| Entries |
| Document | Title | Date |
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| 20080197235 | Technique for preventing the thermal insulating foam falling off the space shuttle and its external tank (ET) - The invention as disclosed herein is a technique for preventing the thermal insulating foam from peeling off from the space shuttle and its external tank (ET) possessing the following characteristics: a high intensity protective net shield designed for the space shuttle or/and the ET, which is made of the high-temperature and high intensity ropes, is installed as one of the following designs: A. Install the protective net shield directly on the out side of the thermal insulating foam of the space shuttle and its ET by covering the thermal insulating foam while the mesh area of the protective net shield is smaller than the area of the single thermal insulating foam chunk so that it would prevent the thermal insulating foam chunks falling out from the mesh, and fix the mesh knots onto corresponding thermal insulating foam chunks; B. Between joint lines of two adjacent polygon thermal insulating foam chunks of the space shuttle and its ET, respectively bind two thermal insulating foam chunks together with a rope through the meshes, and the binding ropes creates at least one binding loop at each joint line; then connect all binding loops of each joint lines of each corresponding thermal insulating foam chunk into a protective loop by the ropes. Connect each protective loop via each binding loop as mesh knots, and thereby form the protective net shield. This invention is practical and easy to operate, which will effectively prevent the thermal insulating foam from peeling off and resolve the safety problem resulted from the peeling off of the thermal insulating foam from the space shuttle and its ET. | 08-21-2008 |
| 20080210817 | Energy-absorbing Square Tube Composite Stanchion - An energy absorbing structural strut employs a composite tube bonded to an end fitting with the bond being slightly lower in strength than the crushing strength of the tube in axial compression. The end fitting incorporates an anvil to rupture the tube and absorb energy upon shearing of the bond with the strut in compression. | 09-04-2008 |
| 20080217478 | AIRCRAFT FLOOR TO FUSELAGE ATTACHMENT - A floor to fuselage attachment structure incorporates a truss having an upper angled attachment engaging the floor proximate an edge and extending at an angle upward from the floor edge to attach to the fuselage. Additionally, the truss includes a lower angled attachment engaging the floor proximate the edge and extending at an angle downward to attach to the fuselage. The upper and lower angled attachments support the floor with the edge spaced from the fuselage and further have a plurality of apertures for providing airflow between a first volume above the floor and a second volume below the floor. | 09-11-2008 |
| 20080223985 | Splicing Fuselage Sections without Shims - Fuselage sections of an aircraft are joined using splice elements that compensate for gaps caused by mismatches between mating surfaces on the fuselage sections. The fuselage sections are virtually assembled using computer models that are based on non-contact measurements of as-built fuselage sections. The virtually assembled fuselage sections are used to map the gaps between the mating surfaces. The mapped gaps are used to produce tool inserts having profiles that reflect the dimensions of the gaps. The tool inserts are used to manufacture splice elements having profiles that fill the gaps when the fuselage sections are assembled and joined, thereby eliminating the need for shims and spaces to fill the gaps. | 09-18-2008 |
| 20080223986 | Trussed Structure - The invention provides a trussed structure comprising a frame and at least one strut, wherein the frame is of composite material and includes sockets which are integral with the frame. The invention also provides a process of making the trussed structures. The struts are typically of composite material and the trussed structures of the invention are particularly suitable for use in aircraft, for example, as wing ribs or floor beams. | 09-18-2008 |
| 20080258007 | ATTACHING PANELS TO SUPPORT STRUCTURES IN AN AIRCRAFT - Apparatus and methods for attaching wall panels to support structures are disclosed. In one embodiment, an aircraft includes a support structure and a wall assembly coupled to the support structure. The wall assembly includes a first member and a second member. The first member is coupled to the support structure and has a first elongated coupling member. The second member has a head portion and a base portion. The head portion has at least one slot disposed therein that is adapted to receive an edge portion of the panel. The base portion includes a second elongated coupling member that is adapted to be coupled to the first elongated coupling member. | 10-23-2008 |
| 20080265093 | Integrated multispar torsion box of composite material - The invention relates to an integrated multispar torsion box structure of composite material for aircraft, comprising a lower skin ( | 10-30-2008 |
| 20080283664 | Aircraft Fuselage Structure - An aircraft fuselage shell section comprises a skin ( | 11-20-2008 |
| 20080283665 | Aircraft Ventral Fairing Partition Wall and Aircraft Equipped with a Ventral Fairing - The invention concerns a wall ( | 11-20-2008 |
| 20080290214 | SHAPED COMPOSITE STRINGERS AND METHODS OF MAKING - A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg. | 11-27-2008 |
| 20080302912 | Bladderless Mold Line Conformal Hat Stringer - Apparatus and techniques for providing a closed hat stringer are disclosed. In one embodiment, a closed hat stringer for stiffening a composite structure includes opposing cavity walls situated between a first flange and a second flange, the cavity walls, first flange and second flange defining an elongated cavity, the second flange including a continuous exterior surface having a width greater than the first flange and configured for attachment to a skin. | 12-11-2008 |
| 20080302913 | CARGO FLOOR, SYSTEM, AND METHOD - Embodiments provide a cargo floor, a system, and a method adapted to be made integral with or complementary of the aircraft fuselage. Cargo floor members may be adapted to be coupled with a flat fuselage bottom inner skin of an aircraft fuselage to serve as the main orthotropic stiffeners to the flat fuselage bottom inner skin such that a portion of the in service loading experienced by the aircraft are shared by a combination of the fuselage and the cargo floor. | 12-11-2008 |
| 20080308676 | Aircraft Fuselage - The present invention provides an aircraft fuselage which comprises a bulletproof layer in at least partial areas, an aircraft fuselage being understood as both a primary fuselage structure of an aircraft, i.e., sheeting and associated frames and stringers, aircraft fuselage insulation, and also cabin internal paneling, which encloses a pressurized cabin on the outside toward the primary fuselage structure. In this way, it may be possible to ensure bulletproof security of the aircraft fuselage and thus prevent danger to passengers and/or flight-relevant systems of the aircraft. | 12-18-2008 |
| 20090001217 | PRE-FABRICATED ARTICLE FOR EME PROTECTION OF AN AIRCRAFT - A pre-fabricated article for a composite aircraft component includes a dielectric layer and a pre-fabricated metalized pattern on the dielectric layer. The metalized pattern is fabricated on the dielectric layer prior to integration with the composite aircraft component. The metalized pattern diverts EME current away from EME protection areas of the aircraft component. | 01-01-2009 |
| 20090008502 | Aircraft Fuselage Interior - An aircraft fuselage interior comprises a side wall that extends in a direction along the length of the fuselage and includes an upper section that slopes inwardly. In one embodiment, the side wall comprises a multiplicity of visible elongate features, such as sloping lines, arranged along the length of the side wall. Each elongate feature extends from a lower portion to an upper portion and slopes relative to a notional line defined by the intersection of the interior surface of the side wall and a plane whose normal axis is parallel to the length of the fuselage. When viewed by a seated passenger, the sloping elongate features may cause the side wall to appear to have a degree of inward sloping less than the actual degree of inward sloping. The fuselage interior may therefore appear larger than it is. | 01-08-2009 |
| 20090014585 | Light Plane in the Ultralight Category and Sport Plane Category - This light aeroplane at the same time fulfilled the weight limits for the European ultra light class or acolyte class as do at the same time for the US-American sport plan Category. It comprises an engine arranged at the nose and is provided with tractor airscrew and the cabin cell that is arranged behind the engine and is wide enough for two adjacent passenger seats. A central tube ( | 01-15-2009 |
| 20090014586 | Light rail system for powered introduction of large loads in a structure - A device for securing installed equipment in an airplane, with one or more oblong attachment rails, one or more attachment means for securing the attachment rails to an airframe structure, and one or more bracket units that can be attached to or in the attachment rails, wherein the bracket units can be attached to the built-in apparatuses to be secured. | 01-15-2009 |
| 20090020645 | Method for Frabricating an Aircraft Fuselage in Composite Material - A method for manufacturing an aircraft fuselage includes an internal framework surrounded by an external skin made of composite material, in which the internal framework at least partially constitutes a mould for manufacture and/or the support for the mould for the external skin made of composite material. The disclosed embodiments also relate to an aircraft fuselage produced using this method. | 01-22-2009 |
| 20090026315 | Reinforcement beam as well as method and fiber laminate for manufacturing the reinforcement beam - Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight. | 01-29-2009 |
| 20090057487 | COMPOSITE FABRIC WITH RIGID MEMBER STRUCTURE - A composite structure is provided including a first fabric and a second fabric. A substantially elongate and substantially rigid first member is spaced apart from and coupled with the first fabric via the second fabric. A resin substantially is infused into the first fabric and the second fabric, and substantially encapsulates the first member to form a unitary structure. | 03-05-2009 |
| 20090072086 | Aircraft floor and interior panels using edge coated honeycomb - Aircraft floor and interior panels where core-skin bonding is improved between honeycomb and composite face sheets (skins) by applying a polyamide and/or rubber-containing adhesive to the edge of the honeycomb prior to bonding. Edge coating of the honeycomb allows one to reduce panel weight without reducing the performance parameters that are required for different types of aircraft floor and interior panels. | 03-19-2009 |
| 20090078823 | Aircraft nose landing gear enclosure - In one embodiment, an aircraft comprises a plurality of hoop frame support members and a landing gear enclosure comprising a curved surface. The plurality of support frame support members abut against and extend over the curved surface to provide support to the landing gear enclosure. In another embodiment, loads are transferred from a landing gear strut through a strut fitting, through at least one inner surface of the landing gear enclosure, through at least one outer surface of the landing gear enclosure, and into the plurality of hoop frame support members. | 03-26-2009 |
| 20090078824 | Paneled Partition - A paneled partition assembly is designed to close an opening and collapses to uncover the opening by a movement of at least one panel that initiates the rotation and translation of at least one other panel. When the paneled partition assembly is in a closed or extended position, the plurality of panels covers the opening regardless of the opening's shape, size, or irregularity. When the paneled partition assembly is in an open or retracted position, the plurality of panels collapse to a smaller configuration. In moving between the extended and retracted positions, the panels rotate and translate fluidly with minimum user interaction. | 03-26-2009 |
| 20090084898 | METHOD AND APPARATUS FOR HOLDING PARTS DURING MANUFACTURING PROCESSING - A method for processing parts. In one advantageous embodiment, a setoff set of studs are welded to a part to form a set of fixed studs. A set of tabs are attached to the set of fixed studs. The set of tabs are affixed to a manufacturing tool. | 04-02-2009 |
| 20090095840 | PROCESS FOR REPAIRING A DAMAGED AREA OF AN AIRCRAFT FUSELAGE - A process for cutting out a damaged area of an aircraft fuselage, in particular so as to repair the damaged area, includes in making at least one cut-out in the fuselage ( | 04-16-2009 |
| 20090101756 | MONOLITHIC SELF-STIFFENED PANELS - A composite panel having a first skin forming the outer wall of the panel, known as the lower face ( | 04-23-2009 |
| 20090121081 | Composite Bulkhead and Skin Construction - Aircraft fuselage structures have fuselage bulkheads in which the bulkhead outer caps are integrated with the skin, thereby reducing fastener count and weight. These outer caps and skin are preferably co-cured to form a strong structure. The outer caps can be advantageously constructed as continuous hoops of pultruded elements. The outer cap need not be interrupted by contours or cutouts for stringers, saving weight and reducing complexity. It is contemplated that by integrating the bulkhead outer caps into the skin, a bulkhead can still maintain equivalent stiffness and strength, while saving a significant number of rivets as compared to a comparable design without the outer cap. | 05-14-2009 |
