WO2015146690A1 - 複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法 - Google Patents

複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法 Download PDF

Info

Publication number
WO2015146690A1
WO2015146690A1 PCT/JP2015/057786 JP2015057786W WO2015146690A1 WO 2015146690 A1 WO2015146690 A1 WO 2015146690A1 JP 2015057786 W JP2015057786 W JP 2015057786W WO 2015146690 A1 WO2015146690 A1 WO 2015146690A1
Authority
WO
WIPO (PCT)
Prior art keywords
composite material
area
hole
continuous fibers
region
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.)
Ceased
Application number
PCT/JP2015/057786
Other languages
English (en)
French (fr)
Inventor
聖紘 柏木
野中　吉紀
阿部　俊夫
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to EP15770101.2A priority Critical patent/EP3103623B1/en
Priority to US15/117,895 priority patent/US10137664B2/en
Priority to BR112016020521-9A priority patent/BR112016020521A2/pt
Priority to RU2016135195A priority patent/RU2645500C1/ru
Priority to CA2940463A priority patent/CA2940463C/en
Priority to CN201580009194.4A priority patent/CN106029346B/zh
Publication of WO2015146690A1 publication Critical patent/WO2015146690A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • 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
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/02—Bending or folding
    • 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
    • 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
    • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two-dimensional [2D] structure
    • B29C70/228—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two-dimensional [2D] structure the structure being stacked in parallel layers with fibres of adjacent layers crossing at substantial angles
    • 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
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • 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
    • B32B3/26—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 particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/266—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 particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
    • 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
    • B32B5/06—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 a fibrous or filamentary layer mechanically connected, e.g. by needling to another layer, e.g. of fibres, of paper
    • 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
    • B32B5/14—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 a layer differing constitutionally or physically in different parts, e.g. denser near its faces
    • 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
    • B32B5/14—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 a layer differing constitutionally or physically in different parts, e.g. denser near its faces
    • B32B5/142—Variation across the area of the 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
    • 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
    • B32B7/03—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 with respect to the orientation of features
    • 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
    • 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
    • B64C1/12—Construction or attachment of skin panels
    • 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
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • 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
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1476—Canopies; Windscreens or similar transparent elements
    • B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/20—Integral or sandwich constructions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water
    • 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
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • 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
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • B29K2105/10—Cords, strands or rovings, e.g. oriented cords, strands or rovings
    • B29K2105/101—Oriented
    • 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
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • B29K2105/10—Cords, strands or rovings, e.g. oriented cords, strands or rovings
    • B29K2105/101—Oriented
    • B29K2105/105—Oriented uni directionally
    • 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
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • B29K2105/10—Cords, strands or rovings, e.g. oriented cords, strands or rovings
    • B29K2105/101—Oriented
    • B29K2105/108—Oriented arranged in parallel planes and crossing at substantial angles
    • 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
    • B29K2307/00—Use of elements other than metals as reinforcement
    • B29K2307/04—Carbon
    • 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
    • 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
    • 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
    • B29L2031/737—Articles provided with holes, e.g. grids, sieves
    • 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
    • B32B2250/00—Layers arrangement
    • B32B2250/20—All layers 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
    • 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
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B32B2260/023—Two or more layers
    • 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
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/07—Parts immersed or impregnated in a matrix
    • 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
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/10—Fibres of continuous length
    • 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
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/10—Fibres of continuous length
    • B32B2305/20—Fibres of continuous length in the form of a non-woven mat
    • 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
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/54—Yield strength; Tensile strength
    • 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
    • B32B2313/00—Elements other than metals
    • B32B2313/04—Carbon
    • 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
    • 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
    • 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
    • B32B5/28—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 impregnated with or embedded in a plastic substance
    • 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
    • Y10T428/16—Two dimensionally sectional layer
    • 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
    • Y10T428/16—Two dimensionally sectional layer
    • Y10T428/162—Transparent or translucent layer or section
    • 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
    • Y10T428/16—Two dimensionally sectional layer
    • Y10T428/163—Next to unitary web or sheet of equal or greater extent
    • Y10T428/164—Continuous two dimensionally sectional layer
    • 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
    • Y10T428/24074—Strand or strand-portions
    • Y10T428/24083—Nonlinear strands or strand-portions
    • 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
    • Y10T428/24074—Strand or strand-portions
    • Y10T428/24091—Strand or strand-portions with additional layer[s]
    • Y10T428/24099—On each side of strands or strand-portions
    • 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
    • Y10T428/24074—Strand or strand-portions
    • Y10T428/24116—Oblique to direction of web
    • 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
    • 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.]
    • Y10T428/24132—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in different layers or components parallel
    • 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.]
    • Y10T428/24273—Structurally defined web or sheet [e.g., overall dimension, etc.] including aperture
    • Y10T428/24322—Composite web or sheet
    • 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.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree

Definitions

  • the present invention relates to a composite structure, an aircraft wing and an aircraft fuselage provided with the composite structure, and a method for manufacturing the composite structure.
  • the present invention is particularly directed to a composite structure having a plurality of holes formed side by side in one direction.
  • FRP fiber reinforced plastic
  • JP 2013-180627 A (Claims 1 and 3)
  • ⁇ Holes may be formed in such composites for inspection or for access during assembly.
  • stress concentration occurs in the peripheral region of the hole. Even if the stress concentration portion reaches the yield stress, the metal does not break immediately, but reaches a final fracture with plastic deformation.
  • the static strength is evaluated by the net stress obtained by dividing the load by the cross-sectional area excluding the holes.
  • composite materials have less plastic deformation than metal, they are highly sensitive to stress concentration (holes, notches), and it is necessary to consider stress concentration in static strength evaluation. As a result, the plate thickness around the hole is increased for reinforcement, and the “light and strong” advantage may not be utilized.
  • Patent Document 1 the tensile rigidity and / or compression rigidity in one direction of the peripheral area of the hole is made smaller than the tensile rigidity and / or compression rigidity in one direction of the other area surrounding the peripheral area.
  • the stress concentration applied to the peripheral region of the hole is alleviated to reduce reinforcement.
  • the fiber orientation in the other region is 0 °
  • the fiber orientation in the peripheral region of the hole is 45 ° or ⁇ 45 °.
  • the other region is adjacent to the peripheral region, but when two composite materials (peripheral region and other region) having different fiber orientations are abutted, the boundary portion (adjacent portion) that abuts is continuous with fibers.
  • the resin serving as the base material transmits a load, the strength of the composite structure may be reduced.
  • Patent Document 1 In the main wing of an aircraft described in Patent Document 1, a main load is applied in the direction in which the holes are arranged, but a shear load may be applied at the same time.
  • other regions having different fiber orientations from the peripheral region are adjacent to both sides of the peripheral region, which may cause a decrease in strength in a direction orthogonal to the main load direction.
  • the boundary where the fibers are discontinuous and the fiber orientation is switched is present on the extended line having a diameter orthogonal to the main load direction of the hole, the risk of strength reduction increases.
  • the present invention has been made in view of such circumstances, and an object thereof is to provide a lightweight composite structure while suppressing a decrease in strength.
  • the present invention is a composite material made of fiber reinforced plastic that extends in one direction and is formed by arranging a plurality of holes at intervals in the one direction.
  • the peripheral region of the hole has a composite material reinforced with continuous fibers aligned in the longitudinal direction, and a center line of the width W of the composite material.
  • a first area which is bent so as to pass between adjacent holes and meanders in the one direction, and the tensile rigidity and / or the compression rigidity of the peripheral area in the one direction is the peripheral area.
  • the tensile rigidity in one direction of the peripheral area of the hole is smaller than the tensile rigidity in one direction of the other area surrounding the peripheral area of the hole, the tensile load is mainly borne by the other area. Therefore, since the tensile load applied to the peripheral region of the hole becomes relatively small, the stress concentration applied to the peripheral region of the hole is relieved. Thereby, the reinforcement of the peripheral region of the hole can be reduced as compared with the case where the peripheral region of the hole has the same tensile rigidity as the other region.
  • the compressive rigidity in one direction of the peripheral region of the hole is smaller than the compressive rigidity in one direction of the other region surrounding the peripheral region of the hole, the compressive load is mainly borne by the other region. Therefore, since the compressive load applied to the peripheral region of the hole is relatively small, the stress concentration applied to the peripheral region of the hole is relieved. Thereby, the reinforcement of the peripheral region of the hole can be reduced as compared with the case where the peripheral region of the hole has the same compression rigidity as that of the other region.
  • the tensile stiffness and the compressive stiffness in one direction of the peripheral region of the hole are changed to the tensile stiffness and the compressive stiffness in one direction of the other region. It is sufficient that the other region mainly bears the tensile load and the compressive load.
  • the peripheral region includes a first area composed of a composite material (composite material A) reinforced with continuous fibers aligned in the longitudinal direction.
  • composite material A composite material reinforced with continuous fibers aligned in the longitudinal direction.
  • the composite material A maintains a continuous state even when it is bent. Compared with the case where a short fiber is used, the intensity
  • the fibers are continuous, there is no concern that a gap between the fibers is generated in the portion where the fiber orientation in the first area is switched. Thereby, it becomes a composite material structure of higher precision than before.
  • a single composite material A can be disposed over a plurality of holes, so that a composite material structure can be manufactured efficiently.
  • the composite material A can also be arranged by a machine.
  • the first area includes an inclined portion in which the continuous fiber faces ⁇ 30 ° or more and ⁇ 60 ° or less, preferably ⁇ 45 ° when the one direction is set to 0 °,
  • the inclined portion may be disposed between adjacent holes.
  • the fiber is oriented in the direction of ⁇ 30 ° or more and ⁇ 60 ° or less, preferably ⁇ 45 °, so that the strength in the shearing direction (direction orthogonal to one direction, that is, ⁇ 90 ° direction) is high.
  • the torsional rigidity can be increased.
  • the said 1st area contains the parallel part arrange
  • the parallel portion may be disposed at a position including an outer edge of the first area in a region parallel to a diameter of the hole in a 0 ° direction.
  • the outer edge of the first area in the region parallel to the 0 ° direction diameter of the hole is the peripheral region at the boundary with the other region.
  • the composite material A meanders such that the center line of the width W of the composite material A passes between the holes. Looking at the 0 ° diameter of the hole as an axis, the composite A on one side for one hole is on the other side for the next hole.
  • the width W is 1 / ⁇ 2 or less of the center distance L between adjacent holes.
  • the width W of the composite material A is set to 1 / ⁇ 2 or less of the distance L between the centers of the holes.
  • the parallel part can be arranged on an extension line of the diameter facing the ⁇ 90 ° direction.
  • the parallel portion may be a region parallel to a diameter of the hole in a 0 ° direction.
  • the composite material reinforced with continuous fibers aligned in the longitudinal direction includes a layer including the first area A that repeats bending in the order of a peak portion and a valley portion, and is aligned in the longitudinal direction.
  • the layer including the first area B in which the composite material reinforced with continuous fibers repeats bending in the order of valley and peak, and the peak of the first area A and the valley of the first area B are vertically It is preferable that the layers are laminated.
  • the fibers are discontinuous from other adjacent areas in the same layer, and the direction of the fibers is different.
  • the peak of the first area A and the valley of the first area B are vertically paired so that the boundary between the inclined portion and the adjacent area is shifted in the vertical direction. Can do. Thereby, the risk of strength reduction in the ⁇ 90 ° direction can be dispersed.
  • the hole may be an access hole formed in a lower skin of an aircraft wing.
  • the lower skin forms the lower part of the torque box that bears the load applied to the main wing of the aircraft. Therefore, a tensile load is applied to the lower surface outer plate in the longitudinal direction of the main wing during flight. Since the predetermined area on the periphery of the access hole is the above peripheral area and the area surrounding this peripheral area is the above other area, the tensile load is mainly borne by the other area, and only a relatively small tensile load is applied to the peripheral area. Absent. Therefore, reinforcement of the peripheral area of the access hole can be reduced, and a lightened main wing can be provided.
  • the hole may be a window hole formed in an outer plate of an aircraft fuselage.
  • a tensile load and a compressive load are applied to the aircraft fuselage in the longitudinal direction. Since the predetermined region of the peripheral edge of the window hole is the peripheral region and the region surrounding the peripheral region is the other region, the tensile load and the compressive load are mainly borne by the other region, and the peripheral region is relatively small. Only tensile and compressive loads are applied. Accordingly, the reinforcement of the peripheral region of the window hole can be reduced, and a lightweight aircraft fuselage can be provided.
  • the present invention is a fiber reinforced plastic composite material that extends in one direction and has a plurality of holes arranged side by side in the one direction, and a tensile load and / or a compressive load is applied in the one direction.
  • a composite material reinforced with continuous fibers aligned in the longitudinal direction is so arranged that the center line of the width W of the composite material is sandwiched between adjacent holes. Bending and meandering in one direction, the tensile stiffness and / or compression stiffness in the one direction of the peripheral region of the hole, the tensile stiffness and / or compression stiffness in the one direction of the other region surrounding the peripheral region
  • a method of manufacturing a composite structure that is smaller than the above is provided.
  • the continuous fiber when the one direction is set to 0 °, has a direction of ⁇ 30 ° to ⁇ 60 °, preferably ⁇ 45 ° between adjacent holes.
  • a composite material reinforced with continuous fibers aligned in the longitudinal direction so as to face may be disposed.
  • the composite reinforced with continuous fibers that are aligned in the longitudinal direction so that the continuous fibers are oriented in the 0 ° direction at positions including an extension line having a diameter facing the ⁇ 90 ° direction of the holes. It is good to arrange the material.
  • a composite material reinforced with continuous fibers aligned in the longitudinal direction so that the continuous fibers in a region parallel to the diameter in the 0 ° direction of the holes face the 0 ° direction is disposed. Also good.
  • the aircraft wing and aircraft fuselage provided with the composite material structure, and the composite material structure manufacturing method the composite material reinforced with continuous fibers aligned in the longitudinal direction is meandered.
  • the composite material reinforced with continuous fibers aligned in the longitudinal direction is meandered.
  • FIG. 3 is a transverse sectional view taken along line AA in FIG. 2. It is the principal part disassembled perspective view which showed the laminated structure of the fiber sheet. It is a principal part top view of the 2nd layer in 1st Embodiment. It is a principal part top view of the 2nd layer in 2nd Embodiment.
  • FIG. 1 (a) shows a lower skin 3 of a main wing 1 of an aircraft.
  • the lower surface outer plate 3 is formed of a composite material structure made of fiber reinforced plastic (FRP: Fiber Reinforced Plastics).
  • FRP Fiber Reinforced Plastics
  • the broken line shown in the figure shows the outline of the main wing 1 including flaps and slats.
  • the lower surface outer plate 3 includes a front spar 20 and a rear spar 22 which are side surface erected from both ends in the width direction of the lower surface outer plate 3, and upper ends of the front spar 20 and the rear spar 22.
