(19)
(11)EP 3 306 146 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
29.04.2020 Bulletin 2020/18

(21)Application number: 16803011.2

(22)Date of filing:  12.05.2016
(51)International Patent Classification (IPC): 
B64D 11/02(2006.01)
F16J 15/06(2006.01)
F17C 13/06(2006.01)
F16J 12/00(2006.01)
F17C 3/00(2006.01)
(86)International application number:
PCT/JP2016/064114
(87)International publication number:
WO 2016/194574 (08.12.2016 Gazette  2016/49)

(54)

WATER TANK FOR AIRCRAFT

WASSERTANK FÜR FLUGZEUG

RÉSERVOIR D'EAU POUR UN AÉRONEF


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 02.06.2015 JP 2015112053

(43)Date of publication of application:
11.04.2018 Bulletin 2018/15

(73)Proprietor: The Yokohama Rubber Co., Ltd.
Minato-ku Tokyo 105-8685 (JP)

(72)Inventors:
  • TAGUCHI, Yuji
    Hiratsuka-shi Kanagawa 254-8601 (JP)
  • OZAWA, Takahiro
    Hiratsuka-shi Kanagawa 254-8601 (JP)
  • KATO, Hayato
    Hiratsuka-shi Kanagawa 254-8601 (JP)

(74)Representative: Dilg, Haeusler, Schindelmann Patentanwaltsgesellschaft mbH 
Leonrodstraße 58
80636 München
80636 München (DE)


(56)References cited: : 
DE-A1- 2 152 123
FR-A1- 2 301 746
JP-A- 2014 019 497
US-A- 5 938 209
FR-A1- 2 193 953
JP-A- 2011 251 736
JP-A- 2015 085 946
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    Technical Field



    [0001] The present invention relates to an aircraft water tank.

    Background Art



    [0002] In the related art, an aircraft water tank has a tank body composed of an inner liner and a fiber-reinforced resin layer covering the inner liner, and the tank body has a cylindrical portion and dome portions provided on both sides of the cylindrical portion.
    Such an aircraft water tank has opening portions for cleaning the interior of the tank body which are provided through the centers of both the dome portions. Each of the opening portions is composed of a mouthpiece attached to the center of the dome portion and a lid detachably joined to the mouthpiece via an O-ring.
    The mouthpiece has a tubular portion on which internal threads are formed, the internal threads being engaged with external threads of the lid; and a skirt portion extending outward from the end of the tubular portion in the radial direction of the tubular portion. The inner liner is attached to the inner peripheral surface of the skirt portion with an adhesive, and the fiber-reinforced resin layer is attached to the outer peripheral surface of the skirt portion.
    The end of the inner liner is located closer to the interior of the tank body than the O-ring on the inner peripheral surface of the skirt portion. When the aircraft water tank is in use, the inner peripheral surface of the skirt portion including the end of the inner liner comes into contact with drinking water.

    Citation List


    Patent Literature



    [0003] 

    Patent Document 1: JP 2011-251736 A

    Patent Document 2: FR 2 301 746 A1


    Summary of Invention


    Technical Problem



    [0004] In the related art, in order to prevent direct contact between the water and the adhesive for attaching the inner liner to the skirt portion while an aircraft water tank is in use, a coating process for applying an FDA-approved material to the surface of the skirt portion around the end of the inner liner is required.

    [0005] Therefore, the coating process is added to the manufacturing process of the aircraft water tank, and this coating has to be inspected and repaired at the time of maintenance. Accordingly, some improvements have been desired for increasing the production efficiency, reducing costs, and increasing the efficiency of the maintenance work.

    [0006] The present invention has been made in view of such circumstances, and an object of the present invention is to provide an aircraft water tank advantageous in increasing the production efficiency, reducing costs, and increasing the efficiency of maintenance work.

