AIRCRAFT COMPRISING A STRUCTURE, A TANK AND MEANS OF ATTACHING THE TANK TO THE STRUCTURE

Abstract

AIRCRAFT COMPRISING A STRUCTURE, A TANK, AND MEANS FOR ATTACHING THE TANK TO THE STRUCTURE. The invention relates to an aircraft comprising a structure (112a-b), a tank (110) attached to the structure (112a-b) by means of attachments (150) which comprise, at a front portion (110a) of the tank (110), a front attachment system (152) arranged to transfer forces in the vertical direction (Z), at a rear portion (110b) of the tank (110), a rear attachment system (154) arranged to transfer forces in the vertical direction (Z) and the transverse direction (Y), between the front attachment system (152) and the rear attachment system (154), a first intermediate attachment system (156) arranged to transfer forces in the transverse direction (Y), and between the first intermediate attachment system (156) and the rear attachment system of fixing (154),a second intermediate fastening system (158) arranged to transfer forces along the longitudinal direction (X). Fig. 2,

Description

Title of the invention: AIRCRAFT COMPRISING A STRUCTURE, A TANK AND MEANS FOR FIXING THE TANK TO THE STRUCTURE Technical field

[0001] The present invention relates to an aircraft comprising a structure, a tank, in particular a dihydrogen tank, and fixing means which ensure the fixing of the tank to the structure. STATE OF THE PRIOR ART

[0002] In the case of kerosene which is used to power the engines of an aircraft, it is known to arrange the kerosene tank in a wing of the aircraft.

[0003] In order to reduce kerosene consumption in aircraft engines, it is known to use dihydrogen as fuel. The tank, which is cylindrical in shape, cannot be placed in the wings and is then arranged in the fuselage of the aircraft.

[0004] The aircraft then comprises a structure to which the tank is fixed by means fixing.

[0005] Currently, the fixing means are not optimized and it is therefore necessary to find a new arrangement. Furthermore, it is desirable to find an arrangement allowing the tank to be easily removed from the aircraft if necessary. Disclosure of the invention

[0006] An object of the present invention is to provide an aircraft comprising a structure, at least one cylindrical tank and fixing means which ensure the fixing of each tank to the structure.

[0007] For this purpose, an aircraft is proposed comprising:

[0008] - a fuselage with a structure,

[0009] - at least one tank housed in the fuselage, and having a longitudinal direction tudinal, a transverse direction and a vertical direction and a vertical longitudinal median plane,

[0010] - for each tank, fixing means which ensure the fixing of the tank to the structure where the fixing means include:

[0011] - at a front part of the tank, a front fixing system arranged for transfer forces in the vertical direction,

[0012] - at the level of a rear part of the tank, a rear fixing system arranged to transfer forces in the vertical direction and the transverse direction,

[0013] - between the front fixing system and the rear fixing system, a first intermediate fixing system arranged to transfer forces in the transverse direction, and

[0014] - between the first intermediate fixing system and the rear fixing system, a second intermediate fixing system arranged to transfer forces in the longitudinal direction.

[0015] Such an arrangement makes it possible to have fixing means which are optimized in particular for the transfer of forces from the tank to the structure.

[0016] Advantageously, the structure comprises a floor above which the tank is arranged, the front fixing system comprises a front shoe fixed to the floor and on either side of the vertical longitudinal median plane, a front connecting rod fixed by a first end to the front shoe and by a second end to the tank and each front connecting rod is inscribed in a plane perpendicular to the longitudinal direction.

[0017] Advantageously, a point of attachment of the second end to the tank has with the vertical longitudinal median plane, an angle of 60° ±5°.

[0018] Advantageously, the structure comprises a hoop and the rear fixing system comprises a flange fixed to the rear of the tank, a first connecting rod fixed parallel to the transverse direction between the flange and the hoop and a second connecting rod fixed parallel to the vertical direction between the flange and the hoop.

[0019] Advantageously, the structure comprises a floor above which the tank is arranged, and the first intermediate fixing system comprises a lateral connecting rod fixed between the floor and a lower part of the tank where the lateral connecting rod is inscribed in a plane perpendicular to the longitudinal direction.

[0020] Advantageously, the structure comprises a floor above which the tank is arranged, the second intermediate fixing system comprises an intermediate shoe fixed to the floor and on either side of the vertical longitudinal median plane, an intermediate connecting rod fixed by a first end to the intermediate shoe and by a second end to the tank and each intermediate connecting rod is inscribed in a plane generally perpendicular to the vertical direction.

[0021] Advantageously, a point of attachment of the second end to the tank has, with the vertical longitudinal median plane, an angle of 20° ± 5°.

[0022] Advantageously, the second intermediate fixing system comprises a hoist ensuring fixing between the intermediate shoe and each first end.

[0023] Advantageously, the aircraft comprises a front slide secured to the tank and comprising a front guide means, an intermediate slide secured to the tank and comprising an intermediate guide means, a front guide rail secured to the front shoe and arranged to cooperate with the front guide means to provide a sliding connection of the front slide relative to the front guide rail parallel to the transverse direction and an intermediate guide rail secured to the intermediate shoe and arranged to cooperate with the intermediate guide means to provide a sliding connection of the intermediate slider relative to the intermediate guide rail parallel to the transverse direction. Brief description of the drawings

[0024] 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:

[0025] [Fig-1] is a side view of an aircraft according to the invention,

[0026] [Fig.2] is a schematic representation in side view of a reservoir and the means of fixing,

[0027] [Fig.3] is a schematic representation in bottom view of the tank and the fixing means,

[0028] [Fig.4] is a front view of a front attachment system,

[0029] [Fig.5] is a perspective view of the front attachment system,

[0030] [Fig.6] is a side view of the front attachment system,

[0031] [Fig.7] is a rear view of a second intermediate fixing system,

[0032] [Fig.8] is a perspective view of the second intermediate fixing system,

[0033] [Fig.9] is a side view of the second intermediate fixing system,

[0034] [Fig. 10] is a front view of a first intermediate fixing system, and

[0035] [Fig. 11] is a perspective view of a rear attachment system.

[0036] DETAILED DESCRIPTION OF EMBODIMENTS

[0037] In the following description, the terms relating to a position are taken with reference to an aircraft in normal flight position, that is to say as shown in [Fig.l]. The arrow F indicates the forward direction of the aircraft 100.

[0038] [Fig.l] shows an aircraft 100 which comprises a fuselage 102 on each side of which is fixed a wing 104 which carries at least one engine 106 operating with fuel such as dihydrogen or kerosene.

[0039] The fuel is stored in at least one tank 110 which is housed and secured to inside the fuselage 102 and here at the rear of the fuselage 102 by fixing means.

[0040] In the description, mention is made of a single tank 110, but there may be several, and in particular two which are arranged on either side of the median plane of the aircraft 100.

[0041] The reservoir 110 takes a shape of revolution around an axis of revolution and it has a section of circular or elliptical shape.

[0042] In the following description, and by convention, X is the longitudinal and horizontal direction of the tank 110 passing through the axis of revolution of the tank. 110, we call Y the transverse and horizontal direction and Z the vertical direction, these three directions X, Y and Z being orthogonal to each other. The tank 110 also has a vertical longitudinal median plane XZ which contains the longitudinal direction X and the vertical direction Z. The longitudinal direction X is generally parallel to the longitudinal axis of the aircraft 100.

[0043] [Fig.2] and [Fig.3] show the tank 110 and the fixing means 150 which ensure the fixing of the tank 110 to the structure 112a-b of the fuselage 102, namely a hoop 112a and a floor 112b. Conventionally, the skin of the fuselage 102 is fixed on the outside of the hoops 112a.

