FR3043655A1 - TRAPPER FOR HINGING A MATT OF AN AIRCRAFT NACELLE EQUIPPED WITH A MOBILE RABAT - Google Patents

Abstract

The invention relates to a hatch (32) for access to at least one hinge (28) of a mast of an aircraft nacelle, the hatch (32) delimiting a slot provided for the passage of said hinge (28). ) and the flap (32) being associated with a flap (36) which is pivotally mounted about a longitudinal axis (B), between a closed position in which the flap (36) covers the lumen (34), and a position opening in which the flap (36) discovers the light (34), characterized in that the flap (36) has an anchoring portion (38) which is integral in movement of the door (32), a movable portion (40). ) which is designed to cover the lumen (34), and an elastically deformable intermediate portion (42) which connects the movable portion (40) to the anchor portion (38) of the flap (36) to form a hinge .

Description

The invention relates to a hatch for access to hinges of a mast of an aircraft nacelle, equipped with a movable flap.

An aircraft is driven by several turbojet engines each housed in a nacelle housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped.

A turbojet engine nacelle generally has a substantially tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of said turbojet engine, a downstream section intended to surround the combustion chamber of the turbojet engine and possibly incorporating combustion engine means. thrust reversal, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.

The nacelle is designed to be fixed on the structure of the aircraft, for example on the underside of a wing via a mast, or pylon.

In general, the structure of an inverter comprises an inverter cover movable between, on the one hand, an inverted jet position in which it opens in the nacelle a passage intended for the flow of deflected air, and other on the other hand, a direct jet position in which it closes this passage.

In addition, in order to facilitate access to the interior of the nacelle for maintenance operations, the downstream section of the nacelle comprises two covers which are pivotally mounted symmetrically about a longitudinal axis, by means of hinges. which connect the upper edge of each hood to the mast.

Typically, each pivoting cover has hatches that allow access to the hinges.

To avoid a collision between the access doors and the hinges during the pivoting of the covers, each hatch defines a light that allows the passage of the associated hinge.

However, these lights form a potential passage for lightning.

In addition, the lights disturb the aerodynamic continuity of the hatch.

To avoid these inconveniences, it is known to equip each light with a flap that is pivotally mounted, between a closed position in which the flap covers the light, and an open position in which the flap discovers the light and allows the passage of the hinge through the light. The disadvantage of such an arrangement is that it requires means for hinging the flap on the hatch, such as hinges, and furthermore a proper closure of this flap is never completely guaranteed: it can be result in aerodynamic loss of the nacelle, as well as greater vulnerability to lightning.

In addition, in the particular case of hinges of the "piano" type, it has been possible to identify risks of fouling and galling.

The present invention aims in particular to solve these disadvantages and relates for this purpose to a hatch for access to at least one hinge of a mast of an aircraft nacelle, the hatch delimiting a light provided for the passage of said hinge and the hatch being associated with a flap which is pivotally mounted about a longitudinal axis, under the action of the hinge, between a closed position in which the flap covers the light, and an open position in which the flap discovers the light, characterized in that the flap has: - an anchoring portion which is integral in movement of the hatch, - a movable portion which is designed to cover the light, and - an intermediate portion which is elastically deformable and which connects the movable portion on the anchoring portion of the flap to form a hinge.

Thanks to its elasticity, this flap is adapted to deform under the action of the hinge when opening a hood of the nacelle, and to resume its initial position when closing the hood of the nacelle.

This flap memory shape saves the means of articulation, which allows to gain weight and reliability.

According to another characteristic, the anchoring portion of the flap is fixed on a lower face of the hatch, that is to say on a side turned facing the interior of the nacelle.

According to another characteristic, the anchoring portion of the flap is fixed by riveting.

According to another feature, the flap is made of a piece made of material in a shape memory material.

According to another feature, the hatch has a recessed portion forming a recess that matches the contours of the flap to allow the flap, in its closed position, to rest in alignment in the plane of the door.

According to another characteristic, the light defined by the hatch has dimensions adapted to prevent a lightning strike against the hinge in case of loss of the flap.

Preferably, the light defines a passage less than five centimeters.

According to another characteristic, the movable portion of the flap extends transversely globally to the edge of the hatch.

This feature allows the flap to cooperate with a seal that extends along the edge of the hatch.

According to another characteristic, the hatch is mounted on a movable hood of the nacelle. The invention also relates to an aircraft turbojet engine nacelle equipped with a hatch of the type described above. Other characteristics and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended drawings in which: FIG. 1 is a schematic perspective view illustrating a turbojet engine nacelle; which is mounted on a wing by a mast; - Figure 2 is a detail view which illustrates a flap mounted on a light defined by a hatch for access to a hinge of the mast of Figure 1; - Figure 3 is a detail view similar to that of Figure 2, which illustrates the light defined by the door, without the flap; - Figure 4 is a detail view in cross section, which illustrates the flap in its closed position; - Figure 5 is a detail view in cross section, which illustrates the flap in its open position.

To clarify the description and the claims, the longitudinal, vertical and transverse terminology will be adopted in a nonlimiting manner with reference to the L, V, T trihedron indicated in the figures, the L axis of which is parallel to the axis of the nacelle.

In all of these figures, identical or similar references represent identical or similar organs or sets of members.

FIG. 1 shows an aircraft nacelle 10 which houses a turbojet engine and which extends along a longitudinal axis A.

The nacelle 10 has a substantially tubular structure which comprises an air inlet 12 upstream of the turbojet engine, a median section 14 intended to surround a fan of the turbojet engine, a downstream section 16 intended to surround the combustion chamber of the turbojet engine and incorporating an inverter thrust (not shown), and which is terminated by an ejection nozzle 18 whose output is located downstream of the turbojet engine.

The nacelle 10 is designed to be fixed on the lower face 20 of a wing 22 by means of a mast 24.

In order to facilitate access to the interior of the nacelle 10, in particular for maintenance operations, the downstream section 16 of the nacelle 10 comprises two covers 26, or half-covers, of which only one is visible in FIG. ) type C.

Each cover 26 is pivotally mounted about a longitudinal axis, on either side of the mast 24, between a rest position shown in Figure 1 and a maintenance position (not shown) in which the cover 26 is open. and allows access to the interior of the nacelle 10. For this purpose, each cover is hinged by two hinges 28 (only one of which is shown in FIGS. 3 to 5) which connect an upper part 30 of each cover 26 to the mast 24.

The nacelle 10 has a design symmetry along a vertical and longitudinal plane of symmetry.

Also, for the sake of clarity, only half of the nacelle 10 whose cover 26 is visible in Figure 1 is described later.

The upper part 30 of the mobile hood 26 is equipped with a hatch 32 which allows access to the hinges 28.

As can be seen in Figure 3, the hatch 32 defines a slot 34 which is provided for the passage of the associated hinge 28.

Indeed, when the cover 26 is pivoted from its rest position to its maintenance position, the upper portion 30 of the cover 26 is driven towards the hinges 28, the light 34 avoiding the collision between the hatch 32 and the hinge 28 associate.

Also, the light 34 defined by the hatch 32 has dimensions adapted to prevent a lightning strike against the hinge 28 in case of loss of the flap 36.

For this purpose, the light 34 delimits a passage less than five centimeters, in any one of the transverse and longitudinal directions, thus making it possible to retain the lightning on a stop of the light 34.

Referring to Figure 2, the hatch 32 is associated with a flap 36 which is pivotally mounted about a longitudinal axis B, between a closed position in which the flap 36 covers the slot 34, and an open position in which the flap 36 discovers light 34.

More particularly, the flap 36 has an anchoring portion 38, a movable portion 40 and an intermediate portion 42 which is elastically deformable and which connects the movable portion 40 to the anchoring portion 38 of the flap 36 to form a joint.

The term "articulation" means a joint which allows relative angular displacement of the movable portion 40 and the anchoring portion 38.

