AIRCRAFT ACCESS DOOR ASSEMBLY

Abstract

ACCESS DOOR ASSEMBLY FOR AN AIRCRAFT The invention relates to an access door assembly (250) for a fuselage (202) comprising a structure (210) defining an access hatch (206), an upper part (208a) and a lower part (208b) of an access door (208), hinges (410) fixed between the structure (210) and the upper part (208a) near an upper edge (408), a guide system (600) between the lower part (208b) and the structure (210) and ensuring translational guidance of the lower part (208b), upper locking means between the upper part (208a) and the lower part (208b) and / or the structure (210), and lower locking means (412) between the lower part (208b) and the structure (210). With such an arrangement, the operator can easily remove the two halves without risk of collision with the surroundings. Fig. 4

Description

Title of the invention: ACCESS DOOR ASSEMBLY FOR AN AIRCRAFT Technical field

[0001] The present invention relates to an access door assembly for an aircraft, as well as to an aircraft equipped with such an assembly. STATE OF THE PRIOR ART

[0002] For the maintenance of an aircraft, an operator must be able to easily access the technical elements which are housed behind the panels constituting the fuselage of the aircraft.

[0003] To facilitate this access, access hatches are arranged along the fuselage and they are closed by access doors fixed by removable fixing means to the structure of the aircraft.

[0004] [Fig. 1] shows a section through a vertical plane of an aircraft 100 of the state of the technical. The aircraft 100 comprises a fuselage 102 which comprises a frame 101 and aerodynamic panels fixed on the frame 101. The fuselage 102 contains two tanks 104, in particular dihydrogen tanks.

[0005] To carry out maintenance on the tanks 104, the fuselage 102 has an access hatch 106 which is made through the chassis 101 and which is closed by an access door 108 mounted movably on the chassis 101. The access hatch 106 extends generally on either side of a horizontal plane XY passing through the center of the fuselage 102 and over a certain height to allow an operator access to the interior of the fuselage 102.

[0006] This access hatch 106 and the associated access door 108 are arranged at a certain height relative to the ground 50, which requires the use of a boarding staircase 52.

[0007] This access hatch 106 and the associated access door 108 are arranged on the side of the tank 104.

[0008] There are currently different types of access doors 108 which do not allow easy access to the interior of the fuselage 102.

[0009] There are access doors 108 that open inwards (arrow 54), but with such an access door 108 there is a risk of collision with the tank 104 and the space for maneuvering the access door 108 is small.

[0010] There are access doors 108 which open outwards (arrow 56) by rotation around a hinge axis arranged horizontally in the upper part of the access door 108, but with such an access door 108, there is a risk of collision with boarding staircase 52.

[0011] There are access doors 108 which open outwards (arrow 58) by rotation about a hinge axis arranged vertically on one side of the access door 108, but with such an access door 108 there is also a risk of collision with the boarding stairs 52. Statement of the invention

[0012] An object of the present invention is to provide an access door assembly for an aircraft which does not have the drawbacks of the state of the art and which makes it possible to free access to an access hatch without risk of collision with the environment.

[0013] For this purpose, an access door assembly is proposed for an aircraft fuselage having a chassis, said assembly comprising:

[0014] - a structure delimiting an access hatch and intended to be secured to said chassis,

[0015] - an access door comprising an upper part and a lower part,

[0016] - hinges fixed between the structure and the upper part in the vicinity of an edge upper part of the upper part and having a horizontal hinge axis,

[0017] - a guidance system arranged between the lower part and the structure and ensuring a translational guidance of the lower part relative to the structure, parallel to a translational direction intended to be oriented upwards and outwards from the fuselage when the access door is opened,

[0018] - upper locking means which are mounted on the upper part and which are movable between a locking position in which they lock the upper part with the lower part and / or the structure and an unlocking position where they do not lock the upper part, and

[0019] - lower locking means which are mounted on the lower part and which are movable between a locking position in which they lock the lower part with the structure and an unlocking position where they do not lock the lower part.

[0020] With such an arrangement, the operator can remove the two halves easily without risk of collision with the environment.

[0021] Advantageously, the lower locking means comprise, for each side of the lower part, at least one bolt mounted movably on the lower part and a strike plate integral with the structure where each bolt is movable between a locked position and an unlocked position, a handle mounted movably on the lower part between a first position corresponding to the locked position of the bolts and a second position corresponding to the unlocked position of the bolts, and, for each bolt, a transmission system arranged to transmit the movement of the handle to said bolt.

