Abstract: Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems are disclosed. A fitting in accordance with one embodiment can be positioned adjacent to an aperture in a fuel tank wall having an inner surface and an outer surface. The fitting can include a first member having a flange and a barrel. The barrel can further include a passageway. A first flange seal can be positioned at a face of the flange and can be sealably coupled to a surface, for example, the tank wall. A second flange seal can be disposed outwardly from the first flange seal against the surface. The fitting can further include a second member (e.g., a sensor) positioned within the passageway of the barrel. The fitting can further include first and second barrel seals positioned between the barrel and the second member.

Abstract: An exemplary embodiment provides a shrouded conduit joint assembly that includes a joint assembly and a boot shroud. The joint assembly includes a first ferrule having a first seal, and a second ferrule having a second seal. A clamp operatively engages the first ferrule and the second ferrule. The boot shroud surrounds the joint assembly and is spaced from the joint assembly to create a leak detection space between the joint assembly and the boot shroud.

Abstract: Provided are shrouded adapter assemblies for coupling together a first conduit and a second conduit. The conduits may both be single-walled or one may be shrouded. Thus, the first conduit may include an inner conduit and an outer conduit with a conduit annular space between the inner conduit and the outer conduit. The adapter assembly may include a first adapter body having a first end and a second end. The first end is configured to receive an end of the inner conduit of the first conduit, and to receive an end of the outer conduit of the first conduit. The adapter assembly also includes a second adapter body having a first end and a second end, where the first end of the second adapter body is configured to receive an end of the second conduit. The adapter assembly further includes a clamp operatively engaging and clamping the second end of the first adapter body to the second end of the second adapter body.

Abstract: A shrouded valve apparatus including an outer conduit, an inner conduit disposed within the outer conduit, and a valve member operable to regulate flow through the inner conduit. This apparatus is useful in shrouded aircraft fuel systems.

Abstract: A method for operating an aircraft refueling system, where the aircraft refueling system has a computer system, a plurality of fuel tanks containing a fuel, a plurality of fuel pumps, a plurality of motor operated valves, and at least one refueling connection. The method may involve using the computer system to signal at least one of the motor operated valves to open; initiating a flow of the fuel to the at least one of the refueling connections using at least one of the pumps; sensing a flow condition of the fuel; signaling the flow condition to the computer system; and varying an operating quantity of the pumps in response to the flow condition.

Abstract: An aircraft aerial refueling system includes a fuel tank positioned in at least an aircraft wing to store fuel. At least two fuel pumps operate to transfer the fuel from the tank to a remotely located refueling connection. At least one electrically controlled valve provides each of an open position permitting fuel flow and a closed position isolating fuel flow between the tank and the refueling connection. A computer system automatically varies operation of any quantity of the fuel pumps and controls the electrically controlled valve between the open and closed positions during fuel transfer to the refueling connection. double wall fuel pipe manifolds in manned spaces of the aircraft.

Abstract: Apparatus and methods are provided to minimize the escape of fuel out of a fuel tank when a tank wall is penetrated by a bullet. In one embodiment, a pressure differential may be maintained between a pressure within a fuel tank cavity and another pressure outside the fuel tank cavity in order to minimize the loss of fuel upon penetration of the fuel tank. In another embodiment, a compressed rubber layer of fuel-reactive rubber may be provided which is adapted to be attached to a fuel tank wall and to swell upon contact with fuel in order to substantially seal a penetrated hole in the fuel tank wall.

Abstract: A shrouded body flow meter assembly includes an inner fluid-conducting conduit disposed in a spaced relation from and within an outer conduit. The shrouded flow meter assembly can be connected to other shrouded fluid-conducting apparatus and/or used to replace sections of a shrouded fluid-conducting apparatus system. The shrouded flow meter assembly maintains the integrity of the inner fluid-conducting conduits and outer conduits of the shrouded fluid-conducting apparatus.

Abstract: Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits, are disclosed. An aircraft configured in accordance with one embodiment of the invention includes a fuselage portion, a wing portion, and a fuel tank carried by least one of the fuselage portion and the wing portion. The aircraft also includes a spar carried by at least one of the fuselage portion and the wing portion. The spar includes a first spar rib and a second spar rib spaced apart from the first spar rib. The aircraft further includes a fluid conduit proximate to the spar and operably coupled to the fuel tank. A support member carrying the fluid conduit is operably coupled to the spar. The support member can be positioned to transfer at least approximately all of the axial loads from the fluid conduit to at least one of the first spar rib and the second spar rib.

Abstract: Systems and methods for reducing surge loads in hose assemblies, including aircraft refueling hose assemblies, are disclosed herein. A system in accordance with one embodiment includes a fuel delivery device having a flexible fuel line configured to be deployed overboard an aircraft during aerial refueling and a drogue coupled to the fuel line. The system can further include a surge damping portion positioned along the fuel line away from the aircraft to suppress surge loads traveling along the fuel line. In several embodiments, the surge damping portion can include a compressible material disposed annularly about at least a portion of the fuel line.

