ARRANGEMENT FOR AN AIRCRAFT, SAID ARRANGEMENT WITH A MAST AND A TANK CONTAINING AN EXTINGUISHING AGENT

Description

TECHNICAL FIELD

[0001] The present invention relates to an assembly for an aircraft, said assembly comprising a mast and a tank containing an extinguishing agent, as well as an aircraft comprising at least one such assembly. STATE OF THE PRIOR ART

[0002] An aircraft typically comprises at least one nacelle inside which is arranged an engine, for example of the turbojet type. The nacelle and the engine are attached to the structure of the aircraft by means of a mast fixed under the wing of the aircraft.

[0003] To prevent damage to the aircraft structure when the engine catches fire, the aircraft is equipped with a fire-fighting system that consists of two tanks.

[0004] There Fig. 5 shows a state-of-the-art assembly 800 which comprises a mast 801 and two tanks 802 which are installed in the mast 801 and which each contain an extinguishing agent. Each tank 802 is here spherical and for each tank 802, the mast 801 has an opening 804 which passes through a side wall of the mast 801 and through which the tank 802 is introduced and fixed inside the mast 801.

[0005] Each tank 802 is equipped with a discharge head 806 which includes a seal that closes the tank 802 and an explosive cartridge that destroys the seal when activated. For each tank 802, the fire suppression system also includes a discharge pipe 808 that extends inside the mast 801 between the discharge head 806 and the engine. The destruction of the seal allows the release of the extinguishing agent which then flows or escapes in the discharge pipe 808 towards the engine.

[0006] For environmental reasons, currently used fire extinguishers, such as Halon, must be replaced with newer fire extinguishers. These newer fire extinguishers require a larger volume to perform their function, and therefore each 802 tank must be enlarged.

[0007] Each tank 802 then becomes heavier and the space inside the mast 801 remains restricted, handling and positioning the tank 802 becomes difficult. Document US2021 / 188457 discloses a tank according to the prior art.

[0008] Therefore, it is necessary to find a different installation to improve the existing installation in order to facilitate the installation and removal of each tank. STATEMENT OF THE INVENTION

[0009] An object of the present invention is to provide an assembly for an aircraft, wherein said assembly comprises a mast and at least one tank containing an extinguishing agent, and for the or each tank a system which ensures improved installation of the tank in the mast. For this purpose, an assembly for an aircraft is provided, said assembly comprising: a mast extending in a longitudinal direction and comprising a frame and two side walls arranged on either side of the frame, each provided with an opening, at least one tank comprising fixing means and intended to contain an extinguishing agent, for each tank, a support comprising two support elements and offset along the longitudinal direction relative to said openings, where each support element has a first bearing face oriented upwards and on which the fixing means bear, where each support element has a proximal end on the side of said openings and a distal end on the side opposite said openings, where each proximal end is fixed to the frame by at least one first fixing means which ensures removable fixing of said proximal end,where each distal end is mounted so as to be able to rotate on the chassis around a horizontal axis of rotation perpendicular to the longitudinal direction and where each support element is movable between a position of use in which the associated first bearing face is horizontal and a position of installation in which the first bearing face is tilted downwards, for each tank and for each support element, fixing elements which ensure the fixing of the means for fixing said tank to said support element.

[0010] Such an assembly allows easy removal and installation of the tank inside the mast. Advantageously, the assembly comprises, for each support element, a stop against which said support element bears in the installation position. Advantageously, each first fixing means takes the form, at the proximal end, of a bolt comprising a first nut fixed to the frame and a first clamping screw which screws into the first nut through a first bore of the associated support element.

[0011] Advantageously, the screw head of each first clamping screw is accessible from inside the chassis between the support elements.

[0012] Advantageously, the rotation of each support element is achieved by providing a second fixing means which takes the form, at the distal end, of a bolt comprising a second nut fixed to the frame and a second clamping screw which screws into the second nut through a second bore in the support element. Advantageously, the screw head of each second clamping screw is accessible from inside the frame between the support elements.

[0013] Advantageously, the assembly comprises at the distal end of each support element, a first fixing means comprising a bolt with a first nut fixed to the frame and a first clamping screw which screws into the first nut through a first bore of the associated support element.

[0014] Advantageously, at each distal end, the first fixing means is arranged below the second fixing means.

[0015] Advantageously, each first support face is equipped with at least one step arranged so that in the installation position, a fixing means is located at the rear of a step relative to the downward direction of the first support face.

