FR3114574A1 - Interface element for connecting two aircraft fuselage sections with a reduced number of parts. - Google Patents

Abstract

- Connection interface element to connect two aircraft fuselage sections with a reduced number of parts. - The element at least one elongated strip (5) having a curved shape adapted to at least partially cover a circumferential connection (10) of the two sections and a plurality of modules (7) having a portion intended to be fixed to one of the two sections and a portion intended to be fixed to the other section. The spacing (8) between the modules (7) is intended to accommodate respectively the ends of the stiffeners fixed in the fuselage of the aircraft. The connection interface element (1) makes it possible to reduce the number of spare parts usually required to connect two fuselage sections, which makes it possible to reduce the connection time of the two sections. Figure for the abstract: Fig. 1

Description

Interface element for connecting two aircraft fuselage sections with a reduced number of parts.

The present invention relates to the field of aircraft fuselage assembly. In particular, it relates to an element of a connection interface, the connection interface being intended to form a connection between two fuselage sections. The present invention also relates to a method for connecting two fuselage sections using the connection interface.

STATE OF THE ART

For practical reasons, such as reasons of transport, manufacturing capacities or supply of material, an aircraft fuselage is divided into sections. Each section is provided with stiffeners parallel to the longitudinal axis of the aircraft. In order to assemble these sections, there are orbital joints. These orbital joints must be able to support fuselage loads such as tensile, compressive or shear loads. Assembling these orbital joints with the sections of the fuselage requires hundreds of parts such as buttstraps, fishplates to couple the stiffeners, shims and hundreds of fasteners.

This large number of parts therefore leads to long and costly fuselage assembly times.

The object of the present invention is to overcome this drawback by proposing an orbital joint comprising a reduced number of parts.

To this end, the invention relates to a connection interface element intended to form a circumferential connection between a connection end of a first fuselage section of an aircraft and a connection end of a second fuselage section of the aircraft aligned along a longitudinal axis of the aircraft, the first section and the second section each being provided with a skin having an internal surface on which are fixed stiffeners parallel to the longitudinal axis of the aircraft, each of stiffeners of the first section and of the second section having an end leading respectively to the connection end of the first section and to the connection end of the second section.

According to the invention, the method comprises at least:

• a strip elongated in a circumferential direction and having a curved shape adapted to at least partially cover the circumferential connection straddling the internal surface of the skin of the first section and the internal surface of the skin of the second section, a first longitudinal part the strip being intended to cover the internal surface of the skin at the connection end of the first section and a second longitudinal part of the strip being intended to cover the internal surface of the skin at the connection end of the second section,
• a plurality of modules, each of the modules being level with the strip extending on either side of the strip, the modules being distributed and spaced from one another by a spacing, the modules having a first portion intended to be fixed on the internal surface of the skin at the connection end of the first section and a second portion intended to be fixed on the internal surface of the skin at the connection end of the second section, the spacing being intended to accommodate respectively the end of each of the stiffeners.

Thus, thanks to the connection interface element, it is possible to form an orbital joint with a very reduced number of spare parts. The strip plays the role of joint cover and the modules play the role of splints and wedges in separate parts.

Advantageously, the first longitudinal part of the strip is intended to be fixed on the internal surface of the skin of the first section, the second longitudinal part of the strip being intended to be fixed on the internal surface of the skin of the second section.

In addition, each of the modules has a first splint and a second splint extending on either side of the strip, the first splint and the second splint being parallel to each other and perpendicular to the circumferential direction, each of the splints having a first part intended to be fixed on the internal surface of the skin at the connection end of the first section and a second part intended to be fixed on the internal surface of the skin at the connection end of the second section.

In addition, each of the splints has a shape having an axis of symmetry coinciding with the circumferential direction.

Furthermore, each of the modules has two edges at its two opposite edges perpendicular to the circumferential direction, the two edges each forming a wall perpendicular to the circumferential direction

The invention also relates to a connection interface.

According to the invention, the connection interface comprises a set of at least two connection interface elements as described above, the connection interface elements being fixed with each other by aligning the circumferential direction of each of the connection interface elements until the bands of all the connection interface elements are arranged to be able to completely cover the circumferential connection.

The invention also relates to an aircraft fuselage comprising at least one connection interface as described above making the connection between at least two sections of the fuselage.

The invention also relates to an aircraft, in particular a transport aircraft, comprising at least one fuselage as described above.

