Abstract: An aircraft nacelle with a connecting device between a first conduit of an air intake and a second conduit of a motor, both conduits being arranged end-to-end, the connecting device including an annular flange connected to the air intake, an annular flange connected to the motor pressed against annular flange of the air intake, the flanges extending in a plane perpendicular to the longitudinal axis of the nacelle; bolt holes formed in annular flanges and disposed plumb to one another; and connecting elements located in bolt holes, for connecting the annular flanges, wherein at least one flange includes at least one opening interposed between a bolt hole and junction zone of the flange and/or between a bolt hole and outer edge of the flange.

Abstract: A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.

Abstract: A flow body includes a flow body base body with a first shell element, a leading flow body edge with a second shell element and a clamping body, and a receiving space partially delimited by the clamping body. The flow body base body includes on a front end a projection, having a shape corresponding to that of the receiving space for engaging into the receiving space. The clamping body is internally arranged on the leading flow body edge spaced apart from a rear end of the second shell element. The rear end of the second shell element is flushly positioned on the first shell element when the projection engages into the receiving space. A smooth and harmonious transition that does not influence a laminar flow around the flow body can be achieved between the two components.

Abstract: An insulation package for thermal and acoustic insulation of a vehicle cabin has a cutout to allow a fastening device to pass through. An insulating element that is disposed in an area of the insulation package surrounding the cutout has an opening corresponding to the cutout for allowing a fastening device to pass through. At least part of the insulating element is aligned perpendicularly to an axis of the passthrough in the cutout and conformed so as to create a gap between a fastening device that has passed through and the insulation package. In this way, condensed water may be prevented from passing through the cutout in the insulation package and into the aircraft cabin.

Abstract: The invention comprises a triform fitting 1, essentially made from non-metallic composite materials including several strengthening cross ribs 4 for joining symmetrical flanges 3 and a longitudinal flange 2. The symmetrical flanges 3 include cross slots 8 for receiving the run-out 16 of the webs 11 of several T-shaped internal stringers 9 that form part of the torsion boxes 6. The feet 10 of the stringers 9 are joined along one of their faces to the skins 7 of the torsion boxes 6, while the end zones of the free faces of said feet 10 are placed against the outer face of the symmetrical flanges 3 of the triform fitting 1. This ensures that the symmetrical flanges 3 of the triform fitting 1 remain inside the torsion boxes 6. Alternatively, the fitting 1 may not include the cross slots 8.

Abstract: A structural wing-fuselage component for connecting two aerofoils to a fuselage section of an aircraft includes: a first wing shell component for the first wing and a second wing shell component for the second wing, with each component being made in a single piece and comprising a shell component on the wing side and a shell component on the fuselage side, where each shell component on the fuselage side comprises coupling parts and recesses in each case situated between the coupling parts, where in the installed state the coupling parts and the recesses of the shell component on the fuselage side for the first wing and of the shell component on the fuselage side for the second wing interlock, and where at least two coupling parts at their ends pointing away from the shell component on the wing side each comprises an extension part, a partially cylindrical fuselage shell component whose supporting rims include recesses which are engaged by the extension parts of the first wing shell components.

Abstract: The invention relates to a coupling for joining two frame segments within a fuselage cabin structure of an aircraft. The frame segments may comprise a Z-shaped or I-shaped cross-sectional geometry, optionally including a recess. Towards the top and the bottom, respectively, the frame segments are equipped with a header flange and a footer flange. According to the invention, at least one side plate is arranged in the area of one side of the web, and at least one counter plate is fitted in the area of an opposing side of the web. Because of the side plates and counter plates butted and riveted symmetrically on both sides against the webs of the frame segments to be joined, the coupling is moment-free and can be configured in a weight-optimized way. For further increase of rigidity, the header flanges may additionally be riveted with the side plates and/or counter plates.

Abstract: A lightweight structure is disclosed, in particular a lightweight structure for an aircraft which is formed from a large number of components which can be joined together by weld joining processes. According to the invention, the lightweight structure has a component thickness which is increased corresponding to the loads in the joint region of the at least one welded joint compared to a thickness of the component outside the joint region.

