Entries |
Document | Title | Date |
20080210824 | Connecting structure for an aircraft or spacecraft and method for producing the same - The present invention relates to a connecting structure for an aircraft or spacecraft, with a structural component and a stringer. The stringer is connected to the structural component by means of connecting regions. In order to reduce stress peaks that result for example from impact in the structural component, a high impact material is introduced into at least one of the connecting regions to provide a local increase in the energy absorbing capacity of the at least one connecting region. | 09-04-2008 |
20080245929 | Systems and Methods for Fabricating Multi-Material Joining Mechanisms - Systems and methods for fabricating multi-material joining mechanisms are described. In one embodiment, a tool assembly includes a main body having an outer surface, first and second enclosed ends, and an internal chamber. A plurality of vent holes is disposed through the outer surface, wherein each vent hole fluidly communicates with the internal chamber. A circumferentially-disposed ridge is formed on and extends outwardly from the outer surface proximate the second enclosed end. A port is disposed through the first enclosed end and is configured to be coupled to at least one of a source of pressurized medium and a vacuum. A drive assembly is operatively coupled to the second enclosed end and is configured to rotate the main body during a portion of a fabrication process. During operation, the internal chamber may be evacuated during a cure cycle, or may be pressurized to release a component from the outer surface. | 10-09-2008 |
20080258008 | Joint for Use in Aircraft Construction - A joint for use in aircraft construction, for example a wing, comprises: a cover skin having an interior surface, an exterior surface and a distal portion, said distal portion having an exterior-facing surface; and a butt-strap having a first portion for connection to the skin, said first portion having an interior surface, an exterior surface and a distal end. The first portion of the butt-strap is connected to the distal portion of the skin such that a junction is formed between the exterior surface of the skin and the exterior surface of the first portion of the butt-strap. The exterior-facing surface of the distal portion of the skin is of a shape complementary to the shape of the interior surface of the first portion of the butt-strap. The first portion of the butt-strap tapers towards its distal end such that, at said junction, the exterior surface of the skin and the exterior surface of the first portion of the butt-strap form a substantially continuous exterior surface. | 10-23-2008 |
20080283666 | METHOD AND APPARATUS FOR ATTACHING A WING TO A BODY - A method and apparatus for assembling an aircraft. A wing spar fitting is connected to a spar in a wing for the aircraft. A body frame fitting is connected to a frame in a body for the aircraft. The locations and orientations of the body frame fitting and the wing spar fitting allow for the body frame fitting to be attached to the wing spar fitting when the wing is positioned for attachment to the body of the aircraft. The wing is positioned with respect to the body of the aircraft for attachment to the body. The body frame fitting and the wing spar fitting are attached to each other with a set of fasteners after the body frame fitting is aligned to the wing spar fitting without penetrating any sealed areas in the wing, wherein the wing is attached to the body by a mechanical joint that is formed by the body frame fitting and the wing spar fitting. | 11-20-2008 |
20080302914 | CONNECTION ELEMENT FOR POWER TRANSMISSION BETWEEN A FLAP ACTUATOR AND A FLAP MOUNTED ON A WING OF AN AIRCRAFT SO AS TO SWIVEL - A connection element for power transmission between a flap actuator and a flap mounted swivelably on a wing of an aircraft includes a first section joined to the flap actuator and a second section joined to the flap. The first and second sections are formed by a strap made of a fiber composite material. | 12-11-2008 |
20090026318 | Installation system for an airplane - An exemplary embodiment of the present invention indicates an installation system for an airplane for securing interior equipment, which exhibits longitudinal and transverse rails. The transverse rails are designed as peripheral rails, and exhibit perforations to which the interior equipment can be secured. | 01-29-2009 |
20090072090 | Pivoting panel for aircraft, and composite support piece - A pivoting panel for an aircraft and to a composite support piece for this kind panel. The support piece ( | 03-19-2009 |
20090114772 | CONTINUOUS FUSELAGE CONNECTION - An attachment system for attaching a tail unit to an attachment surface of an aircraft is disclosed. An attachment surface may be a fuselage, for example. In an arrangement, the attachment system includes a mounting with a first bearing surface that is capable of resting against the tail unit, and a second bearing surface that is capable of resting against the attachment surface. The first bearing surface and the second bearing surface, of which there is at least one, include a common line of contact. In the arrangement, the planes of the first bearing surface and of the second bearing surface are at an angle that differs from 0° and 180°. | 05-07-2009 |
20090159749 | CONNECTOR ELEMENT FOR CONNECTING TWO COMPONENT PARTS - A connector element for connecting two component parts which can be for example a fuselage skin which is connected to a ring frame segment. Alternatively the connector element can also serve as a frame coupling for connecting two ring frame segments. The component parts can be formed with the same materials or with different materials. According to the disclosed embodiments the connector element in the ideal case completely compensates a temperature-conditioned change in length of at least one of the component parts by varying a connector element length of the connector elements. Thus two component parts can be connected together with different materials such as for example a fuselage skin | 06-25-2009 |
20090159750 | HOLDER FOR FIXING COMPONENTS, IN PARTICULAR LINES, INSIDE AN AIRCRAFT WITHOUT USING HOLES - Disclosed is a holder for fixing all types of component, in particular lines, without using holes and largely without using tools inside a conventional fuselage structure of an aircraft with stringers and annular formers, the formers each being provided with an angle bracket at crossing points between a stringer and an annular former. The holder is configured so as to be split in two with a lower part and an upper part which can be connected thereto, the lower part being slidable onto an angle bracket. By attaching the upper part to the lower part, the holder is positionally fixed at the crossing point in the top region of an annular former. It is fixed in its final position by connecting the holder to a transverse line holder as a function element by means of an expansion pin or other connection elements. Other alternative function elements for fixing the components, such as a longitudinal line holder, a transverse batten or a longitudinal batten for specific installation requirements, may, if necessary, be combined with at least one holder so as to form holder arrangement with any desired degree of complexity. | 06-25-2009 |
20090166475 | APPARATUS FOR THE PIVOTAL FASTENING OF AN ACTIVE SURFACE, IN PARTICULAR A SPOILER ON A WIND TUNNEL MODEL OF AN AIRCRAFT - An apparatus ( | 07-02-2009 |
20090173826 | TRAPEZOIDAL PANEL PIN JOINT ALLOWING FREE DEFLECTION BETWEEN FUSELAGE AND WING - The invention is directed a trapezoidal panel pin joint for allowing deflection of an aircraft between a fuselage section and a wing section, wherein the pin joint comprises a vertical pin portion, a lug portion, and a clevis portion; wherein at least one vertical flexible tee member is positioned below the pin joint; and wherein the pin joint is coupled to at least two horizontal flexible tee members, such that the pin joint and vertical and horizontal flexible tee members, in combination, release two rotational degrees of freedom. | 07-09-2009 |
20090173827 | METHOD AND APPARATUS FOR MONITORING THE INTEGRITY OF COMPONENTS AND STRUCTURES - A method for monitoring the integrity of a permeable structure that is disposed in an environment containing a fluid at ambient pressure is provided. At least one cavity is formed in or on the permeable structure. A source of first fluid is provided at a first pressure greater than the ambient pressure. The cavity is coupled to the source through a high-fluid-flow impedance to establish a flow of the first fluid through the permeable structure via the cavity. A rate of flow of the first fluid through the permeable structure is allowed to stabilize to a steady-state rate. A change in the steady-state flow rate of the first fluid through the permeable structure is monitored. | 07-09-2009 |
20090179111 | INTERIOR PANEL ATTACHMENT SYSTEM - An attachment system for coupling together two airplane sections includes an attachment section securing one of the airplane sections and a mount section affixed to the other section. The attachment section includes a top, a bottom, a first end, and a second end. Coupled to the top are two clamp sections, whereby at least one of the clamp sections is moveable. Coupled to the bottom is a pair of buttons. The mount section includes a top and a bottom, such that the mount bottom couples to the second airplane section. The mount section further includes a track coupled to the mount top, wherein the track includes an open end having outwardly tapered edges and a closed end. The one of the buttons slides into the track for coupling the attachment section to the mount section. | 07-16-2009 |
20090194638 | FRANGIBLE FASTENERS AND ASSOCIATED SYSTEMS AND METHODS - Frangible fasteners and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage portion, a wing portion, and a winglet carried by the wing portion. The aircraft can also include at least one frangible fastener coupling the winglet to the wing portion. The fastener is coupled to only partially release the winglet from the wing portion when a force on the winglet exceeds a threshold value. | 08-06-2009 |
