CN109605774A - 纤维复合构件及其制造方法以及机翼结构 - Google Patents

纤维复合构件及其制造方法以及机翼结构 Download PDF

Info

Publication number
CN109605774A
CN109605774A CN201811139788.9A CN201811139788A CN109605774A CN 109605774 A CN109605774 A CN 109605774A CN 201811139788 A CN201811139788 A CN 201811139788A CN 109605774 A CN109605774 A CN 109605774A
Authority
CN
China
Prior art keywords
contact pin
fiber composite
fibre
flange
finished product
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201811139788.9A
Other languages
English (en)
Inventor
曼努埃尔·云格
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.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
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 Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of CN109605774A publication Critical patent/CN109605774A/zh
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • 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
    • B29C65/52—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 way of applying the adhesive
    • B29C65/54—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 way of applying the adhesive between pre-assembled parts
    • 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
    • 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
    • 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
    • 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
    • B29C66/1312—Single flange to flange joints, the parts to be joined being rigid
    • 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • 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
    • B29C70/34—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
    • 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
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
    • 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
    • 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
    • B29D99/0007—Producing profiled members, e.g. beams having a variable cross-section
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/182—Stringers, longerons
    • 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
    • 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
    • B29C65/481—Non-reactive adhesives, e.g. physically hardening adhesives
    • B29C65/4815—Hot melt adhesives, e.g. thermoplastic adhesives
    • 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
    • B29C65/52—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 way of applying the adhesive
    • B29C65/54—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 way of applying the adhesive between pre-assembled parts
    • B29C65/546—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 way of applying the adhesive between pre-assembled parts by gravity, e.g. by pouring
    • 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
    • B29C66/52—Joining tubular articles, bars or profiled elements
    • B29C66/524—Joining profiled elements
    • B29C66/5241—Joining profiled elements for forming coaxial connections, i.e. the profiled elements to be joined forming a zero angle relative to each other
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • 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
    • B29C66/54—Joining several hollow-preforms, e.g. half-shells, to form hollow articles, e.g. for making balls, containers; Joining several hollow-preforms, e.g. half-cylinders, to form 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
    • 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
    • B29C66/73—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
    • B29C66/7392—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 thermoplastic
    • B29C66/73921—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 thermoplastic characterised by the materials of both parts being thermoplastics
    • 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
    • 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
    • B29C70/36—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 impregnating by casting, e.g. vacuum casting
    • 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
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
    • 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
    • B29L2031/001—Profiled members, e.g. beams, sections
    • B29L2031/003—Profiled members, e.g. beams, sections having a profiled transverse cross-section
    • 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
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B29L2031/3085—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • 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.]
    • Y10T428/24174—Structurally defined web or sheet [e.g., overall dimension, etc.] including sheet or component perpendicular to plane of web or sheet
    • Y10T428/24182—Inward from edge of web or sheet

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Textile Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Woven Fabrics (AREA)

Abstract

本发明涉及一种纤维复合构件，具有：第一纤维复合元件，该第一纤维复合元件沿着该纤维复合构件的横轴弯曲，使得该第一纤维复合元件依次具有第一基座凸缘、第一接片区段、第一头部凸缘和第一增强接片；以及第二纤维复合元件，该第二纤维复合元件沿着该横轴弯曲，使得该第二纤维复合元件依次具有第二基座凸缘、第二接片区段、第二头部凸缘和第二增强接片；其中该第一基座凸缘和第一头部凸缘彼此平行地安排，该第一接片区段相对于该第一基座凸缘和该第一头部凸缘分别成角度地安排，该第一增强接片相对于该第一头部凸缘成直角地安排；该第一增强接片和该第二增强接片沿着该纤维复合构件的纵轴彼此重合地安排并且彼此相连。

