GB2577128A

GB2577128A - Connector

Info

Publication number: GB2577128A
Application number: GB1815119.1A
Authority: GB
Inventors: Healy Daren; Ruiz-De-Pablo Javier; Bird James
Original assignee: Airbus Operations Ltd
Current assignee: Airbus Operations Ltd
Priority date: 2018-09-17
Filing date: 2018-09-17
Publication date: 2020-03-18
Also published as: GB201815119D0

Abstract

A connector 1 for connecting a conduit to a source of fluid 50 and establishing a fluid flow path between the conduit and the source of fluid comprises a first 2 and second 3 connector portions. The first portion attaches to a source of fluid, and the second portion attaches to a conduit. The first and second connector portions have first and second mating configurations 8, 12 respectively, which, when brought into a mating arrangement, prevent relative rotation of the connector portions. The connector further comprises means of securing 6, 15 the first and second portions together to form a sealing engagement between the first and second connector portions. The invention also encompasses and aircraft fluid transmission arrangement, an aircraft wing with such a fluid transmission arrangement, and an aircraft comprising the wing and/or the fluid transmission arrangement. A method of forming a connection using the fluid transfer arrangement comprises forming a sealing engagement between the first and second connector portions without applying a force to the conduit or the second connector portion to inhibit rotation of the conduit. A further method comprises using a single tool to form a sealing engagement between the first and second connector portions.

Description

(71) Applicant(s):

Airbus Operations Limited

Pegasus House, Aerospace Avenue, Filton, BRISTOL, BS34 7PA, United Kingdom (72) Inventor(s):

Daren Healy

Javier Ruiz-De-Pablo

James Bird (74) Agent and/or Address for Service:

Abel & Imray

Westpoint Building, James Street West, Bath,

BA1 2DA, United Kingdom (51) INT CL:

F16L 19/00 (2006.01) F16L 19/02 (2006.01)

F16L 19/025 (2006.01) (56) Documents Cited:

US 3064998 A US 20080296893 A1

US 20020175519 A1 (58) Field of Search:

INT CLF16L

Other: EPODOC, WPI (54) Title of the Invention: Connector

Abstract Title: Connector ensuring no relative rotation between two connector portions (57) A connector 1 for connecting a conduit to a source of fluid 50 and establishing a fluid flow path between the conduit and the source of fluid comprises a first 2 and second 3 connector portions. The first portion attaches to a source of fluid, and the second portion attaches to a conduit. The first and second connector portions have first and second mating configurations 8, 12 respectively, which, when brought into a mating arrangement, prevent relative rotation of the connector portions. The connector further comprises means of securing 6, 15 the first and second portions together to form a sealing engagement between the first and second connector portions. The invention also encompasses and aircraft fluid transmission arrangement, an aircraft wing with such a fluid transmission arrangement, and an aircraft comprising the wing and/or the fluid transmission arrangement. A method of forming a connection using the fluid transfer arrangement comprises forming a sealing engagement between the first and second connector portions without applying a force to the conduit or the second connector portion to inhibit rotation of the conduit. A further method comprises using a single tool to form a sealing engagement between the first and second connector portions.

1/5

2/5

100

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4/5

1000

5/5

Prior Art

Connector

BACKGROUND OF THE INVENTION [0001] The present disclosure relates to a connector for connecting a conduit to a source of fluid and establishing a fluid flow path between a conduit and a source of fluid.

[0002] The present invention concerns connectors for establishing a fluid flow path. More particularly, but not exclusively, this invention concerns a connector for connecting a conduit to a source of fluid and establishing a fluid flow path between a conduit and a source of fluid. The invention also concerns connector portions for use in a connector, a fluid transfer arrangement, an aircraft fluid transmission arrangement, an aircraft wing and an aircraft.

[0003] Conventional hose connectors comprise a screw thread or the like which is used to secure a hose to a source of fluid (such as a source of hydraulic fluid), the source of fluid being provided with a corresponding screw thread which mates with the connector thread. Tightening of the screw threads urges the two parts of the connector into sealing engagement with one another. Such arrangements will typically remain in sealing engagement if no torsional or turning force is applied to the hose. However, if a torsional or turning force were to be applied to the hose, then this force may be transmitted to the connector, resulting in possible loosening of the screw thread joint and leaking of fluid. This is obviously undesirable.

[0004] The present invention seeks to mitigate the above-mentioned problems. Alternatively or additionally, the present invention seeks to provide an improved connector.

