Aircraft turbojet engine comprising at least one structural panel connected to a structure by at least one removable connection and at least one articulation

Abstract

Aircraft turbojet engine comprising at least one structural panel connected to a structure by at least one removable connection and at least one articulation The invention relates to an aircraft turbojet engine comprising: a structure (52), at least one structural panel (60), at least one removable connection configured to occupy a mounted state in which it immobilizes the structural panel (60) relative to the structure as well as a disassembled state in which the structural panel (60) can be moved away from the structure (52), at least one articulation (70) connecting the structural panel (60) and the structure (52) and allowing, when the removable connection is in the disassembled state, the structural panel (60) to move between positions close to and apart from the structure (52). This articulation (70) makes it possible to support the structural panel (60) and to move it away from the structure (52) when the removable connection is disassembled. Figure 7

Description

Title of the invention: Aircraft turbojet comprising at least one structural panel connected to a structure by at least one removable connection and at least one articulation

[0001] The present application relates to an aircraft turbojet engine comprising at least one structural panel connected to a structure by a removable connection and by at least one articulation as well as to an aircraft comprising at least one such turbojet engine.

[0002] According to an embodiment visible in Figures 1 and 2, an aircraft 10 comprises several propulsion units 12 each connected to a wing 14 of the aircraft by a mast 16.

[0003] A propulsion assembly 12 comprises a turbojet engine 18 as well as a nacelle (not shown in [Fig.2]) positioned around the turbojet engine 18, the latter having an axis of rotation A18.

[0004] For the remainder of the description, a longitudinal direction X is parallel to the axis of rotation A18. A transverse plane is a plane perpendicular to the axis of rotation A18. A vertical median plane PMV (referenced in [Fig.5]) is a vertical plane containing the axis of rotation A18. The terms front and rear refer to the direction of flow of the airflow in the turbojet 18, the airflow flowing from front to rear.

[0005] The turbojet engine 18 comprises a fan, a fan casing 20 and a reactor core 22 which comprises a front part 22.1 positioned inside the fan casing 20 and a rear part 22.2 offset rearwardly relative to the fan casing 20.

[0006] The mast 16 comprises a primary structure 24, in the form of a box, which is connected to the wing 14 by a wing attachment as well as to the turbojet 18 by a front engine attachment 26.1 and a rear engine attachment 26.2.

[0007] The rear part 22.2 of the reactor core 22 comprises a tubular structure 28 which delimits with the nacelle an annular duct in which circulates a flow of secondary air propelled by the fan.

[0008] For the present application, a tubular shape means a cylindrical shape, an evolving cylindrical shape, a barrel shape or the like. A tubular structure is delimited by two tubular-shaped surfaces, these two surfaces having approximately circular and concentric sections in transverse planes.

[0009] According to an embodiment visible in figures 2 and 5, this tubular structure 28 comprises an upper spar 30, positioned at 12 o'clock, which extends parallel to the longitudinal direction between front and rear ends, a lower spar 32, positioned at 6 o'clock, which extends parallel to the longitudinal direction between front and rear ends, a rear frame 34, positioned in a transverse plane, to which are connected the rear ends of the upper and lower side members 30, 32 as well as right and left structural panels 36 positioned on either side of the vertical median plane PMV.

[0010] As illustrated in Figures 2, 5 and 6, each of the right and left structural panels 36 comprises an upper edge 36.1 connected to the upper spar 30 by a first removable connection, a lower edge 36.2 connected to the lower spar 32 by a second removable connection, a front edge 36.3 which, like the front ends of the upper and lower spars 30, 32, is connected to the front part 22.1 of the reactor core 22 by a third removable connection as well as a rear edge 36.4 connected to the rear frame 34 by a fourth removable connection. Given the forces to which it is subjected, each structural panel 36 is relatively thick and strong. In addition, each of the first, second, third and fourth removable connections comprises a large number of bolts.

[0011] According to an embodiment visible in Figures 3 to 5, the upper spar 30 comprises a main part 30.1, a first plate 30.2 which has a first contact face F30.2 oriented towards one of the structural panels 36 as well as a plurality of first ribs 30.3, positioned in transverse planes, connecting the main part 30.1 and the first plate 30.2. In addition, the structural panel 36 comprises a second main part 38.1 and, at its upper edge 36.1, a second L-shaped plate 38.2 which has a second contact face F38.2 oriented towards the upper spar 30 as well as a plurality of second ribs 38.3, positioned in transverse planes, connecting the wings of the second L-shaped plate 38.2. The first removable connection comprises a plurality of bolts 40 which pass through the first and second plates 30.2, 38.2 and hold the first and second contact faces F30.2 and F38.2 pressed against each other. When the structural panel 36 is assembled, each of the first ribs 30.3 is positioned in the same transverse plane as a second rib 38.3 and the bolts 40 are positioned between the first and second ribs 30.3, 38.3. .

[0012] During operation of the aircraft, it is necessary to access elements of the reactor core 22 located under the structural panels 36 for maintenance or repair operations. Prior to dismantling a structural panel 36, a handling support 42 is fixed to the structural panel 36. For this purpose, the latter comprises anchor points for fixing the handling support 42. When the structural panel 36 is connected to the handling support 42, all the bolts 40 are removed. After removal of all the bolts 40, the panel structural 36 is removed by moving the handling support 42 using a lifting device.

[0013] This embodiment is not satisfactory because the operation of removing a structural panel 36 is long and requires a handling support 42 as well as a lifting device. The fact of having to move the structural panel 36 suspended from a lifting device also constitutes a source of risk for the operators.

[0014] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0015] To this end, the invention relates to an aircraft turbojet engine comprising a structure, at least one structural panel and at least one removable connection configured to occupy a mounted state in which the removable connection connects the structural panel to the structure and immobilizes it relative to the latter, as well as a disassembled state in which the structural panel can be, at least partially, separated from the structure.

[0016] According to the invention, the turbojet engine comprises at least one articulation connecting the structural panel and the structure and allowing, when the removable connection is in the dismantled state, the structural panel to move between a close position in which the structural panel cooperates with the structure and a separated position in which the structural panel is, at least partially, separated from the structure.

[0017] This articulation makes it possible to support the structural panel when the latter is in the disassembled state and to move it aside to access the interior area during maintenance or repair operations. Thus, it is no longer necessary to remove the structural panel using a handling support and a lifting device.

[0018] According to another characteristic, the structure comprises an upper spar substantially parallel to the longitudinal direction, the structural panel comprising an upper edge substantially parallel to the longitudinal direction and connected to the upper spar by the removable connection and the articulation.

[0019] According to another characteristic, the articulation comprises at least one pivoting connection which has a pivot axis allowing the structural panel to pivot relative to the structure around the pivot axis between the close and separated positions.

[0020] According to another characteristic, each pivoting connection comprises a pin which has an axis of revolution corresponding to the pivoting axis, at least one yoke secured to a first element among the structural panel and the structure as well as a tab secured to a second element, different from the first element, among the structural panel and the structure; each yoke comprising two wings substantially parallel to each other, between which is positioned the tab substantially parallel to the wings, the wings of the yoke and the tab each comprising a through hole for housing the pin and form a hinge with the latter.

[0021] According to another characteristic, the removable connection comprises: a. a first plate, secured to the upper spar, which has a first contact face oriented towards the structural panel, b. a plurality of first ribs, perpendicular to the longitudinal direction, connected to the first plate and configured to stiffen it, c. a second plate, secured to the structural panel, which has a second contact face oriented towards the upper spar, d. a plurality of second ribs, perpendicular to the longitudinal direction, connected to the second plate and configured to stiffen it, e. bolts which pass through the first and second plates and connect them while keeping the first and second contact faces pressed against each other, f. the wings of the yoke corresponding to two of the first ribs, each of which comprises a through hole, g. the tab being integral with the second plate, projecting from the second contact face and in the extension of one of the second ribs.

[0022] According to another characteristic, the first plate comprises, for each tab, a notch configured to accommodate the tab when the structural panel is in the close position.

[0023] According to another characteristic, each of the through holes of the yoke has a diameter substantially equal to that of the pin, the through hole of the lug having a diameter greater than that of the pin.

[0024] According to another characteristic, the pin is removable and configured to be removed when the first removable connection is in the mounted state.

[0025] According to another characteristic, each pivoting connection is removable and configured to occupy a disassembled state in which the yoke and the leg are detached from the structure and the structural panel as well as a mounted state in which the yoke and the leg are secured to the structure and the structural panel.

[0026] According to another characteristic, the turbojet engine comprises at least one holding mechanism configured to hold the structural panel in the spaced position.

[0027] According to another characteristic, the turbojet engine comprises at least one actuator for assisting or causing a pivoting movement of the structural panel between the close and separated positions.

[0028] According to another characteristic, the structural panel and the structure comprise cooperating shapes configured to correctly reposition the structural panel relative to the tubular structure upon return to the close position.

[0029] The invention also relates to an aircraft comprising at least one turbojet engine according to one of the preceding characteristics.

[0030] Other characteristics and advantages will emerge from the description of the invention which follows, a description given by way of example only, with reference to the appended drawings, among which:

[0031] [Fig-1] is a perspective view of an aircraft and a propulsion assembly,

[0032] [Fig.2] is a perspective view of a propulsion assembly without a nacelle illustrating an embodiment of the prior art,

[0033] [Fig.3] is a perspective view of a junction area connecting a spar upper and a structural panel of an aircraft turbojet engine illustrating an embodiment of the prior art,

[0034] [Fig.4] is a perspective view illustrating a detail of the visible junction area on [Fig.3],

[0035] [Fig.5] is a half-cross section of a tubular structure of a turbojet engine aircraft and a handling support illustrating an embodiment of the prior art,

[0036] [Fig.6] is a perspective view of a structural panel illustrating a method of rea prior art, in the disassembled state,

[0037] [Fig.7] is a cross-section of a tubular structure of a turbojet engine aircraft illustrating an embodiment of the invention, the structural panels being in a spaced apart position,

[0038] [Fig.8] is a perspective view of a junction zone connecting an upper spar and a structural panel of an aircraft turbojet engine illustrating an embodiment of the invention, the structural panel being in the assembled state,

[0039] [Fig.9] is a perspective view of a junction area connecting a spar upper and a structural panel of an aircraft turbojet engine illustrating an embodiment of the invention, the structural panel being in a spaced apart position,

[0040] [Fig. 10] is a perspective view illustrating a detail of the junction area visible in [Fig.8],

[0041] [Fig. 11] is a cross-section of a junction area connecting an upper spar and a structural panel of an aircraft turbojet engine illustrating another embodiment of the invention, without temporary articulation,

[0042] [Fig.12] is a cross-section of the junction area, visible in [Fig.11], equipped with a temporary joint.

[0043] As indicated previously, an aircraft comprises at least one propulsion assembly which comprises a turbojet engine. For example, the latter is a dual-flow turbojet engine. The turbojet engine comprises a reactor core 50 which comprises a front part as well as a tubular structure 52, visible in [Fig. 7], located in the extension of the front part. The tubular structure 52 separates an interior zone ZI (inside the tubular structure) and an exterior zone ZE (outside the tubular structure). It comprises an upper spar 54, positioned at 12 o'clock, which extends parallel to the longitudinal direction between front and rear ends, a lower spar 56, positioned at 6 o'clock, which extends parallel to the longitudinal direction between front and rear ends, a rear frame 58, positioned in a transverse plane, to which the rear ends of the upper and lower spars 54, 56 are connected as well as right and left structural panels 60, 60' positioned on either side of a vertical median plane PMV.

[0044] Each structural panel 60, 60' is configured to occupy an assembled state in which it prevents access to the interior zone ZI of the tubular structure 52 and a disassembled state in which it allows access to the interior zone ZI.

[0045] Each structural panel 60, 60' extends between upper and lower edges 62.1, 62.2, substantially parallel to the longitudinal direction X, which respectively adjoin the upper and lower side members 54, 56 in the assembled state as well as between front and rear edges, positioned in two transverse planes, which respectively adjoin the front casing and the rear frame 58 in the assembled state.

[0046] In the assembled state, the tubular structure 52 comprises, for each structural panel 60, 60', a first removable connection 64 connecting the upper edge 62.1 and the upper spar 54, a second removable connection connecting the lower edge 62.2 and the lower spar 56, a third removable connection connecting the front edge and the front casing as well as a fourth removable connection connecting the rear edge and the rear frame 58. Each of the first, second, third and fourth removable connections is a rigid connection immobilizing the structural panel 60, 60'.

[0047] According to one configuration, each of the first, second, third and fourth detachable connections comprises a set of fastening elements, such as bolts for example.

[0048] The upper spar 54 and each structural panel 60, 60' respectively comprise first and second main parts 54.1, 60.1 respectively having a first outer surface F54 and a second outer surface F60 oriented towards the outer zone ZE.

[0049] According to an embodiment visible in Figures 8 and 10, for at least one structural panel 60, the first removable connection 64 comprises a first plate 64.1, integral with the first main part 54.1 of the upper spar 54, which has a first contact face F64.1 oriented towards the structural panel 60, a second plate 64.2, integral with the second main part 60.1 of the structural panel 60, which has a second contact face F64.2 oriented towards the upper spar 54 as well as bolts 64.3 which pass through the first and second plates 64.1, 64.2 and connect them while keeping the first and second contact faces F64.1, F64.2 pressed against each other.

[0050] According to one configuration, the upper spar 54 comprises a plurality of first ribs 66.1 positioned in transverse planes, connected to the first plate 64.1 and configured to stiffen it. At least one of the structural panels 60, 60' comprises a plurality of second ribs 66.2 positioned in transverse planes, connected to the second plate 64.2 and configured to stiffen it.

[0051] Each of the first ribs 66.1 is positioned in the same transverse plane as a second rib 66.2. The bolts 64.3 are positioned between the first and second ribs 66.1, 66.2.

[0052] Of course, the invention is not limited to this embodiment for the first removable connection 64.

[0053] For at least structural panels 60, 60', the tubular structure 52 comprises an upper junction zone 68 connecting the structural panel 60 and the upper spar 54. In the assembled state, the upper junction zone 68 comprises the first removable connection 64.

[0054] With the exception of the upper junction zones 68, the upper and lower side members 54, 56, the rear frame 58, the structural panels 60, 60' as well as the first, second, third and fourth removable connections are not further described because they may be identical to those of the prior art.

[0055] Of course, the invention is not limited to this embodiment. Whatever the embodiment, the turbojet comprises a structure 52, at least one structural panel 60 as well as at least one removable connection 64 configured to occupy a mounted state, corresponding to the assembled state of the structural panel, in which the removable connection 64 connects the structural panel 60 to the structure 52 and immobilizes it relative to the latter as well as a disassembled state, corresponding to the disassembled state of the structural panel 60, in which the structural panel 60 can be, at least partially, separated from the structure 52.

[0056] The structural panel 60 has a periphery. According to a preferred configuration, the turbojet engine comprises one or more removable connections which extend over the entire periphery of the structural panel 60. According to one embodiment, each removable connection comprises several bolts. According to this embodiment, the structural panel 60 is bolted in the assembled state.

[0057] According to a particular feature, the tubular structure 52 comprises, for at least one of the structural panels 60, 60', at least one articulation 70, located in one of the upper junction zones 68, connecting the upper edge 62.1 of the structural panel 60 and the upper spar 54 and allowing, when the first removable connection 64 is in the dismantled state, the structural panel 60 to occupy a close position, visible on Figures 8, 11 and 12, in which the upper, lower front and rear edges respectively adjoin the upper spar 54, the lower spar 56, the front casing and the rear frame 58 as well as a spaced position, visible in [Fig.7], in which at least the lower edge 62.2 is spaced from the lower spar 56 and the structural panel 60, 60' allows access to the interior zone ZI.

[0058] According to one configuration, the structural panels 60, 60' are substantially symmetrical with respect to the vertical median plane PMV. Consequently, the description is only made for one of the structural panels 60, 60'.

[0059] According to one embodiment, the articulation 70 comprises at least one pivoting connection 72 which has a pivot axis A72, substantially parallel to the longitudinal direction X, allowing the structural panel 60 to pivot about the pivot axis A72 between the close and separated positions. According to a configuration visible in FIGS. 8 and 9, the articulation 70 comprises several pivoting connections 72.

[0060] According to one arrangement, each pivoting connection 72 comprises a pin 74 which has an axis of revolution corresponding to the pivot axis A72, at least one yoke 76 secured to a first element among the structural panel 60 and the upper spar 54 as well as a tab 78 secured to a second element, different from the first element, among the structural panel 60 and the upper spar 54. Each yoke 76 comprises two wings 76.1, 76.2, substantially parallel to each other and positioned in transverse planes, between which is positioned the tab 78 substantially parallel to the wings, the wings 76.1, 76.2 of the yoke 76 and the tab 78 each comprising a through hole T76.1, T76.2, T78 to house the pin 74 and form with the latter a hinge.

[0061] According to one arrangement, the yoke 76 is integral with the upper spar 54 and the tab 78 is integral with the structural panel 60.

[0062] According to an embodiment visible in Figures 7 to 10, the wings 76.1, 76.2 of the yoke 76 correspond to two first ribs 66.1, each of them comprising a through hole T76.1, T76.2. In addition, the tab 78 is positioned in a transverse plane, projecting relative to the second contact face F64.2 and in the extension of a second rib 66.2. In addition, the first plate 64.1 comprises, for each tab 78, a notch 80 configured to allow the passage of the tab 78 when the structural panel 60 is in the close position. The upper spar 54 does not comprise a first rib 66.1 in line with the tab 78.

[0063] According to a first configuration, the pin 74 is not removable. It is always housed in the through holes T76.1, T76.2, T78 of the wings 76.1, 76.2 of the yoke 76 and of the lug 78. According to one arrangement, each of the through holes T76.1, T76.2 of the yoke 76 has a diameter substantially equal to that of the pin 74. In addition, the through hole T78 of the lug 78 has a diameter greater than that of the pin 74. The presence of a clearance between the lug 78 and the pin 74 prevents the passage of forces at the pin 74 when the structural panel 60 is in the assembled state. Alternatively, the through hole T78 of the lug 78 could have a diameter substantially equal to that of the pin 74. In addition, each of the through holes T76.1, T76.2 of the yoke 76 could have a diameter greater than that of the pin 74.

[0064] According to a second configuration, the pin 74 is removable and can be removed when the structural panel 60 is in the assembled state or the first removable connection is in the mounted state. In this case, each pivoting connection 72 is partly removable. Thus, the pin 74 is inserted into the through holes T76.1, T76.2, T78 of the wings 76.1, 76.2 of the yoke 76 and the tab 78 only during maintenance and repair operations, when the structural panel 60 must be moved aside to access the interior zone ZI. According to this first embodiment, each of the through holes T76.1, T76.2, T78 of the wings 76.1, 76.2 of the yoke 76 and the tab 78 has a diameter substantially equal to that of the pin 74.

[0065] According to an embodiment visible in Figures 11 and 12, each pivoting connection 72 is removable and configured to occupy a disassembled state, visible in [Fig. 11], when the yoke 76 and the tab 78 are separated from the upper spar 54 and the structural panel 60 as well as a mounted state, visible in [Fig. 12], when the yoke 76 and the tab 78 are secured to the upper spar 54 and to the structural panel 60.

[0066] According to this second embodiment, the yoke 76 and the tab 78 are connected to the upper spar 54 and to the structural panel 60 by fixing elements 82. According to one arrangement, the yoke 76 and the tab 78 project relative to the outer surfaces F54, F60 of the upper spar 54 and of the structural panel 60. For each fixing element 82, the upper spar 54 or the structural panel 60 comprises an anchoring point for securing the fixing element 82, for example for screwing it.

[0067] According to one configuration, for at least one of the structural panels 60, 60', the turbojet engine comprises at least one holding mechanism configured to hold the structural panel 60, 60' in the spaced apart position. For example, the holding mechanism may be a holding rod.

[0068] The pivoting of the structural panel 60 may be manual and unassisted. According to another configuration visible in [Fig.7], the turbojet engine comprises at least one actuator 84 for assisting or causing a pivoting movement of the structural panel 60 between the close and separated positions. According to one arrangement, the actuator 84 is configured to maintain the structural panel 60 in the position spaced apart. For example, the actuator 84 may be a hydraulic or electromechanical cylinder.

[0069] Generally, the turbojet engine comprises at least two means for holding the structural panel 60 in the spaced position, such as a holding rod and an actuator.

[0070] According to another embodiment, the structural panel 60 and the tubular structure 52 comprise cooperating shapes, such as centering pins for example, to correctly reposition the structural panel 60 relative to the tubular structure 52 when returning to the close position in order to facilitate the installation of the fixing elements such as the bolts of the removable connections.

[0071] Of course, the invention is not limited to the embodiments previously described. Thus, the articulation 70 is not necessarily positioned at the upper edge of the structural panel 60. Thus, it could be positioned at another edge of the structural panel 60. Whatever the embodiment, the turbojet engine comprises at least one articulation 70 which connects the structural panel 60 and the structure 52, allowing, when the removable connection 64 is in the disassembled state, the structural panel 60 to move relative to the structure 52 between a close position in which the structural panel 60 cooperates with the structure 52 and a separated position in which the structural panel 60 is, at least partially, separated from the structure 52. When it occupies the close position, the structural panel 60 can be assembled or disassembled and the removable connection 64 can switch between the assembled and disassembled states.

[0072] The articulation 70 makes it possible to support the structural panel 60 when the latter is in the disassembled state and to move it aside to access the interior zone ZI during maintenance or repair operations. Thus, it is no longer necessary to remove the structural panel 60 using a handling support 42 and a lifting device.

Claims

Claims

1. Aircraft turbojet engine comprising a structure (52), at least one structural panel (60) and at least one removable connection (64) configured to occupy a mounted state in which the removable connection (64) connects the structural panel (60) to the structure (52) and immobilizes it relative to the latter and a disassembled state in which the structural panel (60) can be, at least partially, separated from the structure (52); characterized in that the turbojet engine comprises at least one articulation (70) connecting the structural panel (60) and the structure (52) and allowing, when the removable connection (64) is in the disassembled state, the structural panel (60) to move between a close position in which the structural panel (60) cooperates with the structure (52) and a separated position in which the structural panel (60) is, at least partially, separated from the structure (52).

2. Aircraft turbojet according to claim 1, characterized in that the structure (52) comprises an upper spar (54) substantially parallel to the longitudinal direction (X) and in that the structural panel (60) comprises an upper edge (62.1), substantially parallel to the longitudinal direction (X), connected to the upper spar (54) by the removable connection (64) and the articulation (70).

3. Aircraft turbojet according to one of the preceding claims, characterized in that the articulation (70) comprises at least one pivoting connection (72) which has a pivot axis (A72) allowing the structural panel (60) to pivot relative to the structure (52) around the pivot axis (A72) between the close and separated positions.

4. Aircraft turbojet according to the preceding claim, characterized in that each pivoting connection (72) comprises a pin (74) having an axis of revolution corresponding to the pivoting axis (A72), at least one yoke (76) secured to a first element among the structural panel (60) and the structure (52) as well as a lug (78) secured to a second element, different from the first element, among the structural panel (60) and the structure (52); each yoke (76) comprising two wings (76.1, 76.2), substantially parallel to each other, between which is positioned the lug (78) substantially parallel to the wings, the wings (76.1, 76.2) of the yoke (76) and the lug (78) each comprising a through hole (T76.1, T76.2, T78) for housing the pin (74) and form a hinge with the latter.

5. Aircraft turbojet according to claims 2 and 4, characterized in that the removable connection (64) comprises: a. a first plate (64.1), secured to the upper spar (54), which has a first contact face (F64.1) oriented towards the structural panel (60), b. a plurality of first ribs (66.1), perpendicular to the longitudinal direction (X), connected to the first plate (64.1) and configured to stiffen it, c. a second plate (64.2), secured to the structural panel (60), which has a second contact face (F64.2) oriented towards the upper spar (54), d. a plurality of second ribs (66.2), perpendicular to the longitudinal direction (X), connected to the second plate (64.2) and configured to stiffen it, e. bolts (64.3) which pass through the first and second plates (64.1, 64.2) and connect them while keeping the first and second contact faces (F64.1, F64.2) pressed against each other, f. the wings (76.1, 76.2) of the yoke (76) corresponding to two of the first ribs (66.1), each of them comprising a through hole (T76.1, T76.2), g. the tab (78) being integral with the second plate (64.2), projecting relative to the second contact face (F64.2) and in the extension of one of the second ribs (66.2).

6. Aircraft turbojet according to the preceding claim, characterized in that the first plate (64.1) comprises, for each tab (78), a notch (80) configured to house the tab (78) when the structural panel (60) is in the close position.

7. Aircraft turbojet according to one of claims 4 to 6, characterized in that each of the through holes (T76.1, T76.2) of the yoke (76) has a diameter substantially equal to that of the pin (74), the through hole (T78) of the lug (78) having a diameter greater than that of the pin (74).

8. Aircraft turbojet according to one of claims 4 to 7, characterized in that the pin (74) is removable and configured to be removed when the first removable connection is in the mounted state.

9. Aircraft turbojet according to claim 4, characterized in that each pivoting connection (72) is removable and configured to occupy a disassembled state in which the yoke (76) and the lug (78) are detached from the structure (52) and the structural panel (60), as well as a mounted state in which the yoke (76) and the lug (78) are secured to the structure (52) and the structural panel (60).

10. Aircraft turbojet engine according to one of the preceding claims, characterized in that the turbojet engine comprises at least one holding mechanism configured to hold the structural panel (60) in the spaced position.

11. Aircraft turbojet engine according to one of the preceding claims, characterized in that the turbojet engine comprises at least one actuator (84) for assisting or causing a pivoting movement of the structural panel (60) between the close and separated positions.

12. Aircraft turbojet according to one of the preceding claims, characterized in that the structural panel (60) and the structure (52) comprise cooperating shapes configured to correctly reposition the structural panel (60) relative to the tubular structure (52) upon return to the close position.

13. Aircraft comprising at least one turbojet engine according to one of the preceding claims.

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