Abstract: A fuselage structure for an aircraft, comprising a fuselage vessel and a pressure bulkhead arranged in an end region of the fuselage vessel and having a central region extending in a planar manner and a connection region adjoining the central region in a radial direction and surrounding the central region and being secured to the fuselage vessel. The pressure bulkhead divides the fuselage vessel with respect to the longitudinal direction into a first region for subjecting to an internal pressure and a second region for subjecting to an external pressure which is lower than the internal pressure. The central region of the pressure bulkhead has an arching in the direction of the first region of the fuselage vessel.

Abstract: A method for adapting a 3D printing model includes calculating a layer representation model on the basis of a 3D object model of an object; determining a plurality of overhang regions in the layer representation model where the boundary edges of first layers extend over the boundary edges of second layers, the first layers being directly adjacent and subsequent to the second layers when going into the build-up direction of the layer representation model; determining a local overhang angle in each of the plurality of overhang regions; adapting the layer representation model by re-defining the boundary edges of layers in the overhang regions so that the local overhang angle remains below a predetermined overhang threshold angle; and outputting the adapted layer representation model as 3D printing model to the 3D printing apparatus.

Abstract: A vortex generator arrangement for an aircraft including a surface section, a flap element pivotable between a first position and a second position, a biasing arrangement biasing the flap element towards the second position, retaining devices retaining the flap element in the first or second position, and a release device releasing the flap element from the first retaining device. The biasing arrangement, the first retaining device and the second retaining device are configured such that the second retaining device automatically retains the flap element in the second position after the flap element has been pivoted by the biasing arrangement from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device automatically releases the flap element, which pivots against the force of the biasing arrangement into the first position and is automatically retained therein by the first retaining device.

Abstract: A method of manufacturing a shell component for an aircraft or spacecraft includes positioning a skin panel, which includes a skin of the aircraft or spacecraft and first and second stringers stiffening the skin, opposite a frame having first and second mouseholes for receiving the first and second stringers, elastically bending the skin panel, inserting the first stringer into the first mousehole, and releasing the elastic bend to insert the second stringer into the second mousehole.

Abstract: A fairing for an aircraft is disclosed in which the fairing comprises a first fairing portion configured to be fixedly attached to a first structural component and having a first edge; a second fairing portion configured to be fixedly attached to a second structural component and having a second edge, wherein the first edge and the second edge define an interface configured to enable relative movement between the first fairing portion and the second fairing portion.

Abstract: A pressure bulkhead system comprises a pressure bulkhead adapted to be connected to a fuselage of a vehicle to separate a pressurized cabin space of the vehicle from an unpressurized cabin space of the vehicle, and a peripheral pressure frame to sealingly connect the pressure bulkhead to the vehicle fuselage. The peripheral pressure frame comprises an attachment section sealingly attached to an outer rim portion of a first surface of the pressure bulkhead. The first surface, when the pressure bulkhead system is installed in the vehicle, faces the unpressurized cabin space of the vehicle. A flange section is adapted to be sealingly attached to an inner surface of the vehicle fuselage and extends in a direction facing away from the first surface of the pressure bulkhead. A flexible section interconnects the attachment section and the flange section and is flexible to accommodate cabin pressure acting on the pressure bulkhead.

Abstract: A manufacturing method for passenger door corner components of aircraft or spacecraft includes using additive layer manufacturing, ALM, to form an integral passenger door corner component. The integral passenger door corner component includes a substantially cruciform shape having a frame coupling member with two frame couplings as end pieces. The frame coupling member intersect with a beam coupling member with two beam couplings as end pieces.

Abstract: This relates to a multi-part attachment device for attaching a device to a stiffening element and to an outer skin of a vehicle. The multi-part attachment device comprises a base body having an angular profile for attaching the attachment device to the stiffening element and to the outer skin of the vehicle. Furthermore, the multi-part attachment device comprises an upper part with a lug, wherein the upper part is attached to the base body. This also relates to a method for attaching a device to a stiffening element and to an outer skin of a vehicle as well as to an aircraft with a multi-part attachment device.

Abstract: A vortex generator arrangement for an aircraft, a flow control system and an aircraft comprising such vortex generator arrangement. The arrangement includes a surface portion facing a first region of space to constitute a flow surface, a vortex generating element, an element support structure connected to the element, a mounting structure. The element support structure and the element together are rotatable between first and second positions and a biasing device, retainer and release are provided. The rotational axis extends transversely with respect to the surface portion. The projection of the element onto a projection plane is smaller in the first rotational position than in the second rotational position, the projection plane extending perpendicularly to a tangent plane of the surface portion at a reference point of the surface portion and to a predetermined direction parallel to the extension of the tangent plane.

Abstract: A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed.

Abstract: An aircraft fuselage structure having a first fuselage barrel section and a second fuselage section barrel which are joined by tension fasteners extending through frame holes. A shank diameter of the fasteners is smaller than a respective frame hole diameter. A first positive locking element and a second positive locking element is provided forming a form-fit area with the first positive locking element in the circumferential direction. A method for producing such an aircraft fuselage section is also provided.

