CN103068565A - 具有复合材料-金属接头的复合材料结构以及制造其的方法 - Google Patents

具有复合材料-金属接头的复合材料结构以及制造其的方法 Download PDF

Info

Publication number
CN103068565A
CN103068565A CN2011800395871A CN201180039587A CN103068565A CN 103068565 A CN103068565 A CN 103068565A CN 2011800395871 A CN2011800395871 A CN 2011800395871A CN 201180039587 A CN201180039587 A CN 201180039587A CN 103068565 A CN103068565 A CN 103068565A
Authority
CN
China
Prior art keywords
metal
composite
sheet metal
fiber
flaggy
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.)
Granted
Application number
CN2011800395871A
Other languages
English (en)
Other versions
CN103068565B (zh
Inventor
K·H·格瑞斯
G·E·乔格森
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of CN103068565A publication Critical patent/CN103068565A/zh
Application granted granted Critical
Publication of CN103068565B publication Critical patent/CN103068565B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • B32B7/14—Interconnection of layers using interposed adhesives or interposed materials with bonding properties applied in spaced arrangements, e.g. in stripes
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
    • B29C66/124—Tongue and groove joints
    • B29C66/1248—Interpenetrating groove joints
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/723—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being multi-layered
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/723—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being multi-layered
    • B29C66/7232—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being multi-layered comprising a non-plastics layer
    • B29C66/72321—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being multi-layered comprising a non-plastics layer consisting of metals or their alloys
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
    • 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
    • B29C70/304—In-plane lamination by juxtaposing or interleaving of plies, e.g. scarf joining
    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to 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
    • 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
    • B32B3/02—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 features of form at particular places, e.g. in edge regions
    • B32B3/06—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 features of form at particular places, e.g. in edge regions for securing layers together; for attaching the product to another member, e.g. to a support, or to another product, e.g. groove/tongue, interlocking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/14—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a face layer formed of separate pieces of material which are juxtaposed side-by-side
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/18—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by an internal layer formed of separate pieces of material which are juxtaposed side-by-side
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/02—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by a sequence of laminating steps, e.g. by adding new layers at consecutive laminating stations
    • 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
    • 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
    • B64C1/061—Frames
    • 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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/71—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the composition of the plastics material of the parts to be joined
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72143—Fibres of discontinuous lengths
    • 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
    • B29K2703/00—Use of resin-bonded materials for preformed parts, e.g. inserts
    • B29K2703/04—Inorganic materials
    • B29K2703/06—Metal powders, metal carbides or the like
    • 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
    • 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
    • B29L2031/3002—Superstructures characterized by combining metal and plastics, i.e. hybrid parts
    • 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
    • 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
    • B32B2250/05—5 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
    • 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
    • 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
    • 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
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/07—Parts immersed or impregnated in a matrix
    • B32B2305/076—Prepregs
    • 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
    • B32B2305/77—Uncured, e.g. green
    • 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
    • B32B2307/714—Inert, i.e. inert to chemical degradation, corrosion
    • 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
    • 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
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • 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
    • Y10T428/19—Sheets or webs edge spliced or joined
    • 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
    • Y10T428/19—Sheets or webs edge spliced or joined
    • Y10T428/192—Sheets or webs coplanar
    • 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
    • Y10T428/19—Sheets or webs edge spliced or joined
    • Y10T428/192—Sheets or webs coplanar
    • Y10T428/195—Beveled, stepped, or skived in thickness
    • 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.]
    • Y10T428/24752—Laterally noncoextensive components

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)

