Abstract: A fluid transport device including a first line connector, second line connector and inner line component that fluidly connects the first line connector to the second line connector via respective first and second coupling ends. In a mounted state, an outer line component of the device is attached to the first line connector and to the second line connector, so the outer line component covers the first and second coupling ends. In a demounted state, the outer line component is detached from the first and second line connector, wherein the outer line component is movable relative to the inner line component to uncover the first coupling end or the second coupling end. A method for assembling and disassembling a fluid transport device is also disclosed.

Abstract: A clamping apparatus connecting tube flanges, includes first and second bracing devices. The first bracing device connects first and second mounting devices and has a partially circular shape with a first inner and a first outer wall. The second bracing device connects first and second connecting devices. The first bracing device inner wall has a first recess. The first bracing device outer wall is configured to contact the second bracing device which is configured to contact the first bracing device outer wall to apply substantially radial force on that first outer wall. The first recess shape is configured to substantially convert the radial force applied to the first bracing device outer wall into an axial force inside the first inner wall. The first and second mounting devices each comprise at least two attachment devices connecting the first and second connecting devices of the second bracing device.

Abstract: A fluid pipe connection is disclosed having an inner pipe assembly including a first inner pipe section and a second inner pipe section, and an inner joint between the first inner pipe section and second inner pipe section; an outer pipe assembly having a first outer pipe section, a second outer pipe section, a shroud covering the inner joint and mechanically connecting the first outer pipe section to the second outer pipe section via a mechanical connection, and a hatch fastened to the shroud by one or more fasteners and covering a hole in the shroud, wherein the hatch is moveable between a closed position and an open position to provide access to the inner joint through the hole.

Abstract: A fuel cell system comprising a fuel cell, a fuel tank, a fuel distribution pipe fluidly connecting the fuel tank with a fuel inlet of the fuel cell, a shroud surrounding at least a portion of the fuel distribution pipe, an inerting system configured to generate nitrogen enriched air, NEA, and oxygen enriched air, OEA, and an NEA pipe conducting the nitrogen enriched air into the shroud.

Abstract: A gas distribution system for aircrafts includes a corrugated hose having a first connecting end and a second connecting end, and a shroud surrounding the corrugated hose concentrically along a longitudinal direction of the corrugated hose, thereby building an intermediate space between the corrugated hose and the shroud. The first connecting end is configured to be connected to a gas tank. The second connecting end is configured to be connected to a gas consumer. The corrugated hose is flexible so as to compensate for in-flight deflections of the gas distribution system. Also, an aircraft including a fuselage, a Hydrogen consumer, a Hydrogen tank, and the gas distribution system is provided. The gas distribution system fluidly connects the Hydrogen tank with the Hydrogen consumer.

Abstract: A fluid transport device including a first line connector, second line connector and inner line component that fluidly connects the first line connector to the second line connector via respective first and second coupling ends. In a mounted state, an outer line component of the device is attached to the first line connector and to the second line connector, so the outer line component covers the first and second coupling ends. In a demounted state, the outer line component is detached from the first and second line connector, wherein the outer line component is movable relative to the inner line component to uncover the first coupling end or the second coupling end. A method for assembling and disassembling a fluid transport device is also disclosed.

Abstract: A clamping apparatus connecting tube flanges, includes first and second bracing devices. The first bracing device connects first and second mounting devices and has a partially circular shape with a first inner and a first outer wall. The second bracing device connects first and second connecting devices. The first bracing device inner wall has a first recess. The first bracing device outer wall is configured to contact the second bracing device which is configured to contact the first bracing device outer wall to apply substantially radial force on that first outer wall. The first recess shape is configured to substantially convert the radial force applied to the first bracing device outer wall into an axial force inside the first inner wall. The first and second mounting devices each comprise at least two attachment devices connecting the first and second connecting devices of the second bracing device.

Abstract: A fluid pipe connection is disclosed having an inner pipe assembly including a first inner pipe section and a second inner pipe section, and an inner joint between the first inner pipe section and second inner pipe section; an outer pipe assembly having a first outer pipe section, a second outer pipe section, a shroud covering the inner joint and mechanically connecting the first outer pipe section to the second outer pipe section via a mechanical connection, and a hatch fastened to the shroud by one or more fasteners and covering a hole in the shroud, wherein the hatch is moveable between a closed position and an open position to provide access to the inner joint through the hole.

Abstract: The present invention provides an arrangement for passing a line in a load-free manner through a pressure frame of a fuselage of an aircraft or spacecraft, including an opening penetrating the pressure frame, through which opening the line is passed, the line being mechanically decoupled from the pressure frame; and a flexible sealing device arranged outside the opening at least in portions, which sealing device is simultaneously operatively connected to the line and the pressure frame for the pressure-tight separation of a first side from a second side of the pressure frame. The present invention also provides a fuselage for an aircraft or spacecraft having an arrangement of this type and an aircraft or spacecraft having an arrangement of this type or having a fuselage of this type.