    Solution to Problem



    [0007] In order to achieve the above object, provided according to the present invention is an aircraft water tank according to claim 1. The provided aircraft water tank includes:

    a tank body having an inner surface formed of an inner liner; an annular mouthpiece attached to the tank body; an opening portion provided inside the mouthpiece; and a lid detachably joined to the mouthpiece. In such an aircraft water tank, the opening portion is opened and sealed by the lid, the mouthpiece has a tubular portion to which the lid is joined, the tubular portion has a bulging portion provided on an inner peripheral portion of the tubular portion, the bulging portion bulging inward in a radial direction of the tubular portion, the inner liner is attached to a surface of the bulging portion, a seal member is provided between a portion of the lid located inside the tubular portion and a portion of the inner liner attached to the surface of the bulging portion,

    in a state where the lid is joined to the tubular portion, compression of the seal member seals the opening portion liquid-tightly to form a sealed water storage space inside the tank body, and an end of the inner liner attached to the surface of the bulging portion is located outside the water storage space.


    Advantageous Effects of Invention



    [0008] According to the present invention, when the aircraft water tank is in use, the drinking water stored in the tank body does not come into contact with the end of the inner liner.

    [0009] This eliminates the need of the coating process, using an FDA-approved material, for preventing water from directly coming into contact with the adhesive that is used to attach the inner liner to the skirt portion. Therefore, a drastic reduction in time required for applying an FDA-approved material at the time of manufacturing, maintenance, and inspection is advantageous in increasing the production efficiency of the aircraft water tank, reducing costs, and increasing the efficiency of maintenance work.

    Brief Description of Drawings



    [0010] 
    FIG. 1
    is a perspective view of an aircraft water tank.
    FIG. 2
    is an enlarged view of main portions of a mouthpiece and a lid in a state where the mouthpiece and the lid are separated from each other.
    FIG. 3
    is an enlarged view of the main portions of the mouthpiece and the lid in a state in which the mouthpiece and the lid are joined.

    Description of Embodiments


    First Embodiment



    [0011] Next, embodiments of the present invention will be described with reference to the drawings.

    [0012] As illustrated in FIG. 1, an aircraft water tank 10 installed in an aircraft and containing drinking water has a tank body 12, the interior of which serves as a water storage space.

    [0013] The tank body 12 has a cylindrical portion 14 and dome portions 16 provided on both sides of the cylindrical portion 14.

    [0014] As illustrated in FIG. 2, opening portions 18 for cleaning the interior of the tank body 12 are provided through the centers of both the dome portions 16, and each of the opening portions 18 is opened and sealed by a lid 34. A piping nozzle (not illustrated) for supplying water to various places of the aircraft is provided on the upper portion of the cylindrical portion 14, and a piping nozzle (not illustrated) for discharging water is provided on the lower portion of the cylindrical portion 14.

    [0015] As illustrated in FIG. 2, the tank body 12 includes an inner liner 22 serving as the inner surface of the aircraft water tank 10 and a fiber-reinforced resin layer 24 covering the outer surface of the inner liner 22. The inner liner 22 is a hollow body defining the contour of the aircraft water tank 10 and is manufactured by blow molding. The blow molding involves melting a synthetic resin into a pipe shape, clamping the pipe-shaped resin into a mold, and feeding air into the pipe-shaped resin to obtain a molded product.
    For the inner liner 22, various known materials in the related art approved by the FDA are available. Examples of such materials include polyolefin resins such as polypropylene and polyethylene which are thermoplastic resins.

    [0016] The fiber-reinforced resin layer 24 is formed by filament winding in which reinforcing fibers (filaments) impregnated with a thermosetting resin are wound around the outer peripheral surface of the inner liner 22. Various known synthetic resins in the related art such as an epoxy resin are available for the thermosetting resin. Various known fibers in the related art such as carbon fibers or glass fibers are available for the reinforcing fibers.

