US20170284099A1 - Composite structural element and method of producing the same - Google Patents

Composite structural element and method of producing the same Download PDF

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Publication number
US20170284099A1
US20170284099A1 US15/287,778 US201615287778A US2017284099A1 US 20170284099 A1 US20170284099 A1 US 20170284099A1 US 201615287778 A US201615287778 A US 201615287778A US 2017284099 A1 US2017284099 A1 US 2017284099A1
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US
United States
Prior art keywords
structural element
composite
interlayers
composite layers
composite structural
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.)
Abandoned
Application number
US15/287,778
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English (en)
Inventor
Chih-Hsiao Chien
Wen-Bin Hsieh
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.)
Taiyoi Graphite Co Ltd
Tyko Tech Co Ltd
Original Assignee
Taiyoi Graphite Co Ltd
Tyko Tech Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from TW105204660U external-priority patent/TWM526495U/zh
Priority claimed from TW105212899U external-priority patent/TWM537020U/zh
Application filed by Taiyoi Graphite Co Ltd, Tyko Tech Co Ltd filed Critical Taiyoi Graphite Co Ltd
Assigned to TAIYOI GRAPHITE CO., LTD., TYKO TECH CO., LTD. reassignment TAIYOI GRAPHITE CO., LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CHIEN, CHIH-HSIAO, HSIEH, WEN-BIN
Publication of US20170284099A1 publication Critical patent/US20170284099A1/en
Abandoned legal-status Critical Current

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    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C3/00—Structural elongated elements designed for load-supporting
    • E04C3/02—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces
    • 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

