Abstract: In a holder arrangement of an aircraft or spacecraft comprising a structural member, a holder comprising at least one lower part and at least one upper part is provided, and these are formed so as to be able to be clamped together to be attached with a non-positive fit to a fastening portion of the structural member. The fastening portion can be clamped between the lower part and the upper part. The holder arrangement is characterised by at least one fixing strip which can be connected to the fastening portion of the structural member in the longitudinal direction thereof and which comprises a fixing profile for fixing the holder to the structural member in the longitudinal direction of the structural member with a positive fit. An aircraft or spacecraft has at least one holder arrangement of this type.

Abstract: A floor section for a vehicle cabin includes juxtaposed profiled elements of identical cross section. Each profiled element includes a mainly planar elongated cross member and a generally flat elongated panel. The cross member includes a lower stiffener, is positioned in a transverse vertical plane, and is attachable at two extremities to a vehicle frame. The elongated panel is positioned in a horizontal plane and includes an overlap region along one longitudinal edge and a bearing region along another longitudinal edge. The overlap region and the bearing region are of similar width and of total thickness less than or equal to a mean panel thickness. The panel is perpendicular to the cross member, and a bearing region underside is coplanar with a lower face of the elongated panel and is secured to the cross member at two or more points substantially in line with a middle of the bearing region.

Abstract: A panel assembly, in which the liaison between two adjacent panels is sealed by a sealing joint, where the sealing joint comprises a central part, housed in an interstice between the two panels, and an external part, facing the exterior of the panel assembly, and capable of covering at least partially the external face of the two longitudinal edges of the panels surrounding the interstice. Also, a method for mounting a panel assembly, in which two adjacent panels are fixed to one another.

Abstract: A retention device, in the form of a trunking with a substantially U-shaped section, for retaining at least one cable running along the structure of an aircraft, fastened to said structure by a fastening device and providing an electrical continuity over the whole of its length is disclosed. The device is electrically connected to a current-return circuit from the items of equipment of the aircraft. The trunking includes at least one curve on its longitudinal axis corresponding substantially to that of a frame of a fuselage. It is intended to be mounted on a frame of an aircraft made of carbon fibers and to protect the skin of the aircraft against a possible contact with a damaged cable.

Abstract: A device for holding an insulating blanket and for fastening systems in an aircraft includes a base and at least one support. The base has two ends from each of which there extends an arm. One arm is a jointed arm that is jointed onto the base to be pivotable relative to the base. The at least one support is configured to accommodate a system. The base includes an elongated shape and defines a plane, the base includes two longitudinal edges, and at one end of the base, each longitudinal edge has a flange extending from the base on a same side of the base from which the arms extend.

Abstract: A connecting device having two curved ribs of an aircraft or spacecraft, with: a coupling element which can be connected by means of predetermined coupling sections to respective connecting sections of the two ribs; wherein at least the predetermined coupling sections of the coupling element are rectilinearly designed; and wherein at least the respective connecting sections of the two ribs each have rectilinearly running inner belt regions for a respective rectilinear connection of the predetermined coupling sections of the coupling element.

Abstract: An aircraft wing comprising first and second fuel pipe segments which are coupled together with a pipe coupling device comprising a corrugated tube formed from an elastomer filled with conductive material. The pipe coupling device is particularly useful for connecting together fuel pipe segments in an aircraft wing as it removes the need to attach bonding leads between fuel pipe segments to dissipate lightning currents and static.

Abstract: A method and apparatus for an aircraft structure. In one embodiment, the aircraft structure may have first and second stringers, each having a vertical stringer portion defining a lengthwise gap. The embodiment may include a cruciform fitting having a central rib attachment member and first and second extensions extending in opposite directions from said central rib attachment member. Stringer attachment portions extending up from said first and second extensions are inserted into the lengthwise gaps of the first and second stringer portions, respectively. The rib attachment member may be attached to a side-of-body rib.

Abstract: A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto.

