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AIRCRAFT STRUCTURE

Subclass of:

244 - Aeronautics and astronautics

Patent class list (only not empty are listed)

Deeper subclasses:

Class / Patent application numberDescriptionNumber of patent applications / Date published
244129100 Details 398
244119000 Fuselage and body construction 271
244118500 Passenger or crew accommodation 256
244135000 Fuel supply 114
244134000 Ice prevention 95
244123100 Airfoil construction 84
244118100 Load (e.g., cargo) accommodation 70
244137100 Passenger or cargo loading or discharging 66
244136000 Material discharging and diffusing 19
244117000 Skin cooling 4
20130026292STIFF PANEL FOR AIRCRAFT, COMPRISING STIFFENERS WITH NOTCHED CORES - A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter.01-31-2013
20100025529Rib Post - A rib post (02-04-2010
20130082138VENTILATION SYSTEM, AIR BLOWING AND EXTRACTION CIRCUITS OF SUCH A SYSTEM, AS WELL AS AN AIRCRAFT AVIONICS BAY - A ventilation system for an avionics bay has two strut assemblies for stiffening the floor of the cockpit, each strut assembly being arranged symmetrically regarding to the central plane of the aircraft, and means of distribution of the blowing air in the cabinets of the bay from the strut assemblies. The extraction circuit includes exhaust ducts integrated in the cabinets and couples together by tight inter-cabinets junctions in an overall configuration of maximized compactness.04-04-2013
20100270429EQUIPMENT ELEMENT WITH RETRACTABLE LINE - An equipment element for transportation means, in particular an airplane, includes, but is not limited to a retractable line, the length of which can be set using a retraction mechanism.10-28-2010
20120286090CONNECTION OF A FUSELAGE TO AN AIRCRAFT WING - A wing box rib (11-15-2012
20090134275Metallic aircraft component - The invention relates to metallic aircraft components which can preferably be used for aircraft structures in the fuselage region. A damage-tolerant design is usual for aircraft components in the fuselage region. It is the object of the invention to provide metallic components in which metal sheets are connected to one another by weld seams which have an improved damage tolerance behavior and fatigue crack propagation behavior. In an aircraft component in accordance with the invention, at least two metal sheets are welded to one another as butt joints. The centerline of the join line of the weld seam is predetermined by the outer edge contour of the metal sheets connected to one another. In this connection, it is formed deviant from a continuously straight line shape such that the total length of the weld seam is increased by changes in direction periodically occurring at the edge contours engaging into one another in a complementary manner.05-28-2009
20100264266METAL-COATED FABRICS FOR FIBER-METAL LAMINATES - Disclosed herein are laminates that include a layer containing a metal-coated fabric. The laminate may also include a layer or layers of an organic polymeric matrix composite. In accordance with certain embodiments, the matrix composite includes a thermosetting or thermoplastic resin matrix with parallel-oriented reinforcing fibers embedded therein, interposed between the metal-coated fabric layers.10-21-2010
20090090813Method of Dimensioning and Producing Stiffened Structural Components, Use of Structural Condition Sensors and an Aircraft - The invention concerns a method of dimensioning and producing stiffened structural components (04-09-2009
20090050737Polysilazane coatings - A composition and process for manufacturing a camouflaged aircraft component. The process includes providing an aircraft component; applying an uncured coating onto the aircraft component wherein the uncured coating comprises polysilazane resin, at least one pigment, at least one matting agent, and at least one diluent; allowing the diluent to evaporate; curing the coating to provided a cured coating that comprises cured polysilazane, at least one pigment, and at least one matting agent.02-26-2009
20090261199METHOD FOR PRODUCING CONTOURED COMPOSITE STRUCTURES AND STRUCTURES PRODUCED THEREBY - A method is provided for forming a composite part contoured along its length and having at least one leg. The method includes forming a stack of fiber reinforced, pre-preg plies by laying down individual segments of unidirectional fibers in each ply. Each of the segments is placed in a preselected orientation related to the contour of the part. The leg is formed by bending a portion of the stack over a tool.10-22-2009
20090032640SELF SUPPORTING CELLULAR THERMAL ACOUSTIC INSULATION - In one embodiment, a device includes first and second frame members, and a foam insulation member having first and second ends. At least one of the first and second ends is disposed at an angle greater than 0 degrees relative to a vertical plane. The first and second ends of the foam insulation member extend between the first and second frame members in compression. The foam insulation member is fixedly held in place between the first and second frame members due to a friction fit resulting from the foam insulation member being disposed between the first and second frame members in compression.02-05-2009
20100127122COMPOSITE STRUCTURE COMPRISING A STRINGER WITH A PAD EMBEDDED IN THE RECESS OF A PANEL AND METHOD OF TRANSMITTING FORCES - A composite structure which may form, for example, the skin of an aircraft wing or fuselage comprises a panel (05-27-2010
20110155849RESIN INFUSION APPARATUS AND SYSTEM, LAYUP SYSTEM, AND METHODS OF USING THESE - A resin infusion apparatus and system, layup system comprising the same, and methods of using these are provided. The resin infusion apparatus comprises a hollow cylinder having a plurality of pores perforating an arcuate surface thereof. The interior of the cylinder is provided with one or more flow restrictors that assist in controlling the flow out of the pores of the cylinder. Laminates made of prepregs prepared using the apparatus and/or system may thus be essentially free of voids.06-30-2011
20090283635IMPACT RESISTANT COMPOSITE STRUCTURES - An impact resistant composite sandwich structure includes least one laminate face sheet joined to a stiffening element. The stiffening element includes a plurality of fibers and a resin for binding the fibers. The resin has a strain-to-failure greater than approximately 6%.11-19-2009
20100170985COMPOSITE PANEL STIFFENER - A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer. The risk of causing, during fabrication of the stringer, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the stringer varies may be reduced by means of such arrangements.07-08-2010
20110180663METHOD AND A DEVICE FOR DRAINING A TANK, AND A TANK AND AN AIRCRAFT FITTED WITH SUCH A DEVICE - The present invention relates to a method of draining a tank (07-28-2011
20120132743AIRCRAFT LIFTING SURFACE SKIN - A mult-rib box-shaped aeronautical structure comprising upper and lower skins (05-31-2012
20120286091Composite Aircraft Joint - A method and apparatus comprises a first number of layers of a composite material for a wing, a second number of layers of the composite material for the wing, and a metal layer located between the first number of layers and the second number of layers in the wing. The metal layer has a first thickness at a first area configured to receive a number of fasteners and a second thickness at a second area.11-15-2012
20100308163APPARATUS WITH DAMAGE INDICATION FEATURE - A method of designing and manufacturing apparatus. The method comprises: creating a design space; analysing expected loads acting on the design space to calculate a first load path within the design space; analysing expected loads acting on the design space when the apparatus is in a damaged state to calculate a second load path within the design space; selecting a region of the second load path which falls outside the first load path; and creating a final design which includes: a primary structure falling within the first load path; and a damage indication feature falling within the selected region. The damage indication feature is designed to provide a visual indication when the load transmitted by the damage indication feature exceeds a threshold.12-09-2010
20110315820AIRCRAFT STRUCTURAL ASSEMBLY AND ASSOCIATED ASSEMBLING METHOD - An assembly includes a structural wall and a composite wall extending in the extension of the structural wall and defining a second section positioned facing a first section of the wall. The assembly includes an elongated traction element received in a first passage made in the structural wall, the first passage opening out into the first section and into a cell made in the structural wall. The composite wall defines a second passage opening out into the second section and receiving the elongated element, The assembly includes a locking member added onto the elongated element. The composite wall delimits an access cavity connecting an outer surface of the composite wall to the second passage. The locking member is received into the access cavity.12-29-2011
20120006940METHOD FOR REALIZATION OF AN AIRCRAFT STRUCTURE AND RESULTING STRUCTURE - An aircraft structure includes a skin (01-12-2012
20080277526Aircraft Cooling Duct - An aircraft structure, for example a wing, includes a section of skin, for example a lower wing panel, the panel defining an external (lower) surface that in use is on the exterior of the aircraft and an internal (upper) surface opposite the external surface, and a duct comprising a section of duct for transporting cooling fluid, for example air, between the internal and external surfaces of the panel from a first location in the panel to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the panel. The cooling air cools an electronic hydrostatic actuator (EHA 11-13-2008
20090277993SYSTEMS AND METHODS FOR A PASSIVE, FORCED CONVECTION COOLING SYSTEM - Systems and methods for a passive, forced convection cooling system. A system for passive forced convection cooling includes, an intake port located in an area of high pressure on an air frame. The system further has an exhaust port located in an area of low pressure on an air frame. The areas of high and low pressure refer to areas of comparatively high and low pressure regions of the exterior ambient environment. Further still, an internal cooling duct connecting the intake port with the exhaust port, such that air flows from the intake port through the cooling duct to the exhaust port. Additionally the system contains, at least one heat sink located in proximity of the intake port and orientated inside the cooling duct in order to allow the cool air traveling through the cooling duct to cool the at least one heat sink.11-12-2009
20090101755SYSTEM, METHOD, AND APPARATUS FOR LEADING EDGE STRUCTURES AND DIRECT MANUFACTURING THEREOF - Leading edge structures for high performance aircraft and the direct manufacture thereof are disclosed. Direct manufacturing technology is used to deposit leading edge structures directly from a digital model to form near-net shape products. This technique permits a wider range of materials to be utilized, such as casting alloys capable of the highest temperature usage that are not available in billet or sheet form. Refractory metals or high temperature ceramics also may be used to form the entire lead edge structure, or just a replaceable tip of the leading edge structure.04-23-2009
20110133026EXTENDED PLUG COLD PLATE - Heat exchange systems, devices and methods are provided. A particular heat exchange device includes a housing defining an inlet and an outlet. The heat exchange device also includes at least one ceramic foam member inside the housing. The at least one ceramic foam member defines a plurality of pores. The heat exchange device also includes a plurality of extended plugs that extend from a first side of the housing through the at least one ceramic foam member to a second side of the housing. The first side of the housing is spaced apart from the at least one ceramic foam member by first ends of the plurality of extended plugs.06-09-2011
244126000 Airship skin construction 3
20090032643ENVIRONMENTALLY STABLE HYBRID FABRIC SYSTEM FOR EXTERIOR PROTECTION OF AN AIRCRAFT - A method of forming an exterior surface protective structure (02-05-2009
20130126675DURABLE AIRSHIP HULL AND IN SITU AIRSHIP HULL REPAIR - A system for airship hull reinforcement and in-situ repair includes a sensor for detecting a leak in the airship hull of a lighter-than-air airship and a repair mechanism inside lighter-than-air airship for dispensing repair material to seal the leak. A durable airship hull includes an inner gas barrier, an outer gas barrier, and a microlattice layer sandwiched between the inner gas barrier and the outer gas barrier.05-23-2013
20090039199ENVIRONMENTALLY STABLE HYBRID FABRIC SYSTEM FOR EXTERIOR PROTECTION OF AN AIRCRAFT - A method of forming an exterior surface protective structure (02-12-2009
244127000 Airship load attachment 2
20120085864WIND TURBINE GENERATOR INSTALLATION BY AIRSHIP - The invention relates to a method for positioning an airship 04-12-2012
20120091274WIND TURBINE GENERATOR INSTALLATION BY AIRSHIP - The invention relates to a method for handling at least one wind turbine generator component 04-19-2012
244128000 Airship gas cell construction and arrangement 1
20100025534Envelope For Lighter-Than-Air Aircraft - An envelope is disclosed for holding gas in a lighter-than-air aircraft. The envelope includes a shell having a leading edge, a trailing edge, an upper surface and a lower surface. The upper surface and the lower surface each extend between the leading edge and the trailing edge. The shell has an airfoil-shaped cross-section having a reflex camber quality.02-04-2010
Entries
DocumentTitleDate
20130026292STIFF PANEL FOR AIRCRAFT, COMPRISING STIFFENERS WITH NOTCHED CORES - A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter.01-31-2013
20100025529Rib Post - A rib post (02-04-2010
20130082138VENTILATION SYSTEM, AIR BLOWING AND EXTRACTION CIRCUITS OF SUCH A SYSTEM, AS WELL AS AN AIRCRAFT AVIONICS BAY - A ventilation system for an avionics bay has two strut assemblies for stiffening the floor of the cockpit, each strut assembly being arranged symmetrically regarding to the central plane of the aircraft, and means of distribution of the blowing air in the cabinets of the bay from the strut assemblies. The extraction circuit includes exhaust ducts integrated in the cabinets and couples together by tight inter-cabinets junctions in an overall configuration of maximized compactness.04-04-2013
20100270429EQUIPMENT ELEMENT WITH RETRACTABLE LINE - An equipment element for transportation means, in particular an airplane, includes, but is not limited to a retractable line, the length of which can be set using a retraction mechanism.10-28-2010
20120286090CONNECTION OF A FUSELAGE TO AN AIRCRAFT WING - A wing box rib (11-15-2012
20090134275Metallic aircraft component - The invention relates to metallic aircraft components which can preferably be used for aircraft structures in the fuselage region. A damage-tolerant design is usual for aircraft components in the fuselage region. It is the object of the invention to provide metallic components in which metal sheets are connected to one another by weld seams which have an improved damage tolerance behavior and fatigue crack propagation behavior. In an aircraft component in accordance with the invention, at least two metal sheets are welded to one another as butt joints. The centerline of the join line of the weld seam is predetermined by the outer edge contour of the metal sheets connected to one another. In this connection, it is formed deviant from a continuously straight line shape such that the total length of the weld seam is increased by changes in direction periodically occurring at the edge contours engaging into one another in a complementary manner.05-28-2009
20100264266METAL-COATED FABRICS FOR FIBER-METAL LAMINATES - Disclosed herein are laminates that include a layer containing a metal-coated fabric. The laminate may also include a layer or layers of an organic polymeric matrix composite. In accordance with certain embodiments, the matrix composite includes a thermosetting or thermoplastic resin matrix with parallel-oriented reinforcing fibers embedded therein, interposed between the metal-coated fabric layers.10-21-2010
20090090813Method of Dimensioning and Producing Stiffened Structural Components, Use of Structural Condition Sensors and an Aircraft - The invention concerns a method of dimensioning and producing stiffened structural components (04-09-2009
20090050737Polysilazane coatings - A composition and process for manufacturing a camouflaged aircraft component. The process includes providing an aircraft component; applying an uncured coating onto the aircraft component wherein the uncured coating comprises polysilazane resin, at least one pigment, at least one matting agent, and at least one diluent; allowing the diluent to evaporate; curing the coating to provided a cured coating that comprises cured polysilazane, at least one pigment, and at least one matting agent.02-26-2009
20090261199METHOD FOR PRODUCING CONTOURED COMPOSITE STRUCTURES AND STRUCTURES PRODUCED THEREBY - A method is provided for forming a composite part contoured along its length and having at least one leg. The method includes forming a stack of fiber reinforced, pre-preg plies by laying down individual segments of unidirectional fibers in each ply. Each of the segments is placed in a preselected orientation related to the contour of the part. The leg is formed by bending a portion of the stack over a tool.10-22-2009
20090032640SELF SUPPORTING CELLULAR THERMAL ACOUSTIC INSULATION - In one embodiment, a device includes first and second frame members, and a foam insulation member having first and second ends. At least one of the first and second ends is disposed at an angle greater than 0 degrees relative to a vertical plane. The first and second ends of the foam insulation member extend between the first and second frame members in compression. The foam insulation member is fixedly held in place between the first and second frame members due to a friction fit resulting from the foam insulation member being disposed between the first and second frame members in compression.02-05-2009
20100127122COMPOSITE STRUCTURE COMPRISING A STRINGER WITH A PAD EMBEDDED IN THE RECESS OF A PANEL AND METHOD OF TRANSMITTING FORCES - A composite structure which may form, for example, the skin of an aircraft wing or fuselage comprises a panel (05-27-2010
20110155849RESIN INFUSION APPARATUS AND SYSTEM, LAYUP SYSTEM, AND METHODS OF USING THESE - A resin infusion apparatus and system, layup system comprising the same, and methods of using these are provided. The resin infusion apparatus comprises a hollow cylinder having a plurality of pores perforating an arcuate surface thereof. The interior of the cylinder is provided with one or more flow restrictors that assist in controlling the flow out of the pores of the cylinder. Laminates made of prepregs prepared using the apparatus and/or system may thus be essentially free of voids.06-30-2011
20090283635IMPACT RESISTANT COMPOSITE STRUCTURES - An impact resistant composite sandwich structure includes least one laminate face sheet joined to a stiffening element. The stiffening element includes a plurality of fibers and a resin for binding the fibers. The resin has a strain-to-failure greater than approximately 6%.11-19-2009
20100170985COMPOSITE PANEL STIFFENER - A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer. The risk of causing, during fabrication of the stringer, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the stringer varies may be reduced by means of such arrangements.07-08-2010
20110180663METHOD AND A DEVICE FOR DRAINING A TANK, AND A TANK AND AN AIRCRAFT FITTED WITH SUCH A DEVICE - The present invention relates to a method of draining a tank (07-28-2011
20120132743AIRCRAFT LIFTING SURFACE SKIN - A mult-rib box-shaped aeronautical structure comprising upper and lower skins (05-31-2012
20120286091Composite Aircraft Joint - A method and apparatus comprises a first number of layers of a composite material for a wing, a second number of layers of the composite material for the wing, and a metal layer located between the first number of layers and the second number of layers in the wing. The metal layer has a first thickness at a first area configured to receive a number of fasteners and a second thickness at a second area.11-15-2012
20100308163APPARATUS WITH DAMAGE INDICATION FEATURE - A method of designing and manufacturing apparatus. The method comprises: creating a design space; analysing expected loads acting on the design space to calculate a first load path within the design space; analysing expected loads acting on the design space when the apparatus is in a damaged state to calculate a second load path within the design space; selecting a region of the second load path which falls outside the first load path; and creating a final design which includes: a primary structure falling within the first load path; and a damage indication feature falling within the selected region. The damage indication feature is designed to provide a visual indication when the load transmitted by the damage indication feature exceeds a threshold.12-09-2010
20110315820AIRCRAFT STRUCTURAL ASSEMBLY AND ASSOCIATED ASSEMBLING METHOD - An assembly includes a structural wall and a composite wall extending in the extension of the structural wall and defining a second section positioned facing a first section of the wall. The assembly includes an elongated traction element received in a first passage made in the structural wall, the first passage opening out into the first section and into a cell made in the structural wall. The composite wall defines a second passage opening out into the second section and receiving the elongated element, The assembly includes a locking member added onto the elongated element. The composite wall delimits an access cavity connecting an outer surface of the composite wall to the second passage. The locking member is received into the access cavity.12-29-2011
20120006940METHOD FOR REALIZATION OF AN AIRCRAFT STRUCTURE AND RESULTING STRUCTURE - An aircraft structure includes a skin (01-12-2012
20080277526Aircraft Cooling Duct - An aircraft structure, for example a wing, includes a section of skin, for example a lower wing panel, the panel defining an external (lower) surface that in use is on the exterior of the aircraft and an internal (upper) surface opposite the external surface, and a duct comprising a section of duct for transporting cooling fluid, for example air, between the internal and external surfaces of the panel from a first location in the panel to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the panel. The cooling air cools an electronic hydrostatic actuator (EHA 11-13-2008
20090277993SYSTEMS AND METHODS FOR A PASSIVE, FORCED CONVECTION COOLING SYSTEM - Systems and methods for a passive, forced convection cooling system. A system for passive forced convection cooling includes, an intake port located in an area of high pressure on an air frame. The system further has an exhaust port located in an area of low pressure on an air frame. The areas of high and low pressure refer to areas of comparatively high and low pressure regions of the exterior ambient environment. Further still, an internal cooling duct connecting the intake port with the exhaust port, such that air flows from the intake port through the cooling duct to the exhaust port. Additionally the system contains, at least one heat sink located in proximity of the intake port and orientated inside the cooling duct in order to allow the cool air traveling through the cooling duct to cool the at least one heat sink.11-12-2009
20090101755SYSTEM, METHOD, AND APPARATUS FOR LEADING EDGE STRUCTURES AND DIRECT MANUFACTURING THEREOF - Leading edge structures for high performance aircraft and the direct manufacture thereof are disclosed. Direct manufacturing technology is used to deposit leading edge structures directly from a digital model to form near-net shape products. This technique permits a wider range of materials to be utilized, such as casting alloys capable of the highest temperature usage that are not available in billet or sheet form. Refractory metals or high temperature ceramics also may be used to form the entire lead edge structure, or just a replaceable tip of the leading edge structure.04-23-2009
20110133026EXTENDED PLUG COLD PLATE - Heat exchange systems, devices and methods are provided. A particular heat exchange device includes a housing defining an inlet and an outlet. The heat exchange device also includes at least one ceramic foam member inside the housing. The at least one ceramic foam member defines a plurality of pores. The heat exchange device also includes a plurality of extended plugs that extend from a first side of the housing through the at least one ceramic foam member to a second side of the housing. The first side of the housing is spaced apart from the at least one ceramic foam member by first ends of the plurality of extended plugs.06-09-2011

Patent applications in class AIRCRAFT STRUCTURE

Patent applications in all subclasses AIRCRAFT STRUCTURE