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WO1996040551A1 - Poutre composite hybride possedant une ame en metal - Google Patents

Poutre composite hybride possedant une ame en metal Download PDF

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Publication number
WO1996040551A1
WO1996040551A1 PCT/US1996/009630 US9609630W WO9640551A1 WO 1996040551 A1 WO1996040551 A1 WO 1996040551A1 US 9609630 W US9609630 W US 9609630W WO 9640551 A1 WO9640551 A1 WO 9640551A1
Authority
WO
WIPO (PCT)
Prior art keywords
composite
susceptor
bondline
flange
weld
Prior art date
Application number
PCT/US1996/009630
Other languages
English (en)
Inventor
Brad L. Kirkwood
Michael M. Stepan
Paul J. Patt
Original Assignee
The Boeing Company
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
Priority claimed from US08/482,513 external-priority patent/US5829716A/en
Priority claimed from US08/473,910 external-priority patent/US5688426A/en
Priority claimed from US08/483,407 external-priority patent/US5556565A/en
Application filed by The Boeing Company filed Critical The Boeing Company
Priority to AU62637/96A priority Critical patent/AU6263796A/en
Publication of WO1996040551A1 publication Critical patent/WO1996040551A1/fr

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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
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/34—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
    • B29C65/36—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
    • B29C65/3604—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the type of elements heated by induction which remain in the joint
    • B29C65/364—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the type of elements heated by induction which remain in the joint being a woven or non-woven fabric or being a mesh
    • 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
    • B29C65/34—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
    • B29C65/36—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
    • B29C65/3604—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the type of elements heated by induction which remain in the joint
    • B29C65/3644—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the type of elements heated by induction which remain in the joint being a ribbon, band or strip
    • 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
    • B29C65/34—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
    • B29C65/36—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
    • B29C65/3672—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the composition of the elements heated by induction which remain in the joint
    • B29C65/3676—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the composition of the elements heated by induction which remain in the joint being metallic
    • 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
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B29C65/564—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined hidden in the joint, e.g. dowels or Z-pins
    • 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
    • B29C66/1122—Single lap to lap joints, i.e. overlap 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
    • B29C66/303—Particular design of joint configurations the joint involving an anchoring effect
    • B29C66/3034—Particular design of joint configurations the joint involving an anchoring effect making use of additional elements, e.g. meshes
    • B29C66/30341—Particular design of joint configurations the joint involving an anchoring effect making use of additional elements, e.g. meshes non-integral with the parts to be joined, e.g. making use of extra elements
    • 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
    • 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
    • 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
    • B29C66/5326—Joining single elements to the wall of tubular articles, hollow articles or bars said single elements being substantially flat
    • 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
    • B29C66/73—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
    • B29C66/737—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 state of the material of the parts to be joined
    • B29C66/7371—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 state of the material of the parts to be joined oriented or heat-shrinkable
    • B29C66/73711—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 state of the material of the parts to be joined oriented or heat-shrinkable oriented
    • 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
    • B29C66/737—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 state of the material of the parts to be joined
    • B29C66/7371—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 state of the material of the parts to be joined oriented or heat-shrinkable
    • B29C66/73711—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 state of the material of the parts to be joined oriented or heat-shrinkable oriented
    • B29C66/73712—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 state of the material of the parts to be joined oriented or heat-shrinkable oriented mono-axially
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/812—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the composition, by the structure, by the intensive physical properties or by the optical properties of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps
    • B29C66/8126—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the composition, by the structure, by the intensive physical properties or by the optical properties of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps characterised by the intensive physical properties or by the optical properties of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps
    • B29C66/81261—Thermal properties, e.g. thermal conductivity, thermal expansion coefficient
    • 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
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/814—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps
    • B29C66/8145—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the constructional aspects of the pressing elements, e.g. of the welding jaws or clamps
    • B29C66/81457—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the constructional aspects of the pressing elements, e.g. of the welding jaws or clamps comprising a block or layer of deformable material, e.g. sponge, foam, rubber
    • 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
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/818—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the cooling constructional aspects, or by the thermal or electrical insulating or conducting constructional aspects of the welding jaws or of the clamps ; comprising means for compensating for the thermal expansion of the welding jaws or of the clamps
    • B29C66/8181—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the cooling constructional aspects, or by the thermal or electrical insulating or conducting constructional aspects of the welding jaws or of the clamps ; comprising means for compensating for the thermal expansion of the welding jaws or of the clamps characterised by the cooling constructional aspects
    • B29C66/81811—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the cooling constructional aspects, or by the thermal or electrical insulating or conducting constructional aspects of the welding jaws or of the clamps ; comprising means for compensating for the thermal expansion of the welding jaws or of the clamps characterised by the cooling constructional aspects of the welding jaws
    • 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
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/818—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the cooling constructional aspects, or by the thermal or electrical insulating or conducting constructional aspects of the welding jaws or of the clamps ; comprising means for compensating for the thermal expansion of the welding jaws or of the clamps
    • B29C66/8182—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the cooling constructional aspects, or by the thermal or electrical insulating or conducting constructional aspects of the welding jaws or of the clamps ; comprising means for compensating for the thermal expansion of the welding jaws or of the clamps characterised by the thermal insulating constructional aspects
    • B29C66/81821—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the cooling constructional aspects, or by the thermal or electrical insulating or conducting constructional aspects of the welding jaws or of the clamps ; comprising means for compensating for the thermal expansion of the welding jaws or of the clamps characterised by the thermal insulating constructional aspects of the welding jaws
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/82—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps
    • B29C66/822—Transmission mechanisms
    • B29C66/8223—Worm or spindle mechanisms
    • 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
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/83—General aspects of machine operations or constructions and parts thereof characterised by the movement of the joining or pressing tools
    • B29C66/832—Reciprocating joining or pressing tools
    • B29C66/8322—Joining or pressing tools reciprocating along one axis
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    • E04C3/29—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces built-up from parts of different material, i.e. composite structures
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    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/34—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
    • B29C65/36—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
    • B29C65/3668—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the means for supplying heat to said heated elements which remain in the join, e.g. special induction coils
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    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/34—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
    • B29C65/36—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
    • B29C65/3672—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the composition of the elements heated by induction which remain in the joint
    • B29C65/3676—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the composition of the elements heated by induction which remain in the joint being metallic
    • B29C65/368—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the composition of the elements heated by induction which remain in the joint being metallic with a polymer coating
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    • 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
    • B29C66/731—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 intensive physical properties of the material of the parts to be joined
    • B29C66/7311—Thermal properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • 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
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    • 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
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    • B29C66/80—General aspects of machine operations or constructions and parts thereof
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    • B29C66/812—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the composition, by the structure, by the intensive physical properties or by the optical properties of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps
    • B29C66/8122—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the composition, by the structure, by the intensive physical properties or by the optical properties of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps characterised by the composition of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps
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    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the present invention relates to a hybrid composite stiffening element, particularly a titanium I or T section web with composite caps that are formed into flanges of the web.
