US2693922A - Leading edge structure for airfoil - Google Patents
Leading edge structure for airfoil Download PDFInfo
- 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
- Authority
- US
- United States
- Prior art keywords
- leading edge
- edge structure
- metal sheet
- skin
- airfoil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 229910052751 metal Inorganic materials 0.000 claims description 13
- 239000002184 metal Substances 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 4
- 239000003351 stiffener Substances 0.000 claims description 3
- 239000004819 Drying adhesive Substances 0.000 claims description 2
- 238000007605 air drying Methods 0.000 claims description 2
- 229920006328 Styrofoam Polymers 0.000 description 8
- 239000008261 styrofoam Substances 0.000 description 8
- 239000000853 adhesive Substances 0.000 description 5
- 230000001070 adhesive effect Effects 0.000 description 5
- 241001427367 Gardena Species 0.000 description 2
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 229920006248 expandable polystyrene Polymers 0.000 description 2
- 239000000945 filler Substances 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 235000013175 Crataegus laevigata Nutrition 0.000 description 1
- RPNUMPOLZDHAAY-UHFFFAOYSA-N Diethylenetriamine Chemical compound NCCNCCN RPNUMPOLZDHAAY-UHFFFAOYSA-N 0.000 description 1
- 239000004793 Polystyrene Substances 0.000 description 1
- YSVZGWAJIHWNQK-UHFFFAOYSA-N [3-(hydroxymethyl)-2-bicyclo[2.2.1]heptanyl]methanol Chemical compound C1CC2C(CO)C(CO)C1C2 YSVZGWAJIHWNQK-UHFFFAOYSA-N 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 239000006262 metallic foam Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920002223 polystyrene Polymers 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01G—CAPACITORS; CAPACITORS, RECTIFIERS, DETECTORS, SWITCHING DEVICES, LIGHT-SENSITIVE OR TEMPERATURE-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.
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Architecture (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Laminated Bodies (AREA)
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.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US267252A US2693922A (en) | 1952-01-19 | 1952-01-19 | Leading edge structure for airfoil |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US267252A US2693922A (en) | 1952-01-19 | 1952-01-19 | Leading edge structure for airfoil |
Publications (1)
Publication Number | Publication Date |
---|---|
US2693922A true US2693922A (en) | 1954-11-09 |
Family
ID=23017972
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US267252A Expired - Lifetime US2693922A (en) | 1952-01-19 | 1952-01-19 | Leading edge structure for airfoil |
Country Status (1)
Country | Link |
---|---|
US (1) | US2693922A (en) |
Cited By (34)
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 |
US3087571A (en) * | 1959-05-05 | 1963-04-30 | Bolt Beranek & Newman | Apparatus for damping |
US3087581A (en) * | 1960-03-07 | 1963-04-30 | Pitman Mfg Company | Fiberglas structural member and method of making same |
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)
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 |
-
1952
- 1952-01-19 US US267252A patent/US2693922A/en not_active Expired - Lifetime
Patent Citations (15)
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)
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 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2693922A (en) | Leading edge structure for airfoil | |
US4188171A (en) | Rotor blade internal damper | |
CN107571985A (en) | A kind of ultralight whole wing structure of truss-like | |
US3273833A (en) | Airfoil structure | |
US4284443A (en) | Single stage hot bonding method for producing composite honeycomb core structures | |
GB1060421A (en) | Rotor blade for a rotary wing aircraft | |
CN103466074B (en) | A kind of carrier-borne net that hits reclaims unmanned plane | |
US2236482A (en) | Airplane cabin | |
US3645481A (en) | Airfoil structure | |
CN107726926B (en) | A kind of stealthy/force-bearing type structure aerofoil | |
US1814556A (en) | Airplane construction and method therefor | |
US3305196A (en) | Vehicular structures made from foamed plastic materials | |
US4927100A (en) | Airfoil configuration | |
US2389210A (en) | Airplane wing or fin with improved airfoil characteristics | |
US3310117A (en) | Helicopter spar having integral mass and stiffness control provisions | |
US2574651A (en) | Sustaining rotor blade | |
US2644537A (en) | Spar type rotor blade | |
US3724123A (en) | Flying model airplane | |
US3123144A (en) | Znventors | |
US1771567A (en) | Airplane wing | |
US2477113A (en) | Rotor blade for rotative winged aircraft | |
US1790894A (en) | Seaplane | |
US1789288A (en) | Manufacturing material for airplane uses | |
KR200288482Y1 (en) | wing of model plane using styrofoam | |
JP2002299937A (en) | Constituent material of radome for flaying object |