| 20090146007 | Methods and Systems for Attaching Aircraft Wings to Fuselages - Methods and systems for attaching aircraft wings to fuselages are disclosed herein. An aircraft configured in accordance with an embodiment of the invention includes a fuselage and a wing. The wing includes a right wing portion extending outwardly from a right side portion of the fuselage and a left wing portion extending outwardly from a left side portion of the fuselage. In this embodiment, the right wing portion is fixedly attached to the left wing portion by a wing center section extending through at least a portion of the fuselage. The aircraft further includes a first pivotable link structurally attaching the wing center section to the right side portion of the fuselage, and a second pivotable link structurally attaching the wing center section to the left side portion of the fuselage. | 06-11-2009 |
| 20090146008 | Door Frame Compartment of Cast Titanium and Structural Fuselage Part - A door frame component of cast titanium for a door opening in an outer skin of an aircraft or space vehicle is provided, the component including a contact surface for bearing against the outer skin, wherein the contact surface is formed to correspond to an inner contour of the outer skin in such a manner that the contact surface essentially fills the contour. From a further viewpoint the invention makes available a structural fuselage part for an aircraft or space vehicle which comprises an outer skin which has a carbon fiber reinforced plastic material together with a door frame component of the type described. | 06-11-2009 |
| 20090159745 | Aircraft stringer clip and related methods - An aircraft stinger clip and related methods are disclosed that provide an apparatus for attaching aircraft elements to an aircraft stringer. In one embodiment, the stringer clip is a three-piece clamp assembly spanning the width of an aircraft stringer and including a single bottom member and two opposing top members that are configured to be engagingly coupled. The top and bottom members of the stringer clip are preferably made of rigid, but light-weight and flame retardant material. | 06-25-2009 |
| 20090159746 | HULL STRUCTURE - The present invention provides a hull structure, for use in particular in an aircraft or spacecraft, the hull structure comprising an outer skin and structural components which are connected to said skin, as well as an inner lining which forms a supporting structure together with the outer skin and the structural components. | 06-25-2009 |
| 20090159747 | Aircraft Fuselage Element - An aircraft fuselage element ( | 06-25-2009 |
| 20090166471 | Fuselage Structure and Method for the Production of a Fuselage Structure - The present invention provides a method for the production of a fuselage structure, and a fuselage structure, in particular of an aircraft or spacecraft, with an inner shell arrangement which has an upper inner shell and a lower inner shell, the upper inner shell being spaced apart at least in some sections from the lower inner shell by a first gap in order to form a window region; and a window band which is arranged at least in the window region and has a pane device which comprises a grid structure which absorbs fuselage forces. | 07-02-2009 |
| 20090184201 | JOINING FUSELAGE SKINS USING FRICTION STIR WELDING - Fuselage skins of aircraft are joined using friction stir welding. A strip of cladding is removed from the skins along an abutment between the skins before the skins are welded in order to prevent the cladding from interfering with the welding process. The cladding is replaced after the welding is completed. | 07-23-2009 |
| 20090236472 | TRUSS NETWORK FOR AIRCRAFT FLOOR ATTACHMENT - A truss network for aircraft floor attachment includes an aircraft fuselage, an aircraft floor disposed in the aircraft fuselage and a three-dimensional truss network comprising at least two truss assemblies each comprising a plurality of tie rod assemblies connecting the aircraft fuselage to the aircraft floor. A method of attaching a floor structure to a honeycomb fuselage structure and an aircraft having a truss network connecting an aircraft fuselage to an aircraft floor are also disclosed. | 09-24-2009 |
| 20090261201 | LINE TRANSFER SYSTEM FOR AIRPLANE - A method is provided for establishing a physical reference inside an airplane representing the airplane's optimized line of flight based on the as-built orientation of aerodynamically significant features of the airplane. Values generated for aerodynamic pitch, roll and yaw representing the optimized line of flight are used to orient a tool reference surface outside the airplane. The orientation of the tool reference surface is recorded using an inertial reference unit placed on the tool reference surface. The tool reference surface and inertial reference unit are moved into the airplane where they are used to establish the physical reference on the airframe. | 10-22-2009 |
| 20090266936 | AIRCRAFT FUSELAGE STRUCTURAL COMPONENTS AND METHODS OF MAKING SAME - Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a friction stir weld region. Such aircraft fuselage structural components may thus be provided with plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers each being positioned within a respective one of the stringer holes of the frame member. The reinforcement members are lap joined to corresponding surfaces of frame members in the vicinity of the stringer holes such that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region. | 10-29-2009 |
| 20090277994 | HYBRID AIRCRAFT FUSELAGE STRUCTURAL COMPONENTS AND METHODS OF MAKING SAME - An aircraft fuselage assembly of basic construction in composite materials employs metallic frames with reduced quantity of metallic shear ties attached to the composite stiffened skin, formed by two or more longitudinal panels, spliced with longitudinal metallic splice members. Typically, the latitudinal metallic frame members are fastened to the inward outstanding flange portion of the composite stringers which are in turn integrated to the skin. As such, the frame members are spaced from (floating over) the fuselage skin. An electrical path may thus be established so as to protect the fuselage structure against the impact of electrical discharges commonly encountered in the atmosphere by providing metallic shear ties interconnecting the frame and splice members so as to span the space therebetween. | 11-12-2009 |
| 20090277995 | SUPPORTING STRUT FOR SUPPORTING AN INTERMEDIATE DECK THAT IS ARRANGED IN AN AIRCRAFT FUSELAGE, AND METHOD FOR PRODUCING A ROD BODY FOR SUCH A SUPPORTING STRUT - A supporting strut for supporting an intermediate deck ( | 11-12-2009 |
| 20090283637 | Aircraft floor and fuselage supplied with said floor - The invention refers to an aircraft floor ( | 11-19-2009 |
| 20090283638 | INTEGRATED AIRCRAFT STRUCTURE IN COMPOSITE MATERIAL - Integrated aircraft structure in composite material that comprises a skin and stringers ( | 11-19-2009 |
| 20090294587 | AIRCRAFT FLOOR, USE OF SAID FLOOR AND AIRCRAFT SECTION FITTED WITH SAID FLOOR - An aircraft floor, and aircraft section provided with such a floor, and the utilization of such a floor in an aircraft section. The aircraft floor generally includes at least one central rail firmly mounted on a rigid structure of the aircraft, at least two lateral rails positioned on both sides of the central rail, and floor panels. Each lateral rail is connected vertically to the structure of the aircraft through a vertical connecting rod, each lateral rail being transversely free. Each floor panel is positioned between two adjacent rails, so that the transverse forces to which the lateral rails are subjected pass through the floor panels to the central rail. | 12-03-2009 |
| 20090308975 | APPARATUS FOR PROVIDING VARIABLE THERMAL INSULATION FOR AN AIRCRAFT - Apparatus is disclosed for providing variable thermal insulation for an aircraft. | 12-17-2009 |
| 20090314890 | COLLAPSIBLE SHAPE MEMORY ALLOY (SMA) NOSE CONES FOR AIR VEHICLES, METHOD OF MANUFACTURE AND USE - A nose cone formed from a shape memory alloy (SMA) having a recoverable strain of at least 2% collapses about the dome for storage, deploys at launch to protect the sensor dome and reduce drag during atmospheric flight and is shed to allow sensing for terminal maneuvers. The SMA is shape-set at elevated temperatures in its Austenite phase with a memorized shape having a radius of curvature greater than that of the sensor dome to reduce aerodynamic drag. The temperature is reduced and the SMA collapsed to conform to the curvature of the sensor dome within the recoverable strain for storage. A first mechanism is configured to return the collapsed SMA to its memorized shape at launch or prior to going supersonic. In one embodiment, the SMA is stored below its Martensite finish temperature in a temperature-induced Martensite phase in which case the mechanism heats the SMA above the Austenite finish temperature to return the material to its memorized shape. In another embodiment, the SMA is stored above its Austenite finish temperature in which case collapsing the SMA places the material in a strain-induced Martensite phase. The mechanism holds the collapsed SMA in place and the releases the stored energy allowing the SMA to return to the memorized shape. | 12-24-2009 |
| 20090314891 | Aircraft Fuselage Structure and Method for its Production - An aircraft fuselage structure is described, which is constructed from a plurality of shells ( | 12-24-2009 |
| 20090321567 | Intercostal for an aircraft or spacecraft - The present invention relates to an intercostals for an aircraft or space craft for diverting a load from a first rib to a second rib and/or a skin of the aircraft and/or space craft, with at least one opening region for guiding through system lines or the like, wherein the intercostal has a traverse that is movable at least between a first and a second position, wherein the traverse in the first position is provided for forming a force flow for diverting a load between the first rib and the second rib, and in the second position reveals the opening region from a predetermined side. | 12-31-2009 |
| 20090321568 | Aircraft Fuselage with Circular-Arc-Shaped Exterior Contour - A fuselage section comprises an interior that forms a passenger cabin. In horizontal projection the fuselage section is geometrically defined by a first exterior skin region and a second exterior skin region, wherein the second exterior skin region faces the first exterior skin region. Both the first exterior skin region and the second exterior skin region in longitudinal direction of the passenger cabin comprise in horizontal projection a circular-arc-shaped contour of uniform radius of curvature. | 12-31-2009 |
| 20090321569 | Aircraft fuselage structure and method for its production - An aircraft fuselage structure with frames ( | 12-31-2009 |
| 20100001134 | AIRPLANE HAVING A FUSELAGE SHELL AND A FLOOR STRUCTURE - An airplane has a fuselage shell and a floor structure that includes cross members and floor plates. Rods are used exclusively to connect the fuselage shell to the floor structure. | 01-07-2010 |
| 20100012781 | Aircraft with retracted front landing gear - An aircraft has a fuselage | 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 |
| 20100038487 | FUSELAGE STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT, WITH A FOAM LAYER AS THERMAL INSULATION - The present invention creates a fuselage structural component of an aircraft or spacecraft, with a non-load-bearing outer skin and a load-bearing inner framework structure, wherein a foam layer which effects heat insulation and/or impact protection is arranged between the outer skin and the inner framework structure. | 02-18-2010 |
| 20100044510 | Floor Structure for a Fuselage - The present invention provides a floor structure for a fuselage comprising a plurality of cross beams to which respectively at least one first strut and at least one second strut are associated for connecting the respective cross beam to the fuselage. The at least one first strut is aligned in a corresponding first direction vector and the at least second strut is aligned corresponding to a second direction vector. The projections of the first direction vector and of the second direction vector onto the longitudinal direction of the fuselage are different for absorbing a force acting in the longitudinal direction of the fuselage on the floor structure, through the first and second struts. | 02-25-2010 |
| 20100059626 | FUSELAGE ARRANGEMENT FOR AIRPLANE - An aircraft fuselage with a shape elongated along a longitudinal axis X along a longitudinal axis of the aircraft that determines a direction toward the front along a direction of motion of the aircraft in flight. A front section with straight cross sections widening relative to the X axis, located at the front of the fuselage and ending in the front of the fuselage in a fuselage nose, and delimited at the rear by a cross section for joining to a rear part of the fuselage behind the front section. The front section includes a cockpit located above a floorboard between a cockpit bulkhead to the rear and a front base to the front. | 03-11-2010 |
| 20100065685 | PRESSURE BULKHEAD FOR AN AEROSPACE FUSELAGE - A pressure bulkhead for an aerospace fuselage includes a bulkhead main portion having an approximately flat shape in unloaded state; and a frame supporting and connecting said bulkhead main portion to the fuselage; wherein said bulkhead main portion includes an airtight structure having a reticular component. | 03-18-2010 |
