(19)
(11)EP 2 879 956 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
27.04.2016 Bulletin 2016/17

(21)Application number: 13736579.7

(22)Date of filing:  12.07.2013
(51)International Patent Classification (IPC): 
F16K 27/00(2006.01)
(86)International application number:
PCT/EP2013/064798
(87)International publication number:
WO 2014/019833 (06.02.2014 Gazette  2014/06)

(54)

VALVE FOR A JETTISONABLE AIRCRAFT FUEL TANK

VENTIL FÜR EINEN ABWERFBAREN TREIBSTOFFTANK EINES FLUGZEUGES

SOUPAPE POUR UN RESERVOIR EJECTABLE D'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: 31.07.2012 GB 201213626

(43)Date of publication of application:
10.06.2015 Bulletin 2015/24

(73)Proprietor: Eaton Limited
Titchfield Fareham Hampshire PO14 9ED (GB)

(72)Inventor:
  • POWELL, Melvyn
    Waterlooville Hampshire PO7 7PY (GB)

(74)Representative: Eaton IP Group EMEA 
c/o Eaton Industries Manufacturing GmbH Route de la Longeraie 7
1110 Morges
1110 Morges (CH)


(56)References cited: : 
DE-B- 1 195 606
US-A- 4 306 693
US-A- 3 129 718
US-A- 4 790 350
  
      
    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


    [0001] The present invention relates to a valve for connecting an external tank to an aircraft. In particular, but not exclusively, the invention relates to a valve for connecting to an aircraft fuel system.

    [0002] It is known to provide auxiliary fuel tanks which may be externally carried on an aircraft (sometimes referred to as "Drop Tanks"). Exterior tanks are typically connected to an aircraft fuel system by means of a two-part valve which comprises an aircraft valve attached to the aircraft and a complimentary valve on the tank. The valve must provide a connection between the external tank and the aircraft system and provide a leak-proof seal between the tank and the aircraft.

    [0003] A fuel tank valve according to an existing design is shown in Figure 1 (with a cross sectional profile shown in Figure 1b). The valve 10 comprises a valve body 12 having a generally cylindrical profile so as to define a central bore through which fluid may flow. A telescopic seal member 14 is received within the valve body and extends the central bore beyond the external surface 24 of the valve body 12. The telescopic seal member 14 is biased towards an extended position by a spring 18. In use, the spring is intended to be in a compressed state, as the telescopic seal member 14 is at least partial pressed back into the valve body 12. Thus, the spring provides a sealing force at the seal surfaces. The proximal (i.e. internal) end of the telescopic seal member 14 is provided with a seat 22 on its external surface for receiving an O-ring to seal against the internal surface of the valve body 12. The distal (i.e. external) end of the telescopic seal member 14 is provided with a resilient portion in the form of a compressible elastomer seal 20 which, in use, is intended to form a sealing engagement with a planar seal surface of the aircraft. The telescopic member 14 is arranged such that it has a degree of lateral freedom within the valve body. Specifically, a clearance gap is maintained between the telescopic seal member 14 and both the valve body 12 (for example between the seal seat 22 and the internal surface of the valve body 12) and the hole 26 in the outer surface 24 of the valve body. Additionally, the telescopic seal member is provided with a tapered external profile which converges slightly towards its distal end. The telescopic seal member may for example be arranged such that it may tilt its.longitudinal axis by up to 5 degrees. This freedom is intended to allow the seal to both align with the aircraft seal surface when fitted to the aircraft and to accommodate any relative dynamic movement between the tank and aircraft during manoeuvres on the ground or in flight.

    [0004] It has been found that a cause of leakage in existing designs is a result of the seal surface losing full contact with the aircraft seal surface. In particular, in the case of lateral movement between the aircraft and the tank (which may for example be the result of rapid manoeuvring) the high friction between the elastomer seal 20 and the seal surface may partially prevent the elastomer seal from sliding across the surface resulting in angling of the seal. Embodiments of the invention seek to provide a valve arrangement with an improved leak resistance and, in particular, an arrangement with an increased leak resistance during aircraft manoeuvers.

