EP0883484A1 - Structure composite nid d'abeille en sandwich - Google Patents

Structure composite nid d'abeille en sandwich

Info

Publication number
EP0883484A1
EP0883484A1 EP97903737A EP97903737A EP0883484A1 EP 0883484 A1 EP0883484 A1 EP 0883484A1 EP 97903737 A EP97903737 A EP 97903737A EP 97903737 A EP97903737 A EP 97903737A EP 0883484 A1 EP0883484 A1 EP 0883484A1
Authority
EP
European Patent Office
Prior art keywords
core
laminate
die
tiedown
resin
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.)
Withdrawn
Application number
EP97903737A
Other languages
German (de)
English (en)
Inventor
Dale E. Hartz
William B. Hopkins
Christopher L. Pederson
Dave G. Erickson
Darrell H. Corbett
Stuart A. Smith
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
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
Priority claimed from US08/587,160 external-priority patent/US5604010A/en
Priority claimed from US08/616,903 external-priority patent/US5895699A/en
Priority claimed from US08/620,829 external-priority patent/US5685940A/en
Application filed by Boeing Co filed Critical Boeing Co
Publication of EP0883484A1 publication Critical patent/EP0883484A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • 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

Definitions

  • the present invention relates to composite honeycomb sandwich structure, and particularly to resin impregnated fabric sheets forming outer skins adhered on opposed surfaces of a honeycomb core with an intermediate barrier to eliminate resin flow from the skins to the core.
  • U.S. Patent 5,445,861 describes composite sandwich structure for sound absorption (acoustic insulation) and other applications.
  • the sandwich structures have seven layers as follows:
  • microcracking that originated in the migrated resin could propagate to the bond line and degrade mechanical performance. Such microcracking potential poses a catastrophic threat to the integrity of the panel and dictates that flow be eliminated or, at least, controlled.
  • the added tiedown ply means mat three or more tiedown plys will be included in d e final preform of the panel.
  • tiiere will also be tiedown plys on die outer surfaces of die panel and possibly between d e laminate and die adhesive barrier film.
  • Each tiedown ply extends outwardly from the part beyond die net trim line of die finished product.
  • die tiedown plies are secured individually and sequentially to die layup mandrel witii tape. Especially when using low density core it is important to fix the relation of the plies to one another and to the mandrel. Failure of die tape results in facesheet ply wrinkles or core crush.
  • die present invention relates to an improvement in the manufacture of composite structure, especially composite honeycomb sandwich structure, where tiedown plys are used to secure the part during autoclave curing at elevated temperature and pressure.
  • tiedown plys are used to secure the part during autoclave curing at elevated temperature and pressure.
  • a lower temperature curing adhesive to cure and to connect the several plys together during the early stages of autoclave curing prior to applying pressure.
  • Fig. 1 illustrates a typical composite honeycomb sandwich structure.
  • Fig. 2 is a schematic, partial sectional view of die skin-core interface in sandwich structure having a scrim-supported barrier film to prevent resin flow from the skin to the core.
  • the supported film adhesive and barrier film layers in the sandwich structure also function as corrosion barriers between the skin 102 and core 106 in the case where the core is metal, such as aluminum, and d e skin includes a galvanically dissimilar material, such as carbon fiber.
  • Core crush 200 occurs in the chamfer region 155 when the barrier film 1 10 and core 106 slip relative to the facesheets 102 when autoclave pressure is applied and when the resin is melted. As shown in Fig. 5, the barrier films 100 and core 106 have moved toward the right to compress the core in the chamfer region 155 to produce die core crush 200. The skin 102 has sagged in the edgeband region 160 where d e core moved away.
  • die improved honeycomb sandwich panel includes at least one tiedown ply 150 in contact with the core 106 along a chamfer 155.
  • a chamfer i.e. an angled transition in the core, often at the edgeband 160
  • Such a chamfer typically occurs around the periphery ofthe panel, but it might also occur intermediate of the panel at join lines or hard points where fasteners or pass-throughs might be necessary in the assembled structure.
  • a single ply 150 of carbon fiber or fiberglass fabric witii a conventional 0/90 fiber orientation in the fabrication of bismaleimide panels having 5 or 8 Ib/ft ⁇ HRP core, like Hartz et al. describe.
  • the tiedown ply 150 functions to prohibit or to limit slippage ofthe skin relative to the core so as to reduce core crush otherwise attributable to the slippage.
  • the tiedown ply 150 anchors the core with the inherent roughness of the fabric when the preform is heated during the autoclave processing cycle and me matrix resin softens, melts, and, for high flow resins, essentially liquefies. Witii these panels, we can save between 2.5-4 lb/ft ⁇ of core because we can use lighter density honeycomb core without suffering core crush. For a fighter, this change can save as much as 25 lbs per vehicle.
  • the tiedown ply 150 is a narrow, peripheral strip tiiat contacts the core 106 along at least a portion of the chamfer 155 for about 1 inch overlap with the core 106 and extends outward into the edgeband 160 beyond d e trimline 165 of the part.
  • the tiedown ply 150 might be on either the flat side of the chamfer or the angled surface (which is how we show it in Fig. 6).
  • the key factor is that the tiedown ply 150 contact die core beneath the adhesive and barrier film 110 which is used to bond d e laminate skin to the core.
  • the tiedown ply 150 is cutaway everywhere in the body of die part otiier than a narrow peripheral area in the chamfer region, and forms a peripheral frame around d e edge of the panel. In this way, the tiedown ply 150 allows an adhesive interface between the core 106 and die skins 102 in the panel region.
  • the tiedown plies 150 and 175 extend through die edgeband 160 beyond the net trim line 165 to anchoring points that we tape to the layup mandrel.
  • a low curing (i.e. 121°C for BMI panels) film adhesive 180 between die tiedown plies just outside d e net trim line of the part.
  • the film adhesive 180 eliminates movement of one ply relative to the others when we apply pressure during the autoclave curing cycle. Curing at a temperature of about 100 - 150°F below the curing temperature ofthe laminate resin, the tiedown adhesive cures before we need to increase d e autoclave pressure and die cured adhesive bonds the tiedown plys to one another.
  • Using the adhering method eliminates relative movement of die plys and eliminates facesheet wrinkles and core crush that otherwise can occur.
  • the tiedown method saves material, reduces cost, and saves weight, because it use die "picture frame” peripheral tiedown ply 150 (with the traditional, internal sheets omitted).
  • the normal tiedown procedure entails plys on the outer surfaces ofthe skins and internally between the skin and underlying adhesive (Fig. 5).
  • a traditional tiedown system will fail without the "picture frame” ply because the barrier film 110 permits the core to slip.
  • the Corbett and Smith method will fail occasionally witiiout the adhering method of die present invention.
  • chamfer we mean an angled, cut region (a ramp) of the honeycomb core tapering from full thickness to no thickness with a steady slope.
  • a chamfer is used at the edge band of a composite honeycomb sandwich panel to provide a smooth transition between the structural body ofthe panel that has the embedded honeycomb and a connecting edge band lacking any honeycomb core.
  • the method of d e present invention allows us to use much steeper chamfer angles than traditional practices often require if one is to avoid core crush without one tiedown ply. While we prefer a 20° chamfer, we believe that we could increase die angle to whatever angle suited the panel design requirements.

