CN211391658U

CN211391658U - Quick assembly disassembly structure and aircraft of aircraft wingtip winglet

Info

Publication number: CN211391658U
Application number: CN201921107026.0U
Authority: CN
Inventors: 谭冠珩; 周江华
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-07-15
Filing date: 2019-07-15
Publication date: 2020-09-01
Anticipated expiration: 2029-07-15

Abstract

The utility model discloses a quick assembly disassembly structure of aircraft wingtip winglet, include: an airfoil; a winglet connected to a free end of the wing by at least one set of quick connect mechanisms. Because the winglet of the utility model is connected with the wing through the quick connecting mechanism, the traditional assembling mode of locking the winglet on the wing by a plurality of bolts is abandoned, so that a worker does not need to twist a plurality of bolts when assembling or disassembling the winglet, and the assembling or disassembling efficiency of the winglet is improved; simultaneously the utility model provides an aircraft, including the aircraft main part, the aircraft main part is gone up and is used foretell a quick assembly disassembly structure of aircraft wingtip winglet, because the aircraft is through the quick assembly disassembly structure who adopts foretell aircraft wingtip winglet, can improve the assembly or the dismantlement speed of winglet, and then helps improving the assembly production efficiency of aircraft or the aircraft of being convenient for to dismantle and maintain.

Description

Quick assembly disassembly structure and aircraft of aircraft wingtip winglet

Technical Field

The utility model belongs to the technical field of the aircraft and specifically relates to a quick assembly disassembly structure and an aircraft of aircraft wingtip winglet.

Background

At present, an existing model airplane or an existing unmanned aerial vehicle generally comprises a main body, and wings are respectively installed on two sides of the middle of the main body.

In order to enhance the flight performance of a model airplane or drone, a winglet is also typically provided at the free end of the wing remote from the main body of the airplane. In order to ensure that the winglet can be firmly installed at the free end of the wing, the winglet is generally installed on the machine body by adopting a plurality of bolts, so that the winglet can be assembled and disassembled only by screwing a plurality of bolts when a worker assembles or maintains a model airplane or an unmanned aerial vehicle, time and labor are wasted, and the efficiency is low.

SUMMERY OF THE UTILITY MODEL

The utility model aims to at least solve one of the technical problems in the prior art and provide a quick dismounting structure which is convenient for dismounting wingtips winglets of aircrafts; an aircraft is also provided that facilitates assembly or maintenance.

The utility model discloses a solve above-mentioned technical problem and adopt following technical scheme:

a quick-disconnect structure for a winglet of an aircraft wing tip, comprising:

an airfoil;

a winglet connected to a free end of the wing by at least one set of quick connect mechanisms.

As an improvement of the above technical solution, the quick connection mechanism includes:

the connecting bayonet lock comprises a connecting cylinder, and a block piece is arranged at the free end of the connecting cylinder; the diameter-changing hole comprises a large-diameter hole through which the clamping block piece can pass, and the side wall of the large-diameter hole extends outwards and arches to form a small-diameter hole which can be clamped with the clamping block piece; one of the connecting bayonet lock and the reducing hole is arranged on the wing, and the other connecting bayonet lock and the reducing hole are arranged on the winglet.

As a further improvement of the above technical solution, the connecting bayonet is fixedly arranged on the winglet, and the reducing hole is arranged at the free end of the wing; the connecting cylinder for connecting the clamping pin is a bolt fixedly arranged on the winglet, and the clamping block piece is a nut in threaded connection with the bolt.

Furthermore, a positioning block is arranged at the position, adjacent to the small-diameter hole, of the inner side wall of the free end of the wing, and a positioning notch matched with the shape of the clamping block piece is formed in the positioning block.

Still further, the winglet is connected with the free end of the wing through two groups of quick connecting mechanisms, and the two groups of quick connecting mechanisms are respectively arranged at two sides of the free end of the wing.

An aircraft comprises an aircraft body, wherein the aircraft body is provided with the quick-release structure of the wingtip winglet of the aircraft.

The utility model has the advantages that: because the winglet of the utility model is connected with the wing through the quick connecting mechanism, the traditional assembling mode of locking the winglet on the wing by a plurality of bolts is abandoned, so that a worker does not need to twist a plurality of bolts when assembling or disassembling the winglet, and the assembling or disassembling efficiency of the winglet is improved; additionally, the utility model discloses an aircraft can improve the assembly or the dismantlement speed of winglet through the quick assembly disassembly structure that adopts foretell aircraft wingtip winglet, and then helps improving the assembly production efficiency or the aircraft of being convenient for of aircraft to dismantle and maintain.