Description

纤维复合构件及其制造方法以及机翼结构
技术领域
本发明涉及一种尤其用在航空航天器结构中的纤维复合构件、一种用于制造此类纤维复合构件的方法以及一种具有此类纤维复合构件的机翼结构。
背景技术
在航空航天技术中通常由纤维复合材料来制造用于航空航天器的构件。此类纤维复合构件具有与实心材料形成的构件相当的材料特性同时只有几分之一的重量。为了进一步改善壳状构件(例如机身或机翼外壳)的机械特性，使用了附加的桁条，这些桁条应提高外壳在纵向上的强度。
对于这些桁条，优选使用所谓的欧米茄形桁条(Omega-Stringer)，因为与替代性地同样已知的T形桁条相比它们一般具有更高强度。此类欧米茄形桁条以及其制造方法例如在DE 10 2008 032 834 B4中描述。
欧米茄形桁条对于纤维复合构件而言具有相当复杂的结构并且相对应地在其制造中也是复杂的。尤其是对于希望沿着桁条的长度有变化的强度的情况(如在机翼结构中尤其是这种情况)，其实现可能性至今一直受到限制。为此必须进行纤维复合材料的复杂的成型过程，或者设置附加的纤维复合材料。
发明内容
在此背景下，本发明的基本目的是提供用于航空航天器构造的更好的桁条，该桁条即使在对其强度特性有复杂要求的情况下也能更简单地进行制造。
根据本发明，这个目的通过一种纤维复合构件、一种方法以及一种机翼结构来实现。
据此提供了一种纤维复合构件。该纤维复合构件包括：第一纤维复合元件，该第一纤维复合元件沿着该纤维复合构件的横轴弯曲，使得该第一纤维复合元件依次具有第一基座凸缘、第一接片区段、第一头部凸缘和第一增强接片；以及第二纤维复合元件，该第二纤维复合元件沿着该横轴弯曲，使得该第二纤维复合元件依次具有第二基座凸缘、第二接片区段、第二头部凸缘和第二增强接片；其中该第一基座凸缘和第一头部凸缘彼此平行地安排，该第一接片区段相对于该第一基座凸缘和该第一头部凸缘分别成角度地安排，该第一增强接片相对于该第一头部凸缘成直角地安排，该第二基座凸缘和该第二头部凸缘彼此平行地安排，该第二接片区段相对于该第二基座凸缘和该第二头部凸缘分别成角度地安排，该第二增强接片相对于该第二头部凸缘成直角地安排，并且该第一增强接片和该第二增强接片沿着该纤维复合构件的纵轴彼此重合地安排并且彼此相连。
此外，提出了一种用于制造纤维复合构件的方法。该方法包括成型第一纤维复合半成品，使得该第一纤维复合半成品沿着第一横轴依次具有第一基座凸缘、第一接片区段、第一头部凸缘和第一增强接片，其中该第一基座凸缘和第一头部凸缘彼此平行地安排，该第一接片区段相对于该第一基座凸缘和该第一头部凸缘分别成角度地安排，并且该第一增强接片相对于该第一头部凸缘成直角地安排；成型第二纤维复合半成品，使得该第二纤维复合半成品沿着第二横轴依次具有第二基座凸缘、第二接片区段、第二头部凸缘和第二增强接片，其中该第二基座凸缘和第二头部凸缘彼此平行地安排，该第二接片区段相对于该第二基座凸缘和该第二头部凸缘分别成角度地安排，并且该第二增强接片相对于该第二头部凸缘成直角地安排；安排并固定该第一纤维复合半成品和该第二纤维复合半成品，使得该第一增强接片和该第二增强接片沿着一条共同的纵轴彼此重合地安排，沿着纤维取向将基质材料引入该第一纤维复合半成品和该第二纤维复合半成品中，以及固化该基质材料。
此外提出了一种用于飞行器的机翼结构。该机翼结构包括桁条，该桁条包括根据本发明的纤维复合构件。
在本发明的上下文中，纤维复合元件的单独的子区段准确地以其在本文中列出的顺序相对于彼此安排并且与其相应的相邻子区段相连。比如说，第一接片区段位于第一基座凸缘与第一头部凸缘之间并且分别与之相连。在相邻的子区段之间实际上还可以存在附加的任选区段(如果通过这个区段能够在所列出的本发明子区段之间分别限定连续的贯通的连接)。
