WO2015032276A1

WO2015032276A1 - Fuselage butt joint structure connected to aircraft vertical fin, and aircraft comprising fuselage butt joint structure

Info

Publication number: WO2015032276A1
Application number: PCT/CN2014/084771
Authority: WO
Inventors: 卢秉贺; 吴承思; 李希岩; 宫占峰; 李萍; 罗腾腾
Original assignee: 中国商用飞机有限责任公司; 中国商用飞机有限责任公司上海飞机设计研究院
Priority date: 2013-09-03
Filing date: 2014-08-20
Publication date: 2015-03-12
Also published as: CN103434636B; CN103434636A

Abstract

A fuselage butt joint structure (10) connected to an aircraft vertical fin, the fuselage butt joint structure (10) comprising: a structural main body (20) provided with a plurality of reinforcing ribs (21); and a plurality of joints (30), the joints (30) being installed back-to-back in pairs at the front side and rear side of the structural main body (20); two ends of each joint (30) are respectively provided with reinforcing ribs (31); the reinforcing ribs (31) of the joint (30) are connected to the reinforcing ribs (21) of the structural main body (20) via fasteners; and the aircraft vertical fin is installed onto the joint via fasteners. The fuselage butt joint structure of the present invention has performance against fatigue, and is easy to maintain.

Description

Aircraft docking structure connecting aircraft tail and tail aircraft and aircraft including body docking structure

The present invention relates to the field of airframe structure design, and more particularly to a fuselage docking structure for connecting a tail of an aircraft and an aircraft including a body docking structure. Background technique

In the design of aircraft structure, we should strive to achieve the overall integrity of the structure. However, due to the needs and limitations of structural design, process, maintenance, etc., the design and process separation surfaces must be arranged between the fuselage and the vertical tail. The connection design of these parts is Become an essential key link.

The aircraft connection area is the part of the structure that is prone to damage. Therefore, a well-designed fuselage and vertical tail docking structure will improve the carrying efficiency. Structural design also needs to consider maintainability, processability and economy.

The traditional fuselage docking structure that connects the tail of the aircraft is monolithic. The most directly transported parts are most prone to damage. Once such local damage occurs, the docking structure needs to be replaced as a whole, making maintenance difficult. The overall structural process is difficult to manufacture and the product rejection rate is high. The overall structure requires a large wool size, a low utilization rate of the finished product, a high scrap rate and a low material utilization rate, resulting in poor economy. Summary of the invention

In order to solve the above problems, the present invention provides a novel combined fuselage docking structure for connecting a tail of a aircraft, which has better fatigue performance, maintainability, workability and economy.

According to an aspect of the invention, a fuselage docking structure for connecting a tail of an aircraft is provided, the body docking structure comprising:

a structural body having a plurality of reinforcing ribs;

a plurality of joints that are mounted back to back in pairs to the front side of the structural body And a rear side, each of the two ends of each joint is respectively provided with a reinforcing rib, the reinforcing rib of the joint is connected to the reinforcing rib of the structural body by a fastener, and the tail of the aircraft is mounted by a fastener to The joint.

Wherein, the fuselage docking structure comprises four joints.

Wherein, the structural body is made of an aluminum alloy material.

Wherein the joint is made of a titanium alloy material.

Wherein the front side and/or the rear side of the structural body are provided with a thickness-enhancing region, and the joint is mounted to the thickness-enhancing region.

The joint on the front side of the structural body and the joint on the rear side of the structural body are connected to each other by a fastener penetrating the structural body.

According to another aspect of the invention, an aircraft is provided, the fuselage of the aircraft comprising a fuselage docking structure according to the foregoing description.

Due to the large size of the fuselage structure connecting the tail of the aircraft, it is necessary to purchase a large-sized wool material, and the material utilization rate of the finished product after machining is less than 2%. The fuselage structure of the combined connecting aircraft is divided into a structural body and a joint, wherein the material utilization rate of the structural body is

About 3.4%, the material utilization rate of the joint is 5.8%. In combination, the material docking structure of the fuselage structure with the combined connection of the aircraft's vertical tail is improved by at least 70% compared with the traditional butt-tailed fuselage structure, which is conducive to cost saving.

According to the finite element analysis, under the same load, the stress of the fuselage butt joint structure of the new type of combined aircraft with the vertical tail is equivalent to that of the traditional fuselage butt joint structure. However, compared with the conventional docking structure with the vertical tail, the direct bearing part structure is changed into a titanium alloy joint, and the titanium alloy material has good bearing capacity and fatigue performance compared with the aluminum alloy material. Therefore, the new modular connection with the vertical tail body has a better load bearing capacity and fatigue performance.

Titanium alloy joints are attached to the structural body by fasteners such as bolts for easy replacement and reassembly. The docking portion with the vertical tail is also connected by bolts, and the bolt holes can be matched with a large gap to facilitate assembly.

The invention splits the overall structure into 5 parts, which reduces the manufacturing difficulty of the product, reduces the product scrap rate, and is beneficial to process manufacturing and cost saving. DRAWINGS

Other features and advantages of the present invention will be better understood from the following detailed description of the preferred embodiments illustrated in the <RTIgt;

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a schematic illustration of one embodiment of a fuselage docking structure for connecting a vertical tail of an aircraft in accordance with the present invention;

Figure 2 is a schematic view of the structural body of the body docking structure of Figure 1; and Figure 3 is a schematic view of the joint of the body docking structure of Figure 1.

among them:

10 fuselage butt structure

20 structural subjects

21 reinforcing bars

22 thickness enhancement zone

30 connector

31 strong mouth ribs

In the following detailed description of the preferred embodiments, reference will be made to the accompanying drawings in which The accompanying drawings illustrate, by way of example, specific embodiments These embodiments are not intended to be exhaustive of all embodiments in accordance with the invention. It is to be understood that other embodiments may be utilized and structural or logical modifications may be made without departing from the scope of the invention. Therefore, the following detailed description is not to be considered as limiting

As shown in Figure 1, the fuselage docking structure 10 for connecting the vertical tail of the aircraft is shown.

