JP2012520205A - 準等方性ラミネート材を用いた複合構造 - Google Patents
準等方性ラミネート材を用いた複合構造 Download PDFInfo
- Publication number
- JP2012520205A JP2012520205A JP2011554087A JP2011554087A JP2012520205A JP 2012520205 A JP2012520205 A JP 2012520205A JP 2011554087 A JP2011554087 A JP 2011554087A JP 2011554087 A JP2011554087 A JP 2011554087A JP 2012520205 A JP2012520205 A JP 2012520205A
- Authority
- JP
- Japan
- Prior art keywords
- composite
- plies
- skin
- stack
- 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.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 100
- 239000000835 fiber Substances 0.000 claims abstract description 33
- 239000003733 fiber-reinforced composite Substances 0.000 claims abstract description 10
- 238000000034 method Methods 0.000 claims description 28
- 239000012783 reinforcing fiber Substances 0.000 claims description 4
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 239000002648 laminated material Substances 0.000 description 10
- 238000004519 manufacturing process Methods 0.000 description 10
- 239000000463 material Substances 0.000 description 8
- 239000002184 metal Substances 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 6
- 230000007423 decrease Effects 0.000 description 5
- 230000002787 reinforcement Effects 0.000 description 5
- 239000012779 reinforcing material Substances 0.000 description 5
- 229920000049 Carbon (fiber) Polymers 0.000 description 4
- 239000004917 carbon fiber Substances 0.000 description 4
- 230000032798 delamination Effects 0.000 description 4
- 150000002739 metals Chemical class 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 238000013459 approach Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 239000003351 stiffener Substances 0.000 description 3
- 238000013517 stratification Methods 0.000 description 3
- 239000004593 Epoxy Substances 0.000 description 2
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- -1 aluminum or titanium Chemical class 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 239000011151 fibre-reinforced plastic Substances 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000013475 authorization Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 230000001902 propagating effect Effects 0.000 description 1
- 238000009419 refurbishment Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Images
Classifications
-
- 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
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
- B32B5/12—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
- B29C70/202—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC]
-
- 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
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
- B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
-
- 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
- B32B1/00—Layered products having a non-planar shape
-
- 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
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
-
- 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
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
-
- 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
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/18—Layered products comprising a layer of synthetic resin characterised by the use of special additives
-
- 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
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/38—Layered products comprising a layer of synthetic resin comprising epoxy resins
-
- 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
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
- B32B5/022—Non-woven fabric
-
- 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
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
-
- 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
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
-
- 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
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- 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
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
- B29K2995/0037—Other properties
- B29K2995/0045—Isotropic
-
- 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
- B29L2031/3082—Fuselages
-
- 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
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
-
- 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
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/04—Impregnation, embedding, or binder material
- B32B2260/046—Synthetic resin
-
- 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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
-
- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
-
- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/708—Isotropic
-
- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/718—Weight, e.g. weight per square meter
-
- 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
- B32B2605/00—Vehicles
-
- 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
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- 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
-
- 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.]
- Y10T428/24058—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
- Y10T428/24124—Fibers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
【選択図】図1
Description
を備える複合ラミネート材。
第1の複合部材、及び
第1の複合部材に結合されて、第1の複合部材により補強された第2の複合部材であって、各々が一方向性の補強ファイバと一のファイバ配向とを有する複数の複合プライが積み重なったスタックを含んでいる第2の複合部材
を備え、
スタック中の少なくとも一部の隣接し合うプライが、第2の複合部材中の亀裂の伝播を止めるのに十分な量だけ異なるポアソン比をそれぞれ有している、
複合構造。
第2の複合部材が、フレームを覆う胴体外板である、
請求項4に記載の複合構造。
少なくとも一の補強材、及び
補強材に結合された外板であって、各々が一のファイバ配向を有し、一方向性のファイバ補強複合材料からなる複数のプライのスタックを含む外板
を備え、
複数のプライが、補強材に接近する外板中の亀裂の伝播経路を変更するファイバ配向シーケンスに積み重ねられている、
複合材料からなる機体。
外板が接着により補強材に結合されている、
請求項8に記載の複合材料からなる機体。
複合材料からなるフレーム部材を作製すること、
複合外板を作製することであって、一方向性のファイバ強化複合プライのスタックを、外板に準等方性の特性を付与するプライ配向シーケンスに積み上げることを含むこと、及び
フレーム部材を外板に結合すること
を含む方法。
を更に含む、請求項12に記載の方法。
を更に含む、請求項14に記載の方法。
各々がファイバ強化複合ラミネート材から形成された、複合材料からなる複数のバレル状フレーム部材、及び
フレーム部材に接着される複合外板であって、一方向性のファイバ補強ポリマーからなる重ね合わせた複数のプライを含み、これらのプライが、各々が一の共通するファイバ配向を有する複数の組に構成されており、隣接し合う組のファイバ配向が少なくとも約45°異なっており、隣接し合うプライの組のポアソン比の不一致が通常約15〜40%である、複合外板
を備える機体。
複数の複合材料からなるフレーム部材を作製すること、
複合外板を作製することであって、
外板中の亀裂を止める助けとなるのに必要な、隣接し合うプライ間のポアソン比の不一致レベルを決定することと、
一方向性のファイバ補強複合プライからなるプライのスタックを、決定されたポアソン比の不一致レベルを達成する配向に積み上げることと
を含むこと、並びに
外板にフレーム部材を接着すること
を含む方法。
υ=−εt/εl
と表わすことができ、ここで
υ=ポアソン比
εt=横方向の歪み
εl=縦方向又は軸方向の歪み
であり、歪みは
ε=dl/Lと表わすことができ、ここで
dl=長さの変化
L=最初の長さ
である。
Claims (9)
- 亀裂を止める機能を有する複合構造であって、
第1の複合部材、及び
前記第1の複合部材に結合されて前記第1の複合部材により補強される第2の複合部材であって、各々が一方向性の補強ファイバと一のファイバ配向とを有する複数の複合プライを重ね合わせたスタックを含む第2の複合部材
を備えており、
前記スタック中の少なくとも一部の隣接し合うプライが、前記第2の複合部材の亀裂の伝播を止めるのに十分に異なるポアソン比をそれぞれ有している、複合構造。 - 前記ポアソン比の差異が通常約15〜40%である、請求項1に記載の複合構造。
- 前記少なくとも一部の隣接し合うプライのファイバ配向が約45°である、請求項1に記載の複合構造。
- 前記第1の複合部材が航空機のフレームであり、且つ
前記第2の複合部材が前記フレームを覆う胴体外板である、
請求項1に記載の複合構造。 - 亀裂を止める機能を有する複合材料からなる機体を構築する方法であって、
複合材料からなるフレーム部材を作製すること、
複合外板を作製することであって、一方向性のファイバ補強複合プライのスタックを、外板に準等方性の特性を付与するプライ配向シーケンスで積み上げることを含むこと、及び
前記外板に前記フレーム部材を結合すること
を含む方法。 - 前記プライのスタックを積み上げることが、隣接し合うプライのファイバ配向が少なくとも約45°相違するように、隣接し合うプライの向きを合わせることを含む、請求項5に記載の方法。
- 外板が準等方性の特性を示すように、前記スタック中における隣接し合うプライ間のポアソン比の不一致レベルを決定すること
を更に含む、請求項5に記載の方法。 - 前記決定されたポアソン比の不一致レベルを達成するプライ配向シーケンスを選択すること
を更に含む、請求項7に記載の方法。 - 前記外板に前記フレーム部材を結合することが、前記外板に前記フレーム部材を接着することを含む、請求項5に記載の方法。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/401,541 | 2009-03-10 | ||
US12/401,541 US20100233424A1 (en) | 2009-03-10 | 2009-03-10 | Composite structures employing quasi-isotropic laminates |
PCT/US2010/026229 WO2010104741A1 (en) | 2009-03-10 | 2010-03-04 | Composite structures employing quasi-isotropic laminates |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2015172206A Division JP6162186B2 (ja) | 2009-03-10 | 2015-09-01 | 準等方性ラミネート材を用いた複合構造 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2012520205A true JP2012520205A (ja) | 2012-09-06 |
JP2012520205A5 JP2012520205A5 (ja) | 2013-03-07 |
Family
ID=42136041
Family Applications (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2011554087A Pending JP2012520205A (ja) | 2009-03-10 | 2010-03-04 | 準等方性ラミネート材を用いた複合構造 |
JP2015172206A Active JP6162186B2 (ja) | 2009-03-10 | 2015-09-01 | 準等方性ラミネート材を用いた複合構造 |
JP2017116163A Pending JP2017213900A (ja) | 2009-03-10 | 2017-06-13 | 準等方性ラミネート材を用いた複合構造 |