Abstract

复合材料结构包括层压的纤维增强树脂板层和金属片的堆叠组。树脂板层与金属片的边缘交叉，以形成将树脂板层与金属片连接的复合材料-金属接头。

Description

具有复合材料-金属接头的复合材料结构以及制造其的方法
技术领域
一般而言，本公开内容涉及复合材料结构，具体而言，涉及纤维增强树脂层压板层，并且更具体地涉及具有复合材料-金属(composite-to-metal)接头的混合复合材料。
背景技术
粘合技术通常用于组装复合材料结构。在复合材料结构还需要紧固件的应用中，可能需要增加围绕紧固件的结构的局部厚度或规格(gauge)以便承受传输经过紧固件接头的负荷。随着所述结构的局部厚度增加，紧固件可能需要延长，从而对结构增加重量。此外，该结构的局部厚度增加可增加通过紧固件接头的负荷路径的偏心率，这可能将不期望的弯曲负荷置于紧固件上。
上述问题的一种解决方案由将金属配件附接到紧固件区域中的复合材料结构组成。这些金属配件可以由钛或可基本上不与接触其的碳纤维增强复合材料发生化学反应的类似金属形成。然而，钛配件可能相对较贵，特别是当必须使其形成复杂形状时。
因此，需要复合树脂-金属接头，其可用于将基本上全金属配件与基本上全复合树脂结构连接，其相对便宜且易于制造，并且其可以承受紧固件连接点周围传输的负荷。还需要复合树脂-金属接头，其基本上避免全金属配件和全复合树脂结构之间的化学反应。
发明内容
公开的实施方式提供了混合型复合材料结构，其包括可用于将基本上全金属配件与基本上全复合树脂结构连接的纤维增强树脂复合材料-金属接头。该接头提供复合材料与金属结构之间的过渡，其适合用在更高性能的应用中，比如航天运载工具。这种从基本上全复合材料到基本上全金属材料的过渡可以降低或消除腐蚀的可能性和/或由于偏心率造成的问题。在复合材料结构的铺叠(lay-up)期间，金属片被一些复合材料板层替换，并且从复合材料板层到金属片的过渡出现在交错的位置，以便提供从复合材料部分到金属部分的足够负荷转移。交错的过渡造成复合材料板层和金属片之间的交叉(interleaving)并且产生多个接合缝，其可以减少接头中裂缝或脱胶(disbond)的发生和/或蔓延。金属片之间放置的粘合剂将金属片粘接和组合为接近实心的金属配件。
根据一个公开的实施方式，提供了复合材料结构，其包括一叠层压的纤维增强树脂板层和一叠金属片。金属片具有边缘，其与纤维增强树脂板层的边缘交叉，以形成连接纤维增强树脂板层与金属片的复合材料-金属接头。
根据另一个实施方式，提供了混合树脂-金属结构，其包括复合树脂部分、金属部分以及树脂部分和金属部分之间的过渡段。树脂部分包括纤维增强树脂的层压板层，并且金属部分包括粘合的金属片。过渡段包括在所述层压板层和金属片之间交错的重叠。
根据另一个实施方式，提供了混合复合材料金属部件。该部件包括纤维增强复合材料的铺叠，其终止于界面位置。在界面位置处，与复合材料相同厚度的金属板层延续至部件的金属边缘，并且重复铺叠，其中复合材料-金属界面从已有的界面位置朝向部件的边缘交错。结构粘合剂层置于金属板层之间，其中下一个金属-复合材料界面与部件边缘错开，以产生嵌套拼接，并且继续交错的界面堆叠——其产生嵌套的接头片(tab)——直至部件的全部厚度，其中复合材料板层都没有完全延伸至部件的边缘。
根据又另一个实施方式，提供了制造复合材料结构的方法。该方法包括形成具有复合材料部分和金属部分的多板层复合材料铺叠，并且在复合材料部分和金属部分之间形成复合材料-金属接头。该方法进一步包括将铺叠压实和固化。
根据进一步的实施方式，提供了生产混合金属部件的方法。该方法包括铺设至少一个纤维增强复合材料板层，其终止于界面位置；和铺设相邻的金属板层，其中金属板层与相邻纤维增强复合材料板层的厚度基本相同。重复铺设复合材料板层和相邻金属板层的步骤以形成复合材料-金属界面，其从已有界面位置朝向所述部件的边缘交错。该方法进一步包括在金属板层之间铺设结构粘合剂层，并且重复复合材料和金属板层铺叠，其中下一个金属-复合材料界面与部件边缘错开，以产生嵌套拼接。
9.混合复合树脂-金属结构，包括：
复合树脂部分，其包括纤维增强树脂的层压板层；
金属部分，其包括粘合的金属片；以及
过渡段，其在所述复合树脂部分和所述金属部分之间，所述过渡段包括在所述层压板层和所述金属片之间交错的重叠。
10.权利要求9所述的混合复合树脂-金属结构，其中：
所述层压板层和所述金属片分层排列，并且
每个层包括基本上边对边对接的一个所述金属片和多个所述纤维增强树脂板层。
11.权利要求10所述的混合复合树脂-金属结构，其中每个层中所述板层的厚度基本上等于所述层中所述金属片的厚度。
20.生产混合金属部件的方法，包括：
铺设至少一个纤维增强复合材料板层，其终止于界面位置；
铺设相邻的金属板层，其中所述金属板层与所述相邻的纤维增强复合材料板层的厚度相同；
重复所述铺设复合材料板层和相邻的金属板层的步骤以形成复合材料-金属界面，其从已有的界面位置朝向所述部件的边缘交错；
在所述金属板层之间铺设结构粘合剂层；和
重复所述复合材料和金属板层铺叠，其中下一个金属-复合材料界面与所述部件边缘错开，以产生嵌套拼接。
21.权利要求20所述的方法，进一步包括：
继续所述复合材料和金属板层的交错界面堆叠以产生嵌套接头片，直至所述部件的全部厚度，其中复合材料板层都没有完全延伸至所述部件的边缘。
22.权利要求21所述的方法，进一步包括：
真空袋加工所述部件以去除所述铺叠中的空气空隙；并且将铺叠的部件固化。
23.混合复合树脂-金属航空器结构，包括：
多个层压的层，其形成纤维增强的全复合材料部分、全金属部分、以及将所述复合材料部分与所述金属部分连接的混合复合材料-金属指形接头，
所述层中的每个都包括多个复合树脂板层和钛金属片，其中所述板层和所述金属片彼此边对边对接排列，在所述层中形成复合材料-金属过渡点，并且其中所述层中的过渡点相对于彼此交错以形成所述指形接头；和
在所述金属片之间用于将所述金属片组合的粘合剂层，并且
其中每个所述层中的板层的厚度基本上等于一个片和粘合剂层的组合厚度。
24.制造混合复合树脂-金属航空器结构的方法，包括：
形成铺叠，其包括纤维增强的全复合材料部分、全金属部分以及将所述复合材料部分与所述金属部分连接的混合复合材料-金属指形接头；形成所述铺叠，包括铺叠多个层，其中每个层通过将多个复合树脂板层与钛金属片边对边对接而形成，在所述层中形成复合材料-金属过渡点；
在所述金属片之间放置粘合剂层n以将所述金属部分组合；
通过将所述层中的过渡点相对于彼此交错，在所述复合材料部分和所述金属部分之间形成接头；
将所述铺叠压实；并且
将所述铺叠固化。
12.权利要求9所述的混合复合树脂-金属结构，其中所述交错的重叠在所述复合树脂部分和所述金属部分之间形成复合材料-金属指形接头。
13.权利要求9所述的混合复合树脂-金属结构，进一步包括在每个所述金属片之间的粘合剂层，用于将所述片粘合在一起并且将所述金属部分组合。
14.权利要求9所述的混合复合树脂-金属结构，其中每个所述金属片是钛合金。
15.混合复合材料-金属部件，包括：
纤维增强复合材料的铺叠，其终止于界面位置，其中与所述复合材料相同厚度的金属板层延续至部件的金属边缘，并且重复铺叠，其中复合材料-金属界面从已有的界面位置朝向部件边缘交错，并且包括在所述金属板层之间的结构粘合剂层，其中下一个所述金属-复合材料界面与所述部件边缘错开，以产生嵌套拼接，并且继续所述交错的界面堆叠——其产生嵌套的接头片——直至部件的全部厚度，其中所述复合材料板层都没有完全延伸至所述部件的边缘。
附图简述
图1是具有复合材料-金属接头的复合材料结构的截面图图示。
图2是包括复合材料-金属接头的复合材料结构的透视图图示。
图3是图2中指定为图3的区域的透视图图示。
图4是接头的截面图图示，更好地显示复合材料板层和金属片之间的交叉。
图5是图4中所示接头的两个单独层的截面图图示，也显示施加薄膜粘合剂在金属片上。
图6是通过图5中所示的两个层形成的接头的一部分的放大截面图图示。
图7是用于制造具有图2-4中所示的复合材料接头的复合材料结构的方法的宽泛流程图图示。
图8是显示图7中所示方法的额外细节的流程图图示。
图9是用于制造具有图2-4中所示的复合材料接头的复合材料结构的另一方法的流程图。
图10是航空器生产和维护方法的流程图图示。
图11是航空器的框图图示。
详述
首先参考图1，混合复合材料结构20包括复合树脂部分22，其通过包括复合材料-金属接头26的过渡段25连接到金属部分24。在图示的实例中，复合材料结构20是基本上平的复合材料片，然而，取决于应用，结构20可具有一个或多个弯曲、弧面(contour)或其它几何特征。例如，复合材料结构20可以构成航空器内和/或外成型的蒙皮(未显示)，其借助搭接接头(lap joint)30和经过蒙皮20进入框架28的紧固件32固定到航空器的框架28部分。
框架28可包括复合材料、金属或其它刚性材料，并且结构20的金属部分24可以用作刚性金属配件24，其适于在框架28和复合材料部分20之间转移一定范围的负荷和多种类型的加载。如下面将更详细讨论的，金属部分24可以包括任意各种金属，比如但不限于钛，其基本上不与复合材料部分20和结构28发生反应并可相容。在一个实际的实施方式中，例如但不限于，复合树脂部分22可以包括碳纤维增强环氧树脂，金属部分24可以包括钛合金，并且框架28可以包括铝合金或复合材料。过渡段25和接头26强度足以承载复合树脂部分22和金属部分24之间通常范围和类型的负荷，包括但不限于张力、弯曲、扭曲和剪切负荷。虽然图示的过渡段25和接头26在全复合树脂部分22和全金属部分24之间形成，但也可能使用其连接两种不同的复合材料结构(未显示)或两种不同的金属结构(未显示)。
参考图1-4，复合材料板层35的铺叠终止于下文称作过渡点39的界面位置39，其中基本上与复合材料板层35相同厚度的金属片或板层37延续至金属部分24的金属边缘24a，并且重复铺叠，其中复合材料-金属界面39从已有的界面位置39朝向金属边缘24a交错，并且包括在金属板层37之间的结构金属粘合剂层45(参见图5和6)，其中下一个金属-复合材料界面39与部件边缘24a错开，以产生嵌套拼接27。继续该交错的界面堆叠——其产生嵌套的接头片29(参见图3)——直至混合复合材料结构20的全部厚度，其中复合材料板层35都没有完全延伸至全金属部分24的金属边缘24a。
现在还参考图2-4，结构20的复合材料部分22包括纤维增强树脂板层35的层压堆叠34，并且结构20的金属部分24包括金属片或板层37的堆叠36，其粘合在一起以形成基本上组合的金属结构。如图5和6中所示，复合材料板层35和金属片37以层38排列。每个层38包括与一个金属片37基本上边对边对接的一个或多个复合材料板层35。因此，每个层38在点39处从复合材料即复合树脂板层35过渡到金属即金属片37。
过渡点39根据预定的铺叠计划相对于彼此交错，使得板层35和金属片37在过渡段25(图1)中彼此重叠。过渡点39的交错产生多个接合缝，其可以减少接头26中裂缝或脱胶的发生和/或蔓延。过渡点39的交错还产生复合材料板层35和金属片37在接头26内交叉的形式，其在全复合材料部分22和全金属部分24之间形成嵌套拼接27。该嵌套拼接27也可以称为指形粘接26、指形接头26或多梯级搭接接头26。相邻的过渡点39在结构20的面内方向上彼此间隔开，以便获得粘合的接头26，其展现最佳的性能特点，包括强度和对脱胶以及不一致(inconsistency)比如裂缝蔓延的抗性。在图示的实例中，形成接头26的嵌套拼接27为双指形接头26的形式，其中过渡点39从最大重叠的大致中心点55在相对方向上交错。然而，其它接头构型也是可能的，其包括但不限于单指形接头，其中多个过渡点39在单个方向上交错。
复合材料板层35可以包括纤维增强树脂，比如但不限于，碳纤维环氧树脂，其形式可以是单向的预浸带或织物。其它的纤维增强是可能的，包括玻璃纤维，并且使用非预浸材料可以是可能的。复合材料板层35可以具有预定的纤维取向，并且根据预定的板层计划铺叠，以满足期望的性能规格。如之前所述，粘合的片37可以包括金属比如钛，其适用于预期的应用。在图示的实例中，金属片37的堆叠36具有总厚度t1，其一般基本上等于板层35的层压的堆叠34的厚度t2。然而，在图示的实例中，在堆叠37的相对侧上，t2略微大于t1数个外包板层43的厚度。
图5和6图示说明图2-4所示的接头26的两个邻接层38的细节。在该实例中，每个层38包括具有集体总厚度T1的四个板层35。相邻层38的单个金属片37借助于结构粘合剂层45粘合在一起，结构粘合剂层45可以包括商业薄膜粘合剂或者其它形式的合适的粘合剂，其在铺叠过程期间置于金属片36之间。
图5中表示为T2的每个金属片37和一个粘合剂层45的组合厚度基本等于层38中复合材料板层35的厚度T1。虽然图中没有显示，粘合剂的薄膜可置于板层35之间以增加层间粘合强度。在一个实际的实施方式中，可使用钛合金金属片37，其中每个具有大约0.0025英寸的厚度，薄膜粘合剂45可以是大约0.005英寸厚，并且可以在每个具有大约0.30英寸的集体总厚度的层38中使用四个复合材料碳纤维环氧树脂板层35。取决于应用，使用除钛以外的金属是可能的。相邻过渡点39之间的距离、并因此层38之间重叠的长度、以及复合材料板层35的厚度和数量与金属片37的厚度将取决于具体应用的要求，包括待传输经过接头26的负荷的类型和大小，以及可能的其它性能规格。
分别在复合材料部分22和金属部分24(图1)的两种不同材料之间的接头26的不同层38使得结构20非常适合于使用嵌入式或悬挂式(mounted)传感器(未显示)进行粘合质量的非破坏性评估。超声结构波(未显示)可以在金属部分24的边缘、复合材料部分22或过渡段25中引入结构20。这些超声波行进经过相当于由金属37片和复合材料板层35与金属片37之间的界面(未显示)形成的波导。出于分析接头26中接合缝状态的目的，放置在结构20中的基于MEMS(微电子机械)的传感器、薄压电传感器(未显示)或其它变换器可用于接收超声结构波。
现参考图7，如65所示，制造复合材料结构20的一种方法包括形成多层复合材料铺叠。形成铺叠包括在步骤67铺叠复合树脂部分22，并且在69铺叠金属部分24。形成铺叠的步骤65进一步包括在铺叠的复合树脂部分和金属部分之间形成复合材料-金属接头，在71显示。
图8图示说明图7中所示方法的额外细节。在步骤40开始，将单个金属片37修整成期望的尺寸和/或形状。然后在42，通过适当方法制备金属片37的表面，该方法可包括用溶剂清洁片37、将其干燥等等，而后在44，通过以由预先定义的板层计划(未显示)确定的顺序铺叠金属片36和复合材料板层35而组装铺叠，该计划包括在每个层38中的板层35和金属片36之间的过渡点39的预定交错。
在铺叠过程期间，金属片37如同板层按顺序排列成铺叠，更如同在传统铺叠过程中复合材料板层按顺序排列成铺叠。如步骤46所示，可在金属片37之间引入粘合剂，以便将其粘合在一起成为组合的金属结构。类似地，虽然没有在图8中显示，但可在单独的复合材料板层35之间引入粘合胶，以便增加这些板层35之间的粘合强度。接下来，在48，可以使用任意数种已知的压实技术比如真空装袋将铺叠压实，而后在步骤50使用高压釜或非高压釜固化方法将铺叠固化。在步骤52，如果需要，可以修整和/或检查固化的复合材料结构20。
图9图示说明了制造混合复合材料部件20的方法的又另一个实施方式。该方法开始于步骤73，其中将至少一个终止于界面位置39的复合材料板层35铺设在合适的铺叠工具(未显示)上。在75，铺叠相邻的金属板层37，其基本与相邻的复合材料板层35的厚度相同。如77所示，重复铺叠过程，其中复合材料-金属界面39从已有的界面位置39朝向部件20的金属边缘24a交错。在79，在金属板层37之间铺设结构粘合剂层45。继续地重复步骤73-79，以产生嵌套拼接27和形成嵌套接头片29的交错界面堆叠，直至混合部件20的全部厚度，其中复合材料板层35都没有完全延伸至部件20的金属边缘24a。虽然图9中没有显示，但完成的铺叠进行真空装袋加工以去除空隙，并且随后使用任何合适的固化方法进行固化。
本公开内容的实施方式可用于多种潜在的应用，特别是在运输产业中，包括，例如，航空航天、船舶和汽车应用。因此，现参考图10和11，本公开内容的实施方式可用在图10所示的航空器制造和维护方法60和图11所示的航空器62的情况中。公开的实施方式的航空器应用可以包括，例如，各种结构性复合部件和组件，特别是在组装过程中需要使用紧固件的那些。在生产前期间，示例性方法60可以包括航空器62的规格和设计64以及材料采购66。在生产期间，发生航空器62的部件和子组件的制造68以及系统整合70。其后，航空器62可经受认证和交付72以便投入使用74。在消费者使用的同时，航空器62安排进行日常维修和保养76(其还可以包括改进、重新配置、整修等等)。
方法60的每个过程可以通过系统整合人员、第三方和/或操作人员(例如，消费者)执行或实施。出于该描述的目的，系统整合人员可以包括但不限于诸多航空器制造商和主要系统转包商；第三方可以非限制性地包括诸多销售商、转包商和供应商；以及操作者可以是航空公司、租赁公司、军事实体、服务组织等。
如图11所示，通过示例性方法60生产的航空器62可以包括具有多个系统80的机体78和内部82。高水平系统82的实例包括一个或多个推进系统84、电力系统86、液压系统88和环境系统90。可以包括任意数量的其它系统。公开的方法可用于制造用在机体78或内部82中的部件、结构和组件。虽然显示航空航天的实例，但本公开内容的原理还可适用于各种其它的工业，比如于船舶和汽车工业。
可以在生产和维护方法60的任意一个或多个阶段期间利用本文实施的系统和方法。例如，对应于生产过程68的部件、结构和组件可以以与使用航空器62时生产的部件、结构和组件类似的方式构造或制造。另外，例如通过大幅加快航空器62的装配或减少航空器62的成本，可以在生产阶段68和70期间利用一个或多个装置实施方式、方法实施方式或其组合。类似地，当航空器62在使用中，例如但不限于，用于维修和保养76时，可以利用一个或多个装置实施方式、方法实施方式或其组合。
虽然本公开内容的实施方式已经关于某些示例性的实施方式进行了描述，但应当理解特定实施方式是出于说明而非限制的目的，本领域技术人员将想到其它变型。