20090200424 | Lateral Force Joint - A lateral force joint, with which a plate-like spar can be fastened to a fuselage strap mounted on an airplane fuselage. The plate-like spar has a through bore, into which a fastening cylinder mounted on the flange can be inserted for connecting both components. In order to allow for the location of the spar to be adjusted with respect to the fuselage strap, a bearing bush of the spar is eccentrically fitted into the through bore. Correspondingly, the fastening cylinder of the fuselage strap is mounted eccentrically on a bearing bush so that a rotation of the bearing bushes allows the lateral force joint to be adjusted. | 08-13-2009 |
20090200425 | Fitting - 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. | 08-13-2009 |
20090218445 | AIRFRAME ATTACHMENT FITTING - An airframe attachment fitting includes a fitting base having a base attachment surface and a flange attachment surface, at least one attachment post extending from the base attachment surface of the fitting base and at least one attachment flange carried by the flange attachment surface of the fitting base. An aircraft fuselage and a method of attaching a system or subsystem component to an airframe are also disclosed. | 09-03-2009 |
20090218446 | AIRCRAFT STRUCTURE WITH HINGE RIB ASSEMBLY - An aircraft structure comprising; a rear spar, an upper cover which is attached to the rear spar and overhangs to its rear; a lower cover which is attached to the rear spar and overhangs to its rear, a hinge rib assembly comprising: a first hinge rib arm attached to a first one of the covers; and a second hinge rib arm connected to the first hinge rib arm and attached to a second one of the covers; and an aerodynamic control element pivotally mounted to the hinge rib assembly. The first and second hinge rib arms are separate parts. This provides the ability to disassemble the hinge rib in-situ for repair or maintenance purposes; the ability to install or remove the hinge rib without having to move it inboard along the structure; reduced material wastage during manufacture; and the ability to install one or more elongate lines which extend in a span-wise direction along the aircraft structure. | 09-03-2009 |
20090218447 | VIBRATION ISOLATION DEVICES AND ASSOCIATED SYSTEMS AND METHODS - 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. | 09-03-2009 |
20090261202 | Universal Retaining Device, Particularly For Fastening Panel Elements And/Or Accessory Parts In Aircraft - 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. | 10-22-2009 |
20090272848 | Aircraft Component - A method of manufacturing an aircraft component such as a wing rib. The method comprises: providing a body with two or more connectors arranged in a line on the body, each connector having an arm extending from the body, a first flange positioned on a first side of the line, and a second flange positioned on a second side of the line; and attaching a separate connector to the body, the separate connector having an arm extending from the body, a first flange positioned on a first side of the line and a second flange positioned on a second side of the line. A connector for transferring load between a body of an aircraft component and a cover, the cover having an aerodynamic external surface, the connector comprising: a plate for securing the connector to the body of the aircraft component; the plate having a first face on a first side of the connector, a second face on a second side of the connector, and an edge between the first and second faces; an arm extending from the edge of the plate; a first flange carried by the arm on a first side of the connector, and a second flange carried by the arm on a second side of the connector. The arm has a relatively wide base adjacent to the edge of the plate and a relatively narrow distal end which carries the flanges. | 11-05-2009 |
20090272849 | Frame element, aircraft component assembly system and method of fitting a component in an aircraft - A frame element ( | 11-05-2009 |
20090283639 | WING TIP JOINT IN AIRFOILS - An aircraft joint comprises a wing structure and a wing tip. The wing structure has a first part of a clevis and lug fastening system located around an outer end of the wing structure. The wing tip has a second part of the clevis and lug fastening system located around an end of the wing tip. The wing tip is capable of being joined to the outer end of the wing structure. An upper aerodynamic surface and a lower aerodynamic surface are formed by joining the wing structure and the wing tip. The first part and the second part are located about a center between the upper aerodynamic surface and the lower aerodynamic surface. The first part and the second part engage each other such that a moment reaction occurs around the upper aerodynamic surface and the lower aerodynamic surface. | 11-19-2009 |
20090283640 | ATTACHMENT SYSTEM AND METHOD - An attachment system includes a dual sleeve nut comprising at least two spaced-apart nut housings; at least two interiorly-threaded fastener openings extending through the nut housings, respectively; and a nut base connecting the nut housings. At least two threaded fasteners extend through the fastener openings, respectively, of the nut housings. A method of attaching a bracket to a composite structure is also disclosed. | 11-19-2009 |
20090283641 | AIRCRAFT WITH CONNECTION ELEMENT FOR CONNECTING A CONDUIT SYSTEM TO COOLING AGGREGATES IN AIRCRAFT CABINS - The invention relates to an aircraft with a connection element for connecting at least one first conduit element or the like positioned in a supply chamber of an aircraft with at least one second conduit element positioned in a cabin chamber of the aircraft, wherein supply chamber and cabin chamber are separated from each other by means of a separation element, substantially comprising a connection part comprising fastening elements for fastening the first and second conduit element. | 11-19-2009 |
20090294592 | Fastening Device for an Aircraft Interior Equipment Component - The invention relates to a fastening device for an aircraft interior equipment component, with at least one suspension point ( | 12-03-2009 |
20090314894 | AIRPLANE FAIRING PANEL ADJUSTABLE FITTING ASSEMBLY, KIT AND METHOD - An airplane fairing panel adjustable fitting assembly allows for installation and removal of a fairing panel from outside the fairing. Blind retention features are provided and a pivoting link structure is facilitated to accommodate flexing of an aircraft structure in use. Kits and methods of attaching fairing panels are also disclosed. | 12-24-2009 |
20090321574 | ATTACHMENT ASSEMBLY AND METHOD - 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. | 12-31-2009 |
20090321575 | STRUCTURE OF AN AIRCRAFT AEROFOIL - Aircraft aerofoil structure, in particular rear spar structure ( | 12-31-2009 |
20100001137 | Method and Apparatus for Fastening Components Using a Composite Two-Piece Fastening System - 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. | 01-07-2010 |
20100006702 | Fastner-Free Primary Structural Joint for Sandwich Panels - Techniques for providing fastener-free primary structural joint for sandwich panels are disclosed. In one embodiment, a technique includes positioning a first panel having a first edge portion proximate a second panel having a second edge portion such that the first and second edge portions cooperatively form an interior recess on an interior side of the first and second panels, applying adhesive to at least one of the recessed interior side of the panel assembly and a plug configured to occupy the interior recess, inserting the plug into the interior recess, the plug including a cap that extends beyond the interior recess and overlaps adjacent portions of the first and second panels, applying adhesive to at least one of a splice and an exterior side opposite from the interior side, and attaching the splice on the exterior side. | 01-14-2010 |
20100012783 | COUPLING FOR JOINING TWO FRAME SEGMENTS - 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. The side plates comprise an L-shaped cross-sectional geometry, while the counter plates may comprise an L-shaped or T-shaped cross-sectional geometry. | 01-21-2010 |
20100038489 | LIGHTWEIGHT STRUCTURE - 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. | 02-18-2010 |
20100044514 | CONNECTION ARRANGEMENT FOR CONNECTING A FIRST AND SECOND REINFORCING ELEMENT FOR AN AIRCRAFT OR SPACECRAFT, AND A SHELL COMPONENT - 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. A shell component of an aircraft or spacecraft comprises at least two shell elements connected to a strap element at a transverse seam, which shell elements each comprise at least a first and second reinforcing element which, in turn, are connected to a connection arrangement. | 02-25-2010 |
20100065688 | METHOD AND APPARATUS FOR REINFORCING COMPOSITE STRUCTURES - 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. | 03-18-2010 |
20100065689 | LOAD INTRODUCING ELEMENT - A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element. | 03-18-2010 |
20100096506 | Connecting rod for the structural reinforcement of a fuselage structure of an aircraft - A connecting rod for the structural reinforcement of a fuselage structure of an aircraft includes a shank and eyes arranged at the shank ends on both sides for connecting the connecting rod to the fuselage structure. The connecting rod may have a reinforcing arrangement, which is configured as an all-over casing, the casing being formed by mechanically high-strength reinforcing fibers. The casing may also be formed by reinforcing fiber strands, which for their part comprise a multiplicity of discrete reinforcing fibers running parallel to one another. Carbon fibers, glass fibers, aramid fibers and high-strength ceramic fibers come into consideration in particular as reinforcing fibers. | 04-22-2010 |
20100116938 | METHOD AND APPARATUS FOR JOINING COMPOSITE STRUCTURAL MEMBERS AND STRUCTURAL MEMBERS MADE THEREBY - A composite structural member includes first and second composite sections spliced together by an overlapping composite splice member. | 05-13-2010 |