本发明的基本构思在于，由两个单独的纤维复合元件来组合成在其他情况下基本上具有欧米茄形轮廓的一个纤维复合构件。这允许形成腔室状的结构，通过该结构可以设定纤维复合构件的强度。然后可以通过单独纤维复合元件的初始形状来固定纤维复合构件的强度。纤维复合元件尤其可以在其组合之前被对应地加工，这可以实现纤维复合构件的简化的制造。
有利的构型和改进方案从下文以及从参考附图的说明得出。
根据一个改进方案，该第一增强接片和该第二增强接片可以分别具有沿着该纵轴变化的宽度。
这允许以特别简单的方法沿着纵轴调节纤维复合构件的强度。此外，纤维复合构件的欧米茄形轮廓可以沿着纵轴保持不变，在用芯填充纤维复合构件以额外地进行增强时这是特别有利的。
根据另一个实施例，该第一纤维复合元件和该第二纤维复合元件可以相对于该纤维复合构件的沿着该纵轴延伸的中央平面形成为相对彼此镜面对称。这简化了纤维复合构件的制造，因为这两个纤维复合元件能够以相同的方式并且通过相同的手段来提供。
根据一个改进方案，该第一纤维复合元件和该第二纤维复合元件可以成型为，使得该第一接片区段和该第二接片区段分别具有沿着该纵轴变化的宽度。这允许纤维复合构件的节省空间并节省材料的设计，这对于在机翼结构中的应用可能是特别令人希望的，因为在其中存在对纤维复合构件的体积和重量的特殊限制。
根据另一个实施例，该第一接片区段与该第一基座凸缘或第一头部凸缘之间的角度以及该第二接片区段与该第二基座凸缘或第二头部凸缘之间的角度分别具有在95°与115°之间的值。这能够实现纤维复合构件的欧米茄形轮廓的接近直角的设计，进而对应于纤维复合构件的特别节省空间的设计形式。
根据一个改进方案，纤维复合构件可以在该第一增强接片和该第二增强接片的区域中包括第三纤维复合元件。这个第三纤维复合元件用于进一步提高纤维复合构件的强度。然后，可以预先以标准形状制造第一和第二纤维复合元件，而无论纤维复合构件的最终希望的强度如何。
根据另一个实施例，该第三纤维复合元件可以安排在该第一增强接片与该第二增强接片之间并且分别与之相连。这是将第三纤维复合元件整合到纤维复合构件中的一种特别简单的实现方式。
根据一个改进方案，该第三纤维复合元件可以具有沿着该纵轴变化的厚度。由此，第三纤维复合元件可以有助于调节纤维复合构件的强度。此类的基本上无弯曲的纤维复合元件此外还可以简单地制造为具有变化的厚度。
当然，纤维复合构件的所有设计也都可以转移到用于制造该纤维复合构件的方法上并且反之亦然。
上面的构型和改进方案在有意义的情况下可以任意地彼此组合。本发明的其他可行的构型、改进方案和实现方式还包括本发明的先前或随后参照实施例描述的特征的没有明确提及的组合。在此，本领域技术人员尤其还可将单独的方面作为改进内容或补充内容添加到本发明的相应的基础形式中。
附图说明
下面借助于在示意性附图中给出的实施例来详细解说本发明。附图中示出：
图1a示出穿过根据本发明实施例的纤维复合构件的示意性横截面；
图1b示出来自图1a的实施例的示意性侧视图；
图2示出纤维复合构件的另一个实施例的示意性侧视图；
图3示出纤维复合构件的另一个实施例的示意性侧视图；
图4示出纤维复合构件的另一个实施例的示意性横截面；
图5a-c示出了用于制造纤维复合构件的方法的若干所选步骤的示意性图示；
图6示出用于制造纤维复合构件的示例性方法的示意性流程图。
附图应当提供对本发明实施方式的进一步理解。它们展示实施方式并用于与说明书相关地解说本发明的原理和概念。其他的实施方式和上述优点中的许多都从查看附图而得出。图中的元素并不一定是按相互比例显示的。
在附图中，相同的、功能相同的和以相同方式起作用的元件、特征和部件，只要没有另外详细说明，就相应地设置有相同的参考符号。
具体实施方式