    [0005] Accordingly, a first aspect of the present invention provides a valve for connecting an external tank to an aircraft, the valve comprising:

    a valve body; and

    a seal assembly arranged, in use, to resiliently engage a seal surface of an aircraft, the seal assembly comprising:

    a telescopic seal member extending from a proximal end within the valve body to a distal end, the telescopic seal member being constrained within the valve body so as to maintain axial alignment of the telescopic seal member and the valve body; and

    a seal carrier provided at the distal end of the telescopic seal member, the seal carrier being pivotable relative to the telescopic seal member for alignment, in use, with the aircraft seal surface.



    [0006] Advantageously, the provision of a pivotable seal carrier ensures that the seal assembly of the valve is able to accommodate relative angular movement between the tank and the aircraft seal surface at a location which is only a short distance from the valve mating surfaces. This acts to discourage the seal from tilting on the aircraft seal surface, which may otherwise result in partial seal opening.

    [0007] The distal end of the telescopic seal member and the seal carrier may be provided with complimentary bearing surfaces which enable the seal carrier to pivot relative to the telescopic seal member and provide a sealing surface between the seal carrier and the telescopic seal member. Preferably, the distal end of the telescopic seal member comprises a generally convex bearing surface and the seal carrier comprises a complimentary concave bearing surface. Alternatively, it will be appreciated that the surfaces may be reverse such that the distal end of the telescopic seal member comprises a generally concave bearing surface and the seal carrier comprises a complimentary convex bearing surface.

    [0008] The seal carrier may have a single degree of freedom (for example by providing a radial bearing surface) which would typically be aligned with the expected plane of the flexure ' of the tank in use. Preferably, a spherical bearing is provided between the seal carrier and the telescopic seal member (such that the seal member may align to any angular displacement of the tank).

    [0009] Advantageously, a spherical bearing may be arranged such that the seal carrier may rotate about its longitudinal axis and may thereby enable the seal carrier to accommodate rotational movement between the tank and the aircraft. This provides a further advantage over the existing arrangement in which both the seal surface of the elastomer seal and the O-ring between the valve body and telescopic seal member provide friction forces which act to resist rotation movement of the seal.

    [0010] It will be appreciated that a spherical bearing requires at least one of the complimentary bearing surfaces to have a substantially spherical surface profile. The other of the complimentary bearing surfaces may be substantially spherical, substantially conical (for example frustoconical) or simply a circumferential edge.

    [0011] The valve body may comprise an external surface which, in use, opposes a surface of an aircraft and wherein the surface is provided with a hole through which the telescopic seal member protrudes, said hole being dimensioned and sized to closely match the external profile of the telescopic seal member. Thus the hole may be arranged to enable axial movement and/or rotation of the telescopic seal member about its longitudinal axis but will limit tilting of the telescopic seal member axis.

    [0012] The valve body may comprise a generally cylindrical body and the telescopic seal member may comprises a generally cylindrical body having an external diameter which is less that the internal diameter of the valve body so as to be received within the valve body. A seal may typically be provided between the internal surface of the valve body and the external surface of the telescopic seal member. For example the external surface of the telescopic seal may be provided with a valve seat which retains an o-ring in sealing engagement with the valve body. The valve seat may be dimensioned and sized to closely match the internal diameter of the valve body.

    [0013] A biasing means, for example a spring, is typically disposed between the valve body and the telescopic seal member and arranged to bias the telescopic seal member toward an extended position.

    [0014] The seal carrier may comprise an abutment surface for engaging, in use, a seal surface on an aircraft. The abutment surface may comprise a seal seat. The abutment surface is substantially planar so as to allow the seal carrier to slide across the aircraft seal surface in the event of relative lateral displacement between the tank and the aircraft. The abutment surface may be provided with an O-ring which may be partially recessed into the abutment surface.

    [0015] The seal carrier may be generally annular. The seal carrier may be arranged to engage the distal end of the telescopic seal member. The seal carrier may resiliently engage the telescopic seal member, for example the seal carrier may be mounted on the telescopic seal member by a snap fit arrangement. The seal carrier and telescopic seal member may be provided with mutual engagement features to retain the seal carrier thereon, for example the mutual engagement features may comprise a complimentary tab and recess. The mutual engagement features may comprise a circumferential recess on the inner surface of the seal carrier and an outwardly extending tab on the outer surface of the distal end of the telescopic seal member arranged to engage the recess.