Definitions

  • the present invention relates to a structural element, and more particularly, to a composite structural element and a method of producing the same.
  • a method of producing a composite structural element disclosed in U.S. Pat. No. 7,357,726 is a conventional pultrusion method that is commonly used for continuously producing a special-shaped product, which enables the cross section of the molded structural element to have an I-shape, a C-shape, an L-shape, or an annular shape, and so on through a molding space provided by a specific mould, for use in construction, automotive, and other industries.
  • a desired arrangement direction of reinforcing materials such as fiber must be maintained by means of a base material such as resin, and a closed protection film is formed at the periphery of the fiber to provide a lateral support, so as to avoid stress concentration caused by the damage of the fiber due to the mutual friction, thereby affecting the strength and structure of the structural element itself.
  • a base material such as resin
  • a closed protection film is formed at the periphery of the fiber to provide a lateral support, so as to avoid stress concentration caused by the damage of the fiber due to the mutual friction, thereby affecting the strength and structure of the structural element itself.
  • the prior art discloses that on the premise that the integrity of fiber in the composite material is maintained, the structural element is combined with other components by adhering.
  • the structural element is combined with other components by adhering.
  • such technologies can avoid the damage on the fiber so as to ensure the strength of the composite structural element, due to the limited adhesion of the combination sites, the application of the composite structural element is limited.
  • a vehicle transmission shaft made of carbon fiber can only be combined with metal joints on both ends by means of gluing, and the deterioration degree of the adhesive and the fatigue tolerance of the metal interfaces are unpredictable and thus have become potential dangerous factors for the driving security.
  • the composite material has been widely used in various technical fields, the combination thereof with other components is still limited in technology.
  • good combination strength can be provided by means of the combining components such as bolts, but the concentration of stress will result in the damage on the composite structural element itself; and for the adhesive gluing means, the integrity of the composite structural element can be maintained, thereby avoiding the occurrence of stress concentration, but due to the deterioration of the adhesive that cannot be avoided, the combination strength is less than that of the bolts. Both means are imperfect.
  • the major objective of the present invention is to provide a composite structural element and a method of producing the same, which can avoid the damage on the structural element due to the stress concentration caused by the damage of the structural element at local structures such as drilled holes during the combination between the structural element and the external components.
  • the present invention provides a composite structural element, obtained by taking a tape formed by alternatively laminating composite layers made of a non-isotropic composite material and interlayers made of an isotropic material as a major component of the structural element, molding into a structural element of a fixed shape for use in industry, and optionally, directly drilling holes on the laminate of the composite layers and the interlayers.
  • Each of the composite layers has unidirectionally aligned fiber reinforcing materials and a polymeric base material wrapping each of the fiber reinforcing materials, and each of the interlayers is made of an isotropic material, and is located between any two adjacent ones of the composite layers.
  • the composite structural element further includes an inner portion having a specific shape, and each of the composite layers and each of the interlayers wrap the external side of the inner portion, so as to forma profile having the same contour as that of the inner portion.
  • the shape of the inner portion may be an I-shape, an L-shape, a C-shape, or other geometric shapes, and the inner portion may be a non-physical space in addition to a physical article.
  • the interlayers are evenly distributed among the composite layers such that they are sequentially alternatively laminated with each other. Also, in order to further strengthen the mechanical strength of the structural element, the individual thickness of the composite layers is made between 10 ⁇ m and 40 ⁇ m, and the individual thickness of the interlayers is made between 6 ⁇ m and 35 ⁇ m.
  • interlayers are made of aluminum or alloy materials thereof, surface treatment such as anodizing treatment should be performed on the interlayers, so as to avoid galvanic corrosion.
  • the method of producing a composite structural element includes forming a laminate by laminating the composite layers with the interlayers as described above, winding the laminate into a tubular outer portion, then taking a core having a specific shape to pass through the inner space of the outer portion as a mould, and exerting an external force such as an air pressure, such that the outer portion is contracted and attached to the periphery of the core, and then curing.
  • the core may be formed integrally with the outer portion, such that the core serves as the inner portion of the structural element.
  • foamed plastics or other lightweight materials can be used to produce the core.
  • the core may also be drawn off, such that the space where the core is originally located becomes a non-physical space, so as to form the inner portion with a non-physical space.
  • FIG. 1 is a perspective view of a structural element according to a preferred embodiment of the present invention.
  • FIG. 2 is a schematic view of a laminate of composite layers and interlayers alternatively laminated with each other according to a preferred embodiment of the present invention.
  • FIG. 3 is a cross-sectional view of a preferred embodiment of the present invention.
  • FIG. 4 is a schematic view of a producing process according to a preferred embodiment of the present invention.
  • a composite structural element ( 10 ) provided in a preferred embodiment the present invention has an I-shape, which can be used as a substitute of an I-shaped steel beam in building materials or a component of a vehicle, and of course, it may also has other different shapes or structures for use in other different industries.
  • the so-called structural element in the present invention is not limited to the so-called structural element in the building technology, and in terms of the structure, the composite structural element ( 10 ) mainly comprises an outer portion ( 20 ) and an inner portion ( 30 ).
  • the outer portion ( 20 ) is a laminate formed by laminating a plurality of single layers respectively made of a composite material and an isotropic material with each other, and includes a plurality of composite layers ( 21 ) and a plurality of interlayers ( 22 ), wherein the composite layers ( 21 ) are respectively structured as a fiber tape and not a fiber cloth, and each have unidirectionally aligned fiber reinforcing materials and a polymeric base material wrapping on each of the fiber reinforcing materials.
  • the thickness of the single layer is preferably between 10 ⁇ m and 40 ⁇ m, and may be a material such as a glass fiber, a graphite fiber, a Keviar fiber, a carbon nanotube, or a substitute or surrogate thereof;
  • each of the interlayers ( 22 ) is made of an isotropic material including metals such as aluminum or other non-metals, and the thickness of a single layer thereof is preferably between 6 ⁇ m and 35 ⁇ m; and
  • each of the composite layers ( 21 ) and each of the interlayers ( 22 ) are sequentially alternatively laminated with each other, such that the interlayers ( 22 ) can be uniformly distributed in the whole laminate, whereby the interlayers ( 22 ) can uniformly distribute the received force inside the laminate, thereby avoiding the damage derived from the local concentration of stress.
  • the inner portion ( 30 ) serves to give a specific shape as a whole of the structural element ( 10 ) and achieve the effect of increasing the volume of the structural element and reducing the usage amount of the outer portion ( 20 , and thus may be a lightweight material such as foam or foamed plastics, such that the outer portion ( 20 ) is wrapped onto the inner portion ( 30 ).
  • the composite structural element ( 10 ) can provide a good mechanical strength by means of the outer portion ( 20 ), and also, a plurality of fixing holes ( 11 ) may be directly drilled on the outer portion ( 20 ) and the inner portion ( 30 ) to respectively pass through each of the composite layers ( 21 ) and each of the interlayers ( 22 ).
  • the combining components such as bolts are fixed in the fixing holes ( 11 ) to combine the composite structural element ( 10 ) with another composite structural element or an external component
  • the fiber continuity of the fiber reinforcing materials is damaged by the fixing holes ( 11 ), so that the force fails to be further transmitted and focuses at breakpoint sites
  • the force that is not transmitted by the fiber may be further transmitted to the fiber with the isotropy of the material of the interlayers ( 22 ), so as to avoid stress concentration, thereby achieving the purpose of enhancing the mechanical strength of the combination sites of the composite structural element ( 10 ) and making the composite structural element ( 10 ) have a wider application range.
  • the interlayers ( 22 ) are uniformly distributed in the laminate and have a very small thickness, the uniform distribution of force can be ensured and the delamination can be avoided, so as to maintain the structural stability of the composite structural element ( 10 ).
  • the following steps may be carried out:
  • the core ( 41 ) becomes the inner portion ( 30 ) of the composite structural element ( 10 ) as shown in (a) of FIG. 4 .
  • a lightweight material such as foams or other foamed plastics is preferably used as the material of the core, so as to achieve the purpose and effect of lightweight.
  • a possibility of separating the outer portion ( 20 ) from the core ( 41 ) should be provided, for example, a release agent is applied on the surface of the core ( 41 ) in advance, such that after the step d is carried out, the core ( 41 ) is drawn away, and as shown in (b) of FIG. 4 , the space after the core ( 41 ) is drawn away forms the inner portion ( 30 ) of the composite structural element ( 10 ).
  • the efficacy of avoiding the stress concentration achieved by the outer portion ( 20 ) is not affected, and also, in order to obtain a specific shape of the composite structural element ( 10 ), in addition to the I-shape, the sectional shape of the core may be a C-shape, an L-shape, or other geometric shapes, such that the shape of the composite structural element ( 10 ) can satisfy different requirements.