20100116939 | AIRCRAFT APPLYING MULTISYSTEM CONNECTION DEVICES - An aircraft including a cabin, on at least one wall of which are attached first portions of plural multisystem connection devices, each device including a male portion or plug and a female portion or socket capable of fitting into each other. Each male and female portion includes: a first mechanism connecting to a liquid or gas supply of the aircraft; and a second mechanism connecting to a supply of electricity and/or electric signals of the aircraft. | 05-13-2010 |
20100127127 | ASSEMBLY BETWEEN A FRONT FITTING AND THE TRACTION COUPLING OF THE TWO LATERAL BOXES OF THE HORIZONTAL STABILIZER OF AN AIRCRAFT - The invention relates to an assembly between a front fitting and the traction coupling of the two lateral boxes of the horizontal stabilizer of an aircraft comprising a front fitting ( | 05-27-2010 |
20100127128 | DEVICE FOR MOUNTING NON-DIMENSIONING EQUIPMENT ON THE STRUCTURAL FRAME OF A VEHICLE, VEHICLE FITTED WITH SUCH DEVICE AND MOUNTING METHOD - A device for mounting non-dimensioning equipment ( | 05-27-2010 |
20100140408 | Vibrations Damper for Fastenings Elements in Aircrafts - Means for attaching installed parts ( | 06-10-2010 |
20100140409 | SYSTEM FOR ACCOMMODATING AT LEAST ONE OBJECT IN A CABIN OF A VEHICLE - A system for accommodating at least one object in a cabin of a vehicle exhibits at least one first connecting means, at least one second connecting means and at least one latching device, wherein the first connecting means is positioned in the cabin of the vehicle, and the second connecting means is positioned on the object, the first connecting means and the second connecting means establish a connection in an accommodating position of the object, and the latching device latches the object in the accommodating position. This makes it possible to replace conventional stowage compartments with a weight-saving system, which may accommodate correspondingly prepared luggage items or other objects in a vehicle cabin. | 06-10-2010 |
20100148008 | RIB-FITTING - Rib-fitting as a component ( | 06-17-2010 |
20100148009 | CONNECTING ARRANGEMENT COMPRISING A COUPLING ELEMENT AND TWO CURVED RIBS OF AN AIRCRAFT OR SPACECRAFT - The present invention relates to a connecting device two curved ribs ( | 06-17-2010 |
20100170995 | SUPPORT STRUCTURE FOR A WING - A support structure for an aircraft, includes one or several bar elements and one or several junction elements. At least one bar element includes a transition region which can be made to engage at least one junction element. When the transition region of the bar element engages at least one junction element, centric force transmission takes place between the bar element and the junction element. | 07-08-2010 |
20100176242 | Gap Covering Device - A gap covering device ( | 07-15-2010 |
20100181428 | Profile Comprising at Least One Hollow Profile Section - The present invention provides a profiled part, for use, in particular, within an aircraft or spacecraft, the profiled part comprising at least one hollow profiled part portion and a T-shaped and/or L-shaped profiled part portion. | 07-22-2010 |
20100187362 | FASTENING ELEMENT FOR INSULATION PACKAGES - A fastening element includes, but is not limited to at least one first body, at least one second body, and at least one locking device. The first body and the second body in each case on one end include, but are not limited to a pressing element for pressing an insulation package against an object. The first body and the second body movably engage each other so that the pressing elements are located at opposite ends of the fastening element. The at least one relative position of the first body to the second body may be fixed by means of the locking device. In this way effective fastening of insulation packages to objects in an aircraft cabin may be ensured without all the insulation packages having to comprise openings for accommodating fastening pins. | 07-29-2010 |
20100230544 | Fastening Device of a Floor Module - 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. | 09-16-2010 |
20100237194 | TRANSVERSE SPLICING PLATE FOR CREATING A FUSELAGE, AND A METHOD FOR CONNECTING TWO, IN PARTICULAR WOUND, CFP FUSELAGE SECTIONS - A transverse splicing plate for producing a fuselage of an aircraft by connecting several CFP fuselage sections that have in particular been produced in the winding method, in each case by forming a transverse seam, wherein the flexible transverse splicing plate is of a multilayer construction, in other words it comprises a multitude of plate segments arranged one above the other, wherein each of the plate segments comprises a multitude of longitudinal slits, each being able independently of each other to make small radial bending movements in order to cause tolerance compensation in radial direction between the fuselage sections to be joined, in which tolerance compensation a sliding movement between the sub-plates of the plate segments arranged one above the other takes place in axial direction of the barrel-shaped fuselage sections, and wherein on the inside the ends of the fuselage sections comprise chamfers; as well as a method for producing a connection between two CFP fuselage sections, which have preferably been produced in the winding method, by means of a transverse splicing plate according to the invention. | 09-23-2010 |
20100243810 | INTEGRATIVE STRUCTURE FOR AIRCRAFT FAIRING - Joining structure for aircraft fairing ( | 09-30-2010 |
20100252683 | Conjoining of a cross beam to a structure part - A conjunction for mounting a cross beam to a structure part of an aircraft fuselage by means of at least one conjunction device wherein the conjunction device defines a circular path on which loads acting on the cross beam are applied in the structure element. | 10-07-2010 |
20100252684 | FUSELAGE CELL STRUCTURE OF AN AIRPLANE FOR THE SIMPLIFIED INSTALLATION AND ATTACHMENT OF FASTENERS FOR FASTENING CONDUITS - 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 aluminium 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. | 10-07-2010 |
20100258676 | AIRCRAFT INCLUDING STIFFENER EDGE JUNCTIONS AND METHOD FOR PRODUCING ONE SUCH AIRCRAFT - 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. | 10-14-2010 |
20100264271 | FITTINGS FOR ATTACHING THE VERTICAL TAIL STABILIZER OF AN AIRCRAFT - The invention relates to fittings ( | 10-21-2010 |
20100264272 | AIRCRAFT STRUCTURE INCLUDING STIFFENER EDGE JUNCTIONS - An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area. | 10-21-2010 |
20100294889 | DEVICE FOR JOINING TORSION BOXES OF AIRCRAFT - The invention relates to a device ( | 11-25-2010 |
20100301166 | EXPANDABLE PRECURED JOINT FILLER - 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. | 12-02-2010 |
20100301167 | Holder System for Fastening an Aircraft Interior Component to a Transporting Apparatus and to an Aircraft Structure - A holder system for fastening an aircraft interior component to a transporting apparatus and to an aircraft structure includes an interior component holder configured to be connected to the interior component and which has a fastening device for fastening the interior component holder to the transporting apparatus. A structure holder is configured to be connected to the aircraft structure. A connecting element is fastened to the interior component holder and is configured to be connected to the structure holder in order to fasten the interior component to the aircraft structure. | 12-02-2010 |
20100308170 | COMPOSITE JOINT PROTECTION - The present invention relates to a joint between a laminar composite cover ( | 12-09-2010 |
20100314494 | ADAPTER PLATE FOR AIRPLANE STRUCTURE - The invention is directed to an adapter plate ( | 12-16-2010 |
20100314495 | DEVICE FOR ATTACHING A PIECE OF FURNITURE TO THE FLOOR OF AN AIRCRAFT - Devices associated with an interface that is advantageous for the customized attachment of pieces of furniture to the floor of an aircraft. The interface includes rails extending longitudinally in the aircraft cabin, able to receive anchoring devices for connecting the furniture elements to these rails. The anchoring devices include axial and radial claw clamping devices which are associated together in pairs and operated together in pairs by a single and same lever ( | 12-16-2010 |
20100320327 | INSTALLATION SYSTEM FOR THE CONNECTION OF SYSTEMS TO A STRUCTURE OF AN AIRCRAFT, A MEASUREMENT SYSTEM AND A METHOD - An installation system includes a structure for an aircraft, at least one carrier for an arrangement of at least one device of the aircraft, at least two attachment elements configured to attach the at least one carrier to the structure, and at least one mounting having an adjustable reception element receiving one of the at least two attachment elements. | 12-23-2010 |
20110001010 | ARRANGEMENT OF TWO FUSELAGE SECTIONS OF AN AIRCRAFT AND A CONNECTING STRUCTURE FOR CONNECTING FUSELAGE SKINS - 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. | 01-06-2011 |
20110006160 | FIXING SYSTEM FOR A SEAT, IN PARTICULAR AN AIRCRAFT SEAT - The system comprising a base ( | 01-13-2011 |
20110011980 | CONNECTING ARRANGEMENT FOR JOINING TWO STIFFENING ELEMENTS HAVING DIFFERENT CROSS-SECTIONAL PROFILES FOR AN AIRCRAFT OR SPACECRAFT, AND SHELL COMPONENT - A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with in each case 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 in each case. | 01-20-2011 |
20110024565 | Aircraft Component Assembly System - An aircraft component assembly system ( | 02-03-2011 |
20110024566 | ELECTRICAL POWER TRANSFER ASSMEBLY - An assembly for an aircraft including a first structure mounted to a second structure, and a power transfer assembly electrically connecting the first and second structures. The first structure is movable relative to the second structure between a retracted and an extended position. The power transfer assembly includes a housing, a spool mounted for rotation relative to the housing and biased to rotate in a first direction, and an electrical cable adapted to be wound around the spool when the spool rotates, such that movement of the first structure from its retracted to its extended position causes the cable to be unwound from the spool by rotation of the spool in a second direction opposite the first. Also, a method of electrically connecting the first and second structures. The invention may be applied to an aircraft wing to electrically connect a leading edge slat to a fixed aerofoil portion. | 02-03-2011 |