SUMMARY OF THE INVENTION [0005] The present invention provides, according to a first aspect, a connector for connecting a conduit to a source of fluid and establishing a fluid flow path between a conduit and a source of fluid, the connector comprising:

a first connector portion for attachment to a source of fluid;

a second connector portion for attachment to a conduit;

the first and second connector portions being provided with first and second mating configurations, respectively, which are configured so that when brought into a mating arrangement with one another relative rotation of the first and second connector portions is prevented; and means of securing the first and second portion together to form a sealing engagement between the first and second connector portions.

[0006] Those skilled in the art will realise that neither the conduit nor the source of fluid are part of the connector of the first aspect of the present invention. The term “fluid” encompasses both liquids and gases.

[0007] The applicant has discovered that provision of such first and second mating configurations prevents rotation of the first and second portions of the connector which may be caused if a torsional or twisting force is applied to the second portion (for example, via a connected hose which is bent or kinked out of a plane). In a standard known connector, such torsional forces may exert a turning force on the second portion of the connector, which cause unwanted loosening of the connector that may cause a leak. The connector of the first aspect of the present invention prevents this from happening by preventing relative rotation of the first and second connector portions. Furthermore, it is anticipated that the connector of the first aspect of the present invention may present advantages, even when used with a hose which lies in one plane.

[0008] The first mating configuration may comprise a female or male configuration. The second mating configuration may comprise a male or female configuration. For example, if the first mating configuration comprises a female configuration, the second mating configuration typically comprises a male configuration. A female configuration typically comprises an opening that may comprise, for example, an aperture (i.e. a substantially two-dimensional opening), but more preferably comprise a passage (a three-dimensional opening). A male configuration typically comprises a projection for insertion into the opening provided in the female configuration. A male configuration may optionally be located about a channel for the passage therethrough of fluid.

[0009] The first and second mating configurations may be configured so that the first and second mating configurations can only be mated together at one relative orientation of the first and second mating configurations. This may be achieved, for example, if the first and second configurations are asymmetrical or do not have rotational symmetry. Alternatively, the first and second mating configurations may be configured so that the first and second mating configurations may be mated together at more than one relative orientation of the first and second mating configurations.

[0010] For the avoidance of doubt, the first and second connector portions may be provided with a plurality of first and second mating configurations. For example, the first connector portion may be provided with several female configurations configured to mate with several corresponding male configurations provided on the second connector portion.

[0011] A male mating configuration may have a cross-sectional shape selected from one or more of a polygon, a regular polygon, a rounded polygon, a rounded regular polygon, a curve of constant width, a Realeaux polygon and multilobular. An example of a male mating configuration with a multilobular shape is a Torx® hexalobular shape. Such male mating configurations may have the same cross-sectional shape (but optionally not the same cross-sectional area) along the length of the male mating configuration. A male mating configuration may comprise a prism (i.e. substantially the same cross-sectional shape and area along the length of the male mating configuration).

[0012] The means of securing the first and second connector portions together may comprise a first attachment configuration and a second attachment configuration, the first and second attachment configurations being complementary to one another to facilitate securing of the first and second connector portions. The first attachment configuration may be associated with the first connector portion and the second attachment configuration may be associated with the second connector portion. The first connector portion may comprise the first attachment configuration and the second connector portion may comprise the second attachment configuration. The first and second attachment configurations may each comprise a thread, for example, the first and second attachment configurations together forming complementary threads.

[0013] For example, the first connector portion may be provided with a first screw thread (typically provided on an external surface of the first portion). The connector may be provided with a second attachment component (such as a nut) provided with a second screw thread (typically on an internal surface) which mates with the first screw thread. The second attachment component (e.g. the nut) may be associated with the second connector portion. For example, the second attachment component may be attached to the second connector portion so that it cannot be detached from the second connector portion.

[0014] The first and second attachment configurations may, for example, comprise two complementary parts of a bayonet fitting.

[0015] The second connector portion may comprise an interface for sealing engagement with a conduit. The connector, and optionally the second connector portion, may comprise a rotational coupling for the attachment of a conduit, the rotational coupling permitting rotation of an attached coupling relative to the second connector portion. The rotational coupling may provide the interface for sealing engagement with a conduit.

[0016] One or both of the first and second connector portions may comprise a seal member. When the first and second portions are secured together, the seal member(s) forms a seal to inhibit egress of fluid from the connector.