[0044] The tank 110 is housed in the fuselage 102.

[0045] At a front portion 110a of the tank 110 relative to the longitudinal direction X, i.e. towards the front of the aircraft 100, the fixing means 150 comprise a front fixing system 152 which is arranged to transfer forces in the vertical direction Z. A particular embodiment of the front fixing system 152 is shown in Figs. 4, 5 and 6. The front fixing system 152 is arranged under the tank 110, i.e. between the tank 110 and the floor 112b.

[0046] At a rear portion 110b of the tank 110 relative to the longitudinal direction X, i.e. towards the rear of the aircraft 100, the fixing means 150 comprise a rear fixing system 154 which is arranged to transfer forces in the vertical direction Z and the transverse direction Y. A particular embodiment of the rear fixing system 154 is shown in [Fig.l 1]. The rear fixing system 154 is arranged at the rear of the tank 110.

[0047] Between the front fixing system 152 and the rear fixing system 154, and here rather towards the front of the tank 110 relative to the longitudinal direction X, the fixing means 150 comprise a first intermediate fixing system 156 which is arranged to transfer forces in the transverse direction Y. A particular embodiment of the first intermediate fixing system 156 is shown in [Fig. 10]. The first intermediate fixing system 156 is arranged under the tank 110, that is to say between the tank 110 and the floor 112b.

[0048] Between the first intermediate fixing system 156 and the rear fixing system 154, and here rather between the middle and the rear of the tank 110 relative to the longitudinal direction X, the fixing means 150 comprise a second intermediate fixing system 158 arranged to transfer forces in the longitudinal direction X. A particular embodiment of the second intermediate fixing system 158 is shown in Figs. 7, 8 and 9. The second intermediate fixing system 158 is arranged under the tank 110, that is to say between the tank 110 and the floor 112b.

[0049] Such an arrangement allows isostatic fixing of the tank 110 to the structure 112a-b.

[0050] According to a particular embodiment of the invention, the front fixing system 152 comprises a front shoe 402 fixed to the floor 112b by any suitable fixing means.

[0051] The front fixing system 152 also comprises, on either side of the vertical longitudinal median plane XZ, a front connecting rod 403a-b fixed by a first end to the front shoe 402 and by a second end to the tank 110, here at the level of a lateral pallet 406 of the tank 110. There is thus a front connecting rod 403a to starboard and a front connecting rod 403b to port.

[0052] As shown in [Fig.5], for reasons of redundancy, each front connecting rod 403a-b is made up of two sub-connecting rods 423a-b fixed to each other. And each sub-connecting rod 423a-b is fixed to the front shoe 402 by a clevis system 420a-b whose axes are parallel to the longitudinal direction X. Each clevis system 420a-b is here made up of a female clevis of the sub-connecting rod 423a-b and a male clevis of the front shoe 402 which is inserted and fixed in the female clevis by placing at least one shaft 425.

[0053] In the same way, the two sub-connecting rods 423a-b are fixed to the tank 110 by a yoke system 420c with an axis parallel to the longitudinal direction X. The yoke system 420c is here constituted by a pair of connecting rods fixed between the tank 110, here the lateral pallet 406, and the sub-connecting rods 423a-b. The two connecting rods form a female yoke in which the two sub-connecting rods 423a-b are inserted and fixed by placing at least one shaft 427.

[0054] Each front connecting rod 403a-b is inscribed in a plane generally perpendicular to the longitudinal direction X.

[0055] According to a particular embodiment, the attachment point 404 of the second end of each front connecting rod 403a-b, here of the associated connecting rod, to the tank 110 has, with the vertical longitudinal median plane XZ, an angle of 60° ± 5°. The attachment point 404 is thus rather towards the underside of the tank 110 and on the sides relative to the vertical longitudinal median plane XZ.

