Patent application number | Description | Published |
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 |
20100272954 | Method for Coupling Stiffening Profile Elements and Structural Component - This invention provides a coupling method for coupling a first and a second stiffening profile element for an outer skin of an aircraft or space craft. In a first step the stiffening profile elements are arranged on the outer skin in such a manner that the stiffening profile elements oppose each other with their respective front sides and enclose within themselves a cavity. Furthermore, a fixing hole is formed through a wall of at least one of the stiffening profile elements in the cavity inside a coupling zone of the stiffening profile element. An access opening is formed through the wall in the cavity along the coupling zone. A coupling strap, which couples the stiffening profile elements together, is fastened to the coupling zone by means of a fastening element guided through the fixing hole. | 10-28-2010 |
20100320322 | TRANSVERSE BUTT CONNECTION BETWEEN TWO FUSELAGE SECTIONS - The invention relates to a transverse butt connection ( | 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 |
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 |
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 |
20110236622 | FIBER COMPOSITE COMPONENT FOR ABSORBING ENERGY - In the case of a fiber composite component for energy absorption in the event of a crash for an aircraft or spacecraft, the fiber composite component is formed as a laminate construction made of CFRP layers and at least one integrated metal foil portion which is corrosion-resistant with respect to the CFRP layers. A fuselage structure portion of an aircraft or spacecraft is formed using at least one fiber composite component of this type. An aircraft or spacecraft comprises a fuselage structure portion of this type. | 09-29-2011 |
20110297788 | SHELL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT - The present invention provides a shell component for an aircraft or spacecraft. The shell component comprises a skin panel, a plurality of stringers which are arranged on the skin panel, a former which comprises a fibre composite material and is arranged over the stringers so as to cross said stringers, and a former connection structure which comprises a ductile material and a plurality of foot portions fixed to the skin panel. The foot portions each transition integrally into a shoulder portion fixed to the former over an associated fixing span, the fixing spans associated with the foot portions extending along the former substantially continuously over the stringers. | 12-08-2011 |
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 |