The invention also relates to a connection method between a connection end of a first and a second fuselage section as specified above,

According to the invention, the method comprises at least one step of fixing the connection interface which comprises the following sub-steps:

• a first fixing sub-step comprising fixing the first portion of each of the modules to the internal surface of the skin at the connection end of the first section so that the ends of the stiffeners of the first section are housed in the spaces between the modules of the connection interface element,
• a second fixing sub-step comprising fixing the second portion of each of the modules to the internal surface of the skin at the connection end of the second section so that the ends of the stiffeners of the second section are housed in the spaces between modules.

According to a first embodiment, the first fixing sub-step also comprises the fixing of the first longitudinal part of the band on the internal surface of the skin at the connection end of the first section. The second fixing sub-step also comprises the fixing of the second longitudinal part of the band on the internal surface of the skin at the connection end of the second section.

According to a second embodiment, the method further comprises a first positioning step which precedes the first fixing sub-step, the first positioning step comprising the positioning of the connection interface element so that the spacings between the modules can accommodate the ends of the stiffeners of the first section. The method also comprises a second positioning step which follows the first fixing sub-step and which precedes the second fixing sub-step, the second positioning step including the positioning of the second section so that the ends of the stiffeners of the second section can be accommodated in the spaces between the modules.

BRIEF DESCRIPTION OF FIGURES

The invention, with its characteristics and advantages, will emerge more clearly on reading the description made with reference to the appended drawings in which:

FIG. 1 represents a perspective view of a connection interface element.

Figure 2 shows a perspective view of a connection interface comprising a plurality of connection interface elements.

FIG. 3 schematically represents a perspective view of two fuselage sections to be assembled by the connection interface.

FIG. 4a schematically represents the steps of a method for connecting a first section to a second fuselage section according to a first embodiment.

FIG. 4b schematically represents the steps of a method for connecting a first section to a second fuselage section according to a second embodiment.

FIG. 5 represents a perspective view of an embodiment of two splints of two adjacent modules of a connection interface element connecting two fuselage sections.

FIG. 6 represents a perspective view of another embodiment of two splints of two adjacent modules of a connection interface element connecting two fuselage sections.

FIG. 7 represents a profile view of an aircraft whose fuselage comprises sections connected using a connection interface.

DETAILED DESCRIPTION

An AC aircraft fuselage F, in particular of a transport aircraft, generally comprises at least one aerodynamic skin 2 as well as stiffeners 3 which extend longitudinally and which are fixed to the internal surface 6 of the skin 2.

The fuselage F may comprise at least two sections T1 and T2 connected together by a connection interface 100 composed of connection interface elements 1 as shown in FIGS. 1 and 2. The connection interface 100 is thus intended to form a circumferential connection 10 (FIG. 7) between a connection end C1 of a section T1 of fuselage F of the aircraft AC and a connection end C2 of a section T2 of fuselage F of the aircraft AC (FIG. 3 ). The two sections T1 and T2 are aligned along the longitudinal axis L1 of the aircraft AC to be connected.

The section T1 and the section T2 are each provided with a skin 2 having an internal surface 6 on which the stiffeners 3 are fixed. The stiffeners 3 are fixed parallel to the longitudinal axis L1 of the aircraft AC. Each of the stiffeners 3 of the section T1 and of the section T2 has an end 4 leading respectively to the connection end C1 of the section T1 and to the connection end C2 of the section T2.

In a non-limiting way, each of the stiffeners 3 of the section T1 can be configured to be aligned with each of the stiffeners 3 of the section T2 parallel to the longitudinal axis L1 of the aircraft AC. Thus, a stiffener 3 of section T1 may be intended to be aligned with a stiffener 3 of section T2.

The connection interface element 1 comprises at least one strip 5 and a plurality of modules 7. Each of the modules 7 extends on either side of the strip 5.

Strip 5 is elongated in a circumferential direction L2. The strip 5 has an axis of symmetry, parallel to the circumferential direction L2, which separates the strip 5 into a first longitudinal part and a second longitudinal part. The circumferential direction L2 is included in a plane which is intended to be perpendicular to the longitudinal axis L1 of the aircraft AC when the sections T1 and T2 are connected using the connection interface 100.

The strip 5 also has a curved shape adapted to cover at least part of the circumferential connection 10 straddling the internal surface 6 of the skin 2 of the section T1 and the internal surface 6 of the skin 2 of the section T2.

A first longitudinal part of the strip 5 is intended to cover both the internal surface 6 of the skin 2 at the connection end C1 of the section T1. A second longitudinal part of the strip 5 is intended to cover the internal surface 6 of the skin 2 at the connection end C2 of the section T2. Thus, the strip 5 makes it possible to play the role of the joint cover.

