Aircraft comprising at least one cowling having two parts movable relative to each other

Abstract

Aircraft comprising at least one cowling having two parts movable relative to each other. The invention relates to an aircraft comprising at least one propulsion assembly and at least one mast, the propulsion assembly comprising at least one cowling (46), connected by at least one first hinge (48) to a fixed support (50), comprising a curved main part (54) and a secondary side fairing (56) positioned in line with a main side fairing (52) of the mast when the cowling (46) is in the closed position. According to the invention, the secondary side fairing (56) comprises at least first and second parts (62, 64) movable relative to each other, the first part (62) being connected to the main part (54) of the cowling (56).This solution prevents the first part (62) of the secondary side fairing (56), fixed relative to the hood (46), from coming into contact with the primary structure of the mast (42) when the hood (46) is open. Figure 6.

Description

Title of the invention: Aircraft comprising at least one cowl having two parts movable relative to each other

[0001] The present application relates to an aircraft comprising at least one cowl having two parts movable relative to each other.

[0002] According to an embodiment visible in Figures 1 and 2, an aircraft 10 comprises a fuselage 12, a wing 14 as well as propulsion assemblies 16 positioned under the wing 14 and connected to the latter by masts 18. Each propulsion assembly 16 comprises a motorization 20 as well as a nacelle 22 positioned around the motorization 20, said nacelle 22 comprising an air inlet 23 making it possible to channel the air inside the nacelle 22 towards the motorization 20, a central part 24 as well as a rear part 26.

[0003] The motorization 20 comprises an axis of rotation A20. For the remainder of the description, a longitudinal direction is a direction parallel to the axis of rotation A20 of the motorization 20. A transverse plane is a plane perpendicular to the axis of rotation A20 of the motorization 20. A vertical median plane is a vertical plane containing the axis of rotation A20 of the motorization 20. The concepts front / rear refer to the direction of flow of the airflow in the nacelle, which flows from front to rear.

[0004] As illustrated in Figures 3 and 4, each mast 18 comprises a primary structure 18.1 ensuring the transmission of forces between the propulsion assembly 16 and the wing 14 as well as a secondary structure 18.2 forming a fairing around the primary structure 18.1.

[0005] At its central portion 24, the nacelle 22 comprises two cowls 28, 28' positioned on either side of the vertical median plane, each comprising an upper edge 28.1 connected by at least one articulation 30 to the primary structure 18.1 of the mast 18 as well as a lower edge 28.2, each cowl 28, 28' being movable between a closed position (visible in [Fig.3]) in which the lower edges 28.2 of the two cowls 28, 28' are joined and an open position (visible in [Fig.4]) in which the lower edge 28.2 of at least one of the cowls 28, 28' is spaced from the vertical median plane allowing access under the cowl 28, 28'.

[0006] Each articulation 30 comprises a pivoting connection having a pivot axis A30 substantially parallel to the longitudinal direction.

[0007] To the right of each hood 28, 28', the secondary structure 18.2 of the mast 18 comprises a main lateral fairing 32 which is substantially vertical and slightly spaced from the primary structure 18.1 of the mast 18.

[0008] Each cover 28, 28' has a curved main part 34 (following the profile of the nacelle 22) as well as a secondary lateral fairing 36, substantially planar, ensuring aerodynamic continuity between the main lateral fairing 32 of the mast 18 and the main part 34 of the cover 28, 28' when the latter is in the closed position. Thus, this secondary lateral fairing 36 comprises a lower edge 36.1 secured to the main part 34 of the cover 28, 28' as well as an upper edge 36.2 cooperating with the lower edge 32.1 of the main lateral fairing 32 of the mast 18 when the cover 28, 28' is in the closed position.

[0009] As illustrated in Figures 3 and 4, the pivot axis A30 being integral with the main part 34 of the cover 28, the upper edge 36.2 of the secondary lateral fairing 36 is spaced from the pivot axis A30 and offset upwards relative to the latter.

[0010] When the hood 28 is opened, the main part 34 and the secondary side fairing 36 pivot about the pivot axis A30 until the upper edge 36.2 of the secondary side fairing 36 is in contact with the primary structure 18.1 of the mast 18, as illustrated in [Fig. 4]. According to this configuration, the hood 28 can pivot by approximately 45 to 50° relative to a vertical plane, its opening movement being limited due to the contact of the upper edge 36.2 of the secondary side fairing 36 against the primary structure 18.1 of the mast 18.