  • Aircraft are expensive to manufacture because safety concerns dictate quality manufacture while weight limits range, performance, and payload. There are significant design challenges. Large aircraft are commonly made from aluminum alloys riveted and fastened together. The fasteners add significantly to the total weight. Military aircraft, especially fighters, are more and more being made from thermoset or thermoplastic materials for improved strength-to-weight ratios, but the construction still parrots metal construction with fasteners to join parts into assemblies. Military airplanes must satisfy even more requirements than commercial transport airplanes, such as the Congressionally-imposed "Live Fire" tests. Military airplanes also have unusual performance requirements. To obtain the desired performance, reducing the cost and weight of construction are two enviable objectives.
  • the present invention is a hybrid beam that combines metal with composites to marry the advantages each offers. This description will first discuss the problems of composite manufacturing before turning to a brief discussion of emerging solutions to address the cost and weight objectives where the beam of the present invention offers the greatest leverage. 1. Composite Manufacturing
  • Fiber-reinforced organic resin matrix composites have a high strength-to-weight ratio or a high stiffness-to-weight ratio and desirable fatigue characteristics that make them increasingly popular as a replacement for metal in aerospace applications where weight, strength, or fatigue is critical.
  • Organic resin composites be they thermoplastics or thermosets, are expensive today. Improved manufacturing processes would reduce touch labor and forming time.
  • Prepregs combine continuous, woven, or chopped reinforcing fibers with an uncured, matrix resin, and usually comprise fiber sheets with a thin film of the resin matrix.
  • Sheets of prepreg generally are placed (laid-up) by hand or with fiber placement machines directly upon a tool or die having a forming surface contoured to the desired shape of the completed part or are laid-up in a flat sheet which is then draped and formed over the tool or die to the contour of the tool. Then the resin in the prepreg lay up is consolidated (i.e. pressed to remove any air, gas, or vapor) and cured (i.e., chemically converted to its final form usually through chain-extension) in a vacuum bag process in an autoclave (i.e., a pressure oven) to complete the part.
  • an autoclave i.e., a pressure oven
  • the tools or dies for composite processing typically are formed to close dimensional tolerances. They are massive, must be heated along with the workpiece, and must be cooled prior to removing the completed part. The delay caused to heat and to cool the mass of the tools adds substantially to the overall time necessary to fabricate each part. These delays are especially significant when the manufacturing ran is low rate where the dies need to be changed frequently, often after producing only a few parts of each kind.
  • An autoclave has similar limitations; it is a batch operation.
  • the prepreg is laid-up to create a preform, which is bagged (if necessary), and placed between matched metal tools that include forming surfaces to define the internal, external, or both mold lines of the completed part.
  • the tools and composite preform are placed within a press and then the tools, press, and preform are heated.
  • the tooling in autoclave or hot press fabrication is a significant heat sink that consumes substantial energy. Furthermore, the tooling takes significant time to heat the composite material to its consolidation temperature and, after curing the composite, to cool to a temperature at which it is safe to remove the finished composite part.
  • Patent Application 08/341,779 a technique that readily and reliably seals facesheets of the retort without the need for welding and permits reuse of the facesheets in certain circumstances.
  • Our "bag-and-seal" technique applies to both resin composite and metal processing.
  • the dies or tooling for induction processing are cast ceramic because a ceramic is not susceptible to induction heating and, preferably, is a thermal insulator (i.e., a relatively poor conductor of heat).
  • Cast ceramic tooling is strengthened and reinforced internally, with fiberglass rods or other appropriate reinforcements and externally with metal or other durable strongbacks to permit it to withstand the temperatures and pressures necessary to form, to consolidate, or otherwise to process the composite materials or metals.
  • Cast ceramic tools cost less to fabricate than metal tools of comparable size and have less thermal mass than metal tooling, because they are unaffected by the induction field.
  • the ceramic tooling is not susceptible to induction heating, it is possible to embed induction heating elements in the ceramic tooling and to heat the composite or metal retort without significantly heating the tools.
  • the induction heating elements themselves connect to form a water cooling network.
  • induction heating can reduce the time required and energy consumed to fabricate a part.
  • Heating is by conduction from the retort to the workpiece.
