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

Abstract

AIRCRAFT COMPRISING A STRUCTURE, A TANK AND MEANS OF FIXING THE TANK TO THE STRUCTURE The invention relates to an aircraft comprising a floor (102a), a tank (110) and means of fixing (150) the tank (110) to the floor (102a). The fastening means (150) comprise guide rails fixed to the floor (102a), a frame (152) with guide grooves cooperating with the guide rails, two rear connecting rods (158a-b) mounted articulated between the frame (152) and the tank (110), two front connecting rods (156a-b) fixed to the frame (152) and mounted articulated on the tank (110), a lateral connecting rod (160) mounted articulated between the frame (152) and a lower portion of the tank (110), and two intermediate connecting rods (162a-b) mounted articulated between the frame (152) and the tank (110). Fig. 2

Description

Title of the invention: AIRCRAFT COMPRISING A STRUCTURE, A TANK AND FIXING 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 hydrogen tank, and fixing means for fixing the tank to the structure. State of the prior art

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

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

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

[0005] Currently, the fixing means are not optimized and it is therefore necessary to find a new arrangement. In addition, it is desirable to find an arrangement that allows the tank to be easily removed from the aircraft if necessary, particularly parallel to the longitudinal axis of the aircraft. 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 that ensure the fixing of each tank to the structure.

[0007] To this end, an aircraft is proposed comprising:

[0008] - a fuselage with a floor,

[0009] - a tank housed in the fuselage above the floor, and having a direction longitudinal and a vertical longitudinal median plane,

[0010] - fastening means that secure the tank to the floor and that include:

[0011] - the first guiding means fixed to the floor,

[0012] - a chassis comprising second guiding means cooperating with the primary guiding methods for creating a sliding joint parallel to the longitudinal direction,

[0013] - at the rear of the tank, on either side of the vertical longitudinal median plane, a rear connecting rod, one end of which is articulated on the chassis and the other end of which is articulated on the tank

[0014] - at the front relative to the rear connecting rods, on either side of the median plane longitudinal vertical, a front connecting rod, one end of which is fixed to the chassis and the other end of which is articulated on the tank.

[0015] - between the front connecting rods and the rear connecting rods, a lateral connecting rod, a first One end is mounted hinged on the chassis, and the other end is mounted hinged on a lower part of the tank,

[0016] - between the lateral connecting rod and the rear connecting rods, on either side of the median plane longitudinal vertical, an intermediate connecting rod, one end of which is mounted articulated on the chassis and the other end of which is mounted articulated on the tank.

[0017] Such an arrangement allows for fastening means that are optimized in particular for the transfer of forces from the tank to the structure as well as the removal of the tank parallel to the longitudinal axis of the aircraft.

[0018] Advantageously, each intermediate connecting rod is inscribed in a plane that is generally parallel to the floor.

[0019] Advantageously, the front connecting rods are inscribed in a plane perpendicular to the longitudinal direction.

[0020] Advantageously, the rear connecting rods are inscribed in a plane perpendicular to the longitudinal direction.

[0021] Advantageously, the lateral connecting rod is inscribed in a plane perpendicular to the longitudinal direction.

[0022] Advantageously, each connecting rod is a double connecting rod.

[0023] Advantageously, the first guiding means take the form of two rails parallel to the longitudinal direction, where each rail has a web extending in a plane perpendicular to the floor and parallel to the longitudinal direction and a flange attached to the web extending in a plane parallel to the floor, and the second guiding means take, for each rail, the form of two slides mounted sliding on said rail where each slide has a groove arranged to receive the web and the flange.

[0024] Advantageously, the fastening means comprise, for each slide, a first locking pin whose axis is perpendicular to the vertical longitudinal median plane and which is housed simultaneously in a first bore of the web and in a second bore of the slide, and a second locking pin whose axis is perpendicular to the floor and which is housed simultaneously in a third bore of the wing and in a fourth bore of the slide.

[0025] Advantageously, the aircraft includes hoops and reinforcing beams, where each reinforcing beam is fixed between the floor and a hoop.