Abstract: A fuselage structure includes a pressure bulkhead and a frame being arranged behind the pressure bulkhead. The fuselage structure includes a first beam element with a first cantilever and a second cantilever, while the first beam element extends in a vertical direction of the fuselage structure. The first cantilever and the second cantilever protrude from the first beam element in a first direction toward the frame. The first direction of both cantilevers is inclined at a first angle with respect to a longitudinal direction of the fuselage structure. An aircraft with a fuselage structure and a method for manufacturing a fuselage structure are also described.

Abstract: An aircraft frame includes a first partial aircraft frame configured to be attached to a first aircraft fuselage segment, and a second partial aircraft frame configured to be attached to a second aircraft fuselage segment. The first and second partial aircraft frames include corresponding first and second stringer coupling sections. The first partial aircraft frame and the second partial aircraft frame are configured to be attached to each other via a first web and a second web. The first stringer coupling section is located between the first inner flange and the first outer flange and the second stringer coupling section is located between the second inner flange and the second outer flange. The first stringer coupling section includes a first wall which extends from the first web into the first section of the first partial aircraft frame, and the second stringer coupling section comprises a second wall, which extends from the second web into the second section of the second partial aircraft frame.

Abstract: This relates to a fuselage section comprising an inner surface with a non-circular contour and a pressure bulkhead comprising a non-circular outer edge. The non-circular outer edge of the pressure bulkhead is aligned with the non-circular contour of the inner surface of the fuselage section when the pressure bulkhead is attached to the fuselage section. This further relates to an aircraft with a fuselage section and a method for manufacturing a fuselage section.

Abstract: A vertical stabilizer for an aircraft, including a fin, pivotable rudder, rudder adjustment arrangement, and vortex generator arrangement having on each side of the fin a turbulence generation element, each turbulence generation element disposed in a surface section of the fin and mounted moveably between a first, retracted position, where it is retracted into an interior space of the fin, and a second, extended position, where it projects at least partially outwardly from the fin transversely with respect to the surface section, and a turbulence generation element adjustment arrangement which is coupled to the rudder. The turbulence generation element adjustment arrangement engages the turbulence generation elements to move them. In a range of angular positions of the rudder, the turbulence generation element adjustment arrangement is inoperative for causing a movement of the turbulence generation elements out of the first position.

Abstract: A vortex generator arrangement for an aircraft including a surface section, a flap element pivotable between a first position and a second position, a biasing arrangement biasing the flap element towards the second position, retaining devices retaining the flap element in the first or second position, and a release device releasing the flap element from the first retaining device. The biasing arrangement, the first retaining device and the second retaining device are configured such that the second retaining device automatically retains the flap element in the second position after the flap element has been pivoted by the biasing arrangement from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device automatically releases the flap element, which pivots against the force of the biasing arrangement into the first position and is automatically retained therein by the first retaining device.

Abstract: A floor arrangement for a passenger cabin of an aircraft or spacecraft includes mounting rails for mounting cabin outfitting components, wherein each mounting rail has at least one upper support flange for supporting floor panels. The floor arrangement further includes curved floor panels being inherently formed with a convex top surface and a concave bottom surface, wherein each curved floor panel is mounted to two respective adjacent mounting rails and is supported by one respective upper support flange of each of the two adjacent mounting rails.

Abstract: A method for joining two fuselage sections involves fastening a crossbeam to an elliptical interface frame to form an intermediate coupling assembly; temporarily fastening the intermediate coupling assembly to a planar mounting frame at a number of fixation holes formed in the planar mounting frame; temporarily fastening a buttstrap circumferentially around the interface frame; permanently attaching the intermediate coupling assembly and the buttstrap to a first fuselage section; disengaging the intermediate coupling assembly from the mounting frame; and permanently attaching a second fuselage section to the first fuselage section at the buttstrap.

Abstract: A method for adapting a 3D printing model includes calculating a layer representation model on the basis of a 3D object model of an object; determining a plurality of overhang regions in the layer representation model where the boundary edges of first layers extend over the boundary edges of second layers, the first layers being directly adjacent and subsequent to the second layers when going into the build-up direction of the layer representation model; determining a local overhang angle in each of the plurality of overhang regions; adapting the layer representation model by re-defining the boundary edges of layers in the overhang regions so that the local overhang angle remains below a predetermined overhang threshold angle; and outputting the adapted layer representation model as 3D printing model to the 3D printing apparatus.

Abstract: This relates to a multi-part attachment device for attaching a device to a stiffening element and to an outer skin of a vehicle. The multi-part attachment device comprises a base body having an angular profile for attaching the attachment device to the stiffening element and to the outer skin of the vehicle. Furthermore, the multi-part attachment device comprises an upper part with a lug, wherein the upper part is attached to the base body. This also relates to a method for attaching a device to a stiffening element and to an outer skin of a vehicle as well as to an aircraft with a multi-part attachment device.