Abstract: A device for holding an insulating blanket and for fastening systems for an aircraft including aircraft frames, a skin, and connecting pieces between the skin and the frames, the connecting pieces including clips, includes two brackets and a member that contours at least a portion of one of the aircraft frames. Each bracket has a first branch configured to be fastened to one of the clips and a second branch provided with a slot. The member that contours at least a portion of one of the aircraft frames includes a base and two arms. Each arm has a free end forming a securing lug configured to be inserted into the slot of one of the brackets with a flange which forms a stop countering displacement of the securing lug once the latter is inserted into the slot. Each arm further includes at least one support configured to accommodate a system.

Abstract: The integrally stiffened panel includes one or more stiffeners oriented in one direction, and one or more stiffeners oriented in a different direction. The stiffeners are integral with a sheet member and intersect at a joint. The joint is configured to incorporate a pocket at the stiffener intersections. The pocket geometry is inverse to the stiffener geometry, and thereby provides moment and stiffness continuity across the joint and between adjacent intersecting stiffeners.

Abstract: According to one embodiment, a windshield attachment device for coupling a windshield to a body includes a fastener portion, a bolt, and an elastomeric load isolator. The fastener portion has an opening therethrough. The bolt is configured to extend through the opening of the fastener portion and couple the fastener portion to the body. The elastomeric load isolator surrounds at least a portion of the fastener portion and separating the fastener portion from the windshield.

Abstract: Apparatus and methods provide for a structural joint utilizing overlapping blade stringers coupled to opposing sides of a continuous skin. According to embodiments described herein, a structural joint includes a number of inside blade stringers associated with a first component are coupled to an inside surface of a continuous skin. A number of outside blade stringers associated with a second component may be coupled to an outside surface of the continuous skin. The inside blade stringers and outside blade stringers may overlap on opposing surfaces of the continuous skin.

Abstract: A joint construction for an aeronautical structure made from composite material having an internal structural element and an adjoining skin element which define the aeronautical structure, which includes a coupling element disposed between and contiguous with the internal structural element and the adjoining skin element, wherein the coupling element has opposing adjoining diagonally configured end portions which form a wedge shaped diagonal joint therebetween which terminates at the internal structural element at one end and the skin element at the other end, and a plurality of rivets extending from the internal structured element to the adjoining skin, across the coupling element and across the diagonal joint.

Abstract: A connection device for a plurality of cabin components of an aircraft includes a rail extending in a longitudinal direction of an aircraft structure, wherein the plurality of cabin components is disposed on the rail; and a plurality of adjustment devices configured to self-adjust each of the plurality of cabin components in the longitudinal direction.

Abstract: A support assembly (1) for guiding a flap (42) on an aircraft wing (41) during deployment of the flap is disclosed. The assembly comprises a guide track (2) defining a two-dimensional path, a cylindrical bearing follower (12) having a longitudinal axis constrained so as to follow said path during flap deployment, a shaft (23) extending from the bearing follower and, a spherical bearing coupling an end of the shaft to the bearing follower such that the bearing follower is rotatable relative to the shaft about the longitudinal axis of the bearing follower as it travels along the track. The spherical bearing also enabling rotation of the shaft about its longitudinal axis relative to the bearing follower and rotation of the shaft about a center point of the spherical bearing such that the flap is fret to move in multiple directions.

Abstract: Aircraft fuselage structures have fuselage bulkheads in which the bulkhead outer caps are integrated with the skin, thereby reducing fastener count and weight. These outer caps and skin are preferably co-cured to form a strong structure. The outer caps can be advantageously constructed as continuous hoops of pultruded elements. The outer cap need not be interrupted by contours or cutouts for stringers, saving weight and reducing complexity. It is contemplated that by integrating the bulkhead outer caps into the skin, a bulkhead can still maintain equivalent stiffness and strength, while saving a significant number of rivets as compared to a comparable design without the outer cap.

Abstract: Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces. Set of fuselage sections assembled by means of a device of the type described above. Method of assembling two fuselage sections by means of a device of the type described above.

Abstract: A sealing (1) for a fairing (2) against transverse airflow between a wing (3) and a fuselage (4) of an aircraft. Inner and outer sides (7, 8) of the sealing (1) are provided with lips biased against the fairing (2) and the wing (3). At least two gaskets (5, 6) are positioned between respective ends of the sides (7, 8), thus sealing the fairing (2) and the wing (3) against longitudinal airflow.

Abstract: An air-sucking vehicle fuselage component includes an outer delimitation part, and inner delimitation part, and connecting elements. The inner delimitation part is connected via the connecting elements to the outer delimitation part. The outer delimitation part includes a continuously curved shape. The inner delimitation part includes two or more flat delimitation part components, which are each connected to one another at one edge to form a connection edge, and the connection edge is configured to be attached to the outer delimitation part. A type of framework structure is thus provided, which causes increased stability and can split impacting objects in particular if two inner delimitation part components are used on the vehicle fuselage component.

Abstract: A mounting assembly for mounting a sound-deadening body to a fuselage of an aircraft and a method for attaching a sound-deadening body to a fuselage of an aircraft using the mounting assembly is disclosed herein. In a non-limiting embodiment, the mounting assembly includes, but is not limited to, a retaining member that is configured to engage the sound-deadening body. The mounting assembly further includes an isolating member that is engaged with the retaining member. The isolating member is configured for connection to the fuselage and is further configured to diminish transmission of vibration from the fuselage to and through the retaining member, and therefore to reduce the transmission of sound into the cabin.

Abstract: The present invention provides a structural component for an aircraft or a space craft having an outer skin and a first reinforcing element which runs on the outer skin along a first spatial direction. A second reinforcing element runs over the first reinforcing element in a second spatial direction. A foot element supports the second reinforcing element on the outer skin, the foot element having a feed-through opening in which the first reinforcing element is held in a positive manner. From another point of view, a method is provided for reinforcing an outer skin of an aircraft or space craft, in which a first reinforcing element is attached to the outer skin along a first spatial direction. A foot element having a feed-through opening is attached over the first reinforcing element such that the first reinforcing element is held positively in the feed-through opening. A second reinforcing element is attached to the foot element in a second spatial direction over the first reinforcing element.

Abstract: A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.

Abstract: A covering device includes a sealing element and a rib structure which is disposed on a surface of the sealing element. The rib structure includes a plurality of ribs which extend parallel to the surface of the sealing element, wherein the bendability of the ribs parallel to the surface of the sealing element is high, and perpendicular to the surface of the sealing element is low.

Abstract: A method and apparatus for attaching parts. A composite male fastening component is placed through at least a first part and a second part. The composite male fastener component preferably has a threaded portion. A composite female fastener component is positioned adjacent to and surrounding the threaded portion of the male fastener component. A portion of the composite female fastener component is caused to flow around and form into the threaded portion of the composite male fastener component. The portion of the composite female fastener component that flowed around and formed into the threaded portion of the composite male fastener component is re-solidified and re-consolidated such that the composite female fastener component is securely attached to the composite male fastener component thereby joining the mating parts.

Abstract: A shroud panel (60) is attached to a wing skin overhang (28) by a series of pivoting butt straps (86) to permit relative strains to occur.

Abstract: The invention relates to a fastening device for installing a hatrack on a substructure of a means of locomotion, wherein the fastening device comprises a pre-locking device and a main locking device. In this arrangement the pre-locking device is designed for automatic provisional affixation of the hatrack to the fastening device when the hatrack during an installation movement of the hatrack is moved in the direction to the fastening device. The main locking device is designed for final affixation of the hatrack to the fastening device.