[0026] Advantageously, the fastening means comprise a hoist mounted articulated in its middle on the frame at the level of the vertical longitudinal median plane (XZ), and where each end of the hoist is mounted articulated to a first end of an intermediate connecting rod. Brief description of the drawings

[0027] The features of the invention mentioned above, as well as others, will become clearer upon reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:

[0028] [Fig-1] is a side view of an aircraft according to the invention,

[0029] [Fig.2] is a schematic perspective representation of a reservoir and of fastening means implemented in the invention,

[0030] [Fig.3] is a schematic side view representation of the tank and the fastening means,

[0031] [Fig.4] is a perspective view of the fastening means,

[0032] [Fig.5] is a front view of the tank and the fastening means,

[0033] [Fig.6] is a cross-sectional view of the means for fixing by plane VI of [Fig.2], and

[0034] [Fig.7] is an enlargement of a detail of the fastening means.

[0035] DETAILED STATEMENT OF IMPROVEMENTS

[0036] In the following description, terms relating to a position are taken with reference to an aircraft in its normal flight position, i.e., as shown in [Fig. 1]. Arrow F indicates the forward direction of aircraft 100.

[0037] Fig. 1 shows an aircraft 100 which has 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.

[0038] The fuel is stored in at least one tank 110 which is housed and fixed inside the fuselage 102 and here at the rear of the fuselage 102 by fastening means.

[0039] The description refers to a single tank 110, but there may be several, and in particular two which are arranged on either side of the vertical median plane of the aircraft 100 or one behind the other.

[0040] The reservoir 110 takes a shape of revolution around an axis of revolution and it has a circular or elliptical cross-section.

[0041] In the following description, and by convention, X is called the longitudinal and horizontal direction of the tank 110 passing through the axis of revolution of the tank 110, Y is called the transverse and horizontal direction, and Z is called the direction vertical, these three directions X, Y, and Z being orthogonal to each other. Tank 110 also has a vertical longitudinal median plane XZ that contains the longitudinal direction X and the vertical direction Z. The longitudinal direction X is generally parallel to the longitudinal axis of aircraft 100.

[0042] Figs. 2 to 7 show the tank 110 and the fastening means 150 which secure the tank 110 to a floor 102a of the fuselage 102. As shown in [Fig. 5], the floor 102a is conventionally fixed to hoops 102b of the fuselage 102 which extend around the longitudinal direction of the aircraft 100 and one after the other along the longitudinal direction of the aircraft 100. Conventionally, a skin of the fuselage 102 is fixed to the outside of the hoops 102b.

[0043] The tank 110 is housed in the fuselage 102 and above the floor 102a.

[0044] The fastening means 150 include first guiding means 151a-b which are fixed to the floor 102a.

[0045] The first guiding means 15la-b here take the form of two rails parallel to the longitudinal direction X and arranged side by side and on either side of the vertical longitudinal median plane XZ. Each rail has a web 153a which extends vertically in a plane which is perpendicular to the floor 102a and which is parallel to the longitudinal direction X. Each rail also has a flange 153b which is integral with the web 153a and which extends horizontally in a plane parallel to the floor 102a, here at the top of the web 153a.

[0046] In the embodiment of the invention, the wing 153b extends on both sides of the web 153a, but it could be on only one side.

[0047] Here, each rail has an I-profile with a lower flange 153c which is fixed to the floor 102a.

[0048] In general, the core 153a is fixed to the floor 102a by any suitable means such as screw elements fixing the lower wing 153c.

[0049] The fastening means 150 also include a chassis 152 which has second guide means 154a-b which cooperate with the first guide means 15la-b to make a sliding connection parallel to the longitudinal direction X. As described below, the tank 110 is fixed on the chassis 152 and it is thus possible to move it by sliding the chassis 152 on the first guide means 15la-b when necessary.