Claims (12)

1.复合材料结构，包括：
纤维增强树脂板层的层压堆叠；以及
金属片的堆叠，所述金属片具有与所述纤维增强树脂板层的边缘交叉的边缘，以形成将所述纤维增强树脂板层与所述金属片连接的复合材料-金属接头。
2.权利要求1所述的复合材料结构，其中：
所述纤维增强树脂板层和金属片的堆叠分层排列，其中每个所述层包括金属片和至少一个所述纤维增强树脂板层。
3.权利要求2所述的复合材料结构，其中每个所述层中的所述纤维增强树脂板层的厚度大体等于所述层中所述金属片的厚度。
4.权利要求2所述的复合材料结构，其中：
每个所述层中的所述纤维增强树脂板层和所述金属片具有基本对接的边缘，形成树脂-金属过渡点。
5.权利要求4所述的复合材料结构，其中所述层的所述过渡点相对于彼此交错。
6.权利要求2所述的复合材料结构，其中所述层在所述树脂板层的堆叠和所述金属片的堆叠之间形成纤维增强树脂-复合材料指形接头。
7.权利要求1所述的复合材料结构，进一步包括：
在相邻的所述金属片之间的粘合剂层，用于将所述片粘合在一起。
8.权利要求1所述的复合材料结构，其中：
所述金属片是钛合金，并且
所述板层的所述纤维增强包括碳。
9.制造复合材料结构的方法，包括：
形成具有纤维增强复合树脂部分和金属部分的多层复合材料铺叠，包括在所述铺叠的所述复合树脂部分和所述金属部分之间形成复合材料-金属接头。
10.权利要求9所述的方法，其中形成所述铺叠包括通过将至少一个纤维增强复合树脂板层和一个金属片以彼此基本上边对边对接放置，形成每个所述层，以在所述层中的所述纤维增强复合树脂和所述金属之间形成过渡点。
11.权利要求10所述的方法，其中形成所述铺叠包括将所述层中的所述过渡点相对于彼此交错。
12.权利要求10所述的方法，进一步包括：
通过在所述金属片之间放置粘合剂层而将所述金属部分组合。
CN201180039587.1A 2010-08-17 2011-06-22 具有复合材料-金属接头的复合材料结构以及制造其的方法 Active CN103068565B (zh)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US12/857,835 US8652606B2 (en) 2010-08-17 2010-08-17 Composite structures having composite-to-metal joints and method for making the same
US12/857,835 2010-08-17
PCT/US2011/041519 WO2012024023A1 (en) 2010-08-17 2011-06-22 Composite structures having composite-to-metal joints and method for making the same

Publications (2)

Publication Number Publication Date
CN103068565A true CN103068565A (zh) 2013-04-24
CN103068565B CN103068565B (zh) 2016-05-18

Family

ID=44280683

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201180039587.1A Active CN103068565B (zh) 2010-08-17 2011-06-22 具有复合材料-金属接头的复合材料结构以及制造其的方法

Country Status (8)