[0056] According to a particular embodiment of the invention, the rear fixing system 154 comprises a flange 1102 fixed to the rear of the tank 110, a first connecting rod 1104a fixed parallel to the transverse direction Y between the flange 1102 and the hoop 112a and a second connecting rod 1104b fixed parallel to the vertical direction Z here downwards between the flange 1102 and the hoop 112a.

[0057] The hoop 112a is around the flange 1102.

[0058] The direction of the first connecting rod 1104a and the direction of the second connecting rod 1104b intersect at the longitudinal direction X.

[0059] The attachment of each connecting rod 1104a-b to the flange 1102 and to the arch 112a is carried out here by a yoke system whose axis is parallel to the longitudinal direction X. Each connecting rod 1104a-b thus has at each end a female yoke in which is inserted and fixed by the installation of a shaft 1110, a male yoke respectively of the flange 1102 and of the arch 112a.

[0060] According to a particular embodiment of the invention, the first intermediate fixing system 156 comprises a lateral connecting rod 602, a first end of which is fixed to the floor 112b, here by means of a first pallet 604 and a second end of which is fixed to a lower part of the tank 110, here by means of a second pallet 606.

[0061] The attachments of the lateral connecting rod 602 to the floor 112b and to the tank 110 are carried out here by yoke systems whose axes are parallel to the longitudinal direction X. The lateral connecting rod 602 thus has at each end a female yoke in which is inserted and fixed by the installation of a shaft 608, a male yoke respectively of the floor 112b and of the tank 110 and formed here respectively by the first pallet 604 and the second pallet 606.

[0062] The lateral connecting rod 602 is thus inscribed in a plane perpendicular to the longitudinal direction X and it is generally parallel to the transverse direction Y and under the tank 110.

[0063] According to a particular embodiment of the invention, the second intermediate fixing system 158 comprises an intermediate shoe 902 fixed to the floor 112b by any suitable fixing means.

[0064] The second intermediate fixing system 158 also comprises, on either side of the vertical longitudinal median plane XZ, an intermediate connecting rod 904a-b fixed by a first end to the intermediate shoe 902 and by a second end to the tank 110, here at the level of an intermediate pallet 907 of the tank 110. There is thus an intermediate connecting rod 904a to starboard and an intermediate connecting rod 904b to port.

[0065] The intermediate connecting rods 904a-b are inscribed in a plane generally perpendicular to the vertical direction Z.

[0066] As shown in [Fig.8], the attachment of the second end of each intermediate connecting rod 904a-b to the reservoir 110 is carried out here by a yoke system whose axis is generally parallel to the vertical direction Z. The intermediate connecting rod 904a-b thus has at its second end a female yoke in which is inserted and fixed by the installation of a shaft 909, a male yoke respectively of the reservoir 110 and formed here by the intermediate pallet 907.

[0067] In the embodiment of the invention presented here, the second intermediate fixing system 158 also comprises a hoist 908 ensuring the fixing between the intermediate shoe 902 and the first end of each intermediate connecting rod 904a-b.

[0068] The hoist 908 is mounted articulated on the intermediate shoe 902 by a pivot connection whose axis is generally parallel to the vertical direction Z. To this end, the shoe in intermediate 902 has a female yoke in which is inserted and fixed by the installation of a shaft 908a, the hoist 908 forming a male yoke.

[0069] The first end of each intermediate connecting rod 904a-b is mounted articulated on the hoist 908 by a pivot connection whose axis is generally parallel to the vertical direction Z. To this end, the first end of each intermediate connecting rod 904a-b takes the form of a female yoke in which is inserted and fixed by the installation of a shaft 908b, the hoist 908 forming a male yoke.

[0070] According to a particular embodiment, the attachment point 906 of the second end of each intermediate connecting rod 904a-b to the tank 110 has an angle of 20° ± 5° with the vertical longitudinal median plane XZ. The attachment point 906 is thus rather below the tank 110 and slightly to the sides relative to the vertical longitudinal median plane XZ,

[0071] while the point of attachment of the first end of each intermediate connecting rod 904a-b to the intermediate shoe 902 is generally in the vertical longitudinal median plane XZ.

