Fuselage And Body Construction Patents (Class 244/119)
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Patent number: 12221203Abstract: In an example, a method for installing a decoration panel in a ceiling assembly in an aircraft is disclosed. The method comprises removing a generic panel from the ceiling assembly to produce an opening in the ceiling assembly. The method also comprises inserting the decoration panel through the opening in the ceiling assembly. The method also comprises coupling the decoration panel to the ceiling assembly using a plurality of fasteners such that the decoration panel extends across the opening in the ceiling assembly. The plurality of fasteners includes a first type of fastener and a second type of fastener.Type: GrantFiled: February 13, 2024Date of Patent: February 11, 2025Assignee: The Boeing CompanyInventors: Jordan R. Brunner, Justin L. Tabora
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Patent number: 12187407Abstract: An aircraft including a fuselage including an opening and beams that are aligned and that are interrupted at the edges of the opening, a removable panel where for each pair of aligned beams of the fuselage interrupted at the opening a beam of the removable panel extends between the two beams of the pair and each end of the beam of the removable panel faces an end of a beam of the pair and at the end of at least one beam of the fuselage facing an end of a beam of the removable panel, fixing means providing a removable fixing between the ends.Type: GrantFiled: June 19, 2023Date of Patent: January 7, 2025Assignee: Airbus Operations SASInventors: Anthony Mertes, Patrick Lieven
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Patent number: 12187411Abstract: An aircraft floor including at least one hinge connecting movable and fixed floor parts, which has a pivot axis parallel to a longitudinal direction. The floor also includes at least two beams, each including first and second beam portions secured respectively to the fixed and movable floor parts and connected together by a pivot link, and at least one rail including at least one first rail portion secured to the movable floor part and at least one second rail portion secured to the fixed floor part of the floor, extending the first rail portion.Type: GrantFiled: November 11, 2022Date of Patent: January 7, 2025Assignee: AIRBUS OPERATIONS SASInventors: Benoit Orteu, Ludovic Mil, Lionel Laganier, Dominique Marty, Philippe Robert
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Patent number: 12179904Abstract: A compliant root structure for connecting an airfoil to a fuselage structure capable of dampening the dynamic response of the fuselage structure when the airfoil encounters abrupt aerodynamic loads due to a turbulent atmosphere. The compliant root structure includes a connecting arm(s) that pivotally connects the airfoil to the fuselage structure so that the airfoil can displace relative to the fuselage structure in the direction relatively perpendicular to the spanwise and chordwise axes of the airfoil. A restoring force can be provided by the compliant root structure (for example, by spring means) to the airfoil when it is displaced relative to the fuselage. In some embodiments, the connecting arms can exhibit relatively high flexibility, and can be adapted to interconnect the airfoil and the fuselage by means of rigid joints. The flexibility of these connecting arms may eliminate the need for a separate spring means.Type: GrantFiled: March 9, 2022Date of Patent: December 31, 2024Inventor: John Christian Colley
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Patent number: 12162600Abstract: An aircraft panel assembly with a panel and a plurality of stiffeners on the panel is disclosed. Each stiffener has an attachment part attached to the panel and a structural part spaced apart from the panel. A rib foot beam crosses the stiffeners at a series of intersections. At each intersection the rib foot beam is located between the panel and the structural part of a respective one of the stiffeners.Type: GrantFiled: May 13, 2020Date of Patent: December 10, 2024Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS OPERATIONS GmbHInventors: Chris Heaysman, John Martin Gaitonde, Hauke Seegel
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Patent number: 12151445Abstract: A composite skin is attached to an underlying structure by fasteners that are countersunk into the structure. The composite skin comprises a thermoplastic material that has been melted and formed into a countersink in the structure using a heated tool.Type: GrantFiled: September 28, 2022Date of Patent: November 26, 2024Assignee: The Boeing CompanyInventors: Gregory James Schoepen Hickman, Aaron Ross Cowin