Country Link
US (2) US8652606B2 (zh)
EP (1) EP2605902B1 (zh)
JP (1) JP5840687B2 (zh)
KR (1) KR101859783B1 (zh)
CN (1) CN103068565B (zh)
BR (1) BR112013003588B1 (zh)
CA (1) CA2805468C (zh)
WO (1) WO2012024023A1 (zh)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105501428A (zh) * 2014-10-09 2016-04-20 波音公司 具有复合物-金属接头的复合结构及其制造方法
CN106457703A (zh) * 2014-03-17 2017-02-22 Gtm先进产品有限公司 金属片和相互结合的粘合剂层的叠层及获得此叠层的方法
CN107160703A (zh) * 2016-03-08 2017-09-15 形状连接技术有限公司及两合公司 功能元件
CN107453018A (zh) * 2016-05-31 2017-12-08 洛阳尖端技术研究院 超材料天线及其成型方法
CN111791552A (zh) * 2019-04-08 2020-10-20 波音公司 层压金属结构及其制造方法
CN113601934A (zh) * 2020-04-17 2021-11-05 本田技研工业株式会社 过渡结构在纤维增强复合材料层中的功能性集成
WO2023134124A1 (zh) * 2022-01-17 2023-07-20 哈焊国创(青岛)焊接工程创新中心有限公司 一种轻质合金与纤维增强复合材料异质接头及制备方法

Families Citing this family (50)

* Cited by examiner, † Cited by third party
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
US8442804B2 (en) 2007-10-25 2013-05-14 The Boeing Company Method and apparatus for composite part data extraction
US8620627B2 (en) 2009-10-13 2013-12-31 The Boeing Company Composite information display for a part
US8993084B2 (en) 2010-08-17 2015-03-31 The Boeing Company Multi-layer metallic structure and composite-to-metal joint methods
US8652606B2 (en) 2010-08-17 2014-02-18 The Boeing Company Composite structures having composite-to-metal joints and method for making the same
US9522512B2 (en) 2010-08-17 2016-12-20 The Boeing Company Methods for making composite structures having composite-to-metal joints
GB201016279D0 (en) 2010-09-28 2010-11-10 Airbus Operations Ltd Stiffener run-out
US8784596B2 (en) * 2010-11-19 2014-07-22 The Boeing Company Method for making and joining composite sandwich shell edge joint
US8875931B2 (en) 2010-11-19 2014-11-04 The Boeing Company Composite sandwich shell edge joint
KR20130059153A (ko) * 2011-11-28 2013-06-05 현대자동차주식회사 접착제를 이용한 금속재와 고분자 복합재 결합체의 제조방법
EP2650120B1 (en) * 2012-04-10 2020-06-17 The Boeing Company Multi-layer metallic structure
FR2989723B1 (fr) * 2012-04-20 2024-02-09 Astrium Sas Assemblage de troncons de pieces structurables
US8770134B2 (en) * 2012-04-30 2014-07-08 Carl E. Baugh Structurally-interlaminated marine vessel
US10655328B2 (en) * 2012-05-24 2020-05-19 The University Of Kentucky Research Foundation Structural reinforcement, reinforced structural member and related method
GB201209437D0 (en) * 2012-05-28 2012-07-11 Kitchener Renato Power supply and battery charger
CN102941703A (zh) * 2012-10-21 2013-02-27 刘君才 超级复合材料迭层板
WO2014116151A1 (en) * 2013-01-24 2014-07-31 Saab Ab An aerial skin article with reinforced fastening holes
US9040138B2 (en) 2013-04-29 2015-05-26 General Electric Company Composite article including composite to metal interlock and method of fabrication
EP2999587A1 (en) * 2013-05-21 2016-03-30 Cutting Dynamics, Inc. Reinforced thermoplastic structural component and process to make the same
US9227718B2 (en) * 2013-06-07 2016-01-05 The Boeing Company Lower joints between outboard wing boxes and center wing sections of aircraft wing assemblies
RU2548435C2 (ru) * 2013-07-18 2015-04-20 Открытое акционерное общество "Национальный институт авиационных технологий" (ОАО НИАТ) Соединение листовых деталей из металлокомпозитных материалов и способ его изготовления
US9524356B2 (en) * 2013-10-16 2016-12-20 General Electric Company System and methods of generating a computer model of composite component
DE102013221168A1 (de) * 2013-10-18 2015-05-07 Bayerische Motoren Werke Aktiengesellschaft Bauteilanordnung
US9403350B2 (en) 2013-12-16 2016-08-02 The Nordam Group, Inc. Flash control metal bonding
JP5972854B2 (ja) * 2013-12-17 2016-08-17 三菱重工業株式会社 繊維強化複合部材の接合方法及び接合体、並びに風車翼の製造方法
EP3095296B1 (en) * 2014-01-13 2019-12-18 Kjell Lindskog Method and arrangement for manufacture of a product or completion of a product
US9719536B2 (en) 2014-07-03 2017-08-01 The Boeing Company Assemblies including shape memory alloy fittings and composite structural members
US10518484B2 (en) 2015-02-13 2019-12-31 The University Of Tokyo Bonded structure
KR101846648B1 (ko) 2016-03-15 2018-04-09 현대자동차주식회사 접합구조를 갖는 복합재 부품
KR102507815B1 (ko) 2016-04-06 2023-03-08 현대자동차주식회사 금속시트 삽입형 복합재
US11491766B2 (en) 2016-08-29 2022-11-08 Northrop Grumman Systems Corporation Hybrid metal composite structures, rocket motors and multi stage rocket motor assemblies including hybrid metal composite structures, and related methods
US10603873B2 (en) 2016-08-29 2020-03-31 Northrop Grumman Innovation Systems, Inc. Hybrid metal composite structures, rocket cases, and related methods
JP6789047B2 (ja) * 2016-09-23 2020-11-25 矢崎総業株式会社 車両アース構造
KR101836716B1 (ko) 2016-10-12 2018-03-08 현대자동차주식회사 금속 플레이트가 삽입된 복합재 부품 및 그 제조방법
NL2017849B1 (en) * 2016-11-23 2018-05-28 Gtm Advanced Products B V Laminate of mutually bonded adhesive layers and spliced metal sheets
JP6810593B2 (ja) * 2016-12-14 2021-01-06 三菱重工業株式会社 複合材料の成形方法及び複合材料
US20180179990A1 (en) 2016-12-27 2018-06-28 Orbital Atk, Inc. Hybrid metal composite structures, rocket motors and multi-stage rocket motor assemblies including hybrid metal composite structures, and related methods
US10661838B2 (en) 2017-05-31 2020-05-26 Honda Motor Co., Ltd. Multi-material vehicle roof stiffener
US11760043B2 (en) 2017-09-29 2023-09-19 Honda Motor Co., Ltd. High strength mechanical fastening inclusions for fiber reinforced polymer structures
US10994856B2 (en) * 2017-10-16 2021-05-04 Rohr, Inc. Structural panel with splice joint between adjacent core structures
DE102018126473A1 (de) * 2018-07-12 2020-01-16 Tdk Electronics Ag Anordnung
US11358345B2 (en) 2019-01-02 2022-06-14 The Boeing Company Internal tooling for composite parts
NL2023482B1 (en) 2019-07-11 2021-02-03 Dutch Thermoplastic Components B V Thermoplastic composite product
US11806948B2 (en) 2019-12-12 2023-11-07 The Boeing Company Method of forming flyaway stringer end caps
US11718047B2 (en) * 2019-12-12 2023-08-08 The Boeing Company Flyaway stringer end caps
US11376812B2 (en) 2020-02-11 2022-07-05 Helicoid Industries Inc. Shock and impact resistant structures
US11346499B1 (en) 2021-06-01 2022-05-31 Helicoid Industries Inc. Containers and methods for protecting pressure vessels
US11852297B2 (en) 2021-06-01 2023-12-26 Helicoid Industries Inc. Containers and methods for protecting pressure vessels
WO2024006078A1 (en) 2022-06-27 2024-01-04 Helicoid Industries Inc. High impact-resistant, reinforced fiber for leading edge protection of aerodynamic structures

