A mast assembly with a movable fairing and a nacelle with a movable hood

Abstract

ASSEMBLY OF A MAST WITH A MOVABLE FAIRING AND A CABIN WITH A MOVABLE HOOD The invention relates to an assembly (150) comprising a mast (102), a movable fairing (202b) having a second edge (203b) and hinged to the mast (102) between an open and a closed position, a nacelle (104) with a hood (106) having a first edge (106a) and hinged to the mast (102) between an open and a closed position, where, in the closed position of the movable fairing (202b) and the hood (106), the second edge (203b) of the movable fairing (202b) extends or overlaps the first edge (106a) of the hood (106). The installation of a movable fairing frees up the space necessary for a wider opening of the hood. Fig. 3

Description

Title of the invention: ASSEMBLY OF A MAST WITH A MOVABLE FAIRING AND A NACELLE WITH A COVER MOBILE Technical field

[0001] The present invention relates to an assembly for a propulsion system of an aircraft, which comprises a mast with a fairing and a nacelle, one of the cowls of which is movable, as well as an aircraft comprising at least one such assembly. STATE OF THE PRIOR ART

[0002] [Fig. 4] shows a front view of a detail of an assembly 400 for a propulsion system of an aircraft of the state of the art. The assembly 400 comprises a mast 401 which is surrounded, in the upper part, by a fairing 402 which creates an aerodynamic surface around the mast 401.

[0003] The assembly 400 also comprises an engine, such as a turbomachine, surrounded by a nacelle 404.

[0004] To access the engine and more generally the interior of the nacelle 404, the latter comprises at least one cover 406 which is mounted articulated on the mast 401 between a closed position (in solid lines) and an open position (in dotted lines).

[0005] To ensure the articulation of the hood 406, it is mounted on the mast 401 by means of a hinge connection 408.

[0006] In the closed position of the hood 406, the hood 406 and the fairing 402 extend one another so as to form a continuous aerodynamic surface.

[0007] When the hood 406 moves into the open position, it is lifted and pivots around the hinge connection 408. During this rotation, the hood 406 moves closer to the fairing 402 and the presence of the latter limits the rotation of the hood 406.

[0008] Currently, turbomachines have increasingly larger diameters and to maintain a minimum distance between the nacelle 404 and the ground, the nacelle 404 is moved upwards to move closer to the wing which supports the mast 402. This move closer results in the appearance of significant aerodynamic interactions and the limitation of the opening angle of the cowl 406.

[0009] To ensure the necessary opening angle of the hood 406, the hinge connection 408 is made by swan-neck fittings 410. Such fittings 410 make it possible to ensure the opening angle for better access to the interior of the nacelle 404, but they are relatively heavy and bulky.

[0010] The fixing of these fittings 410 is carried out here on a connecting fitting 412 which obstructs the aerodynamic flow 414 coming from the engine. The connecting fitting 412 is arranged between an outer skin and an inner skin of the hood 406.

[0011] For all these reasons, it is desirable to find a different arrangement. Statement of the invention

[0012] An object of the present invention is to provide an assembly for a propulsion system of an aircraft, which comprises a mast and a nacelle, one of the cowls of which is movable, and where a fairing of the mast is also movable to release the cowl.

[0013] For this purpose, an assembly is proposed for an aircraft, said assembly comprising:

[0014] - a mast,

[0015] - a mobile fairing of the mast having an edge, called the second edge, and mounted articulated on the mast between an open position in which the second edge is raised and a closed position in which the second edge is lowered, and

[0016] - a nacelle comprising a hood having a first edge and mounted articulated on the mast between an open position in which said hood is raised and a closed position in which said hood is lowered,

[0017] where in the closed position of the mobile fairing and the hood, the second edge of the mobile fairing extends or overlaps the first edge of the hood.

[0018] The installation of a movable fairing makes it possible to ensure the necessary opening of the hood while reducing the intrusion into the aerodynamic flow coming from the engine.