Abstract: A device for connecting movable parts with structural components of airplanes or other high-speed vehicles, including at least one fitting provided with at least one bearing. In order to provide such a device exhibiting low thermal stresses, a low weight, a high bearing capacity and a producibility as simple as possible, it is provided that the at least one fitting is made of a synthetic material and glued with the movable part. The resin transfer molding (RTM)-method is particularly suitable to produce the fitting.

Abstract: A plug mounting (50) is provided as a combination of a plug (10) and a mount (30), for the detachable mounting of an equipment part, such as an inner panel, to a supporting frame, such as an aircraft fuselage. The plug (10) has a mounting pin (12), which has an annular groove (25) on one end, which can be engaged with a slide (34) of the mount (30), which is under spring pretension. The mounting pin (12) can be connected to the foundation by a damping element. The mount (30) is fastened to the housing (32) on the equipment part. The mount (30) has an eccentric lever (42) for unlocking the plug (10) by displacing the slide (34) against the spring pretension. The arrangement is made so that only the mounting pin (12) of the plug (10) needs to be inserted into the opening of the housing of the mount (30).

Abstract: A transverse butt connection between two fuselage sections, more particularly for creating a fuselage cell for an aircraft, can have a number of stringers arranged spaced out uniformly parallel to one another inside on an outer skin. In order to enable a universal tolerance compensation with standardised compensating means within a predetermined tolerance band between two fuselage sections which are to be joined together, both end areas of the fuselage sections can have on the inside oppositely inclined skin wedge surfaces and the connection of the two end areas is carried out by a circumferential transverse butt strap which is provided with two oppositely inclined transverse butt strap wedge surfaces in the underneath area wherein a wedge can be pushed in between each one transverse butt strap wedge surface and a skin wedge surface for tolerance compensation between the fuselage sections.

Abstract: An aircraft huffer coupling adapter comprises a flange assembly having one or more attachment members in communication with a flange ring via one or more strut members. The flange assembly is attached with a port end of an inner coupling of a huffer coupling via the one or more attachment members. The flange ring defines an inner diameter larger than an outer diameter of the huffer coupling, with at least one space between an inner wall of the flange ring and the outer diameter of the air hose coupling arranged to allow airflow therethrough.

Abstract: The invention relates to an aircraft comprising a force transmission element which detachably connects a cabin structural segment to an aircraft primary structure and which comprises a cabin bearing element and a structure bearing element, the cabin bearing element being connected to the cabin structural segment and the structure bearing element being connected to the aircraft primary structure. The force transmission element is designed in such a manner that a force transmission can take place between the cabin structural segment and the aircraft primary structure with at least one degree of freedom of movement.

Abstract: Aircraft component with panels (11) stiffened with stringers (15) configured with a central section (17) and some feet (19) in which there are zones of potential intersections or interferences of said stringers (15) with spars (25) and ribs (27), in which the configuration of the ends of the stringers (15) affected by said intersections or interferences includes a first section (41) in which the height of the central section (17) of the stringer (15) is reduced until it disappears and the width of the feet (19) is increased until it reaches a predetermined width A and a second section (43) with some extended feet (23) of said predetermined width A and no central section (17), including in said first section (41) the mechanical means (31) for binding the end of the stringer (15) to the skin (13). The invention also relates to a method for manufacturing said panels (11).

Abstract: An attachment arrangement for attaching a component to the fuselage of an aircraft. The attachment arrangement comprises an elongated stringer that can be connected to the aircraft fuselage, and a fitting that can be connected to the component. The stringer comprises a multitude of recesses that are formed one behind the other in the direction of longitudinal extension of the stringer. The fitting comprises at least one engagement element that is adapted for positive-locking engagement in the recesses of the stringer. The stringer and/or the fitting can comprise CFC. The fittings can also comprise various other plastics or metal. Weight savings are achieved while at the same time providing stable and variably-positionable attachment. Furthermore, a method for constructing a stringer for an attachment arrangement is proposed, in which method, by providing reinforcement fibers adjacent to the recesses, a carbon scrim is locally reinforced around the recesses.