[0017] The connector may optionally be suitable for use in aircraft hydraulic and/or pneumatic systems. In this connection, the connector may be suitable for withstanding pressures of at least 10 Bar, at least 70 Bar and at least 200 Bar. The connector may be suitable for withstanding pressures of up to 400 Bar, optionally up to 300 Bar and optionally up to 250 Bar.

[0018] The connector may optionally conform to aircraft authority standards, for example, one or more (and preferably each) of standards set by the European Aviation Safety Authority, the UK Civil Aviation Authority and the US Federal Aviation Authority, especially in relation to connectors for use in aircraft hydraulic and/or pneumatic systems.

[0019] According to a second aspect of the present invention there is also provided a first connector portion for use in the connector of the first aspect of the present invention.

[0020] According to a third aspect of the present invention there is also provided a second connector portion for use in the connector of the first aspect of the present invention.

[0021] According to a fourth aspect of the present invention, there is also provided a fluid transfer arrangement comprising a second connector portion in accordance with the third aspect of the present invention and a conduit for the passage of fluid therethrough attached to the second connector portion.

[0022] The conduit may be suitable for the transmission of hydraulic fluid (liquid or gas).

[0023] The conduit may optionally be suitable for use in aircraft hydraulic and/or pneumatic systems. In this connection, the connector may be suitable for withstanding pressures of at least 10 Bar, at least 70 Bar and at least 200 Bar. The conduit is optionally resistant to corrosion by hydraulic fluid. Those skilled in the art will realise that hydraulic fluid is typically a liquid. The conduit may be suitable for withstanding pressures of up to 400 Bar, optionally up to 300 Bar and optionally up to 250 Bar.

[0024] The conduit may optionally conform to aircraft authority standards, for example, one or more (and preferably each) of standards set by the European Aviation Safety Authority, the UK Civil Aviation Authority and the US Federal Aviation Authority, especially in relation to connectors for use in aircraft hydraulic and/or pneumatic systems.

[0025] The conduit may optionally be flexible. The present invention is particularly useful when used with flexible conduits which may be bent or twisted so as to apply an unwanted force on the connector. However, the present invention may also be used with non-flexible conduits, such as metal conduits (e.g. copper or stainless steel Piping).

[0026] The fluid transfer arrangement may be provided with a rotational coupling, optionally between two portions of conduit. The rotational coupling may be configured to permit rotation of a first portion of conduit relative to a second portion of conduit.

[0027] The fluid transfer arrangement of the fourth aspect of the present invention may comprise a first connector portion described above with reference to the connector of the first aspect of the present invention. Therefore, the fluid transfer arrangement of the fourth aspect of the present invention may comprise the connector in accordance with the first aspect of the present invention.

[0028] According to a fifth aspect of the present invention, there is also provided an aircraft fluid transmission arrangement comprising a first aircraft component, a connector in accordance with the first aspect of the present invention, a conduit and a second aircraft component, the connector and the conduit providing a fluid flow path from the first aircraft component to the second aircraft component. Transmission of fluid from a first aircraft component to a second aircraft component is therefore facilitated.

[0029] The first aircraft component may be a source of fluid, such as hydraulic fluid. The first aircraft component may comprise a pump and/or reservoir of fluid. The second aircraft component may comprise an actuator (or part thereof). The actuator (or part thereof) may be arranged to move a third aircraft component, such as any component that is typically moved using the aircraft’s hydraulic system. For example, the third aircraft component may comprise an aircraft control surface, a door (such as a cargo, undercarriage or passenger door), an undercarriage, a front wheel carriage, or a steering mechanism. The third aircraft component may comprise one or more aircraft control surface. The one or more aircraft control surface may comprise one or more of an aileron, elevator, rudder, spoiler, flap, slat, flaperon or air brake. The actuator (or part thereof) may be coupled to the third aircraft component with a spherical bearing or spherical joint.

[0030] According to a sixth aspect of the present invention, there is provided an aircraft wing comprising an aircraft fluid transmission arrangement in accordance with the fifth aspect of the present invention. The aircraft wing may comprise an aircraft control surface, and the second aircraft component of the aircraft fluid transmission arrangement may be arranged to move said control surface.

[0031] According to a seventh aspect of the present invention, there is provided an aircraft comprising an aircraft fluid transmission arrangement in accordance with the fifth aspect of the present invention, and/or an aircraft wing in accordance with the sixth aspect of the present invention.