    [0016] A mechanical stop may be provided to limit the range of motion of the seal carrier with respect to the telescopic seal member. The mutual engagement features may be further configured to provide a stop to limit the range of motion of the seal carrier.

    [0017] The valve body and seal assembly may define a central bore (through which fluid flows in use) which may generally extend along the longitudinal axis of the valve. A valve engagement member may extend through the central bore, and shaped and configured to engage an opening mechanism of a valve on an aircraft.

    [0018] The seal carrier may be adapted for alignment, in use, with a planar aircraft seal surface or a non-planar aircraft seal surface.

    [0019] According to a second aspect of the invention there is provided an external tank for an aircraft comprising a valve in accordance with embodiments of the invention. The external tank may be an aircraft fuel tank. The external tank may comprise a plurality of valves in accordance with embodiments of the invention.

    [0020] Whilst the invention has been described above, it extends to any inventive combination of features set out above or in the following description or drawings.

    [0021] Specific embodiments of the invention will now be described in detail, by way of example only, and with reference to the accompanying drawings in which:

    Figure 1a is a schematic three dimensional view of an existing valve for an external fuel tank;

    Figure 1b is a schematic three dimensional cross sectional view of the valve of Figure 1a;

    Figure 2a is a schematic three dimensional view of a valve for an external fuel tank according to an embodiment of the invention;

    Figure 2b is a schematic three dimensional cross sectional view of the valve of Figure 2a;

    Figure 3a and 3b is schematic cross sectional detail of the valve of Figure 2;

    Figure 4 is a schematic partial cross section of an alternate seal assembly in accordance with an embodiment of the invention; and

    Figure 5 is a schematic partial cross section of a further alternate seal assembly in accordance with another embodiment of the invention.



    [0022] A valve 100 in accordance with an embodiment of the invention is shown in Figure 2. The valve comprises a valve body 112 is formed from aluminium and has a substantially cylindrical body with a cylindrical internal surface which is arranged to receive a telescopic seal member 114. A central bore for the flow of fluid extends along the longitudinal axis of the valve body 112 and along the longitudinal axis of the telescopic seal member 114. The valve body 112 is provided with an outer annular channel 113, which surrounds the central bore, for accommodating the telescopic seal member 114 such that the diameter of the central bore may remain substantially constant throughout the valve.

    [0023] The telescopic seal member 114 comprises a cylindrical aluminium pipe and is arranged to extend from the body and, in use, to engage a seal surface on an aircraft in a sealing arrangement. A steel spring 118 is provided between the telescopic seal member 114 and the valve 112 so as to bias the telescopic seal member out of the valve body 112.

    [0024] The valve 100 further comprises a valve engagement member 116 which extends through the central bore of both the telescopic seal member and the valve body to engage a valve member on a complimentary valve part mounted on an aircraft. As best seen in Figure 2b, with the spring 118 is compressed and the telescopic seal member 114 partially retracted into the valve body 112 the engagement member 116 extends beyond the seal surface of the valve 100.

    [0025] In accordance with the invention, a seal carrier 150 is disposed upon the distal end of the telescopic seal member 114. A spherical bearing 160 is provided between the seal carrier 150 and the telescopic seal member 114 such that the seal carrier 125 is pivotable relative to the telescopic seal member 114 to enable alignment with a seal surface of an aircraft. The arrangement of the seal carrier is explained in further detail below.