[0072] Such an arrangement also makes it possible to ensure the evacuation of the tank 110 from the fuselage 102 through a passage 120 made through the skin of the fuselage 102 and to the side relative to the tank 110. The passage 120 is closed by a door not shown. The door is thus movable between a closed position in which the passage 120 is closed by the door and an open position in which the passage 120 is open to allow the passage of the tank 110. The movement of the tank 110 takes place parallel to the transverse direction Y.

[0073] In this particular embodiment, the aircraft 100 comprises a front slider 410 and an intermediate slider 910.

[0074] The front slide 410 is integral with the tank 110 and more particularly arranged under the tank 110 and here above the front shoe 402.

[0075] The intermediate slide 910 is also integral with the reservoir 110 and more particularly arranged under the reservoir 110 and here above the intermediate shoe 902.

[0076] The front slider 410 comprises a front guide means 412 which here takes the form of a T-shaped groove parallel to the transverse direction Y and, in the same way, the intermediate slider 910 comprises an intermediate guide means 912 which also here takes the form of a T-shaped groove parallel to the transverse direction Y.

[0077] The front slide 410 and the intermediate slide 910 are independent of the shoes 402 and 902 and therefore do not provide any structural constraint as long as the movement of the tank 110 is not requested.

[0078] The aircraft 100 also comprises a front guide rail 414 and an intermediate guide rail 914 which are put in place only when the movement of the tank is requested.

[0079] When the movement of the tank 110 is required, the front guide rail 414 is made integral with the front shoe 402 and the intermediate guide rail 914 is made integral with the shoe of the intermediate shoe 902. Each rail 414, 914 is arranged parallel to the transverse direction Y and the fixing of the rail 414, 914 to the associated shoe 402, 902 is carried out here by two pins 450, 950 which pass through the rail 414, 914 and the associated shoe 402, 902 perpendicular to the transverse direction Y to lock the position of the rail 414, 914 relative to the shoe 402, 902.

[0080] The front guide rail 414 is arranged to cooperate with the front guide means 412 to provide a sliding connection of the front slider 410 relative to the front guide rail 414 parallel to the transverse direction Y. Here the front guide rail 414 takes an I-shape, a part of which fits into the T-groove of the front guide means 412.

[0081] In the same way, the intermediate guide rail 914 is arranged to cooperate with the intermediate guide means 912 to provide a sliding connection of the intermediate slider 910 relative to the intermediate guide rail 914 parallel to the transverse direction Y. Here the intermediate guide rail 914 takes an I-shape, a part of which is inserted into the T-groove of the intermediate guide means 912.

[0082] The disassembly and removal of the tank 110 consists of placing the front guide rail 414 and the intermediate guide rail 914 and fixing them respectively to the front shoe 402 and to the intermediate shoe 902, here by cooperation of the T shapes and by the installation of the pins 450 and 950.

[0083] A lift 50 is then placed under the tank 110 and is actuated to lift the tank 110 in order to lower the stresses present at the various fixings of the tank 110.

[0084] The various fasteners are then dismantled, that is to say that the front fastener system 152, the rear fastener system 154, the first intermediate fastener system 156 and the second intermediate fastener system 158 are dismantled to release the tank 110.

[0085] After this step, the elevator 50 is lowered and the tank 110 then rests on the front guide rail 414 and the intermediate guide rail 914 by means of the front slider 410 and the intermediate slider 910 respectively.

[0086] The tank 110 can then be moved along the rails 414 and 914 by moving the front slider 410 and the intermediate slider 910 along the associated rail 414, 914.