20110031350 | COMPONET, IN PARTICULAR A SHELL COMPONENT, WHICH CAN BE JOINED THERMALLY AND/OR MECHANICALLY, FOR BUILDING A FUSELAGE SECTION OF AN AIRCRAFT - A component for building a fuselage section of an aircraft includes a border area connectable to a corresponding further border area of a further component so as to form an electrically conductive joint, wherein the component includes a composite structure | 02-10-2011 |
20110031351 | Support assembly - A support assembly for guiding a flap on an aircraft wing during deployment of the flap is disclosed. The assembly comprises an arcuate guide track mountable to an aircraft wing and defining a two-dimensional path, a carriage mounted on the guide track so as to slide along the track during flap deployment, a part-spherical bearing, and a shaft having one end attachable to a flap and the opposite end coupled to the carriage via said part-spherical bearing. The shaft is free to pivot relative to the carriage about a centre of the part-spherical bearing in all directions, as the carriage slides along the track. | 02-10-2011 |
20110042519 | INTERCONNECTION AND AIRCRAFT OR SPACECRAFT HAVING SUCH AN INTERCONNECTION - The present invention provides an interconnection, in particular in the field of aerospace. The interconnection has a T-stringer, an Ω-stringer and a connecting arrangement. The connecting arrangement connects base sections of the T-stringer and of the Ω-stringer to one another. This provides a coupling of an Ω-stringer to a T-stringer which is comparatively insensitive with respect to tolerances relating to the orientation of the Ω-stringer in relation to the T-stringer. | 02-24-2011 |
20110073711 | JOINING OF STRUCTURAL AIRCRAFT ELEMENTS - Joining of a structural aircraft element ( | 03-31-2011 |
20110073712 | Lateral Coupling Device For Holding And Guiding At Least One Aerodynamic Body Relative To The Main Wing Of An Aircraft, Airfoil And Aircraft With Such A Lateral Coupling Device - A lateral coupling device for holding and guiding at least one aerodynamic body relative to the main wing in its wingspread direction during the adjustment thereof features: a coupling connection, a first coupling joint for coupling a first end of the coupling connection to the main wing or an aircraft component connected thereto or another aerodynamic body, as well as a second coupling joint for coupling the second end of the coupling connection to the aerodynamic body, where the lateral coupling device has a total of five degrees of freedom and allows an adjusting motion of the aerodynamic body relative to the main wing transverse to the wingspread direction thereof. | 03-31-2011 |
20110089292 | AIRCRAFT JOINT - A method of joining a wing to an aircraft fuselage by forming a series of pinned lug joints between a fuselage side and a wing side of a wing box structure. The joint forming process includes providing a single row of lugs on one side of the joint to be formed, and providing a respective double row of lugs on the other side of the joint to be formed. A gap between opposing lugs of the double row varies along the row. The wing side and the fuselage side of the wing box structure are brought together such that the lugs of the single row are located within the respective gaps between opposing lugs of the double row, and the lugs are pinned to form the series of pinned lug joints. Also, a joint formed by the method. | 04-21-2011 |
20110108668 | DEVICE, IN PARTICULAR CONNECTION ROD, FOR BRACING A FUSELAGE STRUCTURE OF AN AIRCRAFT AND/OR FOR FASTENING A COMPONENT - 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. | 05-12-2011 |
20110155852 | STIFFENING ELEMENT FOR AN AIRCRAFT AND A SURFACE STRUCTURE WITH A STIFFENING ELEMENT OF THIS TYPE - A stiffening element for stiffening a surface structure of an aircraft includes a web and a foot configured to connect to the surface structure. The foot includes an inner section near the web and an outer section further from the web than the inner section. The outer section has a greater elasticity than the inner section. | 06-30-2011 |
20110155853 | Interface Element, Aircraft Interior Equipment Component And Method For Installing An Aircraft Interior Equipment Component - An interface element ( | 06-30-2011 |
20110168842 | JOINING SYSTEM BETWEEN LININGS AND THE STRUCTURAL ELEMENTS THAT SUPPORT THEM - The invention relates to a coupling system for use between cladding and structural elements supporting same, said cladding comprising thin sheets ( | 07-14-2011 |
20110174928 | JOINING ARRANGEMENT FOR THE LATERAL BOXES OF A HORIZONTAL TAIL STABILISER WITH A TUBULAR CENTRAL BOX AND MANUFACTURING METHOD FOR SAID BOX - Joining arrangement for the lateral boxes ( | 07-21-2011 |
20110174929 | LOCKING DEVICE FOR LOCKING A STRUCTURAL ELEMENT AGAINST AN ADJACENT STRUCTURE, AN AIRCRAFT PROVIDED WITH SAID DEVICE, AND AN EXTRACTION METHOD IMPLEMENTED BY SAID DEVICE - The present invention relates to a locking device provided with a latch ( | 07-21-2011 |
20110174930 | FUSE LINK DEVICE BETWEEN A MOBILE PART AND A FIXED PART OF AN AIRCRAFT NACELLE - The object of the invention is an aircraft nacelle that comprises at least one part, called a door ( | 07-21-2011 |
20110198445 | CONNECTION ASSEMBLY FOR AT LEAST ONE ITEM OF ELECTRONIC EQUIPMENT IN AN AIRCRAFT - The invention relates to an assembly for connection ( | 08-18-2011 |
20110210206 | CONNECTION OF A WING TO A FUSELAGE OF AN AIRPLANE - An aerofoil connection on a fuselage airframe comprising a plurality of double-jointed coupling members. In each case at least two z-coupling members extending substantially parallel to a vertical axis of the aircraft and in each case at least two xz-coupling members are arranged in the region of two longitudinal edges of a fuselage airframe recess wherein the xz-coupling members are configured in each case for a first maximum of a load in the event of a crash and of a load in normal flight operation parallel to a longitudinal axis of the aircraft, and for a second maximum of a load in the event of a crash and of a load in normal flight operation parallel to the vertical axis. The xz-coupling members are capable of absorbing force components parallel to the x-axis as well as force components which arise parallel to the z-axis. | 09-01-2011 |
20110215202 | WING SPAR SPLICE JOINT - A wing spar joint is provided for coupling the inboard ends of a right wing spar and a left wing spar. The wing spar joint comprises a forward fitting, an aft fitting, a spar cap a lower chord fitting and a strap member. A first plurality of fasteners secure the forward fitting and the aft fitting together through a web portion of the wing spars. A second plurality of fasteners secure the upper spar cap, the lower spar cap and the forward fitting together through upper chords of the wing spars. A third plurality of fasteners secure the lower chord fitting, the strap member and the forward fitting together through lower chords of the wing spars. The forward fitting, aft fitting, spar cap and strap member are thus secured together with the wing spars to form a rigid connecting joint at the inboard ends of the wing spars. | 09-08-2011 |
20110215203 | ATTACHMENT STRUCTURE, ATTACHMENT DEVICE AND ATTACHMENT SYSTEM FOR ATTACHMENT OF A FINISHING COMPONENT IN AN AIRCRAFT - An attachment device for attaching an equipment component in an aircraft, comprising a second attachment element for attaching an equipment component in an aircraft, the second attachment element comprising a guiding element, a contact element and a locking element, wherein the guiding element is introducible into a first section of a first attachment element, wherein the guiding element is movable from the first section of a first attachment element according to the present invention into a second section of the first attachment element, wherein the first attachment element and the second attachment element are mechanically couplable by engaging from behind the first attachment element in the second section of the first attachment element, wherein, in the coupled state, the contact element provides a mechanical contact between first and second attachment element and wherein by operating the locking element the first attachment element and the second attachment element are releasably fixable relative to one another. | 09-08-2011 |
20110233338 | JOINT - A joint between an aircraft wing box cover and a leading/trailing edge structure, the cover and the structure having flush aerodynamic outer surfaces, wherein the structure has an integrally formed land that extends over an inner surface of the cover, and the land of the structure is fastened to the cover. Also a method of forming the joint. | 09-29-2011 |
20110233339 | PASSENGER SEAT ASSEMBLY AND ASSOCIATED FLOOR PANEL STRUCTURE - A system is provided, including at least one floor panel adapted to matingly engage and be supported by a support structure; and securing means for securing at least one seat support to the floor panel; wherein the seat support corresponds to a vertical plane at a substantially horizontal end of at least one seat. | 09-29-2011 |
20110248119 | STRUCTURAL CONNECTORS AND METHODS OF USING SAME - Structural connectors for watercrafts, buildings and aircrafts are disclosed. In general, each structural connector includes at least a pair of members extending outwardly from and substantially perpendicular to a body of the structural connector, the members spaced apart from one another so as to form a recess therein between. In some embodiments, the recess may be sized and shaped for receiving supporting members including the likes of stringers and support plates. | 10-13-2011 |