Abstract: The present invention provides a method for producing a component for joining structures at intersection regions thereof, comprising the following steps: forming a first fibre having a meandering shape which includes a plurality of first loops; forming a second fibre having a meandering shape which includes a plurality of second loops; and swivelling a first loop portion of a respective first loop and a first loop portion of a respective second loop such that a respective first loop and a respective second loop engage with one another.

Abstract: An aircraft comprising includes a fuselage shell with fuselage frames, a floor structure with transverse and longitudinal beams, and a fastening arrangement for supporting the floor structure on the fuselage shell. The fastening arrangement includes first bars each connecting an end of a transverse beam to a fuselage frame so as to transfer forces extending in a transverse direction between the floor structure and the shell. Second bars each connect an end of a transverse beam to a fuselage frame so as to transfer forces in a longitudinal direction between the floor structure and the fuselage shell. Third bars disposed beneath the floor structure transfer forces extending in a. vertical direction between the floor structure and the fuselage shell. Fourth bars each connect an end of a transverse beam to a fuselage frame so as to transfer forces extending in the vertical direction between the floor structure and the shell.

Abstract: Composite panels used in aircraft are formed by a sandwich including a lightweight honeycomb core reinforced by a solid plank in medial regions of the panel. The plank is bonded to the honeycomb and forms an integral part of the core where a strut is attached to the panel. The plank distributes point loads imposed on the panel by the strut.

Abstract: The invention relates to a fuselage cell structure of an aircraft for the simplified installation and attachment of at least one fastener for at least one conduit, the fuselage cell structure having a large number of reinforcing elements formed in particular using an aluminum alloy material. According to the invention, the reinforcing elements within the fuselage cell structure are provided with at least one groove in which the fasteners can be secured by producing a combined pressing and clamping fit creating a positive fit at least in certain regions. For this purpose, the fasteners can have at the lower face thereof, for example, two retaining feet which can be spread apart and attached by driving a fixing element into the groove. The reinforcing elements are continuous stringers preferably produced by extrusion and cross-bars, the required grooves being simultaneously extruded during the production process.

Abstract: A floor panel, in particular for covering floors of cargo holds of aircraft, is formed by a plurality of milled profiles, which are friction stir welded along their longitudinal edges, with preference continuously to form longitudinal (butt) seams. The milled profiles each form a beam “of equal stress”, with an upper flange and a lower flange spaced apart from one another along their extent. The milled profiles have a double-T-shaped cross-sectional profile, the upper flanges and the lower flanges being respectively connected by webs. With preference, the milled profiles are milled out in one piece from solid material of a sufficiently tough aluminum alloy. The joining together of the floor panel including a plurality of milled profiles that are arranged in parallel and friction stir welded allows a high mechanical load-bearing capacity of the floor panel in comparison with conventional sandwich floor panels along with a comparatively low weight.

Abstract: A fitting is provided to fix a vertical tail stabilizer of an aircraft to a composite skin and a composite frame of the aircraft in an area of a rear fuselage thereof. The fitting includes a first composite piece having lugs to attach to the vertical tail stabilizer and having vertical walls to fix the fitting to the composite frame of the rear fuselage. The fitting further includes at least one pair of additional composite pieces, each having a horizontal wall to fix the fitting to the composite skin of the rear fuselage. A second pair of additional composite pieces may be provided to further secure the fitting to the skin of the aircraft.

Abstract: In an embodiment of the disclosure, there is provided an apparatus to provide a panel stiffening element. The apparatus has an outer braided thermoplastic tube and an inner braided thermoplastic tube disposed within the outer braided thermoplastic tube. The apparatus further has a separation ply layer co-consolidated between the outer braided thermoplastic tube and the inner braided thermoplastic tube. The separation ply layer provides reinforcement and impact damage resistance to the inner braided thermoplastic tube in order to avoid a loss in structural loading capability.