  • Induction focuses heating on the retort (and workpiece) and eliminates wasteful, inefficient heat sinks. Because the ceramic tools in our induction-heating workcell do not heat to as high a temperature as the metal tooling of conventional, prior art presses, problems caused by different coefficients of thermal expansion between the tools and the workpiece are reduced.
  • thermoplastic orgamc matrix composite preform of PEEK or ULTEM for example, within a metal susceptor envelope (i.e., retort).
  • retort metal susceptor envelope
  • the susceptor facesheets of the retort are inductively heated to heat the preform.
  • consolidation and forming pressure to consolidate and, if applicable, to form the preform at its curing temperature.
  • the sealed susceptor sheets form a pressure zone.
  • the retort often includes three susceptor sheets sealed around their periphery to define two pressure zones.
  • the first pressure zone surrounds the composite panel/preform or metal workpiece and is evacuated and maintained under vacuum.
  • the second pressure zone is pressurized (i.e., flooded with gas) at the appropriate time and rate to help form the composite panel or workpiece.
  • the shared wall of the three layer sandwich that defines the two pressure zones acts as a diaphragm in this situation.
  • thermoplastic thermoset composite components at high speeds with minimum touch labor and little, if any, pretreatments.
  • the welding interlayer (comprising the susceptor and surrounding thermoplastic resin either coating the susceptor or sandwiching it) also can simultaneously take the place of shims required in mechanical fastening. As such, composite welding holds promise to be an affordable joining process.
  • thermoplastic and thermoset composite parts together, the resin that the susceptor melts functions as a hot melt adhesive. If fully realized, the
  • thermoplastic-thermoset bonding will further reduce the cost of composite assembly.
  • thermoplastic welding to refer to either bonding operation unless the context forces a different meaning.
  • U.S. Patent 4,673,450 describes a method to spot weld graphite fiber reinforced PEEK composites using a pair of electrodes After roughening the surfaces of the prefabricated PEEK composites in the region of the bond, Burke placed a PEEK adhesive ply along the bond line, applied a pressure of about 50 - 100 psi through the electrodes, and heated the embedded graphite fibers by applying a voltage in the range of 20 - 40 volts at 30 - 40 amps for approximately 5 - 10 seconds with the electrodes. Access to both sides of the assembly is required in this process which limits its application.
  • Thermoplastic welding is a process for forming a fusion bond between two faying thermoplastic faces of two parts.
  • a fusion bond is created when the thermoplastic on the surface of the two thermoplastic composite parts is heated to the melting or softening point and the two surfaces are brought into contact, so that the molten thermoplastic mixes, and the surfaces are held in contact while the thermoplastic cools below the softening temperature.
  • thermoplastic welding process sounds, and easy as it is to perform in the laboratory on small pieces, it becomes difficult to perform reliably and repeatably in a real factory on full-scale parts to build a large structure such as an airplane wing box.
  • the difficulty is in getting the proper amount of heat to the bondline without overheating the entire structure, and also in achieving intimate contact of the faying surfaces of the two parts at the bondline during heating and cooling despite the normal imperfections in the flatness of composite parts, thermal expansion of the thermoplastic during heating to the softening or melting temperature, flow of the thermoplastic out of the bondline under pressure (i.e., squeeze out), and then contraction of the thermoplastic in the bondline during cooling.
  • the current density in the susceptor may be higher at the edges of the susceptor than in the center because of the nonlinearity of the coil, such as occurs when using a cup core induction coil like that described in U.S. Patent 5,313,037. Overheating the edges of the assembly can result in underheating the center, either condition leading to inferior welds because of non-uniform curing. It is necessary to have an open or mesh pattern in the susceptor embedded at the bondline to allow the resin to create the fusion bond between the composite elements of the assembly when the resin heats and melts. a. Moving coil welding processes
  • a tailored susceptor having openings with a length (L) to width (W) ratio of 2: 1 has a longitudinal conductivity about four times the transverse conductivity.
  • we altered the current density in regions near the edges by increasing the foil density (i.e., the absolute amount of metal). Increasing the foil density along the edge of the susceptor increases the conductivity along the edge and reduces the current density and the edge heating.
  • We increased foil density by folding the susceptor to form edge strips of double thickness or by compressing openings near the edge of an otherwise uniform susceptor. We found these susceptors difficult to reproduce reliably. Also, their use forced careful placement and alignment to achieve the desired effect.
  • the tailored susceptor was designed to use with the cup coil of U.S.
  • Patent 5,313,037 where the magnetic field is strongest near the edges because the central pole creates a null at the center. Therefore, the tailored susceptor was designed to counter the higher field at the edges by accommodating the induced current near the edges. The high longitudinal conductivity encouraged induced currents to flow longitudinally.
  • Our selvaged susceptor for thermoplastic welding which is described in U.S. Patent Application 08/314,027 controls the current density pattern during eddy current heating by an induction coil to provide substantially uniform heating to a composite assembly and to insure the strength and integrity of the weld in the completed part.
  • This susceptor is particularly desirable for welding ribs between prior welded spars using an asymmetric induction coil (described in U.S. Patent Application 08/349,647, which we incorporate by reference), because, with that coil, it provides a controllable area of intense, uniform heating, a trailing region with essentially no heating, and a leading region with minor preheating.
  • the heating achieved directly corresponds to the power (or power density).
  • the resulting susceptor has a center portion with a regular pattern of opening and solid foil edges, which we refer to as selvage edge strips.
  • the susceptor in a thermoplastic resin to make a susceptor/resin tape that is easy to handle and to use in performing the composite pieces prior to welding.
  • the impedance of the central portion should be anisotropic with a lower transverse impedance than the longitudinal impedance.
  • the L/W ratio of diamond shaped openings should be less than or equal to one.
  • L for the selvaged susceptor should be less than W.
