US2693922A - Leading edge structure for airfoil - Google Patents

Leading edge structure for airfoil Download PDF

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Publication number
US2693922A
US2693922A US267252A US26725252A US2693922A US 2693922 A US2693922 A US 2693922A US 267252 A US267252 A US 267252A US 26725252 A US26725252 A US 26725252A US 2693922 A US2693922 A US 2693922A
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United States
Prior art keywords
leading edge
edge structure
metal sheet
skin
airfoil
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Expired - Lifetime
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US267252A
Inventor
John M Ellison
Raymond J Moore
Russell J Pease
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Northrop Grumman Corp
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Northrop Grumman Corp
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Priority to US267252A priority Critical patent/US2693922A/en
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Publication of US2693922A publication Critical patent/US2693922A/en
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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01G—CAPACITORS; CAPACITORS, RECTIFIERS, DETECTORS, SWITCHING DEVICES OR LIGHT-SENSITIVE DEVICES, OF THE ELECTROLYTIC TYPE
    • H01G2/00—Details of capacitors not covered by a single one of groups H01G4/00-H01G11/00
    • H01G2/12—Protection against corrosion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
    • E04C2/02—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials
    • E04C2/26—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups
    • E04C2/284—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups at least one of the materials being insulating
    • E04C2/292—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups at least one of the materials being insulating composed of insulating material and sheet metal
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y10T428/24496—Foamed or cellular component
    • Y10T428/24504—Component comprises a polymer [e.g., rubber, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
    • Y10T428/249987—With nonvoid component of specified composition
    • Y10T428/24999—Inorganic
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31511—Of epoxy ether
    • Y10T428/31515—As intermediate layer
    • Y10T428/31522—Next to metal

Definitions

  • the present invention includes a metal sheet having a body of styrofoam bonded thereto with an adhesive having high strength bonding characteristics to both the metal and the styrofoam.
  • a preferred structural form of the invention is a sandwich, with styrofoam between two metal sheets and bonded to both. 'Ihe styrofoam stabilizes the sheet to which it is attached, the styrofoam core resisting the greater part of the shear stresses.
  • the single ligure shows an airplane leading edge member stiiened in accordance with the present invention.
  • 'Il'his cedge member is essentially a sandwich with one side c ose
  • a metal sheet 1 of aluminum alloy is formed into a conventional leading edge member 2 for an airplane control surface, for example, the member 2 having the customary laterally extending stitfeners 3 attached thereto inwardly and rearwardly of the leading edge 4.
  • An interior filler 5 of styrofoam (foamed polystyrene plastic) is cut from a block of the material to lit the interior of member 2.
  • the filler 5 is securely bonded to the interior surfaces of sheet 1 and to the front surfaces of lateral stiffeners 3.
  • a satisfactory strong bond to both metal and foam is obtained by the use of the following adhesive:
  • Epon L-l372 100% solids
  • methanol 8% of diethylenetriamine catalyst based on the resin content of the resultant solution United States Patent O 2,693,922 Patented Nov. 9, 1954 dimethyl methane.
  • the adhesive solution when applied has a viscosity of 32 seconds at 70+ as measured by a ZHAN viscosimeter.
  • This adhesive is placed between all metal and styrofoam surfaces to be bonded and allowed to air dry at room temperature for about five hours. No stresses should be applied for about 24 hours thereafter.
  • the resultant structure has been found to be stronger and lighter than the usual honeycomb core type of stffener heretofore used in similar structural members. It is also easier to cut, and to vfit into the member.
  • a stressed skin leading edge structure for aircraft wings and the like comprising a unitary metal sheet formed to define a spanwise extending hollow leading edge structure of airfoil cross section, a preformed core of low density material separately shaped to t and completely fill the hollow interior of said leading edge structure and forming the sole support for said skin, a layer of air drying adhesive between the interior surface of said metal sheet and the exterior surface of said core, the rear edges of said metal sheet being supported by spanwise extending stiifeners adapted to define faying edges for attaching said leading edge structure to the rcenter section of an aircraft wing or the like.