  • a box-shaped torque box is formed together with the upper surface outer plate 24 that connects the two, and bears the load of the main wing 1.
  • a plurality of stringers 26 are provided in the longitudinal direction of the main wing 1.
  • the stringer 26 is a composite material made of FRP like the lower outer plate 3 and the like.
  • Each stringer 26 is fixed to the inner surfaces of the lower surface outer plate 3 and the upper surface outer plate 24 and mainly bears the load in the longitudinal direction of the main wing 1.
  • ribs 28 are provided so as to divide the internal space into a plurality of parts in the longitudinal direction.
  • the ribs 28 have a plate shape extending in the width direction (direction orthogonal to the longitudinal direction) of the main wing 1, and a plurality of ribs 28 are arranged with a predetermined interval in the longitudinal direction.
  • the front and rear end portions of each rib 28 are fixed to the front spar 20 and the rear spar 22 by predetermined fasteners 30 such as bolts and nuts, respectively.
  • an access hole (hole) 5 is provided on the lower outer plate 3 for use in checking or assembling a fuel tank provided in the main wing 1 along the extending direction of the main wing 1.
  • a plurality are formed at predetermined intervals.
  • the lower outer plate 3 includes a peripheral region 3a positioned around each access hole 5 and another region 3b surrounding the peripheral region 3a, and is formed of an integral composite material.
  • the peripheral region 3a is provided over a predetermined width d on both sides of the axis with a line along the extending direction of the main wing 1 passing through the center of each access hole 5 as an axis.
  • the “width d” is the distance of the peripheral region in the direction orthogonal to the extending direction of the main wing 1.
  • the other region 3b is located around the peripheral region 3a, and substantially the entire region other than the peripheral region 3a is defined as the existence range.
  • the peripheral region 3a and the other region 3b constituting the lower surface outer plate 3 are a composite material mainly composed of carbon fiber reinforced plastic (CFRP: Carbon Fiber Reinforced Plastics).
  • CFRP Carbon Fiber Reinforced Plastics
  • the number of laminated layers of the composite material is determined by the strength to be borne, and is, for example, about several tens.
  • the ratio of the orientation of the carbon fibers in the peripheral region 3a is different from that in the other region 3b, and when the extending direction of the main wing 1 is 0 °, it is ⁇ 30 ° or more ⁇ 60 ° between the adjacent holes 5 and 5
  • the main component is ⁇ 45 °. That is, the orientation ratio of ⁇ 30 ° to ⁇ 60 °, preferably ⁇ 45 °, is larger than that of the other region 3b.
  • each fiber direction is adjusted so that the ⁇ 45 ° orientation ratio is 70% or more.
  • a plurality of fiber sheets are stacked and configured.
  • the fiber in the 0 ° direction may be changed from carbon fiber to glass fiber (Glass fiber) or aramid fiber (Aramid fiber).
  • FIG. 4 is an exploded perspective view of a main part illustrating a laminated structure of fiber sheets.
  • the stacked structure in FIG. 4 is composed of a first layer 41 to a fifth layer 45.
  • the positions of the hole 5, the peripheral region 3a, and the other region 3b in the first layer 41 to the fifth layer 45 correspond to each other in the vertical direction.
  • the direction in which the holes 5 are arranged is 0 °.
  • the first layer 41 is a layer in which fibers are oriented in the + 45 ° direction.
  • the first layer 41 is formed by arranging + 45 ° fiber sheets over the peripheral region 3a and the other region 3b.
  • the second layer 42 is a layer in which fibers are mainly oriented in the 0 ° direction.
  • the second layer 42 is formed by disposing the peripheral region composite material in the peripheral region 3a and disposing the other region composite material in the other region 3b. Detailed arrangement of the composite material for the peripheral region and the composite material for other regions will be described later.
  • the third layer 43 is a layer in which fibers are oriented in the 90 ° direction.
  • the third layer 43 is formed by arranging 90 ° fiber sheets over the peripheral region 3a and the other region 3b.
  • the fourth layer 44 is a layer in which fibers are mainly oriented in the 0 ° direction.
  • the fourth layer 44 is formed by disposing the peripheral region composite material in the peripheral region 3a and disposing the other region composite material in the other region 3b.
  • the fifth layer 45 is a layer in which fibers are oriented in the + 45 ° direction.
  • the fifth layer 45 is formed by arranging + 45 ° fiber sheets over the peripheral region 3a and the other region 3b.
  • FIG. 5 is a main part plan view of the second layer 42.
  • the second layer 42 includes a plurality of holes 5 formed side by side along the direction t in which the main load is applied, a peripheral region 3 a around the hole 5, and a peripheral region 3 a. It is comprised from the other area
  • the peripheral region 3a includes a first area 10 where the first peripheral region composite material is disposed and a second area 11 where the second peripheral region composite material is disposed.
  • the first peripheral region composite material and the second peripheral region composite material are composite materials (composite material A) reinforced with continuous fibers aligned in the longitudinal direction.
  • continuous fiber indicates a state in which the peripheral region 3 a is not cut in the t direction.
  • the composite material A is a sheet-like prepreg or a semi-impregnated prepreg.
  • the first area 10 is formed by meandering the composite material A by bending the composite material A so that the center line of the width W of the composite material A passes between the adjacent holes 5 and 5.
  • the composite material A may be meandered to the target with a line passing through the centers of the plurality of holes 5 as an axis.
  • the composite A may have a width W obtained by arranging a plurality of narrow prepregs.
  • the width W may be a length that allows the gap between the adjacent holes 5 and 5 to be filled with the composite material A when the composite material A is meandered.
  • the width W is the length of the composite material in the direction orthogonal to the orientation of the continuous fibers.
  • the first area 10 includes an inclined portion 12 and a parallel portion 13.
  • the inclined portions 12 and the parallel portions 13 are alternately arranged.
  • FIG. 5 when changing from the inclined portion 12 to the parallel portion 13, the composite A is bent so that the fiber orientation is switched at a predetermined angle, but is bent so that the fiber orientation gradually changes so as to draw a curve. May be.
  • the inclined portion 12 is located between the adjacent holes 5 and the continuous fibers in the composite A are oriented in the direction of ⁇ 30 ° to ⁇ 60 °, preferably ⁇ 45 °.
  • the parallel portion 13 is disposed at a position including an extension line of the short diameter (diameter facing ⁇ 90 ° direction) of the hole 5.
  • the parallel part 13 is good also at the position containing the outer edge 13a of the 1st area 10 in the area
  • the parallel portion 13 is at least partially in contact with the hole 5.
  • the second area 11 is a valley that is a bent portion of the meandering first area.
  • the second area 11 is formed by arranging the second peripheral region composite material in the valley so that the fiber orientation is in the 0 ° direction.
  • the fourth layer 44 has the same configuration as the second layer 42. However, it is preferable that the first area of the fourth layer 44 has a meandering shape in which the arrangement of the mountain and valley portions is opposite to that of the first area of the second layer 42. Specifically, assuming that the first area 10 in the second layer 42 has a meandering shape in which the composite material A repeats bending in the order of peaks and valleys, the first area in the fourth layer 44 is the composite material A. Is a meandering shape that repeats bending in the order of valley and peak. When the second layer 42 and the fourth layer 44 including the first area are stacked, the peak portion of the first area of the second layer 42 and the valley portion of the first area of the fourth layer 44 are paired vertically. Become.
  • the peripheral region 3a is ⁇ 30 ° or more compared to the other region 3b.
  • An orientation ratio of ⁇ 60 ° or less, preferably ⁇ 45 °, can be mainly used.
  • the peripheral region 3a is mainly composed of fibers with an orientation of ⁇ 30 ° to ⁇ 60 °, preferably ⁇ 45 °, compared to the other regions 3b, and has a low rigidity with respect to a tensile load in the 0 ° direction. Because it is. Therefore, since only a small tensile load is applied to the peripheral area 3a compared to the other areas 3b, the required strength of the peripheral area 3a is reduced. That is, it is not necessary to provide a reinforcing laminate for increasing the thickness around the hole. For easy understanding, the reinforcing laminate 104 is also shown in FIG. In this way, the reinforcing laminate 104 is not necessary, and the weight can be reduced by this amount.
  • the peripheral region 3a mainly has ⁇ 30 ° or more and ⁇ 60 ° or less, preferably ⁇ 45 °, so that the rigidity in the shear direction, that is, the torsional rigidity is enhanced. Therefore, the peripheral region 3a bears a torsional load without bearing an axial force (tensile load).
  • the peripheral region 3a includes a first area 10 formed by meandering the composite material A reinforced with continuous fibers aligned in the longitudinal direction. Since the composite material A includes continuous fibers, the fibers are maintained in a continuous state even when bent. Since the fibers are continuous, the strength in the 0 ° direction can be improved as compared with the case where short fibers are used. By using a composite material reinforced with continuous fibers, there is no concern that a gap is generated at the boundary where the fiber orientation in the first area changes. Thereby, it becomes a composite material structure of higher precision than before.
  • the first area 10 can be formed around a plurality of holes, so that the composite material A can be arranged by a machine and is efficient. Can be manufactured.
  • the tensile rigidity in the 0 ° direction (one direction) is reduced, and a region allowing elongation in the tensile direction (and / or the compression direction) is realized. be able to.
  • the fiber is oriented in the direction of ⁇ 30 ° or more and ⁇ 60 ° or less, preferably ⁇ 45 °, the strength in the shearing direction (direction orthogonal to one direction, that is, ⁇ 90 ° direction) Increases and torsional rigidity can be increased.
  • the fiber direction in the peripheral region 3a can be aligned with the fiber direction in the adjacent other region 3b. Thereby, the intensity
  • the boundary of the fiber sheets is shifted in the vertical direction by making the peak of the first area A of one layer and the valley of the first area B of another layer pair. be able to. Thereby, the risk of strength reduction in the ⁇ 90 ° direction can be dispersed.
  • the composite structure according to the present embodiment has the same configuration as that of the first embodiment except that the range in which the parallel portion is provided is different.
  • FIG. 6 the principal part top view of the 2nd layer 52 which concerns on this embodiment is shown.
  • the parallel part 13 is arrange
  • FIG. The length of the parallel portion is the same as the long diameter of the hole 5.
  • the strength around the holes in the 0 ° direction can be improved. Since there is no boundary at which the fiber direction is switched in the ⁇ 90 ° direction of the hole, the strength around the hole in the ⁇ 90 ° direction can be improved.
  • this invention demonstrated the application to the lower surface outer plate 3 of the main wing 1, this invention is not limited to this, If it is a composite material structure which has a hole, it can apply widely.
  • the same configuration as that of the lower surface outer plate 3 may be applied to the upper surface outer plate constituting the torque box together with the lower surface outer plate 3.
  • This embodiment can also be applied to a tail wing or the like.
  • the above embodiment can also be applied to an aircraft fuselage in which a window hole is formed.
  • the composite material structure of the present invention is not limited to an aircraft, and can be applied to, for example, ships and vehicles.
  • CFRP carbon fiber reinforced plastic
  • GFRP Glass Fiber Reinforced Plastic
  • AFRP Aramid Fiber Reinforced Plastic

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
  • Compositions Of Macromolecular Compounds (AREA)

Abstract

強度低下を抑制しつつ、軽量な複合材構造体を提供することを目的とする。一方向に延在するとともに、複数の孔（５）が一方向に間隔を空けて並べて形成された繊維強化プラスチック製の複合材とされ、一方向に引張り荷重および／または圧縮荷重が負荷される複合材構造体において、孔（５）の周縁領域（３ａ）は、長手方向に引き揃えられた連続繊維で強化された複合材が前記複合材の幅Ｗの中心線が隣合う孔（５）と孔（５）との間をぬうように屈曲し一方向に向かって蛇行してなる第１エリア（１０）を含み、孔（５）の周縁領域（３ａ）の一方向における引張り剛性および／または圧縮剛性が、該周縁領域（３ａ）を取り囲む他領域（３ｂ）の一方向における引張り剛性および／または圧縮剛性よりも小さい。

Description

複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法
　本発明は、複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法に関するものである。本発明は、特に、一方向に並んで形成された複数の孔を有する複合材構造体を対象としている。
　航空機、船舶、車両等の分野にて、高強度かつ軽量化された構造体として繊維強化プラスチック（ＦＲＰ：Ｆｉｂｅｒ　Ｒｅｉｎｆｏｒｃｅｄ　Ｐｌａｓｔｉｃｓ）製の複合材が広く用いられている（特許文献１）。複合材は金属に比べて「軽くて強い」ことが利点とされている。
特開２０１３－１８０６２７号公報（請求項１、請求項３）
　このような複合材に対して、点検のためまたは組立時のアクセス用のために、孔が形成されることがある。孔が形成された場合、孔の周縁領域には応力集中が生じる。金属は、応力集中部が降伏応力に達してもすぐに破断せず、塑性変形を伴って最終破壊に至る。一般的な設計では、例えば孔を有する平板の場合、孔を除く断面積で荷重を除したネット応力で静的強度を評価する。一方、複合材は金属に比べて塑性変形が少ないため応力集中（孔、切欠き）に対する感度が高く、静的強度評価においても応力集中を考慮する必要がある。この結果、孔周りの板厚を増やして補強することとなり、「軽くて強い」利点を生かせないことがある。
　上記課題を解決するため、特許文献１では孔の周縁領域の一方向における引張り剛性および／または圧縮剛性を、該周縁領域を取り囲む他領域の一方向における引張り剛性および／または圧縮剛性よりも小さくし、孔の周縁領域に加わる応力集中を緩和させて補強を少なくしている。特許文献１では、他領域の繊維配向を０°とし、孔の周縁領域の繊維配向を４５°または－４５°としている。
　特許文献１において、他領域は周縁領域に隣接しているが、繊維配向が異なる２つの複合材（周縁領域および他領域）を突き合わせた場合、突合せた境界部分（隣接部分）は繊維が連続しておらず、基材となる樹脂が荷重を伝達することとなるため、複合材構造体の強度を低下させる要因となることがある。
　特許文献１に記載の航空機の主翼などでは孔が並んだ方向に主荷重がかかるが、同時に剪断荷重もかかることがある。特許文献１では、周縁領域を挟んだ両側に、周縁領域とは繊維配向の異なる他領域が隣接しているため、主荷重方向と直交する方向での強度低下の要因となりうる。繊維が不連続であり且つ繊維配向が切り替わる境界が、孔の主荷重方向と直交する径の延長線上に存在すると、強度低下のリスクは高くなる。
　本発明は、このような事情に鑑みてなされたものであって、強度低下を抑制しつつ、軽量な複合材構造体を提供することを目的とする。
　上記課題を解決するために、本発明は、一方向に延在するとともに、複数の孔が前記一方向に間隔を空けて並べて形成された繊維強化プラスチック製の複合材とされ、前記一方向に引張り荷重および／または圧縮荷重が負荷される複合材構造体において、前記孔の周縁領域は、長手方向に引き揃えられた連続繊維で強化された複合材が前記複合材の幅Ｗの中心線が隣合う孔と孔との間をぬうように屈曲し前記一方向に向かって蛇行してなる第１エリアを含み、前記周縁領域の前記一方向における引張り剛性および／または圧縮剛性が、該周縁領域を取り囲む他領域の前記一方向における引張り剛性および／または圧縮剛性よりも小さい複合材構造体を提供する。
　孔の周縁領域の一方向における引張り剛性が、孔の周縁領域を取り囲む他領域の一方向における引張り剛性よりも小さいので、引張り荷重は他領域が主として負担することになる。したがって、孔の周縁領域に加わる引張り荷重が相対的に小さくなるので、孔の周縁領域に加わる応力集中が緩和される。これにより、孔の周縁領域を他領域と同等の引張り剛性にした場合に比べて、孔の周縁領域の補強を少なくすることができる。
　孔の周縁領域の一方向における圧縮剛性が、孔の周縁領域を取り囲む他領域の一方向における圧縮剛性よりも小さい場合には、圧縮荷重は他領域が主として負担することになる。したがって、孔の周縁領域に加わる圧縮荷重が相対的に小さくなるので、孔の周縁領域に加わる応力集中が緩和される。これにより、孔の周縁領域を他領域と同等の圧縮剛性にした場合に比べて、孔の周縁領域の補強を少なくすることができる。
　複合材構造体に引張り荷重および圧縮荷重が加わる場合（すなわち曲げ荷重が加わる場合）には、孔の周縁領域の一方向における引張り剛性および圧縮剛性を、他領域の一方向における引張り剛性および圧縮剛性よりも小さくして、引張り荷重および圧縮荷重を他領域が主として負担することとすればよい。
　周縁領域は、長手方向に引き揃えられた連続繊維で強化された複合材（複合材Ａ）で構成された第１エリアを含む。複合材Ａは、屈曲させることで繊維の向きを異なる方向に向けることができる。繊維の向きを変えて配置することで、複合材構造体の強度・剛性を変化させられうる。繊維を一方向に対して傾斜させるよう複合材Ａが配置された領域では、一方向における引張り剛性および圧縮剛性は、他領域の一方向における引張り剛性および圧縮剛性よりも小さくなる。また、繊維を一方向に向けるよう複合材Ａが配置された場合では、繊維配向が他領域と揃うため周縁領域と他領域との境界における強度低下のリスクを排除できる。
　複合材Ａは、屈曲させても繊維は連続した状態が維持される。繊維が連続していることで、短繊維を用いた場合と比較して、一方向における強度を向上できる。本発明は、繊維が連続しているため、第１エリア内の繊維配向が切り替わる部分において繊維の隙間が発生する懸念もない。これにより、従来よりも高精度の複合材構造体となる。
　孔の間をぬうように複合材Ａを蛇行させることで、複数の孔にわたって一枚の複合材Ａを配置できるため、効率的に複合材構造体を製造できるようになる。複合材Ａは、機械により配置することもできる。
　上記発明の一態様において、前記第１エリアは、前記一方向を０°とした場合に前記連続繊維が±３０°以上±６０°以下、好ましくは±４５°の方向を向く傾斜部を含み、前記傾斜部が、隣合う孔と孔との間に配置されているとよい。
　傾斜部を孔と孔との間に配置することで、０°方向（一方向）の引張り剛性が低下して引張り方向（および／または圧縮方向）の伸びを許容する領域を実現することができる。傾斜部では、±３０°以上±６０°以下の方向、好ましくは±４５°方向に繊維が向いているので、剪断方向（一方向に対して直交する方向、すなわち±９０°方向）の強度が大きくなり、捩り剛性を高めることができる。
　上記発明の一態様において、前記第１エリアは、前記連続繊維が０°方向を向くよう配置された平行部を含み、前記平行部は、前記第１エリアの少なくとも前記孔の±９０°方向を向く直径の延長線を含む位置に配置され、前記孔と接しているとよい。
　孔の±９０°方向を向く直径の延長線上に孔と接するよう平行部を設けることで、破断しやすい箇所の強度を低下させずに、孔の周縁領域に加わる応力集中を緩和することが可能となる。これにより、実体強度の強い複合材構造体となる。
　上記発明の一態様において、前記平行部は、前記孔の０°方向の直径に並行する領域にある前記第１エリアの外縁を含む位置に配置されているとよい。
　孔の０°方向の直径に並行する領域にある第１エリアの外縁とは、すなわち他領域との境界にある周縁領域である。複合材Ａは、複合材Ａの幅Ｗの中心線が孔と孔との間をぬうように蛇行している。孔の０°方向の直径を軸として見ると、一の孔に対しては一方の側にある複合材Ａは、次の孔に対しては他方の側にくる。他領域との境界に平行部を配置することで、周縁領域での繊維の向きを、隣接する他領域での繊維の向きと揃えることができる。それにより、周縁領域と他領域との接続部における±９０°方向の強度低下を抑制できる。
　上記発明の一態様において、１の前記傾斜部の連続繊維の向きが次の傾斜部の連続繊維の向きと直交する場合、前記幅Ｗは隣合う孔の中心間距離Ｌの１／√２以下と定義され得る。