Claims

Claims

1. Aircraft (100) comprising: - a fuselage (102) with a structure (112a-b), - at least one tank (110) housed in the fuselage (102), and having a longitudinal direction (X), a transverse direction (Y) and a vertical direction (Z) and a vertical longitudinal median plane (XZ), - for each tank (110), fixing means (150) which ensure the fixing of the tank (110) to the structure (112a-b) where the fixing means (150) comprise: - at a front part (110a) of the tank (110), a front fixing system (152) arranged to transfer forces in the vertical direction (Z), - at a rear part (110b) of the tank (110), a rear fixing system (154) arranged to transfer forces in the vertical direction (Z) and the transverse direction (Y), - between the front fixing system (152) and the rear fixing system (154),a first intermediate fixing system (156) arranged to transfer forces in the transverse direction (Y), and - between the first intermediate fixing system (156) and the rear fixing system (154), a second intermediate fixing system (158) arranged to transfer forces in the longitudinal direction (X).,

2. Aircraft (100) according to claim 1, characterized in that the structure comprises a floor (112b) above which the tank (110) is arranged, in that the front fixing system (152) comprises a front shoe (402) fixed to the floor (112b) and on either side of the vertical longitudinal median plane (XZ), a front connecting rod (403a-b) fixed by a first end to the front shoe (402) and by a second end to the tank (110) and in that each front connecting rod (403a-b) is inscribed in a plane perpendicular to the longitudinal direction (X).

3. Aircraft (100) according to claim 2, characterized in that a point of attachment (404) of the second end to the tank (110) has with the vertical longitudinal median plane (XZ), an angle of 60° ± 5°.

4. Aircraft (100) according to one of claims 1 to 3, characterized in that the structure comprises a hoop (112a) and in that the rear fixing system (154) comprises a flange (1102) fixed to the rear of the tank (110), a first connecting rod (1104a) fixed parallel to the direction transverse (Y) between the flange (1102) and the hoop (112a) and a second connecting rod (1104b) fixed parallel to the vertical direction (Z) between the flange (1102) and the hoop (112a).

5. Aircraft (100) according to one of claims 1 to 4, characterized in that the structure comprises a floor (112b) above which the tank (110) is arranged, and in that the first intermediate fixing system (156) comprises a lateral connecting rod (602) fixed between the floor (112b) and a lower part of the tank (110) where the lateral connecting rod (602) is inscribed in a plane perpendicular to the longitudinal direction (X).

6. Aircraft (100) according to one of claims 1 to 5, characterized in that the structure comprises a floor (112b) above which the tank (110) is arranged, in that the second intermediate fixing system (158) comprises an intermediate shoe (902) fixed to the floor (112b) and on either side of the vertical longitudinal median plane (XZ), an intermediate connecting rod (904a-b) fixed by a first end to the intermediate shoe (902) and by a second end to the tank (110) and in that each intermediate connecting rod (904a-b) is inscribed in a plane generally perpendicular to the vertical direction (Z).

7. Aircraft (100) according to claim 6, characterized in that a point of attachment (906) of the second end to the tank (110) has with the vertical longitudinal median plane (XZ), an angle of 20° ± 5°.

8. Aircraft (100) according to one of claims 6 or 7, characterized in that the second intermediate fixing system (158) comprises a hoist (908) ensuring the fixing between the intermediate shoe (902) and each first end.

9. Aircraft (100) according to claims 2 and 6, characterized in that it comprises a front slider (410) secured to the tank (110) and comprising a front guide means (412), an intermediate slider (910) secured to the tank (110) and comprising an intermediate guide means (912), a front guide rail (414) secured to the front shoe (402) and arranged to cooperate with the front guide means (412) to provide a sliding connection of the front slider (410) relative to the front guide rail (414) parallel to the transverse direction (Y) and an intermediate guide rail (914) secured to the intermediate shoe (902) and arranged to cooperate with the intermediate guide means (912) to provide a sliding connection of the intermediate slider (910) relative to the intermediate rail of guide (914) parallel to the transverse direction (Y).

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