[0032] According to any eighth aspect of the present invention, there is provided a method of forming a connection using a fluid transfer arrangement of the fourth aspect of the present invention comprising both first and second connector portions, the method comprising forming a sealing engagement between the first and second connector portions without applying a force to the conduit or the second connector portion to inhibit movement of the conduit or the second connector portion.

[0033] The first and second mating configurations inhibit relative rotation of the first and second connector portions and therefore a connection may be formed between the first and second connector portions without unwanted movement of the conduit or the second connector portion. Such unwanted movement would typically be a twisting force to the conduit applied about the long axis of the conduit or a bending force which would cause the conduit to bend. There is, therefore, no need to hold the conduit (aside from possibly supporting it) or second connector portion to provide a counter-force when the first and second connector portions are brought together. The method of the eighth aspect of the present invention therefore permits one-handed/one-tooled connection of the first and second connector portions.

[0034] Therefore, in accordance with the ninth aspect of the present invention, there is provided a method of forming a connection using a fluid transfer arrangement of the fourth aspect of the present invention comprising both first and second connector portions, the method comprising using a single tool to form a sealing engagement between the first and second connector portions. “Single” in this instance means one, and only one.

[0035] It will, of course, be appreciated that features described in relation to one aspect of the present invention may be incorporated into other aspects of the present invention.

DESCRIPTION OF THE DRAWINGS [0036] Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which: [0037] Figure 1 shows a perspective, exploded view of a connector according to a first embodiment of the invention;

[0038] Figure 2 shows a schematic view of a fluid transfer arrangement and an aircraft fluid transmission arrangement according to an embodiment of the invention;

[0039] Figure 3 shows a schematic view of an aircraft wing and aircraft according to an embodiment of the invention;

[0040] Figure 4 is a schematic diagram showing a method of forming a connection between first and second connector portions; and [0041] Figure 5 illustrates an embodiment of a method of forming a connection between first and second connector portions using a single tool, compared to prior art methods.

DETAILED DESCRIPTION [0042] An example of a connector according to a first embodiment of the invention will now be described with reference to Figures 1 and 2. The connector is denoted generally by reference numeral 1 and comprises a first connector portion 2 and a second connector portion 3. The connector 1 is for connecting a source of fluid (in this case, a body 50 of an actuator 55) to a conduit 60, and establishing a fluid flow path (typically a liquid flow path) between the conduit 60 and the source of fluid 50. The first connector portion 2 comprises a boss 4 that facilitates attachment of the first connector portion 2 to the body 50. A body portion 5 protrudes from the boss 4. A screw thread 6 is provided on the outer cylindrical surface of the body portion 5. Screw thread 6 complements a corresponding screw thread 16 provided on the internal surface of locking nut 15, the locking nut 15 being attached to second connector portion 3 (attached in this case means that the locking nut cannot be removed but is rotatable relative to the second connector portion 3). Nut 15 is depicted as being transparent in order to enable other features of the connector to be seen. Those skilled in the art will realise that nut 15 is not transparent. Screwing of the locking nut 15 onto the screw thread 6 secures the first and second connector portions together, and brings the seal member 11 provided on cylindrical base 10 of second connector portion 3 into sealing engagement with the seal surface 7 provided on body portion 5 of the first connector portion 2. The first and second connector portions 2, 3 are provided with channels 17, 13 for the passage therethrough of fluid from the actuator body 50 to the conduit 60.

[0043] The first connector portion 2 is provided with a first mating configuration 8 in the form of a female, receiving portion having a plurality of lobe spaces, two of which are labelled 20a, 20b. Mating configuration 8 is shaped to receive second mating configuration 12 provided on the second connector portion 3. Second mating configuration 12 is a male configuration in that is projects from cylindrical base 10, and is provided with a plurality of lobes (two of which are labelled 21a, 21b). Each of the lobes of second mating configuration 12 is configured to be received within a respective lobe space of the first mating configuration 8. The lobes and lobe spaces are configured so that the second mating configuration 12 will only be received by the first mating configuration 8 if the second connector portion 3 is rotated to one particular angle, relative to the first connector portion 2. This so-called “clocking” may be arranged so that the second connector portion 3 can only be attached to the first connector portion 2 in a preferred orientation. Once the first and second mating configurations 8, 12 have been mated together, the first and second connector portions

2, 3 cannot be rotated relative to one another, even if the nut 15 has not been used to secure the first and second connector portions together. This means that even if a torsional or turning force is applied to the second connector portion 3, then the second connector portion 3 cannot rotate relative to the first connector portion 2 and no loosening force is exerted by the second connector portion 3, for example, on locking nut 15. This means that the connector 1 may beneficially be used where torsional force may be applied to a connector by a conduit, such as a hose.