[0050] In the embodiment of the invention presented here, the second guiding means 154a-b take the form of slides integrated into the frame 152. For each rail, there are two slides. Thus, there are two port slides and two starboard slides, that is to say, on either side of the vertical longitudinal median plane XZ, and among the port and starboard slides respectively, there is a front slide and a rear slide.

[0051] Each slide is mounted to slide on the associated rail and here each slide has a groove 155a, in particular a T-groove, arranged to receive the web 153a and the wing 153b.

[0052] At the rear of the tank 110, the mounting means 150 comprise, on either side of the vertical longitudinal median plane XZ, a rear connecting rod 158a-b. There are thus two rear connecting rods 158a-b, each having a first end that is hinged to the frame 152 and a second end that is hinged to the tank 110, here via a rear clevis 110b (shown in shadow lines in [Fig. 4]). Each hinge takes the form of a rotation about an axis parallel to the longitudinal direction X, and here the second ends are fixed overall at the level of the longitudinal direction X of the tank 110.

[0053] The rear connecting rods 158a-b ensure the transfer of forces in the vertical direction Z and the transverse direction Y and are arranged behind the tank 110. According to a particular embodiment, each rear connecting rod 158a-b has, with the vertical longitudinal median plane XZ, an angle of 35° ± 5°.

[0054] At the front relative to the rear connecting rods 158a-b, the fastening means 150 comprise, on either side of the vertical longitudinal median plane XZ, a front connecting rod 156a-b. Each front connecting rod 156a-b has a first end which is fixed to the chassis 152 and a second end which is articulated on the tank 110. The front connecting rods 156a-b ensure the transfer of forces in the vertical direction Z and are located here between the tank 110 and the floor 102a.

[0055] Each second end is hinged to a side pallet 110a of the tank 110, here by means of an intermediate connecting rod 111 hinged between the side pallet 110a and the second end. Each hinge here takes the form of a rotation about an axis parallel to the longitudinal direction X. According to a particular embodiment, the attachment point to the side pallet 110a has an angle of 60° ±5° with the vertical longitudinal median plane XZ. This attachment is thus located rather towards the underside of the tank 110 and to the sides with respect to the vertical longitudinal median plane XZ.

[0056] Between the front connecting rods 156a-b and the rear connecting rods 158a-b, the fastening means 150 include a lateral connecting rod 160. Here, the lateral connecting rod 160 is located between the front connecting rods 156a-b, but it can be moved further rearward. The lateral connecting rod 160 ensures the transfer of forces in the transverse direction Y, and here the lateral connecting rod 160 is arranged under the reservoir 110.

[0057] The lateral connecting rod 160 has a first end which is mounted articulated on the chassis 152 and a second end which is mounted articulated on a lower part of the tank 110. Each articulation here takes the form of a rotation around an axis parallel to the longitudinal direction X.

[0058] Here, the first end of the side connecting rod 160 is fixed to the chassis 152 by means of a first pallet 160a of the chassis 152 and the second end of the side connecting rod 160 is fixed to a lower part of the tank 110, here by means of a second pallet 160b of the tank 110.

[0059] The lateral connecting rod 160 is globally parallel to the transverse direction Y and under the reservoir 110.

[0060] Between the lateral connecting rod 160 and the rear connecting rods 158a-b, the fastening means 150 comprise, on either side of the vertical longitudinal median plane XZ, an intermediate connecting rod 162a-b. There are thus two intermediate connecting rods 162a-b, each having a first end that is hinged to the chassis 152 and a second end that is hinged to the tank 110.

[0061] The intermediate connecting rods 162a-b transfer forces along the longitudinal direction X and are located below the reservoir 110. In the embodiment of the invention shown in [Fig. 5], the intermediate connecting rods 162a-b are not doubled, but in another embodiment not shown, the intermediate connecting rods 162a-b may be doubled for redundancy. In this case, there are two intermediate connecting rods 162a-b on either side of the vertical longitudinal median plane XZ.

[0062] Here, the second end of the intermediate connecting rod 162a-b is fixed to the tank 110 by means of an intermediate pallet 163a of the tank 110.