    [0026] The telescopic seal member 114 is arranged within the valve 100 such that it is held in axial alignment with the valve body 112. In particular, relative rotation of the axis of the telescopic seal member 114 is prevented by the provision of a hole 126 in the external surface 124 of the valve body 112 which is dimensioned and sized to closely match the external diameter of the telescopic seal member 114. Typically, the hole 126 and the telescopic seal member 114 could be arranged with a clearance fit such that the telescopic seal member can freely slide in an axial direction or rotate about its longitudinal axes but would be maintained in alignment. Additionally, a seal arrangement 122 is provided at the proximal (internal) end of the telescopic member 114 and is also configured to help maintain the axial alignment of the telescopic seal member. The seal is provided between the external surface of the telescopic seal member 114 and the internal surface of the valve body 112 and comprises a seal seat 122 for receiving an O-ring. The seal seat is formed by a pair of radially extending circumferential ridges 112A and 112B on the external surface of the telescopic seal member 114. Each of the ridges 122A and 122B are sized so as to maintain the desired spacing between the telescopic seal member 114 and the valve body 112. Typically, a clearance fit may be provided between the seal seat 122 and the valve body 112 thereby maintaining the axial alignment of the telescopic seal member and the valve body.

    [0027] As best seen in Figures 3a and 3b, the seal carrier 150 and the external distal end of the telescopic seal member 114 are provided with complimentary profiles which allow the seal carrier to be retained on the telescopic seal member 114 while also allowing rotation of the seal carrier with respect to the telescopic seal member 114. The seal carrier 150 is typically formed from a plastic material, for example nylon, such that it may resiliently engage the telescopic seal member 114. The seal carrier is, therefore, a "snap-fit" arrangement which undergoes plastic deformation in order to pass over a mutual engagement feature on the telescopic seal member 114 and to be retained thereon. The seal carrier 150 has a generally annular profile and is provided with a substantially planar abutment surface 154 which is arranged to engage a seal surface of an aircraft in use. The abutment surface 154 typically comprises a recessed seal seat 156 for receiving and captivating an O-ring 152. The seal seat may be provided with a profile which converges as the recess extends towards the abutment surface 154 such that an O-ring may be inserted into the seal seat by plastic deformation before being retained therein (as shown in Figure 3b). The abutment surface 154 forms the outer boundary of a mouth 172 which is connected to the central bore of the valve 100. Adjacent to the mouth 172 the inner surface of the seal carrier 150 is provided with a convex surface in the form of a frustoconical bearing surface 170. The bearing surface 170 terminates at an outwardly extending circumferential recess 174 which is partially closed by an inwardly radially projecting circumferential wall 176 which forms the proximal end of the seal carrier 150.

    [0028] The distal end of the telescopic seal member 114 is provided with a convex surface in the form of a spherical bearing surface 180 which is arranged to have a complimentary profile to the conical bearing surface 170 of the seal carrier 150. The spherical bearing surface 180 extends a short distance from the tip of the telescopic seal member 114 and terminates at an inwardly extending circumferential recess 184. The transition between the spherical bearing surface 180 and the external circumferential recess 184 forms a tab 182 which comprises a substantially radially extending wall. The recess 184 and tab 182 of the telescopic seal member have a complimentary profile to the wall 176 and recess 174 of the seal carrier 150 so as to provide mutual engagement features.

    [0029] Accordingly, the seal carrier 150 may be installed upon the telescopic seal member 114 (as shown in Figure 3b) by plastic deformation as the inwardly projecting wall 176 of the seal carrier 150 deflects outwardly as it slides across the spherical bearing surface 180 of the telescopic seal member 180 before returning to its non-deformed position within the recess 184. The tab 182 and wall 176 prevent removal of the seal carrier 150 and also act to provide a physical stop which limits the extent to which the seal carrier 150 is able to rotate with respect to the telescopic seal member 114 (this may be seen on the left hand side of the seal carrier 150 in Figure 2b which has reached the limit of its range of motion). While the cooperating features of the seal carrier 150 and the telescopic seal member 114 are typically circumferentially continuous, it will be appreciated that they could be formed from a plurality of sections, for example the tab 182 could be formed of a number of discrete tab sections spaced around the periphery of the telescopic seal member 114.

