Patent application number | Description | Published |
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 |
20090283509 | METHOD FOR PRODUCING LARGE-SIZED SHELL SEGMENTS AS WELL AS SHELL SEGMENT - The invention relates to a method for producing shell segments with a particularly large length extend for forming a fuselage cell of an aircraft, comprising the following steps:
| 11-19-2009 |
20090294018 | Method for joining aircraft fuselage elements by friction stir welding (FSW) - The invention relates to a method for joining at least two aircraft fuselage segments ( | 12-03-2009 |
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 |
20110011976 | CONNECTION OF CABIN COMPONENTS, CABIN COMPONENT AND METHOD FOR CONNECTING CABIN COMPONENTS - A connection device for a plurality of cabin components of an aircraft includes a rail extending in a longitudinal direction of an aircraft structure, wherein the plurality of cabin components is disposed on the rail; and a plurality of adjustment devices configured to self-adjust each of the plurality of cabin components in the longitudinal direction. | 01-20-2011 |
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 |
20110266392 | PASSENGER SUPPLY ARRANGEMENT FOR AN AEROPLANE - A passenger supply arrangement provides a communications system and comfort system for a passenger of an aeroplane. The passenger supply arrangement includes a presentation surface configured to be integrated into a backrest of a passenger seat of an aeroplane and a passenger supply module configured to be disposed above the passengers seats of the aeroplane. The passenger supply module includes at least one projector configured to project an image onto the presentation surface. The image includes a monitoring area for playback of video and an operating area for displaying and for actuation of operating elements of the passenger supply module. | 11-03-2011 |
20110303791 | Fuselage Section of an Aircraft and Method for the Production of the Fuselage Section - In accordance with the method, an inside layer of a fuselage section skin made from first fibers is placed on a manufacturing surface, the first fibers being placed in one or more first fiber directions. On the inside layer, a stiffening structure is formed from stiffening fibers, the stiffening fibers being placed in one or more stiffening fiber directions. An outside layer of the fuselage section skin, comprising fourth fibers, is placed on the stiffening structure formed from stiffening fibers, the fourth fibers being placed in one or more fourth fiber directions. The stiffening structure is designed and developed in such a way that the fuselage section does not require an additional stiffening structure, is connected with the fuselage section skin, and comprises the inside layer, the stiffening structure, and the outside layer; in particular, an additional stiffening structure in the form of stringers and frames is not required. | 12-15-2011 |
20120012698 | AIRCRAFT COMPRISING AN INSULATION SYSTEM FOR THERMAL AND ACOUSTIC INSULATION - The invention relates to an aircraft comprising an insulation system for thermal and acoustic insulation. Said insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin. | 01-19-2012 |
20120187245 | FUSELAGE SEGMENT, AND METHOD FOR THE PRODUCTION OF A FUSELAGE SEGMENT - A fuselage segment of an aircraft fuselage is provided with an outer skin and an inner skin that are spaced apart from one another by a core, wherein conduits for system installations are integrated into the core, as well as a method for manufacturing such a fuselage segment. | 07-26-2012 |
20120187248 | METHOD AND DEVICE FOR THE INSTALLATION OF SYSTEMS, AND A FREIGHT LOADING SYSTEM - Disclosed is a method for the installation of systems in an aeroplane fuselage | 07-26-2012 |
20120213955 | METHOD FOR MANUFACTURING A SHELL BODY AND CORRESPONDING BODY - In a method for manufacturing a shell, at least two shell sections are fabricated out of a composite fiber material, at least one compensation body of a plastically deformable material is secured to at least one limiting edge of at least one shell section, the shell sections are overlapped to form the shell, yielding flat seams between respectively adjacent shell sections. The at least one compensation body is arranged on at least one of the seams. In order to compensate for dimensional deviations in each overlap, the shape of the corresponding compensation bodies is changed, and the shells sections are joined together at the seams. | 08-23-2012 |
20120328820 | METHOD AND DEVICE FOR JOINING ADHERENDS, AS WELL AS COMPONENT - Disclosed are methods for firmly joining fiber-reinforced, plastic-based adherends, wherein depressions are introduced into opposing lateral surfaces of the adherends, and have injected into them a fiber-reinforced plastic material that serves as an adhesive, a device for implementing such a method, as well as a component joined in this way. | 12-27-2012 |
20120328837 | METHOD AND DEVICE FOR BONDING PARTS TO BE JOINED, AS WELL AS COMPONENT - A method is provided for producing a bonded joint between fiber-reinforced thermoplastic parts to be joined, in which fiber-containing plastic material is mixed into the joining zone while friction stir welding the parts to be joined in the form of a butt joint. A device for carrying out such a method for a joined component is also provided. | 12-27-2012 |
20130099056 | FUSELAGE CELL FOR AN AIRCRAFT, PARTICULARLY AN AIRPLANE - A fuselage cell for an aircraft includes at least two shell segments forming a fuselage cell. The shell segments are provided with a plurality of longitudinal and/or circumferential reinforcements that are integral with a skin panel of the respective shell segment. The reinforcements at least sectionally form a closed cross-sectional geometry together with at least the skin panel of the corresponding shell segment in order to create at least one hollow space, wherein at least one system component at least sectionally extends and/or at least one system medium is at least sectionally routed in the at least one hollow space. The reinforcements also fulfill the function of accommodating at least part of the system components and system mediums of the technical equipment of the aircraft. This results in weight savings and a simplified installation because the number of required mountings and connectors for the system components is reduced. | 04-25-2013 |
20130115404 | LIGHTWEIGHT STRUCTURE, PARTICULARLY PRIMARY AIRCRAFT STRUCTURE OR SUBASSEMBLY, AS WELL AS METHOD FOR THE MANUFACTURE THEREOF - A lightweight structure at least sectionally composed of a plurality of connected mosaic elements and/or skin mosaic elements. The lightweight structure allows an essentially load-appropriate arrangement of the mosaic elements and/or the skin mosaic elements including the optional skin. The lightweight structure requires a significantly reduced number of connecting elements, such that the assembly effort can be reduced and an additional weight reduction can be achieved. Also, two variations of a method for manufacturing a lightweight structure are provided. Large-format lightweight structures such as, for example, an aircraft fuselage cell or partial shells thereof can also be manufactured in a reliable and dimensionally accurate fashion because only mosaic elements and skin mosaic elements, with relatively small dimensions, need to be handled. Other applications of the lightweight structure include launch vehicles, rocket stages, space stations, space station modules, satellites and masts or towers of wind power plants. | 05-09-2013 |
20130216850 | STRUCTURAL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT - A structural component for an aircraft or spacecraft having an outer skin, comprising at least one former element for reinforcing the outer skin. The former element is arcuately curved in accordance with an inner contour of the outer skin | 08-22-2013 |
20130256457 | FUSELAGE SEGMENT AND METHOD FOR MANUFACTURING A FUSELAGE SEGMENT - The invention pertains to a fuselage segment ( | 10-03-2013 |
20130298357 | Fastening arrangement for fastening a component of an aircraft of spacecraft, adhesive retainer of a fastening arrangement of this type and aircraft or spacecraft having a fastening arrangement of this type and/or adhesive retainer of this type - A fastening arrangement for fastening a component, in particular a supply line, of an aircraft or spacecraft. The fastening arrangement includes a structural element of the aircraft or spacecraft; an adhesive retainer, which comprises a flexible connection portion having an adhesive surface for placing onto the structural element and a retaining portion, operatively connected to the connection portion, for receiving the component, at least in portions; and an adhesive material, which is arranged between the adhesive surface and the structural element. Also provided is an adhesive retainer of a fastening arrangement of this type, and an aircraft or spacecraft having a fastening arrangement of this type and/or an adhesive retainer of this type. | 11-14-2013 |
20140013578 | Fastening device and method for producing a fastening device - A fastening device which is suitable, in particular, for use in aircraft construction includes a carrier which is composed of a rollable or foldable material and has a first surface, intended for abutting against a component to be connected to the fastening device, and a second surface opposite the first surface. A plurality of openings are formed in the carrier and pass through the carrier. The fastening device also includes a plurality of heads, each provided with an internal thread, which are connected to the carrier or formed integrally with the carrier and which extend in such a manner from the second surface of the carrier that the internal threads of the heads are aligned with the openings passing through the carrier. | 01-16-2014 |
20140134377 | METHOD OF PRODUCING A COMPOSITE SHELL ELEMENT, COMPOSITE SHELL ELEMENT, MEANS OF TRANSPORT AND USE - Systems and methods for fabrication of composite shell elements and to the assembly of large scale structures comprising such composite shell elements are provided. The composite shell elements comprise two regions in which the resin is cured to different levels. As a consequence, the flexibility of the first region is greater than the flexibility of the second region. Since the first region defines a bending line, the composite shell element can be deformed along the bending line during assembly of the large scale structure. Thus, tolerances in fabrication of the composite shell elements may be compensated for in a time-efficient manner without the need for applying a shimming process. | 05-15-2014 |
20140186574 | METHOD FOR PRODUCING AND CONNECTING FIBRE-REINFORCED COMPONENTS AND AIRCRAFT OR SPACECRAFT - A method for producing and connecting fibre-reinforced components, in particular for an aircraft or spacecraft. The method includes the steps of: (a) providing a textile planar structure, of which merely a first sub-region is impregnated with a matrix; (b) heating the textile planar structure which is impregnated in part, in such a way that the matrix provided in the first sub-region of the textile planar structure cures; (c) connecting the textile planar structure in a second sub-region of the textile planar structure, different from the first sub-region, by stitching the second sub-regions; (d) introducing a further matrix at least into the stitched second sub-regions of the textile planar structure; and (e) heating the impregnated textile planar structure in such a way that the further matrix present in the stitched second sub-regions of the textile planar structure cures. The present invention further relates to aircraft or spacecraft production. | 07-03-2014 |
20140291447 | AIRCRAFT FUSELAGE STRUCTURE - Provided is an aircraft fuselage structure having an outer skin, a support structure arrangement comprising a multiplicity of frame elements and a floor structure arrangement having a multiplicity of floor support struts. The aircraft fuselage structure provides a connection between the floor structure arrangement and the support structure arrangement which is as simple and quick to produce as possible, while not significantly increasing the weight or weakening the structure. Either the floor structure arrangement or the support structure arrangement can have at a connection there between a male connector element or a female connector element. The male connector element can have a peg which extends in the engagement direction and which has a circumferential outer surface which is provided with a multiplicity of circumferential projections. The female connector element can have a cavity, the inner surface of which is provided with a multiplicity of circumferential tabs. | 10-02-2014 |
20140304972 | RIVETING DEVICE AND RIVETING METHOD - A riveting device for the riveting of components in an overlap joint, with an upper tool for driving a rivet into a rivet hole passing through the components, and with a lower tool as a dolly, which has a deforming section for purposes of plastically deforming the end of a rivet shaft driven through the rivet hole, wherein the riveting device has a magazine with a feed device for purposes of feeding a rivet into a shot passage of the upper tool, an actuator for purposes of accelerating the rivet introduced into the shot passage of the upper tool in the direction of the components, and an adjustment system for purposes of aligning the shot channel with the rivet hole. Also disclosed is a method for the riveting of components in an overlap joint. | 10-16-2014 |
20140367519 | METHOD OF INSTALLING A FIXTURE - A method of installing a fixture, such as a bracket, in a fuselage structure of an aircraft includes the steps of: providing or generating a three-dimensional digital model of the fixture; arranging a head of an additive manufacturing apparatus in the fuselage structure; and forming the fixture in situ in the fuselage structure with the head of the additive manufacturing apparatus based upon the digital model of the fixture. The fixture is installed in the fuselage structure by bonding or fusing the fixture to the fuselage structure as the fixture is formed. A fixture, such as a bracket, which is generated in situ in a fuselage structure of an aircraft based upon a three-dimensional digital model, wherein the fixture is bonded or fused to the fuselage structure as the fixture is formed. | 12-18-2014 |
20150034764 | AIRCRAFT FUSELAGE STRUCTURE - An aircraft fuselage structure is disclosed having an outer skin, a support structure arrangement with frame elements, and a floor structure arrangement with floor support struts, the floor structure arrangement connected to the support structure arrangement via connection parts. A connection exists between the floor structure arrangement and the support structure arrangement, with a clamping element on the connection part and a locking element on the connection part. The clamping element includes a longitudinal section having a first and a second end. The first end is pivotally attached to the connection part. The second end includes a transverse section, the locking element including at least one locking groove, and the clamping element pivotable between an engagement position in which the transverse section engages the locking groove, and a released position, in which the transverse section is disengaged therefrom. | 02-05-2015 |
20150083860 | Method For The Assembly Of An Aircraft Fuselage And Fuselage Manufacturing Station - A method for the assembly of an aircraft fuselage, to a fuselage manufacturing station and to a construction kit includes providing a pre-assembled cockpit unit, a pre-assembled wing box, a pre-assembled tail unit and a plurality of pre-fabricated fuselage shell segments. Furthermore, the method involves positioning the cockpit unit, the wing box and the tail unit. Moreover, a first front fuselage shell segment is positioned on a front connecting region of the wing box, and a first rear fuselage shell segment is positioned on a rear connecting region of the wing box. The first front fuselage shell segment is joined to a second front fuselage shell segment, and the first rear fuselage shell segment is joined to a second rear fuselage shell segment. As a result of the above, following the assembly of the aircraft fuselage an aircraft fuselage can be provided that already comprises equipment elements or functional elements. | 03-26-2015 |