[0063] The articulations of the second ends of the intermediate connecting rods 162a-b are here rotations around an axis globally parallel to the vertical direction Z.

[0064] Such an arrangement allows for an isostatic attachment of the tank 110 to the chassis 152. Such an attachment avoids the transfer of forces from the fuselage 102 to the tank 110 while ensuring the transfer of forces from the chassis 152 to the fuselage 102. In addition, such an arrangement allows the tank 110 to be moved along the longitudinal direction X if necessary.

[0065] According to a particular embodiment, the attachment point to the intermediate pallet 163a has an angle of 20° ± 5° with the vertical longitudinal median plane XZ. This attachment is thus located rather towards the underside of the tank 110 and slightly to the sides with respect to the vertical longitudinal median plane XZ.

[0066] The intermediate connecting rods 162a-b are inscribed here in a plane that is globally perpendicular to the vertical direction Z and globally horizontal, that is to say globally parallel to the floor 102a.

[0067] The front connecting rods 156a-b are inscribed here in a plane perpendicular to the longitudinal direction X, i.e. vertical.

[0068] Similarly, the rear connecting rods 158a-b and the lateral connecting rod 160 are inscribed here in a plane perpendicular to the longitudinal direction X.

[0069] For reasons of redundancy, each connecting rod and / or connecting rod is a double connecting rod, i.e. two identical connecting rods in parallel.

[0070] The fixing of each connecting rod is achieved here by a clevis connection consisting of a female clevis and a male clevis inserted and fixed in the female clevis by the placement of a shaft whose axis is parallel to the corresponding articulation axis.

[0071] In the embodiment of the invention presented more particularly in [Fig.4], the fastening means 150 comprise a hoist 163 which secures the first ends of the intermediate connecting rods 162a-b to the frame 152 and allows a transfer of forces along the longitudinal direction X.

[0072] The hoist is mounted articulated in its middle on the frame 152 at the level of the vertical longitudinal median plane XZ by a pivot joint whose axis is globally parallel to the vertical direction Z, i.e. perpendicular to the floor 102a.

[0073] Each end of the hoist 163 is mounted articulated to a first end of an intermediate connecting rod 162a-b by a pivot joint whose axis is globally parallel to the vertical direction Z. To this end, the first end of each intermediate connecting rod 162a-b takes the form of a female clevis into which the hoist 163, forming a male clevis, is inserted and fixed by the installation of a shaft.

[0074] To ensure that the frame 152 is locked in translation relative to the first guide means 151a-b, the fastening means 150 include removable stop means. For each slide, the stop means comprise a first locking pin 161a and a second locking pin 161b.

[0075] Each first locking axis 161a presents its axis perpendicular to the vertical longitudinal median plane XZ, i.e. horizontally, and also ensures the transfer of forces along the longitudinal direction X and the vertical direction Z.

[0076] Each second locking axis 161b presents its axis perpendicular to the floor 102a, i.e. vertically, and also ensures the transfer of forces along the transverse direction Y.

[0077] Each first locking pin 161a is housed simultaneously in a first bore 165a of the web 153a and in a second bore 165b of the corresponding slide. The second bore 165b extends on either side of the web 153a and is coaxial with the first bore 165a. When the first locking pin 161a is inserted and locked into the bores 165a-b, it locks the frame 152. Any subsequent movement of the frame 152 must be preceded by the withdrawal of each first locking pin 161a.

[0078] Similarly, each second locking pin 161b is housed simultaneously in a third bore of the wing 153b and in a fourth bore of the corresponding slide. The second bore 165b extends on both sides of the wing 153b and is coaxial with the third bore. When the second locking pin 161b is put in place and locked in the bores, it locks the chassis 152. Any movement of the chassis 152 must then be preceded by a withdrawal of each second locking pin 161b.

[0079] Each first locking pin 161a and second locking pin 161b pass through the groove 155a when they are in the locked position. The locking pins 161a-b are held in place, for example, by being pressed in, screwed into the slide, or by other means.