[0019] Advantageously, the articulation of the mobile fairing on the mast is a first hinge connection around a first hinge axis and the articulation of the hood on the mast is a second hinge connection around a second hinge axis and the two hinge axes are generally parallel.

[0020] Advantageously, the two hinge axes are parallel to a longitudinal axis of the nacelle.

[0021] Advantageously, the two hinge axes are arranged in the upper part of the nacelle.

[0022] Advantageously, the first hinge pin is arranged on an upper spar of the mast and the second hinge pin is arranged on a side wall of the mast.

[0023] Advantageously, the assembly comprises a set of first actuators where the first actuators are arranged to move the movable fairing from the open position to the closed position and vice versa.

[0024] Advantageously, the assembly comprises a set of second actuators where the second actuators are arranged to move the hood from the open position to the closed position and vice versa.

[0025] Advantageously, the assembly comprises a set of locking systems where each locking system is movable between a locking position in which the movable fairing is locked in the closed position and an unlocking position. rusting in which the moving fairing is free to move.

[0026] The invention also proposes an aircraft comprising at least one assembly according to one of the preceding variants. Brief description of the drawings

[0027] The above-mentioned characteristics of the invention, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the attached drawings, among which:

[0028] [Fig-1] is a side view of an aircraft according to the invention,

[0029] [Fig.2] is a schematic front view of an assembly for a system of propulsion according to the invention,

[0030] [Fig.3] is an enlargement of detail III of [Fig.2], and

[0031] [Fig.4] is a schematic front view of an assembly for a system of state-of-the-art propulsion.

[0032] DETAILED DESCRIPTION OF EMBODIMENTS

[0033] [Fig.l] shows an aircraft 100 which comprises a fuselage 108 on either side of which a wing 110 is fixed. Under each wing 110 is fixed at least one assembly 150 according to the invention for a propulsion system of the aircraft 100.

[0034] The assembly 150 comprises a mast 102 and a nacelle 104. The mast 102 is fixed under the wing 110 and it carries the nacelle 104 in which an engine such as a turbomachine is housed.

[0035] In the following description, and by convention, the longitudinal axis of the nacelle 104, oriented positively in the direction of advancement of the aircraft 100, is called X, the transverse axis which is horizontal when the aircraft 100 is on the ground is called Y, and the vertical axis or vertical height when the aircraft 100 is on the ground is called Z, these three directions X, Y and Z being orthogonal to each other.

[0036] In the following description, the terms relating to a position are taken with reference to the direction of movement of the aircraft 100 when the engine is operating and represented by the arrow F.

[0037] The nacelle 104 comprises a cowl 106 which is mounted articulated on the mast 102 around a second hinge axis 206 produced here by fittings 211 fixed here to a connecting fitting 214 of the cowl 106 which is itself arranged between an outer skin 107a and an inner skin 107b of the cowl 106. The cowl 106 may for example be a fan cowl or a cowl of a thrust reverser system.

[0038] The hood 106 is movable between an open position in which the hood 106 is raised to allow access to the interior of the nacelle 104 and a closed position in which the hood 106 is lowered.

[0039] [Fig.2] shows the assembly 150 with a starboard cover in the closed position and a port hood 106 in the open position. [Fig.3] shows detail III of [Fig.2] with hood 106 in the closed position in solid lines and hood 106 in the open position in dotted lines.

[0040] In the embodiment of the invention shown in Figs. 2 and 3, the mast 102 takes the form of a box with an upper spar 102a which extends generally horizontally along the longitudinal axis X, a lower spar 102c generally parallel to the upper spar 102a and on either side of a vertical median plane XZ of the nacelle 104, a side wall 102b which is integral with the upper spar 102a and the lower spar 102c.

[0041] The assembly 150 also includes a fairing 202 which covers an upper part of the mast 102, here the upper spar 102a, to create an aerodynamic surface around the mast 102.

[0042] The fairing 202 comprises a fixed fairing 202a and a movable fairing 202b. The fixed fairing 202a extends above the upper spar 102a and is fixed to the mast 102 by any suitable fixing means such as rivets, screws, etc.

[0043] The movable fairing 202b has a first edge 203a and a second edge 203b which both extend generally parallel to the longitudinal axis X. The movable fairing 202b extends partly above the upper spar 102a and on the side of the side wall 102b which is on the same side of the vertical median plane XZ.

[0044] The mobile fairing 202b is mounted articulated on the mast 102 between an open position in which the mobile fairing 202b and therefore the second edge 203b is raised and a closed position in which the mobile fairing 202b and therefore the second edge 203b is lowered.

[0045] In the closed position, the first edge 203a comes opposite an edge of the fixed fairing 202a to form the aerodynamic surface and in the open position, the first edge 203a is moved downwards relative to said edge of the fixed fairing 202a.

[0046] The hood 106 is hingedly mounted on the mast 102 between an open position in which the hood 106 is raised and a closed position in which the hood 106 is lowered.

[0047] The cover 106 here takes the form of a half-cylinder coaxial with the longitudinal axis X in the closed position and has a first edge 106a and a second edge 106b which also both extend generally parallel to the longitudinal axis X.

[0048] In the closed position, the first edge 106a of the cover 106 and the second edge 203b of the mobile fairing 202b are in the vicinity of each other and the second edges 106b of the two covers 106 symmetrical with respect to the vertical median plane XZ meet in the lower part of the nacelle 104 here at 6 o'clock with respect to the mast 102. To ensure that the covers 106 are kept in the closed position, locking means known to those skilled in the art are put in place.

[0049] More precisely, in the closed position of the mobile fairing 202b and the cover 106, the second edge 203b of the mobile fairing 202b extends or overlaps the first edge 106a of the cover 106.

[0050] In the embodiment of the invention shown in [Fig. 3], the second edge 203b of the movable fairing 202b overlaps the first edge 106a of the cover 106, but in another embodiment not shown, it is possible to arrange the second edge 203b of the movable fairing 202b so that it overlaps the first edge 106a of the cover 106 in continuity with each other.

[0051] Thus, when the hood 106 is to be opened, the movable fairing 202b is first moved to the open position, which releases the first edge 106a of the hood 106 and clears the side of the mast 102. After this movement, the hood 106 can be moved to the open position and the removal of the movable fairing 202b frees up space for a greater opening of the hood 106 compared to the state of the art.

[0052] Conversely, the cover 106 is returned to the closed position before the movable fairing 202b is moved to the closed position.

[0053] Furthermore, it is possible to ensure the maintenance of certain equipment through the space between the cover 106 and the mast 102 when the mobile fairing 202b is in the open position.

[0054] According to the invention, the articulation of the mobile fairing 202b on the mast 102 is a first hinge connection around a first hinge axis 204 and the articulation of the cover 106 on the mast 102 is a second hinge connection around the second hinge axis 206.

[0055] The two hinge axes 204 and 206 are generally parallel to each other and to the longitudinal axis X.

[0056] With such an arrangement, it is also not necessary to install swan-neck fittings for the hood 106, which lightens the assembly and reduces the space occupied by these fittings. The fitting 211 secured to the hood 106 is then of simpler shape. In addition, the connecting fittings 214 are less invasive in the aerodynamic flow 216 coming from the engine.

[0057] The two hinge axes 204 and 206 are arranged in the upper part of the nacelle 104, here generally at 12 o'clock.

[0058] In the embodiment of the invention shown in Figs. 2 and 3, the first hinge pin 204 is arranged on the upper spar 102a and the second hinge pin 206 is arranged on the side wall 102b which is on the same side as the movable fairing 202b relative to the vertical median plane XZ.

[0059] The movement of the movable fairing 202b from the open position to the closed position and vice versa can be carried out manually or mechanically, for example by a set of first actuators 208 of the set 150, such as jacks.

[0060] Depending on the length of the movable fairing 202b, there may be more or fewer first actuators 208 distributed along the first hinge connection.

[0061] In the embodiment of the invention presented in [Fig. 3], each first actuator 208 takes the form of a jack (hydraulic, electric, etc.) fixed between the mast 102, and more particularly here the upper spar 102a, and the mobile fairing 202b.

[0062] The first actuators 208 can be controlled remotely.

[0063] In the same way, the movement of the cover 106 from the open position to the closed position and vice versa can be carried out manually or mechanically, for example by a set of second actuators 210 of the set 150, such as jacks.

[0064] Depending on the length of the cover 106, there may be more or fewer second actuators 210 distributed along the second hinge connection.

[0065] In the embodiment of the invention presented in [Fig. 3], each second actuator 210 takes the form of a jack (hydraulic, electric, etc.) fixed between the mast 102, and more particularly here a side wall 102b, and the cover 106.

[0066] The second actuators 210 can be controlled remotely.

[0067] To limit the lifting of the movable fairing 202b from the closed position, for example when the aircraft 100 is in flight, the assembly 150 comprises a set of locking systems 212a-b, where each locking system 212a-b is movable alternately between a locking position in which the movable fairing 202b is locked in the closed position and an unlocking position in which the movable fairing 202b is free to move and therefore unlocked.

[0068] According to a particular embodiment, each locking system 212a locks the second edge 203b to the cover 106.

[0069] According to another particular embodiment, each locking system 212a locks the mobile fairing 202b to the mast 102.

[0070] Each locking system 212a-b can take different forms such as a lock, a latch, etc.

[0071] The locking / unlocking of the locking system 212a-b can be carried out manually or mechanically, for example with an electrically controlled lock, and it can then be controlled remotely.

[0072] Depending on the length of the movable fairing 202b, there may be more or less locking systems 212a-b distributed along the second edge 203b.

[0073] According to a particular embodiment, each first actuator 208 may comprise an integrated locking system.

Claims

Claims

1. Assembly (150) for an aircraft (100), said assembly (150) comprising: - a mast (102), - a movable fairing (202b) of the mast (102) having an edge (203b), called the second edge, and mounted articulated on the mast (102) between an open position in which the second edge (203b) is raised and a closed position in which the second edge (203b) is lowered, and - a nacelle (104) comprising a cover (106) having a first edge (106a) and mounted articulated on the mast (102) between an open position in which said cover (106) is raised and a closed position in which said cover (106) is lowered, where in the closed position of the movable fairing (202b) and the cover (106), the second edge (203b) of the movable fairing (202b) extends or overlaps the first edge (106a) of the hood (106).

2. Assembly (150) according to claim 1, characterized in that the articulation of the movable fairing (202b) on the mast (102) is a first hinge connection around a first hinge axis (204), and in that the articulation of the cover (106) on the mast (102) is a second hinge connection around a second hinge axis (206) and in that the two hinge axes (204, 206) are generally parallel.

3. Assembly (150) according to claim 2, characterized in that the two hinge axes (204, 206) are parallel to a longitudinal axis (X) of the nacelle (104).

4. Assembly (150) according to one of claims 2 or 3, characterized in that the two hinge axes (204, 206) are arranged in the upper part of the nacelle (104).

5. Assembly (150) according to one of claims 2 to 4, characterized in that the first hinge axis (204) is arranged on an upper spar (102a) of the mast (102) and in that the second hinge axis (206) is arranged on a side wall (102b) of the mast (102).

6. Assembly (150) according to one of claims 1 to 5, characterized in that it comprises a set of first actuators (208), where the first actuators (208) are arranged to move the movable fairing (202b) from the open position to the closed position and vice versa.

7. Assembly (150) according to one of claims 1 to 6, characterized in that it comprises a set of second actuators (210), where the second actuators (210) are arranged to move the hood (106) from the open position to the closed position and vice versa.

8. Assembly (150) according to one of claims 1 to 7, characterized in that it comprises a set of locking systems (212a-b), where each locking system (212a-b) is movable between a locking position in which the movable fairing (202b) is locked in the closed position and an unlocking position in which the movable fairing (202b) is free to move.

9. Aircraft (100) comprising at least one assembly (150) according to one of the preceding claims.

Images