[0022] Advantageously, the handle is mounted to be able to rotate about an opening axis, for each bolt, the lower part has guides arranged to guide said bolt in translation perpendicular to the opening axis, each transmission system takes the form of a connecting rod, one end of which is mounted to be able to rotate on the handle about an axis parallel to the opening axis and one end of which is mounted to be able to rotate on the bolt about an axis parallel to the opening axis, and the articulation of each connecting rod to the handle is offset relative to the opening axis.

[0023] Advantageously, the guide system comprises a groove fixed to the structure or to the lower part, where the groove extends parallel to the translation direction and a rib fixed respectively to the lower part or to the structure and extending parallel to the translation direction, where the rib is slidably mounted inside the groove.

[0024] Advantageously, the access door assembly comprises at least one stop system arranged at a lower part of the lower part, each stop system comprises a receptacle secured to the structure and whose opening is oriented upwards, and a pin secured to the lower part where the pin is received in the receptacle when the lower part is replaced.

[0025] The invention also proposes an aircraft comprising a fuselage with a chassis and a door assembly according to one of the preceding variants where the structure is integral with said chassis. Brief description of the drawings

[0026] The above-mentioned features 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:

[0027] [Fig-1] is a schematic representation seen in section through a vertical plane of an aircraft of the state of the art,

[0028] [Fig.2] is a top view of an aircraft according to the invention,

[0029] [Fig.3] is a schematic representation seen in section along line II-II of the [Fig.2] of the aircraft according to the invention,

[0030] [Fig.4] is a perspective view of an access door for an assembly according to the invention,

[0031] [Fig.5] is a top and sectional view of lower locking means for an assembly according to the invention,

[0032] [Fig.6] is a perspective view of a guidance system for an assembly according to the invention, and

[0033] [Fig.7] is a perspective view of a support system for an assembly according to the invention.

[0034] DETAILED DESCRIPTION OF EMBODIMENTS

[0035] In the following description, and by convention, X is the longitudinal direction of the aircraft, Y is the transverse direction which is horizontal when the aircraft is on the ground, and Z is the vertical direction which is vertical when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.

[0036] [Fig. 2] shows an aircraft 200 according to the invention which comprises a fuselage 202 inside which are arranged, here at the rear, two tanks 204, for example dihydrogen tanks to supply for example engines of the aircraft 200. Each tank 204 here takes the form of a cylinder whose axis is parallel to the longitudinal direction X.

[0037] The fuselage 202 comprises a frame 201 on the outside of which are fixed panels forming an aerodynamic surface of the fuselage 202.

[0038] The fuselage 202 comprises, for each tank 204, an access door assembly 250 according to the invention and which comprises a structure 210 delimiting an access hatch (206, [Fig. 3]) and an access door 208 which is movable between an open position in which it does not block the access hatch 206 and a closed position in which it blocks the access hatch 206.

[0039] The structure 210 has a frame and is integral with the chassis 201 or constitutes a part thereof.

[0040] The outer surface of the access door 208 constitutes one of the panels of the fuselage 202 and is therefore located here on the side of the fuselage 202, along the tank 204.

[0041] [Fig. 3] shows the operation of opening the access door 208 which closes the access hatch 206.

[0042] The access door 208 comprises an upper portion 208a and a lower portion 208b disposed below the upper portion 208a. Here, each portion 208a-b extends generally over half the total height of the access door 208.

[0043] [Fig.4] shows the access door 208 with the upper part 208a open and the lower part 208b closed.

[0044] The upper part 208a is mounted articulated on the structure 210 by means of hinges 410 of the assembly 250. The hinges 410 are fixed between the structure 210 and the upper part 208a in the vicinity of an upper edge 408 of the upper part 208a and have a horizontal hinge axis 306. The upper part 208a thus opens outwards and upwards by rotation (arrow 32) around the hinge axis 306. Due to the reduced extent of the upper part 208a, there is no risk of collision with the boarding stairs 52 or the tank 204.

[0045] The assembly 250 also comprises a guidance system (600, [Fig.6]) which is arranged between the lower part 208b and the structure 210 and provides guidance in translation of the lower part 208b relative to the structure 210 parallel to a translation direction (arrow 34) which is oriented upwards and outwards from the fuselage 202 when the access door 208 is opened. The removal of the lower part 208b is then carried out by sliding upwards and outwards from the fuselage 202 and there is no risk of collision with the boarding stairs 52 or the tank 204.

[0046] The access door 208 is replaced in the reverse manner, that is to say by replacing the lower part 208b parallel to the translation direction 34 but in the opposite direction, and by tilting the upper part 208a around the hinge axis 306 but in the opposite direction.

