WO1981000993A1 - Bord d'attaque composite pour avion - Google Patents

Bord d'attaque composite pour avion Download PDF

Info

Publication number
WO1981000993A1
WO1981000993A1 PCT/US1980/001095 US8001095W WO8100993A1 WO 1981000993 A1 WO1981000993 A1 WO 1981000993A1 US 8001095 W US8001095 W US 8001095W WO 8100993 A1 WO8100993 A1 WO 8100993A1
Authority
WO
WIPO (PCT)
Prior art keywords
component
leading edge
aircraft
deicer
shoe
Prior art date
Application number
PCT/US1980/001095
Other languages
English (en)
Inventor
T Blaser
N Weisend
Original Assignee
Goodrich Co B F
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Goodrich Co B F filed Critical Goodrich Co B F
Priority to BR8008855A priority Critical patent/BR8008855A/pt
Priority to AU63915/80A priority patent/AU6391580A/en
Publication of WO1981000993A1 publication Critical patent/WO1981000993A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/16—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means
    • B64D15/166—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means using pneumatic boots
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
    • H01Q1/422—Housings not intimately mechanically associated with radiating elements, e.g. radome comprising two or more layers of dielectric material

Definitions

  • COMPOSITE LEADING EDGE FOR AIRCRAFT BACKGROUND The invention relates to leading edges of aircraft sections and particularly to such leading edges which include rubber coverings such as deicer or erosion shoes or boots.
  • boots or “blankets” are often attached along leading edges of aircraft sections through use of a suitable adhesive or cement disposed between the outer surface of the section leading edge portion and the inner surface of the rubber component. Actual application of the rubber component to the leading edge portion is sometimes performed in the field or may be done in the factory of the rubber component manufacturer who is furnished all or a portion of an appropriate aircraft section structure in order to apply the component.
  • leading edge portion for a selected section of an aircraft which leading edge portion is a molded non-metallic composite member consisting of an inner rigid component and an outer sheet-like flexible elastomeric component.
  • the composite is shaped and formed in a mold with the rigid component forming to substantially the leading edge contour and the elastomeric component mold bonding to the outer surface of the inner component and conforming to the proper aerodynamic contour.
  • the outer surface of the outer rubber component forms substantially free of surface irregularities or wrinkles due to the fact that substantially all irregularities of the elastomeric component occur along the interface of its inner surface and the rigid component outer surface.
  • molded composites are readily installed to function as the leading edge of a selected aircraft section, are easily replaceable, provide a substantially wrinkle-free outer elastomeric surface for the leading edge, and provide an elastomeric shoe or boot which is uniformly and strongly bonded because of its being formed simultaneously with the inner component in an appropriate mold.
  • the molded composite as applied to an aircraft section provides a desired aerodynamic surface and an aerodynamic force load carrying member or aerodynamic force transmitting member according to the composite design and manner of attachment.
  • FIG. 1 is a perspective view of a portion of an aircraft wing structure
  • Fig. 2 is a cross-section of the wing structure of Fig. 1 taken along lines 2 - 2 of Fig. 1;
  • Fig. 3 is a cross-sectional view similar to
  • FIG. 2 of a wing structure illustrating a modification
  • Fig. 4 is ' a perspective view of a portion of an aircraft
  • Fig. 5 is a cross-sectional view of the nose structure of the aircraft shown in Fig. 4, taken along lines 5 - 5 of Fig. 4.
  • an aircraft wing is generally referenced 10, which wing comprises a principal or main body portion 12 and a leading edge portion 14.
  • the leading edge portion 14 is illustrated as removably secured to the wing main portion 12 by " a series of spaced"fasteners 16.
  • the removable leading edge portion 14 is understood to extend continuously to the wing tip (also not shown) .
  • the construction of this leading edge portion is in accordance with a presently preferred embodiment of the present invention shown in more detail in Fig. 2, or, alternatively, in Fig. 3.
  • removable leading edge portion 14 is shown as a structural composite comprising an outer flexible sheetlike component 20 and an inner rigid component 24.
  • Outer component 20 is preferably composed of flexible reinforced or unreinforced rubber, or rubberlike material.
  • Inner component 24 is preferably composed of rigid nonmetaUic material such as plastic.
  • the outer and inner components are mold bonded to each other (i.e. are united in a mold used to form the composite to the leading edge contour) .
  • the rubber outer component 20 as shown in
  • Fig. 2 and in accordance with a preferred embodiment is a deicer shoe or blanket.
  • component 20 includes a plurality of chambers 22 adapted to receive fluid, such as air, from a fluid source (not shown) .
  • fluid such as air
  • portions of the outer surface 26 of flexible component 20 expand or bulge such as to break up ice which may form along the leading edge portion of the wing.
  • Deicers such as just described are generally known as pneumatic deicers. It is understood that deicer component 20 could also be an electrical type deicer wherein a rubber blanket or shoe is provided with embedded resistance coils which, when ' energized, generate heat to melt ice which may form along the leading edge of the wing.
  • inner component 24 is preferably of rigid plastic material and more preferably, is constructed of such plastic reinforced by glass fibers. This more preferred material, which is easily formed to selected contours by molding, manifests strength and durability in performance comparable to that of a metal leading edge. Inner component 24 is carefully formed to a preselected contour dictated by the required aero ⁇ dynamic shape of the structure of which it is to form part. As seen further in Fig. 2, deicer outer component 20 is of such area so as.to cover substan ⁇ tially all of the outer surface 27 of inner component 24.
  • the marginal areas 23 of component 24 are not covered by deicer 20 and are formed slightly thicker than remaining areas so as to receive fasteners 16 securing the composite 14 to the main body 12 of the wing. It is also understood that composite 14 may be secured to the wing body 12 by means other than fasteners, such as, for example, by suitable adhesives.
  • FIG. 3 an alternate design is shown wherein composite 14' secured to wing body 12' by fasteners 16' comprises a flexible rubber outer compon- ent 20' and an inner rigid plastic component 24'.
  • outer component 20' of compos ⁇ ite 14' is a simple rubber sheet member which does not function as a deicer.
  • rubber com- ponent 20' functions solely as a protective covering for the leading edge area of the aircraft.
  • nose portion 32 of plane 30 is a removable composite comprising an inner rigid component 44 and an outer flexible component 40 shown in the form of an erosion shoe.
  • Erosion shoe 40 of composite 32 forming the nose portion of aircraft 30 is also composed of flexible reinforced or unreinforced rubber or rubberlike material.
  • Inner rigid component 44 is preferably rigid plastic, and also, more preferably, fiber reinforced plastic as is the inner components 24 and 24' of leading edge composites 14 or 14". As in the embodiments previously described, inner component is carefully formed to a preselected contour in a mold along with the erosion shoe sheet to achieve strong and uniform bonding between the inner surface 45 of the erosion shoe component 40 and the outer surface 47 of inner compon ⁇ ent 44.
  • leading edge com- posites constructed in accordance with the present invention are readily molded composites.
  • these composites can be mold formed by placing within a mold cavity of required preselected aerodynamic contour the two component materials in uncured, partially cured or cured states.
  • a suitable sized layer or layers of rubber can be placed against the female portion of the mold, against which rubber layer is placed the fiber reinforced plastic layer in a par ⁇ tially cured state.
  • a male mold member or preferably conventional bagging techniques, can then form the composite by pressure against the female mold member, while heat introduced into the mold cures the composite within the aerodynamically contoured cavity between the mold members. Mold forming these composites in this manner has been found to provide a leading edge with well-bonded components wherein the outer rubber component is substantially smooth and wrinkle-free. This latter characteristic is believed due to phenomena occurring during the molding operation, where surface irregularities appear adsorbed along the interface between the inner surface of the outer flexible component and the outer surface of the inner rigid component.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Moulds For Moulding Plastics Or The Like (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

Un bord d'attaque d'avion, moule, non metallique, interchangeable (14) comprend un organe rigide interne (24) et un organe elastomere externe flexible (20). L'organe externe peut etre un degivreur ou une semelle d'erosion tandis que l'organe interne peut se composer d'un materiau plastique approprie. Le bord d'attaque non metallique, moule, interchangeable (14) formant le bord d'attaque des ailes ou du nez d'un avion assure que ces composants d'avion dont le contour aerodynamique est critique restent dans un etat d'aerodynamisme approprie meme s'ils portent des elastomeres de degivrage ou des erosions.
PCT/US1980/001095 1979-10-03 1980-08-25 Bord d'attaque composite pour avion WO1981000993A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
BR8008855A BR8008855A (pt) 1979-10-03 1980-08-25 Composto para borda de avanco de aeronaves antecedentes
AU63915/80A AU6391580A (en) 1979-10-03 1980-08-25 Composite leading edge for aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US8159779A 1979-10-03 1979-10-03
US81597 1979-10-03

Publications (1)

Publication Number Publication Date
WO1981000993A1 true WO1981000993A1 (fr) 1981-04-16

Family

ID=22165149

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1980/001095 WO1981000993A1 (fr) 1979-10-03 1980-08-25 Bord d'attaque composite pour avion

Country Status (7)

Country Link
EP (1) EP0036875A4 (fr)
JP (1) JPS5657598A (fr)
BR (1) BR8008855A (fr)
CA (1) CA1161014A (fr)
ES (1) ES262183Y (fr)
IT (1) IT1132967B (fr)
WO (1) WO1981000993A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0359504A1 (fr) * 1988-09-14 1990-03-21 British Aerospace Public Limited Company Radomes
EP0428011A2 (fr) * 1989-11-06 1991-05-22 The B.F. Goodrich Company Profil structural d'aile avec système expulsif intégré
US5449134A (en) * 1993-09-24 1995-09-12 The B. F. Goodrich Company Apparatus and method for providing a pneumatic de-icer with a replaceable environment resistant surface
WO2006040946A1 (fr) * 2004-10-08 2006-04-20 Showa Co., Ltd. Structure de jonction pour panneaux
CN101876293A (zh) * 2009-05-01 2010-11-03 通用电气公司 具有预制的前缘段的风力涡轮叶片
CN103318419A (zh) * 2013-05-20 2013-09-25 西安电子工程研究所 机载电子吊舱舱体与天线罩套接密封结构
WO2014081355A1 (fr) * 2012-11-20 2014-05-30 Saab Ab Bande de protection contre l'érosion pour bord d'attaque d'article à profil aérodynamique
WO2017220794A1 (fr) * 2016-06-24 2017-12-28 Lm Wind Power International Technology Ii Aps Pale d'éolienne et procédé de fabrication
WO2018171874A1 (fr) * 2017-03-21 2018-09-27 Mhi Vestas Offshore Wind A/S Pale d'éolienne, rotor d'éolienne et appareil de production d'énergie d'éolienne
GB2573286A (en) * 2018-04-27 2019-11-06 Airbus Operations Ltd Winglet

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6662715B2 (en) * 2000-07-21 2003-12-16 Aida Engineering Co., Ltd. Slider link press
US10273012B2 (en) * 2016-09-08 2019-04-30 Ge Aviation Systems Llc Deicing module for an aircraft and method for deicing

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2393635A (en) * 1942-04-17 1946-01-29 Robert H Wendt Ice removing device for aircraft
US2762897A (en) * 1951-06-28 1956-09-11 Lockheed Aircraft Corp De-icing means for aircraft and the like
US2956281A (en) * 1954-09-08 1960-10-11 Edward B Mcmillan Dielectric walls for transmission of electromagnetic radiation
US3085925A (en) * 1957-02-20 1963-04-16 Konenklijke Nl Vliegtuigenfabr Method of forming an aircraft part having a pliable deicer boot thereon
DE2726336A1 (de) * 1976-06-11 1977-12-22 Paulstra Sa Verbesserungen fuer die ausgestaltung von fluegeloberflaechen, insbesondere fuer die fluegel von hubschraubern, die mit enteisungsmitteln versehen sind

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2393635A (en) * 1942-04-17 1946-01-29 Robert H Wendt Ice removing device for aircraft
US2762897A (en) * 1951-06-28 1956-09-11 Lockheed Aircraft Corp De-icing means for aircraft and the like
US2956281A (en) * 1954-09-08 1960-10-11 Edward B Mcmillan Dielectric walls for transmission of electromagnetic radiation
US3085925A (en) * 1957-02-20 1963-04-16 Konenklijke Nl Vliegtuigenfabr Method of forming an aircraft part having a pliable deicer boot thereon
DE2726336A1 (de) * 1976-06-11 1977-12-22 Paulstra Sa Verbesserungen fuer die ausgestaltung von fluegeloberflaechen, insbesondere fuer die fluegel von hubschraubern, die mit enteisungsmitteln versehen sind

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0359504A1 (fr) * 1988-09-14 1990-03-21 British Aerospace Public Limited Company Radomes
EP0428011A2 (fr) * 1989-11-06 1991-05-22 The B.F. Goodrich Company Profil structural d'aile avec système expulsif intégré
EP0428011A3 (en) * 1989-11-06 1991-07-31 The B.F. Goodrich Company Structural airfoil having integral expulsive system
US5449134A (en) * 1993-09-24 1995-09-12 The B. F. Goodrich Company Apparatus and method for providing a pneumatic de-icer with a replaceable environment resistant surface
WO2006040946A1 (fr) * 2004-10-08 2006-04-20 Showa Co., Ltd. Structure de jonction pour panneaux
US7980036B2 (en) 2004-10-08 2011-07-19 Showa Co., Ltd. Lining structure
CN101876293A (zh) * 2009-05-01 2010-11-03 通用电气公司 具有预制的前缘段的风力涡轮叶片
WO2014081355A1 (fr) * 2012-11-20 2014-05-30 Saab Ab Bande de protection contre l'érosion pour bord d'attaque d'article à profil aérodynamique
WO2014081380A1 (fr) * 2012-11-20 2014-05-30 Saab Ab Bande multifonction de protection contre l'érosion
US10035578B2 (en) 2012-11-20 2018-07-31 Saab Ab Multifunctional erosion protection strip
CN103318419A (zh) * 2013-05-20 2013-09-25 西安电子工程研究所 机载电子吊舱舱体与天线罩套接密封结构
WO2017220794A1 (fr) * 2016-06-24 2017-12-28 Lm Wind Power International Technology Ii Aps Pale d'éolienne et procédé de fabrication
CN109563805A (zh) * 2016-06-24 2019-04-02 Lm风力发电国际技术有限公司 风轮机叶片及制造风轮机叶片的方法
WO2018171874A1 (fr) * 2017-03-21 2018-09-27 Mhi Vestas Offshore Wind A/S Pale d'éolienne, rotor d'éolienne et appareil de production d'énergie d'éolienne
KR20190097284A (ko) * 2017-03-21 2019-08-20 엠에이치아이 베스타스 오프쇼어 윈드 에이／에스 풍력 터빈 블레이드, 풍력 터빈 로터 및 풍력 터빈 발전 장치
KR102197433B1 (ko) 2017-03-21 2021-01-04 엠에이치아이 베스타스 오프쇼어 윈드 에이／에스 풍력 터빈 블레이드, 풍력 터빈 로터 및 풍력 터빈 발전 장치
US11220998B2 (en) 2017-03-21 2022-01-11 Vestas Wind Systems A/S Wind turbine blade, wind turbine rotor, and wind turbine power generating apparatus
GB2573286A (en) * 2018-04-27 2019-11-06 Airbus Operations Ltd Winglet
GB2573286B (en) * 2018-04-27 2020-10-14 Airbus Operations Ltd Winglet

Also Published As

Publication number Publication date
IT1132967B (it) 1986-07-09
EP0036875A4 (fr) 1982-07-12
ES262183U (es) 1982-06-01
JPS5657598A (en) 1981-05-20
CA1161014A (fr) 1984-01-24
IT8024753A0 (it) 1980-09-18
ES262183Y (es) 1982-12-16
EP0036875A1 (fr) 1981-10-07
BR8008855A (pt) 1981-09-01

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