RU2452596C2 - Method of preparing joint of aircraft fuselage two sections - Google Patents

Abstract

FIELD: process engineering.

SUBSTANCE: invention relates to aircraft engineering, particularly, to assembly of aircraft fuselage. Fuselage sections are arranged so that their openings face each other. Connector with coordinate locking holes is secured to one of said sections to drill set of bores in fuselage section skin and/or said connector using drilling template and said coordinate locking holes.

EFFECT: simplified and shorter procedure.

7 cl, 1 dwg

Description

FIELD OF TECHNOLOGY

The present invention relates to a method for preparing the connection of two sections of the fuselage (cylindrical parts) of the aircraft.

BACKGROUND OF THE INVENTION

The manufacturing process of a commercial aircraft includes preparing the connection of the fuselage sections. It is known that the preparation of the connection and the connection itself are complex and quite lengthy operations, since the connection must be accurate and durable. In particular, the large length of the fuselage leads to the fact that small errors of several millimeters can lead to significant errors in the final section of the fuselage, as a result of which the flight characteristics of the aircraft can change in the most unpredictable way.

Below is a brief description of the currently existing method of preparing the connection of the two sections of the fuselage of the aircraft.

Fuselage sections with pre-installed rails for chairs and stringers are lifted by jacks, shifted and aligned relative to each other, for example along rails for chairs, or along stringers, and / or along the width of the gap between the front edges of the sections (an annular gap should have a constant width of the order of several millimeters ) until the central lines of the cylindrical sections coincide, that is, they will be on the longitudinal axis of the fuselage. Small pads are clamped on the stringers to ensure their connection and to compensate for the above errors. At first, the stringers themselves are not fixed between the last ring frame and the leading edge of one section. In this case, additional compensation of errors is possible. In addition, to compensate for manufacturing errors of one section, it is provided with a longitudinal slot. Ring supports with coordinate-fixing holes are attached to the inner side of the section, overlapping with the front edge of the other section, and are fixed, for example, with temporary rivets. The radius of the supports is equal to the radius of the corresponding part of the section.

In addition to the other connecting elements, such as the small pads mentioned, the ring supports can be fastened with additional clips, such as temporary rivets, to another cylindrical part and a drilling template using rivets for the control rivets.

The next technological operation is the drilling of guide holes for each calculated finished hole in the cladding sections and in the supports. Since material, such as chips generated during drilling, can enter the possible space between the relatively thin skin and the annular support, it is necessary to undock the sections, removing the clips. After drilling the guide holes in the casing and in the annular supports, the drilled holes can be degreased and burrs can be removed.

SUMMARY OF THE INVENTION

The aim of the invention is to provide a simplified and less lengthy method of preparing the connection of two sections of the fuselage (cylindrical parts) of the aircraft.

The goal can be achieved using the method according to the invention.

The main advantage of the invention is that guide holes should not be used for drilling, especially in the supports of the fuselage sections. Performing a drilling operation in one step is ensured by the use of high-speed drilling. The force acting in the downward direction on the section or on the support is substantially less than the force arising in standard drilling operations known in the art. Therefore, deformation of the sections / supports can be avoided.

According to a first preferred embodiment of the present invention, there is provided a method for preparing joints of two fuselage sections. The method may comprise one or all of the following steps, preferably carried out in the order indicated.

- Installing the sections with openings opposite each other and attaching a connecting device, such as a support, in which there are coordinate-fixing holes to at least one section of the fuselage and / or to the stringer element of at least one section, wherein the “attachment” includes precise alignment sections along the longitudinal axis and / or along the vertical axis of the aircraft.

- Disconnecting the fuselage sections from the connecting devices, cleaning the fuselage sections of the burrs and degreasing the sections.

- Application of sealing compound to sections, especially to connecting devices. Fixing / riveting of the fuselage sections and connecting devices in the position for drilling guide holes.

- Attaching at least one drilling template using fixtures and coordinate-fixing holes in the fuselage sections and / or in the connecting devices.

- Drilling a group of preliminary holes (4.6 mm) in the outer skin of at least one cylindrical part, using coordinate-fixing holes as guide holes.

- Finally, high-speed drilling of a group of finished holes (4.8 mm) in the outer skin of at least one fuselage section and / or in connecting devices using one drilling template, the drilling speed reaching 15000-20000 rpm, and high-speed drilling includes lubrication and countersinking of drilled holes. In general, when using high-speed drilling, pre-holes are not necessary.

DETAILED DESCRIPTION OF THE INVENTION

An exemplary embodiment of the present invention is described below in order to explain it and provide a better understanding, with reference to the accompanying drawings.

The drawing shows a schematic side view of part of the fuselage 1 with the first fuselage section 2 in front and with the second fuselage section 3. The first connecting device in the form of an annular support 4 (frame) is mounted on the leading edge 5 of section 2. Finished and guide holes in the indicated sections / device are not shown. Both sections 2, 3 contain additional connecting means in the form of stringers 6. The views in the figure are schematic and performed without observing the scale.

It must be borne in mind that the term “comprising” does not exclude the use of other elements or steps, and the designation of a part or step in the singular does not exclude the use of several such parts or steps. In addition, it is possible to use combinations of elements described in various embodiments of the invention.

Claims (7)

1. A method of preparing the connection of two sections (2, 3) of the aircraft fuselage, including installing sections (2, 3) with openings opposite each other, attaching a connecting device (4, 6), which contains coordinate-fixing holes to at least one sections (2, 3) of the fuselage and / or to the stringer element (6) of at least one section, attaching at least one template for drilling using clamps and coordinate-fixing holes in the fuselage sections and / or in the connecting device and high-speed rlenie group completed the openings in the outer casing of the at least one fuselage section and / or in the connecting apparatus using the drilling template. 2. The method according to claim 1, in which high-speed drilling of a group of finished holes is carried out without drilling guide holes. 3. The method according to claim 1, further comprising degreasing the fuselage sections (2, 3) and deburring the fuselage sections (2, 3). 4. The method according to claim 1, further comprising applying the sealing compound to the sections, especially to the connecting device (4) and fixing and riveting the sections (2, 3) of the fuselage and the connecting device. 5. The method according to claim 1, in which high-speed drilling is performed with a rotation speed of up to 15000-20000 rpm 6. The method according to claim 1, in which when high-speed drilling carry out the lubrication of drilled holes. 7. The method according to claim 1, in which high-speed drilling includes countersinking drilled holes.