The modules 7 of the plurality of modules 7 are distributed and spaced from each other by a spacing 8. The strip 5 binds the neighboring modules 7 two by two at the level of each spacing 8.

The modules 7 are advantageously level with the strip 5 to form the same continuous surface which can be joined against the internal surface 6 of the skin 2.

According to one embodiment, the modules 7 and the strip 5 are in one piece.

According to another embodiment, the modules 7 are attached to the strip 5.

The modules 7 have a portion 91 intended to be fixed on the internal surface 6 of the skin 2 at the connection end C1 of the section T1 and a portion 92 intended to be fixed on the internal surface 6 of the skin 2 at the connection end C2 of section T2. Portion 91 can correspond to one half of a module 7 and portion 92 can correspond to the other half of module 7.

The spacing 8 between the modules is intended to house the end 4 of each of the stiffeners 3 respectively.

The distribution of the modules 7 and the spacings 8 between the modules 7 depend on the distribution of the stiffeners 3 fixed on the internal surface 6 of the skin 2 of the fuselage F. The distribution of the stiffeners 3 generally depends on the loads exerted on the fuselage F. Thus , the zones of the fuselage F on which significant loads are exerted can present a tighter distribution of the stiffeners than the zones on which the loads are less significant. Furthermore, the fuselage zones F on which the windows of the aircraft AC are fixed do not have stiffeners 3. Thus, the modules 7 are absent in these fuselage zones F. FIG. 2 shows two zones 14 without a module 7. These zones 14 correspond to zones without stiffeners in order to be able to show portholes.

In a non-limiting manner, the length d of the modules 7 in the direction perpendicular to the circumferential direction L2 depends on a minimum overlap between the stop of the stiffener 3 and the walls 131 and 132 (described below) which also depends on the loads exerted on the fuselage F of the aircraft AC. The width ℓ of the strip 5 is dependent on the minimum number of fasteners required in the spacing 8 according to the loads exerted on the fuselage.

Advantageously, the modules 7 comprise a splint 101 and a splint 102 extending on either side of the strip 5. The modules 7 can also comprise a central part 103 (partially represented in FIGS. 5 and 6) linking the two splints 101 and 102. The splint 101 and the splint 102 are parallel to each other and perpendicular to the circumferential direction L2. The splints 101 and 102 have an elongated shape in a direction perpendicular to the circumferential direction L2.

Each of the splints 101, 102 has a part 111 intended to be fixed on the internal surface 6 of the skin 2 at the connection end C1 of the section T1 and a part 112 intended to be fixed on the internal surface 6 of the skin 2 at the connection end C2 of the second section T2. Thus, the part 111 of the splint 101 and the part 111 of the splint 102 form the portion 91 of the module 7 intended to be fixed on the internal surface 6 of the skin 2 at the connection end C1 of the section T1. the part 112 of the splint 101 and the part 112 of the splint 102 form the portion 92 of the module 7 intended to be fixed on the internal surface 6 of the skin 2 at the connection end C2 of the section T2.

In particular, each of the splints 101, 102 may have a shape having an axis of symmetry S coinciding with the circumferential direction L2.

The modules 7 can thus have an H shape. The sides 101 and 102 correspond to the vertical bars of the H. The central part 103 linking the sides 101 and 102 corresponds to the horizontal bar of the H. The H shape of the modules 7 makes it possible to reduce the mass of connection interface element 1.

Furthermore, each of the modules 7 has two edges with two opposite edges 121 and 122 perpendicular to the circumferential direction L2. The two edges are perpendicular to the circumferential direction L2. The two edges each form a wall 131 and 132 perpendicular to the circumferential direction L2.

These walls 131 and 132 make it possible to ensure the rigidity provided by the stiffeners 3 at the level of the circumferential connection 10 where the stiffeners 3 do not exist.

Advantageously, the connection interface element 1 comprises a fillet 142 or a fillet between the portions 91 and 92 of each of the modules 7 and the wall 131, 132 and a fillet 141 or a fillet between strip 5 and wall 131, 132.

Figure 5 and Figure 6 illustrate two embodiments of the fishplates 101 and 102. These figures 5 and 6 represent a fishplate 101 of a module 7 and a fishplate 102 of an adjacent module 7. One end 4 of stiffener 3 of each section T1 and T2 is housed in the spacing 8 between the fishplates 101 and 102 of the adjacent modules 7.

In FIG. 5, the splints 101 and 102 have a constant width Le over the major part of their length. This width Le gradually decreases from the part whose width Le is constant to the ends 111, 112 of the fishplates 101 and 102.