[0047] The assembly 250 comprises locking means 402, 412, embodiments of which are described below and which are accessible from outside the fuselage 202.

[0048] There are upper locking means 402 which are mounted on the upper part 208a and which are movable between a locking position in which they lock the upper part 208a with the lower part 208b and / or the structure 210 and an unlocking position where they do not lock the upper part 208a which is then free to pivot.

[0049] There are lower locking means 412 which are mounted on the lower part 208b and which are movable between a locking position in which they lock the lower part 208b with the structure 210 and an unlocking position where they do not lock the lower part 208b which is then free to move.

[0050] With such an arrangement, the access door 208 can be easily removed and replaced without risk of collision with the environment.

[0051] Removing the access door 208 thus consists of moving the upper locking means 402 into the unlocking position, pivoting the upper part 208a upwards, moving the lower locking means 412 into the unlocking position and pulling the lower part 208b upwards. Replacing the access door 208 thus consists of pushing the lower part 208b downwards, moving the lower locking means 412 into the locking position, pivoting the upper part 208a downwards and moving the upper locking means 402 into the locking position.

[0052] There are here four upper locking means 402, with two which lock onto the lower part 208b and two which lock onto the structure 210. Each upper locking means 402 takes for example the form of a lock with a bolt mounted movably on the upper part 208a and a striker 404 secured to the lower part 208b or to the structure 210. Each bolt is movable from the outside of the upper part 208a between a locked position and an unlocked position by means of a suitable handle 406.

[0053] The rotation of the upper part 208a around the hinge axis 306 is achieved here by means of swan-neck fittings 410 distributed along the upper edge 408 of the upper part 208a and forming the hinges.

[0054] [Fig.4] also shows a portion of the lower locking means 412.

[0055] [Fig.5] shows a top view and a section through a horizontal plane of the means lower locking elements 412 at the level of a strip 209 arranged in the upper part of the lower part 208b.

[0056] The lower locking means 412 comprise, for each side of the lower part 208b, that is to say here at the front and at the rear relative to the longitudinal direction X, at least one bolt 412a mounted movably on the lower part 208b and a striker 412b secured to the structure 210. Each bolt 412a is movable between a locked position ([Fig.5] on the left) and an unlocked position ([Fig.5] on the right). The two bolts 412a simultaneously assume the same locked or unlocked position, but for the sake of explanation, [Fig.5] has been divided into two with a bolt 412a in the locked position on the left and a bolt 412a in the unlocked position on the right. In the embodiment of the invention presented here, there are two bolts 412a at the level of the strip 209, but there could be several on the height of the lower part 208b.

[0057] In the locked position, the bolt 412a is housed in the striker 412b to block the lower part 208b and in the unlocked position, the bolt 412a is not housed in the striker 412b to release the lower part 208b.

[0058] The lower locking means 412 also comprise a handle 412c which is mounted to move on the strip 209 of the lower part 208b between a first position corresponding to the locked position of the bolts 412a and a second position corresponding to the unlocked position of the bolts 412a.

[0059] The lower locking means 412 also comprise, for each bolt 412a, a transmission system 412d arranged to transmit the movement of the handle 412c to said bolt 412a.

[0060] In the embodiment of the invention presented in [Fig.5], the transition from the first position to the second position is carried out by rotation of the handle 412c around an opening axis 10 which is here vertical.

[0061] Each bolt 412a moves perpendicular to the opening axis 10, that is to say here horizontally and generally parallel to the longitudinal direction X. To this end, each bolt 412a is guided in translation by guides 502 secured to the strip 209 of the lower part 208b and each transmission system 412d takes the form of a connecting rod 504, one end of which is mounted mobile in rotation on the handle 412c and one end of which is mounted to rotate on the bolt 412a. The two rotations take place around axes parallel to the opening axis 10. The articulation of each connecting rod 504 to the handle 412c is offset relative to the opening axis 10 in order to form a lever arm which pulls or pushes the connecting rod 504 depending on the direction of rotation of the handle 412c.

[0062] [Fig. 6] shows an embodiment of a guidance system 600 ensuring the guidance of the lower part 208b parallel to a translation direction 34. There is a guidance system 600 on each side of the lower part 208b, that is to say here at the front and at the rear relative to the longitudinal direction X.

[0063] The guide system 600 comprises a groove 602 fixed to the structure 210 where the groove 602 extends parallel to the translation direction 34 and a rib 604 fixed on the side of the lower part 208b and also extending parallel to the translation direction 34, where the rib 604 is slidably mounted inside the groove 602.