Drawings

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

Fig. 1 is a schematic structural exterior view of a preferred embodiment of a quick-release structure of a winglet according to the invention;

fig. 2 is a schematic view of the state of the bayonet lock and the reducer hole in the snap-fit connection in a preferred embodiment of the quick-release structure of the wingtip winglet of the aircraft of the invention;

fig. 3 is a schematic view of the state of the bayonet and the reducer hole in non-clamping state in a preferred embodiment of the quick-release structure of the wingtip winglet of the aircraft of the invention;

FIG. 4 is a schematic structural view of a preferred embodiment of a quick release structure for winglets on the tips of aircraft wings according to the present invention, with the winglets and the wings separated;

FIG. 5 is an enlarged schematic view at A in FIG. 2;

fig. 6 is an enlarged schematic view at B in fig. 3.

Detailed Description

This section will describe in detail the embodiments of the present invention, preferred embodiments of the present invention are shown in the attached drawings, which are used to supplement the description of the text part of the specification with figures, so that one can intuitively and vividly understand each technical feature and the whole technical solution of the present invention, but they cannot be understood as the limitation of the protection scope of the present invention.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.

Referring to fig. 1, the present invention provides a preferred embodiment of a quick-release structure for winglets on wingtips of aircrafts, including a wing 10, wherein one end of the wing 10 can be connected to an airframe (not shown) of an aircraft, and a winglet 20 is disposed at a free end of the wing 10 away from the airframe, in this embodiment, the winglet 20 is connected to the free end of the wing 10 through two sets of quick-release connection mechanisms, which are respectively disposed at two sides of the free end of the wing 10, and of course, the number of the quick-release connection mechanisms can be set as one set, three sets or multiple sets without being limited to two sets, and can be set freely according to actual needs.

Referring to fig. 2 and 5, in order to make the structure of the quick-release structure of an aircraft wingtip winglet of the present invention simpler, in this embodiment, the quick-connection mechanism includes a connection bayonet 31 and a diameter-variable hole 32, the connection bayonet 31 includes a connection cylinder 310, one end of the connection cylinder 310 is fixedly connected with the winglet 20, and a free end of the connection cylinder 310 away from the winglet 20 is provided with a block piece 311; the reducing hole 32 is opened at the free end of the wing 10, the reducing hole 32 includes a large-diameter hole 320 through which the clamping block 311 can pass, and the side wall of the large-diameter hole 320 extends outwards and arches to form a small-diameter hole 321 which can be clamped with the clamping block 311. Of course, it is also possible that the connecting bayonet 31 is provided on the wing 10 and the reducing hole 32 is provided on the winglet 20, and the details may be determined according to actual needs.

Referring to fig. 3 and 6, when the winglet 20 is mounted on the wing 10, only the clamping block 311 on the connecting clamping pin 31 needs to apply force to the winglet 20 and push the winglet 20 to move close to the wing 10 to the large-diameter hole 320 on the reducing hole 32, the clamping block 311 passes through the large-diameter hole 320 and enables the connecting cylinder 310 to be located in the large-diameter hole 320, and then the force is applied to the winglet 20 to enable the winglet 20 to drive the connecting cylinder 310 and the clamping block 311 to move horizontally relative to the wing 10, so that the connecting cylinder 310 can be embedded into the small-diameter hole 321 of the reducing hole 32, and the clamping block 311 is clamped with the small-diameter hole 321 at this time, so that the winglet 20 is locked on the wing 10; if the winglet 20 needs to be detached from the wing 10 to realize the rapid assembly of the winglet 20 and the wing 10, only the winglet 20 needs to be pushed to move horizontally in the reverse direction relative to the wing 10, so that the connecting cylinder 310 drives the clamping block 311 to move from the small-diameter hole 321 to the large-diameter hole 320, and at the moment, only force needs to be applied to the winglet 20 to enable the winglet 20 to move away from the wing 10, so that the connecting cylinder 310 and the clamping block 311 can be separated from the large-diameter hole 320, and the rapid separation of the winglet 20 and the wing 10 is realized.

In addition, the quick connection mechanism can adopt other structures besides the structure, such as: the quick connection mechanism includes a fixing pin (not shown) fixedly disposed on the wing 10, a through hole (not shown) for the fixing pin to pass through is formed on the winglet 20, a sliding block (not shown) capable of being clamped with the fixing pin is movably mounted on a side of the winglet 20 away from the wing 10, and a clamping groove matched and clamped with the fixing pin is formed on the sliding block, so that when the winglet 20 is mounted on the wing 10, the fixing pin is only required to be aligned with the through hole on the winglet 20 and inserted into the through hole, and the winglet 20 is tightly attached to the end of the wing 10, and then the sliding block is pushed to move relative to the winglet 20 to be close to the fixing pin and clamped with the fixing pin, so that the winglet 20 is quickly locked on the wing 10; when winglet 20 was dismantled to needs, only need the reverse promotion sliding block to keep away from the fixed round pin post to remove the joint between sliding block and the fixed round pin post, can dial out the fixed round pin post from passing the hole on winglet 20 this moment, thereby pull down winglet 20 from winglet 20 fast, simple and convenient.

Referring to fig. 4, in order to facilitate adjusting the degree of tightness that the winglet 20 is locked on the wing 10, in this embodiment, preferably, the connecting cylinder 310 is a bolt, and the clamping block 311 is a nut screwed onto the bolt, so that during assembly, the connecting cylinder 310 may be fixedly disposed on the winglet 20, that is, the bolt is fixedly disposed on the winglet 20, and since the clamping block 311 is a nut screwed onto the bolt, a user may twist the nut to rotate relative to the bolt, adjust the distance between the nut and the winglet 20, and further adjust the degree of tightness when the winglet 20 is attached to the free end of the wing 10 when the nut is clamped with the diameter-changing hole 32 of the wing 10.

In addition, in order to avoid that the winglet 20 accidentally moves relative to the wing 10 under the action of external force during the flight of the aircraft, so that the clamping between the clamping block 311 and the reducing hole 32 is released, in this embodiment, a user can screw the nut to rotate relative to the bolt after the nut is clamped with the reducing hole 32, and then the nut continuously extrudes the wing 10, so that the wing 10 and the winglet 20 are locked together, and the winglet 20 is prevented from moving relative to the wing 10; if the winglet 20 needs to be detached, the nut can be unscrewed, then the winglet 20 is moved relative to the wing 10, and then the winglet 20 is detached, so that the connection between the winglet 20 and the wing 10 is firm and reliable, the detachment and the installation are convenient, and the requirements of users are better met.

Referring to fig. 6, in order to ensure that the clamping between the clamping piece 311 and the reducing hole 32 is firm and reliable, preferably, a positioning block 40 is disposed at a position adjacent to the small diameter hole 321 on the inner side wall of the free end of the wing 10, and a positioning notch 41 matching with the shape of the clamping piece 311 is disposed on the positioning block 40, because in this embodiment, the clamping piece 311 is preferably a nut, the positioning notch 41 on the positioning block 40 is a rectangular groove matching with the shape of the nut, one side of the rectangular groove is provided with an opening for the nut to enter and exit, by disposing a positioning block 40 on the inner side wall of the free end of the wing 10, the positioning notch 41 on the positioning block 40 is in clamping connection with the nut in a matching manner, so that the nut cannot rotate relative to the bolt, and further the nut cannot be taken off from the bolt, thereby ensuring that the clamping between the nut and the reducing hole 32 cannot be released, and further ensuring that the clamping between the clamping piece 311, the winglet 20 is prevented from accidentally falling out of the wing 10.

Referring to fig. 1, 2 and 5, a preferred embodiment of the present invention includes an aircraft body (not shown), and the aircraft body is provided with the above-mentioned quick-release structure of the winglet. By adopting the quick dismounting structure of the wingtip winglet of the aircraft, the assembling or disassembling speed of the winglets 20 can be increased, and the assembling production efficiency of the aircraft can be improved or the aircraft can be conveniently dismounted and maintained.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.

Claims

1. A quick-release structure for wingtips winglets of aircraft, comprising:

a wing (10);

a winglet (20), the winglet (20) being connected to a free end of the wing (10) by at least one set of quick connect mechanisms;

the quick-connect mechanism includes:

the connecting clamping pin (31), the connecting clamping pin (31) comprises a connecting cylinder (310), and a clamping block piece (311) is arranged at the free end of the connecting cylinder (310);

the reducing hole (32) comprises a large-diameter hole (320) for the clamping block piece (311) to pass through, and the side wall of the large-diameter hole (320) extends outwards and is arched to form a small-diameter hole (321) capable of being clamped with the clamping block piece (311);

one of the connecting clamping pin (31) and the reducing hole (32) is arranged on the wing (10), and the other one is arranged on the winglet (20).

2. A quick-release structure for a winglet of an aircraft wing tip, according to claim 1, wherein:

the connecting bayonet (31) is fixedly arranged on the winglet (20), and the reducing hole (32) is arranged at the free end of the wing (10);

the connecting cylinder (310) for connecting the clamping pin (31) is a bolt fixedly arranged on the winglet (20), and the clamping block piece (311) is a nut in threaded connection with the bolt.

3. A quick-release structure for a winglet of an aircraft wing according to claim 2, wherein:

a positioning block (40) is arranged at the position, adjacent to the small-diameter hole (321), of the inner side wall of the free end of the wing (10), and a positioning notch (41) matched with the shape of the block piece (311) is formed in the positioning block (40).

4. A quick-release structure for a winglet on an aircraft wing tip according to any one of claims 1 to 3, wherein:

the winglets (20) are connected with the free ends of the wings (10) through two groups of quick connecting mechanisms, and the two groups of quick connecting mechanisms are respectively arranged on the two sides of the free ends of the wings (10).

5. An aircraft, characterized in that it comprises, in a plane,

a quick-release structure for a winglet of an aircraft according to any one of claims 1 to 4, comprising an aircraft body to which the structure is applied.