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  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Laminated Bodies (AREA)
  • Rod-Shaped Construction Members (AREA)
US15/287,778 2016-04-01 2016-10-07 Composite structural element and method of producing the same Abandoned US20170284099A1 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
TW105204660U TWM526495U (zh) 2016-04-01 2016-04-01 碳纖維預浸布素材之結構
TW105204660 2016-04-01
TW105212899 2016-08-24
TW105212899U TWM537020U (zh) 2016-08-24 2016-08-24 複合材料構材

Publications (1)

Publication Number Publication Date
US20170284099A1 true US20170284099A1 (en) 2017-10-05

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US15/287,778 Abandoned US20170284099A1 (en) 2016-04-01 2016-10-07 Composite structural element and method of producing the same

Country Status (3)

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US (1) US20170284099A1 (ja)
JP (1) JP3208178U (ja)
CN (1) CN206374269U (ja)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11273622B2 (en) * 2016-12-14 2022-03-15 The Boeing Company Stiffening elements that comprise integral current flowpaths
GB2617894A (en) * 2022-02-15 2023-10-25 Sustainable Resources Ltd A foundation beam

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5480706A (en) * 1991-09-05 1996-01-02 Alliedsignal Inc. Fire resistant ballistic resistant composite armor
US5597631A (en) * 1989-01-25 1997-01-28 Asahi Kasei Kogyo Kabushiki Kaisha Prepreg, composite molding body, and method of manufacture of the composite molded body
US20110167759A1 (en) * 2008-08-21 2011-07-14 Anthony John Cesternino Carbon Fiber Reinforced Beam
US20140234600A1 (en) * 2011-10-14 2014-08-21 E I Du Pont De Nemours And Company Composite laminate having improved impact strength and the use thereof

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5597631A (en) * 1989-01-25 1997-01-28 Asahi Kasei Kogyo Kabushiki Kaisha Prepreg, composite molding body, and method of manufacture of the composite molded body
US5480706A (en) * 1991-09-05 1996-01-02 Alliedsignal Inc. Fire resistant ballistic resistant composite armor
US20110167759A1 (en) * 2008-08-21 2011-07-14 Anthony John Cesternino Carbon Fiber Reinforced Beam
US20140234600A1 (en) * 2011-10-14 2014-08-21 E I Du Pont De Nemours And Company Composite laminate having improved impact strength and the use thereof

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11273622B2 (en) * 2016-12-14 2022-03-15 The Boeing Company Stiffening elements that comprise integral current flowpaths
GB2617894A (en) * 2022-02-15 2023-10-25 Sustainable Resources Ltd A foundation beam

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Publication number Publication date
JP3208178U (ja) 2016-12-28
CN206374269U (zh) 2017-08-04

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AS Assignment

Owner name: TYKO TECH CO., LTD., TAIWAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CHIEN, CHIH-HSIAO;HSIEH, WEN-BIN;REEL/FRAME:039962/0981

Effective date: 20160926

Owner name: TAIYOI GRAPHITE CO., LTD., TAIWAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CHIEN, CHIH-HSIAO;HSIEH, WEN-BIN;REEL/FRAME:039962/0981

Effective date: 20160926

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION