Honeycomb Patents (Class 244/123.6)
-
Patent number: 9505491Abstract: A composite spar for a helicopter blade includes two or more layers of unidirectional laminate material. One or more upper plies of bi-directional laminate extend from an upper airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional laminate material. One or more lower plies of bi-directional laminate material extend from a lower airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional material. The upper plies and the lower plies overlap defining a crackstopper layer configured to prevent propagation of defects in the spar.Type: GrantFiled: August 19, 2011Date of Patent: November 29, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Francis Edward Byrnes, Jacob A. Fehrman
-
Patent number: 9370128Abstract: A display apparatus and a method of spreading heat in the display apparatus are provided. The display apparatus includes: a display panel which display an image on a front surface thereof; an intermediate panel disposed on a rear surface, opposite the front surface, of the display panel; and a heat spreader disposed on the rear surface of the intermediate panel and which spreads heat, the heat spreader extending in a longitudinal direction from a first position of the rear surface of the intermediate panel in which the heat is present to a second position of the rear surface of the intermediate panel.Type: GrantFiled: November 29, 2012Date of Patent: June 14, 2016Assignee: SAMSUNG ELECTRONICS CO., LTD.Inventors: Jung Kyun Kim, Sung Ki Kim, Sru Kim, Jin Hyun Cho
-
Patent number: 8951623Abstract: The invention pertains to a composite panel with a first cover layer, a second cover layer and a first core layer that is arranged between the first cover layer and the second cover layer and features a plurality of cells that are separated from one another by walls at least in certain areas, wherein the first cover layer features a draining layer. The inventive composite panel may be distinguished from a composite panel according to the state of the art in that a second core layer with a plurality of cells that are separated from one another by walls at least in certain areas is arranged between the first cover layer and the first core layer.Type: GrantFiled: March 19, 2009Date of Patent: February 10, 2015Assignee: Airbus Operations GmbHInventor: Stephan Hoetzeldt
-
Patent number: 8919376Abstract: A system and method to mitigate the effect of hydrodynamic ram. The system including a chamber adapted to receive fluid and a core disposed within the chamber. A plurality of columns extend through the core and a plurality of orifices extend through the thickness of the columns. The method includes channeling a portion of a vapor bubble to an ullage space disposed within the chamber with the plurality of columns and changing the fluid state of the vapor bubble with a plurality of orifices extending through the thickness of the plurality of columns.Type: GrantFiled: June 13, 2011Date of Patent: December 30, 2014Assignee: Textron Innovations Inc.Inventor: Chad Elliot Sparks
-
Patent number: 8800922Abstract: The description covers cabin components for aircraft, which can be produced with a sandwich structure and may have the components 1003 for signal and/or power transmission. The cabin components in this case have at least two prepreg layers 1001, 1005 and, for example, a honeycomb layer 1002, which can be connected to one another by pressing and heating. Furthermore, electrical and/or optical signal paths are shown on cabin components, which can be produced by positioning them there or printing. In addition, according to the description, signal and/or power transmission can take place beyond the boundary of cabin components, by means of a transmitter/receiver path.Type: GrantFiled: July 13, 2011Date of Patent: August 12, 2014Assignees: Diehl Aircabin GmbH, Diehl Aerospace GmbHInventors: Frank Schmid, Marc Renz, Norbert Knopp, Jürgen Grabmann, Dietmar Völkle, Markus Klingseis, Wolf-Dieter Kuhnla, Ralph Pätzold, Dirk-Achim Schevardo, Peter Younes
-
Patent number: 8245972Abstract: A leading edge structure includes two or more multilayer panels at least partially overlapping and suitably curved with at least partially congruent concavities. Each multilayer panel includes at least the following three layers: a first metal foil layer metal foil, a second intermediate layer of fiber-glass securely fixed to the first layer, and a third metal honeycomb layer securely fixed to the second layer.Type: GrantFiled: December 9, 2009Date of Patent: August 21, 2012Assignee: Alenia Aeronautica S.p.A.Inventors: Luigi Capasso, Marco Fassero, Massimo Riccio, Ernesto Rinaldi, Salvatore Russo
-
Patent number: 8186631Abstract: An aerofoil member is described which provides for a ‘smart Core’and flexible skin. The core comprises sheet material elements forming adjoining cells. The length of the elements can be changed, for example, using the piezo-electric effect, to alter the cross-sectional shape of the aerofoil without changing the peripheral length. Thus, the shape of the aerofoil may be changed to suit different flight conditions, or to mimic the effect of control surfaces.Type: GrantFiled: June 8, 2009Date of Patent: May 29, 2012Assignee: Imperial Innovations LimitedInventor: Lorenzo Iannucci
-
Patent number: 8167245Abstract: Embodiments of the present disclosure provide an apparatus, method, and system for managing deflections comprising a fuel dam, a first portion of the fuel dam connected with a stringer, a second portion of the fuel dam connected with the first portion, and a third portion of the fuel dam. The second portion is more flexible than the first portion. The third portion is connected with the second portion, and connected with a rib. The second portion accommodates deflection between the stringer and the rib.Type: GrantFiled: November 3, 2009Date of Patent: May 1, 2012Assignee: The Boeing CompanyInventors: Thomas A. Koehler, Richard Bruce Tanner
-
Patent number: 8091829Abstract: A lifting structure for aircraft is essentially applicable to a horizontal stabilizer that includes two side symmetrical boxes that converge at one end (its root) thereof in a shared center area in order to connect integrally in the central area. Both boxes connect by a single part that constitutes a center rib with a double T-shaped profile. The root of the side boxes overlap converging on the inside surfaces of the wings of the center rib. The connection is ensured with rivets (lap joint). The proposed connection simplifies the assembly process (single part) and lead to a weight reduction since a carbon fiber connecting rib can be used.Type: GrantFiled: March 10, 2008Date of Patent: January 10, 2012Assignee: Airbus Operations, S.L.Inventors: Gonzalo Ramírez Blanco, Daniel Barroso Vloedgraven, Jose Luis Lozano García, Miguel Luque Buzo
-
Patent number: 8084114Abstract: A composite member with a reinforced rampdown or taper has a composite noodle bonded to an end of a core to fill the taper.Type: GrantFiled: December 27, 2007Date of Patent: December 27, 2011Assignee: The Boeing CompanyInventors: Douglas L. Grose, Marc J. Piehl, Douglas A. Frisch, Joseph L. Sweetin, Gary J. Peffers
-
Publication number: 20110114791Abstract: A panel structure includes a composite facesheet and a stiffening core having a plurality of core members in an intersecting web configuration provided on the composite facesheet.Type: ApplicationFiled: February 2, 2010Publication date: May 19, 2011Inventors: Christopher P. Henry, Sloan P. Smith, Andrew C. Keefe
-
Patent number: 7662459Abstract: A thermal protection system for atmospheric entry of a vehicle, the system including a honeycomb structure with selected cross sectional shapes that receives and holds thermally cured thermal protection (TP) blocks that have corresponding cross sectional shapes. Material composition for TP blocks in different locations can be varied to account for different atmospheric heating characteristics at the different locations. TP block side walls may be attached to all, or to less than all, the corresponding honeycomb structure side walls.Type: GrantFiled: July 17, 2008Date of Patent: February 16, 2010Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration (NASA)Inventor: Peter T. Zell
-
Patent number: 7090167Abstract: A vessel, such as a wing-integrated aircraft fuel tank. The vessel can include a first surface portion, a second surface portion spaced apart from the first surface portion, and a core positioned between the first and second surface portions. The core can be sealably connected to the first and second surface portions and can be positioned to carry a load from at least one of the first and second surface portions to the other. The core can include a plurality of cells separated by cell walls, at least some of which have wall openings positioned to provide liquid communication between adjacent cells.Type: GrantFiled: June 24, 2005Date of Patent: August 15, 2006Assignee: The Boeing CompanyInventors: Stephen D. Friddell, Alan K. Prichard