CN210681121U

CN210681121U - Molded bearing opening cover of airplane

Info

Publication number: CN210681121U
Application number: CN201921697162.XU
Authority: CN
Inventors: 刘叶; 李钢; 刘蓬; 王亚妮
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2019-10-11
Filing date: 2019-10-11
Publication date: 2020-06-05
Anticipated expiration: 2029-10-11

Abstract

The application belongs to aircraft structural design field, in particular to aircraft mould pressing formula load flap includes: an outer skin; the first inner skin and the second inner skin which have the same structure are symmetrically arranged to form the inner skins and are fixedly arranged on one side surface of the outer skin through the fixing edges of the inner skins; the connecting band plate is used for fixedly connecting the first inner skin and the second inner skin; and one end of the gooseneck hinge is fixedly connected to the outer skin and one of the concave parts of the inner skin, and the other end of the gooseneck hinge is connected with a support fixed on the opening frame. The utility model provides an aircraft mould pressing formula load flap, structural style is simple, and part quantity is less than traditional combination formula flap, and flap weight ratio traditional combination formula flap is light, and flap rigidity is better, can realize quick-release function, and the flap can be opened the settlement angle, need not to lift convenient to use completely off.

Description

Molded bearing opening cover of airplane

Technical Field

The application belongs to the field of aircraft structure design, and particularly relates to an aircraft mould pressing type bearing opening cover.

Background

At present, a large-sized opening cover on an airplane body is in a form of adopting a combined opening cover, namely, a form of adding a skeleton to the opening cover is adopted, the number of common parts of the opening cover is large, and the weight is heavy.

SUMMERY OF THE UTILITY MODEL

In order to solve at least one of the technical problems, the application provides an aircraft mould pressing type bearing opening cover.

The application discloses aircraft mould pressing formula load flap includes:

an outer skin;

the first inner skin and the second inner skin are integrally molded and respectively comprise a peripheral fixing edge, a middle protruding part and a plurality of concave parts, wherein the protruding parts are positioned on the periphery of the first inner skin and the second inner skin are symmetrically arranged to form the inner skins and are respectively fixedly arranged on one side surface of the outer skin through the fixing edges;

the connecting strip plate is used for fixedly connecting the first inner skin and the second inner skin from one side of the inner skin far away from the outer skin at the joint of the first inner skin and the second inner skin;

and one end of the gooseneck hinge is fixedly connected to the inner skin and the outer skin in one of the concave parts, and the other end of the gooseneck hinge is connected with a support fixed on the mouth frame.

According to at least one embodiment of the application, the molded bearing cover of the airplane is characterized by further comprising:

one end of the strut assembly is hinged into one of the concave parts of the inner skin through a support, and the other end of the strut assembly is provided with an elbow matched with a support fixed on the mouth frame structure.

According to at least one embodiment of the present application, the outer skin is formed by bending an aluminum alloy thin plate;

the first inner skin and the second inner skin are respectively formed by integrally pressing and molding an aluminum alloy thin plate.

According to at least one embodiment of the application, the plurality of recesses are each fixedly connected to the outer skin.

According to at least one embodiment of the application, the fixing edge and the outer skin, the connecting strip plate and the first inner skin and the second inner skin, the recess and the outer skin are all connected by rivets.

The application has at least the following beneficial technical effects:

the utility model provides an aircraft mould pressing formula load flap, structural style is simple, and part quantity is less than traditional combination formula flap, and flap weight ratio traditional combination formula flap is light, and flap rigidity is better, can realize quick-release function, and the flap can be opened the settlement angle, need not to lift convenient to use completely off.

Drawings

FIG. 1 is a schematic structural diagram of a molded bearing cover of an airplane according to the present application;

FIG. 2 is a schematic structural diagram of an outer skin in a molded bearing cover of the aircraft of the present application;

FIG. 3 is a schematic view of the split inner skin of the molded bearing cover of the airplane;

fig. 4 is a schematic structural diagram of a gooseneck hinge in the molded bearing cover of the airplane.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

The molded bearing cover of the airplane is further described in detail with reference to the attached drawings 1-4.

The application discloses an aircraft mould pressing type bearing opening cover, as shown in figure 1, can include outer skin 1, inner skin 2, connecting band plate 3 and gooseneck hinge 4.

As shown in fig. 2, the outer skin 1 is preferably formed by bending an aluminum alloy thin plate.

As shown in fig. 3, the inner skin 2 includes a first inner skin 21 and a second inner skin 22 that are identical in structure; the first inner skin 21 and the second inner skin 22 are both integrally molded members, and in this embodiment, an aluminum alloy sheet is preferably molded. Further, the first inner skin 21 and the second inner skin 22 respectively include a fixing edge 201 located at the periphery, a protruding portion 202 located in the middle, and a plurality of recessed portions 203 located on the protruding portion 202, wherein the first inner skin 21 and the second inner skin 22 are symmetrically arranged to form the inner skin 2, and are respectively and fixedly arranged on one side surface of the outer skin 1 through the fixing edge 201.

The connecting strap 3 serves to fixedly connect the first inner skin 21 and the second inner skin 22 from the side of the inner skin 2 remote from the outer skin 1 at the junction of the first inner skin 21 and the second inner skin 22.