[0011] The fact that the hood 28 cannot pivot further reduces accessibility to the equipment of the propulsion assembly 16 located under the hood 28.

[0012] One solution for increasing the pivot angle of the cowl 28 consists of moving the secondary side fairing 36 of the cowl 28 away from the primary structure 18.1 of the mast 18. This solution is not satisfactory because it leads to moving the main side fairing 32 of the secondary structure 18.2 away from the primary structure 18.1, which reduces the aerodynamic performance of the aircraft.

[0013] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0014] For this purpose, the invention relates to an aircraft comprising at least one propulsion assembly, a wing and at least one mast connecting the propulsion assembly and the wing; the mast comprising a primary structure and at least one main lateral fairing, the propulsion assembly comprising at least one cowl connected by at least one first articulation to a fixed support, the cowl being movable between closed and open positions and comprising a curved main part as well as a secondary lateral fairing which comprises a lower edge secured to the main part of the cowl as well as an upper edge configured to cooperate with the main lateral fairing of the mast when the cowl is in the closed position.

[0015] According to the invention, the secondary side fairing comprises at least first and second parts movable relative to each other, the first part having a first lower edge corresponding to the lower edge of the secondary side fairing as well as a first upper edge, the second part having a second upper edge corresponding to the upper edge of the secondary side fairing as well as a second lower edge.

[0016] This solution makes it possible to prevent the first part of the secondary side fairing, fixed relative to the hood, from coming into contact with the primary structure of the mast when the hood is open. This also makes it possible, if necessary, to increase the amplitude of movement between the closed and open positions.

[0017] According to another characteristic, the second lower edge of the second part is configured to cooperate with the first upper edge of the first part.

[0018] According to another characteristic, the first and second parts of the secondary lateral fairing are connected by at least one articulation which has a pivot axis.

[0019] According to another characteristic, each first articulation comprises a pivot axis, the first and second pivot axes being the same.

[0020] According to another characteristic, each second articulation comprises: a. at least one first wing integral with the first part and comprising a first through-hole, b. at least one second wing integral with the second part and comprising a second through hole, c. a cylindrical rod, housed in the first and second through holes of the first and second wings, forming the second pivot axis.

[0021] According to another characteristic, the second wing has a swan neck shape so as to form with the second part a housing in which the first upper edge of the first part is positioned.

[0022] According to another characteristic, the second articulation comprises at least one return element configured to maintain the first and second parts of the secondary lateral fairing substantially coplanar.

[0023] According to another characteristic, the first upper edge of the first part and the second lower edge of the second part are configured so as to overlap and be pressed, directly or indirectly, against each other when the hood is in the closed position, the first upper edge of the first part being positioned between the second lower edge of the second part and the primary structure of the mast.

[0024] According to another characteristic, the aircraft comprises at least one seal and / or a wedge positioned between the first upper edge of the first part and the second lower edge of the second part when the cover is in the closed position.

[0025] According to another characteristic, the first part comprises a groove near its first upper edge so that the first and second parts of the secondary side fairings have substantially coplanar outer faces when the hood is in the closed position.

[0026] 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:

[0027] [Fig-1] is a side view of an aircraft,

[0028] [Fig.2] is a perspective view of a propulsion assembly,

[0029] [Fig.3] is a perspective view of part of a mast and a set of propulsion of an aircraft illustrating an embodiment of the prior art, the cowl being in the closed position,

[0030] [Fig.4] is a cross-section of the mast and the propulsion assembly visible on [Fig.3], the hood being in the open position,

[0031] [Fig.5] is a side view of part of a mast and propulsion assembly of an aircraft illustrating an embodiment of the invention,

[0032] [Fig.6] is a section of part of a mast and a hood illustrating a method of rea implementation of the invention, the hood being in the closed position,

[0033] [Fig.7] is a cross-section of the mast and the hood visible in [Fig.6], the hood being in the open position,

[0034] [Fig.8] is a sectional view of part of a mast and a hood illustrating another mode of embodiment of the invention, the hood being in the closed position,

[0035] [Fig.9] is a cross-section of the mast and hood seen in [Fig.8], the hood being in the open position,

[0036] [Fig. 10] shows schematic sections of the mast and the hood illustrating an embodiment at different times between the closed position of the hood visible on part (A) and the open position of the hood visible on part (D).