Abstract: A coupling element for connecting stringers in the process of joining two fuselage sections by means of at least one transverse splicing plate, wherein in each case the fuselage sections on the inside comprise a multitude of stringers arranged on fuselage skins, as well as annular frame elements, wherein the coupling element comprises a base flange and a frame element flange, and by way of the coupling element in each case a connection between the opposing stringers, the annular frame element and the fuselage skins or the transverse splicing plate takes place so that the coupling element beyond a connection of the stringer base also supports the connection of stringers on the flank side.

Abstract: A universal bracket for fastening different panel elements and/or additional devices in aircraft, comprises a base plate for fastening to a substructure, a support plate connected to the base plate and a plurality of spring clips received in the support plate to provide a releasable and vibration-damping connection to the panel elements. The base plate has at least one bore screen for fastening at least one device carrier for fastening at least one additional device, in particular emergency lighting, an emergency exit sign or the like, in different positions, wherein the fastening of the device carriers is provided with a fastening device such as fastening rivets, screws or the like.

Abstract: In one advantageous embodiment of the present disclosure, an apparatus and method for supporting a load is provided. The apparatus comprises a structure having an inner surface with a shape configured to substantially conform to an outer surface of a stringer. A number of pins extends from the inner surface of the structure such that the number of pins are configured to engage holes in the outer surface of the stringer when the structure is placed over the outer surface of the stringer. The pins support the structure with respect to the stringer when a load is applied to the structure. A number of members extends from the outer surface of the structure such that the number of members is configured to connect to a part.

Abstract: Structures, systems and methods provide a load-bearing aircraft flooring within an aircraft's fuselage. Load-supporting aircraft flooring systems preferably are provided with a longitudinally separated series of transverse bridges having an upper doubler flange which defines latitudinally separated upper openings, and a latitudinally separated series of beams which include an upper flange and a pair of separated depending web flanges received within respective upper openings of transverse bridges. The upper flanges and web flanges of the beams may thus be connected to the transverse bridges so as to support aircraft flooring panels connected to the beams. Seat tracks for attaching aircraft seats and/or other interior aircraft structures/monuments are preferably fixed to the upper flanges of the beams coincident with its longitudinal axis.

Abstract: A method and apparatus comprises a first number of layers of a composite material for a wing, a second number of layers of the composite material for the wing, and a metal layer located between the first number of layers and the second number of layers in the wing. The metal layer has a first thickness at a first area configured to receive a number of fasteners and a second thickness at a second area.

Abstract: A supporting strut for supporting an intermediate deck (2) that is arranged in an aircraft fuselage (1), includes a hollow cylindrical rod body (3) that includes a fiber reinforced material, with the two ends of the rod body (3) being designed as attachment sections for detachable attachment to the aircraft fuselage (1) or to the intermediate deck (2), wherein the rod body (3) includes at least one first reinforcement layer (10a) made from a carbon fiber fabric with an identical number of warp- and weft threads in 45° alignment or 90° alignment, as well as at least one second reinforcement layer (10b, 10c) made from a carbon fiber fabric including a higher number of warp threads than weft threads in 0° alignment, as well as a final layer including glass fiber, which together with artificial resin form a compact fiber reinforced material.

Abstract: A connection arrangement for at least two abutting components to be firmly connected to one another, includes a self-piercing rivet having a rivet head for punching of a hole and subsequent riveting of the components, wherein a washer is allocated to the self-piercing rivet at the distal end region opposite to the rivet head, with the washer including a frontal area for the insertion of a circular indentation to create a firm compression connection between a hole in the washer and the distal end region of the self-piercing rivet.

Abstract: A flexible mounting assembly allows relative movement between a top and a bottom structural member of an air frame, for instance, a helicopter. The flexible mounting assembly comprises a vertical frame member and an isolation frame member where one of the vertical frame member and the isolation frame member has a pin and the other of the vertical frame member and the frame isolation member has an aperture adapted to slidingly receive the pin in a way to accommodate relative vertical motion therebetween while substantially restraining lateral movement therebetween. The flexible mounting assembly may also include a horizontal shear wall assembly extending between adjacent vertical frame members that accommodates relative vertical motion between top and bottom structural members while substantially restraining lateral movement therebetween.

Abstract: A method of manufacturing an aircraft having adjacent spaced apart surface panels using a hollow filler within the gap between the spaced apart surface panels.