  • Additional surface contact can be achieved by applying pressure to the parts to force the faying surfaces into contact, but full intimate contact is difficult or impossible to achieve in this way.
  • Applying heat to the interface by electrically heating the susceptor in connection with pressure on the parts flattens the irregularities, but the time that is needed to achieve full intimate contact with the use of heat and pressure is excessive. The delay need to flatten can result in deformation of the top part.
  • the overall temperature of the "I" beam flanges reaches the softening point, they will begin to yield or sag under the application of the pressure needed to achieve a good bond.
  • Patent Application 08/367,546 enables a moving coil welding process to produce continuous or nearly continuous fusion bonds over the full area of the bondline to yield very high strength welds reliably, repeatably and with consistent quality.
  • This process produces improved low cost, high strength composite assemblies of large scale parts fusion bonded together with consistent quality, and uses a schedule of heat application that maintains the overall temperature of the structure within the limit in which it retains its high strength, so it requires no internal tooling to support the structure against sagging which otherwise could occur above the high strength temperature limit.
  • the process also produces nearly complete bondline area fusion on standard production composite material parts having the usual surface imperfections and deviations from perfect flatness, while eliminating fasteners and the expense of drilling holes, inspecting the holes and the fasteners, inspecting the fasteners after installation, sealing between the parts and around the fastener and the holes; reducing mismatch of materials; and eliminating arcing from the fasteners.
  • an induction heating work coil is passed multiple times over a bondline while applying pressure in the region of the coil to the components to be welded, and maintaining the pressure until the resin hardens.
  • the resin at the bondline is heated to the softening or melting temperature with each pass of the induction work coil and pressure is exerted to flow the
  • the total time at the softened or melted condition of the thermoplastic in the faying surfaces is sufficient to attain deep interdiffusion of the polymer chains in the materials of the two faying surfaces throughout the entire length and area of the bondline, thereby producing a bondline of improved strength and integrity in the completed part, but the total time of the faying surfaces at softened temperature is in separate time segments which allows time for the heat in the interface to dissipate without raising the temperature of the entire structure to the degree at which it loses its strength and begins to sag, so the desired shape and size of the final assembly is maintained.
  • a structural susceptor allows us to include fiber reinforcement within the weld resin to alleviate residual tensile strain otherwise present in an unreinforced weld.
  • the susceptor includes alternating layers of thin film thermoplastic resin sheets and fiber reinforcement (usually woven fiberglass fiber) sandwiching the conventional metal susceptor that is embedded in the resin.
  • the structural susceptor permits gap filling between the welded composite laminates which tailors the thickness (number of plies) in the structural susceptor to fill the gaps, thereby eliminating costly profilometry of the faying surfaces and the inherent associated problem of resin depletion at the faying surfaces caused by machining the surfaces to have complementary contours.
  • thermoplastic welding using our induction heating workcell and, of course, discovered that the process differs from the moving coil processes because of the coil design and resulting magnetic field.
  • our fixed coil workcell presents promise for welding at faster cycle times than the moving coil processes because we can heat multiple susceptors simultaneously.
  • the keys to the process are achieving controllable temperatures at the bondline in a reliable and reproducible process that assure quality welds of high bond strength.
  • Our fixed coil induces currents to flow m the susceptor differently from the moving coils and covers a larger area. Nevertheless, we have developed processing parameters that permit welding with our induction heating workcell using a susceptor at the bondline.
  • Thermoplastic Composites which we incorporate by reference.
  • the problems center on the fact that the metal is a foreign material in the weld or bond present only as a heating source and detriment in other respects. Therefore, welding would be improved if the susceptor could be eliminated.
  • Sagging is also a problem and countering the sagging is an even bigger problem especially when trying to construct realistic aerospace structural assemblies of ribs, spars, closeouts, and skins. Such assemblies usually include isolated regions where it is difficult to insert or to remove support tooling.
  • a hybrid metal webbed composite beam of the present invention preferably includes a titanium sine wave spar web with composite caps that are formed onto flanges of the web.
  • the composite caps are adhered to the titanium web with a hot shoe forming tool to form prefabricated and consolidated thermoplastic composite laminates into a "C" section onto the titanium web or through the lay up, bagging, and consolidation of flexible prepregs onto the titanium flange as an internal tool.
  • the use of the hybrib titanium/composite beam reduces several problems associated with thermoplastic welding of spars and ribs to skins.
  • the titanium I-beam or sinewave provides an internal tool to prevent deformation of the spar caps or delamination of the cap composite plies during the welding process.
  • the hybrid beam is also superior in performance to an all composite spar, rib, or frame in the following areas: cap pulloff, web blast resistance, bending stiffness, dimensional accuracy, and ability to weld into a composite skinned wing structure.
  • the beam uses both the triaxial strength and fracture resistance of titanium in the web and tee joint areas, and takes advantage of the high specific stiffness of composite materials in the outer chord of the caps.
  • the internal titanium I section functions as an internal tool to allow welding of the thermoplastic caps to thermoplastic skins without additional support tooling.
  • Figure 1 is a schematic perspective view of our hybrid metal webbed composite beam.
  • Figure 2 is a schematic perspective view of forming the beam of Fig. 1 with a hot shoe.
  • Figure 3 is a schematic perspective view of forming the beam of Fig. 1 in a lay up and consolidation process.
  • Figure 4 is a perspective view of our induction heating workcell.
  • Figure 5 is a schematic cross sectional view of the induction heating workcell of Fig. 4.
  • Figure 6 is a schematic cross sectional view of our induction heating workcell adapted for thermoplastic welding of a wingskin/spar assembly.
  • Figure 7 is another schematic cross sectional view of the workcell of Fig. 6 rotated 90° from the view in Fig. 6.