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Patent number: 12138894Abstract: A method for stiffening a sheet element is provided. The method includes a first step of providing stiffening modules each having a flange and at least one web. The stiffening modules are attached to the sheet element sequentially along a load path, where the stiffening modules are connected to each other via their respective flanges for a positive, frictional and/or materially bonded connection to form a stiffening structure, such that the stiffening modules have a combined effect, specifically stiffening and reinforcing the sheet element. A stiffening structure for a sheet element is also provided that has a plurality of stiffening modules arranged sequentially, and to a stiffening system that includes a stiffening structure and a sheet element.Type: GrantFiled: July 12, 2021Date of Patent: November 12, 2024Assignee: Photon AGInventors: Thomas Dziekan, Uriel Tradowsky, Andreas Knaub, Robert Braun, Lukas Neumann, Holger Alder
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Patent number: 12134463Abstract: An aircraft including a main landing gear compartment which comprises a rear transverse wall, and a base wall forming a sealed barrier between a first, pressurized area and a second, non-pressurized area. The main landing gear compartment includes a body, produced in a single piece from composite material, separating the first, pressurized area and the second, non-pressurized area. The body includes a first part corresponding to the base wall, as well as a second part corresponding to the rear transverse wall. At least two longitudinal beams made of composite material, are connected to the body. This single body makes it possible to eliminate a large number of parts, to simplify the assembly process, and to reduce the duration thereof.Type: GrantFiled: September 9, 2022Date of Patent: November 5, 2024Assignee: AIRBUS OPERATIONS SASInventors: Matthieu Plet, Laurent Dubreuil, Alain Prudent, Xavier Matheis, Gilles Andrieu, Damien Desgaches
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Patent number: 12136408Abstract: The disclosure describes acoustic panels (such as for gas turbine engines) and techniques for forming acoustic panels. In some examples, the acoustic panel comprises a coversheet comprising an outer face, an inner face, and a plurality of apertures extend from the outer face to the inner face. The acoustic panel also comprises a 3D printed support layer comprising a polymer and defining a plurality of cell openings, wherein a first side of the support layer opposite the cell openings is coincident with the inner face of the coversheet, and wherein the 3D printed support layer is 3D printed directly onto the inner face of the coversheet.Type: GrantFiled: April 29, 2022Date of Patent: November 5, 2024Assignee: Rolls-Royce CorporationInventors: Benedict N. Hodgson, Jeff Higbie
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Patent number: 12103702Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising rotor blades; and at least one fuselage shield removably coupled to the fuselage at a location in alignment with the rotor blades along the lateral direction.Type: GrantFiled: October 15, 2020Date of Patent: October 1, 2024Assignee: General Electric CompanyInventors: David William Crall, Nicholas Joseph Kray, Douglas Duane Ward, Brandon Wayne Miller
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Patent number: 12077287Abstract: An aircraft wing structure (100) including a spar (101) and a systems module (200) that is releasably secured to brackets (300) on a first side of the spar (101) and the second, opposite side of the spar is configured to define a wall of a fuel tank of an aircraft wing.Type: GrantFiled: January 31, 2023Date of Patent: September 3, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: William Tulloch, Javier Ruiz De Pablo, Paul Dean, James Bird
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Patent number: 12065259Abstract: A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.Type: GrantFiled: September 30, 2020Date of Patent: August 20, 2024Assignee: Airbus Defence and Space GmbHInventors: Borja Sanz Lopez, Clemens Brand, Michael Jost, Winfried Lohmiller, Georg Söllinger, Dieter Grebner, Oliver Motlik
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Patent number: 12030613Abstract: Embodiments of the present invention discloses a wing detachment assembly and an aerial vehicle. The wing detachment assembly includes a first connecting portion and a second connecting portion, one of the first connecting portion and the second connecting portion being fixed on a wing and the other being fixed on a vehicle body. The second connecting portion includes a thumb wheel, the thumb wheel being provided with a threaded hole and being rotatably mounted on the vehicle body or the wing. The first connecting portion is threadedly connected to a threaded hole of the thumb wheel, the first connecting portion and the thumb wheel being fastened or detached when the thumb wheel is rotated. The aerial vehicle includes the foregoing wing detachment assembly. The wing detachment assembly and the aerial vehicle have the advantage of being convenient to detach and mount the wing.Type: GrantFiled: March 4, 2022Date of Patent: July 9, 2024Assignee: AUTEL ROBOTICS CO., LTD.Inventor: Yuanyuan Du
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Patent number: 12030652Abstract: An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h L .Type: GrantFiled: June 8, 2022Date of Patent: July 9, 2024Assignee: General Electric CompanyInventors: Keith Edward James Blodgett, William J. Bowden, Egbert Geertsema
