Patent application number | Description | Published |
20090308976 | Cover panel for an aircraft, more particularly a landing gear cover panel for a cargo plane - The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap | 12-17-2009 |
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 |
20100038486 | LOAD INTRODUCTION STRUCTURE, IN PARTICULAR A LINING FRAME, FOR AN AIRCRAFT - The invention relates to a load introduction structure for an aircraft, comprising two lateral frames which are arranged opposite one another in the two lateral regions of a fuselage airframe structure of the aircraft and adjoin a continuous floor surface which rests on a floor frame. The two lateral frames are connected via the top thereof by a ceiling frame, the ceiling frame being suspended from a ceiling region of the fuselage airframe structure. Each lateral frame is divided into at least two lateral frame segments. At least three track portions which extend parallel to a longitudinal axis of the aircraft are arranged on each lateral frame segment. The lateral frames are connected to the fuselage airframe structure, the ring frames in particular, by a plurality of x-rods, y-rods and y-cardan rods. The load introduction structure is largely uncoupled according to the invention from the fuselage airframe structure of the aircraft inter alia by a plurality of coupling members arranged between the track portions to form gaps in order to compensate for load-induced and/or thermally-induced deformations, in particular changes in length, of the fuselage airframe structure. | 02-18-2010 |
20100040433 | CONNECTING ELEMENT, IN PARTICULAR A SPEED NUT - The invention relates to a connection element, in particular a plate nut, comprising a base body for attachment of an arbitrary component to a metallic planar object, in particular to a sheet metal. | 02-18-2010 |
20100096500 | LINING FOR AN AIRCRAFT - The invention relates to a lining | 04-22-2010 |
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 |
20100294884 | ATTACHMENT ARRANGEMENT FOR A CARGO COMPARTMENT FLOOR OF AN AIRCRAFT AND AIRCRAFT WITH AN ATTACHMENT ARRANGEMENT OF THIS TYPE - The present invention provides an aircraft floor of an aircraft consisting of a number of base plates and a number of longitudinal supports and provides an aircraft with a floor of this type. The aircraft floor has transverse joints for partitioning the floor into a plurality of segments transversely to a longitudinal axis of the aircraft, the respective segment consisting of a number of longitudinal support elements, partitioned by the transverse joints, of the longitudinal supports and of a number of base plate elements partitioned by the transverse joints, of the base plates and the segments being coupled together such that they have exclusively a translatory degree of freedom with respect to one another in the direction of the longitudinal axis of the aircraft. | 11-25-2010 |
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 |
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 |
20120006236 | ADHESIVE HOLDER FOR HOLDING OBJECTS AND KIT, AS WELL AS METHOD FOR MAKING AN ADHESIVE HOLDER - An adhesive holder for holding objects comprises an adhesive layer, an object holder, an adapter with a contact surface and a counter element with a counter surface. The counter surface of the counter element is positionable at a distance from the contact surface of the adapter in order to enclose a section of a structural element. The adhesive layer can be applied onto the contact surface of the adapter or onto the counter surface of the counter element. The adhesive holder according to the invention makes it possible to introduce a force into a structural element by exerting compressive stress and shearing stress only such that the adhesive connection is much more durable and the adhesive holder can be subjected to higher loads than in the state of the art. | 01-12-2012 |
20120137484 | Method for Repairing an Aircraft Structure Component - A method is provided for repairing an aircraft structural component which has a component fault in a portion adjoining a cavity of the aircraft structural component. The method includes removing a region of the aircraft structural component that has the component fault, introducing a bearing element into the cavity of the aircraft structural component through an opening, which has been formed in the aircraft structural component by the removal of the region of the aircraft structural component having the component fault, in such a way that a bearing surface of the bearing element comes to lie against a region, adjacent to the opening, of an inner surface of the aircraft structural component facing the cavity of the aircraft structural component, fixing the bearing element in its position in the cavity of the aircraft structural component, and closing the opening by means of a repair material. | 06-07-2012 |
20120145867 | SEAT ADJUSTMENT DEVICE AND AIRCRAFT OR SPACECRAFT - The present invention provides a seat adjustment device for an aircraft or spacecraft, comprising: | 06-14-2012 |
20120152438 | Method of Repairing an Aircraft Structure Component - A method is provided for repairing an aircraft structural component which has a component fault in a portion adjoining a cavity of the aircraft structural component. The method includes removing a region of the aircraft structural component that has the component fault, introducing an expansion body into the cavity of the aircraft structural component through an opening that has been formed by the removal of the region of the aircraft structural component having the component fault, wherein the expansion body while being introduced into the cavity of the aircraft structural component is in a non-expanded state, converting the expansion body that has been introduced into the cavity of the aircraft structural component to an expanded state, and closing the opening by means of a repair material. | 06-21-2012 |
20130105067 | HOLDING DEVICE FOR AT LEAST ONE FIXTURE TO A CELL STRUCTURE OF AN AIRCRAFT FUSELAGE | 05-02-2013 |
20130125354 | AIRCRAFT ASSEMBLY AND METHOD FOR PRODUCING AN AIRCRAFT ASSEMBLY - An aircraft assembly is provided having a first aircraft component and a second aircraft component, at least one of the aircraft components being composed of a fibre-reinforced composite material, a connecting device connecting the first aircraft component to the second aircraft component, the connecting device including a first and a second section having a carrier element connected to the first and second aircraft components respectively, the first section having a first surface facing the first aircraft component and a second surface facing away from the first aircraft components, the second section having a first surface facing the second aircraft component and a second surface facing away from the second aircraft component. The first and second sections include a plurality of hook and loop elements extending from the second surface of the carrier element and cooperate to produce a hook and loop connection between the first and second aircraft components. | 05-23-2013 |
20130157536 | AIRCRAFT INTERIOR LINING COMPONENT AND METHOD FOR PRODUCING AN AIRCRAFT INTERIOR LINING COMPONENT - An aircraft interior lining component includes a composite material, wherein the composite material includes a matrix, first reinforcing fibres embedded in the matrix and second reinforcing fibres embedded in the matrix. The strength of an interface between a surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fibres is greater than the strength of an interface between a surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres. | 06-20-2013 |
20130228667 | HOLDING DEVICE FOR INTERIOR LINING PARTS OF A FUSELAGE AND SUPPORTING SYSTEM EMPLOYING SUCH HOLDING DEVICES - A holding device for in particular panel-shaped interior lining parts of a fuselage, has a configuration that is easy and simple to mount, each holding device includes a supporting device, which is used to anchor the holding device on a primary structure of the fuselage and comprises a joint; a connecting tube, which extends out of the supporting device and one end of which is attached to the joint; a mounting for an interior lining part, to which mounting the other, opposite end of the connecting tube to the one end is attached; and a lanyard, which is fastened to the supporting device is and the mounting and extends through the connecting tube and the length of which is greater than the length of the connecting tube. | 09-05-2013 |
20130327882 | Connection arrangement, aircraft or spacecraft, method for dropping load and method for landing - A connection arrangement having: a fuselage portion; a wing portion which is mounted on the fuselage portion in an upper region thereof; a first Z-coupling element which couples the wing portion to the fuselage portion in the vertical direction thereof; and two XZ-coupling elements which couple the wing portion to the fuselage portion in the vertical direction and longitudinal direction thereof; the first Z-coupling element being longitudinally adjustable in the vertical direction in order to thus adjust an angle of attack of the wing portion. | 12-12-2013 |
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 |
20140370256 | STRUCTURAL MEMBER AND ASSOCIATED METHOD - The present disclosure relates to a structural member for an aircraft or spacecraft, including a first part having a first material having a first coefficient of thermal expansion and a second part including a second material having a second coefficient of thermal expansion, wherein the first part and the second part are rigidly connected with each other, and wherein the second part is configured to induce forces in the first part upon a drop in temperature to counteract loading stresses. A corresponding method of forming a structural member is also provided. | 12-18-2014 |