Wingtip winglet quick release structure and unmanned aerial vehicle

Abstract

The utility model discloses a winglet quick release structure which comprises a winglet body, the winglet assembly is detachably connected with the tail end of the wing body; the locking assembly is arranged on the wing body and / or the wingtip winglet assembly, and when the wingtip winglet assembly is connected with the tail end of the wing body, the locking assembly can detachably lock the wingtip winglet assembly and the wing body; by applying the winglet quick disassembly structure, the winglet can be conveniently disassembled on the premise that normal flight of the unmanned aerial vehicle is guaranteed, and transportation is convenient; the utility model further provides the unmanned aerial vehicle.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane field, in particular to a wing tip winglet quick release structure. BACKGROUND

[0002] Unmanned aircraft is called "unmanned plane" for short, which is a kind of aircraft without cabin, but with automatic pilot, program control device, signal acquisition device and other equipment. The personnel on the ground, ship or mother plane remote control station can track, locate, remotely control, remotely measure and digitally transmit through wireless equipment. It can take off like ordinary aircraft or be launched by booster rocket under wireless remote control.

[0003] In the current unmanned plane, in order to reduce the induced drag of the wing, the wing tip winglet is usually installed at the end of the wing; in order to ensure the overall structural strength of the wing, the wing tip winglet needs to be fixed with the wing body by a relatively firm fixing structure, which makes it difficult to disassemble the wing tip winglet from the wing body and inconvenient for transportation. SUMMARY

[0004] The utility model aims at at least solving one of the technical problems existing in the prior art. Therefore, the utility model provides a wing tip winglet quick release structure, which can be easily disassembled from the wing tip winglet under the premise of ensuring the normal flight of the unmanned plane, and is convenient for transportation.

[0005] The wing tip winglet quick release structure of the utility model comprises: a wing body; a wing tip winglet assembly, which is detachably connected with the end of the wing body; and a locking assembly, which is arranged on the wing body and / or the wing tip winglet assembly and can releasably lock the wing tip winglet assembly and the wing body when the wing tip winglet assembly is connected with the end of the wing body.

[0006] According to some embodiments of the utility model, the locking assembly further comprises: a locking hook arranged at the end of the wing body; and a locking piece movably arranged on the wing tip winglet assembly; when the wing tip winglet assembly is connected with the end of the wing body, the locking piece can be moved to clamp the locking hook; and the locking piece can be moved away from the locking hook.

[0007] According to some embodiments of the utility model, the locking piece is rotationally connected with the wing tip winglet assembly, a clamping hook is arranged on the locking piece, and the locking piece can be rotated to clamp the locking hook with the clamping hook or move the clamping hook away from the locking hook.

[0008] According to some embodiments of the utility model, the locking assembly further comprises a limiting piece arranged on the wing tip winglet assembly, an arc-shaped accommodating groove is arranged on the limiting piece, an extension is arranged on the locking piece, and the extension is slidably matched with the accommodating groove.

[0009] According to some embodiments of the utility model, the locking assembly further comprises a locking spring arranged in the accommodating groove, two ends of the locking spring abut against the extension part and the limiting piece respectively, and the locking spring is used for driving the locking piece to rotate to the hooking piece to hook the locking hook.

[0010] According to some embodiments of the utility model, the locking assembly further comprises a locking cover plate, an unlocking handle is fixedly arranged on the locking piece, and the limiting piece and the locking piece are located between the locking cover plate and the wing tip winglet assembly; an arc-shaped limiting groove is formed in the locking cover plate, and the unlocking handle passes through the limiting groove and extends out of the locking cover plate.

[0011] According to some embodiments of the utility model, a main positioning column is arranged on the wing tip winglet assembly, and a main accommodating hole is arranged at the tail end of the wing body, and the main positioning column can be inserted into the main accommodating hole.

[0012] According to some embodiments of the utility model, the main positioning column has two, and the two main positioning columns are distributed along the front-rear direction.

[0013] The utility model further provides a kind of unmanned aerial vehicle, comprising: fuselage;Above-mentioned wing tip winglet quick-release structure, it is arranged on fuselage.

[0014] Apply above-mentioned wing tip winglet quick-release structure, in the unmanned aerial vehicle transportation process, the locking of wing tip winglet assembly and wing by locking assembly can be released, then wing tip winglet is stored separately after being disassembled;When unmanned aerial vehicle is used, wing tip winglet assembly can be installed at the tail end of wing body, then wing tip winglet assembly and wing body are locked by locking assembly, guarantee the stability of entire wing structure in the unmanned aerial vehicle flight process, normal flight.

[0015] Additional aspects and advantages of the utility model will be partially given in the following description, some will become obvious from the following description, or be understood by the practice of the utility model. BRIEF DESCRIPTION OF DRAWINGS

[0016] The above and / or additional aspects and advantages of the utility model will become apparent and more readily appreciated from the following description of the embodiments, with reference to the following drawings, in which:

[0017] Figure 1 It is the isometric view of wing tip winglet quick-release structure in the embodiment of the utility model;

[0018] Figure 2 It is the isometric view of wing tip winglet quick-release structure in the embodiment of the utility model; Figure 1 Another view of wing tip winglet quick-release structure in the embodiment of the utility model;

[0019] Figure 3 It is the isometric view of wing tip winglet quick-release structure in the embodiment of the utility model; Figure 2 Enlarged view of A in the embodiment of the utility model;

[0020] Figure 4 It is the isometric view of wing tip winglet quick-release structure in the embodiment of the utility model; Figure 1Figure 6 is a bottom view of the mid-wing winglet quick release structure with the locking cover plate removed;

[0021] Figure 5 For Figure 4 Figure 7 is a close-up view of the mid-B;

[0022] Figure 6 For Figure 1 Figure 8 is an isometric view of the mid-wing winglet assembly;

[0023] The above figures contain the following reference numerals.

[0024] DETAILED DESCRIPTION

[0025] Embodiments of the present application are described below in detail, examples of which are shown in the drawings, wherein the same or similar reference numerals represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary, only for explaining the present application, and cannot be understood as a limitation of the present application.

[0026] In the description of the present application, it should be understood that the orientation description, such as the orientation or position relationship indicated by up, down, front, back, left, right, etc. is based on the orientation or position relationship shown in the drawings, only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element indicated must have a particular orientation, be constructed and operated in a particular orientation, therefore cannot be understood as a limitation of the present application.

[0027] In the description of the present application, the meaning of several is one or more, the meaning of multiple is two and two or more, greater than, less than, more than, etc. are understood as not including the number, above, below, etc. are understood as including the number. If the first, second is described, it is only for the purpose of distinguishing technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features or the order of indicated technical features.

[0028] In the description of the present application, unless otherwise explicitly limited, the words such as setting, installing, connecting, etc. should be broadly understood, and the person skilled in the art can reasonably determine the specific meaning of the above words in the present application according to the specific content of the technical solution.

[0029] Referring to Figures 1 to 6The wing tip winglet quick release structure of the embodiment includes: a wing body 100; a wing tip winglet assembly 200 detachably connected with the end of the wing body 100; and a locking assembly arranged on the wing body 100 and / or the wing tip winglet assembly 200, which can releasably lock the wing tip winglet assembly 200 and the wing body 100 when the wing tip winglet assembly 200 is connected with the end of the wing body 100.

[0030] The wing tip winglet quick release structure is applied to release the locking of the wing tip winglet assembly 200 and the wing body 100 by the locking assembly during the unmanned aerial vehicle transportation process, and then the wing tip winglet is detached and stored separately; during the use of the unmanned aerial vehicle, the wing tip winglet assembly 200 is installed at the end of the wing body 100, and then the wing tip winglet assembly 200 and the wing body 100 are locked by the locking assembly, so that the stability of the whole wing structure during the flight of the unmanned aerial vehicle is ensured, and normal flight is achieved.

[0031] The wing tip winglet, English name Winglet, is a small wing similar to the wing surface, which is approximately perpendicular to the wing surface; during flight, the high-pressure area airflow under the wing surface will flow around the wing tip to the upper surface, forming a strong vortex airflow, which extends a long distance backward from the wing, and they take away energy and increase induced drag. The wing tip winglet is used to weaken this resistance.

[0032] The wing tip winglet has the following advantages:

[0033] 1. End plate effect: blocking the flow around the lower surface of the wing to the upper surface, weakening the wing tip vortex intensity, thereby effectively increasing the effective aspect ratio of the wing.

[0034] 2. Dissipation of wing tip vortex: because the wing tip winglet itself is also a small wing, it can also generate a wing tip vortex, which is opposite in direction to the main wing tip vortex and is very close to it. Under the action of viscous dissipation, the two vortexes are intertwined and counteract each other, also achieving the purpose of reducing induced drag.

[0035] 3. Increase of wing lift and forward thrust: the upper wing tip winglet can generate a small wing lift and thrust component by using a three-dimensional distorted flow field.

[0036] 4. Delay of premature separation of wing tip airflow and improvement of stall angle of attack: generally speaking, the wing tip of a backward-swept wing is a three-dimensional effect area, the flow tube is contracted, and when the airflow flows through, it is first sharply accelerated, the pressure is reduced, and then it is sharply recovered, entering a very steep adverse pressure gradient area, which causes premature separation of the wing tip boundary layer, resulting in stall. However, the wing tip winglet installed at the wing tip can use its pressure field to correspond to the wing tip adverse pressure field, so that the pressure distribution is not steep, and the adverse pressure gradient is reduced. If designed properly, the airflow separation at the wing tip of the wing can be delayed, and the stall angle of attack and the buffet lift coefficient of the aircraft can be improved.

[0037] In the embodiment, the front-rear, left-right and up-down directions are described with reference to the common orientation description method of aircraft, i.e., the heading of the aircraft is regarded as the front, the left hand side of a person standing at the rear side of the aircraft and looking forward is regarded as the left, and the direction upward when the roll angle of the aircraft is 0 degree is regarded as the up.

[0038] It can be understood that the locking assembly can be connected to the wing tip winglet assembly 200 and the end of the wing body 100 in various ways, and the locking assembly can releasably lock the wing tip winglet assembly 200 and the wing body 100; for example, the wing tip winglet assembly 200 and the wing body 100 are connected by quick release bolts.

[0039] In the embodiment, the releasable locking of the locking assembly to the wing tip winglet assembly 200 and the wing body 100 means that the locking assembly can lock the wing body 100 and the wing tip winglet assembly 200 during installation, and can release the locking of the two during removal, so as to facilitate the removal of the wing tip winglet assembly 200 from the wing body 100.

[0040] As shown in Figures 3 to 5 , the locking assembly further comprises: a locking hook 101 arranged at the end of the wing body 100; a locking piece 205 movably arranged on the wing tip winglet assembly 200; when the wing tip winglet assembly 200 is connected to the end of the wing body 100, the locking piece 205 can be moved to block the locking hook 101; the locking piece 205 can be moved away from the locking hook 101; wherein the locking piece 205 can move on the wing tip winglet assembly 200, when the wing tip winglet is installed at the end of the wing body 100, the locking piece 205 can be moved to block the locking hook 101; when it is necessary to remove the wing tip winglet assembly 200, only the locking piece 205 needs to be moved away from the locking hook 101 to release the locking of the locking piece 205 and the locking hook 101, and then the wing tip winglet assembly 200 can be removed.

[0041] In the embodiment, the wing body 100 refers to the end of the wing body 100 away from the fuselage.

[0042] As shown in Figure 5 , the locking piece 205 is rotationally connected with the wing tip winglet assembly 200, the locking piece 205 is provided with a clamping hook, and the locking piece 205 can be rotated to block the locking hook 101 or the clamping hook away from the locking hook 101; wherein the locking piece 205 can be rotated relative to the wing tip winglet to block the locking hook 101 or away from the locking hook 101; of course, the locking piece 205 can be arranged in sliding connection with the wing tip winglet assembly 200, so that the locking piece 205 can be slid to block the locking hook 101 or away from the locking hook 101.

[0043] As shown in Figure 5As shown, the locking assembly further comprises a limiting piece 207 arranged on the winglet component 200, and an arc-shaped accommodating groove is formed in the limiting piece 207, and an extension part is arranged on the locking piece 205, and the extension part is in sliding fit with the accommodating groove; wherein the extension path of the accommodating groove is the path of the rotation of the locking piece 205, and the extension part also slides in the accommodating groove when the locking piece 205 rotates, so as to ensure the stability of the rotation of the locking piece 205.

[0044] Specifically, the locking assembly further comprises a locking spring 206 arranged in the accommodating groove, and the two ends of the locking spring 206 abut against the extension part and the limiting piece 207 respectively, and the locking spring 206 is used to drive the locking piece 205 to rotate to the hooking position of the locking hook 101; wherein one end of the accommodating groove is open to fit with the extension part, and the other end is closed to abut against the locking spring 206; after the locking piece 205 clamps the locking hook 101, the locking spring 206 can drive the locking piece 205 to firmly clamp the locking hook 101, so as to ensure the stability of the installation of the winglet component 200; when the winglet component 200 is installed, when the winglet component 200 is installed in place relative to the wing body 100, the locking piece 205 can automatically clamp the locking hook 101 under the action of the locking spring 206, so as to facilitate the installation of the winglet component 200.

[0045] As shown in Figure 3 , the locking assembly further comprises a locking cover plate 204, and an unlocking handle 202 is fixedly arranged on the locking piece 205, and the limiting piece 207 and the locking piece 205 are located between the locking cover plate 204 and the winglet component 200; an arc-shaped limiting groove 203 is formed in the locking cover plate 204, and the unlocking handle 202 passes through the limiting groove 203 and extends out of the locking cover plate 204; wherein the locking piece 205, the limiting piece 207 and the locking spring 206 are located between the cover plate and the winglet component 200, and the locking cover plate 204 is used to fix and protect the locking piece 205, the limiting piece 207 and the locking spring 206; wherein the unlocking handle 202 extending out of the locking cover plate 204 is used to drive the locking piece 205 to rotate when the winglet component 200 is removed, so that the locking piece 205 is away from the locking hook 101; and the extension path of the limiting groove 203 is consistent with the rotation path of the locking piece 205, and the limiting groove 203 is closed at both ends to limit the rotation range of the locking piece 205.

[0046] As shown in Figure 6 , the winglet component 200 is provided with a main positioning column 208, and the end of the wing body 100 is provided with a main accommodating hole, and the main positioning column 208 can be inserted into the main accommodating hole; wherein the aerodynamic force of the winglet component 200 is transmitted to the wing body 100 through the main positioning column 208, so as to prevent the locking assembly from being broken due to excessive force.

[0047] Specifically, the main positioning column 208 has two, and the two main positioning columns 208 are spaced apart in the front-rear direction; wherein the two main positioning columns 208 which are spaced apart can not only disperse and transmit the aerodynamic force received by the winglet assembly 200 to the wing body 100, but also can better withstand the torsional force of the winglet assembly 200 relative to the wing body 100, and ensure the structural stability of the entire wing including the winglet.

[0048] As shown in Figure 6 The mounting component 209 is actually a component for limiting the aileron mounted on the wing, and is not a component mounted on the winglet.

[0049] The embodiment also provides an unmanned aerial vehicle, comprising: a fuselage; and the winglet quick-release structure arranged on the fuselage.

[0050] Wherein, the winglet assembly 200 of the embodiment is a bifurcated winglet, having an upper wing piece and a lower wing piece 201, wherein the upper wing piece is smoothly connected with the wing body 100, and can more effectively reduce the flight resistance.

[0051] The embodiment of the utility model has been described in detail in combination with the drawings, but the utility model is not limited to the above-mentioned embodiment, and various changes can be made within the knowledge range possessed by those skilled in the art without departing from the purpose of the utility model.

Claims

1. A wing tip wing quick release structure, characterized by, The wing body (100) comprises: A wing tip winglet assembly (200) detachably connected to the end of the wing body (100); A locking assembly arranged on the wing body (100) and / or the wing tip winglet assembly (200), which can releasably lock the wing tip winglet assembly (200) and the wing body (100) when the wing tip winglet assembly (200) is connected to the end of the wing body (100). The locking assembly further comprises:

2. The wing tip winglet quick release structure according to claim 1, wherein A locking hook (101) arranged at the end of the wing body (100); A locking piece (205) movably arranged on the wing tip winglet assembly (200); When the wing tip winglet assembly (200) is connected to the end of the wing body (100), the locking piece (205) can be moved to block the locking hook (101); The locking piece (205) can be moved away from the locking hook (101). The locking piece (205) is rotationally connected to the wing tip winglet assembly (200), and a clamping hook is arranged on the locking piece (205), which can be rotated to block the locking hook (101) or to move away from the locking hook (101).

3. The wing tip winglet quick release structure according to claim 2, wherein The locking assembly further comprises a limiting piece (207) arranged on the wing tip winglet assembly (200), an arc-shaped accommodating groove is formed in the limiting piece (207), and an extension is arranged on the locking piece (205), which is in sliding fit with the accommodating groove.

4. The wing tip winglet quick release structure according to claim 3, wherein The locking assembly further comprises a locking spring (206) arranged in the accommodating groove, the two ends of the locking spring (206) abut against the extension and the limiting piece (207) respectively, and the locking spring (206) is used to drive the locking piece (205) to rotate to block the locking hook (101).

5. The wing tip winglet quick release structure according to claim 4, wherein The locking assembly further comprises a locking cover plate (204), an unlocking handle (202) is fixedly arranged on the locking piece (205), and the limiting piece (207) and the locking piece (205) are located between the locking cover plate (204) and the wing tip winglet assembly (200); an arc-shaped limiting groove (203) is formed in the locking cover plate (204), and the unlocking handle (202) passes through the limiting groove (203) and extends out of the locking cover plate (204).

6. The wing tip winglet quick release structure according to claim 5, wherein A main positioning column (208) is arranged on the wing tip winglet assembly (200), and a main accommodating hole is arranged at the end of the wing body (100), and the main positioning column (208) can be inserted into the main accommodating hole.

7. The wing tip winglet quick release structure according to claim 1, wherein The main positioning column (208) has two, and the two main positioning columns (208) are spaced apart in the front-rear direction.

8. The wing tip winglet quick release structure according to claim 7, wherein The wing body (100) comprises:

9. A drone, characterized in that, A wing body; The wing tip winglet quick release structure of claim 1 is arranged on the wing body. ​

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