[0037] As illustrated in [Fig.5], an aircraft comprises at least one propulsion assembly 40, a wing and at least one mast 42 connecting the propulsion assembly 40 and the wing. The propulsion assembly 40 comprises a nacelle 44 surrounding a motorization.

[0038] According to the embodiments visible in Figures 6 to 9, the mast 42 comprises a primary structure 42.1 ensuring the transmission of forces between the propulsion assembly 40 and the wing as well as a secondary structure 42.2 forming a fairing enveloping the primary structure 42.1.

[0039] The motorization comprises a motorization axis parallel to a longitudinal direction. The nacelle 44 has a vertical median plane passing through the motorization axis.

[0040] The nacelle 44 comprises at least one cover 46 connected by at least one first articulation 48 to a fixed support 50 (like the primary structure 42.1 of the mast 42), the cover 46 being movable between closed and open positions. According to one embodiment, the primary structure 42.1 or an element connected thereto provides the support function 50.

[0041] According to one configuration, the nacelle 44 comprises two cowls 46, positioned on either side of the vertical median plane, each comprising a first edge connected by a first articulation 48 to the primary structure 42.1 of the mast 42 as well as a second edge, each cowl 46 being movable between the closed position (visible in [Fig.6]) in which the second edges of the two cowls are joined and the open position (visible in [Fig.7]) in which the second edge of at least one of the cowls 46 is spaced from the vertical median plane allowing access under the cowl 46.

[0042] At least to the right of each cover 46, the secondary structure 42.2 of the mast 42 comprises at least one main lateral fairing 52 substantially vertical and parallel to the longitudinal direction, slightly spaced from the primary structure 42.1 of the mast 42. This main lateral fairing 52 comprises a lower edge 52.1 configured to cooperate with the cover 46.

[0043] With the exception of the hood 46 and the first articulation 48, the other elements of the propulsion assembly 40 and the mast 42 are not further described because they may be identical to those of the prior art.

[0044] Each cowl 46 comprises a curved main portion 54 (following the profile of the nacelle 44) as well as a substantially flat secondary lateral fairing 56 ensuring aerodynamic continuity between the main lateral fairing 52 of the mast 42 and the main portion 54 of the cowl 46 when the latter is in the closed position. The main portion 54 of the cowl has an outer surface in continuity with the other outer surfaces of the nacelle 44 when the cowl 46 is in the closed position. The secondary side fairing 56 comprises a lower edge 56.1 secured to the main part 54 of the cover 46 at a junction zone 58 as well as an upper edge 56.2 configured to cooperate with the lower edge 52.1 of the main side fairing 52 of the mast 42 when the cover 46 is in the closed position, said upper edge 56.2 being spaced from the lower edge 52.1 of the main side fairing 52 of the mast 42 when the cover 46 is in the open position.

[0045] The main part 54 and the secondary lateral fairing 56 are substantially perpendicular to each other at the level of the junction zone 58.

[0046] According to an embodiment visible in Figures 6 and 7, the main part 54 does not extend beyond the secondary lateral fairing 56 and has an upper edge 54.1 positioned in the extension of the secondary lateral fairing 56.

[0047] According to another embodiment visible in Figures 8 and 9, as for the prior art, the main part 54 comprises an extension 54.2 which extends beyond the secondary side fairing 56 and has an edge 54.3 spaced from the secondary side fairing secondary 56.

[0048] Each first articulation 48 comprises a pivoting connection having a first pivot axis A48 substantially parallel to the longitudinal direction. According to one configuration, the cover 46 is connected to the support by several first articulations 48 distributed along the longitudinal direction.

[0049] Each first articulation 48 comprises: a. at least one first wing 60.1, integral with the support 50, positioned in a plane perpendicular to the first pivot axis A48 and comprising a first through orifice, b. at least one second wing 60.2, integral with the cover 46, positioned in a plane perpendicular to the first pivot axis A48 and comprising a second through orifice c. a cylindrical rod 60.3, housed in the first and second through holes of the first and second wings 60.1, 60.2, forming the first pivot axis A48.