Abstract: In an aircraft duct formed with pipes connected in pairs via connectors in which the pipes are mounted with the possibility of axial displacement, there exists a risk that a pipe of the duct, with a dimension greater that the dimension of the nominal pipe, is mounted instead and in place of the latter. In this case, the wrongly mounted pipe would risk not having sufficient clearance in axial translation. In order to solve this problem, it is disclosed to equip one of the relevant connectors with an obstacle limiting the travel of the nominal pipe and preventing the mounting of a pipe with a greater dimension belonging to the duct. A method for assembling an aircraft portion is also proposed, in order to benefit from the particularities of the duct.

Abstract: The present invention provides an arrangement for passing a line in a load-free manner through a pressure frame of a fuselage of an aircraft or spacecraft, including an opening penetrating the pressure frame, through which opening the line is passed, the line being mechanically decoupled from the pressure frame; and a flexible sealing device arranged outside the opening at least in portions, which sealing device is simultaneously operatively connected to the line and the pressure frame for the pressure-tight separation of a first side from a second side of the pressure frame. The present invention also provides a fuselage for an aircraft or spacecraft having an arrangement of this type and an aircraft or spacecraft having an arrangement of this type or having a fuselage of this type.

Abstract: A draining apparatus for draining liquids from a vehicle includes a containment; a drain mast having an outlet opening and an inlet; and an actuator. The containment is adapted for being coupled with a structure of the vehicle, wherein the actuator is coupled with the drain mast and adapted for moving the drain mast into a retracted position and at least one extracted position relative to the containment, and wherein the containment is further adapted for accommodating the drain mast in the retracted position at least partially. The drainage apparatus has clear advantages regarding the parasitic drag compared to known drainage masts as it is only deployed into the flow when it is absolutely necessary.

Abstract: In an aircraft duct formed with pipes connected in pairs via connectors in which the pipes are mounted with the possibility of axial displacement, there exists a risk that a pipe of the duct, with a dimension greater that the dimension of the nominal pipe, is mounted instead and in place of the latter. In this case, the wrongly mounted pipe would risk not having sufficient clearance in axial translation. In order to solve this problem, it is disclosed to equip one of the relevant connectors with an obstacle limiting the travel of the nominal pipe and preventing the mounting of a pipe with a greater dimension belonging to the duct. A method for assembling an aircraft portion is also proposed, in order to benefit from the particularities of the duct.

Abstract: A draining apparatus for draining liquids from a vehicle includes a containment; a drain mast having an outlet opening and an inlet; and an actuator. The containment is adapted for being coupled with a structure of the vehicle, wherein the actuator is coupled with the drain mast and adapted for moving the drain mast into a retracted position and at least one extracted position relative to the containment, and wherein the containment is further adapted for accommodating the drain mast in the retracted position at least partially. The drainage apparatus has clear advantages regarding the parasitic drag compared to known drainage masts as it is only deployed into the flow when it is absolutely necessary.

Abstract: The present invention provides an arrangement for passing a line in a load-free manner through a pressure frame of a fuselage of an aircraft or spacecraft, including an opening penetrating the pressure frame, through which opening the line is passed, the line being mechanically decoupled from the pressure frame; and a flexible sealing device arranged outside the opening at least in portions, which sealing device is simultaneously operatively connected to the line and the pressure frame for the pressure-tight separation of a first side from a second side of the pressure frame. The present invention also provides a fuselage for an aircraft or spacecraft having an arrangement of this type and an aircraft or spacecraft having an arrangement of this type or having a fuselage of this type.

Abstract: The present invention relates to spacers and pipelines. The spacers are mounted between two pipes—an internal line and an external line—and hold them at a defined distance. A closure is necessary for fixing the spacer on the pipes. Space, weight, and mounting time may advantageously be saved by integrating the closure into the spacer.

Abstract: The invention concerns a pipeline 1, in particular a pipeline 1 for fuel systems in aircraft, including an inner pipe 6 and an outer pipe 4 surrounding the inner pipe. In accordance with the invention, the inner pipe 6 is made of a metal material and/or, at least in portions, of a synthetic material and, at least in curved portions 5 of the pipeline 1, the outer pipe 4 is made of a synthetic material. Due to the fact that the outer pipe 4 is made of a synthetic material, a significant weight reduction can be accomplished in comparison to conventional coaxial pipelines, which are made entirely of a metal material and which, due to manufacturing reasons, require a larger number of flange joints 2 and 3 in longer curved pipeline portions. The invention also concerns a method for manufacturing such a pipeline 1, in particular a pipeline 1 for fuel systems in aircraft.

Abstract: The present invention relates to spacers and pipelines. The spacers are mounted between two pipes—an internal line and an external line—and hold them at a defined distance. A closure is necessary for fixing the spacer on the pipes. Space, weight, and mounting time may advantageously be saved by integrating the closure into the spacer.