Specifically, when the inner skin 2 is molded by an aluminum alloy sheet, the inner skin is molded in two directions, a certain height is integrally molded towards the inner mold (namely, a convex part 202 is formed), and then a plurality of reinforcing pits are molded outwards (namely, concave parts 203 are formed); considering the difficulty of the processing technology, the inner skin is divided into 2 pieces, namely the first inner skin 21 and the second inner skin 22, the two pieces of the first inner skin 21 and the second inner skin 22 are connected together by the connecting band plate 3, the inner skin and the outer skin are connected together by two rows of rivets at the edge, a plurality of reinforcing sockets in the middle of the inner skin 2 and the outer skin 1 are also connected together by the rivets, and the flap has good rigidity.

As shown in fig. 4, one end of the gooseneck hinge 4 is fixedly connected to the outer skin 1 and one of the recesses 203 of the inner skin 2, and the other end is connected to a support fixed to the mouth frame. The quantity of gooseneck hinge 4 can carry out suitable selection as required, specifically, two gooseneck hinges 4 are arranged to the flap top and are linked together with the support of fixing on the mouth frame, realize the rotation of flap, and the flap border is arranged and is not pulled off the flap lock and is linked together with the mouth frame, and the flap lock that does not pull off can realize quick dismantlement and load function.

Further, the molded bearing cover of the airplane can also comprise a stay bar component 5; one end of the strut assembly 5 is hinged into one of the recesses 203 of the inner skin 2 by means of a bracket 51, and the other end is provided with a bend 52 adapted to the bracket fixed to the mouth frame structure. When the mouth cover is opened to a set angle, the mouth cover is fixed with a support fixed on the mouth frame structure through the elbow 52 of the stay bar assembly 5.

Further, the fixing modes of the fixing edge 201 and the outer skin 1, the connecting strap 3 and the first inner skin 21 and the second inner skin 22, and the fixing mode of the recessed portion 203 and the outer skin 1 may be various, and in this embodiment, the fixing modes are preferably all connected by rivets.

Further, the installation steps of the aircraft mould pressing type bearing opening cover of the application are as follows:

1) the first inner skin 21, the second inner skin 22 and the connecting band plate 3 are connected together by rivets;

2) the installed inner skin 2 and the installed outer skin 1 are connected together by rivets;

3) installing the gooseneck hinge 4 and the stay bar assembly 5 on the mouth cover;

4) the opening cover is connected with a support on the opening frame through two gooseneck hinges 4;

5) the mouth cover and the mouth frame are fixed by a non-falling mouth cover lock.

The opening step of the molded bearing opening cover of the airplane is as follows:

1) opening a one-circle non-falling cover lock;

2) after the flap is opened, the elbow 52 of the brace assembly 5 is fixed to the support on the mouth frame, and the flap is opened to a set angle.

To sum up, the aircraft mould pressing formula load flap of this application, structural style is simple, and part quantity is less than traditional combination formula flap, and flap weight ratio traditional combination formula flap is light, and flap rigidity is better, can realize quick-release function, and the flap can be opened the set angle, need not to lift completely off convenient to use.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. The utility model provides an aircraft moulding formula load-carrying flap which characterized in that includes:

an outer skin (1);

the structural outer skin comprises a first inner skin (21) and a second inner skin (22) which are identical in structure, wherein the first inner skin (21) and the second inner skin (22) are integrally molded components and respectively comprise a fixing edge (201) positioned on the periphery, a protruding portion (202) positioned in the middle and a plurality of recessed portions (203) positioned on the protruding portion (202), the first inner skin (21) and the second inner skin (22) are symmetrically arranged to form an inner skin (2) and are respectively fixedly arranged on one side face of the outer skin (1) through the fixing edges (201);

a connecting strap (3) for fixedly connecting the first inner skin (21) and the second inner skin (22) from the side of the inner skin (2) remote from the outer skin (1) at the junction of the first inner skin (21) and the second inner skin (22);

and one end of the gooseneck hinge (4) is fixedly connected to the inner skin (2) and the outer skin (1) in one of the concave parts (203), and the other end of the gooseneck hinge is connected with a support fixed on the mouth frame.

2. The aircraft molded access cover of claim 1, further comprising:

and one end of the support rod component (5) is hinged into one of the concave parts (203) of the inner skin (2) through a bracket (51), and the other end of the support rod component is provided with an elbow (52) matched with the bracket fixed on the mouth frame structure.

3. The molded bearing port cover of an airplane as claimed in claim 1, wherein the outer skin (1) is formed by bending an aluminum alloy sheet metal;

the first inner skin (21) and the second inner skin (22) are respectively formed by integrally molding an aluminum alloy thin plate.

4. The aircraft molded bearing cap according to claim 1, wherein the plurality of recesses (203) are fixedly connected with the outer skin (1), respectively.

5. The molded bearing cover for airplane as claimed in claim 4, wherein the fixing edge (201) and the outer skin (1), the connecting strap (3) and the first and second inner skins (21, 22), and the recess (203) and the outer skin (1) are all connected by rivets.