[0050] According to one arrangement, the first wing 60.1 is fixed to the primary structure 42.1 of the mast 42.

[0051] According to a first configuration visible in figures 6 and 7, the second wing 60.2 is fixed on the secondary lateral fairing 56, close to the main part 54 of the cover 46.

[0052] According to a second configuration visible in figures 8 and 9, as for the prior art, the second wing 60.2 is fixed on the extension 54.2 of the main part 54, between the secondary lateral fairing 56 and the edge 54.3 of the extension 54.2.

[0053] According to a feature of the invention, the secondary side fairing 56 comprises at least first and second parts 62, 64 movable relative to each other, the first part 62 having a first lower edge 62.1 corresponding to the lower edge 56.1 of the secondary side fairing 56 as well as a first upper edge 62.2, the second part 64 having a second upper edge 64.1 corresponding to the upper edge 56.2 of the secondary side fairing 56 as well as a second lower edge 64.2. Each first articulation 48 is connected to the main part 54 and / or the first part 62 of the cover 46. As illustrated in [Fig. 10], the first part 62 may have a reduced height.

[0054] According to one configuration, the secondary side fairing 56 comprises first and second parts 62, 64, the second lower edge 64.2 of the second part 64 being configured to cooperate with the first upper edge 62.2 of the first part 62.

[0055] According to one arrangement, the second upper edge 64.1 of the second part 64, corresponding to the upper edge 56.2 of the secondary lateral fairing 56, is substantially parallel to the first pivot axis A48.

[0056] The first upper edge 62.2 of the first part 62 and the second lower edge 64.2 of the second part 64 are substantially parallel to the first pivot axis A48.

[0057] The first lower edge 62.1 of the first part 62, corresponding to the lower edge 56.1 of the secondary side fairing 56, follows the profile of the main part 54 of the cover 46 and is not necessarily parallel to the first pivot axis A48.

[0058] According to one configuration, the lower edge 52.1 of the main side fairing 52 and the second upper edge 64.1 of the second part 64 of the secondary side fairing 56 are configured so that, when the cover 46 is in the closed position (visible in [Fig. 6]), they overlap and are pressed, directly or indirectly, against each other, the second upper edge 64.1 of the second part 64 being positioned between the lower edge 52.1 of the main side fairing 52 and the primary structure 42.1 of the mast 42. According to one arrangement, the aircraft comprises at least one seal and / or a shim 66 positioned between the lower edge 52.1 of the main side fairing 52 and the second upper edge 64.1 of the second part 64 of the secondary side fairing 56 when the cover 46 is in the closed position. Regardless, the seal (and / or the shim) 66 is (are) integral with the lower edge 52.1 of the main side fairing 52 or of the second upper edge 64.1 of the second part 64 of the secondary side fairing 56. .

[0059] According to one embodiment, the second part 64 comprises a groove 68 near its second upper edge 64.1 so that the outer faces of the main side fairing 52 and of the second part 64 of the secondary side fairing 56 are substantially coplanar when the cover 46 is in the closed position.

[0060] According to one configuration, the first upper edge 62.2 of the first part 62 and the second lower edge 64.2 of the second part 64 are configured so as to overlap and be pressed, directly or indirectly, against each other when the cover 46 is in the closed position, the first upper edge 62.2 of the first part 62 being positioned between the second lower edge 64.2 of the second part 64 and the primary structure 42.1 of the mast 42. According to one arrangement, the aircraft comprises at least one seal and / or a shim 70 positioned between the first upper edge 62.2 of the first part 62 and the second lower edge 64.2 of the second part 64 when the cover 46 is in the closed position. Indifferently, the seal (and / or the shim) 70 is (are) integral with the first upper edge 62.2 of the first part 62 or with the second lower edge 64.2 of the second part 64.

[0061] According to one embodiment, the first part 62 comprises a groove 72 near its first upper edge 62.2 so that the outer faces of the first and second parts 62, 64 of the secondary lateral fairing 56 are sen possibly coplanar when the cover 46 is in the closed position.

[0062] The first and second parts 62, 64 are connected to each other by at least one second articulation 74 which comprises a pivoting connection having a second pivot axis A74 substantially parallel to the longitudinal direction. According to one configuration, the first and second parts 62, 64 are connected to each other by several second articulations 74 distributed along the longitudinal direction.

