FR3069185B1 - Profil aerodynamique a noyau creux oblong arrondi en materiau composite renforce par un textile a fibres unidirectionnelles - Google Patents
Profil aerodynamique a noyau creux oblong arrondi en materiau composite renforce par un textile a fibres unidirectionnelles Download PDFInfo
- Publication number
- FR3069185B1 FR3069185B1 FR1756807A FR1756807A FR3069185B1 FR 3069185 B1 FR3069185 B1 FR 3069185B1 FR 1756807 A FR1756807 A FR 1756807A FR 1756807 A FR1756807 A FR 1756807A FR 3069185 B1 FR3069185 B1 FR 3069185B1
- Authority
- FR
- France
- Prior art keywords
- hollow core
- profile
- composite material
- material reinforced
- unidirectional fiber
- 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.)
- Active
Links
- 239000000835 fiber Substances 0.000 title abstract 3
- 239000004753 textile Substances 0.000 title abstract 3
- 239000002131 composite material Substances 0.000 title abstract 2
- 230000002787 reinforcement Effects 0.000 abstract 1
- 239000012783 reinforcing fiber Substances 0.000 abstract 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/185—Spars
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
L'invention porte sur un profil aérodynamique, comportant une peau (6) définissant la surface extérieure dudit profil aérodynamique, un bord d'attaque (1), un bord de fuite (3) et une portion centrale (2) représentant au moins 50% de la corde du profil. Le profil comporte un noyau creux (5) en matériau composite renforcé par un textile à fibres unidirectionnelles. Le noyau creux présente en section une forme oblongue arrondie, notamment à chacune de ses extrémités. La peau (6) prend appui sur le noyau creux (5) sur la longueur de la portion centrale (2) dudit profil aérodynamique, tant à l'intrados qu'à l'extrados dudit profil. Le renfort par un textile à fibres unidirectionnelles permet une orientation adéquate de fibres de renfort pour optimiser des propriétés mécaniques dans certaines directions. La forme allongée le long de la corde du profil et arrondie du noyau creux (5) lui confère une grande résistance à la déformation.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1756807A FR3069185B1 (fr) | 2017-07-18 | 2017-07-18 | Profil aerodynamique a noyau creux oblong arrondi en materiau composite renforce par un textile a fibres unidirectionnelles |
US16/037,269 US11124285B2 (en) | 2017-07-18 | 2018-07-17 | Aerodynamic/hydrodynamic profile with a composite reinforced oblong foam core |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1756807A FR3069185B1 (fr) | 2017-07-18 | 2017-07-18 | Profil aerodynamique a noyau creux oblong arrondi en materiau composite renforce par un textile a fibres unidirectionnelles |
FR1756807 | 2017-07-18 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3069185A1 FR3069185A1 (fr) | 2019-01-25 |
FR3069185B1 true FR3069185B1 (fr) | 2020-07-24 |
Family
ID=59859346
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1756807A Active FR3069185B1 (fr) | 2017-07-18 | 2017-07-18 | Profil aerodynamique a noyau creux oblong arrondi en materiau composite renforce par un textile a fibres unidirectionnelles |
Country Status (2)
Country | Link |
---|---|
US (1) | US11124285B2 (fr) |
FR (1) | FR3069185B1 (fr) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB201522327D0 (en) * | 2015-12-17 | 2016-02-03 | Airbus Operations Ltd | Wing structure |
IL268846B (en) * | 2019-08-22 | 2022-09-01 | Israel Aerospace Ind Ltd | Composite structures for aerodynamic components |
CN110682544A (zh) * | 2019-10-08 | 2020-01-14 | 江西洪都航空工业集团有限责任公司 | 一种薄壁复合材料前缘整流罩的胶接模具及胶接方法 |
US20230078701A1 (en) * | 2021-09-13 | 2023-03-16 | Rohr, Inc. | Composite structure and method for forming same |
Family Cites Families (30)
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US2945655A (en) * | 1956-01-20 | 1960-07-19 | Boeing Co | Double skin airfoil structure |
US3519228A (en) * | 1967-09-29 | 1970-07-07 | Dow Chemical Co | Airfoil structure |
FR2381662A1 (fr) * | 1977-02-28 | 1978-09-22 | Aerospatiale | Pale, notamment pour un rotor d'helicoptere, et son procede de fabrication |
US4524499A (en) * | 1981-11-16 | 1985-06-25 | Trw Inc. | Method of fabricating an aircraft propeller assembly with composite blades |
US4538780A (en) * | 1983-09-26 | 1985-09-03 | The Boeing Company | Ultralight composite wing structure |
FR2617119B1 (fr) * | 1987-06-26 | 1989-12-01 | Aerospatiale | Pale en materiaux composites, a noyau structural et revetement d'habillage profile, et son procede de fabrication |
US5269657A (en) * | 1990-07-20 | 1993-12-14 | Marvin Garfinkle | Aerodynamically-stable airfoil spar |
US5430937A (en) * | 1994-07-15 | 1995-07-11 | United Technologies Corporation | Apparatus and methods for fabricating a helicopter main rotor blade |
CA2198717C (fr) * | 1994-08-31 | 2005-03-15 | William C. Reinfelder | Longeron composite renforce par fibres pour aeronef a voilure tournante et son procede de fabrication |
DE19528664C2 (de) * | 1995-08-04 | 1997-07-31 | Joachim Heyse | Tragkörper aus einem Verbundwerkstoff |
US6976829B2 (en) * | 2003-07-16 | 2005-12-20 | Sikorsky Aircraft Corporation | Rotor blade tip section |
US7165945B2 (en) * | 2003-08-22 | 2007-01-23 | Sikorsky Aircraft Corporation | Braided spar for a rotor blade and method of manufacture thereof |
US7547193B2 (en) * | 2005-07-22 | 2009-06-16 | Sikorsky Aircraft Corporation | Rotor blade assembly with high pitching moment airfoil section for a rotary wing aircraft |
US8114329B2 (en) * | 2008-03-03 | 2012-02-14 | Abe Karem | Wing and blade structure using pultruded composites |
CN102022254B (zh) * | 2009-09-23 | 2014-12-17 | 固瑞特模具(太仓)有限公司 | 风轮机叶片及其生产方法 |
US9156559B2 (en) * | 2011-10-19 | 2015-10-13 | The Boeing Company | Segmented aircraft wing having solar arrays |
CA2858829A1 (fr) * | 2011-12-12 | 2013-06-20 | Saab Ab | Structure d'aeronef possedant une couche de resine de liaison de renforcement a fibres non structurelles |
US10155298B2 (en) * | 2011-12-21 | 2018-12-18 | Sikorsky Aircraft Corporation | Alpha case removal process for a main rotor blade spar |
GB201217801D0 (en) * | 2012-10-05 | 2012-11-14 | Airbus Operations Ltd | An aircraft structure |
US9638048B2 (en) * | 2013-03-15 | 2017-05-02 | Bell Helicopter Textron Inc. | Systems and methods of constructing composite assemblies |
US10723438B2 (en) * | 2013-08-30 | 2020-07-28 | Bell Helicopter Textron Inc. | System and methods of constructing composite assemblies |
US20150266572A1 (en) * | 2014-03-21 | 2015-09-24 | Hamilton Sundstrand Corporation | Propeller blade having compliant spar core |
AT517198B1 (de) * | 2015-04-24 | 2021-12-15 | Facc Ag | Steuerflächenelement für ein Flugzeug |
FR3037315B1 (fr) * | 2015-06-15 | 2017-07-07 | Critt Materiaux Polymeres Composites | Procede de realisation d'une aile d'aeronef en materiau composite, aile d'aeronef obtenue a partir de ce procede |
GB201522327D0 (en) * | 2015-12-17 | 2016-02-03 | Airbus Operations Ltd | Wing structure |
US10239604B2 (en) * | 2016-05-21 | 2019-03-26 | Bell Helicopter Textron Inc. | Structurally biased proprotor blade assembly |
US10569906B2 (en) * | 2016-06-30 | 2020-02-25 | Sikorsky Aircraft Corporation | Apparatus and methods for making rotorcraft rotor blades |
GB2559132A (en) * | 2017-01-25 | 2018-08-01 | Broers Christopher | Fluid foil |
WO2019117304A1 (fr) * | 2017-12-14 | 2019-06-20 | 川崎重工業株式会社 | Giravion ayant un mécanisme de pas de pale variable |
EP3556544B1 (fr) * | 2018-04-17 | 2021-07-28 | Ratier-Figeac SAS | Longeron de pale d'hélice |
-
2017
- 2017-07-18 FR FR1756807A patent/FR3069185B1/fr active Active
-
2018
- 2018-07-17 US US16/037,269 patent/US11124285B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US20190023372A1 (en) | 2019-01-24 |
FR3069185A1 (fr) | 2019-01-25 |
US11124285B2 (en) | 2021-09-21 |
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