Abstract: A mounting assembly for mounting an external cargo basket onto a helicopter and a method of using the mounting assembly. The mounting assembly comprises a plurality of connectors—corresponding male and female connectors being positioned on the helicopter and on the basket, one of said corresponding connectors being an articulating connector. The cargo basket is connected to the helicopter by first connecting the articulating connector then pivoting and rotating the cargo basket using the articulating connector so as to align and connect the remaining connections.

Abstract: An aircraft control surface mounting structure including a cantilever rib mounted to a spar, the rib includes a first arm and a second arm both orientated to be substantially parallel to the line of flight of the aircraft.

Abstract: In the method of making a sealed junction between elongate aircraft parts that extend locally in main directions that are not mutually parallel, the following steps are performed: assembling a plurality of portions of a mold on the parts; and injecting a sealing material into the mold.

Abstract: An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece.

Abstract: A joint arrangement for composite-material structural members in components including a skin and a plurality of structural members, applicable to pairs of first and second intersecting structural members, such as a beam and a frame in an aircraft fuselage, both members having a configuration which includes webs, inner flanges and outer flanges, in which, in the zone of intersection between said members, the laminations of one or both flanges of the first member include transverse flaps which are joined to one or both flanges of the ends of the segments of the second member which are separated at the intersection, acting as means for transmission of loads between them.

Abstract: A fastening device of a floor module in an aircraft hull is provided. The fastening device comprises an intermediate element that on one hand can be fastened to the aircraft hull using a joining device and on the other comprises a receiving device for a holding portion of the floor module. In this case the fastening device is designed in such a way that mobility of the holding portion relative to the aircraft is guaranteed in the aircraft's longitudinal direction by means of which it is possible to guarantee stress-free installation inside the aircraft hull.

Abstract: An aircraft having a fuselage of composite type and more particularly to that of aircraft fuselage panels bearing cabin windows. The invention thus concerns a fuselage panel bearing a window comprising a composite structure cast in one piece, the structure comprising a main portion and at least one opening to accommodate a window, the structure having, on a zone surrounding the opening, a thickness more or less constant and greater than the thickness of the main portion of the structure. The invention also concerns an aircraft comprising a composite fuselage, the latter comprising such a panel or a similar panel made of metal material.

Abstract: An attachment assembly may be adapted for securing a panel member such as a class divider or a secondary door to a mating structure. The attachment assembly comprises at least one structural pin configured to be extendable from a retracted position to a deployed position. The attachment assembly may include a base support configured to be placed in overlapping contact with the panel member. The attachment assembly may include a primary support configured to be mountable such as in overlapping contact to the base support and having at least one sleeve sized and configured to receive the structural pin which is telescopically movable. A locking mechanism such as a quick release pin may be inserted through bores formed in the sleeve and in the structural pin to prevent axial movement of the structural pin relative to the sleeve.

Abstract: A composite structure comprising: a panel formed from two or more plies of composite material, the panel having a surface formed with a step where the thickness of the panel changes. Two or more stiffeners are attached to the surface of the panel. One of the stiffeners engages at least part of the step so as to transmit load forces in the panel.

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 system for affixing a gatebox to an aircraft includes a first type of gatebox operable to release material from an aircraft, a second type of gatebox operable to release material from the aircraft, a frame coupled to the aircraft operable to receive a selected one of the first type of gatebox and the second type of gatebox; and a plurality of fastenings operable to secure the selected one of the first type of gatebox and the second type of gatebox to the frame.

Abstract: A part of composite material having a wedge between two zones, the second zone being shorter than the first zone, whose structure includes from its outer surface to its inner surface: a first section formed from at least two continuous sheets extending parallel to its outer surface, the gradient of the wedge being between 20% and 50%; a wedge in the shape of a triangular prism with its larger surface dimensioned in such a way that it forms a wedge having a gradient of less than 20%; a second section formed by a plurality of continuous sheets extending parallel to the surface bounded by the first section with the wedge placed upon it. The invention also relates to a process for manufacture of the part.

Abstract: A method and apparatus comprises a first section, a second section, and a middle section. The first section is configured to be connected to a first structure. The second section is configured to be connected to a second structure. The first structure and the second structure are connected to each other at a joint. The middle section is located between the first section and the second section. The middle section has a length that is configured to change in response to a movement between the first structure and the second structure. The first section, the middle section, and the second section form a cover that is configured to form a seal for the joint.