[0016] The invention also proposes an aircraft comprising an assembly according to one of the preceding variants. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above-mentioned and other features of the invention will become more clearly apparent from the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which: [ Fig. 1 ] is a side view of an aircraft according to the invention, [ Fig. 2 ] is a side view of assemblies according to the invention, [ Fig. 3 ] is a perspective view of a set of the Fig. 2 , [ Fig. 4 ] is a perspective view of a detail of the installation of a tank on an assembly according to the invention, and [ Fig. 5 ] is a perspective view of a set of the state of the art. DETAILED PRESENTATION OF IMPLEMENTATION METHODS

[0018] There Fig. 1 shows an aircraft 10 which comprises a fuselage 11 on each side of which is fixed a wing 13 which carries an engine 14 such as for example a dual-flow turbojet.

[0019] For each engine 14, the aircraft 10 also includes a mast 12 which ensures the attachment of the engine 14 under the wing 13.

[0020] In the following description, terms relating to a position are taken with reference to an aircraft in a normal flight position, that is to say as it is represented on the Fig. 1 .

[0021] In the following description, and by convention, we call X the longitudinal direction of the mast which supports the engine and which is parallel to the longitudinal axis of the aircraft and oriented forwards, we call Y the transverse direction which is horizontal when the aircraft is on the ground, and Z 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.

[0022] On the other hand, the terms "front" and "rear" are to be considered in relation to a direction of advancement of the aircraft 10 during operation of the engine 14, this direction being represented schematically by the arrow F.

[0023] For each engine 14, the aircraft 10 comprises a fire-fighting system 100 which comprises at least one tank 102a-b filled with an extinguishing agent and, for each tank 102a-b, a discharge pipe 104 which extends between said tank 102a-b and the engine 14 supported by said mast 12.

[0024] As with the prior art, the tank 102a is equipped with a discharge head which is arranged to release the extinguishing agent to the discharge line 104 when needed. Figs. 2 à 4 show an assembly 50 according to the invention which comprises the mast 12 and at least one tank 102a-b. In the embodiment of the invention presented here, there are two tanks 102a-b, but the invention applies in the same way for a single tank 102a-b. In the remainder of the description, unless otherwise specified, reference is made to a single tank 102a.

[0025] The mast 12 conventionally extends in the longitudinal direction X and comprises a structure consisting of a frame 12a and walls 12b fixed around the frame 12a. The mast 12 is generally symmetrical with respect to a vertical median plane XZ of the mast 12 which passes through the axis of the engine 14. The mast 12 takes the form of a box which comprises, among other things, a lower wall 12c, an upper wall 12d and two side walls 12b which are vertical and which extend on either side of the vertical median plane XZ of the mast 12.

[0026] The frame 12a is here made up of several profiles 104 fixed to each other and on which the walls 12b-d are fixed.

[0027] The two side walls 12b are thus fixed on either side of the frame 12a in planes which are generally vertical and parallel to the median plane.

[0028] As shown by the Figs. 2 And 3, each profile 104 here takes the form of an arch which extends in a plane generally perpendicular to the longitudinal direction X and which comprises two posts 104a-b which are oriented vertically and arranged on either side of the median plane XZ. The posts 104a-b are thus spaced apart from each other to allow free passage between them for the tank 102a. Generally speaking, the frame 12a is open to allow the tank 102a to pass between the elements which constitute said frame 12a.

[0029] Each side wall 12b is pierced with an opening 18 (seen in the background on the Fig. 2 ) which allows access to the interior of the mast 12 and the chassis 12a from the exterior of the mast 12 and the opening 18 is sized to allow the passage of the tank 102a. The two openings 18 are arranged opposite each other with respect to the median plane XZ. As shown in the Fig. 4 , the tank 102a is equipped with the fixing means 106 which are arranged on either side of the median plane XZ when the tank 102a is in place. As explained below, when the tank 102a is placed in the mast 12 through the opening 18, the fixing means 106 are accessible from each opening 18. The fixing means 106 are here tabs and they cooperate with fixing elements 108 to ensure the fixing of the tank 102a inside the mast 12 when the tank 102a is in place. The assembly 50 also comprises a support 111a-b which is mounted inside the frame 12a, here between two neighboring arches. Of course, when there are several tanks 102a-b, there is one support 111a-b per tank 102a-b.

[0030] In the embodiment of the invention shown in the Figs. 2 à 4 , the support 111a-b comprises two support elements 110a-b, each extending here parallel to the longitudinal direction X. Each support element 110a-b here has a first bearing face 113 oriented upwards and each fixing means 106 bears on a first bearing face 113 by a second bearing face which it has and which is oriented downwards. Thus, when the reservoir 102a-b is in place on the support element 110a-b, each second bearing face bears against a first bearing face 113.