20110278398 | SYSTEM FOR FASTENING A SEAT IN AN AIRCRAFT RAIL - A system for fastening an aircraft seat in a corresponding rail of the rest of the aircraft, of the type including a base to which the rest of the seat is connected and including support surfaces on the upper face of the rail and associated with a locking slide that can be moved by a lever under the control of an assembly operator, between an assembly/disassembly position of the system relative to the rail and a locking position thereof and therefore of the seat relative to the rail and therefore the aircraft, in which the support surfaces of the base on the rail include elastically deformable facing device(s) for reacting fastening play. | 11-17-2011 |
20110284691 | Method for connecting a first material to a second material in aircraft construction - The invention concerns a method of connecting a first material to a second material by means of a heat-activatable adhesive material ( | 11-24-2011 |
20110284692 | STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT AND A FUSELAGE COMPONENT ARRANGEMENT OF AN AIRCRAFT OR SPACECRAFT - In the case of a structural component of an aircraft or spacecraft comprising a fuselage portion connection region for connecting to an associated fuselage portion and having a thermal expansion coefficient which is approximately matched to the associated fuselage portion; an inner connection region for connecting to an associated installation element and having a thermal expansion coefficient which is approximately matched to the associated installation element; and a separation region for connecting the fuselage portion connection region and the inner connection region, at least one of the regions has a high heat conduction resistance. | 11-24-2011 |
20110303792 | TELESCOPIC STRUT - A telescopic strut for electrically connecting a fixed structure of an aircraft to a movable structure mounted to the fixed structure, wherein the strut is adapted to be mechanically connected to the fixed structure by its one end and to be mechanically connected to the movable structure by its opposite end, the strut comprising a plurality of telescopic elements and containing a helically coiled electrical cable, wherein the cable is adapted to move between retracted and extended positions with the telescoping of the strut. Also, a method of operating an aircraft having a movable structure mounted to a fixed structure, and one or more of the telescopic struts mechanically and electrically connected between the fixed and movable structures. | 12-15-2011 |
20110309196 | DEVICE FOR HOLDING AN INSULATING BLANKET AND FOR FASTENING TWO-PARTS SYSTEMS - This device for holding an insulating blanket and for fastening systems in an aircraft comprises a base ( | 12-22-2011 |
20110309197 | DEVICE FOR HOLDING AN INSULATING BLANKET AND FOR FASTENING SYSTEMS ADAPTED TO BE MOUNTED IN AN AIRCRAFT - This device is intended for an aircraft comprising frames, a skin and connecting pieces between the skin and the frames, referred to as clips. | 12-22-2011 |
20110315823 | FIXATION MECHANISM FOR INSTALLING THERMAL INSULATION SHEETS IN AN AIRCRAFT BODY - The invention relates to a device for holding an insulating blanket and for fastening systems in an aircraft, comprising a base having two ends from each of which an arm extends. | 12-29-2011 |
20120006942 | COUPLING ASSEMBLY - A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm. The shaft is received in the through-bore. A setting device acts between the head and the shaft for setting of the position of the shaft with respect to the head in the axial direction of the shaft. The assembly further includes one or more spherical bearing surfaces, which permit self-alignment of the setting device to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. Also, a joint comprising a first component joined to a second component by one or more of the coupling assemblies. Also, a method of forming a joint using one or more of the coupling assemblies. | 01-12-2012 |
20120025023 | LONGITUDINAL JUNCTION FOR AIRCRAFT FUSELAGE PANELS IN COMPOSITE MATERIALS - An aircraft fuselage structure including at least a first and a second panel made of composite materials, placed side by side along a juncture and assembled with one another through at least one longitudinal joint. The longitudinal joint includes a double Ω stringer including: a first and a second Ω element each including a head and two cores, a first side base-plate situated in continuity of the first core of the first Ω element, a second side base-plate situated in continuity of the last core of the second Ω element, and a central base-plate connecting the second core of the first Ω element with the first core of the second Ω element and covering the juncture between the two panels. | 02-02-2012 |
20120025024 | DEVICE FOR THE MOUNTING OF CONNECTORS - A device for mounting at least one connector in an aircraft fuselage includes a first and a second traverse configured to connect the device to a structural section of the aircraft fuselage at end sections of the first and second traverses. A frame element extends transversely between the first and the second traverses and is configured to accommodate the at least one connector. A first and a second connecting profile respectively connect the frame element to the first and second traverse. | 02-02-2012 |
20120037756 | DEVICE FOR MOUNTING SYSTEMS AND AIRCRAFT OR SPACECRAFT - The present invention provides a device for mounting systems, for example an electrical or fluid-conveying line, on a structure, in particular of an aircraft or spacecraft, the device comprising: a basic holder which is fastenable to the structure; and a system holder for mounting the systems, which system holder is fastenable to a first interface of the basic holder; the basic holder comprising a first part, which comprises the first interface, and a second part, one end of which is attachable to the first part so as to be pivotal about a pivot axis and the other end of which is fastenable to the structure. | 02-16-2012 |
20120061518 | APPARATUS AND METHOD FOR QUICKLY RELEASING A DOME IN A DOMED SATELLITE ANTENNA - An apparatus and method for quickly releasing, without using any tools, the dome from the base of a domed satellite antenna system. An actuator moves in each of a number of quick-release fasteners around the dome to an unlocked position. The dome is lifted to reveal the operational components, the revealed components can then be changed (e.g., by setting switches to receive different satellites), and then the dome is replaced over the base. Each actuator is moved to the locked position to re-attach the dome to the base. | 03-15-2012 |
20120085866 | INTERCHANGEABLE JOINT CONCEPT FOR AN AIRCRAFT REAR FUSELAGE CONE - Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising a balancer fitting, three lugs and a waiting link. When there is a failure in one of the lugs, the balancer fitting acts supporting loads in the transversal direction of the aircraft. The waiting link only acts if a failure in other link occurs. This waiting link is able to support loads in the longitudinal direction of the aircraft. | 04-12-2012 |
20120091275 | Weathertight fitting for aircraft tail vertical stabiliser mounting - Weathertight fitting ( | 04-19-2012 |
20120104169 | VIBRATION ISOLATION DEVICES AND ASSOCIATED SYSTEMS AND METHODS - 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. | 05-03-2012 |
20120126062 | INLET NOSE COWL WITH UNINTERRUPTED AIRFLOW SURFACE - An aircraft component and method of attaching an additional component to an aircraft component are described. The aircraft component includes an exterior surface exposed to external airflow during flight, an interior surface, and a locally thickened fastening portion between the exterior and interior surfaces. An area of the interior surface on the locally thickened fastening portion is substantially parallel to an area of the exterior surface on the locally thickened fastening portion. The thickness of the aircraft engine housing component between the exterior surface and the interior surface is greater at the fastening portion than at an area surrounding the fastening portion. When the additional component is fastened to the substantially parallel area of the interior surface on the fastening portion with mechanical fasteners, the mechanical fasteners do not penetrate the exterior surface. | 05-24-2012 |
20120132753 | INTERFACE ARRANGEMENT BETWEEN TWO COMPONENTS OF AN AIRCRAFT LIFTING SURFACE USING AN INTERMEDIATE PART - Interface arrangement between a first component ( | 05-31-2012 |
20120132754 | INTERFACE ARRANGEMENT BETWEEN TWO-COMPONENTS OF AN AIRCRAFT STRUCTURE - Interface arrangement between a first component ( | 05-31-2012 |
20120132755 | AIRFRAME STRUCTURAL ELEMENT - An airframe structural element, such as an aircraft rib, is disclosed that comprises an integral pipe connector element for connecting pipes through the structural element. The pipe connection means provided by the pipe connector element may be aligned on a common axis with a pipe connection means provided by an adjacent airframe structural element. | 05-31-2012 |
20120132756 | SHELL SEGMENT FOR PRODUCING A FUSELAGE CELL SECTION FOR A FUSELAGE CELL OF AN AIRPLANE - The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. | 05-31-2012 |
20120138747 | LOCKING FASTENING DEVICE, ADJUSTABLE FASTENING DEVICE, COMPONENT SYSTEM, MAIN WING OF A WIND TUNNEL MODEL AIRCRAFT, AND WIND TUNNEL MODEL AIRCRAFT HAVING SUCH A MAIN WING - A locking fastening device for fastening a first component to a second component, an adjustable fastening device for adjustably fastening a first component to a second component, and a component system including at least one first component that is fastened to a second component are described. Also described are a main wing of a wind tunnel model aircraft having an adjusting and fastening system which includes at least one locking fastening device and at least two adjustable fastening devices for adjusting and fastening an aerodynamic additional body that is adjustable relative to the main wing by means of a plurality of retaining devices, as well as a wind tunnel model aircraft having such a main wing. | 06-07-2012 |
20120145829 | FASTENING SYSTEM FOR HANGING MOUNTABLE OVERHEAD CONTAINERS - A fastening system ( | 06-14-2012 |