    [0017] Each of the opening portions 18 is formed by an annular mouthpiece 26 attached between both ends of the inner liner 22 and both ends of the fiber-reinforced resin layer 24. When the aircraft water tank 10 is in use, the opening portion 18 is sealed by the lid 34.
    The mouthpiece 26 has a tubular portion 30 disposed at the center of the dome portion 16 and a skirt portion 32 extending outward from the end portion of the tubular portion 30 in the radial direction of the tubular portion 30.
    Internal threads 36 are provided at a position on an inner peripheral portion of the tubular portion 30, which is remote from the tank body 12 in the axial direction of the tubular portion 30. The internal threads 36 serve as a joint portion of the mouthpiece to which the lid 34 is joined.
    A bulging portion 38 is provided at a position on an inner peripheral portion of the tubular portion 30, which is adjacent to the tank body 12 in the axial direction of the tubular portion 30.
    The bulging portion 38 bulges inward in the radial direction from the minor diameter of the internal threads 36 and has a curved surface protruding inward in the radial direction. The end of the bulging portion 38 adjacent to the internal threads 36 is a flat surface 3802 extending orthogonal to the axial direction of the internal threads 36.
    An inclined surface 40 is formed at a position on an inner peripheral portion of the bulging portion 38 adjacent to the internal threads 36. The inclined surface 40 is inwardly inclined in the radial direction of the tubular portion 30 toward the tank body 12 in the axial direction of the tubular portion 30.

    [0018] A groove 42 having an inner peripheral surface whose diameter is larger than the major diameter of the internal threads 36 is formed at the boundary between the internal threads 36 and the bulging portion 38 on the inner peripheral portion of the tubular portion 30.
    Of a pair of side surfaces which serve as part of the groove 42 and face each other, a side surface 4202 adjacent to the bulging portion 38 is flush with the flat surface 3802 on the end of the bulging portion 38 and extends on a plane orthogonal to the axis of the internal threads 36.
    Further, the inner peripheral portion of the flat surface 3802 serves as a flat surface 3804 which is displaced in a direction away from the internal threads 36 by the thickness of the inner liner 22, and the flat surface 3804 is connected to the inclined surface 40.
    The internal threads 36, the bulging portion 38, and the groove 42 are formed coaxially.

    [0019] As the distance from the bulging portion 38 increases, the inner diameter of the skirt portion 32 gradually increases and the thickness of the skirt portion 32 gradually decreases.
    The inner peripheral surface of the skirt portion 32 and the surface of the bulging portion 38 adjacent to the skirt portion 32 are formed in a continuous shape. That is, the surface of the half of the bulging portion 38 remote from the internal threads 36 in the axial direction of the tubular portion 30 is a curved surface whose inner diameter increases as the distance from the internal threads 36 increases, and this curved surface is continuous with the inner peripheral surface of the skirt portion 32, which allows the inner liner 22 (described below) to be smoothly attached to both the inner peripheral surface of the skirt portion 32 and the surface of the bulging portion 38.
    The fiber-reinforced resin layer 24 is attached to the outer peripheral surface of the skirt portion 32.
    The inner liner 22 is attached to both the inner peripheral surface of the skirt portion 32 and the surface of the bulging portion 38. An end portion 2202 of the inner liner 22 is located on the flat surface 3804 beyond the inclined surface 40. The surface of the end portion 2202 is flush with the flat surface 3802.
    The flat surface 3802 of the bulging portion 38 is located adjacent to the internal threads 36 in the axial direction of the tubular portion 30 and is directed to the space inside the internal threads 36.
    The end portion 2202 of the inner liner 22 is located, on the flat surface 3802, inside the minor diameter of the internal threads 36 in the radial direction. This configuration allows visual observation inside the internal threads 36, of whether the end portion 2202 of the inner liner 22 is securely attached to the bulging portion 38 to be easily performed, which increases the production efficiency.