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000056541A1 (de) * 1999-03-20 2000-09-28 DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbundmaterial mit einem verstärkten verbindungsbereich

Family Cites Families (109)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3711934A (en) 1970-09-17 1973-01-23 Monsanto Co Method of preparing metal foil/graphite fiber/epoxy resin laminates
US3780929A (en) 1971-06-11 1973-12-25 Stack Pac Corp Packaging construction
US4072516A (en) 1975-09-15 1978-02-07 Fiber Materials, Inc. Graphite fiber/metal composites
US4229473A (en) 1978-03-24 1980-10-21 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Partial interlaminar separation system for composites
US4334124A (en) 1980-03-26 1982-06-08 Intergraph Corporation Floating coordinate system
US4498139A (en) 1981-10-09 1985-02-05 Moskovskoe Nauchno-Proizvodstvennoe Objedinenie Po Stroitelnomu I Dorozhnomu Mashinostroeniju Apparatus for designing three-dimensional structures
US4524620A (en) * 1983-02-07 1985-06-25 Hughes Helicopters, Inc. In-flight monitoring of composite structural components such as helicopter rotor blades
US4666546A (en) 1985-10-18 1987-05-19 Treber Gerald C Method for validating sequential ordering of laminate plies
US4849913A (en) 1987-04-10 1989-07-18 The Boeing Company Method for the design and construction of composite parts
US5006990A (en) 1987-04-10 1991-04-09 The Boeing Company Method and apparatus for the design and construction of composite parts
US5031457A (en) 1988-01-22 1991-07-16 Board Of Regents Of The Ou System for nondestructively determining composite material parameters
US4907164A (en) 1988-09-26 1990-03-06 General Electric Company Automatically optimized NC tool path generation for machining
US5038291A (en) 1989-04-03 1991-08-06 General Electric Company Computerized ply pattern generation
US5119309A (en) 1989-04-26 1992-06-02 General Motors Corporation Feature based method of designing automotive panels
US5216612A (en) 1990-07-16 1993-06-01 R. J. Reynolds Tobacco Company Intelligent computer integrated maintenance system and method
US5365996A (en) 1992-06-10 1994-11-22 Amei Technologies Inc. Method and apparatus for making customized fixation devices
US5951800A (en) * 1992-11-18 1999-09-14 Mcdonnell Douglas Corp. Fiber/metal laminate splice
US5500272A (en) 1995-01-11 1996-03-19 Northrop Grumman Corporation High efficiency load transfer in composite structure
US5866272A (en) 1996-01-11 1999-02-02 The Boeing Company Titanium-polymer hybrid laminates
US6030483A (en) 1996-09-10 2000-02-29 Wilson; Graeme Paul Method of forming laminates using a tessellated core
US6253218B1 (en) 1996-12-26 2001-06-26 Atsushi Aoki Three dimensional data display method utilizing view point tracing and reduced document images
US7010472B1 (en) 1997-05-12 2006-03-07 Mcdonnell Douglas Corporation Knowledge driven composite design optimization process and system therefor
US5984511A (en) 1997-05-12 1999-11-16 Mcdonnell Douglas Corporation Knowledge driven composite design optimization process and system therefor
ATE226512T1 (de) * 1997-05-28 2002-11-15 Structural Laminates Co Verfahren zur herstellung eines mehrschichtwerkstoffes und ein mehrschichtwerkstoff der mit diesem verfahren herzustellen ist
US6041132A (en) 1997-07-29 2000-03-21 General Electric Company Computed tomography inspection of composite ply structure
US6052631A (en) 1997-08-08 2000-04-18 Management Systems Data Service, Inc. ("Msds, Inc.") Method and system for facilitating vehicle inspection to detect previous damage and repairs
WO1999034336A1 (en) 1997-12-29 1999-07-08 The United States Of America, Represented By The Administrator Of The National Aeronautics And Space Administration (Nasa) Triangle geometry processing for surface modeling and cartesian grid generation
US6278457B1 (en) 1998-01-15 2001-08-21 International Business Machines Corporation Methods and apparatus for performing sampling based synthesis of three-dimensional geometric models
US6138056A (en) 1998-03-02 2000-10-24 Therwood Corporation System and method for maintenance and repair of CNC machines
JP2000182081A (ja) 1998-12-14 2000-06-30 Suzuki Motor Corp 解析モデル作成方法および装置並びに解析モデル作成用プログラム若しくは解析モデルデータを記憶した記憶媒体
US6356437B1 (en) 1999-03-29 2002-03-12 Siemens Dematic Postal Automation, L.P. System, apparatus and method for providing a portable customizable maintenance support instruction system
DE69910174T3 (de) 1999-04-07 2012-03-08 Mcdonnell Douglas Corp. Wissensbasierter Entwurfsoptimierungsprozess für Verbundwerkstoffe und System dafür
JP2000298734A (ja) 1999-04-12 2000-10-24 Mitsubishi Electric Corp ３次元モデルの断面生成装置
US7424543B2 (en) 1999-09-08 2008-09-09 Rice Iii James L System and method of permissive data flow and application transfer
US6959235B1 (en) 1999-10-28 2005-10-25 General Electric Company Diagnosis and repair system and method
US6629302B2 (en) 1999-12-22 2003-09-30 Shinji Miura Circuit board design aiding apparatus, design aiding method, and storage medium storing design aiding program
US6484776B1 (en) 2000-04-07 2002-11-26 Northrop Grumman Corporation System for constructing a laminate
JP2002036177A (ja) 2000-05-26 2002-02-05 Gerber Technol Inc シート部材の組合せを切り取る装置及び方法
US6982711B1 (en) 2000-09-18 2006-01-03 Hitachi, Ltd. Solid shape describing method and device therefor and solid shape design support system using them
US6690159B2 (en) 2000-09-28 2004-02-10 Eldec Corporation Position indicating system
US6799081B1 (en) 2000-11-15 2004-09-28 Mcdonnell Douglas Corporation Fiber placement and fiber steering systems and corresponding software for composite structures
JP2002183432A (ja) 2000-12-14 2002-06-28 Ibm Japan Ltd データ抽出方法、データ操作方法、債権情報抽出方法、データベースシステム、債権商品化処理装置、記憶媒体及びコンピュータプログラム
US6625618B1 (en) 2000-12-15 2003-09-23 Tsunehiko Arai Maintenance manual interface system and medium containing a computer program product thereof
US7079996B2 (en) 2001-05-30 2006-07-18 Ford Global Technologies, Llc System and method for design of experiments using direct surface manipulation of a mesh model
US20030055812A1 (en) 2001-09-14 2003-03-20 Xccelerator Technologies, Inc. Vehicle parts monitoring system and associated method
DE10148232B4 (de) 2001-09-21 2004-04-15 Vaillant Gmbh Verfahren zur Fehler-Störungsbeseitigung vorzugsweise bei Heizgeräten
US7324103B2 (en) 2001-10-30 2008-01-29 Ford Motor Company System and method of direct mesh manipulation
US7171344B2 (en) 2001-12-21 2007-01-30 Caterpillar Inc Method and system for providing end-user visualization
US20030145017A1 (en) 2002-01-31 2003-07-31 Patton Thadd Clark Method and application for removing material from documents for external sources
GB0208088D0 (en) 2002-04-09 2002-05-22 Delcam Plc Method and system for the generation of a computer model
GB0209543D0 (en) 2002-04-26 2002-06-05 Rolls Royce Plc The automation and optimisation of the design of a component
US6843565B2 (en) 2002-08-02 2005-01-18 General Electric Company Laser projection system to facilitate layup of complex composite shapes
US20040024661A1 (en) 2002-08-02 2004-02-05 Girish Shirhatti Systems and methods for inventory management
US7244230B2 (en) 2002-11-08 2007-07-17 Siemens Medical Solutions Usa, Inc. Computer aided diagnostic assistance for medical imaging
CA2411898A1 (en) 2002-11-15 2004-05-15 Idelix Software Inc. A method and system for controlling access to detail-in-context presentations
US6907313B2 (en) 2003-01-17 2005-06-14 Dp Technology Corp. Method and system for computer aided manufacturing
JP4364520B2 (ja) 2003-01-29 2009-11-18 富士通株式会社 三次元板金モデル作成方法及びコンピュータプログラム
JP2004264993A (ja) 2003-02-28 2004-09-24 Honda Motor Co Ltd 補修用部品統合支援システムおよび補修用部品統合支援方法
US7809679B2 (en) 2003-03-03 2010-10-05 Fisher-Rosemount Systems, Inc. Distributed data access methods and apparatus for process control systems
US7366643B2 (en) 2003-03-20 2008-04-29 Delphi Technologies, Inc. System, method, and storage medium for determining a packaging design for a container
US20040236561A1 (en) 2003-05-21 2004-11-25 Gary Smith Component management engine
JP2005056090A (ja) 2003-08-01 2005-03-03 Tsunehiko Arai 整備マニュアル用インターフェイスシステムおよび整備マニュアル用インターフェイスシステムのプログラム記録媒体
US7159112B1 (en) 2003-08-26 2007-01-02 Nvidia Corporation Decryption of graphics data in a graphics processing pipeline
US7115323B2 (en) * 2003-08-28 2006-10-03 The Boeing Company Titanium foil ply replacement in layup of composite skin
US8262823B2 (en) * 2003-09-04 2012-09-11 The Boeing Company Window skin panel and method of making same
US7300693B2 (en) 2003-09-04 2007-11-27 The Boeing Company Resin infused transparent skin panel and method of making same
US7099725B2 (en) 2003-12-02 2006-08-29 The Boeing Company Alternate ply representation for composite design and manufacturing
US6819966B1 (en) 2003-12-06 2004-11-16 Paul E. Haeberli Fabrication of free form structures from planar materials
US7243055B2 (en) 2004-01-28 2007-07-10 The Boeing Company Composite stacking sequence optimization for multi-zoned composites
US7076323B2 (en) 2004-02-06 2006-07-11 The Boeing Company Apparatus and method for creating sketch-based eggcrate substructures for composite parts
WO2005105641A2 (en) 2004-04-21 2005-11-10 Ingersoll Machine Tools, Inc. Automated fiber placement using multiple placement heads, replaceable creels, and replaceable placement heads
US7513965B2 (en) 2004-04-21 2009-04-07 Ingersoll Machine Tools, Inc. Performing high-speed events “on-the-fly” during fabrication of a composite structure by automated fiber placement
BRPI0418734A (pt) 2004-04-29 2007-09-11 Federico Martinez-Cepeda perfil acanalado retesado
US7621435B2 (en) * 2004-06-17 2009-11-24 The Regents Of The University Of California Designs and fabrication of structural armor
CA2574487A1 (en) 2004-07-19 2006-02-23 David C. Loda System and method for fault code driven maintenance system
US7526418B2 (en) 2004-08-12 2009-04-28 Saudi Arabian Oil Company Highly-parallel, implicit compositional reservoir simulator for multi-million-cell models
MX2007002101A (es) 2004-08-21 2007-08-14 Co Exprise Inc Metodos, sistemas, y aparatos para comercio extendido de empresas.
US7365747B2 (en) 2004-12-07 2008-04-29 The Boeing Company Methods and systems for controlling an image generator to define, generate, and view geometric images of an object
US20080052281A1 (en) 2006-08-23 2008-02-28 Lockheed Martin Corporation Database insertion and retrieval system and method
US20060265198A1 (en) 2005-03-01 2006-11-23 Satoshi Kanai Apparatus and a method of feature edge extraction from a triangular mesh model
JP2006350499A (ja) 2005-06-14 2006-12-28 Shin Caterpillar Mitsubishi Ltd 作業機械の保守管理装置
JP5017909B2 (ja) 2005-06-22 2012-09-05 コニカミノルタエムジー株式会社 領域抽出装置、領域抽出方法及びプログラム
US7423523B2 (en) 2005-08-03 2008-09-09 The Boeing Company Composite ply layup using electronically identifiable tags
US7643970B2 (en) 2005-11-09 2010-01-05 The Boeing Company Tape course generation method and apparatus for programming a composite tape lamination machine
US7376480B2 (en) 2005-11-09 2008-05-20 The Boeing Company Multihead composite material application machine programming method and apparatus for manufacturing composite structures
US7769481B2 (en) 2005-12-23 2010-08-03 The Boeing Company Head assignment system and method
US7747421B2 (en) 2005-12-23 2010-06-29 The Boeing Company Head assignment modeling and simulation
US7561996B2 (en) 2006-01-13 2009-07-14 Chrysler Llc Automated dimensional drawing generating apparatus
US7761183B2 (en) 2006-02-13 2010-07-20 Sullivan Douglas G Methods and systems for producing numerical control program files for controlling machine tools
EP1840775A1 (en) 2006-03-31 2007-10-03 Airbus Espana, S.L. Computer-aided method of obtaining a ply model of composite component
US7545274B2 (en) 2006-04-10 2009-06-09 The Boeing Company RFID data management system
DE102007063608B4 (de) * 2007-05-23 2011-04-21 Airbus Operations Gmbh Verbund und Rumpfzellenabschnitt mit einem derartigen Verbund
US7809531B2 (en) 2007-06-15 2010-10-05 The Boeing Company Methods and systems for explicit representation of composite structures
US7912602B2 (en) 2007-06-29 2011-03-22 Caterpillar Inc. Visual diagnostic system and subscription service
US7555404B2 (en) 2007-08-09 2009-06-30 The Boeing Company Methods and systems for automated ply boundary and orientation inspection
US7809454B2 (en) 2007-09-17 2010-10-05 The Boeing Company Method and apparatus for simulating composite panel manufacturing
US7720561B2 (en) 2007-09-21 2010-05-18 The Boeing Company Optimizing non-productive part motion in an automated tape laydown machine
US8321180B2 (en) 2007-10-25 2012-11-27 The Boeing Company Method and apparatus for composite part data extraction
US8442804B2 (en) 2007-10-25 2013-05-14 The Boeing Company Method and apparatus for composite part data extraction
US8285407B2 (en) 2007-10-25 2012-10-09 The Boeing Company Method and apparatus for composite part data extraction
US20090138139A1 (en) 2007-11-26 2009-05-28 Tsai Ta C Technical data navigation system and method
US7983809B2 (en) 2007-12-21 2011-07-19 Sikorsky Aircraft Corporation Aircraft integrated support system (ISS)
US8165703B2 (en) 2008-08-18 2012-04-24 Airbus Operations S.L. Computer assisted method for the advanced design of bent parts of composite material
US8209838B2 (en) 2008-12-19 2012-07-03 The Boeing Company Repairing composite structures
US8108058B2 (en) 2009-02-09 2012-01-31 The Boeing Company Method of analyzing composite structures
JP4952763B2 (ja) 2009-10-07 2012-06-13 富士通株式会社 連携解析シミュレーション装置、連携解析シミュレーション方法、及び連携解析シミュレーションプログラム
US8620627B2 (en) 2009-10-13 2013-12-31 The Boeing Company Composite information display for a part
US8652606B2 (en) 2010-08-17 2014-02-18 The Boeing Company Composite structures having composite-to-metal joints and method for making the same
US8333345B2 (en) 2010-08-26 2012-12-18 The Boeing Company Composite aircraft joint