[0063] According to a configuration visible in Figures 6 and 7, the first and second pivot axes A48, A74 are merged. According to this configuration, each second articulation comprises: a. at least one first wing 76.1 (merged with the second wing 60.2 of the first articulation 48), integral with the first part 62, positioned in a plane perpendicular to the second pivot axis A74 and comprising a first through orifice, b. at least one second wing 76.2, integral with the second part 64 of the secondary lateral fairing 56, positioned in a plane perpendicular to the second pivot axis A74 and comprising a second through-hole, c. a cylindrical rod 76.3 (merged with the cylindrical rod 60.3 of the first articulation 48) housed in the first and second through holes of the first and second wings 76.1, 76.2, said cylindrical rod 76.3 forming the second pivot axis A74.

[0064] The cylindrical rods 60.3, 76.3 being common to the first and second articulations 48, 74, the second part 64 is also connected by the articulation 74 to the support 50.

[0065] According to another configuration visible in Figures 8 and 9, the first and second articulations 48, 74 are distinct. According to this configuration, each second articulation comprises: a. at least one first wing 76.1, integral with the first part 62, positioned in a plane perpendicular to the second pivot axis A74 and comprising a first through orifice, b. at least one second wing 76.2, integral with the second part 64 of the secondary lateral fairing 56, positioned in a plane perpendicular to the second pivot axis A74 and comprising a second through-hole, c. a cylindrical rod 76.3 housed in the first and second through holes of the first and second wings 76.1, 76.2, said cylindrical rod 76.3 forming the second pivot axis A74.

[0066] According to one embodiment, the second wing 76.2 has a neck shape. swan so as to form with the second part 64 a housing in which the first upper edge 62.2 of the first part 62 is positioned. According to one embodiment, the second wing 76.2 has first and second portions 78.1, 78.2 forming a V, the first portion 78.1 being connected to the cylindrical rod 76.3 of the pivot axis A74, the second portion 78.2 being connected to the second part 64 while being spaced from the second lower edge 64.2. Thus, the first upper edge 62.2 of the first part 62 is positioned between the second lower edge 64.2 of the second part 64 and the first portion 78.1 of the second wing 76.2 of each articulation 74. According to this configuration, when the cover 46 pivots from the closed position to the open position, the first part 62 of the secondary side fairing 56 pivots until it comes into contact with the first portion 78.1 of the second wing 76.2 of each articulation 74.From then on, the pivoting of the hood 46 causes the pivoting of the second part 64 of the secondary lateral fairing 56 until said second part 64 or the second wing 76.2 of at least one articulation 74 is in contact with the primary structure 42.1 of the mast 42.

[0067] When the cover 46 pivots from the open position to the closed position, the first part 62 of the secondary side fairing 56 pivots until it comes into contact with the second lower edge 64.2 of the second part 64. From then on, the pivoting of the cover 46 causes the pivoting of the first and second parts 62, 64 of the secondary side fairing 56 until the second part 64 is in contact with the main side fairing 52 of the mast 42.

[0068] The fact of providing a secondary lateral fairing 56 in two parts 62, 64 movable relative to each other makes it possible to prevent the first part 62 of the secondary lateral fairing 56 fixed relative to the cover 46 from coming into abutment against the primary structure 42.1 of the mast 42 when the cover is open. This also makes it possible to increase the amplitude of the movement between the closed and open positions. Consequently, the cover 46 can pivot at an angle considerably greater than 65° relative to a vertical plane, which contributes to improving accessibility to the equipment of the propulsion assembly located under the cover 46.

[0069] According to one embodiment, the first and second parts 62, 64 of the secondary lateral fairing 56 as well as the second articulation 74 are configured so that the pivoting of the cover 46 automatically generates a pivoting of the second part 64 relative to the first part 62. This solution makes it possible to automatically position the second part 64 in the extension of the first part 62 of the secondary lateral fairing 56 and of the main lateral fairing 52 of the mast 42 when the cover 46 tilts from the open position to the closed position of the cover 46.

[0070] Alternatively, as illustrated in [Fig. 10], the second articulation 74 comprises at least at least one return element 80, such as a spring for example, configured to maintain the first and second parts 62, 64 of the secondary side fairing 56 in contact with each other, as illustrated in parts (A), (B) and (C) of [Fig. 10], until the second swan-neck wing 76.2 is in contact with the support 50.

[0071] In part (A), the hood 46 is in the closed position. At the start of the opening movement, as illustrated in part (B), the hood 46 pivots. The first and second parts 62, 64 also pivot and remain in contact with each other thanks to the return means 80. After a pivoting of the order of 35 to 40°, the second swan-neck wing 76.2 comes into contact with the support 50 (corresponding to the primary structure 42.1 of the mast 42), as illustrated in part (C).Unlike the prior art, the hood 46 can still pivot until it reaches its maximum opening position corresponding to a pivoting of the order of 68°, as illustrated in part (D). When the second wing 76.2 is in abutment against the support 50, the second part 64 remains stationary. Only the first part 62 and the main part 54 of the hood pivot.

Claims

Claims

1. Aircraft comprising at least one propulsion assembly (40), a wing and at least one mast connecting the propulsion assembly (40) and the wing, the mast (42) comprising a primary structure (42.1) and at least one main lateral fairing (52), the propulsion assembly comprising at least one cowl (46) connected by at least one first articulation (48) to a fixed support (50), the cowl (46) being movable between closed and open positions and comprising a curved main part (54) as well as a secondary lateral fairing (56) which comprises a lower edge (56.1) integral with the main part (54) of the cowl (46) as well as an upper edge (56.2) configured to cooperate with the main side fairing (52) of the mast (42) when the cover (46) is in the closed position; characterized in that the secondary side fairing (56) comprises at least first and second parts (62, 64) movable relative to each other, the first part (62) having a first lower edge (62.1) corresponding to the lower edge (56.1) of the secondary side fairing (56) as well as a first upper edge (62.2), the second part (64) having a second upper edge (64.1) corresponding to the upper edge (56.2) of the secondary side fairing (56) as well as a second lower edge (64.2).

2. Aircraft according to claim 1, characterized in that the second lower edge (64.2) of the second part (64) is configured to cooperate with the first upper edge (62.2) of the first part (62).

3. Aircraft according to the preceding claim, characterized in that the first and second parts (62, 64) of the secondary lateral fairing (56) are connected by at least one articulation (74) which has a pivot axis (A74).

4. Aircraft according to the preceding claim, characterized in that each first articulation (48) comprises a pivot axis (A48), the first and second pivot axes (A48, A74) being merged.

5. Aircraft according to one of claims 3 to 4, characterized in that each second articulation (74) comprises at least one first wing (76.1) integral with the first part (62) and comprising a first through-orifice, at least one second wing (76.2) integral with the second part (64) and comprising a second through-orifice as well as a cylindrical rod (76.3) housed in the first and second through-orifices of the first and second wings (76.1, 76.2) and forming the second pivot axis (A74).

6. Aircraft according to the preceding claim, characterized in that the second wing (76.2) has a swan neck shape so as to form with the second part (64) a housing in which the first upper edge (62.2) of the first part (62) is positioned.

7. Aircraft according to one of claims 3 to 6, characterized in that the second articulation (74) comprises at least one return element configured to keep the first and second parts (62, 64) of the secondary lateral fairing (56) substantially coplanar.

8. Aircraft according to one of claims 2 to 7, characterized in that the first upper edge (62.2) of the first part (62) and the second lower edge (64.2) of the second part (64) are configured so as to overlap and be pressed, directly or indirectly, against each other when the cover (46) is in the closed position, the first upper edge (62.2) of the first part (62) being positioned between the second lower edge (64.2) of the second part (64) and the primary structure (42.1) of the mast (42).

9. Aircraft according to the preceding claim, characterized in that the aircraft comprises at least one seal and / or a wedge (70) positioned between the first upper edge (62.2) of the first part (62) and the second lower edge (64.2) of the second part (64) when the cover (46) is in the closed position.

10. Aircraft according to one of claims 8 to 9, characterized in that the first part (62) comprises a groove (72) near its first upper edge (62.2) so that the first and second parts (62, 64) of the secondary lateral fairing (56) have substantially coplanar outer faces when the cowl (46) is in the closed position.

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