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Patent number: 12024291Abstract: A component system for an aircraft, having at least one furnishing component, a plurality of component rails, a plurality of guide elements engageable with and movable relative to the component rails, a plurality of retaining elements connected to the guide elements and configured to be coupled to a hull structure of the aircraft or the at least one furnishing component, and a plurality of locking units arranged on the component rails and/or on the guide elements and configured to lock the guide elements to a particular rail. At least two component rails are arranged on the at least one furnishing component or the hull structure at a distance and parallel to each other such that the furnishing component is retractable via the component rails on guide elements or component rails that are spatially fixed in the aircraft and can be locked in a retracted position by the locking units.Type: GrantFiled: December 10, 2020Date of Patent: July 2, 2024Assignee: AIRBUS OPERATIONS GMBHInventors: Matthias Hegenbart, Peter Linde, Hermann Benthien, Alexander Horn, Florian Schmidt
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Patent number: 12027763Abstract: The embodiments are directed to protecting objects having sensitive electronics from electromagnetic energy radiation. An object with the sensitive electronics has a film applied to the object's outer surface. The film conforms to the object's outer surface contours. The film has a substrate foundation, an array in intimate adjacent contact with the substrate foundation. The array has a plurality of radio frequency (RF) witness films overlain on the substrate foundation. Each RF witness film in the plurality of RF witness films is equally-spaced from adjacent RF witness films.Type: GrantFiled: January 25, 2022Date of Patent: July 2, 2024Assignee: The United States of America, as represented by the Secretary of the NavyInventors: Zachary A. Sechrist, Christopher G. Yelton
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Patent number: 12017748Abstract: Fuselage barrel assemblies and methods of assembling fuselage barrel assemblies are disclosed herein. The fuselage barrel assemblies include a first barrel section and a second barrel section, which is interfaced with the first barrel section to define a barrel joint between the first barrel section and the second barrel section. The fuselage barrel assemblies also include a split longeron, which extends across the barrel joint and is attached to both the first barrel section and the second barrel section. The split longeron includes a first longeron section, which is attached to the first barrel section, and a second longeron section, which is attached to the second barrel section. The split longeron also includes a longeron joint that attaches the first longeron section to the second longeron section. The methods include methods of assembling the fuselage barrel assemblies.Type: GrantFiled: February 25, 2022Date of Patent: June 25, 2024Assignee: THE BOEING COMPANYInventors: Keith A. Christianson, Brent Edward Beneke, Soo H. Teoh, Drew-Daniel Keefe, Kyle Edward Lyon, Andrew Joseph Gubel
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Patent number: 12017800Abstract: [Object] To realize an improvement in design accuracy and a reduction in design time in a process of matching an equivalent cross-sectional area of a design shape of a supersonic aircraft to a target equivalent cross-sectional area in a sonic boom reduction method based on an equivalent cross-sectional area.Type: GrantFiled: February 21, 2019Date of Patent: June 25, 2024Assignee: Japan Aerospace Exploration AgencyInventor: Tatsunori Yuhara
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Patent number: 11999505Abstract: An unmanned vehicle includes a body and a gimbal assembly arranged at the body. The body includes a bottom cover arranged at a bottom of the body. The gimbal assembly includes a shock-absorbing structure arranged inside the body and fixedly mounted at an inner bottom wall of the bottom cover, and a gimbal arranged outside the body and coupled to the shock-absorbing structure. The inner bottom wall is arranged inside the body and faces towards a top of the body.Type: GrantFiled: February 9, 2021Date of Patent: June 4, 2024Assignee: SZ DJI TECHNOLOGY CO., LTD.Inventors: Zihan Chen, Dahu Pan
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Patent number: 12000455Abstract: A method that includes measuring vibration levels in a semiconductor manufacturing apparatus, determining one or more sections of the semiconductor manufacturing apparatus that vibrate at levels greater than a predetermined vibration level, and reducing the vibration levels in the one or more sections to be at or within the predetermined vibration level by coupling one or more weights to an external surface of the semiconductor manufacturing apparatus in the one or more sections.Type: GrantFiled: March 10, 2022Date of Patent: June 4, 2024Assignee: TAIWAN SEMICONDUCTOR MANUFACTURING COMPANY, LTD.Inventors: Yi Chen Ho, Chih Ping Liao, Chien Ting Lin, Jie-Ying Yang, Wei-Ming Wang, Ker-Hsun Liao, Chi-Hsun Lin
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Patent number: 11952101Abstract: An assembly integrates an aft wing spar root fitting to an aircraft fuselage when joining the aircraft wing to the aircraft body. The assembly provides structural strength to the connection between the aircraft wing and the aircraft body, provides corrosion prevention and provides improved inspection capabilities and repair capabilities to the aircraft wing and aircraft body connection.Type: GrantFiled: March 3, 2022Date of Patent: April 9, 2024Assignee: The Boeing CompanyInventors: Michael R. Rush, Orion P. Watson, Daniel H. Fletcher, Ryan A. Fear, Brent E. Beneke, David H. Leibov, Patricia W. Estell, Norma L Alvarez-Quinones, Soo H. Teoh, Jesse R. Wiseman, Mark E. Shadell, Mark R. Mclaughlin, Emmett A. Salisbury
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Patent number: 11952100Abstract: A joint for connecting a center wing box to a bulkhead of an aircraft. The joint includes a flex angle member with a first section shaped to abut against and be connected to the center wing box, a second section shaped to abut against and be connected to a first side of the deck of the bulkhead, and an intermediate rounded corner positioned between the first and second sections. First support members are attached to the center wing box at first pins and support a first side of the second section of the flex angle member. Second support members are attached to the web of the bulkhead at second pins and support a second side of the second section of the flex angle member. The first support members are positioned on a first side of the deck of the bulkhead and the second support members are positioned on an opposing second side of the deck.Type: GrantFiled: January 18, 2022Date of Patent: April 9, 2024Assignee: THE BOEING COMPANYInventors: David Leibov, Ryan Carruthers, Daniel Cox, Scott Michael Spencer, Nicholas Joseph Dominski, Jeffery M. Lazzaro, Roslyn Melookaran
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Patent number: 11946413Abstract: Provided is an inlet bulkhead for large diameter aircraft engines. The inlet bulkhead, in certain examples, includes an annular body having an outer flange, an inner flange, and a web having a first side and an opposing second side. The web extends from the outer flange to the inner flange. The bulkhead also includes at least one annular stiffener disposed on the first side, and multiple radial stiffeners disposed on the first side, each of which extend from the outer flange to the inner flange. The annular and radial stiffeners may be integrally formed with the web.Type: GrantFiled: July 29, 2019Date of Patent: April 2, 2024Assignee: The Boeing CompanyInventors: Janaka Wijesinghe, Andrew G. Rocha, Eric J. Zimney
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Patent number: 11945568Abstract: Embodiments for hybrid pressure deck of an aircraft. One embodiment is a pressure deck disposed over a main gear wheel well of an aircraft. The pressure deck includes longitudinal beams extending in a forward and aft direction between an aft wheel well bulkhead and a rear spar of the aircraft. The pressure deck also includes a web attached to an underside of the longitudinal beams. The web includes a flat web portion supported by transverse stiffeners extending in an inboard and outboard direction, and a curved web portion including arches configured to flex laterally from load in the inboard and outboard direction. A transition between the flat web portion and the curved web portion extends at least partially in the forward and aft direction of the aircraft.Type: GrantFiled: January 6, 2022Date of Patent: April 2, 2024Assignee: The Boeing CompanyInventors: Mark R. McLaughlin, David H. Leibov
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Patent number: 11945574Abstract: Aspects related to aircraft for commercial air travel and methods of manufacture. An aircraft includes a blended wing body, a single deck located within the blended wing body, wherein the single deck additionally includes a passenger compartment located in a lateral middle portion of the blended wing body and at least a cargo store located laterally outside the passenger compartment, and a landing gear, wherein the landing gear includes at least a nose gear located substantially forward of the single deck and at least a main gear located substantially aft of the single deck, wherein one or more of the at least a nose gear and the at least a main gear occupies a gear housing that overlaps with a plane coincident with at least a portion of the single deck.Type: GrantFiled: August 25, 2022Date of Patent: April 2, 2024Assignee: JetZero, Inc.Inventor: Mark A. Page
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Patent number: 11939059Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft, at least a rib, wherein the at least a rib runs longitudinally from fore to aft of the main body, and a plurality of transparent panels located in the top surface of the main body, wherein the plurality of transparent panels are located in channels, wherein the channels are separated by the at least a rib.Type: GrantFiled: December 28, 2022Date of Patent: March 26, 2024Inventor: Mark Allan Page
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Patent number: 11932374Abstract: A trunk route aircraft has at least one wing for supporting the aircraft during flight, and at least one propulsor for forward propulsion of the aircraft. The trunk route aircraft further includes a pressurized trunk route fuselage having a double-bubble cross-sectional shape and a generally vertically-oriented longitudinal bulkhead dividing the trunk route fuselage interior into two side-by-side trunk route payload compartments. The longitudinal bulkhead is loaded in tension when the trunk route fuselage is pressurized. The trunk route payload compartments are each configured to receive a plurality of lightweight ISO (International Organization for Standardization) geometry containers arranged end-to-end, or a plurality of container inserts arranged end-to-end, each container insert also configured to be received within the lightweight ISO-geometry container, or a combination of one or more lightweight ISO-geometry containers and one or more container inserts arranged end-to-end.Type: GrantFiled: November 1, 2019Date of Patent: March 19, 2024Assignee: The Boeing CompanyInventors: Mithra M. K. V. Sankrithi, Sergey D. Barmichev, Anapathur Ramesh
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Patent number: 11926431Abstract: Coupler assemblies are described that removably couple sides of an auxiliary fuel tank in a cargo area of an aircraft. In one embodiment, a first coupler of the coupler assemblies includes a first attachment member that supports a body with a hollow channel having a centerline disposed longitudinally in the fuselage between a first end and a second end, and a slot between an outer surface of the body and the hollow channel. A second coupler of the coupler assemblies includes an engagement member, a second attachment member, and an arm extending between the engagement member and the second attachment member. The engagement member is slidably received within the hollow channel from the first end, and fits slidably within the hollow channel to engage with the body of the first coupler, with the arm extending through the slot.Type: GrantFiled: January 6, 2022Date of Patent: March 12, 2024Assignee: The Boeing CompanyInventors: Sergey D. Barmichev, Gary P. Seagrave
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Patent number: 11919618Abstract: An aircraft pressurized cabin door (1) having an outer panel (2) and a door structure (3) including: two circumferential beams (4) fastened to the lateral edges of the door; a plurality of longitudinal beams (5a, 5b) which are arranged substantially perpendicularly between the circumferential beams (4) and are fastened to the outer panel (2), each longitudinal beam (5a, 5b) extending from one circumferential beam (4) to the other. At least one longitudinal beam (5b) is a beam that has a variable cross-section which increases from the ends (B, M) of the beam to the center (H, L) of the beam, with two bent support bars.Type: GrantFiled: November 30, 2020Date of Patent: March 5, 2024Assignee: LATECOEREInventors: Miloslav Klisky, Jean Michel Borlot, Josef Krena
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Patent number: 11912409Abstract: An unmanned aerial vehicle may include a fuselage and an anchor structure coupled to the fuselage and including a wing retention structure and a power module retention structure. The unmanned aerial vehicle may also include a wing releasably coupled to the wing retention structure, thereby coupling the wing to the fuselage, and a power module releasably coupled to the power module retention structure, thereby coupling the power module to the fuselage.Type: GrantFiled: April 19, 2021Date of Patent: February 27, 2024Assignee: Zipline International Inc.Inventors: Paul Perry, Zoltan Laszlo, Scott Parker, Nathan Goldsberry, Bryan Wade, Keenan Wyrobek, Brian Boomgaard, Zhefei Li, Sven Blaser
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Patent number: 11891178Abstract: A system for a blended wing body aircraft with a combustion engine is illustrated. The aircraft comprises a blended wing body, at least a fuel source located within the blended wing body and configured to store a fuel, wherein the fuel includes liquid hydrogen, and at least a propulsor configured to propel the blended wing body aircraft. The at least a propulsor comprises a combustion engine configured to burn the fuel from the fuel source and produce mechanical work to power the at least a propulsor.Type: GrantFiled: April 28, 2022Date of Patent: February 6, 2024Assignee: JETZERO, INC.Inventors: Ronald Tatsuji Kawai, Shailesh Atreya
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Patent number: 11891161Abstract: An aircraft includes a fuselage that provides an aircraft passenger cell and a plastically deformable protective body secured on the fuselage. The plastically deformable protective body can be secured on the bottom of the fuselage and/or laterally on the fuselage. The plastically deformable protective body can be secured releasably on the fuselage, for example, via a screw connection.Type: GrantFiled: December 13, 2021Date of Patent: February 6, 2024Assignee: DR. ING. H.C. F. PORSCHE AKTIENGESELLSCHAFTInventor: Stephan Andreas Huebner
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Patent number: 11884772Abstract: A polymer formed of at least one phenylphosphine oxide functional epoxide crosslinked with at least one phenylphosphine oxide amine such that the polymer has phosphorous concentrations of at least about 8 percent by weight, at least about 8.5 percent by weight, or any value or range of values therebetween.Type: GrantFiled: August 23, 2021Date of Patent: January 30, 2024Assignee: The University of Southern MississippiInventors: Witold K. Fuchs, Jeffrey Wiggins
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Patent number: 11878804Abstract: An emergency opening device of an aircraft door including a tubular actuating member (2); a resilient compression device; a retaining member for retaining the tubular actuating member (2), having a retaining wire (12) which, when the tubular actuating member (2) is in the retracted position, is held taut between a first attachment (14, 17) and a second attachment (16, 18); a release device which includes a cutting member (22) for transversely cutting the retaining wire (12).Type: GrantFiled: July 6, 2020Date of Patent: January 23, 2024Assignee: LATECOEREInventor: Sabastien Devillez
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Patent number: 11877380Abstract: A cable management system includes a mounting bracket having a backing plate, two face mounts, and a panel, said face mounts each include an orifice and an aperture of different inner diameter, said panel includes a number of openings and a number of holes of different inner diameter, a extender bracket includes two walls and two end pieces secured together, said walls and said end pieces each include an eyelet and a piercing of different inner diameter, a fastening member includes a backing plate insert for engaging with said orifice of said face mounts and said eyelet of said walls and said end pieces of said extender brackets, a screw hole formed in said fastening member and formed through said backing plate insert, and an inner thread formed in said fastening member and spaced from said screw hole and said backing plate insert for engaging with bolts.Type: GrantFiled: January 14, 2022Date of Patent: January 16, 2024Assignee: WANHO MANUFACTURING, LLC.Inventors: Arthur C. Gagnon, David Robert Elliott, Manoj Kurubur Venkateshappa
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Patent number: 11873111Abstract: Embodiments are directed to a fuel cell protection system comprising an aircraft fuselage having an inner surface and an outer surface, an attachment point mounted on the outer surface, an aircraft fuel cell spaced apart from the inner surface, and a plate positioned between the inner surface and the aircraft fuel system, the plate spaced apart from the inner surface to create a void space. The attachment point may be a cargo hook. The void space is configured to receive all or a portion of the cargo hook after a crash. The plate creating the void space may be a rigid material or may be a ballistic fabric material.Type: GrantFiled: January 7, 2021Date of Patent: January 16, 2024Assignee: Textron Innovations Inc.Inventors: Timothy Brian Carr, Douglas Howard Hamelwright, Joshua Andrew Emrich
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Patent number: 11866200Abstract: Systems and methods are provided for fabricating a fuselage of an aircraft. The method includes: disposing arcuate sections of fuselage at a track of a factory such that concavities of the arcuate sections of the fuselage face a floor of the factory, and bearing edges of the arcuate sections of fuselage directly contact the track; advancing the arcuate sections of fuselage synchronously along the track in a process direction; and performing work within concavities of the arcuate sections of fuselage during pauses between pulses of the arcuate section of fuselage via stations that are disposed beneath the concavities and that are directly mounted to the floor of the factory.Type: GrantFiled: November 10, 2021Date of Patent: January 9, 2024Assignee: The Boeing CompanyInventors: Daniel R. Smith, Darrell D. Jones
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Patent number: 11835072Abstract: An ultrasonic airflow severing resistance reducing device for vehicles, including an airflow severing blade assembly, shock-absorbing installation assemblies, ultrasonic vibration components, and a rubber sealing ring assembly; a bottom portion of the airflow severing assembly is provided with an accommodating cavity; a top end of each shock-absorbing installation assembly is fixedly connected to an inner cavity wall of the accommodating cavity; a bottom end of each shock-absorbing installation assembly is formed with a fixed installation bottom portion; the ultrasonic vibration components are installed on the inner cavity wall; the rubber sealing ring assembly is arranged and installed on the airflow severing blade assembly. The ultrasonic vibration components drive the airflow severing blade assembly to generate high frequency ultrasonic vibration to sever airflow.Type: GrantFiled: February 9, 2022Date of Patent: December 5, 2023Inventor: Lahui Tang
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Patent number: 11814174Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.Type: GrantFiled: October 15, 2020Date of Patent: November 14, 2023Assignee: General Electric CompanyInventors: David William Crall, Nicholas Joseph Kray, Douglas Duane Ward, Brandon Wayne Miller
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Patent number: 11807382Abstract: The present invention is directed to an apparatus for managing thermal energy of an electric aircraft energy source. Apparatus may include fins, which extend from a skin of electric aircraft. The energy source may bias or be adjacent to the fins so that heat energy may dissipate from the energy source and through the fins and, thus, the skin. A coolant may also be run through the apparatus, where the coolant may flow through channels that are disposed between the fins.Type: GrantFiled: May 27, 2022Date of Patent: November 7, 2023Assignee: BETA AIR, LLCInventors: Braedon Lohe, Sean Donovan, Sarah Overfield
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Patent number: 11781931Abstract: A method for loading an Unmanned Aerial Vehicle with one or more items is disclosed. The method includes positioning one or more items in specific positions within one of the Unmanned Aerial Vehicle and a container configured to be carried by the Unmanned Aerial Vehicle based on a Center of Gravity of each of the one or more items. The method also includes securing the one or more items in the specific positions within the one of the Unmanned Aerial Vehicle and the container to prevent the one or more items from shifting and changing a combined Center of Gravity of the one or more items combined with the one of the Unmanned Aerial Vehicle and the container during a flight of the Unmanned Aerial Vehicle.Type: GrantFiled: July 30, 2020Date of Patent: October 10, 2023Assignee: Metal Raptor, LLCInventor: Lee Priest
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Patent number: 11780583Abstract: Methods and systems for efficiently loading cargo transports, such as cargo aircraft, are described. The methods and systems rely upon payload profiles for various payloads where the payloads include repeatable payloads that have the same characteristics. Based on the payload profile, the payload is positioned at a designated location in an interior cargo bay of the cargo transport. The designated location is denoted by one or more pre-formed markings in the interior cargo bay that establish where a payload having the respective payload profile should be positioned in the bay. The payload can then be secured in the bay. Because the designated location accounts for centers of gravity, the payload can be loaded and secured in the bay without having to run various calculations each time a payload is loaded. Systems and methods related to how the payloads are packaged in an efficient, expeditious manner are also provided.Type: GrantFiled: June 27, 2022Date of Patent: October 10, 2023Assignee: ZSM Holdings LLCInventors: Etan D. Karni, Scott David Rewerts, Mark Emil Lundstrom
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Patent number: 11768125Abstract: A method for loading one of an Unmanned Aerial Vehicle (UAV) and a container for the Unmanned Aerial Vehicle with one or more items is disclosed. The method includes determining a Center of Gravity (COG) of the one or more items. The method also includes loading the one of the UAV and the container for the UAV with the one or more items based on the COG of the one or more items. The method further includes positioning one or more weights relative to the one or more items and relative to the one of the UAV and the container for the UAV such that a combined COG of the one or more items, the one of the UAV and the container for the UAV, and the one or more weights is positioned within a predetermined region relative to the one of the UAV and the container for the UAV.Type: GrantFiled: July 30, 2020Date of Patent: September 26, 2023Assignee: Metal Raptor, LLCInventor: Lee Priest
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Patent number: 11753140Abstract: An aircraft fuselage portion extending in a general longitudinal direction and comprising a fuselage structure comprising annular frames and a flat floor. The fuselage portion also comprises struts perpendicular to the floor in a nominal position and extending from the floor to a frame. Each strut comprises, in the vicinity of at least one of the ends thereof, a detachable link so that the strut can be moved relative to the fuselage structure or separated from the fuselage structure to temporarily grant access to a triangle area located between the frames, the floor and the struts in the nominal position. This allows access to be granted to the area in which the ducts must be installed in the aircraft, in particular, in the form of sets of ducts assembled prior to their installation in the fuselage.Type: GrantFiled: December 16, 2020Date of Patent: September 12, 2023Assignee: AIRBUS OPERATIONS SASInventors: Jean-Luc Maurel, Vincent Borrel, Laurent Feuillerac, Patrick Salgues, Vincent Auriac
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Patent number: 11725882Abstract: A rotor system including a rotor hub, a plurality of rotor blades supported by the rotor hub, and a fairing mounted to the rotor hub. The fairing includes an external surface exposed to an external airflow and an internal surface defining an interior portion. A component system is mounted to the rotor hub in the interior portion. The component system includes a first heat generating component and a second heat generating component spaced from the first heat generating component. A cooling duct is arranged between the first heat generating component and the second heat generating component.Type: GrantFiled: June 16, 2020Date of Patent: August 15, 2023Assignee: LOCKHEED MARTIN CORPORATIONInventors: William A. Welsh, Damaris R. Zachos
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Patent number: 11724791Abstract: A stringer runout configuration has a pair of fittings with each fitting having a fitting web that is configured for attachment to a stringer web of a stringer on opposite sides of a terminating end of the stringer. The stringer web has a terminating end with a curved configuration and base flanges with rounded terminating ends. Each fitting has a base flange that has a bottom surface with a first surface area and a second surface area positioned at different heights. The first surface area of each of the fittings is configured for attachment to a stringer base flange on opposite sides of a terminating end of the stringer. The second surface area of each of the fittings is configured for attachment to a composite panel surface adjacent the terminating end of the stringer. These and other detailed design features described herein enhance the capability of the runout configuration.Type: GrantFiled: October 8, 2019Date of Patent: August 15, 2023Assignee: The Boeing CompanyInventors: Andrew M. McLean, Clinton L. Johnson, Ryan S. McClarty, Andreas Panayi
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Patent number: 11719283Abstract: An engine that may comprise a first rotatable shaft, a second rotatable shaft, and a turnbuckle shaft. The first shaft rotatable may be disposed about a centerline axis and have threads disposed thereon. The second shaft rotatable may be disposed about the centerline axis and have threads disposed thereon. The turnbuckle shaft may be axially disposed between the first and second shafts, rotatable about the centerline axis, and have threads disposed thereon for engaging the threads of the first and second shafts. The first and second shafts may be drawn together by a force acting on the threads of at least one of the first and second shafts created by a rotation of the turnbuckle shaft relative to the at least one of the first and second shafts. The turnbuckle shaft may rotationally connect the first shaft and second shaft.Type: GrantFiled: April 9, 2019Date of Patent: August 8, 2023Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Brett Hartnagel, Ryan Humes
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Patent number: 11697486Abstract: Embodiments are directed to an aircraft fuselage comprises two keel beams and two roof beams. Each keel beam is formed as a single component having no joints. Each keel beam comprises a first portion that is configured to define a floor of an aircraft and a second portion that is configured to define a tail section of an aircraft. The second portion is positioned at an angle relative to the first portion. Each roof beam is coupled to the second portion of a corresponding keel beam at a point remote from the first portion. Each roof beam and a corresponding keel beam are positioned along a single butt line relative to an aircraft fuselage centerline. Frame members are coupled to both keel beams and both roof beams.Type: GrantFiled: October 9, 2019Date of Patent: July 11, 2023Assignee: Textron Innovations Inc.Inventors: Nicholas Ralph Carlson, William Anthony Amante, Timothy Brian Carr
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Patent number: 11673662Abstract: A telescoping tail assembly for use on an aircraft having a fore-aft length. The telescoping tail assembly includes a housing extending in an aftward direction, a tailboom slidable along the housing into various positions including an extended position and a retracted position and one or more control surfaces coupled to the tailboom. The tailboom increases the fore-aft length of the aircraft in the extended position and decreases the fore-aft length of the aircraft in the retracted position.Type: GrantFiled: January 5, 2022Date of Patent: June 13, 2023Assignee: Textron Innovations Inc.Inventor: Steven Ryan Schafer
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Patent number: 11667379Abstract: Systems, apparatus, and methods are provided for retrieving data from remotely deployed sensor systems. Flight control systems are also provided for maintaining the orientation of a high gain antenna affixed to an aircraft relative to a stationary or nearly stationary transceiver.Type: GrantFiled: November 17, 2020Date of Patent: June 6, 2023Assignee: The United States of America, as represented by the Secretary of the NavyInventor: Judah H. Milgram