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

On élimine un écoulement de résine dans les cellules d'une structure nid d'abeille en sandwich en utilisant un adhésif (108) sous forme de film non renforcé, une couche barrière (110) et une couche adhésive (112) renforcée par un renfort tissé entre le stratifié composite (102) et le noyau (106). On obtient des panneaux de qualité supérieure, allégés, aux caractéristiques mécaniques améliorées et d'une tenue structurelle plus aisément prévisible en laissant de la résine dans le stratifié plutôt qu'en la laissant se perdre dans les cellules du noyau. On diminue l'écrasement du noyau et le plissement des couches dans une structure composite nid d'abeille en sandwich en empêchant le glissement des couches d'arrimage par rapport au mandrin et de l'une par rapport à l'autre durant le durcissement à l'autoclave et l'on obtient, de la sorte, des panneaux de qualité supérieure, allégés, aux caractéristiques mécaniques améliorées et d'une tenue structurelle plus aisément prévisible. Le procédé consiste à apposer un adhésif sous forme de film sur les couches d'arrimage sur le contour de la partie extérieure au bord de coupe net. Durant le chauffage à l'autoclave et avant l'application d'une pression élevée sur la structure composite, l'adhésif sous forme de film durcit pour constituer une liaison solide entre les couches et avec le mandrin. Lorsqu'une certaine pression est appliquée, les couches d'arrimage sont fixées ensemble et sur le mandrin afin d'empêcher tout glissement entre les couches du panneau.
EP97903737A 1996-01-11 1997-01-06 Structure composite nid d'abeille en sandwich Withdrawn EP0883484A1 (fr)

Applications Claiming Priority (7)

Application Number Priority Date Filing Date Title
US587160 1996-01-11
US08/587,160 US5604010A (en) 1996-01-11 1996-01-11 Composite honeycomb sandwich structure
US616903 1996-03-15
US08/616,903 US5895699A (en) 1996-03-15 1996-03-15 Tiedown ply for reducing core crush in composite honeycomb sandwich structure
US08/620,829 US5685940A (en) 1996-03-20 1996-03-20 Adhering tiedown plies in composite construction
US620829 1996-03-20
PCT/US1997/000075 WO1997025198A1 (fr) 1996-01-11 1997-01-06 Structure composite nid d'abeille en sandwich

Publications (1)

Publication Number Publication Date
EP0883484A1 true EP0883484A1 (fr) 1998-12-16

Family

ID=27416496

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97903737A Withdrawn EP0883484A1 (fr) 1996-01-11 1997-01-06 Structure composite nid d'abeille en sandwich

Country Status (5)

Country Link
EP (1) EP0883484A1 (fr)
JP (2) JP3913275B2 (fr)
CN (1) CN1101751C (fr)
AU (1) AU1822997A (fr)
WO (1) WO1997025198A1 (fr)

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DE69917264T2 (de) 1998-05-22 2005-05-25 Cytec Technology Corp., Wilmington Produkte und verfahren zur verhinderung des zusammensdrückens eines kerns
JP4663174B2 (ja) * 2001-08-03 2011-03-30 富士重工業株式会社 ハニカムサンドイッチ構造複合材の成形方法
ATE406998T1 (de) 2003-07-08 2008-09-15 Airbus Gmbh Leichtbaustruktur
EP1495858B1 (fr) 2003-07-08 2019-08-07 Airbus Operations GmbH Structure légère d'un matériau composite métallique
JP2007098819A (ja) * 2005-10-06 2007-04-19 Mitsubishi Rayon Co Ltd サンドイッチパネルの製造方法
FR2908737B1 (fr) * 2006-11-16 2009-12-04 Airbus France Revetement acoustique pour aeronef incorporant un systeme de traitement du givre par effet joule.
US8046915B2 (en) * 2007-12-12 2011-11-01 General Electric Company Methods for making composite containment casings
US8343298B2 (en) * 2007-12-13 2013-01-01 The Boeing Company Aircraft structures bonded with adhesive including magnetostrictive material
US20090155524A1 (en) * 2007-12-13 2009-06-18 Rapp Robert A Composite panel and method of manufacturing the same
BE1017910A3 (fr) 2007-12-21 2009-11-03 Sonaca Sociutu Anonyme Procede de fabrication d'un panneau comprenant au moins un corps en nid-d'abeilles et une premiere peau realisee en materiau composite.
US8491743B2 (en) * 2009-12-15 2013-07-23 The Boeing Company Composite ply stabilizing method
JP5619485B2 (ja) * 2010-06-22 2014-11-05 豊和繊維工業株式会社 積層構造の車両用内装基材及びその製造法
US8844873B2 (en) 2011-09-23 2014-09-30 The Boeing Company Stabilizer torque box assembly and method
FR2987307B1 (fr) * 2012-02-29 2017-02-10 Daher Aerospace Procede et dispositif pour le compactage et la consolidation d'un panneau composite de forte epaisseur a matrice thermoplastique
CN102700181B (zh) * 2012-05-15 2014-09-03 西安交通大学 一种轻质多功能复合结构
US9517594B2 (en) * 2012-10-04 2016-12-13 The Boeing Company Composite structure having a stabilizing element
CN102909899B (zh) * 2012-10-25 2015-03-11 溧阳二十八所系统装备有限公司 防水型纸蜂窝复合夹芯板的制备方法
CN103161391A (zh) * 2013-03-07 2013-06-19 苏州市江诚人防设备有限公司 无机防护门
WO2015013012A1 (fr) 2013-07-26 2015-01-29 Learjet Inc. Matériau composite incorporant une barrière contre l'entrée d'eau
US9579875B2 (en) 2014-02-04 2017-02-28 The Boeing Company Bonded tab and tooling device
JP5992946B2 (ja) 2014-03-25 2016-09-14 富士重工業株式会社 ハニカム構造体及びハニカム構造体の製造方法
CN105539809A (zh) * 2014-10-28 2016-05-04 哈尔滨飞机工业集团有限责任公司 一种分段式蜂窝夹层结构
EA201991043A1 (ru) 2016-10-27 2019-09-30 Руаг Швайц Аг Получение армированного волокнами полимера
JP7039401B2 (ja) 2018-06-28 2022-03-22 三菱重工業株式会社 複合材及び複合材の硬化方法
JP7114367B2 (ja) 2018-06-28 2022-08-08 三菱重工業株式会社 複合材構造体の成形方法
CN109159518A (zh) * 2018-08-28 2019-01-08 丹阳丹金航空材料科技有限公司 一种航空飞行器用复合板
CN111186147B (zh) * 2020-02-24 2021-10-08 江苏亨睿碳纤维科技有限公司 连续纤维混杂短切纤维制备轻量化汽车零部件的成型方法

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Also Published As

Publication number Publication date
JP2000502968A (ja) 2000-03-14
JP3913275B2 (ja) 2007-05-09
WO1997025198A1 (fr) 1997-07-17
JP2007015385A (ja) 2007-01-25
JP4407964B2 (ja) 2010-02-03
CN1101751C (zh) 2003-02-19
AU1822997A (en) 1997-08-01
CN1211947A (zh) 1999-03-24

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