20120160962 | INSTALLATION ASSEMBLY INCLUDING A FIXATION RAIL FOR ATTACHING DEVICES IN AN AIRCRAFT - The invention relates to a fastening assembly for the fastening of systems in an aircraft comprising frames ( | 06-28-2012 |
20120168563 | ADJUSTABLE IRON FITTING FOR THE INSTALLATION AND FITTING OF AIRCRAFT FAIRING - It is intended for installing and fitting, in conjunction with other iron fittings, a fairing on an aircraft in correspondence with a housing located at the junction of a stabiliser and a fuselage of an aircraft structure. Wherein each iron fitting comprises:
| 07-05-2012 |
20120175464 | PRE-INSTALLED ADAPTABLE SUPPLY NETWORK FOR AEROPLANES - An aircraft structure is provided that includes, but is not limited to structural elements, a first multitude of lines that are in a fixed manner connected to structural elements, a second multitude of lines that are in a fixed manner connected to structural elements and whose longitudinal direction intersects the longitudinal direction of the first multitude of lines so that the longitudinal directions of the lines form a network that covers the aircraft structure at least in some sections, and connecting elements in order to, in the state of the structural elements installed in the aircraft structure, connect selected lines of the first multitude to selected lines of the second multitude of selected points of intersection of the network in order to in this way form transmission lines, such as lines for electricity transmission and/or data transmission. Furthermore, a method is provided for manufacturing such an aircraft structure. | 07-12-2012 |
20120193475 | CONNECTOR FOR STIFFENING FRAMES BETWEEN AN AIRCRAFT FUSELAGE AND A WING BOX - The stiffening frames ( | 08-02-2012 |
20120193476 | REMOVABLE FASTENER DEVICE EQUIPPED WITH ATTACHMENT MEANS FOR ATTACHING AN EXTERNAL LOAD AND WITH FASTENER MEANS FOR FASTENING SAID ATTACHMENT MEANS TO AN AIRCRAFT, AN ASSOCIATED AIRCRAFT, AND AN ASSOCIATED METHOD - A fastener device ( | 08-02-2012 |
20120211604 | ADJUSTMENT MECHANISM OF AN ADJUSTMENT DEVICE FOR COUPLING AN ADJUSTMENT FLAP TO A MAIN WING, AND SUCH AN ADJUSTMENT DEVICE - 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. | 08-23-2012 |
20120223188 | MOVABLE CONNECTING PLATE FOR CONNECTING TWO OVERHEAD STORAGE COMPARTMENT ELEMENTS - 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. | 09-06-2012 |
20120228430 | TORSION STOP DEPLOYMENT SYSTEM FOR AIRBORNE OBJECT - 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. | 09-13-2012 |
20120228431 | FASTENING ARRANGEMENT FOR FASTENING A COMPONENT ON A FUSELAGE - 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. | 09-13-2012 |
20120234976 | CEILING PANEL HAVING CURTAIN RAIL IN A TRANSPORT CABIN - 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. | 09-20-2012 |
20120234977 | COUPLING STRUCTURE FOR AIRFRAME COMPONENTS - Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part | 09-20-2012 |
20120241560 | Joint Sealing System - 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. | 09-27-2012 |
20120280083 | METHOD OF MAKING A SEALED JUNCTION BETWEEN AIRCRAFT PARTS - 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. | 11-08-2012 |
20120286094 | Helicopter Cargo Basket Mounting Assembly and Method of Using Same - 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. | 11-15-2012 |
20120305709 | CONNECTION ARRANGEMENT, PARTICULARLY FOR AIRCRAFT STRUCTURE PARTS - 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. | 12-06-2012 |
20120325968 | Clip Attachment System Connecting Aircraft Structures to Each Other - 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. | 12-27-2012 |
20130020440 | STRUCTURE FOR JOINING TORSION BOXES IN AN AIRCRAFT USING A TRIFORM FITTING MADE FROM NON-METALLIC COMPOSITE MATERIALS - The invention comprises a triform fitting | 01-24-2013 |
20130026297 | Multi-Directional Load Joint System - 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. | 01-31-2013 |
20130032669 | FASTENING DEVICE PARTICULARLY SUITABLE FOR THE FASTENING BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - 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. | 02-07-2013 |
20130032670 | WALL COMPONENT FOR AN AIRCRAFT - The present disclosure relates to a wall component for an aircraft for forming an outer wall comprising at least one first wall element, at least one second wall element and at least one connecting device for connecting the first wall element to the second wall element. On wall regions that are to be directed towards each other, the first and the second wall element comprise connecting regions. Furthermore, a joint element is provided, which comprises a joint region with a joint region surface that is to be arranged towards the outside of the aircraft, wherein the joint region is designed to be received with a matching fit into a recess formed by the connecting regions of the wall elements, and wherein the joint region surface, when the joint element is inserted, is flush with the outer surfaces of the wall elements. | 02-07-2013 |
20130043350 | PRESSURE RELIEF LATCH - 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. | 02-21-2013 |
20130062470 | DEVICE FOR LINKING A STRINGER AND A FRAME OF AN AIRCRAFT STRUCTURE - 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. | 03-14-2013 |
20130075529 | Stabilizer Torque Box Assembly and Method - 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. | 03-28-2013 |
20130075530 | METHODS AND SYSTEMS FOR INCORPORATING TRANSLATING BACKPLANES TO FACILITATE WIRE SEPARATION - 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. | 03-28-2013 |
20130146712 | APPARATUS FOR ATTACHMENT OF WING PANELS - A shroud panel ( | 06-13-2013 |
20130168496 | COVERING DEVICE AND AIRCRAFT AREA COMPRISING A COVERING DEVICE - 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. | 07-04-2013 |
20130175395 | MOUNTING ASSEMBLY AND METHOD FOR MOUNTING A SOUND-DEADENING BODY TO A FUSELAGE OF AN AIRCRAFT - 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. | 07-11-2013 |
20130181092 | DEVICE AND METHOD FOR ASSEMBLING TWO SECTIONS OF AIRCRAFT FUSELAGE - 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. | 07-18-2013 |
20130200215 | Structural Joint Having Continuous Skin With Inside And Outside Stringers - 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. | 08-08-2013 |
20130206911 | Attachment Devices for Rotorcraft Front Windshield - 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. | 08-15-2013 |
20130233973 | BONDED SPLICE JOINT - 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. | 09-12-2013 |
20130277500 | SHOCK-RESISTANT DEVICE AND METHOD - A shock-resistant device includes snubbers that may be selectively extended to selectively create a stiff attachment between a vibration-isolated component of the device, and another part of the device. The snubbers may be electromechanical or hydraulically driven. The device may be a sensor system for an unmanned aerial vehicle, with the snubbers extendible to create a stiff attachment between an inner gimbal and an outer shell of the sensor system, for example prior to landing the unmanned aerial vehicle on an aircraft carrier, or prior to transportation or storage of the unmanned aerial vehicle. The snubbers may be able to be manually actuated, even when the unmanned aerial vehicle has no power available. | 10-24-2013 |
20130313367 | AIRCRAFT INTERIOR COMPONENT SYSTEM AND METHOD FOR MOUNTING AN INTERIOR COMPONENT SYSTEM IN AN AIRCRAFT - An aircraft interior component system includes an aircraft interior component, a first structure holder fastened to an element of the aircraft structure, and a first component holder fastened to the aircraft interior component. The first component holder is fastened to the aircraft interior component in a first region thereof which faces an aircraft cabin ceiling when the aircraft interior component is mounted in an aircraft. The first structure holder and the first component holder attach the aircraft interior component in a suspended manner to the element, such that a mounting gap is present, at least in a second region of the aircraft interior component facing an aircraft cabin floor when the aircraft interior component is mounted in an aircraft, between a rear side of the aircraft interior component and an aircraft component opposite the rear side of the aircraft interior component. | 11-28-2013 |
20140084110 | Wing Root Insert System for an Aircraft Family - A single, common, fuselage and wing design of an aircraft structure provides for two different aircraft models or configurations. A fuselage ( | 03-27-2014 |
20140091179 | ARRANGEMENT FOR FASTENING AIRCRAFT INTERIOR-TRIM COMPONENTS - A fastening arrangement for fastening an aircraft interior-trim component to an aircraft structural element, including a pin, including a first coupling element having a bearing-contact face portion, wherein the first bearing-contact face thereof has an engagement projection provided to engage with an opening in the surface of the aircraft interior-trim component. An engagement surface of the bearing-contact face portion includes an engagement element arrangement and includes a spacer fixable relative to the aircraft structural element. An engagement face is provided with an engagement element arrangement and includes a through-bore. When the engagement surface of the coupling element is in bearing contact with an engagement face of the spacer, the coupling element and the spacer cannot be displaced with respect to each other in the plane of the engagement surface, and engagement of the engagement elements arrangement is possible in relative positions of the engagement surface and the engagement face. | 04-03-2014 |
20140131518 | JOINT FOR COMPOSITE WINGS - A wing joint including a T-chord and a splice plate for connecting an inboard wing panel assembly and an outboard wing panel assembly. The wing panel assemblies include a stringer co-bonded or co-cured with a wing skin. The webbing and cap of the stringer may be trimmed to expose a noodle and base flange. The noodle and base flange interface with the bottom of the T-chord and the wing skin interfaces with the splice plate. The exposed noodle may be non-flush with the base flange of the trimmed stringer. The bottom of the T-chord may include a groove to accommodate a non-flush noodle so that a gap does not exist between the T-chord and the base flange. Alternatively, shims may be used to compensate for a non-flush noodle or the base flange and web may include sacrificial plies permitting the base flange and web to be trimmed flush with the noodle. | 05-15-2014 |