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000056541A1 (de) * 1999-03-20 2000-09-28 DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbundmaterial mit einem verstärkten verbindungsbereich

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106457703A (zh) * 2014-03-17 2017-02-22 Gtm先进产品有限公司 金属片和相互结合的粘合剂层的叠层及获得此叠层的方法
CN106457703B (zh) * 2014-03-17 2019-04-19 Gtm先进产品有限公司 金属片和相互结合的粘合剂层的叠层及获得此叠层的方法
CN105501428A (zh) * 2014-10-09 2016-04-20 波音公司 具有复合物-金属接头的复合结构及其制造方法
CN105501428B (zh) * 2014-10-09 2020-06-30 波音公司 具有复合物-金属接头的复合结构及其制造方法
CN107160703A (zh) * 2016-03-08 2017-09-15 形状连接技术有限公司及两合公司 功能元件
CN107453018A (zh) * 2016-05-31 2017-12-08 洛阳尖端技术研究院 超材料天线及其成型方法
CN111791552A (zh) * 2019-04-08 2020-10-20 波音公司 层压金属结构及其制造方法
US11820100B2 (en) 2019-04-08 2023-11-21 The Boeing Company Laminated metallic structures
CN111791552B (zh) * 2019-04-08 2024-03-12 波音公司 层压金属结构及其制造方法
CN113601934A (zh) * 2020-04-17 2021-11-05 本田技研工业株式会社 过渡结构在纤维增强复合材料层中的功能性集成
WO2023134124A1 (zh) * 2022-01-17 2023-07-20 哈焊国创(青岛)焊接工程创新中心有限公司 一种轻质合金与纤维增强复合材料异质接头及制备方法

Also Published As

Publication number Publication date
US20120045606A1 (en) 2012-02-23
US8894801B2 (en) 2014-11-25
US8652606B2 (en) 2014-02-18
JP2013539428A (ja) 2013-10-24
CA2805468A1 (en) 2012-02-23
EP2605902A1 (en) 2013-06-26
WO2012024023A1 (en) 2012-02-23
BR112013003588A2 (pt) 2018-03-20
KR20130096232A (ko) 2013-08-29
KR101859783B1 (ko) 2018-05-18
JP5840687B2 (ja) 2016-01-06
CN103068565B (zh) 2016-05-18
US20130122236A1 (en) 2013-05-16
EP2605902B1 (en) 2021-02-17
CA2805468C (en) 2016-09-13
BR112013003588B1 (pt) 2020-02-11

Similar Documents

Publication Publication Date Title
CN103068565B (zh) 具有复合材料-金属接头的复合材料结构以及制造其的方法
US11084269B2 (en) Multi-layer metallic structure and composite-to-metal joint methods
KR102030192B1 (ko) 복합재 만곡부 충전부 및 이를 제조하는 방법물
CN105501428B (zh) 具有复合物-金属接头的复合结构及其制造方法
JP6505997B2 (ja) 幾何学形状充填材要素を有するラミネート複合角部充填材およびそれを形成する方法
EP2709830B1 (en) Aircraft structure for high capacity pull off
JP5548192B2 (ja) 強化補強材を作製する方法
EP2406071B1 (en) Composite structures employing quasi-isotropic laminates
JP5852887B2 (ja) 適合させたパッチを用いた複合構造の予測可能な結合補修
EP2507050B1 (en) Sandwich structure having arrestment feature and method of making the same
EP2556947B1 (en) Vertical laminate noodle for high capacity pull-off for a composite stringer
EP2650120B1 (en) Multi-layer metallic structure

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant