CN104843169B - 复合材料填料 - Google Patents
复合材料填料 Download PDFInfo
- Publication number
- CN104843169B CN104843169B CN201510044925.0A CN201510044925A CN104843169B CN 104843169 B CN104843169 B CN 104843169B CN 201510044925 A CN201510044925 A CN 201510044925A CN 104843169 B CN104843169 B CN 104843169B
- Authority
- CN
- China
- Prior art keywords
- composite material
- layer
- material filler
- filler
- formed punch
- 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.)
- Active
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 222
- 239000000945 filler Substances 0.000 title claims abstract description 126
- 238000000034 method Methods 0.000 claims abstract description 42
- 238000005452 bending Methods 0.000 claims abstract description 18
- 238000007493 shaping process Methods 0.000 claims abstract description 14
- 239000000463 material Substances 0.000 claims description 28
- 150000001875 compounds Chemical class 0.000 claims description 5
- GPRLSGONYQIRFK-MNYXATJNSA-N triton Chemical compound [3H+] GPRLSGONYQIRFK-MNYXATJNSA-N 0.000 claims 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 27
- 238000004519 manufacturing process Methods 0.000 description 26
- 238000000465 moulding Methods 0.000 description 25
- 238000010586 diagram Methods 0.000 description 15
- 230000008569 process Effects 0.000 description 9
- 238000009833 condensation Methods 0.000 description 5
- 230000005494 condensation Effects 0.000 description 5
- 230000000750 progressive effect Effects 0.000 description 5
- 239000002023 wood Substances 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 4
- 239000004744 fabric Substances 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 239000011230 binding agent Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000009940 knitting Methods 0.000 description 1
- 235000012149 noodles Nutrition 0.000 description 1
- 239000002952 polymeric resin Substances 0.000 description 1
- 239000012783 reinforcing fiber Substances 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 229920003002 synthetic resin Polymers 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- 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
- B29C53/04—Bending or folding of plates or sheets
-
- 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
- B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
- B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
- B29C65/4835—Heat curing adhesives
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- 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