    [0030] In use, as best seen in Figure 2b, the valve is mounted to an aircraft such that the abutment surface 154 of the seal carrier 150 engages a seal surface of the aircraft. The aircraft seal surface is substantially planar and surrounds a spring loaded valve which is biased towards a normally closed position. As the external tank is positioned upon the aircraft the first contact between the valve 100 and the aircraft is between the seal surface of the aircraft and the seal carrier 150 which may pivot in any direction relative to the axis of the valve 100 to align with the aircraft seal surface. As the tank is moved further into position the valve surfaces are compressed against each other to provide a good sealing engagement and the spring 118 is compressed as the telescopic seal member 114 is partially retracted into the valve body 112 (for example to the position shown in figure 2b). It will be appreciated that the extent to which the telescopic seal member is retracted may depend upon the particular mounting that the external tank is being used for. As the telescopic seal member 114 retracts the valve engagement member 116 begins to protrude beyond the plane of the abutment surface 154 of the seal carrier 150 (which is the plane of aircraft seal surface). Thus, the valve engagement member 114 may engage the spring loaded valve on the aircraft and move it to an open position such that the valve of the fuel tank and the aircraft valve are placed in fluid communication. In the event of movement between the tank and aircraft (for example during aircraft manoeuvres) the seal is able retain sealing engagement whilst accommodating the movement. Specifically: axial movement is accommodated by movement between the telescopic seal member and the valve body; rotational or tilting movement is accommodated by the movement of the spherical bearing between the seal carrier and the telescopic member; and lateral movement is accommodated by sliding between the parallel aligned sealing surfaces of the seal carrier and the aircraft seal surface.

    [0031] Figure 4 shows an alternate seal assembly 400 which may be used in alternate embodiments. The seal assembly 400 is equivalent to that of the earlier embodiment but uses a reverse orientated spherical bearing arrangement 460 between the seal carrier 450 and telescopic seal member 414. Accordingly, the telescopic seal member 460 is provided with a concave bearing surface and the seal carrier 450 is provided with a convex bearing surface. The convex surface would typically be spherical and the concave surface frustoconical.

    [0032] Figure 5 shows an alternate seal assembly 500 which may be used in further embodiments. The seal assembly 500 in this embodiment is provided with a radial bearing surface 560 between the between the seal carrier 550 and telescopic seal member 514. This arrangement limits the movement of the seal carrier to pivoting in a single plane. Rotational movement between in this arrangement is also limited compared to embodiments using spherical bearings since rotation movement is accommodated by rotation of the telescopic seal member 514 relative to the valve body. This rotational movement must overcome the frictional forces of the seals (as indicated by locations A and B on figure 5) and rotational resistance of the spring 518.

    [0033] It may be noted that the spherical bearing of the preferred embodiment consists of the combination of a spherical and a frustoconical bearing surface. This provides a line contact between the bearing surfaces and reduces the tolerances required in manufacturing of the surfaces (with the key requirement being only that the mating surfaces have a good surface quality). A frustoconical bearing surface also provides a more wear resistant bearing than a circumferential edge contact arrangement.

    [0034] It will be appreciated that the present invention is intended to be compatible with existing aircraft valve parts without requiring modification. It will also be appreciated that the valve body according to embodiments of the invention may be substantially identical to the valve body of existing designs. Accordingly, a seal assembly according to embodiments of the invention may be retrofitted to an existing valve body to provide
    a valve in accordance with the invention.


    Claims

    1. A valve (100) for connecting an external tank to an aircraft, the valve comprising:

    a valve body (112); and

    a seal assembly arranged, in use, to resiliently engage a seal surface on an aircraft, the seal assembly comprising:

    a telescopic seal member (114) extending from a proximal end within the valve body (112) to a distal end, the telescopic seal member being constrained within the valve body so as to maintain axial alignment of the telescopic seal member and the valve body (112); and

    a seal carrier (150) characterised in that is provided at the distal end of the telescopic seal member (114), the seal carrier (150) being pivotable relative to the telescopic seal member (114) for alignment, in use, with the aircraft seal surface.


     
    2. A valve (100) as claimed in claim 1, wherein the distal end of the telescopic seal member (114) comprises a generally convex bearing surface (180) and the seal carrier (150) comprises a complimentary concave bearing surface (170).
     
    3. A valve (100) as claimed in claim 1 or 2, wherein a spherical bearing is provided between the seal carrier (150) and the telescopic seal member (114).
     