2 shows the structural body 20 of the fuselage docking structure 10 of Fig. 1, and Fig. 3 shows the joint 30 of the body docking structure 10 of Fig. 1.

Specifically, the fuselage docking structure 10 includes a structural body 20 and a plurality of joints 30. The structural body 20 is provided with a plurality of reinforcing ribs 21. Multiple joints 30 are mounted back to back in pairs The front side and the rear side of the structural body 20 are respectively provided with reinforcing ribs 31 at both ends of each joint 30, and the reinforcing ribs 31 of the joint 30 are connected to the reinforcing ribs 21 of the structural main body 20 by fasteners such as bolts. The joint 30 is thus mounted to the structural body 20, and the tail of the aircraft is mounted to the joint 30 by fasteners such as bolts. In the embodiment shown in FIG. 1, the fuselage docking structure 10 includes four joints 30.

Wherein the front side and/or the rear side of the fuselage docking structure 10 is provided with a thickness reinforcing region 22, and the joint 30 is mounted to the thickness reinforcing region 22. The joint on the front side of the structural body 20 and the joint on the rear side of the structural body 20 are interconnected by other mechanical fasteners such as bolts penetrating the structural body 20.

The fuselage docking structure 10 is vertically oriented, and the vertical tail is connected to the four joints of the fuselage docking structure 10 by fasteners such as bolts to mount the vertical tail to the fuselage structure of the aircraft.

The invention divides the conventional docking structure of the vertical tail into five parts, including the structural body and four joints. The structural body is still made of aluminum alloy, and the four joints are made of titanium alloy. The titanium alloy joint is connected to the structural body by fasteners such as bolts, and the body and the tail end abutting portion can also be realized by bolting.

Due to the large size of the fuselage structure connecting the tail of the aircraft, it is necessary to purchase large-sized wool materials, and the material utilization rate of the finished products after machining is less than 2%. The fuselage structure of the combined connection aircraft is divided into a structural body (or frame) and a joint, wherein the material utilization rate of the structural body is about 3.4%, and the material utilization rate of the joint is 5.8%. In combination, the combined use of the composite butt-finished fuselage structure improves the material utilization of the conventional butt-to-tailed fuselage structure by at least 70%, which is conducive to cost savings.

In addition, the structural body of the fuselage butt joint structure of the combined connection aircraft has a thickness-enhancing area at the joint with the joint to improve the joint strength, and the joints are respectively placed in the thickness-enhancing area of the structure, and the two back-to-back joints are fastened. Piece connection. The ends of the joint have reinforcing ribs, and the ribs at the two ends are connected with the ribs of the structural body by fasteners. Thus, a portion of the structural body acts as a corner piece, and the reinforcing ribs of the main body and the reinforcing ribs of the joint act as the outer edges of the structural body, and the new outer edge is a continuous structure, which is advantageous for transmitting loads.

After finite element analysis, under the same load, the new combined connection aircraft The stress of the butt joint structure of the fuselage is equivalent to the traditional docking structure of the fuselage connected to the tail. However, compared with the fuselage butt joint structure of the traditional connecting aircraft, the direct bearing part structure is changed into a titanium alloy joint, which has good bearing capacity and fatigue performance compared with the aluminum alloy material. Therefore, the new combined type aircraft docking structure has better bearing capacity and fatigue performance.

The invention splits the overall structure into 5 parts, which reduces the manufacturing difficulty of the product, reduces the scrap rate of the product, and is beneficial to process manufacturing and cost saving.

The technical content and technical features of the specific embodiments of the present invention have been disclosed above, but it will be understood that those skilled in the art can make various features of the above disclosure and features not explicitly shown by those skilled in the art. The group cooperates with various changes and improvements, but all fall within the scope of protection of the present invention. The description of the above embodiments is illustrative and not restrictive, and the scope of the invention is defined by the claims.

Claims

Claim

A body docking structure (10) for connecting a tail of an aircraft, wherein the body docking structure comprises:

a structural body (20) having a plurality of reinforcing ribs (21);

a plurality of joints (30) mounted to the front side and the rear side of the structural body (20) in a back-to-back manner, and reinforcing ribs are respectively provided at both ends of each joint (30) The rib (31) of the joint (30) is connected to the rib (21) of the structural body (20) by a fastener, and the tail of the aircraft is mounted to the joint by a fastener (30).

2. The fuselage docking structure (10) according to claim 1, wherein the body docking structure (10) comprises four joints (30).

3. The fuselage docking structure (10) according to claim 2, wherein the structural body (20) is made of an aluminum alloy material.

The fuselage docking structure (10) according to claim 3, characterized in that the joint (30) is made of a titanium alloy material.

The fuselage docking structure (10) according to any one of claims 1 to 4, characterized in that the front side and/or the rear side of the structural body (20) is provided with a thickness-enhancing region (22) The joint (30) is mounted to the thickness enhancement region (22).

The fuselage docking structure (10) according to any one of claims 1 to 4, characterized in that the joint of the front side of the structural body (20) and the rear side of the structural body (20) The joints are interconnected by fasteners that extend through the structural body (20).

7. An aircraft, characterized in that the fuselage of the aircraft comprises a fuselage docking structure (10) for connecting a vertical tail of an aircraft according to any one of claims 1 to 6.