20140131519 | FASTENING ARRANGEMENT FOR ATTACHING A FLOOR - A fastening arrangement for attaching a floor to a support structure is provided. The arrangement includes across beam, a floor panel deposited on the cross beam, a fork bolt attached to the cross beam via a barrel nut, and a lug bolt rotary connected to the fork bolt for attaching an attachment element to the cross beam. The fork bolt has a head for accommodating an end of the lug bolt. The fork bolt has a foot with a thread to be screwed into a thread of the barrel nut. The floor panel has an opening for accommodating the head of the fork bolt, such that the floor panel is attached to the cross beam by the fork bolt. The head of the fork bolt is rotatable in the opening of the floor panel for screwing the fork bolt into the barrel nut by rotating the lug bolt. | 05-15-2014 |
20140138489 | Aircraft structure arrangement - An aircraft structure arrangement which is in particular suitable to form a part of a secondary structure of an aircraft comprises a first longitudinal profile and a first frame profile. The aircraft structure arrangement further comprises a mounting bracket which is directly attached to both, the first longitudinal profile and the first frame profile. The mounting bracket further is connectable to a component of a primary structure of the aircraft so as to fasten the first longitudinal profile and the first frame profile to the primary structure of the aircraft. | 05-22-2014 |
20140158828 | AIRCRAFT COMPRISING A WING BOX AND A FUSELAGE PROVIDED WITH A CONNECTING DEVICE CONNECTED TO THE WING BOX - An aircraft comprising a wing box and a fuselage provided with a connecting device configured to be connected to the wing box and to transmit thereto stresses undergone by the fuselage during manoeuvres of the aircraft are provided. The connecting device is formed by a keel beam and a keel beam panel connected to the beam via a connecting portion of the beam, that is moreover provided with a main portion extending in a first, generally longitudinal direction and a transfer portion extending in a second direction different from the first direction and configured to be connected to the box. The main, transfer and connecting portions are configured to direct a major part of the stresses received by the beam in the second direction and transmit said major part of the stresses to the box by compression. | 06-12-2014 |
20140166811 | METHOD FOR THE PRODUCTION OF A CONNECTING ELEMENT, CONNECTING ELEMENT, AND AIRCRAFT OR SPACECRAFT - A method for producing a connecting element for at least two components of an aircraft structure. A hollow initial profile is formed comprising a wall following a closed path in the initial profile cross-section. The wall has a first, second and third section. Material is removed from the wall in one region of the initial profile, to obtain one opening in the one region, the opening extending at least partially within the first section. A portion of the second section and a portion of the third section form part of the connecting element and are each formed so as to be adapted to at least partially abut against the structure. The one opening is formed such that material initially forming part of the wall in the first section and remaining after the formation of the opening forms a stabilizing section connecting the portions of the second and third sections. | 06-19-2014 |
20140197278 | AIRPLANE SIDEWALL ATTACHMENT DEVICE - A system for attaching an aircraft wall panel to an airframe member includes a top support bracket having a mating member, a lower support bracket having a mating pin, and an aircraft wall panel having a first stabilizing attachment and a first securing attachment. The first stabilizing and securing attachments are arranged on a rear surface of the aircraft wall panel. The first stabilizing attachment is configured to connect to the mating member of the top support bracket and retain the aircraft wall panel in proximity to the airframe member. The first securing attachment is configured to connect to the mating pin of the lower support bracket to (a) engage the lower support bracket and facilitate horizontal and vertical adjustments of the aircraft wall panel in relation to the airframe member, and (b) lock a position of the first securing attachment relative to the lower support bracket. | 07-17-2014 |
20140203145 | Variation Compensating Assembly - An apparatus comprising an outer sleeve and an inner sleeve. The outer sleeve has a first channel with an inner wall with a first number of substantially planar surfaces. The inner sleeve has a second channel and an outer wall with a second number of substantially planar surfaces. The outer wall is configured to be received within the first channel. At least one of the second number of substantially planar surfaces on the outer wall of the inner sleeve is configured to slide against at least one of the first number of substantially planar surfaces. | 07-24-2014 |
20140263836 | FISH JOINT DEVICE HAVING AN IMPROVED MECHANICAL HOLD - The invention relates to a fish joint device intended to attach securely first and second structural elements of an aircraft to one another, having two fishplates positioned either side of the structural elements, and attached to them by a set of fishplate through fastenings. According to the invention, the fish joint device includes at least one intermediate fish joint plate which is positioned between one of said fishplates and said structural elements which said intermediate plate partly covers, and which is attached to these elements by a set of intermediate plate through fastenings which includes the set of fishplate through fastenings. | 09-18-2014 |
20140326830 | GASKET HAVING A PLIABLE RESLIENT BODY WITH A PERIMETER HAVING CHARACTERISTICS DIFFERENT THAN THE BODY - A single piece gasket is disclosed having a skeletal member, typically metallic, and a pliable body. The pliable body includes a first portion having a first firmness and a second perimeter portion have a firmer consistency. When such a composite body is placed under compression, the perimeter will tend to limit the flow of the softer inner material past the firmer perimeter region or portion of the gasket. In this manner, creep or overrun of the less firm portion material will be reduced. | 11-06-2014 |
20140361121 | LOWER JOINTS BETWEEN OUTBOARD WING BOXES AND CENTER WING SECTIONS OF AIRCRAFT WING ASSEMBLIES - Lower joints of aircraft wing assemblies are disclosed. In some embodiments, a lower joint includes an outboard lower wing panel, a center lower wing panel, a rib, and a lower joint assembly that includes two outboard flanges operatively coupled to the outboard lower wing panel, an inboard flange operatively coupled to the center lower wing panel, and an upper flange operatively coupled to the rib. In some embodiments, a lower joint assembly includes one or more splice plates, an upper T-fitting, and one or more intermediate plates. In some embodiments, the outboard lower wing panel, the center lower wing panel, and the lower joint assembly are constructed substantially of different materials. | 12-11-2014 |
20150014484 | APPARATUS AND METHODS FOR JOINING COMPOSITE STRUCTURES OF AIRCRAFTS - Apparatus and method for joining composite structures of aircrafts are disclosed. An example apparatus disclosed herein includes an inboard composite wing panel having a first end portion configured to be coupled to upper and lower inboard fittings composed of a metallic material and an outboard composite wing panel having a first end portion configured to be coupled to upper and lower outboard fittings composed of a metallic material. A side of body rib has a plate shaped first end portion composed of a metallic material. A fuselage frame is configured to be joined at one end of the upper inboard fitting, and the upper and lower inboard fittings and the upper and lower outboard fittings are coupled to the side of body rib at the plate shaped first end portion. | 01-15-2015 |
20150048209 | Structures with Internal Microstructures to Provide Multifunctional Capabilities - A structural spacecraft component comprising internal microstructure; wherein said microstructure comprises a plurality of parallel layers and a plurality of spacers that connect adjacent parallel layers; wherein said structural spacecraft component is a product of an additive manufacturing process. | 02-19-2015 |
20150053819 | FUSELAGE INDEXING SYSTEM AND METHOD - A system is disclosed including at least one indexing stub secured to a fuselage in the place of one or more wing stubs and including indexing members protruding from opposite sides of the fuselage. A pair of receivers are mounted to a container and define channels to receive the indexing members. The channels may include an upper flared portion and a lower straight portion. The indexing members are lowered into the channels and the flared portions guide the indexing members into the straight portions. In some embodiments, a pair of clamping members are configured to selectively lock the indexing members within the channels. The indexing members may have a cylindrical shape and may be rotatably mounted to the at least one indexing stub. | 02-26-2015 |
20150102169 | JOINT ASSEMBLY AND METHOD OF ASSEMBLING SAME - A joint assembly for an aircraft is provided. The joint assembly includes a single main fitting including a first flange, a second flange, and a third flange, an external spar component coupled to the first flange using at least one fastener, an internal spar component coupled to the second flange using at least one fastener, and a body rib coupled to the third flange using at least one fastener. | 04-16-2015 |