| 20100096500 | LINING FOR AN AIRCRAFT - The invention relates to a lining | 04-22-2010 |
| 20100102168 | OFFSET ATTACHMENT BOSS FOR RIBBED STRUCTURES - An offset attachment boss for ribbed structure and aircraft components. The ribbed structure including a first plurality of rib members and a second plurality of rib members configured to define a plurality of intersections. At least one offset attachment boss is formed at an intersection of at least one of the first plurality of rib members and at least one of the second plurality of rib members. An anchoring bore is formed in a central aspect of the at least one offset attachment boss and configured to receive a fastener. | 04-29-2010 |
| 20100102169 | FLOOR MADE OUT OF COMPOSITE MATERIAL FOR TRANSPORT VEHICLE AND PROCESS FOR MANUFACTURING PROCESS SUCH A FLOOR - The invention concerns a floor for a transport vehicle that can be attached to a vertical frame structure ( | 04-29-2010 |
| 20100108809 | NOISE-SUPPRESSING STRUT SUPPORT SYSTEM FOR AN UNMANNED AERIAL VEHICLE - A strut support system for a ducted fan unmanned aerial vehicle to suppress noise comprising: a ducted fan fuselage that defines an opening; an engine that extends longitudinally through the opening in the fuselage; a drive mechanism rotatably mounted to the engine, wherein a fan is mounted on the drive mechanism within a duct defined by the opening; and a plurality of struts extending between the ducted fan fuselage and the engine each comprising a first leg and a second leg joined together by a curvilinear junction, wherein the first leg is attached to the ducted fan fuselage and the second leg is attached to the engine, wherein the plurality of struts are positioned upstream of the fan, wherein the junction between the first leg of each of the plurality of struts and the ducted fan fuselage is outside the highlight of the ducted fan fuselage's leading edge. | 05-06-2010 |
| 20100127125 | METAL SHEETS AND PLATES HAVING FRICTION-REDUCING TEXTURED SURFACES AND METHODS OF MANUFACTURING SAME - Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing these metal sheets and plates are disclosed herein. In an embodiment, there is provided a transportation vessel that includes at least one metal product having at least one surface that is substantially grooved, wherein the substantially grooved surface forms a riblet topography, the riblet topography including a multiplicity of adjacent permanently rolled longitudinal riblets running along at least a part of the surface, and wherein the riblet topography is coated with at least one coating sufficiently designed and applied to preserve the riblet topography. In an embodiment, the multiplicity of adjacent permanently rolled longitudinal riblets results in a friction-reducing textured surface. In an embodiment, metal product is used in fabricating at least a portion of an aircraft. In an embodiment, metal product is used in fabricating at least a portion of a rotor blade. | 05-27-2010 |
| 20100133380 | SKIN PANEL FOR AN AIRCRAFT FUSELAGE - The invention relates to a skin panel ( | 06-03-2010 |
| 20100133381 | ATTACHMENT ARRANGEMENT FOR ATTACHING A COMPONENT TO THE FUSELAGE OF AN AIRCRAFT, AIRCRAFT AND METHOD FOR CONSTRUCTING AN ATTACHMENT ARRANGEMENT - Proposed is an attachment arrangement ( | 06-03-2010 |
| 20100140403 | AIRCRAFT FUSELAGE SECTION - The invention relates to an aircraft fuselage section comprising several longitudinal strengthening beams attached to the fuselage section lower panel and several longitudinal rails intended for supporting the floor boards, characterized by at least one crosspiece laid transversally between two strengthening beams and supporting one longitudinal rail, said crosspiece said crosspiece being mounted swiveling on the fuselage section lower panel in order to permit the rotation of the crosspiece around a longitudinal axis. | 06-10-2010 |
| 20100148003 | STRUCTURING CONSTRUCTION FOR AN AIRCRAFT FUSELAGE - A structuring construction ( | 06-17-2010 |
| 20100148004 | Stiffened casing for an aircraft or spacecraft with a laminate stringer of high rigidity and corresponding laminate stringer - The present invention provides a casing structure of low weight provided with a laminate stringer of high rigidity. The stringer has the form of a laminate with a plurality of metallic layers and at least one synthetic fibre layer, which is produced at least partially from Zylon fibres, provided between two metallic layers. | 06-17-2010 |
| 20100148005 | CURVED BEAM OF FIBER COMPOSITE MATERIAL - A curved beam of fiber composite material. The beam includes a first flange curved in a longitudinal direction, a second flange curved in a longitudinal direction and having a greater longitudinal extent than the first flange, and a web curved in a longitudinal direction and extending between the first flange and the second flange. The beam includes a fiber composite laminate including layers of fibers having different fiber directions, wherein a fiber density per unit of area of the second flange is lower than a fiber density per unit of area of the first flange, and wherein the first flange, the second flange and the web are seamless, continuous, and unfolded in a longitudinal direction. | 06-17-2010 |
| 20100155532 | STRUCTURE OF THE LOAD INTRODUCTION ZONE IN THE REAR END OF AN AIRCRAFT - Load introduction zone in the rear end of an aircraft comprising receiving elements ( | 06-24-2010 |
| 20100170986 | AIRCRAFT STRUCTURAL ELEMENT LOCATED AT THE INTERFACE BETWEEN A WING AND THE FUSELAGE - An aircraft structural element situated at an interface between a wing and the fuselage, and including a web and profiled elements flanking the web. At least one the profiled element includes a flat part positioned without overlap in the continuation of a flat part of the web and connected thereto by a welded butt joint using friction stir welding. | 07-08-2010 |
| 20100176241 | AIRCRAFT FRONT PORTION INCLUDING A CONCAVE BULKHEAD SEPARATING A NON-PRESSURIZED RADOME AREA AND A PRESSURIZED AREA - The invention relates to an aircraft front portion ( | 07-15-2010 |
| 20100181426 | Aircraft Fuselage Structure and Method for Producing it - An aircraft fuselage structure is described with frames running in the circumferential direction, stringers running in the longitudinal direction and a skin which is arranged thereon and outwardly seals the aircraft fuselage in a compression-proof manner. According to the invention, it is provided that the aircraft fuselage structure contains prefabricated integral units ( | 07-22-2010 |
| 20100200697 | Weight-Optimizing Internally Pressurized Composite-Body Aircraft Fuselages Having Near-Elliptical Cross Sections - A method for minimizing the weight of an internally pressurized aircraft fuselage of a type that includes an elongated tubular shell having a near-elliptical cross-section with a radius R(φ)- and a curvature Curv(φ), where φ is a roll elevation angle of the shell, includes tailoring at least one structural attribute of the shell as a function of at least one of the elevation angle φ, R(φ) and Curv(φ) so as to reduce the weight of the fuselage relative to an identical fuselage shell in which the same at least one structural attribute has not been so tailored. | 08-12-2010 |
| 20100206986 | CURRENT RETURN NETWORK ELEMENT FOR AN AIRCRAFT - The invention relates to a current return network element ( | 08-19-2010 |
| 20100213314 | ARRANGEMENT FOR INSTALLING ELECTRIC CABLES IN THE FLOOR REGION OF AN AIRCRAFT - An arrangement for installing electric cables in the floor region of an aircraft includes longitudinal guide elements that form cable channels and essentially extend in the longitudinal direction of the aircraft parallel to seat rails that are arranged in the aircraft floor and serve for the mechanical attachment of seat legs. The longitudinal guide elements, which accommodate the data and supply cables to be installed, are not visible to aircraft passengers, but are still readily and easily accessible to the maintenance personnel. The floor plate features an elongate groove-shaped recess extending parallel to the seat rail in the longitudinal direction of the aircraft in the immediate vicinity of one of the two seat rails, wherein an elongate extruded profile is arranged in said recess. The extruded profile features an elongate drawer for transmitting shearing forces and an elongate cable shaft arranged above the drawer and serves for accommodating electric cables. | 08-26-2010 |
| 20100213315 | AIRCRAFT WITH A REINFORCED FLOOR STRUCTURE - The aircraft includes: | 08-26-2010 |
| 20100219294 | COMPOSITE BEAM CHORD BETWEEN REINFORCEMENT PLATES - A composite beam chord is between first and second reinforcement plates. The beam chord includes a first ply of reinforcing fibers with a fiber orientation of +α degrees with respect to a longitudinal axis of the beam chord and a second ply of reinforcing fibers with a fiber orientation of −α degrees with respect to the longitudinal axis. The angle α is between 2 and 12 degrees for suppression or delay of ply splitting. | 09-02-2010 |
| 20100224728 | Interior trim component for an aircraft cabin - An interior trim component ( | 09-09-2010 |
| 20100230538 | CLOSED STRUCTURE OF COMPOSITE MATERIAL - The invention relates to a tubular-shaped closed structure ( | 09-16-2010 |
| 20100230539 | PRESSURE BULKHEAD AND METHOD FOR SUBDIVISION OF AN AIRCRAFT OR SPACECRAFT - The present invention provides a pressure bulkhead for subdivision of an aircraft or spacecraft into an internal and an external pressure region. The pressure bulkhead comprises a pressure plate having an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft, a supporting means which tiltably supports the edge on the inner contour, and a seal which seals the edge with the inner contour. A further aspect of the invention provides a method for subdivision of an aircraft or spacecraft into an internal and an external pressure region. Firstly, a pressure plate is provided that has an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft. In further steps, the edge is tiltably supported on the inner contour and sealed with the inner contour. | 09-16-2010 |
| 20100243803 | INTEGRATED AIRCRAFT FLOOR WITH LONGITUDINAL BEAMS - An integrated floor for an aircraft fuselage includes a composite panel forming a floor surface and composite beams bonded to the floor panel. The beams extend longitudinally within the fuselage and support the floor. | 09-30-2010 |
| 20100243804 | JOINT ARRANGEMENT FOR COMPOSITE-MATERIAL STRUCTURAL MEMBERS - Joint arrangement for composite-material structural members in components comprising a skin and a plurality of structural members, applicable to pairs of first and second intersecting structural members ( | 09-30-2010 |
| 20100243805 | Structural Element of an Aircraft Fuselage - The structural element of an aircraft fuselage, with stringers running in the longitudinal direction of the aircraft fuselage and ribs running transversely to the stringers in the circumferential direction of the fuselage. According to the invention, at least one of the stringers running in the longitudinal direction of the aircraft fuselage is designed as a fastening rail for elements to be installed in the aircraft fuselage. | 09-30-2010 |
| 20100243806 | AIRCRAFT PRESSURE BULKHEAD ASSEMBLY STRUCTURE - The structure comprises: a rim angle ( | 09-30-2010 |
| 20100252681 | INTERNALLY STIFFENED COMPOSITE PANELS AND METHODS FOR THEIR MANUFACTURE - Internally stiffened composite panels and associated manufacturing methods. In one embodiment, an internally stiffened composite panel includes a first face sheet, a second face sheet offset from the first face sheet, and at least one core portion sandwiched between the first and second face sheets. In one aspect of this embodiment, the composite panel further includes a stiffener disposed between the first and second face sheets adjacent to the core portion. The stiffener can have a first attachment portion attached to the first face sheet, a second attachment portion attached to the second face sheet, and an intermediate portion extending between the first and second attachment portions. In another aspect of this embodiment, one or both of the first and second attachment portions is configured to engage a fastener, such as a blind fastener, for attaching a part to the composite panel. | 10-07-2010 |
| 20100282903 | AIRCRAFT PRESSURIZED FLOOR - The invention concerns a pressurized flooring for aircraft, provided with beams ( | 11-11-2010 |
| 20100282904 | AIRCRAFT HAVING A FORWARD-FACING SECTION THAT DEFLECTS ELASTICALLY UNDER IMPACT LOADS - An aircraft comprises a forward-facing aircraft section including composite aircraft skin and a substructure for the skin. The substructure includes a plurality of hoop-shaped composite frames. The frames are designed to deflect elastically under bird impact loads. | 11-11-2010 |
| 20100308165 | STRUCTURAL FRAME MADE OF A COMPOSITE MATERIAL AND AIRCRAFT FUSELAGE COMPRISING SUCH A FRAME - The invention relates to a structural frame made from a composite material. | 12-09-2010 |