Abstract: A composite structure comprises stacked sets of laminated fiber reinforced resin plies and metal sheets. Edges of the resin plies and metal sheets are interleaved to form a composite-to-metal joint connecting the resin plies with the metal sheets.

Abstract: A method for interconnecting electronic equipment within an aircraft is described. The method includes installing a multi-dimensional backplane within the aircraft, the backplane including a plurality of connectors mounted thereon, contacts associated with the connectors interconnected by electrical conductors formed within the backplane, attaching shipside wiring to a first portion of the connectors on the backplane, and attaching electrical connectors of the electronic equipment to corresponding connectors on the backplane.

Abstract: An attachment structure is provided by which interior equipment components of an aircraft passenger cabin can conveniently be affixed. The attachment structure includes, but is not limited to at least one system support that above the cabin floor extends at least along the spacing of two frame elements. The system support has a longitudinal extension along which it comprises a plurality of attachment means, evenly spaced apart from each other, for affixing interior equipment components, wherein the spacing of the attachment means is smaller than the spacing of the frame elements.

Abstract: A computer implemented method and apparatus for creating a structural joint for an aircraft. A first composite component and a second composite component are co-joined to form the structural joint for the aircraft. A hole through the first composite component and the second composite component is created. A composite shear pin is placed through the hole. A composite collar is bonded to the composite shear pin with an adhesive.

Abstract: A device for linking a frame and a stringer of an aircraft structure, including a first portion connected to a support surface of a frame, a second portion connected to a support surface of a stringer and a third portion referred to as intermediary portion connecting the first portion to the second portion. The second portion is connected to the intermediary portion by means of an articulation allowing for a relative movement between the two portions along a rotation axis perpendicular to the support surface of the stringer. The first portion is connected to the intermediary portion by means of an articulation allowing for a relative movement between the two portions along a rotation axis parallel to the support surface of the frame and to the support surface of the stringer.

Abstract: An apparatus may comprise a first skin panel having a first surface, a second skin panel having a second surface, a first flange located at an end of the first skin panel, a second flange located at an end of the second skin panel, and a strip having a third surface. The first skin panel may be located adjacent to the second skin panel such that the first flange and the second flange form a channel. The strip may be bonded in the channel. Fluid flow over the third surface of the strip, the first surface of the first skin panel, and the second surface of the second skin panel may have a desired state.

Abstract: A compartment for a transportation device is provided. The compartment may include a one-piece basin, an inflatable wall member, and multi-directional support arms to attach the basin within the transportation device. The one-piece basin may fit through an opening in the transportation device. Methods of installation for installing the compartment within the transportation device are also provided.

Abstract: The invention relates to a device, in particular a connection rod, for bracing a fuselage structure and/or for fastening components on the fuselage structure. In one embodiment, the joints are integrated into fuselage structure for linking on both sides of connection rod to fuselage structure. As a result of the integration of joints, a reduced number of individual parts is produced in comparison to previously known embodiments, which leads to a reduction in weight, a reduced maintenance and servicing outlay and an improved reliability against failure. Moreover, device according to the invention enables the introduction of forces in the region of neutral fibers of fuselage structure. A further configuration of device provides only a one-sided articulated linking of a component to fuselage structure by means of (first) end portion. Second end portion is screwed to fuselage structure. To this end, both end portions are provided with a thread at least in sections.

Abstract: The invention relates to pressure relief latch for aircraft, able to absorb vibrations and shocks without inopportune opening, as well as to adapt to dimensional stresses during its assembly. The invention thus refers to a pressure relief latch including: a console (31); a lever (34) mounted on the console, an opening effort (E) exerted on a fulcrum (46) of the lever causing an angular displacement (D) of said fulcrum between a closing position and an opening position, a roller (37) able to roll against a profile (36) of the lever and connected to an elastic return device (42), the latch being provided with means (47, 48) able to vary the angular displacement (D) of the fulcrum of the lever according to the opening effort, with two different slopes according to an opening effort E1.