In FIG. 6, the splints 101 and 102 have a width Le which progressively decreases with a maximum width at the level of the axis of symmetry S. The progressive reduction in the width Le can be more or less rapid as we are approaching the ends 111 and 112. Thus, in FIG. 6, the progressive reduction at the ends 111 and 112 is faster than the progressive reduction in the vicinity of the axis of symmetry S.

The connection interface elements 1 thus make it possible to form a connection interface 100 (FIG. 2), otherwise called an “orbital joint”.

The connection interface 100 comprises a set of at least two connection interface elements 1. The connection interface elements 1 are fixed with each other by aligning the circumferential directions L2 of each of the elements of connection interface 1 until the strips 5 of all the connection interface elements 1 are arranged to be able to completely cover the circumferential connection 10.

According to one embodiment, the connection interface elements 1 are fixed to each other end to end.

According to another embodiment, the connection interface elements 1 are fixed to each other by overlapping.

The modules 7 and the strip 5 can be pierced with holes 15 allowing the passage of fastening devices, such as rivets, allowing the fastening of the connection interface 100 on the internal surfaces 6 of the skin 2 of the sections T1 and T2 (figures 5 and 6).

Figure 4 schematically illustrates the connection process between a connection end C1 of a section T1 and a connection end of a section T2 of fuselage F.

The method comprises at least one step E1 of fixing the connection interface 1 which comprises the following sub-steps:

• a fixing sub-step E1A comprising the fixing of the portion 91 of each of the modules 7 on the internal surface 6 of the skin 2 at the connection end C1 of the section T1 so that the ends 4 of the stiffeners 3 of the section T1 are housed in the spaces 8 between the modules 7 of the connection interface element 1,
• a fixing sub-step E1B comprising the fixing of the portion 92 of each of the modules 7 on the internal surface 6 of the skin 2 at the connection end C2 of the section T2 so that the ends 4 of the stiffeners 3 of the section T2 are housed in the spaces 8 between the modules 7.

Advantageously, the fixing sub-step E1A also comprises the fixing of the first longitudinal part of the strip 5 on the internal surface 6 of the skin 2 at the connection end C1 of the section T1. In addition, the fixing sub-step E1B also includes the fixing of the second longitudinal part of the strip 5 on the internal surface 6 of the skin 2 at the connection end C1 of the section T2.

According to a first embodiment, the method comprises an alignment step E0 which precedes the step E1 of fixing the connection element 1. The alignment step E0 comprises the alignment of the section T1 with the section T2 along the longitudinal axis L1 of the aircraft AC.

According to a second embodiment, the method comprises a step E01 of positioning which precedes the sub-step E1A of fixing. The positioning step E01 includes the positioning of the connection interface element 1 so that the spacings 8 between the modules 7 can accommodate the ends 4 of the stiffeners 3 of the section T1. The method further comprises a positioning step E02 which follows the fixing sub-step E1A and which precedes the fixing sub-step E1B. The positioning step E02 includes the positioning of the section T2 so that the ends 4 of the stiffeners 3 of the section T2 can be accommodated in the spacings 8 between the modules 7.

Claims (14)

Connection interface element intended to form a circumferential connection (10) between a connection end (C1) of a first section (T1) of the fuselage (F) of an aircraft (AC) and a connection end (C2 ) of a second section (T2) of fuselage (F) of the aircraft (AC) aligned along a longitudinal axis (L1) of the aircraft (AC), the first section (T1) and the second section (T2) being each provided with a skin (2) having an internal surface (6) on which are fixed stiffeners (3) parallel to the longitudinal axis (L1) of the aircraft (AC), each of the stiffeners (3) of the first section (T1) and of the second section (T2) having an end (4) leading respectively to the connection end (C1) of the first section (T1) and to the connection end (C2) of the second section (T2) );
characterized in that it comprises at least:

• a strip (5) elongated in a circumferential direction (L2) and having a curved shape adapted to at least partially cover the circumferential connection (10) straddling the internal surface (6) of the skin (2) of the first section ( T1) and on the internal surface (6) of the skin (2) of the second section (T2), a first longitudinal part of the strip (5) being intended to cover the internal surface (6) of the skin (2) at the connection end (C1) of the first section (T1) and a second longitudinal part of the strip (5) being intended to cover the internal surface (6) of the skin (2) at the connection end (C2) of the second section (T2),
• a plurality of modules (7), each of the modules (7) being level with the strip (5) and extending on either side of the strip (5), the modules (7) being distributed and spaced between them by a spacing (8), the modules (7) having a first portion (91) intended to be fixed on the internal surface (6) of the skin (2) at the connection end (C1) of the first section ( T1) and a second portion (92) intended to be fixed on the internal surface (6) of the skin (2) at the connection end (C2) of the second section (T2), the spacing (8) being intended to respectively house the end (4) of each of the stiffeners (3).

Element according to claim 1,
characterized in that the first longitudinal part of the strip (5) is intended to be fixed on the internal surface (6) of the skin (2) of the first section (T1), the second longitudinal part of the strip (5) being intended to be fixed on the internal surface (6) of the skin (2) of the second section (T2). Element according to any one of claims 1 and 2,
characterized in that each of the modules (7) has a first splint (101) and a second splint (102) extending on either side of the strip (5), the first splint (101) and the second splint (102) being parallel to each other and perpendicular to the circumferential direction (L2), each of the splints (101, 102) having a first part (111) intended to be fixed on the internal surface (6) of the skin (2) at the connection end (C1) of the first section (T1) and a second part (112) intended to be fixed on the internal surface (6) of the skin (2) at the connection end (C2) of the second section (T2). Element according to any one of Claims 1 to 3,
characterized in that each of the fishplates (101, 102) has a shape presenting an axis of symmetry (S) coinciding with the circumferential direction (L2). Element according to any one of Claims 1 to 4,
characterized in that each of the modules (7) has two edges at its two opposite edges (121, 122) perpendicular to the circumferential direction (L2), the two edges each forming a wall (131, 132) perpendicular to the circumferential direction ( L2). Element according to any one of Claims 1 to 5,
characterized in that the modules (7) and the strip (5) are in one piece. Element according to any one of Claims 1 to 5,
characterized in that the modules (7) are attached to the strip (5). login interface,
characterized in that it comprises a set of at least two connection interface elements (1) according to any one of claims 1 to 7, the connection interface elements (1) being fixed one with the other by aligning the circumferential direction (L2) of each of the connection interface elements (1) until the strips (5) of the set of connection interface elements (1) are arranged to able to completely cover the circumferential connection (10). aircraft fuselage,
characterized in that it comprises at least one connection interface according to claim 8 making the connection between at least two sections (T1, T2) of the fuselage (F). Aircraft,
characterized in that it comprises a fuselage (F) according to claim 9. Connection method between a connection end of a first and a second fuselage section according to claim 9,
characterized in that it comprises at least one step (E1) of fixing the connection interface (1) which comprises the following sub-steps:

• a first attachment sub-step (E1A) comprising the attachment of the first portion (91) of each of the modules (7) to the internal surface (6) of the skin (2) at the connection end (C1) of the first section (T1) so that the ends (4) of the stiffeners (3) of the first section (T1) are housed in the spaces (8) between the modules (7) of the connection interface element (1) ,
• a second attachment sub-step (E1B) comprising the attachment of the second portion (92) of each of the modules (7) to the internal surface (6) of the skin (2) at the connection end (C2) of the second section (T2) so that the ends (4) of the stiffeners (3) of the second section (T2) are housed in the spaces (8) between the modules (7).

Method according to claim 11,
characterized in that the first fixing sub-step (E1A) also comprises the fixing of the first longitudinal part of the band (5) on the internal surface (6) of the skin (2) at the connection end (C1 ) of the first section (T1)
and in that the second fixing sub-step (E1B) also comprises the fixing of the second longitudinal part of the band (5) on the internal surface (6) of the skin (2) at the connection end (C1 ) of the second section (T2). Method according to any one of claims 11 and 12,
characterized in that it comprises a step (E0a) of alignment which precedes the step (E1) of fixing the connection element (1), the step (E0) of alignment comprising the alignment of the first section (T1) with the second section (T2) along the longitudinal axis (L1) of the aircraft (AC). Method according to any one of claims 11 and 12,
characterized in that it further comprises a first step (E01) of positioning which precedes the first sub-step (E1A) of fixing, the first step (E01) of positioning comprising the positioning of the connection interface element (1) so that the spaces (8) between the modules (7) can house the ends (4) of the stiffeners (3) of the first section (T1), and in that it also comprises a second step (E02) positioning which follows the first sub-step (E1A) of fixing and which precedes the second sub-step (E1B) of fixing, the second step (E02) of positioning comprising the positioning of the second section (T2) so that the ends (4) stiffeners (3) of the second section (T2) can be housed in the spaces (8) between the modules (7).