[0064] It is also possible to reverse the position of the groove 602 and the rib 604, that is to say that the guide system 600 comprises a groove 602 fixed to the structure 210 or to the lower part 208b, where the groove 602 extends parallel to the translation direction 34 and a rib 604 fixed respectively to the lower part 208b or to the structure 210 and extending parallel to the translation direction 34, where the rib 604 is slidably mounted inside the groove 602.

[0065] To ensure that the lower part 208b stops in translation when it is replaced, the access door assembly 250 comprises at least one stop system 700 shown in [Fig.7] and arranged at the lower part of the lower part 208b.

[0066] The stop system 700 comprises a receptacle 702 secured to the structure 210 and a pin 704 secured to the lower part 208b. The opening of the receptacle 702 is oriented upwards so as to receive the pin 704 when the lower part 208b is replaced to close the access hatch 206.

[0067] To ensure the sealing of the fuselage 202, seals are arranged between the structure 210 and the upper part 208a and the lower part 208b as well as between the upper part 208a and the lower part 208b.

[0068] Although the access door assembly 250 has been more particularly described in the case of the presence of a dihydrogen tank 204, it can be installed in other locations of the fuselage 202.

Claims

Claims

1. Access door assembly (250) for a fuselage (202) of an aircraft (200) having a frame (201), said assembly (250) comprising: - a structure (210) delimiting an access hatch (206) and intended to be secured to said frame (201), - an access door (208) comprising an upper part (208a) and a lower part (208b), - hinges (410) fixed between the structure (210) and the upper part (208a) in the vicinity of an upper edge (408) of the upper part (208a) and having a horizontal hinge axis (306), - a guide system (600) arranged between the lower part (208b) and the structure (210) and ensuring translational guidance of the lower part (208b) relative to the structure (210) parallel to a translation direction (34) intended to be oriented upwards and outwards from the fuselage (202) when the access door (208) is opened,- upper locking means which are mounted on the upper part (208a) and which are movable between a locking position in which they lock the upper part (208a) with the lower part (208b) and / or the structure (210) and an unlocking position where they do not lock the upper part (208a), and - lower locking means (412) which are mounted on the lower part (208b) and which are movable between a locking position in which they lock the lower part (208b) with the structure (210) and an unlocking position where they do not lock the lower part (208b).,

2. Access door assembly (250) according to claim 1, characterized in that the lower locking means (412) comprise, for each side of the lower part (208b), at least one bolt (412a) mounted movably on the lower part (208b) and a striker (412b) integral with the structure (210) where each bolt (412a) is movable between a locked position and an unlocked position, a handle (412c) mounted movably on the lower part (208b) between a first position corresponding to the locked position of the bolts (412a) and a second position corresponding to the unlocked position of the bolts (412a), and, for each bolt (412a), a transmission system (412d) arranged to transmit the movement of the handle (412c) to said bolt (412a).

3. Access door assembly (250) according to claim 2, characterized in that the handle (412c) is mounted to rotate about an opening axis (10), in that for each bolt (412a), the lower part (208b) has guides (502) arranged to guide said bolt (412a) in translation perpendicular to the opening axis (10), in that each transmission system (412d) takes the form of a connecting rod (504) one end of which is mounted to rotate on the handle (412c) about an axis parallel to the opening axis (10) and one end of which is mounted to rotate on the bolt (412a) about an axis parallel to the opening axis (10), and in that the articulation of each connecting rod (504) to the handle (412c) is offset from the opening axis (10).

4. Access door assembly (250) according to one of claims 1 to 3, characterized in that the guide system (600) comprises a groove (602) fixed to the structure (210) or to the lower part (208b), where the groove (602) extends parallel to the translation direction (34) and a rib (604) fixed respectively to the lower part (208b) or to the structure (210) and extending parallel to the translation direction (34), where the rib (604) is slidably mounted inside the groove (602).

5. Access door assembly (250) according to one of claims 1 to 4, characterized in that it comprises at least one stop system (700) arranged at a lower part of the lower part (208b), in that each stop system (700) comprises a receptacle (702) secured to the structure (210) and whose opening is oriented upwards, and a pin (704) secured to the lower part (208b) where the pin (704) is received in the receptacle (702) when the lower part (208b) is replaced.

6. Aircraft (200) comprising a fuselage (202) with a frame (201) and a door assembly (250) according to one of the preceding claims wherein the structure (210) is integral with said frame (201).

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