[0080] To ensure the transfer of forces from the tank 110 to the aircraft structure 100 in the event of a crash, and thus prevent deformation of the tank 110, the aircraft 100 includes reinforcing beams 170, and each reinforcing beam 170 is fixed between the floor 102a and a hoop 102b. Thus, the forces from the tank 110 are transferred through the reinforcing beams 170 to the hoops 102b.

Claims

Demands

1. Aircraft (100) comprising: - a fuselage (102) with a floor (102a), - a tank (110) housed in the fuselage (102) above the floor (102a), and having a longitudinal direction (X) and a vertical longitudinal median plane (XZ), - fastening means (150) that secure the tank (110) to the floor (102a) and that comprise: - first guide means (151a-b) fixed to the floor (102a), - a chassis (152) comprising second guide means (154a-b) cooperating with the first guide means (151a-b) to create a sliding connection parallel to the longitudinal direction (X), - at the rear of the tank (110), on either side of the vertical longitudinal median plane (XZ), a rear connecting rod (158a-b) the first end of which is articulated on the chassis (152) and of which a second end is mounted articulated on the tank (110), - at the front relative to the rear connecting rods (158a-b),on either side of the vertical longitudinal median plane (XZ), a front connecting rod (156a-b) with one end fixed to the chassis (152) and the other end articulated on the tank (110), - between the front connecting rods (156a-b) and the rear connecting rods (158a-b), a lateral connecting rod (160) with one end articulated on the chassis (152) and the other end articulated on a lower part of the tank (110), and - between the lateral connecting rod (160) and the rear connecting rods (158a-b), on either side of the vertical longitudinal median plane (XZ), an intermediate connecting rod (162a-b) with one end articulated on the chassis (152) and the other end articulated on the tank (110).

2. Aircraft (100) according to claim 1, characterized in that each intermediate connecting rod (162a-b) is inscribed in a plane globally parallel to the floor (102a).

3. Aircraft (100) according to any one of claims 1 or 2, characterized in that the forward connecting rods (156a-b) are inscribed in a plane perpendicular to the longitudinal direction (X).

4. Aircraft (100) according to any one of claims 1 to 3, characterized in that the rear connecting rods (158a-b) are inscribed in a plane perpendicular to the longitudinal direction (X).

5. Aircraft (100) according to any one of claims 1 to 4, characterized in that the lateral connecting rod (160) is inscribed in a plane perpendicular to the longitudinal direction (X).

6. Aircraft (100) according to any one of claims 1 to 5, characterized in that each connecting rod is a double connecting rod.

7. Aircraft (100) according to any one of claims 1 to 6, characterized in that the first guiding means (151a-b) take the form of two rails parallel to the longitudinal direction (X), where each rail has a web (153a) extending in a plane perpendicular to the floor (102a) and parallel to the longitudinal direction (X) and a wing (153b) integral with the web (153a) extending in a plane parallel to the floor (102a), and in that the second guiding means (154a-b) take, for each rail, the form of two slides mounted sliding on said rail, where each slide has a groove (155a) arranged to receive the web (153a) and the wing (153b).

8. Aircraft (100) according to claim 7, characterized in that the fastening means (150) comprise for each slide, a first locking pin (161a) whose axis is perpendicular to the vertical longitudinal median plane (XZ) and which is housed simultaneously in a first bore (165a) of the web (153a) and in a second bore (165b) of the slide, and a second locking pin (161b) whose axis is perpendicular to the floor (102a) and which is housed simultaneously in a third bore of the wing (153b) and in a fourth bore of the slide.

9. Aircraft (100) according to any one of claims 1 to 8, characterized in that it comprises hoops (102b) and reinforcing beams (170), where each reinforcing beam (170) is fixed between the floor (102a) and a hoop (102b).

10. Aircraft (100) according to any one of claims 1 to 9, characterized in that the fastening means (150) comprise a hoist (163) mounted articulated in its middle on the frame (152) at the level of the vertical longitudinal median plane (XZ) and where each end of the hoist (163) is mounted articulated to a first end of an intermediate connecting rod (162a-b).

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