　複合材Ａは孔と孔との間を蛇行しているため、一の傾斜部の繊維の方向と、次に来る傾斜部の繊維の方向は違う方を向く。一の傾斜部の繊維の方向に対して次の傾斜部の繊維の方向が直角である場合、複合材Ａの幅Ｗを孔の中心間距離Ｌの１／√２以下とすることで、孔の±９０°方向を向く直径の延長線上に平行部を配置できる。
　上記発明の一態様において、前記平行部は、前記孔の０°方向の直径と並行する領域であってもよい。
　それにより、孔と並行する領域すべてが平行部となるため、０°方向に対する孔周りの強度を向上できる。孔の±９０°方向において繊維の方向が切り替わる境界がなくなるため、±９０°方向に対する孔周りの強度を向上できる。
　上記発明の一態様において、前記長手方向に引き揃えられた連続繊維で強化された複合材が山部、谷部の順に屈曲を繰り返す第１エリアＡを含む層と、前記長手方向に引き揃えられた連続繊維で強化された複合材が谷部、山部の順に屈曲を繰り返す第１エリアＢを含む層と、が前記第１エリアＡの山部と前記第１エリアＢの谷部とが上下対になるよう積層されていることが好ましい。
　第１エリアの傾斜部は、同一層内において隣接する他のエリアと繊維が不連続であり、かつ、繊維の向きが異なる。上記発明の一態様では、第１エリアＡの山部と第１エリアＢの谷部とが上下対になるようにすることで、傾斜部とそれに隣接するエリアとの境界を上下方向でずらすことができる。それにより、±９０°方向の強度低下リスクを分散できる。
　上記発明の一態様において、前記孔は、航空機の翼の下面外板に形成されたアクセスホールとされ得る。
　下面外板は、航空機の主翼に加わる荷重を負担するトルクボックスの下面部分を構成する。したがって、この下面外板には、飛行時に、主翼長手方向に引張り荷重が加わる。アクセスホールの周縁の所定領域を上記の周縁領域とし、この周縁領域を取り囲む領域を上記の他領域としたので、引張り荷重は主として他領域が負担し、周縁領域には比較的小さな引張り荷重しか加わらない。したがって、アクセスホールの周縁領域の補強を少なくでき、軽量化された主翼を提供することができる。
　上記発明の一態様において、前記孔は、航空機の胴体の外板に形成された窓用孔とされ得る。
　航空機の胴体には、長手方向に引張り荷重および圧縮荷重（すなわち曲げ荷重）が加わる。窓用孔の周縁の所定領域を上記の周縁領域とし、この周縁領域を取り囲む領域を上記の他領域としたので、引張り荷重および圧縮荷重は主として他領域が負担し、周縁領域には比較的小さな引張り荷重および圧縮荷重しか加わらない。したがって、窓用孔の周縁領域の補強を少なくでき、軽量化された航空機胴体を提供することができる。
　本発明は、一方向に延在するとともに、複数の孔が該一方向に間隔を空けて並べて形成された繊維強化プラスチック製の複合材とされ、前記一方向に引張り荷重および／または圧縮荷重が負荷される複合材構造体の製造方法において、長手方向に引き揃えられた連続繊維で強化された複合材を該複合材の幅Ｗの中心線が隣合う孔と孔との間をぬうように屈曲させ前記一方向に向けて蛇行配置し、前記孔の周縁領域の前記一方向における引張り剛性および／または圧縮剛性を、該周縁領域を取り囲む他領域の前記一方向における引張り剛性および／または圧縮剛性よりも小さくする複合材構造体の製造方法を提供する。
　上記発明の一態様において、前記一方向を０°とした場合に、隣合う孔と孔との間で、前記連続繊維が±３０°以上±６０°以下の方向、好ましくは±４５°方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置するとよい。
　上記発明の一態様において、前記孔の±９０°方向を向く直径の延長線を含む位置に、前記連続繊維が０°方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置するとよい。
　上記発明の一態様において、前記孔の０°方向の直径に並行する領域に、外縁において前記連続繊維が０°方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置することが好ましい。
　上記発明の一態様において、前記孔の０°方向の直径に並行する領域の前記連続繊維が０°方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置してもよい。
　本発明の複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法によれば、長手方向に引き揃えられた連続繊維で強化された複合材を蛇行配置することで、強度低下要因が排除された軽量構造を実現可能とする。
本発明の複合材構造体の一実施形態にかかる航空機の主翼の下面外板を示し、（ａ）は平面図であり、（ｂ）は（ａ）のＡ－Ａにおける縦断面図である。 ボックス構造とされた主翼の一部を構成する下面外板およびストリンガを示した斜視図である。 図２のＡ－Ａにおける横断面図である。 繊維シートの積層構造を示した要部分解斜視図である。 第１実施形態における第２層の要部平面図である。 第２実施形態における第２層の要部平面図である。
〔第１実施形態〕
　以下、本発明の一実施形態について、図１から図３を用いて説明する。
　図１（ａ）には、航空機の主翼１の下面外板３が示されている。下面外板３は、繊維強化プラスチック（ＦＲＰ：Ｆｉｂｅｒ　Ｒｅｉｎｆｏｒｃｅｄ　Ｐｌａｓｔｉｃｓ）製の複合材構造体で形成されている。同図に示した破線は、フラップやスラット等を含む主翼１の外形線を示している。
　下面外板３は、図２及び図３に示すように、下面外板３の幅方向両端から立設する側面外板となるフロントスパー２０及びリアスパー２２と、これらフロントスパー２０及びリアスパー２２の上端同士を接続する上面外板２４と共に箱形のトルクボックスを形成しており、主翼１の荷重を負担する。
　主翼１の長手方向には、複数のストリンガ２６が設けられている。ストリンガ２６は、下面外板３等と同様にＦＲＰ製の複合材とされている。各ストリンガ２６は、下面外板３及び上面外板２４の内表面に対して固定されており、主翼１の長手方向の荷重を主として負担する。
　ボックス構造とされた主翼１の内部には、その内部空間を長手方向において複数に分割するようにリブ２８が設けられている。リブ２８は、主翼１の幅方向（長手方向に直交する方向）にわたって延在した板状とされており、長手方向に所定間隔を有して複数配置されている。図３に示すように、各リブ２８の前後の端部は、それぞれ、フロントスパー２０及びリアスパー２２に対してボルト・ナット等の所定のファスナ３０によって固定されている。
　図１に示すように、下面外板３には、主翼１内に設けられた燃料タンクの点検時や組立時等に用いるためのアクセスホール（孔）５が、主翼１の延在方向に沿って所定間隔ごとに複数形成されている。
　下面外板３は、各アクセスホール５の周囲に位置する周縁領域３ａと、この周縁領域３ａを取り囲む他領域３ｂとから成り、一体の複合材料で形成されている。
　周縁領域３ａは、各アクセスホール５の中心を通る主翼１の延在方向に沿った線を軸とし、該軸の両側に所定幅ｄにわたって設けられている。ここで、「幅ｄ」とは、主翼１の延在方向に直交する方向の周縁領域の距離とされる。
　他領域３ｂは、周縁領域３ａの周囲に位置するとともに、周縁領域３ａ以外の略全領域を存在範囲とする。
　下面外板３を構成する周縁領域３ａ及び他領域３ｂは、炭素繊維強化プラスチック（ＣＦＲＰ：Ｃａｒｂｏｎ　Ｆｉｂｅｒ　Ｒｅｉｎｆｏｒｃｅｄ　Ｐｌａｓｔｉｃｓ）が主体とされた複合材となっている。複合材の積層数は、負担する強度によって決定され、例えば数十程度とされる。
　他領域３ｂの炭素繊維の配向の比率は、航空機の構造体として用いられる通常程度とされており、例えば、主翼１の延在方向（長手方向）を０°とした場合、（０°，＋４５°，－４５°，９０°）＝（３０％，３０％，３０％，１０％）となるように、各繊維方向を有する複数の繊維シートが積層されて構成されている。
　周縁領域３ａの炭素繊維の配向の比率は、他領域３ｂとは異なり、主翼１の延在方向を０°とした場合、隣合う孔５と孔５との間において±３０°以上±６０°以下、好ましくは±４５°を主体としたものとなっている。つまり、他領域３ｂよりも±３０°以上±６０°以下、好ましくは±４５°の配向比率を大きくしており、例えば±４５°の配向比率が７０％以上となるように、各繊維方向を有する複数の繊維シートが積層されて構成されている。さらに、０°方向の引張り剛性を低下させるために、０°方向の繊維を炭素繊維からガラス繊維（Ｇｌａｓｓ　ｆｉｂｅｒ）またはアラミド繊維（Ａｒａｍｉｄ　ｆｉｂｅｒ）等に変更しても良い。
　上述のような配合比率を実現する下面外板３の積層構造について、図４を参照して説明する。図４は、繊維シートの積層構造を例示した要部分解斜視図である。図４の積層構造は、第１層４１から第５層４５から構成されている。第１層４１から第５層４５における孔５、周縁領域３ａ及び他領域３ｂの位置は、上下方向でそれぞれ対応している。図４において、孔５が並べられた方向（主翼１の延在方向）を０°とする。
　第１層４１は、繊維が＋４５°方向に配向された層である。第１層４１は、＋４５°繊維シートを周縁領域３ａ及び他領域３ｂにわたって配置して形成する。
　第２層４２は、主に繊維が０°方向に配向された層である。第２層４２は、周縁領域３ａに周縁領域用複合材を配置し、他領域３ｂに他領域用複合材を配置して形成する。周縁領域用複合材及び他領域用複合材の詳しい配置については、後に述べる。
　第３層４３は、繊維が９０°方向に配向された層である。第３層４３は、９０°繊維シートを周縁領域３ａ及び他領域３ｂにわたって配置して形成する。
　第４層４４は、主に繊維が０°方向に配向された層である。第４層４４は、周縁領域３ａに周縁領域用複合材を配置し、他領域３ｂに他領域用複合材を配置して形成する。
　第５層４５は、第１層４１と同様に、繊維が＋４５°方向に配向された層である。第５層４５は、＋４５°繊維シートを周縁領域３ａ及び他領域３ｂにわたって配置して形成する。
　第２層４２について、図５を参照して更に詳しく説明する。図５は、第２層４２の要部平面図である。図５において、第２層４２は、主荷重が負荷される方向ｔに沿って間隔を空けて並べて形成された複数の孔５と、孔５の周りにある周縁領域３ａと、周縁領域３ａを挟んで両側にある他領域３ｂとから構成されている。周縁領域３ａは、第１周縁領域用複合材が配置されてなる第１エリア１０と第２周縁領域用複合材が配置されてなる第２エリア１１とを含む。第１周縁領域用複合材および第２周縁領域用複合材は、長手方向に引き揃えられた連続繊維で強化された複合材（複合材Ａ）である。ここで、「連続繊維」とは周縁領域３ａがｔ方向に切断されていない状態を示す。複合材Ａは、シート状のプリプレグまたは半含浸プリプレグなどである。
　第１エリア１０は、複合材Ａの幅Ｗの中心線が隣合う孔５と孔５との間をぬうように通るよう複合材Ａを屈曲させ蛇行配置してなる。複合材Ａは、複数の孔５の中心を通る線を軸として対象に蛇行させるとよい。複合材Ａは、複数の幅細のプリプレグが並べられて幅Ｗとなったものでもよい。
　幅Ｗは、複合材Ａを蛇行配置したときに隣合う孔５と孔５との間を複合材Ａで埋められる長さにするとよい。幅Ｗは、連続繊維の配向に直交する方向における複合材の長さである。複合材Ａの幅Ｗは、隣合う孔５の中心間距離Ｌにより定めることができる。例えば、図５のように１の傾斜部の繊維の向きが次の傾斜部の繊維の向きと直交する（θ＝９０°の）場合、幅Ｗは隣合う孔５の中心間距離Ｌの１／√２以下にするとよい。
　第１エリア１０は、傾斜部１２および平行部１３を含む。傾斜部１２および平行部１３は交互に配置されている。図５では、傾斜部１２から平行部１３となる際は、所定の角度で繊維配向が切り替わるよう複合材Ａが屈曲しているが、曲線を描くように徐々に繊維配向が変化するよう屈曲させてもよい。
　傾斜部１２は、隣合う孔５と孔５との間に位置し、複合材Ａ中の連続繊維が±３０°以上±６０°以下、好ましくは±４５°の方向を向いている。
　平行部１３は、孔５の短径（±９０°方向を向く直径）の延長線を含む位置に配置されている。平行部１３は、孔５の長径（孔５の０°方向の直径）に並行する領域にある第１エリア１０の外縁１３ａを含む位置にも配置されているとよい。平行部１３は、少なくとも一部が孔５に接している。
　第２エリア１１は、蛇行した第１エリアの屈曲した部分である谷部である。第２エリア１１は、繊維配向が０°方向となるよう該谷部に第２周縁領域用複合材を配置してなる。
　第４層４４も、第２層４２と同様の構成である。ただし、第４層４４の第１エリアは、第２層４２の第１エリアと山谷部の配置が逆となる蛇行形状であることが好ましい。具体的には、第２層４２における第１エリア１０が、複合材Ａが山部・谷部の順に屈曲を繰り返す蛇行形状であるとすると、第４層４４における第１エリアは、複合材Ａが谷部、山部の順に屈曲を繰り返す蛇行形状とする。そのような第１エリアを含む第２層４２および第４層４４を積層すると、第２層４２の第１エリアの山部と、第４層４４の第１エリアの谷部とが上下対になる。
　以上のような第１層４１から第５層４５を繰り返し、あるいはこれらの層の任意の組み合わせを適宜行う（図５参照）ことによって、他領域３ｂに比べて、周縁領域３ａを±３０°以上±６０°以下、好ましくは±４５°の配向比率を主体とすることができる。
　次に、上記構成の主翼１を用いた際の作用効果について説明する。
　飛行時、主翼１には、その先端が上向きに変位するように荷重が加わる。したがって、主翼１の下面外板３には、その延在方向（０°方向）に引張り荷重が加わる。０°方向の引張り荷重は、周縁領域３ａではなく、下面外板３の他領域３ｂが主として負担する。なぜなら、周縁領域３ａは、他領域３ｂに比べて±３０°以上±６０°以下、好ましくは±４５°配向の繊維が主体とされており０°方向の引張り荷重に対して剛性が低い領域とされているからである。したがって、周縁領域３ａには、他領域３ｂに比べて小さな引張り荷重しか加わらないので、周縁領域３ａの必要強度が下がる。つまり、増厚のための強化用積層体を孔周りに設ける必要がない。理解の容易のために、図１（ｂ）には、強化用積層体１０４が併せて示されている。このように、強化用積層体１０４が不要となるので、この分だけ軽量化することができる。
　周縁領域３ａは、±３０°以上±６０°以下、好ましくは±４５°を主体としているので、剪断方向の剛性すなわち捩り剛性については強化されている。したがって、周縁領域３ａは、軸力（引張り荷重）を負担せず、捩り荷重を負担するようになっている。
　周縁領域３ａは、長手方向に引き揃えられた連続繊維で強化された複合材Ａを蛇行させてなる第１エリア１０を含む。複合材Ａは連続繊維を含むため、屈曲させても繊維は連続した状態が維持される。繊維が連続していることで、短繊維を用いた場合と比較して、０°方向における強度を向上できる。連続繊維で強化した複合材を用いることで、第１エリア内の繊維配向が変化する境界において隙間が発生する懸念もない。これにより、従来よりも高精度の複合材構造体となる。
　孔５の間をぬうように複合材Ａを蛇行させることで、複数の孔周りでまとめて第１エリア１０を形成できるため、機械により複合材Ａを配置させることが可能であるし、効率的に製造できるようになる。
　傾斜部１２を孔５と孔５との間に配置することで、０°方向（一方向）の引張り剛性が低下して引張り方向（および／または圧縮方向）の伸びを許容する領域を実現することができる。傾斜部１２では、±３０°以上±６０°以下の方向、好ましくは±４５°方向に繊維が向いているので、剪断方向（一方向に対して直交する方向、すなわち±９０°方向）の強度が大きくなり、捩り剛性を高めることができる。
　孔５の±９０°方向を向く径の延長線上に平行部を設けることで、破断しやすい箇所の強度を低下させずに、孔５の周縁領域３ａに加わる応力集中を緩和することが可能となる。これにより、実体強度の強い複合材構造体となる。
　境界となる周縁領域３ａに平行部１３を配置することで、周縁領域３ａでの繊維の向きを、隣接する他領域３ｂでの繊維の向きと揃えることができる。それにより、周縁領域３ａと他領域３ｂとの境界における±９０°方向の強度低下を抑制できる。
　繊維シートを積層する際、１の層の第１エリアＡの山部と別の層の第１エリアＢの谷部とが対になるようにすることで、繊維シートの境界を上下方向でずらすことができる。それにより、±９０°方向の強度低下リスクを分散できる。
〔第２実施形態〕
　本実施形態に係る複合材構造体は、平行部を設ける範囲が異なる以外は第１実施形態と同様の構成である。
　図６に、本実施形態に係る第２層５２の要部平面図を示す。本実施形態において、平行部１３は、孔５の長径（０°方向の直径）と並行する領域にわたって配置されている。平行部の長さは、孔５の長径と同じである。
　孔５と並行する領域すべてを平行部とすることで、０°方向に対する孔周りの強度を向上できる。孔の±９０°方向において繊維の方向が切り替わる境界がなくなるため、±９０°方向に対する孔周りの強度を向上できる。
　なお、上記実施形態は主翼１の下面外板３への適用について説明したが、本発明はこれに限定されず、孔を有する複合材構造体であれば広く適用することができる。
　例えば、下面外板３とともにトルクボックスを構成する上面外板に、下面外板３と同様の構成を適用しても良い。本実施形態は、尾翼などにも適用することができる。
　上記実施形態は、窓用孔が形成された航空機胴体に適用することもできる。さらには、本発明の複合材構造体は、航空機に限定されず、例えば船舶や車両等にも適用することができる。
　上記実施形態では、炭素繊維強化プラスチック（ＣＦＲＰ）を主として用いることとしたが、本発明はこれに限定されず、例えばガラス繊維強化プラスチック（ＧＦＲＰ：Ｇｌａｓｓ　Ｆｉｂｅｒ　Ｒｅｉｎｆｏｒｃｅｄ　Ｐｌａｓｔｉｃ）やアラミド繊維強化プラスチック（ＡＦＲＰ：Ａｒａｍｉｄ　Ｆｉｂｅｒ　Ｒｅｉｎｆｏｒｃｅｄ　Ｐｌａｓｔｉｃ）を用いても良い。
１　主翼
３　下面外板（複合材構造体）
３ａ　周縁領域
３ｂ　他領域
５　アクセスホール（孔）
１０　第１エリア
１１　第２エリア
１２　傾斜部
１３　平行部
１３ａ　（平行部の）外縁
２０　フロントスパー
２２　リアスパー
２４　上面外板
２６　ストリンガ
２８　リブ
３０　ファスナ
４１　第１層
４２　第２層
４３　第３層
４４　第４層
４５　第５層
１０４　強化用積層体
 

Claims (18)

  1. 　一方向に延在するとともに、複数の孔が前記一方向に間隔を空けて並べて形成された繊維強化プラスチック製の複合材とされ、前記一方向に引張り荷重および／または圧縮荷重が負荷される複合材構造体において、
    　前記孔の周縁領域は、長手方向に引き揃えられた連続繊維で強化された複合材が前記複合材の幅Ｗの中心線が隣合う孔と孔との間をぬうように屈曲し前記一方向に向かって蛇行してなる第１エリアを含み、
    　前記周縁領域の前記一方向における引張り剛性および／または圧縮剛性が、該周縁領域を取り囲む他領域の前記一方向における引張り剛性および／または圧縮剛性よりも小さい複合材構造体。
  2. 　前記第１エリアは、前記一方向を０°とした場合に前記連続繊維が±３０°以上±６０°以下の方向を向く傾斜部を含み、
    　前記傾斜部が、隣合う孔と孔との間に配置されている請求項１に記載の複合材構造体。
  3. 　前記第１エリアは、前記一方向を０°とした場合に前記連続繊維が±４５°方向を向く傾斜部を含み、
    　前記傾斜部が、隣合う孔と孔との間に配置されている請求項１に記載の複合材構造体。
  4. 　前記第１エリアは、前記連続繊維が０°方向を向くよう配置された平行部を含み、
    　前記平行部は、前記第１エリアの少なくとも前記孔の±９０°方向を向く直径の延長線を含む位置に配置され、前記孔と接している請求項１から請求項３のいずれかに記載の複合材構造体。
  5. 　前記平行部は、前記孔の０°方向の直径に並行する領域にある前記第１エリアの外縁を含む位置に配置されている請求項４に記載の複合材構造体。
  6. 　１の前記傾斜部の連続繊維の向きが次の傾斜部の連続繊維の向きと直交する場合、前記幅Ｗは隣合う孔の中心間距離Ｌの１／√２以下と定義される請求項２から請求項５のいずれかに記載の複合材構造体。
  7. 　前記平行部は、前記孔の０°方向の直径と並行する領域にある前記第１エリアである請求項４に記載の複合材構造体。
  8. 　前記長手方向に引き揃えられた連続繊維で強化された複合材が山部、谷部の順に屈曲を繰り返す第１エリアＡを含む層と、
    　前記長手方向に引き揃えられた連続繊維で強化された複合材が谷部、山部の順に屈曲を繰り返す第１エリアＢを含む層と、
    が、前記第１エリアＡの山部と前記第１エリアＢの谷部とが上下対になるよう積層されている請求項１から請求項７のいずれかに記載の複合材構造体。
  9. 　前記孔は、航空機の翼の下面外板に形成されたアクセスホールである請求項１から請求項８のいずれかに記載の複合材構造体。
  10. 　前記孔は、航空機の胴体の外板に形成された窓用孔である請求項１から請求項８のいずれかに記載の複合材構造体。
  11. 　請求項９に記載の複合材構造体を備えている航空機翼。
  12. 　請求項１０に記載の複合材構造体を備えている航空機胴体。
  13. 　一方向に延在するとともに、複数の孔が該一方向に間隔を空けて並べて形成された繊維強化プラスチック製の複合材とされ、前記一方向に引張り荷重および／または圧縮荷重が負荷される複合材構造体の製造方法において、
    　長手方向に引き揃えられた連続繊維で強化された複合材を該複合材の幅Ｗの中心線が隣合う孔と孔との間をぬうように屈曲させ前記一方向に向けて蛇行配置し、
    　前記孔の周縁領域の前記一方向における引張り剛性および／または圧縮剛性を、該周縁領域を取り囲む他領域の前記一方向における引張り剛性および／または圧縮剛性よりも小さくする複合材構造体の製造方法。
  14. 　前記一方向を０°とした場合に、隣合う孔と孔との間で、前記連続繊維が±３０°以上±６０°以下の方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置する請求項１３に記載の複合材構造体の製造方法。
  15. 　前記一方向を０°とした場合に、隣合う孔と孔との間で、前記連続繊維が±４５°方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置する請求項１３に記載の複合材構造体の製造方法。
  16. 　前記孔の±９０°方向を向く直径の延長線を含む位置に、前記連続繊維が０°方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置する請求項１３から請求項１５のいずれかに記載の複合材構造体の製造方法。
  17. 　前記孔の０°方向の直径に並行する領域に、外縁において前記連続繊維が０°方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置する請求項１６に記載の複合材構造体の製造方法。
  18. 　前記孔の０°方向の直径に並行する領域の前記連続繊維が０°方向を向くよう前記長手方向に引き揃えられた連続繊維で強化された複合材を配置する請求項１６に記載の複合材構造体の製造方法。
PCT/JP2015/057786 2014-03-28 2015-03-17 複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法 Ceased WO2015146690A1 (ja)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP15770101.2A EP3103623B1 (en) 2014-03-28 2015-03-17 Composite material structure, aircraft wing and aircraft fuselage provided with same, and method for manufacturing composite material structure
US15/117,895 US10137664B2 (en) 2014-03-28 2015-03-17 Composite material structure, aircraft wing and aircraft fuselage provided with same, and method for manufacturing composite material structure
BR112016020521-9A BR112016020521A2 (pt) 2014-03-28 2015-03-17 Estrutura de material compósito, asa de avião e fuselagem de avião dotadas da mesma e método para fabricação de estrutura de material compósito
RU2016135195A RU2645500C1 (ru) 2014-03-28 2015-03-17 Конструкция из композиционного материала и содержащие ее крыло летательного аппарата и фюзеляж летательного аппарата, способ изготовления конструкции из композиционного материала
CA2940463A CA2940463C (en) 2014-03-28 2015-03-17 Composite material structure, aircraft wing and aircraft fuselage provided with same, and method for manufacturing composite material structure
CN201580009194.4A CN106029346B (zh) 2014-03-28 2015-03-17 复合材料构造体、具有该复合材料构造体的航空机机翼及航空机机身、以及复合材料构造体的制造方法

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2014067920A JP6309324B2 (ja) 2014-03-28 2014-03-28 複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法
JP2014-067920 2014-03-28

Publications (1)

Publication Number Publication Date
WO2015146690A1 true WO2015146690A1 (ja) 2015-10-01

Family

ID=54195213

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2015/057786 Ceased WO2015146690A1 (ja) 2014-03-28 2015-03-17 複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法

Country Status (8)

Country Link
US (1) US10137664B2 (ja)
EP (1) EP3103623B1 (ja)
JP (1) JP6309324B2 (ja)
CN (1) CN106029346B (ja)
BR (1) BR112016020521A2 (ja)
CA (1) CA2940463C (ja)
RU (1) RU2645500C1 (ja)
WO (1) WO2015146690A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016100191A1 (de) * 2016-01-06 2017-07-06 Wobben Properties Gmbh Faserverbundbauteil und Strukturbauteil sowie Herstellungsverfahren

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10843788B2 (en) * 2017-06-29 2020-11-24 Textron Innovations Inc. Damping structures for tiltrotor aircraft wings
FR3068912B1 (fr) * 2017-07-11 2019-08-23 Faurecia Automotive Industrie Procede de fabrication d'une piece d'equipement de vehicule automobile et piece d'equipement associee
US11400685B2 (en) * 2017-12-15 2022-08-02 Unm Rainforest Innovations Gradually recruited fiber reinforced polymer (FRP) composite
JP7112950B2 (ja) * 2018-12-05 2022-08-04 三菱重工業株式会社 複合材の設計方法および複合材
JP7198701B2 (ja) * 2019-03-27 2023-01-04 日産自動車株式会社 繊維強化プラスチック複合材、繊維強化プラスチックプリフォーム、及び繊維強化プラスチック中間基材
JP7390144B2 (ja) * 2019-09-24 2023-12-01 三菱重工業株式会社 複合材の継手部材及び継手構造体
GB2623100A (en) * 2022-10-06 2024-04-10 Bae Systems Plc Aircraft wings
IT202300009465A1 (it) * 2023-05-11 2024-11-11 Leonardo Spa Metodo di realizzazione di una struttura scatolata in materiale composito per aeromobili
GB2638210A (en) * 2024-02-15 2025-08-20 Airbus Operations Ltd Composite structure