20150102170 | SELF-ALIGNING FITTING ASSEMBLIES AND SYSTEMS AND METHODS INCLUDING THE SAME - Self-aligning fitting assemblies and systems and methods including the same are disclosed herein. The self-aligning fitting assemblies include a barrel-side fitting that includes a plurality of barrel-side attachment holes and a floor-side fitting that includes a plurality of floor-side attachment holes. The self-aligning fitting assemblies also include an alignment pin recess and a fitting alignment recess. | 04-16-2015 |
20150322979 | FASTENER DEVICE FOR FASTENING A PANEL TO A STRUCTURE, AND AN AIRCRAFT - A fastener device provided with at least one movable stud and a stationary stud, the movable stud including first magnetization means that co-operate with second magnetization means of the stationary stud. At least one magnetization means is carried by a ball joint, each magnetization means being carried by movement means that cause the magnetization means to move in translation along a longitudinal axis from an engagement position to a disengagement position in reversible manner, the magnetization means being strongly magnetically attracted to each other when they are facing and each in the engagement position and being magnetically attracted only slightly or not at all when at least one magnetization means is in the disengagement position. | 11-12-2015 |
20150322980 | FASTENER DEVICE FOR FASTENING A PANEL TO A STRUCTURE, AND AN AIRCRAFT - A fastener device provided with at least one movable stud and a stationary stud, the movable stud including first magnetization means co-operating with second magnetization means of the stationary stud. One magnetization means is carried by a ball joint, each magnetization means being carried by movement means in order to move the first magnetization means in translation in a plane and to move the second magnetization means in translation along a longitudinal axis that is substantially orthogonal to the plane from an engagement position to a disengagement position in reversible manner, the magnetization means being strongly magnetically attracted to each other when they are facing and each in the engagement position and being magnetically attracted only slightly or not at all when at least one magnetization means is in the disengagement position. | 11-12-2015 |
20150322988 | THIN GEL GASKET AND A METHOD OF MAKING AND USING THE SAME - A thin, cured gel gasket is disclosed, including methods of making the thin gel gasket and the use of the thin gel gasket in an aircraft joint. In one embodiment, the thin gel gasket has no skeleton or other structure and is comprised of only a cured polyurethane gel and has a thickness of less than about 12 mill. It is manufactured using a release film that is adapted in a number of ways to make release from the gel prior to use easier. In one method of making and using the thin gel gasket. it is applied to a joint which is subject to compression, in one embodiment, a lap joint of an aircraft fuselage. | 11-12-2015 |
20150329192 | Joining Structure for Interior Panel for Aircraft - A joining structure for an interior panel for an aircraft includes two interior panels, each provided with a corner portion formed on an internal-side surface plate by an edge of an end portion of an external-side surface plate and an edge of an end portion of an internal-side surface plate being attached, the corner portion extending in the direction the edges extend. Strip-shaped connection pieces are provided at the corner portion and are formed across an entire length of the corner portion by a portion, with gaps between the strip-shaped connection pieces . The two interior panels are joined when brought together, with the connection pieces of the two interior panels passing through the gaps between the connection pieces of the other interior panels and being adhered to the external-side surface plate of the other interior panels by an adhesive. | 11-19-2015 |
20150329193 | BENDING-SUSTAINING JOINT AND AIRCRAFT - The present invention relates to a bending-sustaining joint and an aircraft including the same. The bending-sustaining joint includes a body for attaching to a support structure, the body having a first end with a first bore including an internal thread portion and a non-threaded portion; a sleeve including a fitting portion which can be fit into the non-threaded portion of the first bore, a bearing portion for bearing a born member and a through hole; and a bolt member including a thread section and a bolt head which can abut an end face of the sleeve, the thread section of the bolt member being capable of passing through the through hole of the sleeve and being screwed into the internal thread portion of the first bore so as to secure the sleeve to the body. | 11-19-2015 |
20150344124 | MODULAR REPLACEABLE SLIP JOINT INTERCOSTAL - Systems, methods, and apparatus for a modular replaceable slip joint intercostal are disclosed. In one or more embodiments, an intercostal apparatus for a vehicle comprises a body, where the body is greater in length than in width. In at least one embodiment, the intercostal apparatus further comprises at least one slip joint opening located proximate an end of the body to slidably receive a bushing and a fastener, where the bushing rigidly attaches to a top surface of a seat track by the fastener. | 12-03-2015 |
20150360764 | Structual Assembly Joint - A structural assembly joint including a panel comprising a core sandwiched between a pair of planar sheets. A portion of the core is absent at an edge of the panel to define a space between the sheets at the panel edge. A lug projects from a structural component to be joined to the panel. The lug is received in the space between the sheets and secured in place between the or each sheet. The lug is formed integrally with the structural component. Also provided is a method of manufacturing such a structural assembly joint. | 12-17-2015 |
20150369271 | Fastener - A fastener comprising a shaft having a first end and a second end, the fastener comprising a head at a first end of the shaft, the shaft defining either a radially extending recess between the first and second ends and/or a head with regions having different radii of curvature. | 12-24-2015 |
20160018000 | POLYUREA PERIMETER SEAL FOR AN AIRCRAFT ANTENNA OR OTHER AIRCRAFT PART - A sealant is provided for use on an aircraft or other vehicle. The sealant may be used with a gasket. The sealant is a perimeter seal that comprises a polyurea member. The polyurea member is a self-curing, two-component mix. It may cure to a hardness in the range of about 40 to 100 (Shore A). It may maintain an adequate peel strength to withstand multiple thermal and pressure cycling, and may have a working life, wherein it may be shaped, of less than about eleven minutes. | 01-21-2016 |
20160023745 | SEALING ASSEMBLY ON THE EXTERIOR OF AN AIRCRAFT - A sealing assembly on an aircraft exterior having several sealing elements, lying one behind the other in the flight direction. The contact surfaces of the sealing elements sit on a bearing surface. The sealing elements are attached to seal retainer elements. The rear end of each sealing element lies immediately adjacent to the front end of the subsequent sealing element located further back on the aircraft. Adjacent sealing elements form a stepless contact surface and an essentially continuous top surface, interrupted only by the gaps between them. The front end of each rearward sealing element is mechanically coupled to the rear end of the adjacent forward sealing element in such a way that the gap lying between them is bridged. The front end of the sealing element located further to the rear is prevented from lifting relative to the rear end of the forward sealing element. | 01-28-2016 |
20160033043 | POLYUREA GASKET AND GASKET TAPE AND A METHOD OF MAKING AND USING THE SAME - A gasket or tape material for sealing between two members. The gasket or tape material, in one embodiment, includes a skeletal member and/or metallic and/or non-metallic particles. Enclosing the skeletal member and/or particles is a flexible, compressible resilient polyurea body member having a tacky outer surface, the tacky outer surface for engagement between the two members. The resilient body may be comprised of polyurea. The skeletal member may be comprised of a metallic or a non-metallic material, woven or non-woven metallic or non-metallic. | 02-04-2016 |
20160046362 | PINNED LUG JOINT - A pinned lug joint including: a first part with two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part including a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft. | 02-18-2016 |
20160121561 | COMPOSITE CONNECTING ROD, METHOD FOR MANUFACTURING SUCH A ROD AND AERONAUTIC CEILING OR FLOOR STRUCTURE INCORPORATING SAME - The present invention relates to a composite connecting rod, an aeronautic ceiling or floor structure incorporating it, and a method for manufacturing this connecting rod. The invention applies to reacting primarily axial forces, in particular in the aeronautics field. | 05-05-2016 |
20160131259 | ELASTOMERIC GEL BODY GASKET HAVING A SUBSTANTIALLY INCOMPRESSIBLE SKELETON, A METHOD OF MAKING AND USING THE SAME - Gaskets, including aircraft gaskets, are disclosed, the gaskets having an elastomeric gel body and substantially incompressible skeletons. The bodies may be pliable and deformable and, in one example, may be comprised of a two-part chemically cured polyurethane that sets up as a gel after mixing with the web so that it is fully integral with the web and so that there is substantially no air bubbles or air pockets left in the web. The web may be a regular shaped web and made of nylon. | 05-12-2016 |
20160152317 | Splice Assembly For Joining Structural Components | 06-02-2016 |
20160190675 | UNIVERSAL ADAPTER PLATE ASSEMBLY - An improved universal zero-moment support and adapter plate assembly is shown and described. In one embodiment, the assembly comprises an adjustable zero-moment support configured together with an off-axis adjustment. In other embodiments, an adapter and support assembly includes an external fitting, an adapter plate and an adjustable zero-moment support. | 06-30-2016 |
20160195378 | METHOD AND DEVICE FOR CONNECTING AND SEPARATING TWO ELEMENTS, WITH CONNECTING PLATES | 07-07-2016 |
20170234479 | Load Relief Tie Rod | 08-17-2017 |
20190144097 | ENERGY DISPERSION PLUG FOR UAV | 05-16-2019 |