[0044] Second connector portion 3 comprises a bend 9. Those skilled in the art will realise that this is not an essential feature of the connector 1, but is provided in the present instance to reflect the preferred geometry of the second connector portion

3. Connector 1 also comprises a swivel joint or rotational coupling 14 for connection to a hose. The rotational coupling 14 permits rotation of an attached hose relative to the second connector portion 3. This reduces the risk of any torsional load being applied by an attached hose to connector 1.

[0045] Examples of a fluid transfer arrangement 80 and an aircraft fluid transmission arrangement 200 will now be described with reference to Figures 2 and

3. The fluid transfer arrangement 80 comprises the connector 1 to which is attached conduit 60. A wing 300 of an aircraft 400 comprises an aircraft fluid transmission arrangement 200, the aircraft fluid transmission arrangement comprising a first aircraft component in the form of the main body 50 of actuator 55, connector 1, conduit 60 and a second aircraft component in the form of movable actuator component 100. The connector 1 and conduit 60 facilitate supply of fluid (in this case, hydraulic fluid) from the actuator main body 50 to the movable actuator component 100. As explained above, connector 1 prevents unwanted application of a torsional force to the joint between the first and second connector portions 2, 3, and therefore prevents leaks associated with such torsional forces from occurring. Movable actuator component 100 is coupled to a flaperon 110 by a ball joint 120. The ball joint 120 allows the movable actuator component to be non-normal to the hinge line of the flaperon 110.

[0046] The embodiment of the connector 1 is advantageous in that it facilitates forming a connection using only one hand/one tool. Referring to Figs. 1, 4 and 5, part C, an embodiment of a method of forming a connection will now be described. The method is denoted generally by reference numeral 1000 and comprising bringing 1001 second mating configuration 12 of the second connector portion 3 into mating engagement with first mating configuration 8 of the first connector portion 2. Conduit 60 is attached to second connector portion 3. The method 1001 also comprises securing 1002 the first and second connector portions into sealing engagement by rotating nut 15 onto screw thread 6 using a single tool Tl. The mating engagement between the first and second mating configurations prevents rotation of the second connector portion and therefore the conduit 60, relative to the first connector portion as the nut 15 is screwed onto screw thread 6. This means that no counter-torque has to be applied to the conduit in order to prevent it from rotating when the nut 15 is tightened, meaning that the connection can be formed using one (and only one) tool Tl (that required to fasten the nut 15). The prior art method is shown in Fig. 5, part A, in which a second tool T2 is used to hold connector part 3’ steady while tightening nut 15’ onto connector part 2’ using tool Tl. If tool T2 is not used, then connector part 3’ would rotate, putting an unwanted bend into the hose. Fig. 5, part D, illustrates another embodiment of the method of single-handedly forming a connector 101 by screwing nut 115 onto connector portion 102 using single tool Tl to attach connector portion 103 to connector portion 102. Fig. 5, part B, illustrates the prior art method requiring two tools, Tl, T2, to form a connection. In this case, tool T2 is used to prevent rotation of hose 50” while nut 15” is rotated to attach connector part 3” to connector part 2”.

[0047] Whilst the present invention has been described and illustrated with reference to particular embodiments, it will be appreciated by those of ordinary skill in the art that the invention lends itself to many different variations not specifically illustrated herein. By way of example only, certain possible variations will now be described.

[0048] The example above demonstrates that screw threads may be used to attach the two portions of the connector together. Those skilled in the art will realise that other configurations may be used, such as bayonet fittings or clamps.

[0049] The example above shows the use of asymmetric mating configurations which can only be mated together in one way i.e. with the two configurations at one particular relative orientation. While desirable this “clocking” feature is not an essential feature of the present invention, and those skilled in the art will realise that it would be possible to provide configurations that mate together in more than one relative orientation. For example, if one configuration comprises a square section opening, the other configuration may comprise a square section projection.

[0050] The example above illustrates the use of a connector with aircraft components. Those skilled in the art will realise that the connector may be suitable for use in all situations in which a torsional or rotational force may be applied to one of the components of the connector.

[0051] The example above shows the use of a swivel joint or rotatable connector that inhibits transmission of torque to the connector. While desirable the swivel joint is by no means essential to the present invention.

[0052] The example above illustrates the use of the connector with an actuator. Those skilled in the art will realise that other uses are possible.

[0053] The example above shows that the connector may be used to facilitate the transmission of hydraulic fluid. Those skilled in the art will realise that the connector may be used to facilitate the transmission of other fluids.

[0054] Where in the foregoing description, integers or elements are mentioned which have known, obvious or foreseeable equivalents, then such equivalents are herein incorporated as if individually set forth. Reference should be made to the claims for determining the true scope of the present invention, which should be construed so as to encompass any such equivalents. It will also be appreciated by the reader that integers or features of the invention that are described as preferable, advantageous, convenient or the like are optional and do not limit the scope of the independent claims. Moreover, it is to be understood that such optional integers or features, whilst of possible benefit in some embodiments of the invention, may not be desirable, and may therefore be absent, in other embodiments.

Claims

1. A connector for connecting a conduit to a source of fluid and establishing a fluid flow path between a conduit and a source of fluid, the connector comprising:

a first connector portion for attachment to a source of fluid;

a second connector portion for attachment to a conduit;

2. A connector according to claim 1 in which the first mating configuration comprises a female or male configuration and the second mating configuration comprises the other of a male or female configuration.

3. A connector according to claim 2 in which the male configuration is located about a channel for the passage therethrough of fluid.

4. A connector according to any preceding claim in which the first and second mating configurations are configured so that the first and second mating configurations can only be mated together at one relative orientation of the first and second mating configurations.

5. A connector according to any of claims 1 to 3 in which the first and second mating configurations are configured so that the first and second mating configurations may be mated together at more than one relative orientation of the first and second mating configurations.

6. A connector according to any preceding claim in which the means of securing the first and second connector portions together comprises a first attachment configuration and a second attachment configuration, the first and second attachment configurations being complementary to one another to facilitate securing of the first and second connector portions.

7. A connector according to claim 6 in which the first attachment configuration is associated with the first connector portion and the second attachment configuration is associated with the second connector portion.

8. A connector according to any claim 6 or claim 7 in which the first and second attachment configurations each comprise a thread, the first and second attachment configurations together forming complementary threads.

9. A connector according to any preceding claim in which the first connector portion is provided with a first screw thread, and the connector comprises a second attachment component provided with a second screw thread which cooperates with the first screw thread.

10. A connector according to claim 9 in which the second attachment component is attached to the second connector portion so that it cannot be detached from the second connector portion.

11. A connector according to any preceding claim comprising an interface for sealing engagement with a conduit.

12. A connector according to any preceding claim comprising a rotational coupling for the attachment of a conduit.

13. A first connector portion and/or a second connector portion for use in the connector of any preceding claim.

14. A fluid transfer arrangement comprising a second connector portion of claim 13 and a conduit for the passage of fluid therethrough attached to the second connector portion.

15. A fluid transfer arrangement according to claim 14 comprising a rotational coupling.

16. A fluid transfer arrangement according to claim 14 or claim 15 comprising a connector in accordance with any of claims 1 to 12.

17. An aircraft fluid transmission arrangement comprising a first aircraft component, a connector in accordance with any of claims 1 to 12, a conduit and a second aircraft component, the connector and the conduit providing a fluid flow path from the first aircraft component to the second aircraft component.

18. An aircraft fluid transmission arrangement according to claim 17 in which the first aircraft component comprises a pump and/or reservoir of fluid.

19. An aircraft fluid transmission arrangement according to claim 17 or claim 18 in which the second aircraft component comprises an actuator (or part thereof).

20. An aircraft fluid transmission arrangement according to claim 19 in which the actuator (or part thereof) is arranged to move one or more aircraft control surface.

21. An aircraft wing comprising an aircraft fluid transmission arrangement according to any of claims 17 to 20.

22. An aircraft wing according to claim 21 comprising an aircraft control surface, the second aircraft component of the aircraft fluid transmission arrangement being arranged to move said control surface.

23. An aircraft comprising an aircraft fluid transmission arrangement according to any of claims 17 to 20 and/or an aircraft wing according to claim 21 or claim 22.

24. A method of forming a connection using a fluid transfer arrangement according to claim 16, the method comprising forming a sealing engagement between the first and second connector portions without applying a force to the conduit or the second connector portion to inhibit rotation of the conduit.

25. A method of forming a connection using a fluid transfer arrangement according to claim 16, the method comprising using a single tool to form a sealing engagement between the first and second connector portions.

Intellectual

Property

Office

Application No:

GB1815119.1