阅读说明：本技术 一种飞机蒙皮连接组件 (Aircraft skin coupling assembling ) 是由 曹莹 卢学峰 杜金柱 郭子铭 于 2021-05-27 设计创作，主要内容包括：本申请一种飞机蒙皮连接组件,包括：螺栓,其包括具有外螺纹的螺栓本体和位于所述螺栓本体端部的螺栓端头；固定螺母,其具有前端部、后端部和介于前端部与后端部之间延伸的多个弹性部,所述后端部具有与所述螺栓本体配合的内螺纹；其中,当螺栓自飞机蒙皮一侧穿过后并与飞机蒙皮另一侧的固定硫螺栓配合后,通过旋转螺栓能够使得固定螺母的后端部能够沿着轴向方向移动,从而使所述弹性部变形而压紧所述飞机蒙皮；其中,所述固定螺母的弹性部内侧具有轴向延伸且固定在前端部的支撑杆和固定在后端部的触头,当所述弹性部压紧所述飞机蒙皮时,支撑杆和触头配合形成支撑结构。本申请的飞机蒙皮连接组件能够提高其结构强度,满足大载荷使用要求。(The application provides an aircraft skin coupling assembling includes: a bolt including a bolt body having an external thread and a bolt head at an end of the bolt body; a fixing nut having a front end portion, a rear end portion, and a plurality of elastic portions extending between the front end portion and the rear end portion, the rear end portion having an internal thread that is fitted with the bolt body; after the bolt passes through one side of the aircraft skin and is matched with the fixed sulfur bolt on the other side of the aircraft skin, the rear end part of the fixed nut can move along the axial direction by rotating the bolt, so that the elastic part is deformed to press the aircraft skin; the inner side of the elastic part of the fixing nut is provided with a support rod which axially extends and is fixed at the front end part and a contact which is fixed at the rear end part, and when the elastic part presses the aircraft skin, the support rod and the contact are matched to form a support structure. The aircraft skin connecting assembly can improve the structural strength and meet the use requirement of large load.)

1. An aircraft skin connection assembly, comprising:

a bolt (1) comprising a bolt body (11) having an external thread and a bolt head (12) at the end of the bolt body (11);

a fixing nut (2), the fixing nut (2) having a front end portion (21), a rear end portion (23), and a plurality of elastic portions (22) extending between the front end portion (21) and the rear end portion (22), the rear end portion (23) having an internal thread that is fitted with the bolt body (11);

wherein, after the bolt (1) passes through one side of the aircraft skin and is matched with the fixed sulfur bolt (2) on the other side of the aircraft skin, the rear end part (23) of the fixed nut (2) can move along the axial direction by rotating the bolt (1), so that the elastic part (22) is deformed to press the aircraft skin;

the inner side of the elastic part (2) of the fixing nut (2) is provided with a support rod (24) which extends axially and is fixed at the front end part (21) and a contact (25) which is fixed at the rear end part, and when the elastic part (22) presses the aircraft skin, the support rod (24) and the contact (25) are matched to form a support structure.

2. The aircraft skin connection assembly of claim 1, characterized in that the bolt (1) and/or the fixing nut (2) are made of a titanium alloy material.

3. The aircraft skin connection assembly of claim 1, characterized in that the bolt end (13) of the bolt body (11) remote from the bolt head (12) is tapered.

4. An aircraft skin connection assembly according to claim 3, wherein the bolt head (12) is of countersunk form, the nose portion (21) having a tapered chamfer of predetermined depth therein, the tapered chamfer providing the end face of the bolt (1) to be flush with the nose portion (21).

5. The aircraft skin connection assembly of claim 1, characterized in that the width of the nose portion (21) is determined as a function of the thickness of the aircraft skin (31, 32).

6. The aircraft skin connection assembly of claim 1, characterized in that the bolt head (11) has a straight or cross-shaped groove.

7. The aircraft skinning connection assembly of claim 1, characterized in that the outer end face of the nose portion (21) has at least two stop protrusions (26), the stop protrusions (26) being circumferentially equispaced.

8. The aircraft skin connection assembly of claim 1, characterized in that the number of spring portions (23) is plural, with gaps between adjacent spring portions (23).

9. The aircraft skinning assembly of claim 8, wherein a plurality of the resilient portions (23) are circumferentially equispaced.

10. An aircraft skin connection assembly, comprising:

a bolt (1) comprising a bolt body (11) having an external thread and a bolt head (12) at the end of the bolt body (11);

a fixing nut (2), the fixing nut (2) having a front end portion (21), a rear end portion (23), and a plurality of elastic portions (22) extending between the front end portion (21) and the rear end portion (22), the rear end portion (23) having an internal thread that is fitted with the bolt body (11);

wherein, after the bolt (1) passes through one side of the aircraft skin and is matched with the fixed sulfur bolt (2) on the other side of the aircraft skin, the rear end part (23) of the fixed nut (2) can move along the axial direction by rotating the bolt (1), so that the elastic part (22) is deformed to press the aircraft skin;

wherein the fixing nut (2) has, inside the spring part (2), a support rod (24) which extends axially and is fixed to the front end (21) or the rear end, the support rod (24) being able to form a support structure when the spring part (22) presses against the aircraft skin (31, 32).