在所示的实施例中，纤维复合构件和纤维复合元件以大部分直线的子区段示出，以便简化图示。然而实际上，此类纤维复合构件具有部分地非常复杂的弯曲。因此，在典型对于直线和平面来定义纤维复合构件的单独子区段及其相对彼此的几何关系的表述，对于本发明的应用范围而言对应地更广泛地来解释。
尤其术语“平行”应理解为，两个平面式和/或彼此局部至少简单弯曲的面在想象中以至少局部彼此相等间隔开的方式在空间中延伸。作为特别简单的例子，如具有平行延伸的柱体轴的两个柱体的罩面可以理解为在本发明意义上“平行”。
当在本发明的范围内描述纤维复合构件的两个子区段之间的角度时，由此不一定是指在连接点或连接轴处的准确角度。因为实际上在单独的子区段之间的过渡部通常可能是弯曲的并且浮动的，所以此类严格的解释是较为不便的。该角度而应指在描述单独子区段的回归平面之间的角度。
图1a示出穿过根据本发明实施例的纤维复合构件1的示意性横截面。虚线表示的纤维复合构件1的假想横轴X在此水平地延伸穿过该图。纤维复合构件1包括在此实施例中镜面对称形成的第一纤维复合元件10和第二纤维复合元件20。第一纤维复合元件10从左向右依次具有第一基座凸缘11、第一接片区段12、第一头部凸缘13和第一增强接片14。第二纤维复合元件20从右向左依次具有第二基座凸缘21、第二接片区段22、第二头部凸缘23和第二增强接片24。
第一基座凸缘11水平安排。第一基座凸缘11的右端与第一接片区段12的左端相连。在第一接片区段12与第一基座凸缘11之间的角度为约100°。第一接片区段12的右端与第一头部凸缘13的左端相连。第一头部凸缘13水平安排。第一头部凸缘13的右端与第一增强接片14的下端相连。第一增强接片14竖直安排。
第二基座凸缘21水平安排。第二基座凸缘21的左端与第二接片区段22的右端相连。在第二接片区段21与第二基座凸缘22之间的角度为约100°。第二接片区段22的左端与第二头部凸缘23的右端相连。第二头部凸缘23水平安排。第二头部凸缘23的左端与第二增强接片24的下端相连。第二增强接片24竖直安排。
出于清晰展示的原因，第一增强接片14和第二增强接片24展示为相对彼此间隔开。在实际的纤维复合构件1中，第一增强接片14和第二增强接片24彼此重合地相连。
如可以清晰地辨认出的，第一基座凸缘11、第一接片区段12、第一头部凸缘13、第二头部凸缘23、第二接片区段22和第二基座凸缘21构成典型的欧米茄形轮廓。第一增强接片14和第二增强接片24一起构成腔室形结构，该结构额外地增强纤维复合构件1。
图1b示出来自图1a的纤维复合构件1的示意性侧视图。在这个视图中，仅仅第二纤维复合元件20可见，尤其是第二接片区段22和第二增强接片24。纤维复合构件的假想的纵轴Y在此视图中水平延伸。第二增强接片24安排在第二接片区段22上。第二接片区段22和第二增强接片24均具有水平取向的直角的侧面轮廓。
在此情况下，纤维复合构件1的强度沿着纵轴Y是不变的。纤维复合构件1的这个实施例，由于其简单的几何形状，是特别容易制造的。
图2示出纤维复合构件1的另一个实施例的示意性侧视图。在此展示的实施例与在图1b中展示的实施例的区别在于，第二增强接片24具有沿着纵轴Y一直减小的宽度。第二增强接片24由此具有锥形的侧面轮廓。第二增强接片24的下边缘还是水平安排的。第二增强接片24的左边缘和右边缘形成为相对彼此平行，其中右边缘形成为比左边缘短。
在这个实施例中，纤维复合构件1的强度从左向右连续减小。这样的强度曲线例如在机翼结构中是有利的，其中在此种情况下，飞行器的机身安排在左侧并且机翼尖端安排在右侧。
图3示出纤维复合构件1的另一个实施例的示意性侧视图。此实施例与在图1b中展示的实施例的区别在于，第二接片区段22具有沿着纵轴Y一直减小的宽度。第二接片区段22由此具有锥形的侧面轮廓。第二接片区段22的下边缘还是水平安排的。第二接片区段的左边缘和右边缘形成为相对彼此平行，其中右边缘形成为比左边缘短。第二增强接片24具有沿着纵轴Y变化的宽度，由此第二增强接片24的上边缘具有持续的弯曲。
