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2592results about "Fuselage frames" patented technology
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Unmanned aerial vehicle apparatus, system and method for retrieving data
InactiveUS6868314B1Unacceptable costHigh maintenance costFuselage framesDigital data processing detailsTerrainWireless transceiver
The present invention relates to a system for retrieving data from remote difficult to reach terrain, such as wilderness areas, etc. and in particular to a system comprised of one or more surface based data collectors in communication with one or more wireless transceivers adapted to transmit the collected data to an unmanned aerial vehicle adapted to fly within a predetermined distance from the data collector and receive data collected therefrom. The present invention further relates to an unmanned aerial vehicle adapted to fly a flight pattern relative to a moveable surface object or for controlling the position of a moveable surface object relative to the flight path of the unmanned aerial vehicle. Finally, the present invention relates to an improved unmanned aerial vehicle having airframe structural elements with electrical circuits adhered to the surfaces of the structural elements.
Owner:FRINK BENTLEY D
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.
Owner:THE BOEING CO
Friction welding metal components
InactiveUS6328261B1Additions can be avoidedPrevent skinFuselage framesWingsFriction weldingButt welding
A method of forming a structural airframe component for an aircraft and an airframe structural component The method includes placing at least two components (1,2) in abutting relationship with each other and joining them together by friction stir butt welding (3), and the structural airframe component comprises a component manufactured according to the method of the invention.
Owner:AIRBUS OPERATIONS LTD
Tubular members integrated to form a structure
InactiveUS7063763B2Eliminate needEffective carryFuselage framesAircraft stabilisationMechanical engineeringFilament winding
Integrally stiffened and formed, load carrying structures comprising a plurality of elongated thin-walled tubes placed co-extensively in a complementary side-by-side fashion which together form a hollow structure having a desired external contour. Integral skins forming the external and internal surfaces of the structure cooperatively therewith. The structure can be formed with an underlying internal support member spanning the interior of the load carrying structure, thereby connecting opposite sides of the structure together. Also, each of the tubes are wound with fibers in controlled orientations generally paralleling the direction of the loads applied to the tubes to optimize the strength to weight ratio of the tubes.
Owner:CHAPMAN JR W CULLEN
Multi-rotor safety shield
ActiveUS20160200415A1Rapid decent, and/orImprove usabilityFuselage framesFlying saucersPropellerEngineering
The Multi-Rotor Safety Shield (MRSS) provides a complete and substantial encasement system which can be secured about a Drone, protecting a multitude of aircraft components from contact with any outside disturbance and which can protect the sensitive components from dust, water, wind, rain, snow, fingers, toes, appendages of any kind, and atmospheric changes as example, from disabling the Drone and can protect people, places or things from high velocity spinning exposed rotor / propellers. The MRSS provides rigid non-permeable platform for attaching or incorporating additional safety devices as found in the Drone industry (or other industries) resulting in a safety device that completely prevents the loss a Drone due to the catastrophic failure of any Drone system or combination of systems which would typically result in rapid decent, and / or uncontrolled flight. The MRSS makes Drones safe near humans and safe to use around public gatherings, stadium events, accident scenes, disaster search and rescue and disaster relief, and indoors for the security and communications markets among others expanding the availability of Drones to further assist humanity.
Owner:ROTOR SHIELD LLC
System and method of forming structural assemblies with 3-D woven joint pre-forms
InactiveUS6849150B1Improve structural strengthEliminate needFuselage framesCylinder headsAdhesiveEngineering
A system and method for forming structural assemblies with 3-D woven joint pre-forms. The method of the present invention forms complex structural assemblies with pre-formed structures. Adhesive is applied between the preformed structures and uncured 3-D woven textile pre-forms. Then together the preformed structures and uncured resin impregnated 3-D woven textile are cured with heat and / or pressure to form the larger complex structural assemblies.
Owner:LOCKHEED MARTIN CORP
Lightweight ballistic resistant rigid structural panel
InactiveUS6825137B2Without sacrificing ballistic resistanceImprove fatigueFuselage framesFuselage bulkheadsAdhesiveEngineering
A lightweight ballistic resistant rigid structural panel especially for use in aircraft interiors is disclosed. The rigid structural panel is made up of a core layer including a plurality of sheets of flexible, high-tensile strength fabric interleaved with a plurality of sheets of a thermal-fusible film adhesive, and a sheet of cushioning material adhered to the plurality of sheets of flexible, high-tensile strength fabric. Fiber-reinforced face skins are adhered to exterior surfaces of the panel core for structural strength and rigidity. The rigid structural panel is capable of resisting ballistic attack from handguns and like weapons, while maintaining a high degree of strength and rigidity.
Owner:NORDISK AVIATION PRODS A S
Sidewall panel integrated with insulation and air ducts
A mobile platform interior panel is provided that includes a body formed by a low pressure injection process and at least one of a duct and a layer of insulation integrated with the body. The low pressure injection process allows the duct and insulation to be integrated with the body simultaneously with the forming of the panel. More specifically, the duct is integrated with the panel by forming at least one internal cavity within the panel as the panel is formed. Additionally, the insulation is integrated with the panel by forming the panel using a low pressure injection material having desired insulative properties.
Owner:THE BOEING CO
Transformable airplane
ActiveUS7093798B2Reconfigured easily and rapidlyLow costFuselage framesFuselage bulkheadsCommand and controlFlight vehicle
A transformable airplane may be reconfigured easily and rapidly to perform any one or a combination of tanking, transport, bombing, or command and control missions as desired for a tactical situation by installing or replacing mission-specific modules as desired. A reconfigurable aircraft includes a pair of wings and an aircraft body having at least one bay defined in an interior of the aircraft body. The at least one bay is configured to accept a plurality of removably replaceable modules that configure the aircraft to perform a plurality of missions. Transport mission modules may include space and tie-downs for cargo pallets and / or palletized seating. A roll-on / roll-off ramp may be provided. Tanking mission modules may include a remote aerial refueling operator station. Bombing mission modules may include a bomb rack and a bomb ejector. ISR mission modules may include command and control stations in signal communication with phased array antennas.
Owner:THE BOEING CO
Single piece fuselage barrel
In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.
Owner:THE BOEING CO
Method and apparatus for assembling a three-dimensional structural component
InactiveUS20010054228A1Precise tolerance rangeExact rangeFuselage framesAutomatic control devicesClassical mechanicsMechanical engineering
Three-dimensional large scale bodies such as jumbo aircraft fuselages (14) are assembled in body sections around a central longitudinal assembly core (1) which itself is mounted at its ends and accessible all around along its length. Robots carrying tools for holding, transporting and precisely positioning preassembled wall shell sections, are movable along the central core (1). First, at least one floor grid (2 or 3) is releasably mounted to the core. Then, side wall shell sections (4, 5) are secured to the floor grids. Then, top and bottom wall shell sections (10, 8) are secured to the side wall shell sections (4, 5) to form a body section (BS) of the large scale body (14). Neighboring body sections are secured to each other along cross-seams. Upon completion, the floor grids are released from the core (1) and the core is removed preferably withdrawn longitudinally from the assembled large component or body.
Owner:AIRBUS OPERATIONS GMBH
Composites joined with z-pin reinforcement
InactiveUS6436507B1Easy to manufactureLasting shelf-lifeFuselage framesLayered productsEngineeringBond line
Prefabricated composite detail parts use precured strips that include Z-pin reinforcement along the bond line. Each strip has Z-pin stubble protruding from opposed faces so that the pins are embedded into the detail parts when the joint forms.
Owner:THE BOEING CO
Line system for an aircraft
ActiveUS20080185478A1Reduce expensesReduce effortFuselage framesElectrical apparatusTransmitted powerEngineering
A line system for an aircraft, in particular an airplane, having multiple assemblies, in particular multiple fuselage sections of a fuselage cell and multiple wing shells, the line system including multiple lines for transmitting power and / or information, wherein the lines are integrated on and / or in a support layer, the support layer being situated on and / or in the shell-shaped assemblies.
Owner:AIRBUS OPERATIONS GMBH
Random-access multi-directional CDMA2000 turbo code interleaver
InactiveUS6871303B2Fuselage framesData representation error detection/correctionControl signalParallel computing
An interleaver that implements the LCS turbo interleaver algorithm utilized by the CDMA2000 standard is described. The interleaver includes a first computation unit for receiving an input address and computing a first sequential interleaved address during a first clock cycle in response thereto. A second computation unit is included for receiving an input address and computing a second sequential interleaved address during the first clock cycle in response thereto. The interleaver further includes a comparator for determining whether the first or the second sequential interleaved address is invalid and generating a signal in response thereto. The output of the comparator provides a control signal to a switch which selects the first or the second sequential interleaved address as an output interleaved address for the first clock cycle. The interleaver is further designed to move in a forward direction or a reverse direction.
Owner:QUALCOMM INC
One-piece closed-shape structure and method of forming same
The present invention relates to a one-piece closed-shape structure and a method for manufacturing a one-piece closed-shape structure. In particular, the present invention relates to a one-piece fuselage and a method for manufacturing a one-piece fuselage. One embodiment of the method of the invention involves the use of molding technology, tooling technology, the integration of the molding and tooling technology, and fiber placement to manufacture a one-piece closed shape structure.
Owner:TOYOTA MOTOR CO LTD
Titanium foil ply replacement in layup of composite skin
Laminate structures and methods for forming same are disclosed. In one embodiment, a laminate structure includes a metal-polymer composite lamina. The metal-polymer composite lamina has a first face and a second face spaced apart, and extends to a terminal edge. The lamina includes a ply of fiber-reinforced polymer that extends between the first face and the second face and has an interior edge. The interior edge defines at least one cutout. A ply of metal foil extends between the first face and the second face substantially from the interior edge filling the at least one cutout.
Owner:THE BOEING CO
Joining member for mechanically joining a skin to a supporting rib
InactiveUS7037568B1Reduce riskLess expensiveFuselage framesLayered productsSkin surfaceAdhesive materials
A joining member for mechanically joining a skin to a supporting rib has a first surface and a second surface opposite the first surface. The first surface is adapted for bonding to a surface of the skin via a layer of a first adhesive material. The second surface includes a groove having an inner surface adapted for receiving and bonding to an outer edge of the rib via a layer of a second adhesive material. The joining member enables a novel method of construction having advantages over the prior art.
Owner:ROGERS TERRY W +1
Method of constructing a fixed-wing aircraft
ActiveUS20110147521A1Easy to assembleShorten the timeFuselage framesAircraft stabilisationEngineeringFixed wing
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.
Owner:AIRBUS OPERATIONS (SAS)
Aircraft joint
InactiveUS20110089292A1Simplify the assembly processReduce in quantityFuselage framesAircraft stabilisationFuselageAirplane
A method of joining a wing to an aircraft fuselage by forming a series of pinned lug joints between a fuselage side and a wing side of a wing box structure. The joint forming process includes providing a single row of lugs on one side of the joint to be formed, and providing a respective double row of lugs on the other side of the joint to be formed. A gap between opposing lugs of the double row varies along the row. The wing side and the fuselage side of the wing box structure are brought together such that the lugs of the single row are located within the respective gaps between opposing lugs of the double row, and the lugs are pinned to form the series of pinned lug joints. Also, a joint formed by the method.
Owner:AIRBUS OPERATIONS LTD
Integral structural shell component for an aircraft and method of manufacturing the same
A structural panel component, such as an aircraft fuselage shell component, includes a single integral part having longitudinal and crosswise stiffening elements integrally arranged on a skin sheet. This integral component has been formed by a high speed milling chip removal process applied to a solid plate-shaped semi-finished starting material. The skin sheet has areas of differing thicknesses, and the height, thickness, and spacing of the stiffening elements varies as needed, depending on the local loading conditions that will prevail on the finished structural component. The configuration of the component can be optimized to minimize the weight while satisfying all load strength requirements. The manufacturing method is very simple and economical.
Owner:AIRBUS OPERATIONS GMBH
Unmanned aerial vehicle for logistical delivery
InactiveUS20050006525A1Safe and reliable and effective and economicalLow costFuselage framesGlidersNacelleRocket
A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and / or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and / or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.
Owner:US SEC THE NAVY CHIEF OF NAVAL RES OFFICE OF COUNSEL ATTN CODE OOCIP
Unmanned aerial vehicle for logistical delivery
InactiveUS7059566B2Safe and reliable and effective and economicalLow costFuselage framesGlidersNacelleRocket
Owner:US SEC THE NAVY CHIEF OF NAVAL RES OFFICE OF COUNSEL ATTN CODE OOCIP
Apparatus, system, and method of joining structural components with a tapered tension bond joint
InactiveUS7244487B2Enhanced ballistics survivabilityStop crackingFuselage framesAircraft stabilisationEngineeringHigh intensity
A system of composite and adhesive materials provides for a high strength, producible closeout joint in the form of tapered tension bond joint for high performance structures. The system includes one skin that is co-bonded to flat panel spars, with the joint being positioned at the opposite side of the spars. The spar includes a female receptacle that receives a male blade from the closeout skin assembly. The blade and receptacle are wedge-shaped woven preforms. The flat panel spars have imbedded nut elements that serve as “internal tooling” to provide a positive stop for locating and clamping the structural members together.
Owner:LOCKHEED MARTIN CORP
Impact resistant structure for the helicopter and energy absorber used for the same
InactiveUS6959894B2Improve performanceHarmful initial load peak level is reducedPortable framesFuselage framesNacelleEngineering
An impact resistant structure of a helicopter having an energy absorber positioned under a floor of the helicopter and directly connected to a cabin frame of the helicopter. The energy absorber is arranged in accordance with a distribution of a ground reaction force on a general ground at a time of crash situation. The energy absorber also includes a plurality of independent hollow tubes of fiber reinforced composite material integrally formed by bundling only the hollow tubes. The hollow tubes are arranged so as to reduce a number of intersecting wall surfaces of the hollow tubes.
Owner:KAWASAKI HEAVY IND LTD
Method for assembling a three-dimensional structural component
InactiveUS6408517B1Guaranteed accuracyImprove accessibilityFuselage framesAssembly machinesEngineeringFuselage
Three-dimensional large scale bodies such as jumbo aircraft fuselages (14) are assembled in body sections around a longitudinal central assembly core (1) which itself is mounted at its ends and accessible all around along its length. Robots carrying tools for holding, transporting and precisely positioning preassembled wall sections, are movable along the central assembly core (1). First, at least one floor support grid (2 or 3) is releasably mounted to the central assembly core. Then, side wall sections (4, 5) are first secured to the floor support grids. Then, top and bottom wall sections (10, 8) are secured to the side wall sections (4, 5) to form a body section (BS) of the large scale body (14). Neighboring body sections are secured to each other along cross-seams. Upon completion, the floor support grids are released from the central assembly core (1) and the core is removed preferably withdrawn longitudinally from the assembled large body.
Owner:AIRBUS OPERATIONS GMBH
Joint for Use in Aircraft Construction
A joint for use in aircraft construction, for example a wing, comprises: a cover skin having an interior surface, an exterior surface and a distal portion, said distal portion having an exterior-facing surface; and a butt-strap having a first portion for connection to the skin, said first portion having an interior surface, an exterior surface and a distal end. The first portion of the butt-strap is connected to the distal portion of the skin such that a junction is formed between the exterior surface of the skin and the exterior surface of the first portion of the butt-strap. The exterior-facing surface of the distal portion of the skin is of a shape complementary to the shape of the interior surface of the first portion of the butt-strap. The first portion of the butt-strap tapers towards its distal end such that, at said junction, the exterior surface of the skin and the exterior surface of the first portion of the butt-strap form a substantially continuous exterior surface.
Owner:AIRBUS OPERATIONS LTD
Mobile Platforms for Performing Operations Along an Exterior of a Fuselage Assembly
A method and apparatus for performing an assembly operation. A tool may be macro-positioned relative to an exterior of a fuselage assembly. The tool may be micro-positioned relative to a particular location on the exterior of the fuselage assembly. An assembly operation may be performed at the particular location on the panel using the tool.
Owner:THE BOEING CO
Multirotor flying vehicle
A multirotor flying vehicle including at least one rotor support frame organized on a geometric grid, with a plurality of rotor assemblies coupled to the at least one rotor support frame. At least one power supply is coupled to and powers the rotor assemblies. A control system is coupled to the rotor assemblies and is configured to operate the vehicle.
Owner:GEISE DAVID +1
Copper grid repair technique for lightning strike protection
ActiveUS20070177330A1Quick and cost-effective repairMaintain integrityFuselage framesAircraft lighting protectorsGlass fiberLightning strike
A method for reestablishing the electrical continuity of an electrically conductive layer of a composite aircraft wing damaged by a lightning strike or other mechanical event is disclosed in which a copper patch replaced the damaged section of the electrically conductive layer contained. The repair is performed by first removing any surfacers, fasteners, and damaged electrically conductive layer to expose a portion of the underlying composite skin. A copper patch having a copper foil section coupled to an unsupported film adhesive is then introduced onto an underlying composite skin opening contained within an undamaged section of a copper foil grid and covered with resin-impregnated fiberglass material. The film adhesive and resin-impregnated fiberglass material are then cured and fasteners are then reinserted within the fiberglass material, copper patch and underlying composite skin. The surface of the composite wing is then reprimed and repainted to complete the repair.
Owner:THE BOEING CO
Door Frame Compartment of Cast Titanium and Structural Fuselage Part
InactiveUS20090146008A1Low production costEasy maintenanceFuselage framesWindow/door framesFiberCarbon fibers
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.
Owner:AIRBUS OPERATIONS GMBH
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