Technical Field

The application belongs to the technical field of aircraft structures, in particular to an aircraft skin connecting assembly.

Background

The mounting connection of the aircraft skin structure may be directly related to the safety of the aircraft in flight. In the installation and maintenance of the aircraft skin, the situation that the skin needs to be locally installed and connected but no reserved hole is reserved or no embedded nut is arranged at the original installation position is often encountered, so that a lot of troubles are brought to the installation and maintenance. This time requires the destruction of the surrounding structure to complete the local connection, which is both time consuming and material consuming.

In order to avoid unnecessary work, reduce repetitive work, and consider the problems of production, manufacture, maintenance cycle, etc., a connection structure is required to meet the above-mentioned installation technical requirements.

Disclosure of Invention

It is an object of the present application to provide an aircraft skin connection assembly that addresses or mitigates at least one of the problems of the background art.

In a first aspect of the present application, there is provided an aircraft skinning connection assembly, comprising:

the bolt comprises a bolt body with external threads and a bolt end head positioned at the end part of the bolt body;

a fixing nut having a front end portion, a rear end portion, and a plurality of elastic portions extending between the front end portion and the rear end portion, the rear end portion having an internal thread that is fitted with the bolt body;

after the bolt passes through one side of the aircraft skin and is matched with the fixed sulfur bolt on the other side of the aircraft skin, the rear end part of the fixed nut can move along the axial direction by rotating the bolt, so that the elastic part is deformed to press the aircraft skin;

the inner side of the elastic part of the fixing nut is provided with a support rod which axially extends and is fixed at the front end part and a contact which is fixed at the rear end part, and when the elastic part presses the aircraft skin, the support rod and the contact are matched to form a support structure.

Further, the bolt and/or the fixing nut are made of titanium alloy materials.

Furthermore, the tail end of the bolt body, which is far away from the bolt end, is conical.

In the above embodiment, the tapered chamfer of a predetermined depth is provided in the tip portion, and the tapered chamfer makes the end face of the bolt flush with the tip portion.

Further, the width of the nose portion is determined according to the thickness of the aircraft skin.

Furthermore, a straight or cross groove is formed in the end of the bolt.

Furthermore, the outer end face of the front end portion is provided with at least two limiting protrusions which are evenly distributed in the circumferential direction.

Further, the number of the elastic parts is multiple, and a gap is formed between every two adjacent elastic parts.

In the above embodiment, the plurality of elastic portions are evenly distributed in the circumferential direction.

In another aspect of the present application, there is provided an aircraft skinning connection assembly, comprising:

the bolt comprises a bolt body with external threads and a bolt end head positioned at the end part of the bolt body;

a fixing nut having a front end portion, a rear end portion, and a plurality of elastic portions extending between the front end portion and the rear end portion, the rear end portion having an internal thread that is fitted with the bolt body;

after the bolt passes through one side of the aircraft skin and is matched with the fixed sulfur bolt on the other side of the aircraft skin, the rear end part of the fixed nut can move along the axial direction by rotating the bolt, so that the elastic part is deformed to press the aircraft skin;

wherein the fixing nut has a support rod extending axially inside the spring part and fixed to the front end or the rear end, the support rod being able to form a support structure when the spring part presses against the aircraft skin.

The application provides a connection aircraft organism skin structure that aircraft skin coupling assembling can be quick, satisfy the required precision of installation, adopt this coupling assembling can avoid the work of other structures of dismouting in order to install local structure, unsafe factor in the installation has been avoided, including field work personnel safety, equipment safety, and can satisfy different models, not unidimensional organism skin rather than the connection of inner structure, also can be applied to the connection of other structures of hatch door, the field installation is simple, installation and maintenance cycle can be shortened, avoid unnecessary work, improve the installation accuracy, practice thrift cost of maintenance.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

Fig. 1 is a schematic view of a bolt structure according to the present application.

Fig. 2 is a schematic structural view of the fixing bolt of the present application.

Fig. 3 is a sectional view taken along the direction a-a in fig. 2.

Fig. 4 is a schematic view illustrating an installation state of the connecting assembly of the present application.

Fig. 5 is a schematic view illustrating a motion process of a connecting member according to an embodiment of the present application.

Fig. 6 is a schematic view illustrating a motion process of a connecting assembly according to another embodiment of the present application.

Fig. 7 is a schematic view of the connection assembly of the present application in a state of being connected to a skin.

Reference numerals:

1-bolt, 11-bolt head, 12-bolt body, 13-bolt end

2-fixing bolt, 21-front end, 22-elastic part, 23-rear end, 24-support rod, 25-contact and 26-limit projection

31-first skin, 32-second skin

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.