Description

Nov. 9, 1954 J M ELLlsoN ET Al.
LEADING EDGE STRUCTURE FOR AIRFOIL Filed Jan. 19, 1952 40//55/1/6 HOA/0 LEADING EDGE STRUCTURE FOR AIRFOIL `lohn M. Ellison, Gardena, Raymond I. Moore, Long Beach, and Russell J. Pease, Gardena, Calif., assgnors to Northrop Aircraft, Inc., Hawthorne, Calif., a corporation of California Application January 19, 1952, Serial No. 267,252
2 Claims. (Cl. 244-123) Our invention relates to sheet stiieners and more particularly to metal sheets having a backing of styrofoam, an extremely light expanded form of polystyrene plastic, bonded thereto.
In airplane structures, a multiplicity of skin stiifeners are utilized in what is well known as stressed skin construction. These stiffeners are usually in the form of ribs or light corrugated sheet attached to the inner side gif 1ihe airplane skin sheets exposed to the airstream in It is an object of the present invention to provide a sheet stiifener in contact with and securely bonded to substantially the entire free skin area of the sheet.
In brief the present invention includes a metal sheet having a body of styrofoam bonded thereto with an adhesive having high strength bonding characteristics to both the metal and the styrofoam. A preferred structural form of the invention is a sandwich, with styrofoam between two metal sheets and bonded to both. 'Ihe styrofoam stabilizes the sheet to which it is attached, the styrofoam core resisting the greater part of the shear stresses.
The single ligure shows an airplane leading edge member stiiened in accordance with the present invention. 'Il'his cedge member is essentially a sandwich with one side c ose In the gure, a metal sheet 1 of aluminum alloy is formed into a conventional leading edge member 2 for an airplane control surface, for example, the member 2 having the customary laterally extending stitfeners 3 attached thereto inwardly and rearwardly of the leading edge 4. An interior filler 5 of styrofoam (foamed polystyrene plastic) is cut from a block of the material to lit the interior of member 2. In order that maximum stilening be obtained, the filler 5 is securely bonded to the interior surfaces of sheet 1 and to the front surfaces of lateral stiffeners 3. A satisfactory strong bond to both metal and foam is obtained by the use of the following adhesive:
100 parts by weight of Epon L-l372 (100% solids) 76 parts by weight of methanol ,8% of diethylenetriamine catalyst based on the resin content of the resultant solution United States Patent O 2,693,922 Patented Nov. 9, 1954 dimethyl methane. The adhesive solution when applied has a viscosity of 32 seconds at 70+ as measured by a ZHAN viscosimeter.
The above adhesive is not per se a claimable part of the present invention; but forms the subject of the pending U. S. application Ser. No. 240,179, filed August 3, 1951, by Pease.
This adhesive is placed between all metal and styrofoam surfaces to be bonded and allowed to air dry at room temperature for about five hours. No stresses should be applied for about 24 hours thereafter. The resultant structure has been found to be stronger and lighter than the usual honeycomb core type of stffener heretofore used in similar structural members. It is also easier to cut, and to vfit into the member.
While in order to comply with the statute, the invention has been described in language more or less specic as to structural features, it is to be understood that the invention is not limited to the specific features shown, but that the means and construction herein disclosed comprise the preferred form of putting the invention into elfect, and the invention is therefore claimed in any of its forms or modifications within the legitimate and valid scope of the appended claims.
What is claimed is:
1. A stressed skin leading edge structure for aircraft wings and the like; comprising a unitary metal sheet formed to define a spanwise extending hollow leading edge structure of airfoil cross section, a preformed core of low density material separately shaped to t and completely fill the hollow interior of said leading edge structure and forming the sole support for said skin, a layer of air drying adhesive between the interior surface of said metal sheet and the exterior surface of said core, the rear edges of said metal sheet being supported by spanwise extending stiifeners adapted to define faying edges for attaching said leading edge structure to the rcenter section of an aircraft wing or the like.
2. A stressed skin leading edge structure according to claim 1 wherein said low density material is foamed polystyrene.
References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 1,507,143 Toussaint et al. Sept. 2, 1924 1,874,685 Wright Aug. 30, 1932 2,121,052 Roberts et al. June 21, 1938 2,414,125 Rheinfrank, Jr. lan. 14, 1947 2,461,761 Nye Feb. 15, 1949 2,484,141 Alex Oct. 11, 1949 2,511,816 Shaw .Tune 13,v 1950 2,512,996 Bixler June 27, 1950 2,548,447 Shokal et al Apr. 10, 1951 2,566,701 Griese Sept. 4, 1951 2,574,651 Meyers Nov. 13, 1951 2,576,073 Kropa et al. Nov. 20, 1951 2,596,818 Meyers May 13, 1952 2,613,893 Young Oct. 14, 1952 2,630,868 Ellenberger Mar. 10, 1953