| 20100320319 | SYSTEMS AND METHODS FOR REDUCING NOISE IN AIRCRAFT FUSELAGES AND OTHER STRUCTURES - Systems and methods for reducing noise in aircraft fuselages and other structures are described herein. A noise reduction system configured in accordance with one embodiment of the invention includes an auxetic core, a damping layer, and a constraining layer. In this embodiment, the auxetic core is supported by a structural member, and the damping layer is sandwiched between the auxetic core and the constraining layer. A method for manufacturing a structural assembly in accordance with another embodiment of the invention includes forming a stiffener by positioning a first ply of composite material against a first tool surface, positioning damping material against the first ply, and positioning a second ply of composite material against the damping material to sandwich the damping material between the first and second plies. The method can further include forming a skin by positioning a third ply of composite material against a second tool surface offset from the first tool surface, and attaching the stiffener to the skin by co-curing the first, second and third plies of composite material. | 12-23-2010 |
| 20100320320 | AEROPSPACE STRUCTURE INCLUDING COMPOSITE BEAM CHORD CLAMPED BETWEEN REINFORCEMENT PLATES - A structure for an aerospace vehicle includes a composite beam chord clamped between first and second metal plates. The beam chord is clamped at a force that precludes or reduces beam chord delamination under axial loading during operation of the vehicle. | 12-23-2010 |
| 20100327113 | DESIGN OF AIRCRAFT FRAMES - The invention relates to a reinforcing frame ( | 12-30-2010 |
| 20110001007 | METHOD AND SYSTEM FOR CONTROLLING SWAYING OF AN OBJECT - A method of configuring a mount or of controlling sway in an object to be mounted includes configuring isolators of the mount to put a center of elasticity of the flexible mount at a desired height relative to a base of the mount. This desired distance may be at a location of expected minimum clearance between the object to be mounted and the structure expected to surround the object to be mounted and is the center of rotation of the flexible mount. The location of the center of elasticity also may be farther from the base than a center of mass or gravity of the object to be mounted. An equation relating the location of the center of elasticity as a function of isolator material properties and of angle between the isolators and the base may be used to analytically predict the location of the center of elasticity and the center of rotation. | 01-06-2011 |
| 20110001008 | Aircraft floor of optimized compactness - An aircraft floor portion includes crossmembers. Each crossmember comprises a top partial crossmember and a bottom crossmember, with at least one gap being left between the top partial crossmember and the bottom partial crossmember of each crossmember. | 01-06-2011 |
| 20110006159 | FUSELAGE OF AN AIRCRAFT OR SPACECRAFT AND CORRESPONDING AIRCRAFT OR SPACECRAFT - The invention relates to a fuselage of an air- or spacecraft. The fuselage comprises at least one shell element and one insulation element. The insulation element is configured as a passive, watertight insulation element and can be mounted on an inner side of the at least one shell element in a completely air- and watertight manner. The invention furthermore relates to a respective aircraft or spacecraft. | 01-13-2011 |
| 20110011978 | FLOOR SYSTEM FOR A FUSELAGE AIRFRAME OF AN AIRCRAFT - A floor system for a fuselage section of an aircraft is provided. The floor system has an essentially self-supporting design and is substantially mechanically separate from the fuselage section as primary structure. Consequent to the free or self-supporting design of the floor system in the fuselage cell, the layout of the floor system along an aircraft axis can be matched to customer specifications in a simple manner without reference to structural boundary conditions of the fuselage structure. A floor surface for the floor system is formed from a number of floor elements which can be fitted with functional elements, wherein filling of empty spaces or cavities can be achieved with a number of floor equalisation elements. As the floor elements have a relatively large support or fixing surface the loads induced by the functional elements are introduced into the floor system distributed over a large area such that the structural components thereof can be of a structurally lighter and thus weight-saving size. | 01-20-2011 |
| 20110024561 | FRAME ELEMENT, AIRCRAFT AIR-CONDITIONING SYSTEM AND METHOD FOR THE INSTALLATION OF A FRAME ELEMENT IN AN AIRCRAFT - A frame element ( | 02-03-2011 |
| 20110024562 | METHOD FOR MANUFACTURING A FIBRE-COMPOSITE COMPONENT, FIBRE-COMPOSITE COMPONENT AND FIBRE-COMPOSITE FUSELAGE COMPONENT OF AN AIRCRAFT - A method for manufacturing a fibre-composite component with a cladding field and a primary component for reinforcing the fibre-composite component includes the steps of: applying a prepreg semifinished product to a mould to form the cladding field, where in the prepreg semifinished product fibres extend in some sections in a curved manner according to an assumed flow force path in the cladding field of the component to be manufactured; curing the prepreg semifinished product; applying layers of a semifinished textile product to the cured prepreg semifinished product to form the primary component; impregnating the semifinished textile product with matrix material; and curing the assembly comprising pre-cured prepreg semifinished product and semifinished textile product; a fibre-composite component with at least one structural component and a skin section connected to said structural component with a recess as well as a fibre-composite fuselage component of an aircraft with a shell component with at least one recess and with a structural component formed as a frame component. | 02-03-2011 |
| 20110068228 | CABLE WAY FOR AIRCRAFT WITH A STRUCTURE MADE OF COMPOSITE MATERIAL - A retention device, in the form of a trunking with a substantially U-shaped section, for retaining at least one cable running along the structure of an aircraft, fastened to said structure by a fastening means and providing an electrical continuity over the whole of its length, said device being electrically connected to a current-return circuit from the items of equipment of said aircraft, characterized in that said trunking comprises at least one curve on its longitudinal axis corresponding substantially to that of a frame of a fuselage. It is intended to be mounted on a frame of an aircraft made of carbon fibers and to protect the skin of the aircraft against a possible contact with a damaged cable. | 03-24-2011 |
| 20110095129 | ARRANGEMENT OF A CIRCUMFERENTIAL JOINT OF STRUCTURAL ELEMENTS WITH A COUPLING ELEMENT MANUFACTURED IN COMPOSITE MATERIAL - Arrangement of a circumferential joint of structural elements with a coupling element manufactured in composite material in a aeronautic structure, which comprises: two sections ( | 04-28-2011 |
| 20110095130 | COMPOSITE AND STRUCTURE, PARTICULARLY IN THE AEROSPACE SECTOR - The present invention provides a composite, in particular in the field of aviation and aerospace, comprising an omega-stringer that comprises a comb portion, and a connecting member that is connected at one end to the comb portion of the omega-stringer and can be connected at its other end to a standard coupling member. The idea underlying the present invention consists in forming omega-stringers with a connection zone that, on the one hand, is coupled to the comb portion of the omega-stringer and therefore makes it possible to transfer comparatively high loads and, on the other hand, can be connected to a standard coupling member so as to utilise the advantages of standard coupling members of this type when connecting omega-stringers to other stringers, for example T-stringers or other omega-stringers. | 04-28-2011 |
| 20110101163 | TAIL STRUCTURE FOR AN AIRCRAFT OR SPACECRAFT - A tail structure for an aircraft or spacecraft, which adjoins a fuselage section of the aircraft or spacecraft, includes a support construction for supporting at least one craft component, and a bulkhead unit intended for the pressure-tight sealing of the fuselage section and able to be coupled both to the support construction and to the fuselage section so as to form a force flow path between the at least one craft component and the fuselage section. | 05-05-2011 |
| 20110108667 | Thermoplastic Composite Window Panel for Aircraft Applications - An aircraft trim panel structure includes a thermoplastic resinated quadraxial fiberglass lay-up prepreg first open structure skin layer having at least a 28% open area. A thermoplastic resinated quadraxial fiberglass lay-up prepreg second open structure skin layer has at least a 28% open area. An open structure core layer having at least a 28% open area is sandwiched between the first open structure skin layer and the second open structure skin layer. The first open structure skin layer, the second open structure skin layer and the open structure core layer are formed into a three dimensional shape corresponding to the aircraft trim panel. | 05-12-2011 |
| 20110133031 | CNT-TAILORED COMPOSITE AIR-BASED STRUCTURES - An apparatus having a composite air-based structure with a first carbon nanotube infused material and a second carbon nanotube infused material. The first and second carbon nanotube infused materials each having a range of carbon nanotube loading selected to provide different functionalities. | 06-09-2011 |
| 20110147521 | METHOD OF CONSTRUCTING A FIXED-WING AIRCRAFT - The following steps are performed in the method of constructing an aircraft: taking a subassembly comprising two wings that are rigidly fastened together, and fitting it to a fuselage wall; and fastening the subassembly to the wall by means of fastener elements that are distinct from the subassembly and that present main axes that are vertical. | 06-23-2011 |
| 20110155850 | CROSS-BEAM AND AN AIRCRAFT WITH CROSS-BEAMS OF THIS TYPE - A cross-beam for a floor structure of an aircraft includes a web having opposing end sections configured to connect to opposing structural sections of an aircraft fuselage and at least one stepped section. The stepped section is formed by a displacement of the web in a direction corresponding to a normal axis of the web. | 06-30-2011 |
| 20110186683 | METHOD AND A DEVICE FOR THE MANUFACTURE OF A STIFFENING STRUCTURE FOR AN AIRCRAFT FUSELAGE SEGMENT, AND ALSO A STIFFENING STRUCTURE - A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners. | 08-04-2011 |
| 20110198443 | FUSELAGE SECTION HAVING AN INTEGRAL PRESSURE BULKHEAD, AS WELL AS A FUSELAGE SHELL HAVING SUCH A FUSELAGE SECTION - A fuselage section for the pressure fuselage of an aircraft which comprises a fuselage shell structure and at least one pressure bulkhead made of a fibre composite material, the pressure bulkhead being formed in one piece with the fuselage shell structure. A fuselage shell comprising at least one fuselage section of this type. | 08-18-2011 |
| 20110226901 | METHOD FOR LAYING A FLOOR COVERING IN A CABIN OF A VEHICLE - A method for laying a floor covering onto a floor in a cabin of a vehicle comprises the steps of applying a connection means to an element of a group comprising the floor covering and a floor, compacting the floor covering into a compact unit having an open end, bringing the floor covering into the cabin, pulling the open end of the floor covering along a length of the cabin beneath seats disposed in the cabin on the cabin floor and connecting the floor covering to the cabin floor using the connection means. The connection is made by way of one or more adhesive layers, for example. In this way, a carpet floor can be laid or replaced in a cabin of a vehicle without having to remove the seats located in the cabin. | 09-22-2011 |
| 20110233334 | STRUCTURE, ESPECIALLY A FUSELAGE STRUCTURE OF AN AIRCRAFT OR A SPACECRAFT - The present invention provides a fuselage structure ( | 09-29-2011 |
| 20110233335 | IMPACT RESISTANT AND DAMAGE TOLERANT AIRCRAFT FUSELAGE - The aircraft fuselage part ( | 09-29-2011 |
| 20110233336 | FUSELAGE STRUCTURE FOR COMBINED FIXING OF INSULATION BLANKETS AND ITEMS OF EQUIPMENT, AIRCRAFT INCORPORATING SUCH A STRUCTURE - An installation of systems in aircraft fuselages such as thermophonic insulation mattresses and devices such as onboard systems, and bundles of electric wires or fluid ducts (air, water, oxygen, hydraulic fluid). A structure for fastening onto an aircraft fuselage includes at least frames and stringers, the structure further including: fuselage stabilizers connecting the frames and stringers, wherein two stabilizers of two consecutive frames face each other between the two consecutive frames; and a strip board connecting the two stabilizers and including a fastening mechanism arranged so as to receive corresponding fastening mechanisms of the insulation mattresses and the devices. | 09-29-2011 |
| 20110278395 | STRUCTURAL COMPONENT WITH IMPROVED CONDUCTIVITY AND MECHANICAL STRENGTH, AND A METHOD FOR ITS MANUFACTURE - A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection. | 11-17-2011 |
| 20110278396 | MODULAR FLOOR SECTION FOR AIRCRAFT - The floor section for a vehicle cabin consists of a juxtaposition of profiled elements ( | 11-17-2011 |
| 20110290939 | CIRCUMFERENTIAL STIFFENER FOR AN AIRCRAFT FUSELAGE - A circumferential stiffener configured for a fuselage of an aircraft includes a web disposed at an angle to a normal axis of the circumferential stiffener, at least one inner flange, at least one outer flange and an integral angle profile configured for connection to a skin section of the fuselage. | 12-01-2011 |
| 20110315821 | METHOD FOR ASSEMBLING A FLOOR IN A COCKPIT STRUCTURE PREVIOUSLY CONSTRUCTED FROM A SECTION OF AIRCRAFT FUSELAGE - A section of aircraft fuselage comprises a body structure ( | 12-29-2011 |
| 20120001023 | AIRCRAFT FUSELAGE MADE OUT WITH COMPOSITE MATERIAL AND MANUFACTURING PROCESSES - Aircraft fuselage made out with composite material and manufacturing processes. The structure of the fuselage ( | 01-05-2012 |