As can be seen in FIG. 4, the anchoring portion 38 has the shape of a tongue which is fixed on a lower face 44 of the hatch 32, that is to say on a face turned facing inside the basket 10.

Preferably, the anchoring portion 38 is fixed by riveting on the hatch 32. Without limitation, the anchoring portion 38 of the flap 36 may also be fixed on a support other than the hatch 32, for example on a part hinge 28 which has the same kinematics as the hatch 32.

The movable portion 40 is adapted to cover the lumen 34 when the flap 36 is in its closed position, as can be seen in FIG. 2, and to discover the lumen 34 when the flap 36 is in its open position. For this purpose, as can be seen in Figure 5, when the cover 26 is driven to its maintenance position, the flap 36 is pushed by the hinge 28 associated so that the flap 36 slides on the hinge 28 and pivots upwards, thus discovering the light 34.

According to another aspect illustrated in Figure 2, the hatch 32 is delimited by an upper edge 46 which runs along the mast 24 and which cooperates with a seal (not shown) which seals at the junction between the cover 26 and the mast 24.

Also, the movable portion 40 of the flap 36 extends transversely to the upper edge 46 of the hatch 32 so that the free end edge 48 of the movable portion 40 of the flap 36 also cooperates with the seal.

This feature limits the flap flap 36, if any.

According to a preferred embodiment, the flap 36 is made of a piece made of material in a shape memory material, that is to say that the flap 36 is made in one piece unlike the other. a flap that includes a hinge connecting two independent parts.

The material used to make the flap 36 is a metallic material, for example titanium. Without limitation, the flap 36 may also be made of spring steel.

According to a preferred embodiment, the flap 36 has a thickness of 0.6 millimeters.

According to another aspect of the invention, the hatch 32 has a recessed portion forming a recess 50 which matches the contours of the flap 36 to allow the flap 36, in its closed position, to lie in alignment in the plane of the hatch 32.

The trimming 50 is for example made by stamping the hatch 32.

The present description of the invention is given by way of non-limiting example.

Claims (10)

Hatch (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10), the hatch (32) delimiting a light (34) provided for the passage of said hinge (28) and the hatch (32) being associated with a flap (36) which is pivotally mounted about a longitudinal axis (B), under the action of the hinge (28), between a closed position in which the flap (36) covers the light (34), and an open position in which the flap (36) discovers the light (34), characterized in that the flap (36) has: - an anchoring portion ( 38) which is integral in movement of the hatch (32), - a movable portion (40) which is designed to cover the light (34), and - an intermediate portion (42) which is elastically deformable and which connects the movable portion (40) on the anchoring portion (38) of the flap (36) to form a hinge. 2. Hatch (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10) according to claim 1, characterized in that the anchoring portion ( 38) of the flap (36) is fixed on a lower face of the hatch (32), that is to say on a side facing the interior of the nacelle (10). 3. Trap (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10) according to claim 2, characterized in that the anchoring portion ( 38) of the flap (36) is fixed by riveting. 4. Trap (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10) according to any one of the preceding claims, characterized in that the flap (36) is made of a piece made of material in a shape memory material. 5. Trap (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10) according to any one of the preceding claims, characterized in that it has a recessed portion forming a recess (50) that conforms to the contours of the flap (36) to allow the flap (36), in its closed position, to lie in alignment in the plane of the door (32). Trapdoor (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10) according to any one of the preceding claims, characterized in that the light (34) delimited by the hatch (32) has dimensions adapted to prevent a lightning strike against the hinge (28) in case of loss of the flap (36). 7. hatch (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10) according to claim 6, characterized in that the light (34) delimits a passage less than five centimeters. 8. Trap (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10) according to any one of the preceding claims, characterized in that the portion movable (40) of the flap (36) extends transversely generally to the edge (46) of the hatch (32). 9. Trap (32) for access to at least one hinge (28) of a mast (24) of an aircraft nacelle (10) according to any one of the preceding claims, characterized in that the hatch (32) is mounted on a hood (26) movable from the nacelle (10). 10. Nacelle (10) aircraft turbojet equipped with a hatch (32) according to any one of the preceding claims.