Family Applications After (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2015172206A Active JP6162186B2 (ja) | 2009-03-10 | 2015-09-01 | 準等方性ラミネート材を用いた複合構造 |
JP2017116163A Pending JP2017213900A (ja) | 2009-03-10 | 2017-06-13 | 準等方性ラミネート材を用いた複合構造 |
Country Status (5)
Country | Link |
---|---|
US (1) | US20100233424A1 (ja) |
EP (1) | EP2406071B1 (ja) |
JP (3) | JP2012520205A (ja) |
ES (1) | ES2564837T3 (ja) |
WO (1) | WO2010104741A1 (ja) |
Families Citing this family (37)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9586699B1 (en) | 1999-08-16 | 2017-03-07 | Smart Drilling And Completion, Inc. | Methods and apparatus for monitoring and fixing holes in composite aircraft |
US9625361B1 (en) | 2001-08-19 | 2017-04-18 | Smart Drilling And Completion, Inc. | Methods and apparatus to prevent failures of fiber-reinforced composite materials under compressive stresses caused by fluids and gases invading microfractures in the materials |
US8617694B1 (en) | 2009-03-09 | 2013-12-31 | The Boeing Company | Discretely tailored multi-zone bondline for fail-safe structural repair |
US8540909B2 (en) * | 2009-03-09 | 2013-09-24 | The Boeing Company | Method of reworking an area of a composite structure containing an inconsistency |
US8449703B2 (en) * | 2009-03-09 | 2013-05-28 | The Boeing Company | Predictable bonded rework of composite structures using tailored patches |
US8409384B2 (en) * | 2009-03-09 | 2013-04-02 | The Boeing Company | Predictable bonded rework of composite structures |
US9492975B2 (en) | 2009-03-09 | 2016-11-15 | The Boeing Company | Structural bonded patch with tapered adhesive design |
US8524356B1 (en) | 2009-03-09 | 2013-09-03 | The Boeing Company | Bonded patch having multiple zones of fracture toughness |
US8857128B2 (en) * | 2009-05-18 | 2014-10-14 | Apple Inc. | Reinforced device housing |
US8815132B2 (en) | 2010-01-18 | 2014-08-26 | The Boeing Company | Method of configuring a patch body |
WO2011142699A1 (en) * | 2010-05-11 | 2011-11-17 | Saab Ab | A composite article comprising particles and a method of forming a composite article |
US8372495B2 (en) | 2010-05-26 | 2013-02-12 | Apple Inc. | Electronic device enclosure using sandwich construction |
US8765042B2 (en) | 2010-06-11 | 2014-07-01 | Airbus Operations Gmbh | Fuselage section of an aircraft and method for the production of the fuselage section |
DE102010023496B4 (de) * | 2010-06-11 | 2017-02-23 | Airbus Operations Gmbh | Rumpfsegment eines Flugzeugs |
US9120272B2 (en) | 2010-07-22 | 2015-09-01 | Apple Inc. | Smooth composite structure |
US9011623B2 (en) | 2011-03-03 | 2015-04-21 | Apple Inc. | Composite enclosure |
EP2806418A4 (en) * | 2012-01-16 | 2015-12-16 | Nec Corp | MOBILE TERMINAL DEVICE |
US9545757B1 (en) | 2012-02-08 | 2017-01-17 | Textron Innovations, Inc. | Composite lay up and method of forming |
US20130280477A1 (en) * | 2012-03-26 | 2013-10-24 | Peter C. Davis | Off-angle laid scrims |
WO2013148696A1 (en) * | 2012-03-26 | 2013-10-03 | Saint-Gobain Adfors Canada, Ltd. | Off-angle laid scrims |
US9964096B2 (en) * | 2013-01-10 | 2018-05-08 | Wei7 Llc | Triaxial fiber-reinforced composite laminate |
US20160009368A1 (en) * | 2013-02-28 | 2016-01-14 | The Boeing Company | Composite laminated plate having reduced crossply angle |