[0031] The fixing elements 108 ensure the fixing of the fixing means 106 of the tank 102a to a support element 110a-b and each takes for example the form of a screw which screws into the support element 110a-b in a bore provided for this purpose by passing through the fixing means 106.

[0032] The support 111a-b is offset along the longitudinal direction X relative to the openings 18, and as shown in Fig. 2 , there is a support 111a which is forward relative to the openings 18 and a support 111b which is rearward relative to the openings 18. It is thus possible to arrange a reservoir 102a in front of the openings 18 and one at the rear. Each support element 110a-b has a proximal end 112a which is on the side of the openings 18 and a distal end 112b which is on the side opposite said openings 18.

[0033] Thus, the support 111a has its proximal ends 112a towards the rear and its distal ends 112b towards the front, and the support 111b has its proximal ends 112a towards the front and its distal ends 112b towards the rear.

[0034] Each proximal end 112a is fixed to the frame 12a, here to one of the two posts 104a-b constituting a profile 104, by at least one first fixing means 114 which ensures removable fixing of the proximal end 110a to the frame 12a.

[0035] In the embodiment of the invention shown in the Fig. 2 , there are two first fastening means 114 per proximal end 112a to provide redundancy, and each here is a bolt comprising a first nut 114a fixed to the frame 12a and a first clamping screw 114b which screws into the first nut 114a through a first bore 114c of the support element 110a-b. The screw head of each first clamping screw 114b is accessible from inside the frame 12a between the support elements 110a-b so that the operator is not hindered by the side walls 12b. The heads of the first clamping screws 114b of one support element 110a-b are thus opposite the heads of the first clamping screws 114b of the other support element 110b-a.

[0036] Each distal end 112b is mounted to rotate on the frame 12a around a horizontal axis of rotation 60 perpendicular to the longitudinal direction X. Each support element 110a-b is thus able to rotate alternately between a position of use ( Fig. 2 ) in which the first associated support face 113 is horizontal and in which the support element 110a-b is fixed by the first fixing means 114 and a positioning position ( Fig. 3 ) in which the first bearing face 113 is tilted downwards and in which the support element 110a-b is not fixed by the first fixing means 114.

[0037] Thus, when a tank 102a-b is to be put in place, each first fixing means 114 is removed, to release the rotation of each support element 110a-b which, due to its weight, pivots downwards around the axis of rotation 60 as shown by the arrow 62 to arrive in the position of installation. In this position, the first bearing face 113, i.e. the top of the support element 110a-b, is oriented towards the openings 18, which facilitates the positioning of the reservoir 102a-b on the support elements 110a-b, and more particularly the first bearing faces 113, and the positioning of the fixing elements 108 on the fixing means 106. Each support element 110a-b can then be raised into its position of use, i.e. with the first bearing face 113 in a horizontal position (in the opposite direction to the arrow 62), and each first fixing means 114 is put back in place to fix the position of the support element 110a-b.

[0038] Removing a 102a-b tank is done in the same way.

[0039] Access to the fixing elements 108 and to the first fixing means 114 is thus facilitated, which limits the risks for an operator installing a heavy and bulky tank 102a-b. To limit the rotation of each support element 110a-b downwards and maintain the installation position, the assembly 50 comprises, for each support element 110a-b, a stop 120 against which the support element 110a-b bears in the installation position. In the embodiment of the invention presented here, it is the proximal end 112a of the support element 110a-b which bears against the stop 120, here by means of a tab in which the first bores 114c of the first fixing means 114 are made.

[0040] In the embodiment of the invention presented in the Fig. 3 , the stop 120 takes the form of a fold of a fitting 122 secured to the frame 12a, here of a post 104a-b, where the fitting 122 also carries here the first nuts 114a of the first fixing means 114.

[0041] According to a particular embodiment, each stop 120 is arranged so that in the installation position, the first support face 113 has an angle of 20° downwards with the horizontal.

[0042] In the embodiment of the invention presented to the Figs. 2 And 3, the rotation of each support element 110a-b is achieved by placing at the distal end 112b of each support element 110a-b, a second fixing means 126 which takes the form of a bolt comprising a second nut 126a fixed to the frame 12a and a second clamping screw 126b which screws into the second nut 126a through a second bore of the support element 110a-b. The screw head of each second clamping screw 126b is also accessible from inside the frame 12a between the support elements 110a-b.

[0043] In the use position, the second clamping screw 126b is tightened to help hold the support member 110a-b and in the installation position, the second clamping screw 126b is loosened but remains engaged with the second nut 126a to form a shaft about which the support member 110a-b pivots.

[0044] To provide redundancy in securing the distal end 112b, the assembly 50 comprises at the distal end 112b of each support element 110a-b, a first securing means 114, i.e. here, a bolt with a first nut 114a secured to the frame 12a and a first clamping screw 114b which screws into the first nut 114a through a first bore 114c of the associated support element 110a-b. The first clamping screw 114b unscrews entirely to be removed to allow rotation of the support element 110a-b.

[0045] For better access in the installation position, in the embodiment of the invention shown in the Fig. 3 , at the distal end 112b, the first fixing means 114 is arranged below the second fixing means 126.

[0046] To ensure that the reservoir 102a is held on the support elements 110a-b in the position of installation and to prevent the fixing means 106 from moving along the first bearing faces 113 due to the angle of inclination, each first bearing face 113 is equipped with at least one step 130. When the reservoir 102 is being installed, it is installed in such a way that on each first bearing face 113, a fixing means 106 is located at the rear of a step 130 relative to the downward direction of the first bearing face 113 in the position of installation, to be blocked by the latter.

[0047] In the embodiment of the invention shown in the Figs. 3 And 4, each support element 110a-b comprises a lower beam 115a which comprises the first bores 114c and the second bore and an upper beam 115b fixed on the lower beam 115a by means of spacers and having the first bearing face 113.

Claims

1. Assembly (50) for an aircraft (10), said assembly (50) having: - a pylon (12) extending along a longitudinal direction (X) and having a chassis (12a) and two side walls (12b) disposed on either side of the chassis (12a), each provided with an aperture (18), - at least one reservoir (102a-b), which has fastening means (106) and is intended to contain an extinguishing agent, - for each reservoir (102a-b), a support (111a-b) which has two support elements (110a-b), characterized in that each support (111a-b) is offset along the longitudinal direction (X) with respect to said apertures (18), wherein each support element (110a-b) has an upwardly facing first bearing face (113) against which the fastening means (106) bear, wherein each support element (110a-b) has a proximal end (112a) at said apertures (18) and a distal end (112b) on the opposite side to said apertures (18), wherein each proximal end (112a) is fastened to the chassis (12a) by at least one first fastening means (114) which ensures removable fastening of said proximal end (112a), wherein each distal end (112b) is mounted on the chassis (12a) rotatably about a horizontal axis of rotation (60) perpendicular to the longitudinal direction (X), and wherein each support element (110a-b) can be moved between a use position, in which the associated first bearing face (113) is horizontal, and a fitted position, in which the first bearing face (113) is tilted downwards, - for each reservoir (102a-b) and for each support element (110a-b), fastening elements (108) which fasten the fastening means (106) of said reservoir (102a-b) to said support element (110a-b).

2. Assembly (50) according to Claim 1, characterized in that it has, for each support element (110a-b), a stop (120) against which said support element (110a-b) bears in the fitted position.

3. Assembly (50) according to either of Claims 1 and 2, characterized in that each first fastening means (114) takes the form, at the proximal end (112a), of a bolt having a first nut (114a) fastened to the chassis (12a) and a first clamping screw (114b) which is screwed in the first nut (114a) through a first bore (114c) in the associated support element (110a-b).

4. Assembly (50) according to Claim 3, characterized in that the screw head of each first clamping screw (114b) is accessible from the inside of the chassis (12a) between the support elements (110a-b).

5. Assembly (50) according to one of Claims 1 to 4, characterized in that the rotation of each support element (110a-b) is realized by the fitting of a second fastening means (126) which takes the form, at the distal end (112b), of a bolt having a second nut (126a) fastened to the chassis (12a) and a second clamping screw (126b) which is screwed in the second nut (126a) through a second bore in the support element (110a-b).

6. Assembly (50) according to Claim 5, characterized in that the screw head of each second clamping screw (126b) is accessible from the inside of the chassis (12a) between the support elements (110a-b).

7. Assembly (50) according to either of Claims 5 and 6, characterized in that it has, at the distal end (112b) of each support element (110a-b), a first fastening means (114) having a bolt with a first nut (114a) fastened to the chassis (12a) and a first clamping screw (114b) which is screwed in the first nut (114a) through a first bore (114c) in the associated support element (110a-b).

8. Assembly (50) according to Claim 7, characterized in that, at each distal end (112b), the first fastening means (114) is disposed below the second fastening means (126).

9. Assembly (50) according to one of Claims 1 to 8, characterized in that each first bearing face (113) is equipped with at least one step (130) arranged such that, in the fitted position, a fastening means (106) is located to the rear of a step (130) in relation to the descending direction of the first bearing face (113).

10. Aircraft (10) having an assembly (50) according to one of the preceding claims.