| 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 |