  • Figure 8 is a schematic cross sectional view of a reinforced susceptor.
  • Figure 9 is a schematic sectional view of an alternative beam.
  • Figure 10 illustrates schematically in cross section a "smart" susceptor brazed to the spar cap flange to provide improved pulloff strength.
  • Figure 11 illustrates schematically in cross section a double-sided "smart" susceptor similar to the susceptor of Fig. 10.
  • Figure 12 illustrates schematically in cross section the susceptor of Fig. 11 interfacing at a weld between a composite skin and a composite spar cap.
  • the hybrid beam of the present invention is useful as a spar 105, rib, frame, or beam in high performance military or commercial aircraft.
  • This invention consists of two major components: A superplastically formed and diffusion bonded/brazed titanium I section 150 which forms the web of the spar or frame; and a thermoplastic or thermoset composite (spar or frame) cap 160 which is formed around the Titanium I section and consolidated to it.
  • the titanium web section can either be a straight section or take on a sinusoidal wave pattern. For straight, untapered I sections the use of extrusion directly from titanium billet to near net shape is an attractive process. We can use three manufacturing processes to attach the caps to the titanium webs.
  • the caps are formed onto the titanium I section using an automated hot shoe tool that runs down the spar, forming preconsolidated thermoplastic composite laminate into a C section cap as shown in Figure 2.
  • This invention can also be practiced by hand laying-up a thermoset tape laminate onto the titanium I section as a internal lay-up mandrel tool to produce a hybrid composite spar, frame, or rib as shown on Figure 3.
  • a thrid process for making the beam involves forming a thermoset or thermoplastic cap on another tool and either slip fitting or attaching the cap to the web followed by co-bonding the assembly in an autoclave or in our induction heating workcell.
  • thermoplastic caps because these materials can be hot formed and molded onto the titanium I-section in a rapid, automated process.
  • Another advantage of thermoplastics is their inherent ductility which allows us to produce thicker laminates of uniaxial lay-ups without thermal stress induced microcracking which would affect thermoset composites.
  • the present invention addresses the fundamental problem with the design of T or I section graphite composite spars and frames whose cap pulloff strength is limited by out- of-plane tensile stresses at the cap/web intersection. These out-of-plane stresses are between the gap filler and the composite plies which wrap from the web into the cap and cause failure at this point in a pulloff test.
  • the beam also addresses the fundamental weakness of titanium spar or frame designs that have more than adequate cap pulloff strengths, but suffer because titanium has a low specific stiffriess relative to composite material and are therefore heavier than composite designs for a given stiffness, even though they are more resistant to damage.
  • Another advantage of this hybrid beam design is the ability to use a majority of uniaxal plies of a thermoplastic composite material in the caps. The shear ( ⁇ 45) plys that are present in traditional composite designs are no longer necessary because the thin titanium web section provides the necessary shear transfer function.
  • Laminates that contain a high percentage of uniaxial plies in their lay-up have up to a factor of three better stiffness in the longitudinal direction than a traditional quasi-isotropic or fabric laminate used in traditional all-composite designs, resulting in a lighter, stiffer spar.
  • Our beam concept also solves the major difficulty of removing internal tooling from a closed box after welding the spars to the skin. Internal tooling is required when welding all composite spars and ribs to skins to prevent the cap plys from deforming or delaminating when the temperature is above the glass transition temperature.
  • the I-section titanium web of our beam acts to stiffen and support the cap during the induction welding process, so that internal tooling is not required to weld the caps to thermoplastic skins.
  • the hybrid beam also provides lower total variation of the spar's height as compared to conventional all-composite designs because the total composite laminate thickness on the caps is much thinner than in all-composite designs which must include shear plys that transition into the webs.
  • the superplastically formed I-sections are more dimensionally accurate after fabrication than the corresponding portion of an all composite spar and can be finish machined for even better accuracy.
  • a large variation in the spar height of about ⁇ 50 mils requires extensive and costly shimming or machining of skin pad- ups to make it fit with the mating skin during assembly.
  • ⁇ 8 mils the maximum gap that can be pulled up in assembly of composites
  • the cost of wing assembly is reduced in traditional assembly processes and greatly improves the thermoplastic welding process.
  • the T-section is preferably made by superplastic forming suitable titanium sheet stock with two corresponding "C" elements bonded, welded, fused, brazed or fastened together. Normally the elements are diffusion bonded together after the SPF process is complete, although brazing may be more reliable process as discussed in Boeing's U.S. Patent 5,420,400. a. Forming the I-beam
  • Superplastic forming is a fabrication technique that relies on superplasticity.
  • a typical SPF process involves placing one or more sheets of metal or plastic in a die, heating the sheets to an elevated temperature within the superplastic range, and superplastically forming the sheet(s) at the SPF temperature.
  • a differential forming pressure from a gas manifold is used to stretch the sheet(s) into the desired shape against the die surface(s).
  • This forming process can be called blow molding insofar as it uses differential pressure to form the material.
  • the differential pressure is selected to strain the material at a strain rate that is within its superplastic range.
  • SPF Simple Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar Planar, tungsten, tungsten, and tungstens, and tungstens, and tungstens, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten, and tungsten.
  • joining processes such as diffusion bonding, brazing or
  • the sheet metal is placed between dies, at least one of which has a contoured surface corresponding to the shape of the product.
  • the dies are placed on platens which are heated, generally using embedded resistive heaters. The platens heat the dies to about 1650°F (900°C). Because the titanium will readily oxidize at the elevated temperature, an inert gas, such as argon, surrounds the die and workpiece. The dies heat the sheet metal to the temperature range where the sheet metal is superplastic. Then, under applied differential pressure, the sheet metal deforms against the contoured surface.
  • the platens and dies have a large thermal mass. They take considerable time and energy to heat and are slow to change their temperature unless driven with high heat input or with active cooling. To save time and energy, they must be held near the forming temperature throughout a production run (i.e., the production of a number of parts using the same dies).
  • the raw sheet metal must be inserted onto the dies, and formed parts removed, at or near the elevated forming temperature. The hot parts must be handled carefully at this temperature to minimize bending. Within the SPF range, the SPF metals have the consistency of taffy, so bending can easily occur unless the operators take suitable precautions.
  • the web is readily manufactured using conventional SPF processes and generally is shaped to include a transverse sinusoidal waveform shape for increased strength.
  • the spar cap 160 is attached to the web section 150 with the methods shown schematically in Fig. 2 & 3.
  • a prefabricated and preconsolidated thermoplastic composite is heated and formed with a hot shoe 170 mat passes slowly along the web from end to end.
  • the cap 160 is prepared from prepreg that is laid up on the web section 150 in the desired final configuration to surround the T.
  • the lay-up is bagged with a conventional autoclave consolidation film material 180, and the pregreg is consolidated in an autoclave or other suitable process, using a caul plate 190 on the faying surface of the prepreg to obtain a smooth, finished surface and to assure equal pressure over the entire faying surface.
  • the web might include upright tips on the ends of the T to define a shallow channel in which the composite seats. Plies of the prepreg interfere with the lip of the tips. This shallow channel option is illustrated in Fig. 9.
  • the mermoplastic is typically PEI, PEEK, PEK, PEKK, or polyimide reinforced with glass, carbon, or graphite fibers.
  • the web section is typically an SPF alloy of titanium.
  • the T-section ofthe web can function as the induction susceptor in the welding operation, if the cap is thin enough to melt at the faying surface when heated from within.
  • a susceptor might be used at the bondline including, if desired, a reinforced susceptor fabric weave as the ply immediately adjacent the faying surface, as described in our U.S. Patent Application 08/469,986, which we incorporate by reference, and as schematically illustrated in Fig. 8.
  • the hybrid beam is particularly suitable for use in thermoplastic welding of aerospace wingbox or wing tip structure where ribs and spars are welded to wingskins.
  • thermoplastic welding of aerospace wingbox or wing tip structure where ribs and spars are welded to wingskins.
  • an induction heating workcell 10 includes tools or dies 20 and 22 mounted within an upper 24 and a lower 26 strongback.
  • the strongbacks are each threaded onto four threaded column supports or jackscrews 28 or they float free on the columns and are fixed with nuts. We can turn the jackscrews to move one strongback relative to me other.
  • the strongbacks 24 and 26 provide a rigid, flat backing surface for the upper and lower dies 20 and 22 to prevent the dies from bending and cracking during manufacturing operations.
  • the strongbacks hold the dies to a surface tolerance of ⁇ 0.003 inches per square foot of the forming surface. Such tolerances are desirable to achieve proper part tolerances.
  • the strongbacks may be steel, aluminum, or any other material capable of handling the loads present during forming or consolidation, but we prefer materials that are nonmagnetic to avoid any distortion to the magnetic field that our induction coils produce. In some circumstances, the dies may be strong enough themselves mat strongbacks are unnecessary. The strongbacks transfer pressure input through the columns evenly to the dies.
  • the dies 20 and 22 are usually cast ceramic and are reinforced with a plurality of fiberglass rods 32 that are held with bolts 74 and that extend both longitudinally and transversely in a grid through each die.
  • Each die usually is framed with phonemic reinforcement 72 as well, to maintain a compressive load on the die.
  • Each die may be attached to its strongback by any suitable fastening device such as bolting or clamping.
  • both dies are mounted on support plates 76 which are held in place on the respective strongbacks through the use of clamping bars 77.
  • the clamping bars 77 extend around the periphery of the support plates 76 and are bolted to the respective strongbacks through the use of fasteners (not shown).
  • the dies should not be susceptible to inductive heating so that heating is localized in the retort rather than distributed in the press as well.
  • a ceramic that has a low coefficient of thermal expansion, good thermal shock resistance, and relatively high compression strength, such as a castable fused silica ceramic.
  • FIG. 4 we show four separate induction segments mat overlie me top and bottom of the workpiece, but the number usually is higher, as shown in Fig. 6, and the segments can surround the workpiece on the top, bottom, and all sides.
  • Each segment is formed from a straight tubing section 36 that extends along the length of each die and a flexible coil connector 38 that joins the straight tubing sections 36 in the upper die 20 to the corresponding straight tubing section in the lower die 22.
  • Connectors 40 located at the ends of the induction coil 35 connect the induction coil 35 to an external power source or coil driver 50 and to a circulation system for cooling fluid. While the tubes are shown as being circular in cross-section, other shapes can be used, such as rectangular channels.
  • Cavities 42 and 44 in the respective dies hold tool inserts 46 and 48.
  • the upper tool insert 46 in some applications has a contoured forming surface 58 that has a shape corresponding to the desired shape of the outer mold line surface of the completed composite.
  • the lower tool insert determines the inner mold line.
  • the tool inserts also should not be susceptible to inductive heating, preferably being formed of a castable ceramic.
  • both the dies and the tool inserts can be made from a matrix resin rather than from a ceramic. Using a resin, however, limits use of the tooling to low temperature operations, such as forming or consolidating certain organic matrix composites. We prefer ceramic tooling which provides the greatest flexibility and versatility for the induction heating workcell.
  • the forming surfaces can be an integral part of the dies, we prefer the separate die and tool insert configuration shown in Fig. 5 because changing tool inserts to make different parts is easier and quicker (because they are significantly smaller) and the overall tooling costs are reduced.
  • Each die surrounds and supports the respective tool insert and holds the straight sections 36 of the induction coil in proper position in relationship to the tool insert 46 or 48.
  • the interior 70 of the dies is formed of a castable phonemic or ceramic and the exterior sides from precast composite phonemic resin blocks 72. In some applications, we prefer to reinforce the phonemic or ceramic with chopped fibers or nonwoven or woven reinforcing mats.
  • Fig. 5 shows a retort 60 between tool inserts 46 and 48.
  • the retort 60 includes a workpiece and sandwiching susceptor facesheets.
  • the retort is heated to a forming or consolidation temperature by energizing the coil 35.
  • Pressure source 52 applies pressure to the upper surface of the retort 60 through a conduit 62 that passes through the upper die 20 and upper tool insert 46
  • pressure source 54 applies a pressure to the lower surface of the retort 60 through a conduit 64 that passes through the lower die 22 and lower tool insert 48.
  • the pressure applied to the retort 60 is maintained until me retort has formed to the contour of the forming surface 58 and the matrix resin has consolidated.
  • the pressure sources 52 and 54 generally apply a differential pressure to the retort 60. We do not use a retort in the present invention.
  • An alternating oscillating electrical current in the induction coil 35 produces a time varying magnetic field that heats the susceptor sheets of the retort via eddy current heating.
  • the frequency at which the coil driver 50 drives the coils 35 depends upon the nature of the retort 60. We power the coil with up to about 400 kW at frequencies of between about 3-10 kHz. Current penetration of copper at 3 kHz is approximately 0.06 inches (1.5 mm), while penetration at 10 kHz is approximately 0.03 inches (0.75 mm).
  • the shape of the coil has a significant effect upon the magnetic field uniformity.
  • Field uniformity usually is important because temperature uniformity induced in the retort is directly related to the uniformity of me magnetic field. Uniform heating insures that different portions of the workpiece will reach the operating temperature at approximately the same time.
  • Solenoid type induction coils like those we illustrate provide a uniform magnetic field, and are preferred. Greater field uniformity is produced in a retort that is located symmetrically along the centerline of the surrounding coil.
  • Those of ordinary skill can establish series/parallel induction coil combinations, variable turn spacing, and distances between the part and the induction coil by standard electrical calculations to achieve the desired heating from whatever coil configuration is used.
  • the tool inserts and dies are usually substantially thermally insulating and trap and contain heat within the retort. Since the dies and tool inserts are not inductively heated and act as insulators to maintain heat within the retort, the present invention requires far less energy to achieve the desired operating temperature than conventional autoclave or resistive hot press methods where the metal tooling is a massive heat sink.
  • the dies cool rapidly to a temperature at which we can remove the workpiece from the workcell, saving time and energy over conventional systems. Coolant flowing through the coil tubes functions as an active heat exchanger to transfer heat out of the workpiece, retort, and dies.
  • the thermal cycle is not as limited by the heating and cooling cycle of the equipment and tools so we can tailor the thermocycle better to the process for which we are using the induction heating workcell.
  • a susceptor tape 115 usually is positioned along the bondline between the wingskin 100 and the spar caps.
  • a susceptor tape we mean a metal ribbon embedded in thermoplastic resin or a structural susceptor as described in U.S. Patent Application 08/471,625 having the resin-embedded ribbon sandwiched with alternating plies of thermoplastic film and fiber reinforcement to alleviate residual tensile strain in the weld and to simplify gap filling while ensuring a resin rich, quality weld.
  • the metal ribbon may be copper, a cobalt alloy, nickel-iron alloys, or any other suitable "smart" susceptor from the alternatives discussed in U.S. Patent Application 08/469,604.
  • the susceptor might be narrow metal strips about 0.10 - 0.20 in wide held in side-by- side array with the thermoplastic resin or woven with carbon fibers or other reinforcement.
  • the induction coil of our induction heating workcell induces eddy currents that run longitudinally. Therefore, the susceptor should have a lower longitudinal impedance to promote longitudinal current flow.
  • We might use a modified, selvaged susceptor (see U.S. Patent Application 08/314,027) having solid copper bands alternating with mesh sections with the solid bands in the bondline rather than falling outside it, since they are the primary current carriers.
  • the matrix resin does not wet with the metal as well as it does with the reinforcing fibers and the metal does not have the strength commonly available with the fibers. Therefore, a reinforced susceptor promises improved bond strength.
  • the need for a susceptor in the bondline poses many obstacles to the preparation of quality parts.
  • the metal which is used because of its high susceptibility differs markedly in physical properties from the resin or fiber reinforcement so dealing with it becomes a significant issue.
  • the reinforced susceptor (Fig 8) overcomes problems with conventional susceptors by including the delicate metal foils 200 (0.10 - 0.20 in wide x 0.005 - 0.010 in thick;
  • the foil is always on the remote side of the fabric because it is between the warp thread and the weave threads 210. This arrangement holds the foils in place longitudinally in the fabric in electrical isolation from each other yet substantially covering the entire width of the weld surface while still having adequate space for the flow and fusion of the thermoplastic resin. Furthermore, in the bondline, the resin can contact, wet, and bond with the reinforcing fiber rather than being presented with the resinphilic metal of the conventional systems. There will be a resin-fiber interface with only short runs of a resin-metal interface.
  • the short runs are the length of the diameter of two weave fibers plus the spatial gap between the weave fibers, which is quite small.
  • the metal is shielded within the fabric and a better bond results.
  • this woven arrangement to foil can assume readily the contour of the reinforcement.