- B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
- B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
- B29C65/5014—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being fibre-reinforced
-
- 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
- B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
- B29C65/5057—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like positioned between the surfaces to be joined
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- 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
- B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
- B29C65/5064—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped
- B29C65/5078—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped and being composed by several elements
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- 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
- B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
- B29C66/112—Single lapped joints
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- 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
- B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
- B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
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- 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
- B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
- B29C66/53—Joining single elements to tubular articles, hollow articles or bars
- B29C66/532—Joining single elements to the wall of tubular articles, hollow articles or bars
-
- 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
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- 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
- B29C66/63—Internally supporting the article during joining
- B29C66/636—Internally supporting the article during joining using a support which remains in the joined object
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- 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
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- B29C66/721—Fibre-reinforced materials
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- 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
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- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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- 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
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- B29C70/345—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
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- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0003—Producing profiled members, e.g. beams
- B29D99/0005—Producing noodles, i.e. composite gap fillers, characterised by their construction
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B1/00—Layered products having a non-planar shape
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- 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
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/0012—Mechanical treatment, e.g. roughening, deforming, stretching
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- 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
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- 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
- B64C1/064—Stringers; Longerons
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- 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
- B29C66/73—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 intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
- B29C66/739—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 intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset
- B29C66/7394—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 intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoset
- B29C66/73941—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 intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoset characterised by the materials of both parts being thermosets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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Abstract
本发明提出了一种方法和装置。复合材料的层被铺放在成型工具上。在所述层中的每一层中形成各自的弯曲以在成型工具上形成包含弯曲层的复合材料填料。将包含弯曲层的复合材料填料放入由至少一个复合材料结构形成的间隙中。
Description
背景技术
通过组合两个或更多个功能部件而产生的复合材料是坚韧且是轻质的材料。例如,复合材料可以包括结合在聚合物树脂基体中的增强纤维。该纤维可以是单向的或可以表现为织布或织物的形式。在热固性复合材料中,纤维和树脂被设置且被固化以形成复合材料。
当复合材料结构元件被连接在一起时,沿着元件之间的粘接线可以存在间隙或空隙,该间隙或空隙会需要被填充以便增加粘接的强度。例如,在飞行器制造业中,复合材料机身加强件(诸如纵梁)可以包括在纵梁和机身蒙皮之间的半径粘接线处的粘合剂填料。粘合剂填料以三角形横截面带的形式被应用,有时称之为填面(noodles)或填料,其填充粘接线处的空隙。粘合剂填料可以由诸如粘合剂、预浸料坯带或织物等的复合材料形成。
当加强件在填料的区域中具有足够的拉脱(pull-off)强度时,加强件抵抗针对给定的应用施加在加强件上的拉伸负荷。为了实现足够的拉脱强度,增加加强件的规格是必要的,因此增加了飞行器的重量。可替代地,半径块可以被添加至加强件,以便增加拉脱强度,但是半径块可能增加飞行器的不期望的重量、复杂性或成本。
填料可以由挤压材料、轧制复合材料或平行于飞行器蒙皮的复合材料的堆叠条形成。当填料具有足够坚硬度时,填料可以将一些负荷从加强件传递至基座。如果填料不足够坚硬,则其可能无法起传递负荷的作用。
因此,将期望具有考虑至少上述一些问题以及其他可能的问题的方法和装置。
发明内容
本公开的说明性实施例提供了形成复合材料填料的方法。复合材料的层被铺放在成型工具上。在层中的每一层中形成各自的弯曲以在成型工具上形成包含弯曲层的复合材料填料。包含弯曲层的复合材料填料被放入由至少一个复合材料结构形成的间隙中。
本公开的另一个说明性实施例提供了复合材料填料。该复合材料填料包含具有第一弯曲形状的第一层和具有第二弯曲形状的第二层。
本公开的又一个说明性实施例提供了复合材料填料。该复合材料填料包含多个复合材料层,每个复合材料层具有各自的弯曲形状。
这些特点和功能能够在本公开的各种实施例中被独立地实现或者可以被结合在另一些实施例中,参考以下实施方式和附图能够了解实施例的进一步细节。
附图说明
在随附的权利要求中阐明了被认为是说明性实施例的特性的新颖性特征。然而,当结合附图阅读时,通过参考本公开的说明性实施例的以下具体实施方式,将更好地理解说明性实施例以及优选的使用模式,及其进一步的目标和特征,其中:
图1是在其中可以实施说明性实施例的飞行器的图示说明;
图2是根据说明性实施例的复合材料填料和复合材料结构元件的等距视图的图示说明。
图3是根据说明性实施例的复合材料填料和复合材料结构元件的主视图的图示说明。
图4是根据说明性实施例的复合材料填料的主视图的图示说明。
图5是根据说明性实施例的第一层和成型设备的图示说明。
图6是根据说明性实施例的具有第一弯曲形状的第一层和成型设备的图示说明。
图7是根据说明性实施例的第二层、具有第一弯曲形状的第一层和成型设备的图示说明。
图8是根据说明性实施例的具有第一弯曲形状的第一层、具有第二弯曲形状的第二层和成型设备的图示说明。
图9是根据说明性实施例的具有各自的弯曲形状的多个层和成型设备的图示说明。
图10是根据说明性实施例的第一模用冲头(die punch)的图示说明。
图11是根据说明性实施例的第二模用冲头的图示说明。
图12是根据说明性实施例的第三模用冲头的图示说明。
图13是根据说明性实施例的第四模用冲头的图示说明。
图14是根据说明性实施例的第五模用冲头的图示说明。
图15是根据说明性实施例的第六模用冲头的图示说明。
图16是根据说明性实施例的用于形成复合材料填料的过程的流程图的图示说明。
图17是根据说明性实施例的制造环境的框图的图示说明。
图18是根据说明性实施例的飞行器制造和使用方法的框图的图示说明。
图19是在其中可以实施说明性实施例的飞行器的框图的图示说明。
具体实施方式
说明性实施例意识到并考虑一种或更多种不同的考量。说明性实施例意识到并考虑遵循半径的铺层可以沿着半径引导负荷。因此,说明性实施例意识到并考虑形成遵循加强件的半径的铺层的填料可以沿着半径引导负荷而不是进入填料。因而,说明性实施例意识到并考虑形成遵循加强件的半径的填料可以增加填料的拉脱强度。
说明性示例进一步意识到并考虑形成遵循加强件的半径的填料可以具有额外的优点。具体地,说明性示例考虑当填料材料由复合材料结构元件的材料的类似形状和形式组成时,在固化周期期间或之后的至少一者中填料可以具有有利的热性能。
现在参考附图,并且具体地,参考图1,其示出了在其中可以实施说明性实施例的飞行器的图示说明。在该说明性示例中,飞行器100具有附接至主体106的机翼102和机翼104。飞行器100包括附接至机翼102的发动机108和附接至机翼104的发动机110。
主体106具有尾段112。水平稳定器114、水平稳定器116和垂直稳定器118被附接至主体106的尾段112。
飞行器100是飞行器的示例,可以根据说明性实施例在其中实施复合材料填料。例如,复合材料填料可以被放置在飞行器100的加强件120和复合材料蒙皮122之间。图1描绘了加强件120的展示图。
提供飞行器100的图示说明是为了说明在其中可以实施不同的说明性实施例的一种环境。图1中的飞行器100的图示说明并不意味着暗示对其中不同的说明性实施例可以被实施的方式的架构限制。例如,飞行器100被示出为商业客机。不同的说明性实施例可以被应用至其他类型的飞行器,诸如私人客机、旋翼飞机以及其他合适类型的飞行器。
现在转到图2,其根据说明性实施例示出了复合材料填料和复合材料结构元件的等距视图的图示说明。具体地,图2是沿图1的截面2-2的加强件120的加强件202的放大图。如所示出的,复合材料填料204被放置在由加强件202和复合材料蒙皮122形成的间隙206中。在该说明性示例中,复合材料填料204具有大体三角形横截面。尽管加强件202是单个的复合材料结构元件,但是在一些说明性示例中,加强件202反而可以为两个或更多个复合材料结构元件。贯穿全文,“复合材料结构元件”和“复合材料结构”可以被互换使用。在一些说明性示例中,加强件202是复合材料纵梁。
现在转到图3,其根据说明性实施例示出了复合材料填料和复合材料结构元件的主视图的图示说明。具体地,图3是自图2的方向3-3看过去的加强件202、复合材料填料204和复合材料蒙皮122的视图。
加强件202具有半径300和半径302。复合材料填料204的第一边304遵循半径300。复合材料填料204的第二边306遵循半径302。
现在转到图4,其根据说明性实施例示出了复合材料填料的主视图的图示说明。复合材料填料400可以是图2和图3中的复合材料填料204的实施例。复合材料填料400由多个层402形成。多个层402由至少一种复合材料形成。
多个层402可以包含一个或更多个铺层取向。具体地,多个层402可以具有0°铺层、+/-10°铺层、+/-15°铺层、+/-30°铺层、+/-45°铺层、+/-60°铺层、+/-75°铺层或者+/-90°铺层中的至少一者。
如本文所使用的,短语“至少一者”当与一系列项目一起使用时意味着所列项目中的一个或更多个的不同组合可以被使用并且可以只需要列表中每个项目中的一个。换句话说,“至少一者”意味着项目的任意组合并且可以使用来自列表的许多项目,但并不是需要列表中的所有项目。项目可以是特定对象、事物或者类别。
例如,“项目A、项目B、或项目C中的至少一者”可以包括但不限于项目A、项目A和项目B、或项目B。该示例也可以包括项目A、项目B、项目C、或项目B和项目C。当然,可以存在这些项目的任意组合。在另一些示例中,例如,“至少一者”可以是但不限于两个项目A;一个项目B和十个项目C;四个项目B和七个项目C;或其他合适的组合。
在该说明性示例中,多个层402包括第一层404、第二层406、第三层408、第四层410、第五层412、第六层414、第七层416、第八层418、第九层420、第十层422、第十一层424和第十二层426。尽管多个层402在该说明性示例中包括了十二层,但是多个层402可以包括等于或大于两层的任意数量的层。
多个层402中的每一层具有各自的弯曲形状428。各自的弯曲形状428中的每一个可以具有不同的角度。多个层402中的每一层可以堆叠或嵌套以形成复合材料填料400。
如由图4可见,多个层402的每一层具有各自的长度。在该说明性示例中,第一层404比多个层402中的每个其他层长。在该说明性示例中,多个层402中的每个连续层比每个先前层短。例如,第三层408比第二层406和第一层404二者都短。
第一层404形成复合材料填料400的第一边430和第二边432。复合材料填料400的第一边430和第二边432可以接触复合材料结构元件。第一边430具有半径433。第二边432具有半径435。多个层402遵循半径433和半径435。遵循半径433和半径435的多个层402可以沿着半径433和半径435中的至少一者引导负荷。复合材料填料400的第三边434由多个层402形成。第三边434可以接触诸如复合材料蒙皮的复合材料零件。
如所示出的,复合材料填料400包括挤压材料436。挤压材料436紧挨第十二层426被放置。挤压材料436可以存在以填充复合材料填料400中的间隙。在一些示例中,复合材料填料400可以只具有多个层402。
如所示出的,多个层402中的每一层包含单个铺层。然而,在另一些说明性示例中,多个层402的至少一层可以包含多个铺层。
现在转向图5,其根据说明性实施例示出了第一层和成型设备的图示说明。制造环境500可以是用于形成图4中的复合材料填料的制造环境的示例。制造环境500包括成型设备502和第一层504。第一层504可以由复合材料形成。在其中第一层由复合材料形成的说明性示例中,第一层504也可以被称为第一复合材料层。第一层504具有长度505。成型设备502包括第一模用冲头506和基座508。
如所示出的,基座508包括第一部分510、第二部分512和间隙514。为了形成复合材料填料,第一模用冲头506可以沿箭头516的方向向基座508移动。通过向基座508移动第一模用冲头506,成型设备502可以改变第一层504的形状。在该示例中,第一模用冲头506接触第一层504并沿箭头516的方向将负荷施加第一层504上。具体地,通过向基座508移动第一模用冲头506,成型设备502可以将第一层504形成到基座508。
现在转向图6,其根据说明性实施例示出了具有第一弯曲形状的第一层和成型设备的图示说明。如所示出的,第一层504已经被形成到基座508。在图5中第一模用冲头506沿箭头516的方向向基座508的运动已经改变了第一层504的形状。如所示出的,第一层504具有第一弯曲形状602。第一层504接触第一部分510和第二部分512并延伸入间隙514。
现在转向图7,其根据说明性实施例示出了第二层、具有第一弯曲形状的第一层和成型设备的图示说明。如所示出的,制造环境500包括成型设备502、第一层504和第二层702。在该示例中,成型设备502包括基座508和第二模用冲头704。如所示出的第一层被形成到基座508,并且具有长度706的第二层702相对于第一层504被放置。
第二层702可以由复合材料形成。在其中第二层702由复合材料形成的说明性示例中,第二层702也可以被称为第二复合材料层。第二层702的长度706小于图5中第一层504的长度505。此外,第二模用冲头704的形状不同于图5中第一模用冲头506的形状。
为了形成复合材料填料,第二模用冲头704可以沿箭头516的方向向基座508移动。在该示例中,第二模用冲头704接触第二层702并沿箭头516的方向将负荷施加在第二层702上。通过向基座508移动第二模用冲头704,成型设备502可以改变第二层702的形状。具体地,通过向基座508移动第二模用冲头704,成型设备502可以将第二层702形成到第一层504。
现在转向图8,其根据说明性实施例示出了具有第一弯曲形状的第一层、具有第二弯曲形状的第二层和成型设备的图示说明。如所示出的,第二层702已经被形成到基座508上的第一层504。第二层702具有第二弯曲形状802。如由图8可见,第二弯曲形状802不同于第一弯曲形状602使得第二层702被形成到第一层504。
现在转向图9,其根据说明性实施例示出了具有各自的弯曲形状的多个层和成型设备的图示说明。如所示出的,复合材料填料900被形成到基座508。复合材料填料900由多个层901组成。多个层901包含第一层504、第二层702、第三层902、第四层904、第五层906、第六层908、第七层910、第八层912、第九层914、第十层916、第十一层918和第十二层920。多个层901中的每一层包含各自的弯曲形状922。各自的弯曲形状922包含分别来自图6和图8的第一弯曲形状602和第二弯曲形状802。
多个层901中的每一层可以通过具有不同形状的多个连续模用冲头形成各自的弯曲形状922。在一些说明性示例中,多个模用冲头中的每一个模用冲头可以具有各自不同的弯曲形状以形成多个层901中的每一个连续层。在另一些说明性示例中,多个模用冲头中的一个模用冲头可以被用于形成多个层901的不止一层。在一种说明性示例中,多个模用冲头中的一个模用冲头可以被用于形成多个层901中的两个连续层。
图10-图15是可以被用于将多个层成形为弯曲形状的模用冲头的图示说明。首先转向图10,其根据说明性实施例示出了第一模用冲头的图示说明。第一模用冲头1000可以是来自图5的第一模用冲头506的示例。第一模用冲头1000可以被用于形成诸如图5的第一层504的复合材料层。
第一模用冲头1000具有成形部分1001和基座1003。成形部分1001具有高度1002、横截面1004和角度1006。
现在转向图11,其根据说明性实施例示出了第二模用冲头的图示说明。第二模用冲头1100可以是来自图7的第二模用冲头704的示例。第二模用冲头1100可以被用于形成诸如图7的第二层702的复合材料层。
第二模用冲头1100具有成形部分1101和基座1103。成形部分1101具有高度1102、横截面1104和角度1106。如由图10和图11可见,高度1102小于第一模用冲头1000的高度1002。
现在转向图12,其根据说明性实施例示出了第三模用冲头的图示说明。第三模用冲头1200可以是在使用第二模用冲头1100形成复合材料层之后在连续复合材料层上使用的连续模用冲头的示例。第三模用冲头1200可以被用于形成诸如图9的第三层702的复合材料层。
第三模用冲头1200具有成形部分1201和基座1203。成形部分1201具有高度1202、横截面1204和角度1206。如由图10-图12可见,高度1202分别小于第二模用冲头1100和第一模用冲头1000的高度1102和高度1002二者。
现在转向图13,其根据说明性实施例示出了第四模用冲头的图示说明。第四模用冲头1300可以是在使用图12中的第三模用冲头1200形成复合材料层之后在连续复合材料层上使用的连续模用冲头的示例。第四模用冲头1300可以被用于形成诸如图9的第四层904的复合材料层。
第四模用冲头1300具有成形部分1301和基座1303。成形部分1301具有高度1302、横截面1304和角度1306。如由图10-图13可见,高度1302分别小于第三模用冲头1200、第二模用冲头1100和第一模用冲头1000的高度1202、高度1102和高度1002。
现在转向图14,其根据说明性实施例示出了第五模用冲头的图示说明。第五模用冲头1400可以是在使用图13中的第四模用冲头1300形成复合材料层之后在连续复合材料层上使用的连续模用冲头的示例。第五模用冲头1400可以被用于形成诸如图9的第五层906的复合材料层。
第五模用冲头1400具有成形部分1401和基座1403。成形部分1401具有高度1402、横截面1404和角度1406。如由图10-图14可见,高度1402分别小于第四模用冲头1300、第三模用冲头1200、第二模用冲头1100和第一模用冲头1000的高度1302、高度1202、高度1102和高度1002。
现在转向图15,其根据说明性实施例示出了第六模用冲头的图示说明。第六模用冲头1500可以是在使用图14中的第五模用冲头1400形成复合材料层之后在连续复合材料层上使用的连续模用冲头的示例。第六模用冲头1500可以被用于形成诸如图9的第六层908的复合材料层。
第六模用冲头1500具有成形部分1501和基座1503。成形部分1501具有高度1502、横截面1504和角度1506。如由图10-图15可见,高度1502分别小于第五模用冲头1400、第四模用冲头1300、第三模用冲头1200、第二模用冲头1100和第一模用冲头1000的高度1402、高度1302、高度1202、高度1102和高度1002。
图5-图15中的模用冲头和成型设备的图示说明并不意味着暗示对说明性实施例可以被实施的方式的物理或架构限制。图10-图15中的模用冲头提供了模用冲头的形状的一些非限制性示例。进一步地,尽管所示出的基座508包括第一部分510、第二部分512和间隙514,但是在一些说明性示例中,成型设备502可以包含不同于所示出的那些的配置。基座508只是基座的一种非限制性示例,诸如以下图17的基座1758。
现在转向图16,其根据说明性实施例示出用于形成复合材料填料的过程的流程图的图示说明。图16中所图示说明的过程可以在制造环境(诸如图5的制造环境500)中被实施以形成复合材料填料(诸如图4的复合材料填料400)。例如,可以使用图5的成型设备502实施该过程的操作。
该过程可以通过将复合材料的层铺放在成型工具上开始(操作1602)。在一些说明性示例中,复合材料的层中的至少一层包含复合材料的多个铺层。在一些说明性示例中,复合材料的每个连续层具有比复合材料的先前层的宽度短的宽度。例如,在图4中,多个层402的每一层具有连续地较短的宽度。
该过程然后可以在层中的每一层中形成各自的弯曲以在成型工具上形成包含弯曲层的复合材料填料(操作1604)。在一些说明性示例中,在将连续层铺放在复合材料的层中之前,复合材料的层中的每一层被铺放并且然后成形。形成连续层的说明性示例可以在图5-图8中了解。在一些说明性示例中,在层中的每一层中形成各自的弯曲包含在层中的每一层中单独地形成各自的弯曲。
在一些说明性示例中,在层中的每一层中形成各自的弯曲包含使用一系列的模用冲头,每个模用冲头具有各自的横截面和期望的角度以在层中的一层中形成各自的弯曲。图10-图15可以是模用冲头的示例,其中每个模用冲头具有各自的横截面和期望的角度。在一些说明性示例中,在层中的每一层中形成各自的弯曲形成了复合材料填料的第一边和第二边。如由图4可见,多个层402的第一层404可以形成复合材料填料400的第一边430和第二边432。
该过程然后可以将挤压的复合材料添加至复合材料填料(操作1606)。在使用复合材料填料之前,该挤压的复合材料可以被可选地添加至复合材料填料。
该过程然后可以将包含弯曲层的复合材料填料放入由至少一个复合材料结构形成的间隙中(操作1608),且其后该过程结束。在一些说明性示例中,复合材料填料的横截面是大体三角形。例如,复合材料填料400的横截面是大体三角形。在一些说明性示例中,所述至少一个复合材料结构包含复合材料纵梁。
不同的所示出的实施例中的流程图和框图说明了在说明性实施例中的装置和方法的一些可能实施方式的架构、功能和操作。就这一点而言,流程图或框图中的每个框可以代表模块、段(segment)、功能和/或操作或步骤的一部分。
在说明性实施例的一些可替代实施方式中,在框中注解的一种或多种功能可以不按照图中注解的顺序发生。例如,在一些情况中,连续地示出的两个框可以基本同时地执行,或框可以有时以相反的顺序执行,这取决于所涉及的功能。除了在流程图或框图中所说明的框以外,还可以添加其他的框。进一步地,一些框可以不被实施。例如,操作1606可以不被执行。在该示例中,复合材料填料不包括任选的挤压材料。
现在转向图17,其根据说明性实施例示出制造环境的框图的图示说明。图5中的制造环境500是在图17中以框图的形式示出的制造环境1700的物理实施方式的示例。
制造环境1700包含复合材料填料1702、成型设备1704、复合材料1706和切割机1708。复合材料填料1702可以被配置为被放置在由复合材料结构1712、复合材料结构1714和复合材料蒙皮1716形成的间隙1710中。
复合材料填料1702由多个层1718形成。多个层1718可以由复合材料1706形成。在其中多个层1718由复合材料1706形成的说明性示例中,多个层1718也可以被称为多个复合材料层。多个层1718具有各自的弯曲形状1720。多个层1718具有多个宽度1722。具体地,每个连续层在多个层1718中可以具有比每个先前层小的宽度。
第一层1724具有第一宽度1726和第一弯曲形状1728。第一宽度1726可以是多个层1718中最宽的。第一弯曲形状1728可以具有多个层1718的各自的弯曲形状1720的最尖锐的角度。
第二层1730可以被形成在第一层1724上。第二层1730具有第二宽度1732和第二弯曲形状1734。第二宽度1732可以小于第一层1724的第一宽度1726。第二宽度1732可以比多个层1718中的其余层宽。第二弯曲形状1734可以具有比第一弯曲形状1728宽的角度。
第三层1736可以被形成在第二层1730上。第三层1736具有第三宽度1738和第三弯曲形状1740。第三宽度1738可以小于第一宽度1726和第二宽度1732。第三弯曲形状1740可以具有比第二弯曲形状1734宽的角度。
复合材料填料1702具有横截面1742。横截面1742可以被配置为适合在间隙1710的横截面1743内。在一些说明性示例中,横截面1742可以是大体三角形1744。大体三角形1744的横截面1742具有第一边1746和第二边1748。复合材料填料1702的第一边1746可以接触复合材料结构1712。在一些说明性示例中,复合材料结构1712可以具有半径1750。在这些说明性示例中,复合材料填料1702的第一边1746可以遵循半径1750。
复合材料填料1702的第二边1748可以接触复合材料结构1714。在一些说明性示例中,复合材料结构1714可以具有半径1752。在这些说明性示例中,复合材料填料1702的第二边1748可以遵循半径1752。
当第一层1724具有第一弯曲形状1728时,第一层1724可以形成复合材料填料1702的第一边1746。当第一层1724具有第一弯曲形状1728时,第一层1724可以形成复合材料填料1702的第二边1748。
在一些说明性示例中,复合材料填料1702还可以包括挤压材料1754。挤压材料1754可以被放置在多个层1718的最后一层上。挤压材料1754和多个层1718形成复合材料填料1702的第三边1756。第三边1756可以接触复合材料蒙皮1716。
多个层1718可以由复合材料1706形成。复合材料1706可以采取带1755、条1757或其他期望的复合材料的形式。可以使用切割机1708将复合材料1706切成多种宽度1722。
复合材料填料1702可以使用成型设备1704由复合材料1706形成。成型设备1704可以包括基座1758和多种模具1760。来自图10-图15的第一模用冲头1000、第二模用冲头1100、第三模用冲头1200、第四模用冲头1300、第五模用冲头1400和第六模用冲头1500可以是多种模具1760的物理实施例。多种模具1760具有多种横截面1762。多种模具1760中的每一种可以被用于形成多个层1718中的单独的层。多种横截面1762中的每一种可以形成多个层1718的各自的弯曲形状1720。
在一些说明性示例中,成型设备1704可以包括多种滚筒1764而不是多种模具1760。在这些说明性示例中,多种滚筒1764可以形成多个层1718的各自的弯曲形状1720。
当多个层1718遵循复合材料结构的半径时,复合材料填料1702可以具有增加的拉脱强度。通过遵循复合材料结构的半径,复合材料填料可以沿着半径引导负荷。
图17中的制造环境1700的图示说明并不意味着暗示对说明性实施例可以被实施的方式的物理或架构限制。除了或替代所说明的部件之外,另一些部件可以被使用。一些部件可以是不必要的。同样,框被用来说明一些功能部件。当在说明性实施例中实施时,这些框中的一个或更多个可以被组合、拆分或组合和拆分成不同的框。
例如,制造环境1700可以不包括复合材料结构1714。在该示例中,复合材料结构1712和复合材料蒙皮1716可以形成间隙1710。
本公开的说明性实施例可以在如图18所示的飞行器制造和使用方法1800以及图19所示的飞行器1900的背景下被描述。首先转向图18,其根据说明性实施例示出了飞行器制造和使用方法的框图的图示说明。在预生产期间,飞行器制造和使用方法1800可以包括图19中的飞行器1900的规格和设计1802和材料采购1804。
在生产期间,进行图19中的飞行器1900的部件和子组件制造1806和***整合1808。然后,图19中的飞行器1900可以经过认证和交付1810以便投入使用1812。在由顾客使用1812中,图19中的飞行器1900被安排日常维护和维修1814,这可以包括改进、重构、翻新以及其他维护或维修。
飞行器制造和使用方法1800的步骤中的每一个可以由***集成商、第三方和/或操作者完成或执行。在这些示例中,操作者可以是顾客。为了本描述的目的,***集成商可以包括但不限于任意数量的飞行器制造者和主***分包商;第三方包括可以包括但不限于任意数量的销售商、分包商和供应商;并且操作者可以是航空公司、租赁公司、军事实体、服务组织等。
现在参考图19,其示出了在其中可以实施说明性实施例的飞行器的框图的图示说明。在该示例中,飞行器1900由图18中的飞行器制造和使用方法1800生产并且可以包括具有多个***1904的机身1902和内部1906。***1904的示例包括推进***1908、电气***1910、液压***1912和环境***1919中的一个或更多个。还可以包括任意数量的其他***。尽管示出的是航空航天示例,但是不同的说明性实施例可以被应用于其他工业,诸如汽车工业。
本文所体现装置和方法可以在图18中的飞行器制造和使用方法1800中的至少一个阶段期间使用。在部件和子组件制造1806期间可以使用一种或更多种说明性实施例。例如,在部件和子组件制造1806期间可以使用图17中的复合材料填料1702。进一步地,在维护和维修1814期间也可以使用复合材料填料1702执行替换。
本公开提供了用于形成复合材料填料的方法。复合材料的层被铺放在成型工具上。各自的弯曲在层中的每一层中形成以在成型工具上形成包含弯曲层的复合材料填料。包含弯曲层的复合材料填料被放入由至少一个复合材料结构形成的间隙中。
与当前使用的复合材料填料相比,复合材料填料可以具有增加的拉脱强度。在一些示例中,多个层可以遵循复合材料结构的半径。通过遵循复合材料结构的半径,复合材料填料可以沿着半径引导负荷。
复合材料填料的第一层可以形成复合材料填料的第一边和第二边。第一层可以接触至少一个复合材料结构。多个层可以形成第三边。第三边可以接触复合材料蒙皮。
为了说明和描述的目的,已经提出了不同的说明性实施例的描述,并且并不试图以公开的形式穷尽或限制于所述实施例。许多修改和变体对本领域的普通技术人员将是显而易见的。进一步地,与另一些说明性实施例相比,不同的说明性实施例可以提供不同的特征。所选定的一个或多个实施例被选择和描述以便最好地解释实施例的原则、实际应用,并使得本领域的其他普通技术人员能够理解具有各种修改的各种实施例的公开,其适合预期的特定应用。进一步地,本公开包含根据以下条款的实施例:
条款1:一种形成复合材料填料的方法,所述方法包含:
将复合材料的层铺放在成型工具上;
在层中的每一层中形成各自的弯曲以在成型工具上形成包含弯曲层的复合材料填料;以及
将包含弯曲层的复合材料填料放入由至少一个复合材料结构形成的间隙中。
条款2:根据条款1所述的方法,其中将连续层铺放在复合材料的层中之前,复合材料的层中的每一层被铺放并且然后被成形。
条款3:根据条款1所述的方法,其中在层中的每一层中形成各自的弯曲包含在层中的每一层中单独地形成各自的弯曲。
条款4:根据条款1所述的方法,其中在层中的每一层中形成各自的弯曲包含使用一系列的模用冲头,每个模用冲头具有各自的横截面和期望的角度以在层中的一层中形成各自的弯曲。
条款5:根据条款1所述的方法,其中复合材料的层中的至少一层包含复合材料的多个铺层。
条款6:根据条款1所述的方法,还包含:
在将复合材料填料放入间隙之前,将挤压的复合材料添加至复合材料填料。
条款7:根据条款1所述的方法,其中复合材料填料的横截面是大体三角形。
条款8:根据条款1所述的方法,其中复合材料的每个连续层具有比复合材料的先前层的宽度短的宽度。
条款9:根据条款1所述的方法,其中在层中的每一层中形成各自的弯曲形成了复合材料填料的第一边和第二边。
条款10:一种复合材料填料,其包含:
具有第一弯曲形状的第一层;和
具有第二弯曲形状的第二层。
条款11:根据条款10所述的复合材料填料,还包含:
具有第三弯曲形状的第三层。
条款12:根据条款10所述的复合材料填料,还包含:
挤压的复合材料。
条款13:根据条款10所述的复合材料填料,其中复合材料填料具有大体三角形横截面。
条款14:根据条款13所述的复合材料填料,其中第一弯曲形状大体遵循复合材料填料的大体三角形横截面。
条款15:根据条款13所述的复合材料填料,其中第一层形成复合材料填料的大体三角形横截面的第一边和第二边。
条款16:根据条款10所述的复合材料填料,其中第一层和第二层中的至少一层包含复合材料的多个铺层。
条款17:一种复合材料填料,其包含:
多个复合材料层,每个复合材料层具有各自的弯曲形状。
条款18:根据条款17所述的复合材料填料,还包含:
挤压的复合材料。
条款19:根据条款17所述的复合材料填料,其中复合材料填料具有大体三角形横截面。
条款20:根据条款19所述的复合材料填料,其中多个复合材料层中的第一复合材料层形成了复合材料填料的大体三角形横截面的第一边和第二边。
Claims (13)
1.一种形成复合材料填料的方法,所述方法包含:
将复合材料的第一层铺放在成型工具上;
通过使用第一模用冲头抵靠所述成型工具按压所述第一层在所述第一层中形成弯曲;
针对所述复合材料的额外连续层使用连续较小模用冲头重复所述铺放步骤和形成步骤以在所述成型工具上形成包含弯曲复合层的复合材料填料,每个所述连续层中的相应弯曲通过利用所述较小模用冲头中的相应一个来按压而形成;以及
将所述复合材料填料从所述成型工具转移到由至少一个复合材料结构形成的间隙中。
2.根据权利要求1所述的方法,其中每个连续的模用冲头具有不同的横截面和不同的角度,从而在所述连续层中的相应一层中形成相应的弯曲。
3.根据权利要求1所述的方法,其中所述连续层中的至少一层包含复合材料的多个铺层。
4.根据权利要求1所述的方法,还包含:
在将所述复合材料填料放入所述间隙之前,将挤压的复合材料添加至由最后的连续层的弯曲所形成的打开空间内。
5.根据权利要求1所述的方法,其中所述复合材料填料的横截面是大体三角形。
6.根据权利要求1所述的方法,其中复合材料的每个连续层具有比所述复合材料的先前层的宽度短的宽度。
7.根据权利要求1所述的方法,其中在所述第一层和所述连续层中的每一个内的弯曲形成分别与所述复合材料填料的第一边和第二边平行的成角度的第一层边和第二层边。
8.一种通过根据权利要求1-7中的任一项所述的方法形成的复合材料填料,其包含:
具有第一弯曲形状的第一层;和
具有第二弯曲形状的第二层。
9.根据权利要求8所述的复合材料填料,还包含:
具有第三弯曲形状的第三层。
10.根据权利要求8所述的复合材料填料,还包含:
挤压的复合材料。
11.根据权利要求8所述的复合材料填料,其中所述复合材料填料具有大体三角形横截面。
12.根据权利要求11所述的复合材料填料,其中所述第一弯曲形状大体遵循所述复合材料填料的所述大体三角形横截面。
13.根据权利要求11所述的复合材料填料,其中所述第一层形成所述复合材料填料的所述大体三角形横截面的第一边和第二边。
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