US10407955B2 (en) | 2013-03-13 | 2019-09-10 | Apple Inc. | Stiff fabric |
US9314979B1 (en) | 2013-07-16 | 2016-04-19 | The Boeing Company | Trapezoidal rework patch |
CN104831470B (zh) | 2013-12-20 | 2018-07-27 | 苹果公司 | 利用编织纤维增加抗张强度并用于固定附连机制 |
EP2910365B1 (en) * | 2014-02-21 | 2017-04-26 | Airbus Operations GmbH | Composite structural element and torsion box |
US9850173B2 (en) | 2015-01-09 | 2017-12-26 | The Boeing Company | Hybrid sandwich ceramic matrix composite |
DE102015010436B4 (de) * | 2015-08-14 | 2019-01-24 | Airbus Defence and Space GmbH | Wabenkern für dimensionsstabile Sandwichbauteile, dessen Verwendung, Sandwichplatte mit diesem Wabenkern und Verfahren zur Herstellung des Wabenkerns |
US10005267B1 (en) | 2015-09-22 | 2018-06-26 | Textron Innovations, Inc. | Formation of complex composite structures using laminate templates |
FR3061129B1 (fr) * | 2016-12-22 | 2019-05-31 | Airbus Operations | Procede de fabrication d'un module d'isolation thermophonique pour aeronef comprenant une etape de cintrage |
RU179119U1 (ru) * | 2017-09-14 | 2018-04-26 | Российская Федерация, от имени которой выступает ФОНД ПЕРСПЕКТИВНЫХ ИССЛЕДОВАНИЙ | Устройство выхода волоконно-оптического датчика из композита |
US10864686B2 (en) | 2017-09-25 | 2020-12-15 | Apple Inc. | Continuous carbon fiber winding for thin structural ribs |
US11400657B2 (en) * | 2017-10-02 | 2022-08-02 | The Boeing Company | Methods of fabrication of composite repair parts and related kits |
WO2020146336A1 (en) * | 2019-01-10 | 2020-07-16 | Polyone Corporation | Resiliently flexible composite articles with overmolded rigid portions |
US20220410502A1 (en) * | 2019-11-29 | 2022-12-29 | Toray Industries, Inc. | Fiber-reinforced composite material and sandwich structure |
CN114761212A (zh) * | 2019-11-29 | 2022-07-15 | 东丽株式会社 | 纤维增强复合材料及夹层结构体 |
US11969953B2 (en) * | 2022-07-26 | 2024-04-30 | The Boeing Company | Prepreg charge optimized for forming contoured composite laminate structures |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3995080A (en) * | 1974-10-07 | 1976-11-30 | General Dynamics Corporation | Filament reinforced structural shapes |
US20060060705A1 (en) * | 2004-09-23 | 2006-03-23 | Stulc Jeffrey F | Splice joints for composite aircraft fuselages and other structures |
US20060243860A1 (en) * | 2005-04-28 | 2006-11-02 | The Boeing Company | Composite skin and stringer structure and method for forming the same |
JP2007016122A (ja) * | 2005-07-07 | 2007-01-25 | Toray Ind Inc | 炭素繊維強化複合材料 |
JP2007532384A (ja) * | 2004-04-06 | 2007-11-15 | ザ・ボーイング・カンパニー | 航空機胴体およびその他の構造の複合バレルセクション、および係るバレルセクションを製造する方法およびシステム |
JP2008517812A (ja) * | 2004-10-27 | 2008-05-29 | ザ・ボーイング・カンパニー | 中間層が不織連続材料で形成された複合部材を形成するための方法およびプリフォーム |
Family Cites Families (54)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4352707A (en) * | 1981-04-23 | 1982-10-05 | Grumman Aerospace Corporation | Composite repair apparatus |
US4497404A (en) * | 1983-09-30 | 1985-02-05 | Lowrance William T | Protective device for a golf club |
US4588853A (en) * | 1984-06-21 | 1986-05-13 | Roll Form Products, Inc. | Electrical trench grommet member |
US4967799A (en) * | 1984-08-15 | 1990-11-06 | Dayco Products, Inc. | Plastic abrasion-resistant protective sleeve for hose and method of protecting hose |
US5034254A (en) * | 1984-10-29 | 1991-07-23 | The Boeing Company | Blind-side panel repair patch |
US4820564A (en) * | 1984-10-29 | 1989-04-11 | The Boeing Company | Blind-side repair patch kit |
US4588626A (en) * | 1984-10-29 | 1986-05-13 | The Boeing Company | Blind-side panel repair patch |
US4961799A (en) * | 1984-10-29 | 1990-10-09 | The Boeing Company | Blind-side panel repair method |
US4916880A (en) * | 1986-07-21 | 1990-04-17 | The Boeing Company | Apparatus for repairing a hole in a structural wall of composite material |
US4978404A (en) * | 1986-07-21 | 1990-12-18 | The Boeing Company | Method for repairing a hole in a structural wall of composite material |
US4912594A (en) * | 1986-11-03 | 1990-03-27 | The Boeing Company | Integral lightning protection repair system and method for its use |
US4824500A (en) * | 1987-11-03 | 1989-04-25 | The Dow Chemical Company | Method for repairing damaged composite articles |
US4808253A (en) * | 1987-11-06 | 1989-02-28 | Grumman Aerospace Corporation | Method and apparatus for performing a repair on a contoured section of a composite structure |
US4858853A (en) * | 1988-02-17 | 1989-08-22 | The Boeing Company | Bolted repair for curved surfaces |
US5207541A (en) * | 1988-12-13 | 1993-05-04 | The Boeing Company | Scarfing apparatus |
US5023987A (en) * | 1989-08-28 | 1991-06-18 | The Boeing Company | Strato streak flush patch |
US5190611A (en) * | 1991-02-13 | 1993-03-02 | The Boeing Company | Bearing load restoration method for composite structures |
JPH04341837A (ja) * | 1991-05-17 | 1992-11-27 | Ishikawajima Harima Heavy Ind Co Ltd | Frp積層板 |
US5214307A (en) * | 1991-07-08 | 1993-05-25 | Micron Technology, Inc. | Lead frame for semiconductor devices having improved adhesive bond line control |
US5232962A (en) * | 1991-10-09 | 1993-08-03 | Quantum Materials, Inc. | Adhesive bonding composition with bond line limiting spacer system |
US5344515A (en) * | 1993-03-01 | 1994-09-06 | Argo-Tech Corporation | Method of making a pump housing |
US5374388A (en) * | 1993-04-22 | 1994-12-20 | Lockheed Corporation | Method of forming contoured repair patches |
CA2162171A1 (en) * | 1993-05-05 | 1994-11-10 | Frederick S. Campbell | Composite sandwich element |
US5620768A (en) * | 1993-10-15 | 1997-04-15 | Pro Patch Systems, Inc. | Repair patch and method of manufacturing thereof |
US5601676A (en) * | 1994-02-25 | 1997-02-11 | The Board Of Trustees Operating Michigan State University | Composite joining and repair |
US5709469A (en) * | 1995-03-13 | 1998-01-20 | The United States Of America As Represented By The Secretary Of The Air Force | Process for testing integrity of bonds between epoxy patches and aircraft structural materials |
US5626934A (en) * | 1995-10-20 | 1997-05-06 | United States Of America | Enhancing damage tolerance of adhesive bonds |
US5868886A (en) * | 1995-12-22 | 1999-02-09 | Alston; Mark S. | Z-pin reinforced bonded composite repairs |
US5732743A (en) * | 1996-06-14 | 1998-03-31 | Ls Technology Inc. | Method of sealing pipes |
GB9622780D0 (en) * | 1996-11-01 | 1997-01-08 | British Aerospace | Repair of composite laminates |
FR2763882B1 (fr) * | 1997-05-29 | 1999-08-20 | Aerospatiale | Outillage de reparation sur site d'une structure composite presentant une zone endommagee et procede correspondant |
US5993934A (en) * | 1997-08-06 | 1999-11-30 | Eastman Kodak Company | Near zero CTE carbon fiber hybrid laminate |
US6265333B1 (en) * | 1998-06-02 | 2001-07-24 | Board Of Regents, University Of Nebraska-Lincoln | Delamination resistant composites prepared by small diameter fiber reinforcement at ply interfaces |
JP2001183833A (ja) * | 1999-12-27 | 2001-07-06 | Sumitomo Chem Co Ltd | レジスト組成物 |
BR0117299B1 (pt) * | 2000-03-03 | 2014-11-25 | Quickstep Technologies Pty Ltd | Métodos para unir componentes compósitos |
US6472758B1 (en) * | 2000-07-20 | 2002-10-29 | Amkor Technology, Inc. | Semiconductor package including stacked semiconductor dies and bond wires |
US7208220B2 (en) * | 2001-12-06 | 2007-04-24 | Toray Industries, Inc. | Fiber-reinforced composite material and method for production thereof |
US6656299B1 (en) * | 2001-12-19 | 2003-12-02 | Lockheed Martin Corporation | Method and apparatus for structural repair |
US6761783B2 (en) * | 2002-04-09 | 2004-07-13 | The Boeing Company | Process method to repair bismaleimide (BMI) composite structures |
US6758924B1 (en) * | 2002-04-15 | 2004-07-06 | The United States Of America As Represented By The Secretary Of The Air Force | Method of repairing cracked aircraft structures |
NL1022706C2 (nl) * | 2003-02-17 | 2004-08-19 | Stichting Fmlc | Laminaat uit metaalplaten en elkaar kruisende dradenlagen uit verschillende materialen in kunststof. |
US6764754B1 (en) * | 2003-07-15 | 2004-07-20 | The Boeing Company | Composite material with improved damping characteristics and method of making same |
JP4118264B2 (ja) * | 2004-07-15 | 2008-07-16 | 本田技研工業株式会社 | 衝撃吸収部材 |
US20060029807A1 (en) * | 2004-08-04 | 2006-02-09 | Peck Scott O | Method for the design of laminated composite materials |
EP1683627A1 (en) * | 2005-01-25 | 2006-07-26 | Saab Ab | Method and apparatus for repairing a composite article |
US20070095457A1 (en) * | 2005-11-02 | 2007-05-03 | The Boeing Company | Fast line maintenance repair method and system for composite structures |
US7398698B2 (en) * | 2005-11-03 | 2008-07-15 | The Boeing Company | Smart repair patch and associated method |
US7935205B2 (en) * | 2006-06-19 | 2011-05-03 | United Technologies Corporation | Repair of composite sandwich structures |
US7628879B2 (en) * | 2007-08-23 | 2009-12-08 | The Boeing Company | Conductive scrim embedded structural adhesive films |
GB0721546D0 (en) * | 2007-11-01 | 2007-12-12 | Rolls Royce Plc | Composite material repair |
US8540909B2 (en) * | 2009-03-09 | 2013-09-24 | The Boeing Company | Method of reworking an area of a composite structure containing an inconsistency |
US8617694B1 (en) * | 2009-03-09 | 2013-12-31 | The Boeing Company | Discretely tailored multi-zone bondline for fail-safe structural repair |
US8409384B2 (en) * | 2009-03-09 | 2013-04-02 | The Boeing Company | Predictable bonded rework of composite structures |
US8449703B2 (en) * | 2009-03-09 | 2013-05-28 | The Boeing Company | Predictable bonded rework of composite structures using tailored patches |
-
2009
- 2009-03-10 US US12/401,541 patent/US20100233424A1/en not_active Abandoned
-
2010
- 2010-03-04 ES ES10707416.3T patent/ES2564837T3/es active Active
- 2010-03-04 EP EP10707416.3A patent/EP2406071B1/en active Active
- 2010-03-04 WO PCT/US2010/026229 patent/WO2010104741A1/en active Application Filing
- 2010-03-04 JP JP2011554087A patent/JP2012520205A/ja active Pending
-
2015
- 2015-09-01 JP JP2015172206A patent/JP6162186B2/ja active Active
-
2017
- 2017-06-13 JP JP2017116163A patent/JP2017213900A/ja active Pending
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3995080A (en) * | 1974-10-07 | 1976-11-30 | General Dynamics Corporation | Filament reinforced structural shapes |
JP2007532384A (ja) * | 2004-04-06 | 2007-11-15 | ザ・ボーイング・カンパニー | 航空機胴体およびその他の構造の複合バレルセクション、および係るバレルセクションを製造する方法およびシステム |
US20060060705A1 (en) * | 2004-09-23 | 2006-03-23 | Stulc Jeffrey F | Splice joints for composite aircraft fuselages and other structures |
JP2008514484A (ja) * | 2004-09-23 | 2008-05-08 | ザ・ボーイング・カンパニー | 複合航空機胴体および他の構造物のための継手接合 |
JP2008517812A (ja) * | 2004-10-27 | 2008-05-29 | ザ・ボーイング・カンパニー | 中間層が不織連続材料で形成された複合部材を形成するための方法およびプリフォーム |
US20060243860A1 (en) * | 2005-04-28 | 2006-11-02 | The Boeing Company | Composite skin and stringer structure and method for forming the same |
JP2007016122A (ja) * | 2005-07-07 | 2007-01-25 | Toray Ind Inc | 炭素繊維強化複合材料 |
Also Published As
Publication number | Publication date |
---|---|
JP2016020206A (ja) | 2016-02-04 |
JP2017213900A (ja) | 2017-12-07 |
EP2406071B1 (en) | 2016-03-02 |
JP6162186B2 (ja) | 2017-07-12 |
US20100233424A1 (en) | 2010-09-16 |
EP2406071A1 (en) | 2012-01-18 |
ES2564837T3 (es) | 2016-03-29 |
WO2010104741A1 (en) | 2010-09-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP6162186B2 (ja) | 準等方性ラミネート材を用いた複合構造 | |
US11084269B2 (en) | Multi-layer metallic structure and composite-to-metal joint methods | |
US9370921B2 (en) | Composite radius fillers and methods of forming the same | |
EP2605902B1 (en) | Composite structures having composite-to-metal joints and method for making the same | |
JP6214215B2 (ja) | 接合された複合翼型及び製造方法 | |
EP2871050B1 (en) | Laminated composite radius filler with geometric shaped filler element and method of forming the same | |
US10005267B1 (en) | Formation of complex composite structures using laminate templates | |
EP2650120B1 (en) | Multi-layer metallic structure | |
US8875931B2 (en) | Composite sandwich shell edge joint |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20130118 |
|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20130118 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20140115 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20140311 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20140611 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20140618 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20140620 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20150106 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20150728 |