  • the arrangement permits efficient heat transfer from the foil to the resin in the spatial region where the bond will form.
  • the reinforced susceptor might be an analog of the structural, selvaged, or tailored susceptors of one other application (i.e. a tape encased in resin and placed along the bondline) or may be fabricated as part of the facing flies of the prefabricated composites that abut along the bondline.
  • the susceptors at the bondlines for the top and bottom are connected together into a loop circuit with jumpers 115 at the ends of the spars 105.
  • the jumpers 115 allow the current which the magnetic field induces to flow around the assembly to generate heat in the bondlines.
  • the web's spar cap functions as an embedded susceptor so it may be unnecessary to use an additional susceptor at the bondline.
  • the flange is oriented properly in the assembly to heat under the time varying magnetic field from the induction coil (moving or fixed). The flange, accordingly can heat the composite cap and with its melting, the cap can create the desired fusion bond or weld.
  • the integrity of the weld is critical to the performance of the completed, welded structure.
  • the quality of the weld is related to the temperature along the bondline and good welds require control of the temperature within a relatively narrow range during the welding.
  • a "smart" susceptor made from a Co, Ne, or Fe alloy with a Curie temperature slightly above the melting temperature of the resin will help ensure that we produce quality welds.
  • an alloy like Invar 42 (42% Ni - 58% Fe) has a coefficient of thermal expansion (CTE) comparable to the resin composite so that embedding the susceptor into the completed part will not have as dramatic an impact if the susceptor is such an alloy rather than copper or another metal where the CTE mismatch between the resin and susceptor is larger.
  • CTE coefficient of thermal expansion
  • the Invar can be brazed to the spar cap as shown in Fig. 10.
  • the "smart" susceptor includes sharp, barbed prongs 250 (Fig.
  • the "smart" susceptor is described in our U.S. Patent Application 08/486,560 entitled Barbed Susceptor for Improving Pulloff Strength of Welded Thermoplastic Composites, which we incorporate by reference.
  • the "smart” susceptor might also be made from martensitic 400 series stainless steel or INCO 909 iron-nickel alloy, the prongs 250 generally extend upwardly about 0.020 - 0.030 inch. They are barbed by making slanted laser cuts along their shafts to allow the prongs to penetrate easily but to pull out with difficulty.
  • the present invention is applicable to all types of organic matrix composites including both thermosetting and the thermoplastic composites such as epoxies, bismaleimides, polyimides, PEEK, PEK, PEKK, PES, or the like. It is especially suited, however, for consolidation or forming of resins that have low volatiles content and that are nonreactive (i.e., the true thermoplastics like PEEK or ULTEM).
  • the surface of an aircraft wing skin must be maintained to a close tolerance to achieve an efficient aerodynamic surface.
  • the tolerances of the inner mold line surface of the wing skin must also be maintained at a close tolerance at least in a buildup area where the wing skin will be joined to a spar to ensure that the wing skin and spar can be precisely joined. It is not critical, however, to control the inner mold line surface in areas where the wing skin is not attached to other structures.
  • the composite panel has additional plies to define the buildup areas. The additional reinforce the composite panel in these areas which is necessary where a spar will be attached, and provide a convenient way to match the skin and spar to produce the desired outer wing configuration even if the spars are imprecise in their dimensions. We can fabricate built up areas at the faying surfaces to provide the precision fit, in which we can eliminate shims.
  • the susceptor may be in sheet, mesh, expanded, milled, selvaged or other suitable form and should be structured from the optimum conductivity longitudinally and transversely needed to obtain controlled, reliable, and reproducible heating. Geometry and structure are closely related to the type of induction head used, as those of ordinary skill will understand. Therefore, the spar caps might include etched, stamped, or machined apertures in a predetermined pattern to produce the desired heating pattern.

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Abstract

Poutre composite hybride possédant une âme en métal, dont la section (150) présente une forme de I ou de T, ainsi qu'un revêtement composite (160) recouvrant l'âme en forme de I ou de T par adhérence. Cette poutre allie les avantages des métaux et des composites dans la construction aérospatiale moderne, ce qui permet d'effectuer sa soudure thermoplastique à des revêtements d'appareils, tandis qu'elle possède la résistance du métal.
PCT/US1996/009630 1995-06-07 1996-06-06 Poutre composite hybride possedant une ame en metal WO1996040551A1 (fr)

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AU62637/96A AU6263796A (en) 1995-06-07 1996-06-06 Hybrid metal webbed composite beam

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
US08/482,513 US5829716A (en) 1995-06-07 1995-06-07 Welded aerospace structure using a hybrid metal webbed composite beam
US08/473,910 US5688426A (en) 1995-06-07 1995-06-07 Hybrid metal webbed composite beam
US08/483,407 1995-06-07
US08/482,513 1995-06-07
US08/473,910 1995-06-07
US08/483,407 US5556565A (en) 1995-06-07 1995-06-07 Method for composite welding using a hybrid metal webbed composite beam

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GB2442301A (en) * 2006-09-29 2008-04-02 Boeing Co Composite structural member having a web and a flange
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US8444087B2 (en) 2005-04-28 2013-05-21 The Boeing Company Composite skin and stringer structure and method for forming the same
US9878773B2 (en) 2012-12-03 2018-01-30 The Boeing Company Split resistant composite laminate
WO2019213529A1 (fr) 2018-05-03 2019-11-07 Triumph Aerostructures, Llc. Aérostructure thermoplastique avec isolation de pli localisée et procédé de formation d'une aérostructure
CN114872329A (zh) * 2022-06-14 2022-08-09 中国船舶重工集团公司第七二五研究所 一种一体化成型复合材料蒙皮与骨架连接方法
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