Abstract: Control surface assemblies have a torque tube base. In one embodiment, a method includes moving an aerospace vehicle through a medium; and moving at least a portion of a control surface assembly to generate a force for controlling the vehicle.

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: A ceiling panel is configured for attaching a curtain in a cabin of a transportation device with an attachment unit, a mounting unit, and a curtain attachment unit. The ceiling panel is configured to integrate the attachment unit, the attachment unit is configured to attach the mounting unit to the ceiling panel, the mounting unit is configured to attach the curtain attachment unit, and the curtain attachment unit is configured to support the curtain.

Abstract: A wing cover panel for an aircraft wing is formed as a plurality of sections each carrying stringer sections which are then fixed together to form a wing cover panel with an integral hollow stringer.

Abstract: A fitting for joining a first component to a second component, the fitting comprising a composite part and a reinforcement element. The composite part is formed from a composite material and comprises: a base; an end wall meeting the base at a first corner; and a side wall meeting the end wall at a second corner and the base at a third corner. The reinforcement element is shaped such that it can be fitted to the composite part and engage the end wall of the composite part, the first corner of the composite part; and the second corner of the composite part.

Abstract: A mounting assembly is provided for the mounting of components in a body of a vehicle comprises at least one base element, at least one holding rail and connecting elements. The base element is designed to be arranged on the body of the vehicle. The holding rail is designed for mounting the components, and the base element and the holding rail are connected by the connecting elements so as to be spaced apart from each other.

Abstract: Embodiments of a torsion stop deployment system for utilization onboard an airborne object are provided. In one embodiment, the torsion stop deployment system includes a deployable element hingedly coupled to the airborne object and rotatable from a non-deployed position to a deployed position. The torsion stop deployment system further includes a torsion bar member, which is fixedly coupled to the airborne object and which resiliently resists the rotation of the deployable element to reduce shock to the airborne object during deployment of the deployable element.

Abstract: A device for the releasable fastening of a component in an aircraft includes a component carrier with a base plane, wherein the component carrier comprises an installation state in which the base plane of the component carrier comprises an angle relative to the horizontal base plane of the aircraft, and wherein the component carrier is equipped to accommodate a component in a releasably affixed manner.

Abstract: An aircraft wing includes a rear spar, a first skin, a second skin overhanging and converging to an opening of width (A), a support structure including a bracket engaging the spar and skins and a rib engaging the bracket via a rib attachment portion with a dimension (C) less than dimension (A).

Abstract: The invention relates to a reinforcing frame (1) of the fuselage (2) of an aircraft, said fuselage (2) comprising a skin (3) and stringers (20), the mentioned frame (1) comprising a structural member (4) and a closed, internally hollow honeycomb member (5), the structural member (4) comprising a lower base (6) which is arranged on the inner face of the skin (3) of the fuselage (2), and through which the stringers (20) connecting the frames (1) to the rest of the structure of the fuselage (2) pass, and upper reinforcing members (7) on which the mentioned honeycomb members (5) are arranged, such that the honeycomb members (5) increase the inertia and the stiffness of the frame (1) without adding weight thereto, the frame (1) having high stiffness in the transverse direction, in addition to being intrinsically stable to local buckling.

Abstract: A fastening device for connecting two overhead storage compartment elements of an aircraft is provided. A passenger service channel (PSC) extends in the overhead storage compartment elements which comprises coupling elements on the sides of the overhead storage compartment elements to be connected, said coupling elements having to be aligned with one another without being subjected to loading. For easy mountability on a first fastening element a connecting plate is arranged in a longitudinally movable manner. In the delivered state of the overhead storage compartment elements, the connecting plate is already connected to the fastening element and pushed beneath the lower face of the overhead storage compartment element, so that it does not protrude thereover and does not interfere when the overhead storage compartment element is handled before attaching to the cabin ceiling.

Abstract: An aircraft has a flight termination system that allows flight of an unmanned aircraft to be quickly and efficiently terminated. The flight termination system separates one of the control surfaces of the aircraft, such as a wing, from a fuselage of the aircraft, while one or more other control surfaces connected to the fuselage. The separation may be accomplished by firing one or more explosive bolts to release a clamp that connects the control surface to the fuselage. The separation causes an asymmetry in configuration that results in a rapid crash of the aircraft. The flight termination system causes termination to be effected in small flight footprint, without use of powerful explosives, and without a large cost in weight or volume. The flight termination system may be used in unpowered or powered aircraft.

Abstract: The invention relates to a system for attaching an element (3) capable of vibrating onto an aircraft structure (2), comprising at least one pair of scoops (10) attached onto the element capable of vibrating, as well as onto the structure, each scoop (10a, 10b) of the pair of scoops comprising: an outer rigid element (12) attached onto the structure; an inner rigid element (13) mounted inside the outer rigid element and rigidly connected to the element capable of vibrating; and a flexible element (14) placed along each outer rigid element flank, between the outer rigid element and the inner rigid element.

Abstract: An adjustment mechanism of a device for coupling a flap to a wing of an aerofoil and for adjusting the flap. The adjustment mechanism includes: a first lever, hinged to the wing via a first rotational joint to form a first axis of rotation; a second lever; a third lever, hingedly coupled to the second lever via a second rotational joint to form a second axis of rotation and hingedly coupled to the flap via a fourth rotational joint; and a push-pull rod, which is connected via a first ball joint to the second lever and via a second ball joint to the flap. The first lever and the second lever are hingedly coupled to one another via a middle joint to form a third axis of rotation. The first, second and third axes of rotation in each position of the flap run through a common pole.

Abstract: An apparatus for pivotally fastening an aerodynamic surface. The apparatus includes a bearing block. A clamping block is connected to the bearing block and includes at least two elongate holes. A pivotally mounted strip member is coupled to the aerodynamic surface and to the clamping block. At least one fastening device is insertable into each of the at least two elongate holes for locking the clamping block relative to the bearing block. The aerodynamic surface is lockable in at least one angular position.

Abstract: The stiffening frames (14) of an aircraft fuselage (2) remain continuous while passing through an upper panel (5) of the wing box and extend over the ribs (3) situated in that box. The overall mechanical strength of the assembly is improved, despite the notches it is necessary to make in the panel (5).

Abstract: A fastener device (10) provided with attachment means (20) for attaching an external load (5) and with fastener means (30) provided with a support beam (40) and with anchor means (50) for anchoring said support beam (40). A first mechanical coupling (60) connects said support beam (40) to the anchor means (50) so as to enable the support beam (40) to pivot about a first pivot axis (AX1). In addition, coupling means (70) are hinged to the support beam (40) so as to make pivoting possible about a second pivot axis (AX2), the attachment means (20) being hinged to the coupling means (70) to make pivoting possible about a third pivot axis (AX3). This fastener device (10) includes automatic folding means (100).

Abstract: Vibration isolation devices and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first fuselage section. The aircraft can also include at least one vibration isolation device coupling the first fuselage section to the second fuselage section. The vibration isolation device is translationally stiffer along a longitudinal axis than it is along a lateral and a vertical axis, and rotationally stiffer about a pitch and a yaw axis than it is about a roll axis.

Abstract: A connection arrangement for connecting a first and second reinforcing element of an aircraft or spacecraft, the reinforcing elements each have profiled cross-sections comprising at least one foot portion and at least one web portion. They are spaced from one another at their end connection faces by a strap element. The connection arrangement comprises at least one foot portion connection element, which can be adjusted and firmly joined on one side to the geometrical shape of the foot portion of the first reinforcing element, on the other side to the geometrical shape of the foot portion of the second reinforcing element and to the interposed strip element, and comprising at least one web coupling element, which can be adjusted and firmly joined on one side to the geometrical shape of the web portion of the first reinforcing element, and on the other side to the strap element.

Abstract: Disclosed is a fitting for introducing great loads into a fuselage cell of an aircraft, in particular those which emanate from undercarriage components or are introduced into them. The fitting has a shoulder plate for bearing against the inside of the skin of the fuselage cell for example over its full surface area. Arranged underneath the shoulder plate is a vertical lug shackle with a lug for introducing the loads, wherein the lug shackle is led to the outside through a clearance in the skin of the fuselage cell. At least one approximately upright fastening shackle is provided on the upper side of the shoulder plate for connecting the fitting to a frame web. According to the invention, the loads occurring are introduced into the frame, substantially “moment-free” in the region of a neutral fiber, so that the said frame is not exposed to any appreciable flexural stresses and can be of a more lightweight design.