The invention provides an aircraft skin connecting assembly, which aims to achieve the aims of simple later-stage installation and meeting the requirement of installing aircraft skins.

As shown in fig. 1 to 7, the aircraft skin connection assembly provided by the present application mainly includes a bolt 1 and a fixing nut 2, the bolt 1 includes a bolt body 11 having an external thread and a bolt head 12 at an end of the bolt body 11, the fixing nut 2 has a front end portion 21, a rear end portion 23, and a plurality of elastic portions 22 extending between the front end portion 21 and the rear end portion 22, and the rear end portion 23 has an internal thread that is fitted with the external thread on the bolt body 11.

After the bolt 1 has been passed through the first skin 31 and the second skin 32 of the aircraft and has been engaged with the fixing nut 2 on the right, the bolt 1 can be rotated to move the rear end 23 of the fixing nut 2 in the axial direction on the bolt body 11, so that the elastic portion 22 is deformed and presses against the aircraft skin, so that the first skin 31 and the second skin 32 are fastened together.

Wherein, the inner side of the elastic part 2 of the fixing nut 2 is provided with a support rod 24 which extends axially and is fixed at the front end part 21 and a contact 25 which is fixed at the rear end part, and when the elastic part 22 presses the first skin 31 and the second skin 32 of the airplane, the support rod 24 and the contact 25 are connected together in a matching way so as to form a support structure.

Fixing nut 2 in this application can be selected according to actual mounted position's space and intensity requirement on the whole in diameter size, length dimension and material, and the diameter of bolt 1, the size of length and screw thread can be selected according to the covering of different thickness, should be simultaneously with fixing nut 2 looks adaptation, and its material can be selected according to actual intensity requirement in order to satisfy the installation intensity problem.

In some embodiments of the above-mentioned connecting assembly, for example, both the bolt 1 and the fixing nut 2 may be made of titanium alloy material, or only the bolt 1 or the fixing nut 2 may be made of titanium alloy material, but in a preferred embodiment, the bolt 1 is made of steel material and the fixing nut 2 is made of titanium alloy material, so that the elastic portion 22 has better elasticity and is stronger after being fixedly connected by locking.

In the application, since the front end 21 of the fixing bolt 2 mainly serves to be matched with the skin, the front end 21 of the fixing nut 2 is in interference fit with a mounting hole arranged on the aircraft skin, and the width of the front end 21 can be determined according to the thickness of the aircraft skin.

In addition, the left end of the front end portion 21 is provided with a stopper protrusion 26, and the stopper protrusion 26 can prevent the fixing nut 2 from rotating when it is installed. In some preferred embodiments, the number of the limiting protrusions 26 may be two or more, and may be uniformly distributed in the circumferential direction. For example, in the embodiment provided in the drawings of the present application, the number of the stopper projections 26 is 2.

As shown in fig. 1, the bolt end 13 of the bolt body 11 away from the bolt head 12 is tapered to prevent jamming during the process of inserting the bolt 1 into the fixing nut 2.

As shown in fig. 4, the bolt head 12 is preferably in the form of a countersunk screw, while the front end 21 may be provided therein with a conical chamfer of a predetermined depth, which keeps the end face of the bolt head 11 of the bolt 1 flush with the front end 21 of the fixing bolt 2, i.e. flush with the skin plane, thereby improving the aircraft stealth performance while increasing the service load.

In this application, can be provided with a word or cross recess on the bolt end 11, make things convenient for control bolt 1 to rotate.

In the present application, the number of the elastic portions 23 on the fixing bolt 2 is plural, and a gap is provided between the adjacent elastic portions 23. Further, the plurality of elastic portions 23 are evenly distributed in the circumferential direction. For example, in the embodiment provided in the figures, the number of the elastic portions 23 is 4.

In the preferred embodiment of the present application, the bolt 1 and the fixing nut 2 in the connecting assembly can be made into a single body, so as to facilitate installation and use.

It should be noted that, in the above embodiment, the support rod 24 and the contact 25 provided inside the elastic part 2 of the fixing nut 2 also form a support structure in other forms, for example, in another embodiment, the support rod 24 is provided on the left end part 21 of the fixing nut 2, but the contact 25 is not provided on the right end part 23, or the support rod 24 is provided on the left end part 21 of the fixing nut 2, but a groove is provided on the right end part 23, so that when the bolt 1 is rotated, the support rod 24 on the left end part 21 can still form a support structure with the right end part 23, thereby improving the overall strength of the connecting assembly.

The application provides a connection aircraft organism skin structure that aircraft skin coupling assembling can be quick, satisfy the required precision of installation, adopt this coupling assembling can avoid the work of other structures of dismouting in order to install local structure, unsafe factor in the installation has been avoided, including field work personnel safety, equipment safety, and can satisfy different models, not unidimensional organism skin rather than the connection of inner structure, also can be applied to the connection of other structures of hatch door, the field installation is simple, installation and maintenance cycle can be shortened, avoid unnecessary work, improve the installation accuracy, practice thrift cost of maintenance.

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.