    [0020] The lid 34 includes an annular plate portion 44, a tube portion 46 protruding from the inner peripheral portion of one end surface in the thickness direction of the annular plate portion 44, and an end surface portion 48 connecting a tip of the tubular portion 46.
    External threads 50 are formed as a joining portion of the lid configured to be joined to a joining portion of the mouthpiece on the outer peripheral portion of the annular plate portion 44, and the external threads 50 are engageable with the internal threads 36.
    Further, in the present embodiment, an O-ring 52 is mounted, as a seal member, at a position on the outer peripheral surface of the tubular portion 46 adjacent to the end face. The O-ring 52 mounted to the lid 34 allows the opening and sealing of the opening portion 18 using the lid 34 to be easily performed.
    In the present embodiment, the mouthpiece 26 and the lid 34 are formed of the same synthetic resin material approved by the FDA, so that the external threads 50 and the internal threads 36 can be joined smoothly.

    [0021] In a state where the lid 34 is joined to the opening portion 18 via the internal threads 36 and the external threads 50, compression of the O-ring 52 between a portion of the lid 34 extending beyond the internal threads 36 toward the interior of the tank body 12 and a portion of the inner liner 22 attached to the surface of the bulging portion 38 seals the opening portion 18 liquid-tightly to form a sealed water storage space 12A in the tank body 12.
    In the present embodiment, the portion of the lid 34 configured to compress the O-ring 52 is a corner portion formed by the end surface 4402 of the annular plate portion 44 and the outer peripheral surface 4602 of the tubular portion 46, and the portion of the inner liner 22 configured to compress the O-ring 52 is a portion of the inner liner 22 attached to the inclined surface 40.
    The end portion 2202 of the inner liner 22 attached to the surface of the bulging portion 38 is located at a position on the surface of the bulging portion 38 that is farther from the water storage space 12A than the portion where the O ring 52 is compressed.

    [0022] According to the present embodiment, in a state where with the opening portion 18 is sealed by the lid 34, the inner peripheral surface of the skirt portion 32 of the mouthpiece 26 located in the drinking water and the surface of the bulging portion 38 are covered with the inner liner 22, and the end portion 2202 of the inner liner 22 is located on the surface of the bulging portion 38 that is farther from the water storage space 12A than the O-ring 52 that seals the interior of the tank body 12 liquid-tightly. That is, the end portion 2202 of the inner liner 22 is located outside the water storage space 12A.
    This configuration prevents the water in the tank body 12 from coming into contact with the end portion 2202 of the inner liner 22 when the aircraft water tank 10 is in use.
    Therefore, this configuration eliminates the need of the coating process using an FDA-approved material for preventing water leakage on the surface of the skirt portion 32 around the end portion 2202 of the inner liner 22, which is advantageous in increasing the production efficiency of the aircraft water tank 10 and reducing costs. In addition, at the time of maintenance, this configuration eliminates the need of inspections of and repairs on the coating for preventing water leakage formed of an FDA-approved material, which is advantageous in increasing the efficiency of the maintenance work.
    Further, the end portion 2202 of the inner liner 22 is located at a position farther away from the water storage space 12A than a position where the O-ring 52 is compressed, in other words, the end portion 2202 of the inner liner 22 is positioned outside the water storage space 12A, which eliminates the possibility of separation of the inner liner 22 due to the pressure of the drinking water. Thus, even if the inner liner 22 is separated, it is advantageous in eliminating the risk of entering and leaking of water from the position where the inner liner 22 is separated.

    [0023] When the aircraft water tank 10 is in use, the inner peripheral surface of the skirt portion 32 of the mouthpiece 26 located in the drinking water and the surface of the bulging portion 38 are covered with the inner liner 22, which prevents the mouthpiece 26 from directly coming into contact with the drinking water.
    Therefore, in manufacturing the mouth piece 26, materials used are not limited to FDA approved materials, and any desired materials having various properties can be used, which is advantageous in expanding the degree of freedom of design.
    Further, in the present embodiment, at the boundary between the internal threads 36 and the bulging portion 38 on the inner peripheral portion of the tubular portion 30, the groove 42 having an inner peripheral surface whose diameter is larger than the major diameter of the internal threads 36 are formed.
    Therefore, the operation of attaching the inner liner 22 to the surface of the bulging portion 38 including the inclined surface 40, in particular, the operation of attaching the end portion 2202 of the inner liner 22 to the flat surface 3804 of the bulging portion 38 orthogonal to the internal threads 36 becomes easier, which is advantageous in increasing the production efficiency of the aircraft water tank 10 and reducing costs.

    [0024] In the present embodiment, the embodiment in which the joining portion of the mouthpiece is formed by the internal threads 36 and the joining portion of the lid is formed by the external threads 50 has been described. However, it is needless to say that the present invention is applicable to an embodiment in which the joining portion of the mouthpiece is formed by external threads, the joining portion of the lid is formed by internal threads, and the tubular portion 30 is covered with the lid 34.

    Reference Signs List



    [0025] 
    10
    Aircraft water tank
    12
    Tank body
    12A
    Water storage space
    14
    Cylindrical portion
    16
    Dome portion
    18
    Opening portion
    22
    Inner liner
    24
    Fiber-reinforced resin layer
    26
    Mouthpiece
    30
    Tubular portion
    32
    Skirt portion
    34
    Lid
    36
    Internal thread
    38
    Bulging portion
    40
    Inclined surface
    42
    Groove
    44
    Annular plate portion
    46
    Tube portion
    50
    External thread
    52
    O-ring



    Claims

    1. An aircraft water tank (10), comprising:

    a tank body (12) having an inner surface formed of an inner liner (22);

    an annular mouthpiece (26) attached to the tank body (12);

    an opening portion (18) provided inside the mouthpiece (26); and

    a lid (34) detachably joined to the mouthpiece (26), wherein

    the opening portion (18) is opened and sealed by the lid (34),

    the mouthpiece (26) has a tubular portion (30) to which the lid (34) is joined,

    the tubular portion (30) has a bulging portion (38) provided on an inner peripheral portion of the tubular portion (30), the bulging portion (38) bulging inward in a radial direction of the tubular portion (30),

    the inner liner (22) is attached to a surface of the bulging portion (38),

    a seal member is provided between a portion of the lid (34) located inside the tubular portion (30) and a portion of the inner liner (22) attached to the surface of the bulging portion (38),

    in a state where the lid (34) is joined to the tubular portion (30), compression of the seal member seals the opening portion (18) liquid-tightly to form a sealed water storage space (12A) in the tank body (12),

    an end of the inner liner (22) attached to the surface of the bulging portion (38) is located outside the water storage space (12A),

    the bulging portion (38) is provided at position on the inner peripheral portion of the tubular portion (30) adjacent to the tank body (12) in an axial direction of the tubular portion (30),

    a joining portion (36) of the mouthpiece (26) to which the lid (34) is joined is provided at a position on the inner peripheral portion of the tubular portion (30) remote from the tank body (12) in the axial direction of the tubular portion (30),

    the bulging portion (38) is provided protruding inward in the radial direction from an inner diameter of the joining portion of the mouthpiece (26), and

    the bulging portion (38) has a surface (3802) facing a space inside the joining portion (36) of the mouthpiece (26) at a position adjacent to the joining portion (36) of the mouthpiece (26) in the axial direction of the tubular portion (30), characterized in that

    the end (2202) of the inner liner (22) is located at a position on the surface (3802) facing the space inside the joining portion (36) of the mouthpiece (26) located inside in the radial direction of the inner diameter of the joining portion (36) of the mouthpiece (26).


     
    2. The aircraft water tank (10) according to claim 1, wherein

    the lid (34) includes an annular plate portion (44) having a joining portion formed on an outer peripheral surface thereof, the joining portion being configured to be joined to the joining portion of the mouthpiece (26),

    a tube portion (46) protruding from an inner peripheral portion of one end surface in the axial direction of the annular plate portion (44), and an end surface portion of the end surface connecting a tip of the tube portion (46), and

    the bulging portion (38) has an inclined surface (40) inwardly inclined in the radial direction of the tubular portion (30) toward the tank body (12) in the axial direction of the tubular portion (30),

    the portion of the lid (34) configured to compress the seal member is a corner portion formed by the end surface of the annular plate portion (44) and the outer peripheral surface of the tube portion (46), and the portion of the inner liner (22) configured to compress the seal member is a portion of the inner liner (22) attached to the inclined surface (40).


     
    3. The aircraft water tank (10) according to claim 2, wherein
    the seal member is mounted at a position on the outer peripheral surface of the tube portion (46) adjacent to the end surface.
     
    4. The aircraft water tank (10) according any one of claims 1 to 3, wherein
    a groove (42) having an inner peripheral surface whose diameter is larger than the inner diameter of the joining portion of the mouthpiece (26) is formed at a boundary between the joining portion of the mouthpiece (26) and the bulging portion (38) on the inner peripheral portion of the tubular portion (30).
     


    Ansprüche

    1. Luftfahrzeugwassertank (10), umfassend:

    einen Tankkörper (12) mit einer Innenfläche, die aus einer Innenauskleidung (22) gebildet ist;

    ein ringförmiges Mundstück (26), das an dem Tankkörper (12) angebracht ist;

    einen Öffnungsabschnitt (18), der innerhalb des Mundstücks (26) bereitgestellt ist; und

    einen lösbar mit dem Mundstück (26) verbundenen Deckel (34), wobei der Öffnungsabschnitt (18) durch den Deckel (34) geöffnet und

    abgedichtet wird,

    das Mundstück (26) einen rohrförmigen Abschnitt (30) aufweist, mit dem der Deckel (34) verbunden ist,

    der rohrförmige Abschnitt (30) einen Ausbauchungsabschnitt (38) aufweist, der an einem Innenumfangsabschnitt des rohrförmigen Abschnitts (30) bereitgestellt ist, wobei sich der Ausbauchungsabschnitt (38) in einer Radialrichtung des rohrförmigen Abschnitts (30) nach innen wölbt,

    die Innenauskleidung (22) an einer Oberfläche des Ausbauchungsabschnitts (38) angebracht ist,

    ein Abdichtelement zwischen einem Abschnitt des Deckels (34), der sich innerhalb des rohrförmigen Abschnitts (30) befindet, und einem Abschnitt der Innenauskleidung (22), die an der Oberfläche des Ausbauchungsabschnitts (38) angebracht ist, bereitgestellt ist,

    in einem Zustand, in dem der Deckel (34) mit dem rohrförmigen Abschnitt (30) verbunden ist, Kompression des Abdichtelements den Öffnungsabschnitt (18) flüssigkeitsdicht abdichtet, um einen abgedichteten Wasserspeicherraum (12A) in dem Tankkörper (12) zu bilden,

    ein Ende der Innenauskleidung (22), das an der Oberfläche des Ausbauchungsabschnitts (38) angebracht ist, sich außerhalb des Wasserspeicherraums (12A) befindet,

    der Ausbauchungsabschnitt (38) in einer axialen Richtung des rohrförmigen Abschnitts (30) an einer Position auf dem Innenumfangsabschnitt des rohrförmigen Abschnitts (30) benachbart zu dem Tankkörper (12) bereitgestellt ist,

    ein Verbindungsabschnitt (36) des Mundstücks (26), mit dem der Deckel (34) verbunden ist, an einer Position auf dem Innenumfangsabschnitt des rohrförmigen Abschnitts (30) in der axialen Richtung der röhrenförmigen Abschnitt (30) von dem Behälterkörper (12) entfernt bereitgestellt ist, der Ausbauchungsabschnitt (38) von einem Innendurchmesser des Verbindungsabschnitts des Mundstücks (26) in der Radialrichtung nach innen ragend bereitgestellt ist, und

    der Ausbauchungsabschnitt (38) eine Oberfläche (3802) aufweist, die einem Raum innerhalb des Verbindungsabschnitts (36) des Mundstücks (26) an einer Position benachbart zu dem Verbindungsabschnitt (36) des Mundstücks (26) in der axialen Richtung des röhrenförmigen Abschnitts (30) zugewandt ist, dadurch gekennzeichnet, dass

    das Ende (2202) der Innenauskleidung (22) sich an einer Position auf der Oberfläche (3802) befindet, die dem Raum innerhalb des Verbindungsabschnitts (36) des Mundstücks (26), das sich in der Radialrichtung des Innendurchmesser des Verbindungsabschnitts (36) des Mundstücks (26) befindet, zugewandt ist.


     
    2. Luftfahrzeugwassertank (10) nach Anspruch 1, wobei
    der Deckel (34) einen ringförmigen Plattenabschnitt (44) einschließt, der einen Verbindungsabschnitt aufweist, der auf einer Außenumfangsfläche davon gebildet ist, wobei der Verbindungsabschnitt konfiguriert ist, um mit dem Verbindungsabschnitt des Mundstücks (26) verbunden zu werden,
    einen Rohrabschnitt (46), der aus einem Innenumfangsabschnitt einer Endfläche in der axialen Richtung von dem ringförmigen Plattenabschnitt (44) hervorragt, und einen Endflächenabschnitt der Endfläche, die eine Spitze des Rohrabschnitts (46) verbindet, und
    der Ausbauchungsabschnitt (38) eine geneigte Oberfläche (40) aufweist, die in der Radialrichtung des rohrförmigen Abschnitts (30) in Richtung des Tankkörpers (12) in der axialen Richtung des rohrförmigen Abschnitts (30) nach innen geneigt ist,
    wobei der Abschnitt des Deckels (34), der konfiguriert ist, um das Abdichtelement zu komprimieren, ein Eckabschnitt ist, der durch die Endfläche des ringförmigen Plattenabschnitts (44) und die äußere Umfangsfläche des Rohrabschnitts (46) gebildet ist, und der Abschnitt der Innenauskleidung (22), der konfiguriert ist, um das Abdichtelement zu komprimieren, ein Abschnitt der Innenauskleidung (22) ist, der an der geneigten Oberfläche (40) angebracht ist.
     
    3. Luftfahrzeugwassertank (10) nach Anspruch 2, wobei
    das Abdichtelement an einer Position an der Außenumfangsfläche des Rohrabschnitts (46) benachbart zu der Endfläche montiert ist.
     
    4. Luftfahrzeugwassertank (10) nach einem der Ansprüche 1 bis 3, wobei
    an einer Grenze zwischen dem Verbindungsabschnitt des Mundstücks (26) und dem Ausbauchungsabschnitt (38) am Innenumfangsabschnitt des rohrförmigen Abschnitts (30) eine Rille (42) mit einer Innenumfangsfläche gebildet ist, deren Durchmesser größer ist als der Innendurchmesser des Verbindungsabschnitts des Mundstücks (26).
     


    Revendications

    1. Réservoir d'eau d'aéronef (10), comprenant :

    un corps de réservoir (12) ayant une surface intérieure formée d'un revêtement interne (22) ;

    une embouchure annulaire (26) fixée au corps de réservoir (12) ;

    une partie d'ouverture (18) fournie à l'intérieur de l'embouchure (26) ; et

    un couvercle (34) relié de manière détachable à l'embouchure (26), dans lequel

    la partie d'ouverture (18) est ouverte et scellée par le couvercle (34),

    l'embouchure (26) a une partie tubulaire (30) à laquelle le couvercle (34) est relié,

    la partie tubulaire (30) a une partie bombée (38) fournie sur une partie périphérique interne de la partie tubulaire (30), la partie bombée (38) étant bombée vers l'intérieur dans une direction radiale de la partie tubulaire (30),

    le revêtement interne (22) est fixé à une surface de la partie bombée (38),

    un élément d'étanchéité est fourni entre une partie du couvercle (34) située à l'intérieur de la partie tubulaire (30) et une partie du revêtement interne (22) fixée à la surface de la partie bombée (38),

    dans un état où le couvercle (34) est relié à la partie tubulaire (30), la compression de l'élément d'étanchéité scelle la partie d'ouverture (18) de manière étanche au liquide pour former un espace de stockage d'eau scellé (12A) dans le corps de réservoir (12),

    une extrémité du revêtement interne (22) fixée à la surface de la partie bombée (38) est située à l'extérieur de l'espace de stockage d'eau (12A),

    la partie bombée (38) est fournie au niveau d'une position sur la partie périphérique interne de la partie tubulaire (30) adjacente au corps de réservoir (12) dans une direction axiale de la partie tubulaire (30),

    une partie de jonction (36) de l'embouchure (26) à laquelle le couvercle (34) est relié est fournie au niveau d'une position sur la partie périphérique interne de la partie tubulaire (30) éloignée du corps de réservoir (12) dans la direction axiale de la partie tubulaire (30),

    la partie bombée (38) est fournie faisant saillie vers l'intérieur dans la direction radiale depuis un diamètre interne de la partie de jonction de l'embouchure (26), et

    la partie bombée (38) a une surface (3802) faisant face à un espace à l'intérieur de la partie de jonction (36) de l'embouchure (26) au niveau d'une position adjacente à la partie de jonction (36) de l'embouchure (26) dans la direction axiale de la partie tubulaire (30), caractérisé en ce que

    l'extrémité (2202) du revêtement interne (22) est située au niveau d'une position sur la surface (3802) faisant face vers l'espace intérieur de la partie de jonction (36) de l'embouchure (26) située à l'intérieur dans la direction radiale du diamètre interne de la partie de jonction (36) de l'embouchure (26).


     
    2. Réservoir d'eau d'aéronef (10) selon la revendication 1, dans lequel
    le couvercle (34) inclut une partie de plaque annulaire (44) ayant une partie de jonction formée sur une surface périphérique externe de celle-ci, la partie de jonction étant configurée pour être reliée à la partie de jonction de l'embouchure (26),
    une partie de tube (46) faisant saillie depuis une partie périphérique interne d'une surface d'extrémité dans la direction axiale de la partie de plaque annulaire (44), et une partie de surface d'extrémité de la surface d'extrémité reliant une pointe de la partie de tube (46), et
    la partie bombée (38) a une surface inclinée (40) inclinée vers l'intérieur dans la direction radiale de la partie tubulaire (30) vers le corps de réservoir (12) dans la direction axiale de la partie tubulaire (30),
    la partie du couvercle (34) configurée pour comprimer l'élément d'étanchéité est une partie de coin formée par la surface d'extrémité de la partie de plaque annulaire (44) et la surface périphérique externe de la partie de tube (46), et la partie du revêtement interne (22) configurée pour comprimer l'élément d'étanchéité est une partie du revêtement interne (22) fixée à la surface inclinée (40).
     
    3. Réservoir d'eau d'aéronef (10) selon la revendication 2, dans lequel
    l'élément d'étanchéité est monté au niveau d'une position sur la surface périphérique externe de la partie de tube (46) adjacente à la surface d'extrémité.
     
    4. Réservoir d'eau d'aéronef (10) selon l'une quelconque des revendications 1 à 3, dans lequel
    une rainure (42) ayant une surface périphérique interne dont le diamètre est plus grand que le diamètre interne de la partie de jonction de l'embouchure (26) est formée au niveau d'une limite entre la partie de jonction de l'embouchure (26) et la partie bombée (38) sur la partie périphérique interne de la partie tubulaire (30).
     




    Drawing











    Cited references

    REFERENCES CITED IN THE DESCRIPTION



    This list of references cited by the applicant is for the reader's convenience only. It does not form part of the European patent document. Even though great care has been taken in compiling the references, errors or omissions cannot be excluded and the EPO disclaims all liability in this regard.

    Patent documents cited in the description