    4. A valve (100) as claimed in any preceding claim, wherein the valve body (112) further comprises an external surface which, in use, opposes a surface of an aircraft and wherein the surface is provided with a hole (126) through which the telescopic seal member (114) protrudes, said hole being dimensioned and sized to closely match the external profile of the telescopic seal member (114).
     
    5. A valve (100) as claimed in any preceding claim, wherein the valve body (112) comprises a generally cylindrical body and the telescopic seal member (114) comprises a generally cylindrical body having an external diameter which is less that the internal diameter of the valve body (112) so as to be received within the valve body.
     
    6. A valve (100) as claimed in claim 5, wherein a seal (122) is provided between the internal surface of the valve body (112) and the external surface of the telescopic seal member (114).
     
    7. A valve (100) as claimed in any preceding claim, further comprising a biasing means (18) disposed between the valve body (112) and the telescopic seal member (114) and arranged to bias the telescopic seal member (114) toward an extended position.
     
    8. A valve (100) as claimed in any preceding claim, wherein the seal carrier (150) further comprises an abutment surface (154) for engaging, in use, a seal surface on an aircraft and wherein the abutment surface comprises a seal seat (152).
     
    9. A valve (100) as claimed in any preceding claim, wherein the seal carrier (150) is generally annular and is arranged to resiliently engage the distal end of the telescopic seal member (114).
     
    10. A valve (100) as claimed in claim 9, wherein the seal carrier (150) and telescopic seal member (114) are provided with mutual engagement (184, 182; 176, 174) features to retain the seal carrier (150).
     
    11. A valve as claimed in claim 10, wherein the mutual engagement features comprise a circumferential recess (174) on the inner surface of the seal carrier (150) and an outwardly extending tab (182) on the outer surface of the distal end of the telescopic seal member (114) arranged to engage the recess (174).
     
    12. A valve (100) as claimed in claim 10 or 11, wherein the mutual engagement features are further configured to provide a stop to limit the range of motion of the seal carrier (150).
     
    13. A valve as claimed in any preceding claim, further comprising a valve engagement member (116) extending through a central bore, defined by the valve body and seal assembly, and shaped and configured to engage an opening mechanism of a valve on an aircraft.
     
    14. An external tank for an aircraft comprising a valve (100) as claimed in any preceding claim.
     


    Ansprüche

    1. Ventil (100) zum Verbinden eines externen Tanks mit einem Flugzeug, wobei das Ventil Folgendes umfasst:

    einen Ventilkörper (112); und

    eine Dichtungsgruppe, die in Gebrauch dafür ausgelegt ist, sich elastisch mit einer Dichtungsfläche an einem Flugzeug zu verbinden,

    wobei die Dichtungsgruppe Folgendes umfasst:

    ein teleskopisches Dichtungselement (114), das sich von einem proximalen Ende innerhalb des Ventilkörpers (112) bis zu einem distalen Ende erstreckt, wobei das teleskopische Dichtungselement innerhalb des Ventilkörpers eingeschränkt ist, um so eine axiale Ausrichtung des teleskopischen Dichtungselementes und des Ventilkörpers (112) aufrechtzuerhalten; und

    dadurch gekennzeichnet, dass

    ein Dichtungsträger (150) am distalen Ende des teleskopischen Dichtungselementes (114) vorgesehen ist, wobei der Dichtungsträger (150) gegenüber dem teleskopischen Dichtungselement (114) im Gebrauch zur Ausrichtung zur Dichtungsfläche des Flugzeugs drehbar ist.


     
    2. Ventil (100) nach Anspruch 1, wobei das distale Ende des teleskopischen Dichtungselementes (114) eine im allgemeinen konvexe Lagerfläche (180) umfasst, und der Dichtungsträger (150) eine komplementäre konkave Lagerfläche (170) umfasst.
     
    3. Ventil (100) nach Anspruch 1 oder 2, wobei ein Kugellager zwischen dem Dichtungsträger (150) und dem teleskopischen Dichtungselement (114) vorgesehen ist.
     