在图3中展示的纤维复合构件1需要的材料总量少于在图1b和图2中展示的实施例。此外，纤维复合构件1的强度被调节为，使得强度在纤维复合构件1的左半部中变化比在右半部中缓慢。这样的强度曲线通过来自现有技术的已知方法很难实现，但是通过由第一增强接片14和第二增强接片24的强度调节可以在没有较大问题的情况下实施。
图4示出纤维复合构件1的另一个实施例的示意性横截面。在此展示的纤维复合构件1与在图1a中展示的纤维复合构件的区别在于第三纤维复合元件30，该第三纤维复合元件安排在第一增强接片14与第二增强接片24之间。
在此为了清晰的图示，还展示了在第一增强接片14与第三纤维复合元件30之间以及在第三纤维复合元件30与第二增强接片24之间的间隔。在实际的纤维复合构件1中，这些组成部分是没有间隔地彼此相连的。
在图4中展示的纤维复合构件1具有比图1a中展示的纤维复合构件1更大的强度，因为第三纤维复合元件30额外地增强了纤维复合构件1。由此第一纤维复合元件10和第二纤维复合元件20能够使用构成具有不同强度的纤维复合构件1，其方式为对应地选择第三纤维复合元件30的厚度。在这个横截面视图中，第三纤维复合元件30沿着纵轴Y的厚度曲线是不可辨别的。第三纤维复合元件30可以沿着纵轴Y具有不变的厚度或者变化的厚度。
图5a至图5c示出了用于制造纤维复合构件的示例性方法的所选步骤。
图5a示出了在执行示例性方法之前对初始状态的示意性俯视图。可以看到第一纤维复合半成品100和第二纤维复合半成品200。第一纤维复合半成品100和第二纤维复合半成品200分别具有锥形的底部布局并且相对于共同的假想纵轴Y1形成为相对于彼此镜面对称。第一纤维复合半成品100在此安排在左侧，其中第一纤维复合半成品100的左边缘竖直取向并且下边缘和上边缘分别水平取向。上边缘在此比下边缘短并且第一纤维复合半成品100从下向上变窄。第二纤维复合半成品200与之对应对称地形成。任选的第三纤维复合半成品300安排在第一纤维复合半成品100和第二纤维复合半成品200之间的中部并且具有矩形的底部布局。
图5b示出了在第一纤维复合半成品100和第二纤维复合半成品200变形之后的示意性横截面视图。第一纤维复合半成品100沿着第一假想横轴X1从左向右依次具有第一基座凸缘110、第一接片区段120、第一头部凸缘130和第一增强接片140。第二纤维复合半成品200沿着第二假想横轴X2从右向左依次具有第二基座凸缘210、第二接片区段220、第二头部凸缘230和第二增强接片240。
第一基座凸缘110水平安排。第一基座凸缘110的右端与第一接片区段120的左端相连。在第一接片区段120与第一基座凸缘110之间的角度为约100°。第一接片区段120的右端与第一头部凸缘130的左端相连。第一头部凸缘130水平安排。第一头部凸缘130的右端与第一增强接片140的下端相连。第一增强接片140竖直安排。
第二基座凸缘210水平安排。第二基座凸缘210的左端与第二接片区段220的右端相连。在第二接片区段210与第二基座凸缘220之间的角度为约100°。第二接片区段220的左端与第二头部凸缘230的右端相连。第二头部凸缘230水平安排。第二头部凸缘230的左端与第二增强接片240的下端相连。第二增强接片240竖直安排。
任选的第三纤维复合半成品300竖直取向并且安排在第一增强接片140和第二增强接片240之间的中部。
图5c示出将基质材料500引入的示意性横截面视图。来自图5b的第一纤维复合半成品100和第二纤维复合半成品200在此安排为，使得第一增强接片140和第二增强接片240分别与任选的第三纤维复合半成品300相连。处于清晰性的原因，在此单独的组成部分再次以相对彼此的小间距展示。
将基质材料500沿着所示的箭头方向竖直向下引入纤维复合半成品中。在此特别有利的是，基质材料500可以单纯通过重力沿着纤维复合半成品的纤维取向扩展。与来自现有技术的方法(其中必须横向于纤维取向来引入基质材料)相比，如此有助于引入基质材料500。
图6示出用于制造纤维复合构件的示例性方法的示意性流程图。
在此，在一个方法步骤中，成型第一纤维复合半成品100，使得该第一纤维复合半成品沿着第一横轴X1依次具有第一基座凸缘110、第一接片区段120、第一头部凸缘130和第一增强接片140，其中第一基座凸缘110和第一头部凸缘130彼此平行地安排，第一接片区段120相对于第一基座凸缘110和第一头部凸缘130分别成角度地安排，并且第一增强接片140相对于第一头部凸缘130成直角地安排。
在一个后续的方法步骤中，成型第二纤维复合半成品200，使得该第二纤维复合半成品沿着第二横轴X2依次具有第二基座凸缘210、第二接片区段220、第二头部凸缘230和第二增强接片240，其中第二基座凸缘210和第二头部凸缘230彼此平行地安排，第二接片区段220相对于第二基座凸缘210和第二头部凸缘230分别成角度地安排，并且第二增强接片240相对于第二头部凸缘230成直角地安排。
在随后的方法步骤中，安排并固定第一纤维复合半成品100和第二纤维复合半成品200，使得第一增强接片140和第二增强接片240沿着一条共同的纵轴Y1彼此重合地安排。在此方法步骤中可以同时将任选的第三纤维复合半成品300安排并固定在第一增强接片140和第二增强接片的区域中。
然后进行如下方法步骤，其中沿着纤维取向将基质材料500引入第一纤维复合半成品100和第二纤维复合半成品200中。如果存在第三纤维复合半成品300，则在这个步骤中将基质材料500引入任选的第三纤维复合半成品300中。
然后进行另一个方法步骤，其中将基质材料500固化。
为了进行这样的方法，可以对应地使用所有已知用于制造纤维复合半成品的助剂和设备。本领域技术人员在此应毫无问题地看到，需要在何种程度上实际改变已有的助剂和设备以使其适合于进行在此描述的方法。
在图5a-5c以及图6中已经示出了或者至少指明了各个方法步骤的特定顺序。然而本发明不应以任何方式仅受限于方法步骤的这一种顺序。本领域技术人员可以明确看出，方法步骤的哪些顺序对于制造纤维复合构件是有意义的。尤其，第一纤维复合半成品100和第二纤维复合半成品200变形的方法步骤也可以按反转的顺序进行或者还可以同时进行。引入基质材料500以及固化基质材料500的方法步骤也可以在该方法过程中的任意时间点进行。于是例如可以设想的是，在将纤维复合半成品变形之前引入基质材料500、在变形之后固化、并且然后将经固化的纤维复合半成品彼此相连。
在此描述的纤维复合部件在其材料组成方面不受任何限制。所使用的纤维可以例如为碳纤维、芳族聚酰胺纤维、玻璃纤维、陶瓷纤维或所有其他已知的纤维。作为基质纤维可以提出所有可用的热固性聚合物、弹性体、热塑性塑料或类似物。
附图标记列表
1 纤维复合构件
10 第一纤维复合元件
11 第一基座凸缘
12 第一接片区段
13 第一头部凸缘
14 第一增强接片
20 第二纤维复合元件
21 第二基座凸缘
22 第二接片区段
23 第二头部凸缘
24 第二增强接片
30 第三纤维复合元件
100 第一纤维复合半成品
110 第一基座凸缘
120 第一接片区段
130 第一头部凸缘
140 第一增强接片
200 第二纤维复合半成品
210 第二基座凸缘
220 第二接片区段
230 第二头部凸缘
240 第二增强接片
300 第三纤维复合半成品
X 横轴
Y 纵轴
X1 第一横轴
X2 第二横轴
Y1 共同的纵轴

Claims (15)

1.一种纤维复合构件(1)，包括：
第一纤维复合元件(10)，该第一纤维复合元件沿着该纤维复合构件(1)的横轴(X)弯曲，使得该第一纤维复合元件依次具有第一基座凸缘(11)、第一接片区段(12)、第一头部凸缘(13)和第一增强接片(14)；以及第二纤维复合元件(20)，该第二纤维复合元件沿着该横轴(X)弯曲，使得该第二纤维复合元件依次具有第二基座凸缘(21)、第二接片区段(22)、第二头部凸缘(23)和第二增强接片(24)；其中该第一基座凸缘(11)和该第一头部凸缘(13)彼此平行地安排，
该第一接片区段(12)相对于该第一基座凸缘(11)和该第一头部凸缘(13)分别成角度地安排，该第一增强接片(14)相对于该第一头部凸缘(13)成直角地安排，
该第二基座凸缘(21)和该第二头部凸缘(23)彼此平行安排，
该第二接片区段(22)相对于该第二基座凸缘(21)和该第二头部凸缘(23)分别成角度地安排，该第二增强接片(24)相对于该第二头部凸缘(23)成直角地安排，并且
该第一增强接片(14)和该第二增强接片(24)沿着该纤维复合构件(1)的纵轴(Y)彼此重合地安排并且彼此相连。
2.根据权利要求1所述的纤维复合构件(1)，
其中该第一增强接片(14)和该第二增强接片(24)分别具有沿着该纵轴(Y)变化的宽度。
3.根据权利要求1或2之一所述的纤维复合构件(1)，
其中该第一纤维复合元件(10)和该第二纤维复合元件(20)相对于该纤维复合构件(1)的沿着该纵轴(Y)延伸的中央平面形成为相对彼此镜面对称。
4.根据以上权利要求之一所述的纤维复合构件，其中该第一纤维复合元件(10)和该第二纤维复合元件(20)成型为，使得该第一接片区段(12)和该第二接片区段(22)分别具有沿着该纵轴(Y)变化的宽度。
5.根据以上权利要求之一所述的纤维复合构件(1)，其中该第一接片区段(12)与该第一基座凸缘(11)或第一头部凸缘(13)之间的角度以及该第二接片区段(22)与该第二基座凸缘(21)或第二头部凸缘(23)之间的角度分别具有在95°与115°之间的值。
6.根据以上权利要求之一所述的纤维复合构件(1)，其中该纤维复合构件(1)在该第一增强接片(14)和该第二增强接片(24)的区域中包括第三纤维复合元件(30)。
7.根据权利要求6所述的纤维复合构件(1)，
其中该第三纤维复合元件(30)安排在该第一增强接片(14)与该第二增强接片(24)之间并且分别与这些增强接片相连。
8.根据权利要求6或7之一所述的纤维复合构件(1)，
该第三纤维复合元件(30)具有沿着该纵轴(Y)变化的厚度。
9.一种用于制造纤维复合构件(1)的方法，其中该方法包括以下步骤：
成型第一纤维复合半成品(100)，使得该第一纤维复合半成品沿着第一横轴(X1)依次具有第一基座凸缘(110)、第一接片区段(120)、第一头部凸缘(130)和第一增强接片(140)，其中该第一基座凸缘(110)和第一头部凸缘(130)彼此平行地安排，该第一接片区段(120)相对于该第一基座凸缘(110)和该第一头部凸缘(130)分别成角度地安排，并且该第一增强接片(140)相对于该第一头部凸缘(130)成直角地安排；
成型第二纤维复合半成品(200)，使得该第二纤维复合半成品沿着第二横轴(X2)依次具有第二基座凸缘(210)、第二接片区段(220)、第二头部凸缘(230)和第二增强接片(240)，其中该第二基座凸缘(210)和第二头部凸缘(230)彼此平行地安排，该第二接片区段(220)相对于该第二基座凸缘(210)和该第二头部凸缘(230)分别成角度地安排，并且该第二增强接片(240)相对于该第二头部凸缘(230)成直角地安排；
安排并固定该第一纤维复合半成品(100)和该第二纤维复合半成品(200)，使得该第一增强接片(140)和该第二增强接片(240)沿着一条共同的纵轴(Y1)彼此重合地安排，沿着纤维取向将基质材料(500)引入该第一纤维复合半成品(100)和该第二纤维复合半成品(200)中；以及
固化该基质材料(500)。
10.根据权利要求9所述的方法，
其中该第一增强接片(140)和该第二增强接片(240)分别具有沿着该共同的纵轴(Y1)变化的宽度。
11.根据权利要求9或10之一所述的方法，
其中该第一纤维复合半成品(100)和该第二纤维复合半成品(200)相对于该共同的纵轴(Y1)形成为相对彼此镜面对称。
12.根据权利要求9至11之一所述的方法，
其中该第一纤维复合半成品(100)和该第二纤维复合半成品(200)成型为，使得该第一接片区段(120)和该第二接片区段(220)分别具有沿着该共同的纵轴(Y1)变化的宽度。
13.根据权利要求9至12之一所述的方法，
其中该安排并固定的方法步骤另外包括在该第一增强接片(140)和该第二增强接片(240)的区域中安排并固定第三纤维复合半成品(300)。
14.根据权利要求13所述的方法，
其中该第三纤维复合半成品(300)具有沿着该共同的纵轴(Y1)变化的厚度。
15.一种用于航空航天器的具有桁条的机翼结构，该桁条具有根据权利要求1至8之一所述的纤维复合构件(1)。
CN201811139788.9A 2017-09-28 2018-09-28 纤维复合构件及其制造方法以及机翼结构 Pending CN109605774A (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017217339.4 2017-09-28
DE102017217339.4A DE102017217339A1 (de) 2017-09-28 2017-09-28 Faserverbundbauteil und Verfahren zu dessen Herstellung, sowie Flügelstruktur

Publications (1)

Publication Number Publication Date
CN109605774A true CN109605774A (zh) 2019-04-12

Family

ID=63708098

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201811139788.9A Pending CN109605774A (zh) 2017-09-28 2018-09-28 纤维复合构件及其制造方法以及机翼结构

Country Status (5)

Country Link
US (1) US10569476B2 (zh)
EP (1) EP3461629A1 (zh)
CN (1) CN109605774A (zh)
CA (1) CA3018236A1 (zh)
DE (1) DE102017217339A1 (zh)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11458677B2 (en) * 2019-12-26 2022-10-04 Industrial Technology Research Institute Selective laser sintering composition and selective laser sintering 3D printing method employing the same

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008001498B3 (de) * 2008-04-30 2009-08-27 Airbus Deutschland Gmbh Verfahren und Umformvorrichtung zur Herstellung eines Faserverbundbauteils für die Luft- und Raumfahrt
DE102008032834B4 (de) 2008-07-14 2013-08-08 Airbus Operations Gmbh Omega-Stringer zum Versteifen eines flächigen Bauteils und Verfahren zum Herstellen eines Faserverbundbauteils für Schalensegmente
EP2218911A1 (en) * 2009-02-12 2010-08-18 Deen Polyester Constructies B.V. Housing with a special connection assembly as well as a method for manufacturing such a housing.
FR2943944A1 (fr) * 2009-04-06 2010-10-08 Eads Europ Aeronautic Defence Procede de fabrication d'un panneau raidi en materiau composite a matrice thermoplastique et panneau ainsi obtenu

Also Published As

Publication number Publication date
CA3018236A1 (en) 2019-03-28
US20190099960A1 (en) 2019-04-04
US10569476B2 (en) 2020-02-25
EP3461629A1 (de) 2019-04-03
DE102017217339A1 (de) 2019-03-28

Similar Documents

Publication Publication Date Title
EP2933094B1 (en) Method of forming radius fillers for composite structures
CN101772452B (zh) 细长复合结构件及其改进
CN103895857A (zh) 加强桁条及其制造方法
CN103366070B (zh) 一种可用于直升机和固定翼飞行器的复合材料梁设计方法
EP3170587A3 (en) Fibre-reinforced metal component for an aircraft or spacecraft and production methods for fibre-reinforced metal components
CN109583052A (zh) 纤维增强陶瓷基复合材料微结构精确建模及模量计算方法
EP3052306B1 (de) Faserverbundwerkstoffbauteil und verfahren zur herstellung eines faserverbundwerkstoffbauteils
CN103648906B (zh) 纤维复合部件、小翼和具有纤维复合部件的飞行器
JP2011510859A (ja) 航空機や宇宙船における２つの異なる断面形状を有する２つの補強要素を連結するための連結構造体及び骨組み構造体
WO2009112694A3 (fr) Pièce structurale courbe en matériau composite et procède de fabrication d'une telle pièce
CN109605774A (zh) 纤维复合构件及其制造方法以及机翼结构
CN107472502A (zh) 航空器或航天器的结构的增强部件、航空器或航天器及方法
CN107548428A (zh) 包括带有加固件的平台的叶片
DE102012000564A1 (de) Urformwerkzeug und Verfahren für die Fertigung eines aus faserverstärktem Kunststoff bestehenden aerodynamisch geformten Luftfahrzeugbauteils
CN102395459B (zh) 用于为纤维复合材料的弯曲成形的结构部件覆盖针织纤维织物的设备和方法
HUE032174T2 (en) Corner fittings and process for making them
CA2537651A1 (en) Force-introduction point in core composites and method for producing said point using reinforcement elements that traverse the thickness of the core composite
CN107645984A (zh) 操纵面元件
RU2484319C1 (ru) Способ изготовления тяги из композитного материала
CN110344887B (zh) 混合材料风扇叶片及其制备方法
CN107922045A (zh) 一种用于飞机起落架的支柱
IT201900017420A1 (it) Metodo e attrezzo per la fabbricazione di un telaio in materiale composito di una finestra di un velivolo
CN110271680A (zh) 用于承载飞机动力装置的支柱的主要结构，其后部由一组连接杆形成
US20150001343A1 (en) Linking an aircraft fuselage member and a frame by a clip and a spacer
CN107972889B (zh) 一种高刚度高精度复合材料惯组安装结构

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
WD01 Invention patent application deemed withdrawn after publication
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20190412