| 20120001024 | INTERNAL STRUCTURE OF AIRCRAFT MADE OF COMPOSITE MATERIAL - Reinforcement structure ( | 01-05-2012 |
| 20120018579 | SELF-RIGHTING FRAME AND AERONAUTICAL VEHICLE - An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface. | 01-26-2012 |
| 20120018580 | Insulating blanket for an aircraft and assembly integrating such a blanket - This invention proposes an insulation blanket for an aircraft, the said blanket coming in the form of a strip of insulation material of elongated shape having two more or less parallel longitudinal edges ( | 01-26-2012 |
| 20120056037 | FUSELAGE CELL STRUCTURE FOR AN AIRCRAFT IN HYBRID DESIGN - A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one brace which is at least one of a longitudinal and a transverse brace is disposed so as to form at least one of a longitudinal seam and a transverse seam between the at least one double shell skin panel and the at least one monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flange that are disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the at least one monolithic skin panel to the at least one double shell skin panel. | 03-08-2012 |
| 20120061513 | AIRCRAFT INCLUDING FLOOR SUPPORT CROSS-MEMBERS WITH BEARINGS INCLUDING A FLEXIBLE MATERIAL CONNECTING THE CROSS-MEMBER TO THE SUPPORT - An aircraft including: at least one floor cross-member; at least one support carrying the cross-member; and at least one bearing including at least one flexible material and connecting the cross-member to the support. | 03-15-2012 |
| 20120068014 | SEGMENT OF A FUSELAGE OF AN AIRCRAFT - According to an exemplary embodiment of the invention a fuselage segment of an aircraft fuselage is provided, which aircraft fuselage comprises four different radii of curvature, wherein two radii of curvature comprise centre points that are not situated on a vertical symmetry axis of the fuselage segment. | 03-22-2012 |
| 20120104166 | INNER BENT REPAIRMENT - A method for repairing the skin of the fuselage of an airplane from the inside to be used when the skin of the fuselage has been damaged between a first stringer and a second stringer adjacent to the first one is provided. The method comprises four steps which are:
| 05-03-2012 |
| 20120112004 | SHOCK ABSORBING STRUCTURE - It is desired to make a shock absorbing structure small in size. The shock absorbing structure includes a beam-like structural member having a concave section; and a shock absorbing member, one end of which is arranged in the concave section to abut to the structural member and the other end of which is arranged outside the structural member. Even in a case of a dead stroke when the shock absorbing member is bottomed out, the concave section overlaps with the structural member supporting the structure, so that there is no wasteful space. | 05-10-2012 |
| 20120119030 | REINFORCEMENT BEAM AS WELL AS METHOD AND FIBER LAMINATE FOR MANUFACTURING THE REINFORCEMENT BEAM - Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight. | 05-17-2012 |
| 20120126059 | SEALING DEVICE BETWEEN A CROSS MEMBER AND INSULATION BLANKET PROVIDED AT AN AIRCRAFT FUSELAGE - An insulation blanket to be connected at the inside surface ( | 05-24-2012 |
| 20120126060 | METHOD OF FABRICATING AN AIRCRAFT PART BY INFUSING RESIN - The method of fabricating an aircraft part comprises the steps of placing in a stack comprising a preform at least one layer of a material that presents permeability to a predetermined resin that is less than the permeability of a portion of the preform that is the closest to the layer; and placing a resin presence sensor on a side of the layer that is remote from the preform. | 05-24-2012 |
| 20120132747 | UNDER-FLAP STIFFENER FOR AIRCRAFT - An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners. | 05-31-2012 |
| 20120132748 | AIRCRAFT STRUCTURE - An aircraft structure | 05-31-2012 |
| 20120132749 | TAIL-CONE OF AN AIRCRAFT WITH MOVABLE FAIRING - A tail-cone of an aircraft includes a skin provided with a movable fairing which, by a swing articulated mechanism, is supported on the skin in order to allow the opening/closing of the movable fairing and gain access to the inside of the tail-cone. The tail-cone includes actuators for operating the swing articulated mechanism in order to permit the automatic opening and closing of the movable fairing to be carried out. | 05-31-2012 |
| 20120153081 | LINING - A lining comprising at least two opposing profiled frame elements in spaced relationship to each other, at least one membrane element disposed between said profiled frame elements and connected to said profiled frame elements, at least partially, by means of rearwardly engaging fastening means and at least one taughtening means adapted to taughten said membrane element between said profiled frame elements. The membrane element has, as taughtening means, at least one taughtening zip fastener, wherein the state of the membrane element can be changed, by closing the taughtening zip fastener, to a state in which it is taughtened between the profiled frame elements. Installation and opening of the membrane field can be significantly simplified by the inclusion of a second, so-called access zip fastener. | 06-21-2012 |
| 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 |
| 20120211602 | FRAME FOR AN OPENING PROVIDED IN AN AIRCRAFT FUSELAGE - A frame of a door that is provided at an opening made in a fuselage of an aircraft that is delimited by a skin, whereby the frame that includes an upper longitudinal stiffener and a lower longitudinal stiffener provides the connection between two vertical substructures ( | 08-23-2012 |
| 20120248247 | AIRCRAFT FUSELAGE WITH HIGH STRENGTH FRAMES - Fuselage section of an aircraft whose structure comprises a skin ( | 10-04-2012 |
| 20120261510 | CENTER FUSELAGE BELLOWS - A sealing assembly is provided in an airframe of aircraft. The sealing assembly includes, but is not limited to a resilient and yet stiff enough bellows body that is attachable to the fuselage of the aircraft and is further attachable to a center wing box of the aircraft. The sealing assembly seals off a gap between the fuselage and the center wing box so as to allow maintaining pressure in the fuselage if the fuselage is pressurized. The bellows body is a composite and is designed to sustain exposure to tear and wear and exposure to a high and low temperatures as well as exposure to chemicals used during operation of the aircraft. | 10-18-2012 |
| 20120267478 | AIRCRAFT INCLUDING AN INTERNAL PARTITION - The aircraft includes a structural portion such as a fuselage, a wing, or a tail, the structural portion including a wall separating the inside from the outside of the portion and including fractions defining between them an inside volume of the portion and at least one structural partition separating zones of the volume, e.g. a front zone and a rear zone, from each other, the partition including at least one flexible diaphragm suitable for deforming and at least two preferably rigid supports supporting the diaphragm in discontinuous manner. | 10-25-2012 |
| 20120286092 | RECONFIGURABLE FLOORBOARD SYSTEM - A floorboard for a reconfigurable floorboard system may include a substantially trapezoid shaped plate. An interlocking feature may be formed proximate an edge of at least three sides of the plate for interlocking with adjacent floorboards. Each interlocking feature may be formed to interlock with a mating interlocking feature formed at an edge of a side of at least one adjacent floorboard. A notch may be formed on an underside of the plate proximate each corner of the plate to contact a member of a floor grid to prevent movement of the floorboard. | 11-15-2012 |
| 20120286093 | AIRCRAFT FUSELAGE AND SKIN SECTION - Disclosed is a fuselage | 11-15-2012 |
| 20120298799 | SELF-SUPPORTING CABIN STRUCTURAL SEGMENT - A cabin structural segment is provided for an aircraft that includes, but is not limited to a fuselage structure and a floor structure. The fuselage structure defines an interior and separating it from an environment. The fuselage structure includes, but is not limited to an opening for a door. It is possible to provide via the opening a connection between the interior and the environment. The cabin structural segment is designed to be self-supporting. The cabin structural segment is fastenable exclusively to the floor structure. The cabin structural segment is constructed in such a way that the one cabin structural segment frames the opening. | 11-29-2012 |
| 20120298800 | FLY AWAY CAUL PLATE - Techniques and apparatus for providing a fly away caul plate are disclosed. In an embodiment, a method for curing a composite structure includes placing a pre-cured caul plate proximate an uncured composite lay-up, the lay-up may or may not include one or more stiffeners extending substantially perpendicular to the lay-up surface, the caul plate including an aperture for receiving the at least one stiffener. A force may be exerted against the caul plate to engage the composite lay-up. Heat and/or pressure may be applied to the composite lay-up to cure the stiffener panel and co-bond the caul plate to the composite lay-up. | 11-29-2012 |
| 20120305706 | System and Method for Insulating Frame Member - There is provided an insulation system and method for a transport vehicle. The system has first and second frame members; a first rigid foam insulation member extending between the first and second frame members; a second rigid foam insulation member, where a first sidewall of the first insulation member integrates with a second sidewall of the second insulation member; and, a third rigid foam insulation member where the second sidewall of the first insulation member integrates with a first sidewall of the third insulation member. Each of the insulation members is surrounded by a protective layer. When the insulation members are integrated, the second and third insulation members impart one or more compression forces on the first insulation member and on the first frame member in order to secure the first insulation member in place without use of any fastener device. | 12-06-2012 |
| 20120305707 | COMPOSITE AIRCRAFT FRAME - Composite aircraft frame ( | 12-06-2012 |
| 20120312922 | Boron Fiber Reinforced Structural Components - This disclosure is directed to a boron reinforced composite structural member. The concepts and technologies illustrated in this disclosure are taught within the context of a boron reinforced aircraft keel. A boron reinforced composite structural member may be constructed of a structural member core and a surrounding structural member casing. In one embodiment, the structural member core includes alternating layers of boron fiber reinforced plies and layers of interior carbon fiber reinforced plies. The boron fiber reinforced plies are oriented in a longitudinal direction, and the interior carbon fiber reinforced plies are oriented diagonally, perpendicular, and parallel to the boron fiber reinforced plies. The structural member casing includes layers of exterior carbon fiber reinforced plies that substantially surround the structural member core. | 12-13-2012 |
| 20130009008 | STRUCTURAL COMPONENT WITH RIB AND CROSS MEMBER ELEMENT - The present invention provides a fuselage structure for an aircraft or spacecraft with an outer skin. The fuselage structure comprises a rib element for stiffening the outer skin and ad cross member element. Here the rib element is bent in the shape of an arc to correspond to an inner contour of the outer skin. The cross member element connects two arc sections of the rib element transversely to each other. The cross member element has a higher strength than the rib element. From another point of view the invention provides an aircraft with such a fuselage structure. | 01-10-2013 |
| 20130043346 | AIRCRAFT FUSELAGE STRUCTURAL COMPONENTS AND METHODS OF MAKING SAME - Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a friction stir weld region. Such aircraft fuselage structural components may thus be provided with plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers each being positioned within a respective one of the stringer holes of the frame member. The reinforcement members are lap joined to corresponding surfaces of frame members in the vicinity of the stringer holes such that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region. | 02-21-2013 |
| 20130048785 | COVERING SYSTEM FOR AN INTERIOR SPACE OF A VEHICLE, A METHOD FOR COVERING A REGION OF AN INTERIOR SPACE OF A VEHICLE, AND A VEHICLE WITH AN INTERIOR SPACE, WHICH IS COVERED BY THE COVERING SYSTEM IN AT LEAST SOME REGIONS - A covering system for an interior space of a vehicle comprises at least one surface element and at least one sealing element. The surface element comprises an upper surface and at least one bounding edge extending at an angle to the upper surface. The surface element furthermore comprises at least one recess, which runs at least adjacent to the bounding edge. The sealing element has an extent corresponding at least partly with the at least one bounding edge, and a shape corresponding at least partly with the recess of the surface element. | 02-28-2013 |
| 20130048786 | Reinforcement of Friction Plug Welds - A hole in a metal workpiece is filled by friction plug welding. The weld between the workpiece and the plug is reinforced by a weld land in the workpiece that surrounds one end of the plug. The weld land is formed by extruding a portion of the plug into a cavity in an anvil used in the welding process. | 02-28-2013 |
| 20130087656 | AIRCRAFT INTERIOR EQUIPMENT COMPONENT AND AIRCRAFT INTERIOR EQUIPMENT COMPONENT SYSTEM - An aircraft interior equipment component ( | 04-11-2013 |
| 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 |
| 20130105628 | AIRFRAME | 05-02-2013 |