    4. Ventil (100) nach einem der vorhergehenden Ansprüche, wobei der Ventilkörper (112) ferner eine externe Fläche umfasst, die im Gebrauch einer Fläche eines Flugzeugs gegenüberliegt und wobei die Fläche mit einem Loch (126) versehen ist, durch welches das teleskopische Dichtungselement (114) vorragt, wobei das Loch so bemessen und dimensioniert ist, dass es zum externen Profil des teleskopischen Dichtungselementes (114) passt.
     
    5. Ventil (100) nach einem der vorhergehenden Ansprüche, wobei der Ventilkörper (112) einen im Allgemeinen zylindrischen Körper umfasst, und das teleskopische Dichtungselement (114) einen im Allgemeinen zylindrischen Körper umfasst, der einen Außendurchmesser hat, welcher kleiner ist als der Innendurchmesser des Ventilkörpers (112), so dass er innerhalb des Ventilkörpers aufgenommen wird.
     
    6. Ventil (100) nach Anspruch 5, wobei eine Dichtung (122) zwischen der internen Fläche des Ventilkörpers (112) und der Außenfläche des teleskopischen Dichtungselementes (114) vorgesehen ist.
     
    7. Ventil (100) nach einem der vorhergehenden Ansprüche, das ferner ein Vorspannmittel (18) umfasst, das zwischen dem Ventilkörper (112) und dem teleskopischen Dichtungselement (114) angeordnet ist und dafür ausgelegt ist, das teleskopische Dichtungselement (114) gegen eine erweiterte Position vorzuspannen.
     
    8. Ventil (100) nach einem der vorhergehenden Ansprüche, wobei der Dichtungsträger (150) ferner eine Widerlagerfläche (154) zum Kontakt im Gebrauch mit einer Dichtungsfläche an einem Flugzeug umfasst, und wobei die Widerlagerfläche einen Dichtungssitz (152) umfasst.
     
    9. Ventil (100) nach einem der vorhergehenden Ansprüche, wobei der Dichtungsträger (150) im Allgemeinen ringförmig ist und dafür ausgelegt ist, elastisch in das distale Ende des teleskopischen Dichtungselementes (114) einzugreifen.
     
    10. Ventil (100) nach Anspruch 9, wobei der Dichtungsträger (150) und das teleskopische Dichtungselement (114) mit Merkmalen eines wechselseitigen Eingriffs (184, 182; 176, 174) versehen sind, um den Dichtungsträger (150) zu sichern.
     
    11. Ventil nach Anspruch 10, wobei die Merkmale des wechselseitigen Eingriffs eine periphere Vertiefung (174) auf der Innenfläche des Dichtungsträgers (150) und einen sich nach außen erstreckenden Tab (182) auf der Außenfläche des distalen Endes des teleskopischen Dichtungselementes (114) umfassen, die für den Eingriff in die Vertiefung (174) ausgelegt sind.
     
    12. Ventil (100) nach Anspruch 10 oder 11, wobei die Merkmale des wechselseitigen Eingriffs ferner dazu ausgelegt sind, für einen Stopp zu sorgen, um den Bewegungsbereich des Dichtungsträgers (150) zu beschränken.
     
    13. Ventil nach einem der vorhergehenden Ansprüche, das ferner ein Ventileingriffselement (116) umfasst, das sich durch eine Mittelbohrung erstreckt, die durch den Ventilkörper und die Dichtungsgruppe definiert ist und die geformt und dafür ausgelegt ist, in einen Öffnungsmechanismus eines Ventils an einem Flugzeug einzugreifen.
     
    14. Externer Tank für ein Flugzeug, der ein Ventil (100) nach einem der vorhergehenden Ansprüche umfasst.
     


    Revendications

    1. Soupape (100) pour raccorder un réservoir externe à un aéronef, la soupape comprenant :

    un corps de soupape (112) ; et

    un ensemble d'étanchéité aménagé en service pour s'engager de manière élastique sur une surface d'étanchéité sur un aéronef, l'ensemble d'étanchéité comprenant :

    un élément d'étanchéité télescopique (114) s'étendant d'une extrémité proximale dans le corps de soupape (112) à une extrémité proximale, l'élément d'étanchéité télescopique étant contraint dans le corps de soupape de manière à maintenir l'alignement axial de l'élément d'étanchéité télescopique et du corps de soupape (112) ; et

    un support de joint étanche (150), caractérisé en ce qu'il est disposé à l'extrémité distale de l'élément d'étanchéité télescopique (114), le support de joint étanche (150) pouvant pivoter par rapport à l'élément d'étanchéité télescopique (114) pour un alignement en service avec la surface d'étanchéité de l'aéronef.


