, and then the inner hole 44 of the compression cap 4 is placed in cooperation with the spring 2. The large round end of the pin shaft 3 is aligned with the open end 41a of the compression cap 4. Use a slotted screwdriver to press the compression cap 4. When the pin shaft 3 enters the movement locking groove 41, rotate the compression cap 4. The pin shaft 3 moves along the movement locking groove 41 until the rotation of the compression cap 4 is blocked. Stop pressing the compression cap 4. Under the action of the elastic force of the spring 2, the pin shaft 3 falls into the closed end 41b of the movement locking groove 41, the compression cap 4 is locked, the spring 2 applies a corresponding elastic force to the bolt 1, restricting the movement of the bolt 1, and at the same time increasing the bolt pressing force and enhancing the bolt loosening friction force, realizing the anti-loosening function of the bolt 1.

[0054] In summary, a wing blind hole connection mechanism provided by the present invention has at least the following advantages compared with the prior art:

[0055] (1) Through the pre-tightening force provided by the pressing unit to the elastic unit, the fastening unit is pressed by the pre-tightening force of the elastic unit, and the pressing unit is fixed by the fixing unit, thereby restricting the movement of the pressing unit, realizing the stable self-locking of the compression cap, restricting the movement of the fastening unit, and enhancing the fastening and anti-loosening performance and reliability of the wing installation bolt blind hole connection;

[0056] (2) The present invention solves the problem that the gluing of the bolt blind hole connection restricts the disassembly of the wing. It is installed using a screwdriver, and the operation is simple and practical;

[0057] (3) By conformally designing the shape of the compression cap to match the shape of the wing and making the outer diameter of the compression cap follow the contour of the wing bolt mounting holes, the present invention reduces the impact of the wing bolt mounting holes on the aerodynamic shape of the UAV, ensuring the aerodynamic performance during the flight of the UAV.

[0058] For ease of description, spatial relative terms such as "above", "over", "on the upper surface", "upper" etc. can be used here to describe the spatial position relationship of one device or feature to other devices or features as shown in the figures. It should be understood that the spatial relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figure is inverted, a device described as "above" or "over" other devices or structures will then be positioned "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both the orientations of "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and corresponding interpretations should be made for the spatial relative descriptions used here.

[0059] In addition, it should be noted that using terms such as "first", "second" etc. to define components is only for the convenience of differentiating the corresponding components. Without additional statements, these terms have no special meanings, and thus should not be construed as limiting the protection scope of the present invention.

[0060] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.

Claims

1. A wing blind hole connection mechanism, characterized in that It includes a fastening unit, an elastic unit, a fixing unit and a pressing unit. The fastening unit is installed in a through hole provided on the wing and is fixed to the blind hole through the fastening unit; the elastic unit has an elastic force after being pressed and is installed between the fastening unit and the pressing unit. After the pressing unit compresses the elastic unit, it is fixed in the through hole through the fixing unit.

2. The wing blind hole connection mechanism according to claim 1, characterized in that, The fastening unit is a bolt, and a thread corresponding to the bolt is provided in the blind hole.

3. The wing blind hole connection mechanism according to claim 2, characterized in that, The elastic unit is a spring, and the spring is installed with a pre-tightening force.

4. The wing blind hole connection mechanism according to claim 3, characterized in that, The fixing unit is a pin shaft. One end of the pin shaft is installed in a blind hole inside the wing, and the other end is installed in a movement locking groove of the pressing unit. The movement locking groove is located on the outer side surface of the pressing unit. One end of the movement locking groove is open and the other end is closed. The open end provides an opening for the pin shaft to enter the movement locking groove, and the closed end is used to restrict the movement freedom of the pin shaft.

5. The wing blind hole connection mechanism according to claim 4, characterized in that, Two pin shafts are provided, and correspondingly, two movement locking grooves are provided.

6. The wing blind hole connection mechanism according to claim 5, characterized in that, The pin shaft is provided with a large circular segment, with a large diameter at one end and a small diameter at the other end, for fixing and limiting the installation on the wing.

7. The wing blind hole connection mechanism according to claim 3, characterized in that, The pressing unit is a pressing cap with a cylindrical inner hole structure. Movement locking grooves are symmetrically arranged on the outer circular surface to provide a path space for the movement and locking of the pin shaft. A slotted cross recess is provided at the top, which cooperates with a flat-blade screwdriver to control the movement of the pressing cap. The inner hole at the bottom is used to place the spring.

8. The wing blind hole connection mechanism according to claim 7, characterized in that, A switch mark is provided at the top of the pressing cap to guide the movement of the pressing cap to achieve disassembly and locking. The inner hole of the pressing cap is a flat-bottom hole.

9. The wing blind hole connection mechanism according to claim 7, characterized in that, The top end face of the pressing cap conforms to the shape of the wing of the drone.

10. A drone, characterized in that, The drone has a wing blind hole connection mechanism described in this application.

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