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH01263030A (ja) * 1988-04-15 1989-10-19 Agency Of Ind Science & Technol 複合材のファスナ継手
JP2010524769A (ja) * 2007-04-24 2010-07-22 エアバス・オペレーションズ・ゲーエムベーハー 部品を航空機胴体に取り付けるための取付配置構成品、航空機、および取付配置構成品を構成するための方法
WO2012105691A1 (ja) * 2011-02-04 2012-08-09 三菱重工業株式会社 複合材構造体、これを備えた航空機主翼および航空機胴体

Family Cites Families (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5989842A (ja) * 1982-11-12 1984-05-24 Nhk Spring Co Ltd Ｆｒｐ製ばね板
DE3718676A1 (de) 1987-06-04 1988-12-22 Mtu Muenchen Gmbh Formkoerper und verfahren zu seiner herstellung
NL8702487A (nl) * 1987-10-19 1989-05-16 Dsm Resins Bv Werkwijze voor de vervaardiging van persprodukten.
JPH0462038A (ja) 1990-06-25 1992-02-27 Ryobi Ltd 積層管およびその製造方法
JPH0489326A (ja) 1990-07-31 1992-03-23 Matsushita Electric Ind Co Ltd 光学ガラス成形体とその製造方法とその製造装置
JPH04334696A (ja) 1991-05-09 1992-11-20 Mitsubishi Heavy Ind Ltd 複合材製補強パネル
MX9206033A (es) * 1991-10-22 1993-05-01 Univ Brigham Young Amortiguamiento mejorado en estructuras compuestas a traves de acoplamiento por esfuerzo.
DE4234038C2 (de) * 1992-10-09 1997-07-03 Daimler Benz Aerospace Airbus Schalenbauteil aus Faserverbundwerkstoff
FR2699499B1 (fr) * 1992-12-23 1995-03-10 Eurocopter France Pale en composite thermoplastique, notamment pour rotor arrière caréné d'hélicoptère, et son procédé de fabrication avec étape d'injection.
US5771680A (en) * 1995-12-21 1998-06-30 General Electric Company Stiffened composite structures and method of making thereof
US20020028332A1 (en) * 1996-10-09 2002-03-07 Pratt William F. Wavy composite tubular structures
US7906191B2 (en) * 1997-11-14 2011-03-15 William F. Pratt Wavy composite structures
DE29813901U1 (de) * 1998-07-23 1999-02-04 Inst Konstruktion Und Verbundb Verbundbauteil
RU2185964C1 (ru) * 2001-01-19 2002-07-27 Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Слоистый композиционный материал и изделие, выполненное из него
GB0117804D0 (en) * 2001-07-21 2001-09-12 Bae Systems Plc Aircraft structural components
DE10153875A1 (de) * 2001-11-02 2003-05-15 Bpw Bergische Achsen Kg Bauteil in langgestreckter Bauweise aus einem Faser-Kunststoff-Verbund
US9302427B2 (en) 2005-03-31 2016-04-05 The Boeing Company Aeropspace structure including composite beam chord clamped between reinforcement plates
DE102008008386A1 (de) * 2008-02-09 2009-08-13 Airbus Deutschland Gmbh Verfahren zur Herstellung eines FVW-Bauteils
JP5167953B2 (ja) 2008-05-27 2013-03-21 東レ株式会社 積層基材、繊維強化プラスチック、およびそれらの製造方法
CA2768957C (en) * 2009-10-08 2014-07-29 Mitsubishi Heavy Industries, Ltd. Composite-material structure and aircraft main wing and aircraft fuselage provided with the same
JP2011084008A (ja) 2009-10-16 2011-04-28 Toyota Motor Corp Ｆｒｐ積層体の成形方法
JP5808111B2 (ja) 2011-02-04 2015-11-10 三菱重工業株式会社 航空機用複合材構造体、これを備えた航空機主翼および航空機胴体
US8616500B2 (en) 2011-03-04 2013-12-31 The Boeing Company Diamond shaped window for composite and/or metallic airframe
JP6004669B2 (ja) * 2012-02-29 2016-10-12 三菱重工業株式会社 複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法
US9289949B2 (en) * 2012-06-08 2016-03-22 The Boeing Company Optimized cross-ply orientation in composite laminates
DE102012221404A1 (de) * 2012-11-22 2014-06-05 Bayerische Motoren Werke Aktiengesellschaft Aus einem Faserverbund bestehende Komponente, insbesondere für das Fahrwerk eines Kraftfahrzeuges

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH01263030A (ja) * 1988-04-15 1989-10-19 Agency Of Ind Science & Technol 複合材のファスナ継手
JP2010524769A (ja) * 2007-04-24 2010-07-22 エアバス・オペレーションズ・ゲーエムベーハー 部品を航空機胴体に取り付けるための取付配置構成品、航空機、および取付配置構成品を構成するための方法
WO2012105691A1 (ja) * 2011-02-04 2012-08-09 三菱重工業株式会社 複合材構造体、これを備えた航空機主翼および航空機胴体

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP3103623A4 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016100191A1 (de) * 2016-01-06 2017-07-06 Wobben Properties Gmbh Faserverbundbauteil und Strukturbauteil sowie Herstellungsverfahren
US11285688B2 (en) 2016-01-06 2022-03-29 Wobben Properties Gmbh Fiber composite component, structural component, and production method

Also Published As

Publication number Publication date
CN106029346B (zh) 2018-07-24
BR112016020521A2 (pt) 2021-08-24
CN106029346A (zh) 2016-10-12
EP3103623A1 (en) 2016-12-14
JP6309324B2 (ja) 2018-04-11
EP3103623A4 (en) 2017-07-26
CA2940463A1 (en) 2015-10-01
RU2645500C1 (ru) 2018-02-21
US10137664B2 (en) 2018-11-27
EP3103623B1 (en) 2021-09-08
CA2940463C (en) 2018-07-24
JP2015189082A (ja) 2015-11-02
US20170008250A1 (en) 2017-01-12

Similar Documents

Publication Publication Date Title
JP6309324B2 (ja) 複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法
JP6004669B2 (ja) 複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法
JP5308533B2 (ja) 複合材構造体、これを備えた航空機主翼および航空機胴体
JP5808111B2 (ja) 航空機用複合材構造体、これを備えた航空機主翼および航空機胴体
JP5654055B2 (ja) 複合材構造体、これを備えた航空機主翼および航空機胴体
JP5808112B2 (ja) 複合材構造体およびこれを備えた航空機主翼
US10000273B2 (en) Passive load alleviation for a fiber reinforced wing box of an aircraft with a stiffened shell structure
WO2012131137A2 (es) Fuselaje de aeronave con cuadernas altamente resistentes
US20180281923A1 (en) Skin panel of composite material having an internal grid
US10745098B2 (en) Energy-absorbing under-floor airframe
JP2022150610A (ja) 異方性複合材積層構造の設計方法

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 15770101

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 15117895

Country of ref document: US

ENP Entry into the national phase

Ref document number: 2940463

Country of ref document: CA

REEP Request for entry into the european phase

Ref document number: 2015770101

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 2015770101

Country of ref document: EP

NENP Non-entry into the national phase

Ref country code: DE

ENP Entry into the national phase

Ref document number: 2016135195

Country of ref document: RU

Kind code of ref document: A

REG Reference to national code

Ref country code: BR

Ref legal event code: B01A

Ref document number: 112016020521

Country of ref document: BR

ENP Entry into the national phase

Ref document number: 112016020521

Country of ref document: BR

Kind code of ref document: A2

Effective date: 20160905

REG Reference to national code

Ref country code: BR

Ref legal event code: B01E

Ref document number: 112016020521

Country of ref document: BR

Kind code of ref document: A2

Free format text: APRESENTE A TRADUCAO SIMPLES DA FOLHA DE ROSTO DA CERTIDAO DE DEPOSITO DA PRIORIDADE REIVINDICADA; OU DECLARACAO DE QUE OS DADOS DO PEDIDO INTERNACIONAL ESTAO FIELMENTE CONTIDOS NA PRIORIDADE REIVINDICADA, CONTENDO TODOS OS DADOS IDENTIFICADORES (NUMERO DA PRIORIDADE, DATA, DEPOSITANTE E INVENTORES), CONFORME O PARAGRAFO UNICO DO ART. 25 DA RESOLUCAO 77/2013. CABE SALIENTAR NAO FOI POSSIVEL INDIVIDUALIZAR OS TITULARES DA CITADA PRIORIDADE, INFORMACAO NECESSARIA PARA O EXAME DA CESSAO DO DOCUMENTO DE PRIORIDADE, SE FOR O CASO.

ENP Entry into the national phase

Ref document number: 112016020521

Country of ref document: BR

Kind code of ref document: A2

Effective date: 20160905