     
    2. Soupape (100) selon la revendication 1, dans laquelle l'extrémité distale de l'élément d'étanchéité télescopique (114) comprend une surface de palier généralement convexe (180) et le support de joint étanche (150) comprend une surface de palier concave complémentaire (170).
     
    3. Soupape (100) selon la revendication 1 ou la revendication 2, dans laquelle un palier sphérique est disposé entre le support de joint étanche (150) et l'élément d'étanchéité télescopique (114).
     
    4. Soupape (100) selon l'une quelconque des revendications précédentes, dans laquelle le corps de soupape (112) comprend en outre une surface externe qui, en service, est en regard d'une surface d'un aéronef et dans laquelle la surface est pourvue d'un trou (126) à travers lequel l'élément d'étanchéité télescopique (114) fait saillie, ledit trou étant dimensionné et calibré pour correspondre étroitement au profil externe de l'élément d'étanchéité télescopique (114).
     
    5. Soupape (100) selon l'une quelconque des revendications précédentes, dans laquelle le corps de soupape (112) comprend un corps généralement cylindrique et l'élément d'étanchéité télescopique (114) comprend un corps généralement cylindrique ayant un diamètre externe qui est inférieur du diamètre interne du corps de soupape (112) de manière à être reçu dans le corps de soupape.
     
    6. Soupape (100) selon la revendication 5, dans laquelle un joint étanche (122) est disposé entre la surface interne du corps de soupape (112) et la surface externe de l'élément d'étanchéité télescopique (114).
     
    7. Soupape (100) selon l'une quelconque des revendications précédentes, comprenant en outre un moyen de sollicitation (18) disposé entre le corps de soupape (112) et l'élément d'étanchéité télescopique (114) et aménagé pour presser l'élément d'étanchéité télescopique (114) vers une position d'extension.
     
    8. Soupape (100) selon l'une quelconque des revendications précédentes, dans laquelle le support de joint étanche (150) comprend en outre une surface de butée (154) pour s'engager en service sur une surface d'étanchéité d'un aéronef et dans lequel la surface de butée comprend un siège de joint étanche (152).
     
    9. Soupape (100) selon l'une quelconque des revendications précédentes, dans laquelle le support de joint étanche (150) est généralement annulaire et est aménagé pour s'engager de manière élastique sur l'extrémité distale de l'élément d'étanchéité télescopique (114).
     
    10. Soupape (100) selon la revendication 9, dans lequel le support de joint étanche (150) et l'élément d'étanchéité télescopique (114) sont pourvus de dispositifs d'engagement mutuel (184, 182 ; 176, 174) pour retenir le support de joint étanche (150).
     
    11. Soupape selon la revendication 10, dans laquelle les dispositifs d'engagement mutuel comprennent une cavité circonférentielle (174) sur la surface interne du support de joint étanche (150) et une patte (182) s'étendant vers l'extérieur sur la surface externe de l'extrémité distale de l'élément d'étanchéité télescopique (114) aménagée pour s'engager dans la cavité (174).
     
    12. Soupape (100) selon la revendication 10 ou la revendication 11, dans laquelle les dispositifs d'engagement mutuel sont en outre configurés pour fournir un arrêt permettant de limiter la plage de déplacement du support de joint étanche (150).
     
    13. Soupape selon l'une quelconque des revendications précédentes, comprenant en outre un élément d'engagement de soupape (116) s'étendant à travers un alésage central, défini par le corps de soupape et l'ensemble d'étanchéité et formé et configuré pour s'engager dans un mécanisme d'ouverture d'une soupape sur un aéronef.
     
    14. Réservoir externe pour un aéronef comprenant une soupape (100) selon l'une quelconque des revendications précédentes.
     




    Drawing