Abstract: Valves for annular conduits and associated systems and methods are disclosed. A fluid transmission system in accordance with one embodiment of the invention includes a first conduit having a first wall aligned with a flow direction in the first conduit and a second conduit disposed annularly around the first conduit with a second wall aligned with the flow direction. An access channel can be positioned to have an aperture in fluid communication with the first conduit and can be isolated from fluid communication with the second conduit. A valve element can be positioned in fluid communication with the access channel and can be movable between a first position and a second position, with the valve element being positioned to allow a first amount of flow through the access channel when in the first position and being positioned to allow no flow or a second amount of flow less than the first amount of flow through the access channel when in the second position.

Abstract: A shrouded valve apparatus including an outer conduit, an inner conduit disposed within the outer conduit, and a valve member operable to regulate flow through the inner conduit. This apparatus is useful in shrouded aircraft fuel systems.

Abstract: Valves for annular conduits and associated systems and methods are disclosed. A fluid transmission system in accordance with one embodiment of the invention includes a first conduit having a first wall aligned with a flow direction in the first conduit and a second conduit disposed annularly around the first conduit with a second wall aligned with the flow direction. An access channel can be positioned to have an aperture in fluid communication with the first conduit and can be isolated from fluid communication with the second conduit. A valve element can be positioned in fluid communication with the access channel and can be movable between a first position and a second position, with the valve element being positioned to allow a first amount of flow through the access channel when in the first position and being positioned to allow no flow or a second amount of flow less than the first amount of flow through the access channel when in the second position.

Abstract: Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, are disclosed herein. An aircraft system in accordance with one embodiment of the invention includes a fluid conduit carried by an aircraft and a housing fixedly attached to the fluid conduit. The housing can include a first attachment feature having one of a projection extending outwardly from the housing or an aperture extending at least partially through the housing. The system further includes a support member having an attachment portion positioned proximate to the attachment feature. The attachment portion includes a support member aperture positioned over at least a portion of the first attachment feature. An adjustable fitting couples the support member to the housing. The adjustable fitting can include a first side, a second side opposite the first side, and an engagement portion at the second side positioned within at least a portion of the support member aperture.

Abstract: A shrouded body flow meter assembly includes an inner fluid-conducting conduit disposed in a spaced relation from and within an outer conduit. The shrouded flow meter assembly can be connected to other shrouded fluid-conducting apparatus and/or used to replace sections of a shrouded fluid-conducting apparatus system. The shrouded flow meter assembly maintains the integrity of the inner fluid-conducting conduits and outer conduits of the shrouded fluid-conducting apparatus.

Abstract: Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems are disclosed. A fitting in accordance with one embodiment can be positioned adjacent to an aperture in a fuel tank wall having an inner surface and an outer surface. The fitting can include a first member having a flange and a barrel. The barrel can further include a passageway. A first flange seal can be positioned at a face of the flange and can be sealably coupled to a surface, for example, the tank wall. A second flange seal can be disposed outwardly from the first flange seal against the surface. The fitting can further include a second member (e.g., a sensor) positioned within the passageway of the barrel. The fitting can further include first and second barrel seals positioned between the barrel and the second member.

Abstract: Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits, are disclosed. An aircraft configured in accordance with one embodiment of the invention includes a fuselage portion, a wing portion, and a fuel tank carried by least one of the fuselage portion and the wing portion. The aircraft also includes a spar carried by at least one of the fuselage portion and the wing portion. The spar includes a first spar rib and a second spar rib spaced apart from the first spar rib. The aircraft further includes a fluid conduit proximate to the spar and operably coupled to the fuel tank. A support member carrying the fluid conduit is operably coupled to the spar. The support member can be positioned to transfer at least approximately all of the axial loads from the fluid conduit to at least one of the first spar rib and the second spar rib.

Abstract: An aircraft aerial refueling system includes a fuel tank positioned in at least an aircraft wing to store fuel. At least two fuel pumps operate to transfer the fuel from the tank to a remotely located refueling connection. At least one electrically controlled valve provides each of an open position permitting fuel flow and a closed position isolating fuel flow between the tank and the refueling connection. A computer system automatically varies operation of any quantity of the fuel pumps and controls the electrically controlled valve between the open and closed positions during fuel transfer to the refueling connection. The system also includes double wall fuel pipe manifolds in manned spaces of the aircraft.

Abstract: Methods and apparatus for illumination of aerial refueling hoses are disclosed. In one embodiment, a conduit for transferring a flowable material includes a wall member. A plurality of optical fibers arc at least one of formed within an outer layer of the wall member and disposed on an outer surface of the wall member. A light emitted by the optical fibers illuminates the conduit. In an alternate aspect, the optical fibers may be replaced with a luminescent outer portion. The luminescent outer portion may include an electromagnetic substance, a phosphor substance, an ultraviolet-energized material, or any other suitable material.

Abstract: Methods and apparatus for illumination of aerial refueling hoses are disclosed. In one embodiment, a conduit for transferring a flowable material includes a wall member. A plurality of reflective members are at least one of formed within an outer layer of the wall member and disposed on an outer surface of the wall member. The reflective members are adapted to at least partially reflect light incident thereon. In one aspect, the reflective members include reflective glass beads. In a further aspect, a first portion of the wall member has a first concentration of reflective members, and a second portion has a second concentration of reflective members.