Claims (1)

1. A STRESSED SKIN LEADING EDGE STRUCTURE FOR AIRCRAFT WINGS AND THE LIKE; COMPRISING A UNITARY METAL SHEET FORMED TO DEFINE A SPANWISE EXTENDING HOLLOW LEADING EDGE STRUCTURE OF AIRFOIL CROSS SECTION, A PREFORMED CORE OF LOW DENSITY MATERIAL SEPARATELY SHAPED TO FIT AND COMPLETELY FILL THE HOLLOW INTERIOR OF SAID LEADING EDGE STRUCTURE AND FORMING THE SOLE SUPPORT FOR SAID SKIN, A LAYER OF AIR DRYING ADHESIVE BETWEEN THE INTERIOR SURFACE OF SAID METAL SHEET AND THE EXTERIOR SURFACE OF SAID CORE, THE REAR EDGES OF SAID METAL SHEET BEING SUPPORTED BY SPANWISE EXTENDING STIFFENERS ADAPTED TO DEFINE FAYING EDGES FOR ATTACHING SAID LEADING EDGE STRUCTURE TO THE CENTER SECTION OF AN AIRCRAFT WING OR THE LIKE.
US267252A 1952-01-19 1952-01-19 Leading edge structure for airfoil Expired - Lifetime US2693922A (en)

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Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2771144A (en) * 1951-12-28 1956-11-20 Const Aeronautiques De Sud Oue Blades for rotary-wing aircraft
US2869336A (en) * 1955-08-15 1959-01-20 Gen Motors Corp Refrigerating apparatus
US2875117A (en) * 1955-08-29 1959-02-24 Haskelite Mfg Corp Multilaminar panel
US2928456A (en) * 1955-03-22 1960-03-15 Haskelite Mfg Corp Bonded laminated panel
US2941603A (en) * 1956-05-01 1960-06-21 Drago K Jovanovich Helicopter rotor blade
US2972559A (en) * 1957-06-10 1961-02-21 Architectural Porcelain Constr Method of making laminated panels with expanded polystyrene core
US3068043A (en) * 1959-12-16 1962-12-11 Porsche Kg Vehicle body of metal reinforced synthetic resin
US3087581A (en) * 1960-03-07 1963-04-30 Pitman Mfg Company Fiberglas structural member and method of making same
US3087571A (en) * 1959-05-05 1963-04-30 Bolt Beranek & Newman Apparatus for damping
US3123907A (en) * 1964-03-10 figures
US3229935A (en) * 1962-12-06 1966-01-18 August T Bellanca Aircraft wing construction
US3235040A (en) * 1963-05-03 1966-02-15 Dow Chemical Co Sandwich panel structure with edge trim
US3274046A (en) * 1958-10-06 1966-09-20 Owens Corning Fiberglass Corp Combined fiber and cellular article
US3301927A (en) * 1964-08-07 1967-01-31 Gen Dynamics Corp Method of molding a high strength, low density structure
US3640787A (en) * 1966-03-23 1972-02-08 Rudolf Heller Method of producing shaped bodies of low specific gravity
US3645481A (en) * 1970-04-22 1972-02-29 Lanier Ind Inc Airfoil structure
US3910531A (en) * 1972-10-17 1975-10-07 Aerospatiale Shell-type structure for light aircraft
US4167430A (en) * 1978-04-28 1979-09-11 General Dynamics Corporation Method for fabricating a composite bonded structure
US4671471A (en) * 1984-05-21 1987-06-09 Mitchell Wing, Inc. Foam reinforced aluminum wing structure
US4739722A (en) * 1987-01-08 1988-04-26 Rogstad Keith L Laminate structure and boat hull made therefrom
US4850297A (en) * 1987-01-08 1989-07-25 Rogstad Keith L Laminate structure and boat hull made therefrom
US4883552A (en) * 1986-12-05 1989-11-28 Phillips Petroleum Company Pultrusion process and apparatus
US5484257A (en) * 1995-02-06 1996-01-16 Osborn; Norbert L. Wind energy device
US5547629A (en) * 1994-09-27 1996-08-20 Competition Composites, Inc. Method for manufacturing a one-piece molded composite airfoil
US6739553B2 (en) 2000-04-05 2004-05-25 Bell Helicopter Textrom, Inc. K-spar configuration for bonded wing construction
EP1475304A1 (en) 2003-05-09 2004-11-10 Pilatus Flugzeugwerke Ag Aircraft wing
EP1770227A2 (en) * 2005-09-29 2007-04-04 Nikolaos Pantelelis Sandwich panel and method of its construction
US20100123042A1 (en) * 2008-11-18 2010-05-20 Ares Systems Group, Llc Devices, Systems and Methods for Modular Payload Integration for Unmanned Aerial Vehicles
US20110031759A1 (en) * 2009-08-05 2011-02-10 Nitto Denko Corporation Foam filling material for wind power generator blades, foam filling member for wind power generator blades, wind power generator blade, wind power generator, and method for producing the wind power generator blade
US20110095131A1 (en) * 2007-04-24 2011-04-28 The Boeing Company Energy absorbing impact band
US8282040B1 (en) * 2009-04-30 2012-10-09 Lockheed Martin Corporation Composite aircraft wing
US20140294593A1 (en) * 2011-11-01 2014-10-02 General Electric Company Wind turbine blades with cap-assisted bond configuration and associated bonding method
US20150353185A1 (en) * 2012-12-27 2015-12-10 European Aeronautic Defence And Space Company Eads France Energy absorption device for aircraft structural element
US20210340948A1 (en) * 2018-10-29 2021-11-04 Blade Dynamics Limited Wind turbine rotor blade assembly having a structural trailing edge

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1507143A (en) * 1922-03-01 1924-09-02 Jose Luis Sanchez Besa Aircraft construction
US1874685A (en) * 1930-05-23 1932-08-30 Curtiss Aeroplane & Motor Co Ribless wing
US2121052A (en) * 1934-01-15 1938-06-21 Rubatex Products Inc Pontoon, float, and the like
US2414125A (en) * 1943-06-25 1947-01-14 Jr George B Rheinfrank Structural material for aircraft
US2461761A (en) * 1945-02-02 1949-02-15 Us Rubber Co Method of making cellular resin material
US2484141A (en) * 1947-01-09 1949-10-11 United Aircraft Corp Skin stressed laminated fiberglas rotor blade
US2511816A (en) * 1950-06-13 Laminate
US2512996A (en) * 1947-06-11 1950-06-27 Devoe & Raynolds Co Epoxide compositions
US2548447A (en) * 1950-03-11 1951-04-10 Shell Dev Fluid compositions containing glycidyl polyethers
US2566701A (en) * 1946-10-23 1951-09-04 Curtiss Wright Corp Reinforcement for filled hollow steel blades
US2574651A (en) * 1947-05-02 1951-11-13 Piasecki Helicopter Corp Sustaining rotor blade
US2576073A (en) * 1946-01-19 1951-11-20 American Cyanamid Co Fabricated structure comprising porous compositions of matter
US2596818A (en) * 1947-05-08 1952-05-13 Piasecki Helicopter Corp Rotor blade
US2613893A (en) * 1948-04-01 1952-10-14 Curtiss Wright Corp Airfoil construction
US2630868A (en) * 1949-10-29 1953-03-10 Gen Electric Plastic rotor blade

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2511816A (en) * 1950-06-13 Laminate
US1507143A (en) * 1922-03-01 1924-09-02 Jose Luis Sanchez Besa Aircraft construction
US1874685A (en) * 1930-05-23 1932-08-30 Curtiss Aeroplane & Motor Co Ribless wing
US2121052A (en) * 1934-01-15 1938-06-21 Rubatex Products Inc Pontoon, float, and the like
US2414125A (en) * 1943-06-25 1947-01-14 Jr George B Rheinfrank Structural material for aircraft
US2461761A (en) * 1945-02-02 1949-02-15 Us Rubber Co Method of making cellular resin material
US2576073A (en) * 1946-01-19 1951-11-20 American Cyanamid Co Fabricated structure comprising porous compositions of matter
US2566701A (en) * 1946-10-23 1951-09-04 Curtiss Wright Corp Reinforcement for filled hollow steel blades
US2484141A (en) * 1947-01-09 1949-10-11 United Aircraft Corp Skin stressed laminated fiberglas rotor blade
US2574651A (en) * 1947-05-02 1951-11-13 Piasecki Helicopter Corp Sustaining rotor blade
US2596818A (en) * 1947-05-08 1952-05-13 Piasecki Helicopter Corp Rotor blade
US2512996A (en) * 1947-06-11 1950-06-27 Devoe & Raynolds Co Epoxide compositions
US2613893A (en) * 1948-04-01 1952-10-14 Curtiss Wright Corp Airfoil construction
US2630868A (en) * 1949-10-29 1953-03-10 Gen Electric Plastic rotor blade
US2548447A (en) * 1950-03-11 1951-04-10 Shell Dev Fluid compositions containing glycidyl polyethers

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3123907A (en) * 1964-03-10 figures
US2771144A (en) * 1951-12-28 1956-11-20 Const Aeronautiques De Sud Oue Blades for rotary-wing aircraft
US2928456A (en) * 1955-03-22 1960-03-15 Haskelite Mfg Corp Bonded laminated panel
US2869336A (en) * 1955-08-15 1959-01-20 Gen Motors Corp Refrigerating apparatus
US2875117A (en) * 1955-08-29 1959-02-24 Haskelite Mfg Corp Multilaminar panel
US2941603A (en) * 1956-05-01 1960-06-21 Drago K Jovanovich Helicopter rotor blade
US2972559A (en) * 1957-06-10 1961-02-21 Architectural Porcelain Constr Method of making laminated panels with expanded polystyrene core
US3274046A (en) * 1958-10-06 1966-09-20 Owens Corning Fiberglass Corp Combined fiber and cellular article
US3087571A (en) * 1959-05-05 1963-04-30 Bolt Beranek & Newman Apparatus for damping
US3068043A (en) * 1959-12-16 1962-12-11 Porsche Kg Vehicle body of metal reinforced synthetic resin
US3087581A (en) * 1960-03-07 1963-04-30 Pitman Mfg Company Fiberglas structural member and method of making same
US3229935A (en) * 1962-12-06 1966-01-18 August T Bellanca Aircraft wing construction
US3235040A (en) * 1963-05-03 1966-02-15 Dow Chemical Co Sandwich panel structure with edge trim
US3301927A (en) * 1964-08-07 1967-01-31 Gen Dynamics Corp Method of molding a high strength, low density structure
US3640787A (en) * 1966-03-23 1972-02-08 Rudolf Heller Method of producing shaped bodies of low specific gravity
US3645481A (en) * 1970-04-22 1972-02-29 Lanier Ind Inc Airfoil structure
US3910531A (en) * 1972-10-17 1975-10-07 Aerospatiale Shell-type structure for light aircraft
US4167430A (en) * 1978-04-28 1979-09-11 General Dynamics Corporation Method for fabricating a composite bonded structure
US4671471A (en) * 1984-05-21 1987-06-09 Mitchell Wing, Inc. Foam reinforced aluminum wing structure
US4883552A (en) * 1986-12-05 1989-11-28 Phillips Petroleum Company Pultrusion process and apparatus
US4850297A (en) * 1987-01-08 1989-07-25 Rogstad Keith L Laminate structure and boat hull made therefrom
US4739722A (en) * 1987-01-08 1988-04-26 Rogstad Keith L Laminate structure and boat hull made therefrom
US5547629A (en) * 1994-09-27 1996-08-20 Competition Composites, Inc. Method for manufacturing a one-piece molded composite airfoil
US5484257A (en) * 1995-02-06 1996-01-16 Osborn; Norbert L. Wind energy device
US6739553B2 (en) 2000-04-05 2004-05-25 Bell Helicopter Textrom, Inc. K-spar configuration for bonded wing construction
EP1475304A1 (en) 2003-05-09 2004-11-10 Pilatus Flugzeugwerke Ag Aircraft wing
WO2004098993A1 (en) * 2003-05-09 2004-11-18 Pilatus Flugzeugwerke Ag Aircraft wing
EP1770227A2 (en) * 2005-09-29 2007-04-04 Nikolaos Pantelelis Sandwich panel and method of its construction
EP1770227A3 (en) * 2005-09-29 2007-10-03 Nikolaos Pantelelis Sandwich panel and method of its construction
US20110095131A1 (en) * 2007-04-24 2011-04-28 The Boeing Company Energy absorbing impact band
US8066222B2 (en) * 2007-04-24 2011-11-29 The Boeing Company Energy absorbing impact band
US20100123042A1 (en) * 2008-11-18 2010-05-20 Ares Systems Group, Llc Devices, Systems and Methods for Modular Payload Integration for Unmanned Aerial Vehicles
US8256715B2 (en) * 2008-11-18 2012-09-04 Mavg, Llc Devices, systems and methods for modular payload integration for unmanned aerial vehicles
US8282040B1 (en) * 2009-04-30 2012-10-09 Lockheed Martin Corporation Composite aircraft wing
US20110031759A1 (en) * 2009-08-05 2011-02-10 Nitto Denko Corporation Foam filling material for wind power generator blades, foam filling member for wind power generator blades, wind power generator blade, wind power generator, and method for producing the wind power generator blade
US20140294593A1 (en) * 2011-11-01 2014-10-02 General Electric Company Wind turbine blades with cap-assisted bond configuration and associated bonding method
US9702339B2 (en) * 2011-11-01 2017-07-11 General Electric Company Wind turbine blades with cap-assisted bond configuration and associated bonding method
US20150353185A1 (en) * 2012-12-27 2015-12-10 European Aeronautic Defence And Space Company Eads France Energy absorption device for aircraft structural element
US10029441B2 (en) * 2012-12-27 2018-07-24 Airbus Energy absorption device for aircraft structural element
US20210340948A1 (en) * 2018-10-29 2021-11-04 Blade Dynamics Limited Wind turbine rotor blade assembly having a structural trailing edge
US11879426B2 (en) * 2018-10-29 2024-01-23 Blade Dynamics Limited Wind turbine rotor blade assembly having a structural trailing edge

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