| 20130112811 | AIRCRAFT WITH AN INTEGRATED ENERGY-ABSORBING DEFORMATION STRUCTURE AND AIRCRAFT WITH SUCH A FUSELAGE - An aircraft fuselage has an integrated energy-absorbing deformation structure. The fuselage includes annular frames, longitudinal fuselage beams interconnecting the annular frames, and a covering forming a fuselage skin. A lower floor structure is disposed in an interior of the fuselage. The lower floor structure includes a plurality of transverse beams connected to an assigned frame and longitudinal floor beams which interconnect said transverse beams. The deformation structure is formed in a lower fuselage region disposed below the lower floor structure. The deformation structure includes a first inelastically deformable central region and, on a left-hand side and a right-hand side, respective second inelastically deformable regions of greater stiffness in the vertical direction than the central region. | 05-09-2013 |
| 20130126673 | RAIL SYSTEM AND METHOD AND SYSTEM FOR MOUNTING A COMPONENT IN AN AIRCRAFT - A rail system for use when assembling a component in an aircraft comprises a first rail element having a securing device which is designed to be complementary to a first securing device provided in the region of a floor of an aircraft fuselage element and is adapted to cooperate with the first securing device in order to releasably secure the first rail element in the region of the floor of the aircraft fuselage element, wherein a section of the first rail element projects beyond an edge of the floor of the aircraft fuselage element in the connected state of the first rail element and the aircraft fuselage element. The first rail element furthermore comprises a guide device, which is designed to be complementary to a first guide device provided on an assembly aid, which is to be introduced into the aircraft fuselage element, and is adapted to cooperate with the first guide device to enable a guided displacement of the assembly aid to be introduced into the aircraft fuselage element relative to the rail system. The rail system furthermore comprises a second rail element having a securing device which is designed to be complementary to a second securing device provided in the region of the floor of the aircraft fuselage element and is adapted to cooperate with the second securing device in order to releasably secure the second rail element in the region of the floor of the aircraft fuselage element, wherein a section of the second rail element projects beyond an edge of the floor of the aircraft fuselage element in the connected state of the second rail element and the aircraft fuselage element. The second rail element furthermore comprises a guide device, which is designed to be complementary to a second guide device provided on an assembly aid, which is to be introduced into the aircraft fuselage element, and is adapted to cooperate with the second guide device to enable a guided displacement of the assembly aid to be introduced into the aircraft fuselage element relative to the rail system. | 05-23-2013 |
| 20130140401 | HIGHLY LOADED FRAME OF AN AIRCRAFT FUSELAGE WITH A LATTICE STRUCTURED WEB - Frame of a fuselage section of an aircraft that receives external loads, such as the rear section that receives the loads of the tail planes, comprising a first sector ( | 06-06-2013 |
| 20130146710 | AIRCRAFT NOSE STRUCTURE WITH LANDING GEAR COMPARTMENT - An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead. | 06-13-2013 |
| 20130187001 | STRUCTURAL COMPONENT AND FUSELAGE OF AN AIRCRAFT OR SPACECRAFT - A supporting component is provided for reinforcing the skin of an aircraft or spacecraft, for example a stringer or former, this component being configured as a closed profile (hollow profile), such that a system medium (M) can be conducted through the structural component. In this respect, the hollow profile itself serves as a load-bearing component. | 07-25-2013 |
| 20130221156 | AIRCRAFT NOSE STRUCTURE AND CORRESPONDING AIRCRAFT - This aircraft nose structure comprises frames ( | 08-29-2013 |
| 20130264422 | Aircraft frame and method for obtaining the same - An aircraft frame and a method for obtaining an aircraft frame, which frame is made of composite material, and which frame comprises several partitions ( | 10-10-2013 |
| 20130306795 | AIRCRAFT FUSELAGE FRAME ELEMENT - The subject of the invention is an aircraft fuselage frame element ( | 11-21-2013 |
| 20130320140 | WALL INSTALLATION SYSTEM AND METHOD - A system for attaching a wall panel includes a wall panel and a lock strip. The wall panel has a back and a tab extending from the back. The lock strip is moveably attached to a wall frame member, and has a three-position locking slot, including a receiving portion configured to receive the tab, a locking portion configured to lock the tab with respect to the frame member, and a release portion configured to release the tab. The wall panel is removably attachable to the frame member by inserting the tab into the receiving portion and linearly moving the lock strip to lock the tab in the locking portion. The system can be used for attaching interior sidewall panels in an aircraft. | 12-05-2013 |
| 20140027573 | AIRCRAFT FUSELAGE STRUCTURAL ELEMENT WITH VARIABLE CROSS-SECTION - An aircraft fuselage structural element has the general form of an elongated profile and includes a web and at least one flange. The at least one flange has a curved cross-section tangent to the web. Use in a profile to increase the residual compressive strength after impact. | 01-30-2014 |
| 20140054418 | DOOR FRAME CONSTRUCTION, FUSELAGE PORTION AND AIRCRAFT OR SPACECRAFT - The present invention provides a door frame construction in particular for an aircraft or spacecraft, including a former; a fibre metal laminate which is connected to the former; and an outer skin which is connected to the fibre metal laminate. | 02-27-2014 |
| 20140103162 | Method And Apparatus For Attaching An Aircraft Fuselage Frame To A Wing Box - The present disclosure is generally directed to an aircraft body including a fuselage skin on an outboard member of the aircraft body and a wing box extending through a member of the aircraft body. The wing box being enclosed and capable of being pressurized is fixedly attached at an outer surface to at least one pair of an attachment member and an attachment link member that is fixedly attached to the aircraft body. | 04-17-2014 |
| 20140110528 | AIRCRAFT FUSELAGES - Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant. | 04-24-2014 |
| 20140110529 | AIRCRAFT FUSELAGE AND METHOD FOR CONSTRUCTING A FLOOR IN SUCH A FUSELAGE - Such a fuselage includes cross-members adapted for the formation of a floor, at least one of said cross-members including an upper part, a lower part, linkage for the lower part to the upper part, and at least one opening for the passage of systems which is delimited between the lower part and the upper part. The upper part of the cross-member is fastened to the fuselage and is dimensioned so as to bear the stresses to which said cross-member may be subjected when the aircraft remains on the ground. The lower part is fastened to the upper part so as to reinforce it such that when assembled, the upper part and the lower part are adapted to bear the stresses to which the cross-member may be subjected in flight conditions of the aircraft. | 04-24-2014 |
| 20140145031 | Vertically Integrated Stringers - Apparatus and methods provide for the reinforcement of various components of an aircraft utilizing vertically-oriented circumferential stringers. According to embodiments described herein, barrel skin of an aircraft fuselage may be reinforced using stringers that are vertically-oriented and circumferential. According to additional embodiments, the wing stringers of a wing can be aligned with circumferential stringers. According to further embodiments, the wing may also have one or more wing spars having an elliptical aperture. The shape of the elliptical may be configured for attachment to a fuselage so that an outer surface of the aperture is disposed proximate to an inner surface of the fuselage. | 05-29-2014 |
| 20140175223 | AIRCRAFT FRONT PORTION HAVING AN IMPROVED LANDING GEAR BAY - An aircraft front portion in which the landing gear storage bay is arranged under a cockpit floor. The landing gear bay is mechanically connected to the fuselage frames of the aircraft front portion in order to perform the function of taking up the mechanical forces acting on the fuselage frames under the effect of pressurization. The cockpit floor is thus simplified since it serves solely as a plane for the crew to walk on and it can be lowered so as to release space in the cockpit. | 06-26-2014 |
| 20140197277 | AIRCRAFT SUPPORT STRUCTURE - A support unit for a structure within a pressure vessel that includes an external load distribution plate, an internal load distribution plate, a standoff unit between the external load distribution plate and the internal load distribution plate that extends through an opening in a pressure vessel. | 07-17-2014 |
| 20140203142 | Refractive Body Panels (Vehicle Refractive Panels) - Refractive body panels replace traditional metal or fiberglass panels and consist primarily of dyed and moldable plastic in a prism configuration under clear polycarbonate; a bi-layer unit working in concert to scatter and/or change the direction of light to illuminate the exterior and increase safety and performance; the bi-layer unit works together to reduce the weight of a vehicle; the dyed prism allows for panels in various colors: the panels attach to a vehicle's frame as a direct pre-market or post-market replacement (including polyurethane bumpers) and require minimal modifications to the structural design of foot-powered vehicles, motorcycles, cars, trucks, boats, etc. | 07-24-2014 |
| 20140209742 | AIRCRAFT ELECTRICAL CORE - An electrical core of an aircraft is provided. The electrical core includes at least one shelf on which is disposed at least one module containing components and comprising at least one input able to be linked to at least one power supply cable and at least one output able to be linked to at least one output cable. In the module, the output cable or cables travel under or in the shelf disposed under the module. | 07-31-2014 |
| 20140231586 | HIGH-WING-AIRCRAFT FUSELAGE SUPPORT STRUCTURE - A structural support assembly for a high-wing aircraft may include a plurality of columns extending through a passenger compartment of the aircraft having a pair of wings mounted proximate a top of a fuselage. A column upper end of at least one of the columns may be coupled to a center wing box structure adjacent to a rear spar thereof. A column lower end of at least one of the columns may be coupled to a floor substructure. | 08-21-2014 |
| 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 |
| 20140332630 | SUPERPLASTICALLY FORMED ULTRASONICALLY WELDED METALLIC STRUCTURE - Disclosed herein is a method of making a structure by ultrasonic welding and superplastic forming. The method comprises assembling a plurality of workpieces comprising a first workpiece including a first material having superplastic characteristics; ultrasonically welding the first workpiece to a second workpiece, to form an assembly; heating the assembly to a temperature at which the first material having superplastic characteristics is capable of superplastic deformation, and injecting a fluid between the first workpiece and the second workpiece to form a cavity between the first workpiece and the second workpiece. | 11-13-2014 |
| 20140346276 | SUPPORT PLATE FOR THE PASSAGE OF SYSTEMS BETWEEN TWO ZONES WITH DIFFERENT PRESSURIZATIONS OF AN AIRCRAFT - A support plate for the passage of systems between two zones at different pressurizations of an aircraft, in the region of a bulkhead separating the two zones. The support plate comprises a connection plate including at least one retaining element and at least one sealing joint and is provided with a plurality of holes intended for the passage of an assembly of systems which have to pass through said bulkhead. | 11-27-2014 |
| 20140353426 | AIRCRAFT COMPRISING AN IMPROVED CONNECTION ZONE BETWEEN A FRONT BEAM AND A FRONT LOWER FUSELAGE SECTION - An aircraft comprising a front beam having stiffeners and a front lower fuselage section having stiffeners, each stiffener comprising a core and at least one bearing surface. Each stiffener of the front beam is connected to a stiffener of the lower fuselage section by at least one batten which abuts against the bearing surfaces of the stiffeners. A sealed wall is arranged in a transverse plane which corresponds approximately to the connection plane between the front beam and the front lower fuselage section. The sealed wall includes cut-outs in order to allow the stiffeners and the battens to pass. | 12-04-2014 |
| 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 |
| 20150008284 | PRESSURE PANELS - Anisotropic pressure panels are disclosed. The pressure panels include at least two distinct regions, with one region yielding to lateral deformation more than at least one other region. The regions each independently may include a plurality of beads, such beads optionally integrally formed in the body of the pressure panel. In aerospace applications, the pressure panel may be coupled to load-bearing structures, such as wings, and may at least partially define a wheel well. | 01-08-2015 |
| 20150008285 | PRESSURE FUSELAGE OF AN AIRCRAFT WITH A FUSELAGE SHELL AND A PRESSURE BULKHEAD DISPOSED THEREIN - A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells. | 01-08-2015 |
| 20150034763 | AIRCRAFT FUSELAGE FRAME ELEMENT INTEGRATING TABS FOR THE FASTENING OF STIFFENERS - In order to reduce the time and the cost of manufacturing an aircraft fuselage, the subject matter disclosed herein provide an aircraft fuselage frame element comprising a core provided with at least one through-opening intended for the passing of a fuselage stiffener, and further comprising, associated with each opening, a tab for the fastening of the frame element onto the fuselage stiffener, with the tab being a single piece with the core and connected to the latter by a fold that delimits the opening. | 02-05-2015 |
| 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 |
| 20150041589 | AIRCRAFT SIDE OF BODY JOINT - An aircraft includes a wing and a wing box. The wing is joined to the wing box at a side of body joint. The wing and the wing box each includes lower skin and a plurality of stringers on the skin. Ends of at least some of the stringers at the side of body joint have a web cutout and a base that is spanwise tapered to a knife edge at the skin. | 02-12-2015 |
| 20150048206 | UNITARY PANEL FOR THE FLOOR OF A VEHICLE, FLOOR, AND VEHICLE INCLUDING SUCH A UNITARY PANEL - The invention relates to a unitary floor panel ( | 02-19-2015 |
| 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 |
| 20150083861 | STRUCTURAL ELEMENT FOR AN AIRCRAFT FUSELAGE THAT PREVENTS LATERAL-TORSIONAL BUCKLING - The invention relates to a structural element for an aircraft fuselage, generally shaped in the form of a longitudinally elongate section. The element comprises two wings, each wing including: a portion that extends uninterrupted along the entire length of the section, and legs spaced apart from one another and extending from said uninterrupted portion such as to define an opening between two consecutive legs. One of the legs of one wing is arranged to face at least part of the opening defined between two consecutive legs of the other wing. Consequently, the structural element can be produced from a single fibrous preform on a curved tool, minimizing waste material and reducing the weight of said element. | 03-26-2015 |
| 20150102168 | AIRCRAFT FUSELAGE STRUCTURE - An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane. | 04-16-2015 |
| 20150108272 | AIRCRAFT FUSELAGE COMPRISING AN OUTER INSULATION - An aircraft fuselage comprising a structure, a skin connected to the structure and forming a barrier between the interior and the exterior of the fuselage, an external coating being plated or placed against said skin, wherein the external coating comprises a thermal insulator that covers the fuselage at least in part and has at least one foam insulating layer. The external coating comprises a plurality of juxtaposed panels adhesively bonded to the fuselage and/or secured to the fuselage by mechanical fixings. | 04-23-2015 |
| 20150115102 | DECOMPRESSION PANEL FOR USE IN AN AIRCRAFT - A decompression panel includes a body portion having a first end and a second end opposing the first end. The decompression panel also includes a tab extending along the first end and a flange coupled to the body portion. The flange defines a slot adjacent the second end. The decompression panel is secured in an airplane cabin by the tab and slot features, such that unwanted access to areas behind such panels is prevented. | 04-30-2015 |
| 20150115103 | DECOMPRESSION PANEL FOR USE IN AN AIRCRAFT ASSEMBLY - A decompression panel for use in an aircraft assembly is provided. The decompression panel includes a body portion including a top end and a bottom end, and an array of openings formed in the body portion. The openings in the array progressively decrease in size along a height of the body portion from the bottom end towards the top end. | 04-30-2015 |
| 20150115104 | DECOMPRESSION PANEL FOR USE IN AN AIRCRAFT ASSEMBLY - A decompression panel for use in an aircraft assembly is provided. The decompression panel includes a body portion including a top edge and a bottom edge, and a front surface and a rear surface opposing the front surface. A plurality of openings are formed in the body portion, and a first stiffening member is formed on the rear surface below the plurality of openings. The first stiffening member extends from the rear surface towards the top edge such that the plurality of openings are at least partially obstructed by the first stiffening member. | 04-30-2015 |
| 20150136906 | ROTARY WING AIRCRAFT AIRFRAME - A rotary wing aircraft airframe ( | 05-21-2015 |
| 20150144736 | PRESSURE BULKHEAD FOR AN AIRCRAFT AND DEVICE AS WELL AS METHOD FOR MANUFACTURING AN AIRCRAFT STRUCTURAL COMPONENT - A pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure. The bulkhead comprises a first area element, at least one second area element and a plurality of core elements. The first area element has a plurality of receptacles. Each receptacle is configured to receive a core element. The core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element. The surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements. | 05-28-2015 |
| 20150291272 | SELF-RIGHTING FRAME AND AERONAUTICAL VEHICLE - An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has an apex preferably at a top of a central vertical axis. The apex provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a supporting surface. The frame provides self-righting functionality and protection of elements carried therein. | 10-15-2015 |
| 20150307178 | FUSELAGE AIRFRAME - A fuel tank and a differential frame in a fuselage airframe of a helicopter, the fuel tank being installed between the fuselage lower cover shell and the floor panel. The differential frame separates the fuel tank into two individual compartments, the differential frame having a web below the floor panel with a variable-height with a minimum height at the symmetry axis of the fuselage cross-section and a maximum height at lateral frame roots regions. A transversal beam is attached at each of its both ends to the differential frame bridging the entire variable-height of the differential frame and the fuel tank with two front and rear fuel bladders covering both individual tank compartments with a middle bladder installed between the transversal beam and the variable-height web of the differential frame. | 10-29-2015 |
| 20150314867 | CONVERTIPLANE (VARIANTS) - The claimed versions belong, to tilt rotors nonexpendable aircrafts. In general, the convertiplane has a fuselage, a wing and engine groups. In one embodiment each engine group is designed in the form of at least one engine positioned with the possibility to turn, provided that the engines in groups are designed in view of the condition of thrust change relative to each other and/or groups and engine groups are positioned at the tip of corresponding wing at front fuselage and tail fuselage. In a second embodiment the wing is designed combined in the form of forward-swept wing and aft-swept wing, each engine group is designed in the form of at least one engine positioned with the possibility to turn, provided that the engines in groups are designed in view of the condition of thrust change relative to each other and/or groups and groups are positioned at the tip of corresponding wing. The claimed versions allow simplification and weight reduction of AC structure, increasing of its maneuvering ability at every flight stage, improvement of its aerodynamic quality such as stability and aerodynamic efficiency. | 11-05-2015 |
| 20150321742 | STIFFENER FOR AN AIRCRAFT FUSELAGE, METHOD FOR MANUFACTURING SAME, AND AIRCRAFT FUSELAGE EQUIPPED WITH SUCH A STIFFENER - This stiffener is intended for a fuselage. It comprises a hollow section that can be trapezoidal, with a base attached to the fuselage or to the floor, high enough rising sides and a top side contributing to the rigidity and cohesion of the stiffener. A direct assembly with the fuselage is possible. The base is made of two edges provided one on the other or in front of the other. This rigid stiffener, in spite of its discontinuous section, can be manufactured by simple foldings of a planar metal sheet at the beginning. | 11-12-2015 |
| 20150321743 | METHOD FOR MANUFACTURING A LOAD BEARING STRUCTURE AND SUCH A LOAD BEARING STRUCTURE - A method for manufacturing a load bearing structure involves providing a panel; providing a first set of split stiffening elements on a surface of the panel, wherein the split stiffening elements of the first set have bottom surfaces and central portions with open top clearances, respectively, spaced apart from each other; providing a second set of stiffening elements having bottom surfaces and top surfaces and central portions, respectively; inserting the stiffening elements of the second set into respective open top clearances of the split stiffening elements of the first set and providing the second set of stiffening elements on the surface of the panel for forming a grate structure; and attaching top surfaces to the split stiffening elements of the first set for forming complete profiles. | 11-12-2015 |
| 20150336670 | UNMANNED AERIAL VEHICLE AND FUSELAGE THEREOF AND METHOD FOR MANUFACTURING THE FUSELAGE - The present disclosure provides a fuselage of an unmanned aerial vehicle. The fuselage comprises an upper plate, a lower plate opposite to the upper plate, a connecting plate, and a middle spacing plate; the connecting plate is connected between the upper plate and the lower plate; the upper plate, the lower plate, and the connecting plate are enclosed to define a receiving space; the upper plate, the lower plate, the connecting plate, and the middle spacing plate are integrally formed; the upper cavity is located between the middle spacing plate and the upper plate, and the lower cavity is located between the middle spacing plate and the lower plate; and a first mounting opening is defined in the upper plate allowing a component to enter the upper cavity, and a second mounting opening is defined in the lower plate allowing a component to enter the lower cavity. | 11-26-2015 |
| 20150344118 | AIRCRAFT FUSELAGE FRAME MADE OF LAMINATED COMPOSITE MATERIALS AND INCLUDING REINFORCEMENT CURVED ZONES OF VARYING VALUE OF RADIUS OF CURVATURE - A structural frame for a fuselage of an aircraft. The frame is formed from a composite material profile comprising curved zones ( | 12-03-2015 |
| 20150344119 | Sliding connection between the floor structure and the hull structure of an aircraft - An aircraft structure part comprising a floor structure, a hull structure, and a connecting element. The connecting element comprises a rod attached, at its first end, to one of the hull and the floor; an attachment element, attached to the other of the hull and the floor, and provided with an opening in which the second end of the rod is slidably mounted; and an endstop attached to the rod so as to engage with the attachment element, to limit the sliding amplitude of the rod in the opening. When the connection between the floor and the hull is loaded in tension, the endstop makes it possible to comply with the standards for withstanding acceleration towards the aircraft front. When the connection is loaded in compression, the rod slides freely in the opening, which limits the constraints of withstanding compressive stresses, reducing the weight of the connecting element. | 12-03-2015 |
| 20150344120 | FLEXIBLE CONNECTION BETWEEN THE FLOOR STRUCTURE AND THE HULL STRUCTURE OF AN AIRCRAFT - The disclosure herein relates to a part of an aircraft structure including a portion of a floor structure and a portion of a hull structure, connected to one another by a connecting element. In accordance with, the disclosure herein the connecting element includes a flexible cable fixed at one of the ends thereof to the portion of a floor structure and fixed at the other, second of the ends thereof to the portion of a hull structure. When the connection between the portion of a floor structure and the portion of a hull structure is subjected to tensile load, the flexible cable makes it possible to meet the standards of resistance to forward accelerations of the aircraft. When the connection is subjected to compressive load, the flexible cable relaxes and bends, which limits the requirements of withstanding compressive stresses and therefore the weight of the connecting element. | 12-03-2015 |
| 20150353181 | COMPOSITE STRUCTURE FOR AN AIRCRAFT AND MANUFACTURING METHOD THEREOF - The invention refers to a composite structure for an aircraft comprising a panel and at least one stringer joined to a surface of the skin panel, the stringer having a foot and a web protruding from the foot, and a run-out section at one of its ends. The panel includes a plurality of stacked and co-cured plies of composite material, and at least part of the foot of the stringer at the run-out section, is inserted between two plies of the panel, and it is co-bonded, co-cured or secondary bonded with said two plies. The structure of the invention provides a reinforced join between the foot of the stringer and the skin panel, avoiding peeling or de-bonding problems, without substantially modifying the manufacturing process. | 12-10-2015 |
| 20150367929 | AIRCRAFT FUSELAGE STIFFENER FORMED FROM A SHEET FOLDED OVER ONTO ITSELF - The disclosure herein relates to an aircraft fuselage stiffener including a heel, a flange, and a web connecting the heel and the flange, this stiffener comprising a folded sheet extending along the length of the heel, the web and the flange. In addition, to improve the mechanical behaviour of the stiffener, the folded sheet includes on the one hand a main portion extending along the length of the heel, the web and the flange, and on the other hand at least one folded-over portion forming a lining of the main portion over at least part of the web and/or the heel and/or the flange. | 12-24-2015 |
| 20160001869 | AIRCRAFT STRUCTURAL COMPONENT - An aircraft structural component having a skin element, including an inner surface, a multitude of transverse stiffening elements, which lie against the inner surface of the skin element, and a multitude of longitudinal stiffening elements, perpendicular to the transverse stiffening elements against the inner surface of the skin element, wherein between a first and a second transverse stiffening element and also between a first and a second longitudinal stiffening element, a first skin section is defined. An aircraft structural component is provided with the quantity of the longitudinal stiffening elements reduced. A first applied reinforcement includes a core layer having a contour line running along the circumference of the skin element, the first applied reinforcement including a face sheet surrounding the core layer on the side thereof which faces away from the skin element, which face sheet is connected to the skin element along the core layer contour line. | 01-07-2016 |
| 20160009356 | AIRCRAFT FUSELAGE PROVIDED WITH INTERIOR FIT-OUT EQUIPMENT | 01-14-2016 |
| 20160023743 | FLAT-STOCK AERIAL VEHICLES AND METHODS OF USE - A flat-stock aerial vehicle includes a body having a plurality of flat-stock sheets connected to one another, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The aerodynamic propulsors can provide lifting thrust, pitch, yaw, and roll control in both helicopter-like hover flight and airplane-like translational flight. | 01-28-2016 |
| 20160031562 | AIRCRAFT WITH A FRAMEWORK STRUCTURE THAT COMPRISES AT LEAST ONE HOLLOW FRAME - An aircraft with a fuselage that comprises a framework structure having at least one hollow frame that is integrally formed in one piece and comprises fiber reinforced polymers, the at least one hollow frame defining an integrated ventilation air duct that is adapted for guiding ventilation air into the aircraft. | 02-04-2016 |
| 20160046392 | Method For Assembling An Aircraft Fuselage - A method for assembling an aircraft fuselage includes different steps. In a first step the secondary structural components and interior components are assembled to form a core structure. The core structure comprises a cabin floor, side wall panels and ceiling panels. In another step of the method a primary structure is arranged around the core structure to form a part of a fuselage. | 02-18-2016 |
| 20160052617 | HAT STRINGER CLOSEOUT FITTING AND METHOD OF MAKING SAME - A closeout fitting for a hat stringer includes a cover that has a fitting surface. The fitting surface is substantially complementary to at least a portion of an outer surface of the hat stringer. The cover is configured to couple against the hat stringer outer surface. The cover also includes a first portion configured to extend across a gap defined in a cap portion of the hat stringer. The closeout fitting also includes an insert. The insert includes a first outer perimeter surface that is substantially complementary to at least a portion of an interior surface of a channel defined by the hat stringer. The insert is configured to couple against the channel interior surface proximate the hat stringer closeout portion. The insert and the cover are formed with a suitable stiffness to limit a deformation of the hat stringer proximate the closeout portion. | 02-25-2016 |
| 20160068278 | PREVENTING CRACKS AT BOLTED OR RIVETED JOINTS OF AIRCRAFT STRUCTURAL PARTS - A method for joining two aircraft structural parts by a bolted or riveted joint and for preventing cracks at said joint includes a step of providing a first metallic aircraft structural part and a second aircraft structural part, wherein the first aircraft structural part includes a first joint region and a second aircraft structural part includes a second joint region. Furthermore, the method includes a step of inducing compressive residual stresses in a first area of the first joint region for preventing cracks. Finally, the method includes a step of fastening together the first and second aircraft structural parts at the first and second joint regions by a bolted or riveted joint. An aircraft including first and second aircraft structural parts is also described. | 03-10-2016 |
| 20160075424 | CEILING OF A VEHICLE, A VEHICLE, AND A METHOD OF USING SAID CEILING - A ceiling provided with a plurality of rigid panels. Presser means tending to press each panel longitudinally against at least one adjacent panel. At least one panel is a “sliding panel” carried by a guide device so as to slide in a sliding plane. One panel is a “retractable panel” movable from an open position towards a closed position, the sliding panels being free to move in longitudinal translation along the guide device when the retractable panel is in the open position and being locked while being arranged longitudinally one after another when the retractable panel is in the closed position. The ceiling comprises movement means for moving the retractable panel in reversible manner from the closed position to the open position. | 03-17-2016 |
| 20160083070 | BEAM FLANGE CLAMP, STRUCTURAL BEAM JOINT WITH BEAM FLANGE CLAMPS AND METHOD FOR FORMING A STRUCTURAL BEAM JOINT - A beam flange clamp includes a clamp body having a first vise jaw portion with a first gripping surface and a second vise jaw portion with a second gripping surface. The first gripping surface and the second gripping surface are oriented parallel to each other, are facing the same direction and are offset in height by a predetermined clamping distance. The at least one bolting hole is formed through the first vise jaw portion perpendicularly to the first gripping surface. | 03-24-2016 |
| 20160084285 | BEAM FLANGE CLAMP, STRUCTURAL BEAM JOINT WITH BEAM FLANGE CLAMPS AND METHOD FOR FORMING A STRUCTURAL BEAM JOINT - A beam flange clamp includes a clamp body having a first vise jaw portion with a first gripping surface and a second vise jaw portion with a second gripping surface. The first gripping surface and the second gripping surface are oriented parallel to each other and are offset in height by a predetermined clamping distance. The clamp body further including a bolting portion protruding from the second vise jaw portion opposite of the first vise jaw portion, and at least one bolting hole is formed through the bolting portion. | 03-24-2016 |
| 20160089851 | NONWOVEN DECORATIVE LAMINATES AND METHODS OF MAKING THE SAME - A decorative laminate for application to a structural component is provided. The decorative laminate has a substrate layer of a nonwoven fabric material with or without a flame retardant material. The decorative laminate further has an embossable layer disposed upon the substrate layer. The embossable layer includes an embossing resin material and the flame retardant material. The decorative laminate further has a protective layer disposed upon the embossable layer. The protective layer includes a polyvinyl fluoride-based material and has a decorative material printed on a first side of the protective layer facing the embossable layer. An adhesive layer is applied to the substrate layer of the decorative laminate. The decorative laminate is applied to the structural component with the substrate layer facing a bonding surface of the structural component and with an adhesive layer applied between the decorative laminate and the bonding surface of the structural component. | 03-31-2016 |
| 20160089856 | COMPOSITE STRUCTURES HAVING REDUCED AREA RADIUS FILLERS AND METHODS OF FORMING THE SAME - A composite structure having a base charge and an outer channel charge is provided. The outer channel charge has an inner radius and an outer radius. A charge of plies adjacent to the inner radius reduces the inner radius. | 03-31-2016 |
| 20160107743 | PANEL STRUCTURE AND ASSOCIATED METHOD - A panel structure for a vehicle, and especially for an aircraft or spacecraft, includes an area member, especially a skin member, that defines an areal expanse with a first surface and an opposite second surface and having a thickness between the first and second surfaces; and a plurality of elongate stiffener members which are attached to the area member and extend over at least one of the first and second surfaces; wherein at least one of the stiffener members is bifurcated at a bifurcation point into two or more branch stiffener members. | 04-21-2016 |
| 20160107753 | SEAT FASTENING SYSTEM, SEAT OR SEAT GROUP, AIRCRAFT CABIN, AND METHOD FOR FASTENING A SEAT OR A SEAT GROUP - In order to reduce weight, simplify the mounting of a seat or a seat group, and increase the flexibility in the cabin, a seat fastening system for a seat or a seat group of an aircraft comprises at least one mounting plate configured to attach the seat or the seat group to an aircraft structure of the aircraft, and at least one fastening module configured to fasten the seat or the seat group to the mounting plate. | 04-21-2016 |
| 20160129985 | AIRCRAFT STRUCTURE HAVING CABLES LOCATED IN STRINGERS - An aircraft structure having cables located in stringers is disclosed. According to one embodiment, the aircraft structure includes a stringer having a hollow channel. Further, one or more cables are located within the hollow channel. In one example, the one or more cables are capable of carrying a number of signals. | 05-12-2016 |
| 20160129986 | FUSELAGE WITH STRUCTURAL AND NON-STRUCTURAL STANCHIONS - A fuselage portion of a vehicle (e.g., an aircraft) is disclosed. The fuselage portion comprises a frame; a floor beam attached to the frame and comprising ends; a structural stanchion comprising a first end and a second end; a first structural coupling joining the first end of the structural stanchion and the floor beam; a second structural coupling joining the second end of the structural stanchion and the frame; a non-structural stanchion comprising a third end and a fourth end; a first non-structural coupling joining the third end of the non-structural stanchion and the floor beam; and a second non-structural coupling joining the fourth end of the non-structural stanchion and the frame. | 05-12-2016 |
| 20160129987 | INJECTION MOLDING METHOD FOR THE MANUFACTURE OF A PRIMARY-STRUCTURE CONNECTION ELEMENT - An aircraft including a primary-structure connection element for attaching the aircraft skin to the primary structure of the aircraft is provided. The primary-structure connection element is designed as a shearweb, a clip and/or as a frame stabilization element or as a rib stabilization element and is manufactured from a fiber-reinforced thermoplastic material with the use of injection molding. Likewise, an injection molding method for the manufacture of such a primary-structure connection element is provided, in which method the fiber-reinforced thermoplastic material is injected in its melted state into an injection molding device. The manufactured shearweb etc. is removed from the injection molding device. In this method, in particular, chopped carbon fibers and/or glass fibers in combination with polyphenylene sulfide (PPS) and/or polyetherether ketone (PEEK) are used, for example also in pellet form. | 05-12-2016 |
| 20160144945 | FLOOR PANEL RETENTION SYSTEM - A floor panel assembly is used with a floor panel retention system that includes a first retaining element, a second retaining element, and a support element. The floor panel assembly includes a floor panel including a first side edge and an opposing second side edge. The floor panel is configured to rest on the support element. The floor panel assembly also includes at least one tab coupled to the floor panel proximate the first side edge. The tab is configured to engage the first retaining element. The floor panel assembly also includes a latch coupled to the floor panel proximate the second side edge. The latch is configured to selectively engage the second retaining element. | 05-26-2016 |
| 20160152314 | Composite Structural Component | 06-02-2016 |
| 20160176498 | Method and System for Insulating Frame Member | 06-23-2016 |
| 20160185437 | TAIL CONE OF AN AIRCRAFT - A tail cone of an aircraft, more specifically a tail cone made of composite materials comprising an internal skin, an external skin surrounding the internal skin, longitudinal structural members located on the inner face of the internal skin in the longitudinal direction of the tail cone, and transversal structural members located between the external skin and the internal skin in the transverse direction of the tail cone. | 06-30-2016 |
| 20160185438 | JOINT ASSEMBLY AND METHOD CONNECTING AN AIRCRAFT BELLY FAIRING TO THE FUSELAGE PROVIDED WITH A PARTICULARLY POSITIONED STRINGER - A joint assembly in an aircraft connecting a belly fairing to the fuselage of the aircraft. The belly fairing has a sewing angle connected to a main belly fairing section, while the fuselage has a fuselage skin with an exterior and an interior. The joint assembly includes a sewing angle with a flange connected to the fuselage skin exterior at a fixation zone of the fuselage skin, with the fixation zone being overlapped by the flange where it is connected thereto. The joint assembly further includes a stringer connected to the fuselage skin interior and overlapping the fixation zone. This joint assembly is less susceptible to vibrations. The disclosure herein also pertains to a method of providing such a joint assembly. | 06-30-2016 |
| 20160251071 | SPLICE JOINTS FOR COMPOSITE AIRCRAFT FUSELAGES AND OTHER STRUCTURES | 09-01-2016 |
| 20180022433 | AIRCRAFT WITH A FUSELAGE AND A COMPOSITE TAIL BOOM | 01-25-2018 |
| 20180022435 | SPACE FRAME FUSELAGE WITH PRESSURE MEMBRANE | 01-25-2018 |
| 20190144099 | FLOOR ASSEMBLY COMPRISING A MONOLITHIC FLOOR ELEMENT, AND AIRCRAFT REGION AND AIRCRAFT COMPRISING A FLOOR ASSEMBLY | 05-16-2019 |
