WO1991002906A1 - Dispositf de fixation composite ameliore ainsi que son procede et son appareil de fabrication - Google Patents

Dispositf de fixation composite ameliore ainsi que son procede et son appareil de fabrication Download PDF

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Publication number
WO1991002906A1
WO1991002906A1 PCT/US1990/004803 US9004803W WO9102906A1 WO 1991002906 A1 WO1991002906 A1 WO 1991002906A1 US 9004803 W US9004803 W US 9004803W WO 9102906 A1 WO9102906 A1 WO 9102906A1
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WO
WIPO (PCT)
Prior art keywords
blank
head
shank
fastener
fibers
Prior art date
Application number
PCT/US1990/004803
Other languages
English (en)
Inventor
Roland Howard Gapp
Clyde D. Simmons
Original Assignee
Textron Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Textron Inc. filed Critical Textron Inc.
Publication of WO1991002906A1 publication Critical patent/WO1991002906A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D1/00—Producing articles with screw-threads
    • B29D1/005—Producing articles with screw-threads fibre reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B33/00—Features common to bolt and nut
    • F16B33/006—Non-metallic fasteners using screw-thread

Definitions

  • This invention relates to composite fasteners such as those threaded fasteners useful in aircraft construction, and the methods and apparatus for making such fasteners.
  • shear pins differ from the more widely used bolts in that they are designed for use in joints wherein the major load is a shear load, and wherein the tension loads are relatively low.
  • the manufactured head on a shear pin is usually made smaller and lighter than the manufactured head on a commercial bolt.
  • the nuts used on such shear pins are usually smaller and made from a lighter material than the pin itself.
  • commonly used shear pins have steel or titanium bodies to provide high shear strength, while the nut used is typically made of aluminum.
  • a composite material is a physical combination of two or more materials, both of which are usually visible to the naked eye.
  • a very early example is the use of straw, in biblical times, to reinforce mud bricks for building. More recent examples are the use of steel bars to reinforce concrete, the use of glass fiber to reinforce polyester resin in the making of boats, and the use of carbon fiber to reinforce various polymeric resins for aircraft construction.
  • the use of composite materials of the resin plus fiber reinforced variety in military fighter aircraft has increased very rapidly in the last 20 years. For instance, in the F14, which is a twenty-year old design, 0.8% of the total structural weight of the aircraft is made from composite materials.
  • Plastic materials have been used for nuts and bolts, but the unreinforced materials that have commonly been used for these fasteners in the past have not been strong enough for use as aircraft fasteners. Typically, such non- aircraft fasteners have possessed shear strengths of around 5-10 ksi. Recently, injection-molded short fiber reinforced fasteners have been produced having shear strengths in the range of 9-18 ksi. These are satisfactory for aircraft use in some applications. Also, compression- molded fasteners reinforced with short glass or carbon filament fibers have been produced with shear strengths in the range of 13-40 ksi, and these may find some use in aircraft. However, at the present time shear pins made from these compression molded materials have been found to exhibit insufficient consistency in shear and tension properties for wide aircraft use.
  • Weight savings make it possible to either carry a greater payload over a given distance, or to travel a greater distance with the same payload.
  • composite fasteners offer weight savings as well as additional advantages.
  • use of a composite fastener in a composite structure means that a fastener may often be chosen which has a coefficient of expansion equal to that of the surrounding structure.
  • a composite material can be chosen for a composite fastener such that the fastener does not heat up or otherwise interfere with electromagnetic functions in the vicinity of electronic devices such as radar transmitters.
  • use of composite fasteners in place of metal fasteners helps to reduce such visibility. Notwithstanding the suitability of composite fasteners for use in aircraft, their attractiveness would be enhanced in that application by an increase in shear strength, which allows use of fewer fasteners per pound of load to be supported.
  • the fasteners of the present invention are made from composite material having a plurality of long fibers bonded together by a binder. These warm formed fasteners have three portions: a cylindrical shank portion to carry bearing and shear loads; a head end integral with the shank; and a threaded tail end integral with the shank opposite the head.
  • the fibers within the head and tail portions of the fastener are not straight, having been deformed during the warm forming operation.
  • the fibers in the shank portion are straight.
  • the undeformed fibers of the shank portion provide the shear strength in the fastener.
  • Fasteners recently made in accordance with the present invention have average shear strengths in the vicinity of 50 ksi. Also, cylindrical blanks have been fabricated with a shear strength in excess of 60 ksi, therefore it follows that fabricated shear pins in the vicinity of 60 ksi should be available in the near f ture.
  • the fasteners of the present invention are made from a composite blank in a die having a thread forming cavity and a head forming cavity and means for selectively heating the blank portions within those cavities.
  • the fastener is made by selectively heating the blank end adjacent the thread forming cavity to a temperature sufficient to permit the material to deform while maintaining the blank shank portion below that temperature, compressing the blank so as to force the blank thread end material to deform into the thread forming cavity, thereby forming a fastener thread on the blank tail end, selectively heating the blank adjacent the thread forming cavity to a temperature sufficient to permit deformation of the material while maintaining the blank shank portion below that temperature, and compressing the blank so as to deform the blank head end material into the head forming cavity to form threads on the head end.
  • Figure 1 is a perspective view of a stack of composite tape plies formed into a panel, showing a typically square composite bar separated therefrom.
  • Figure 2 is a detailed perspective view of a corner of the sheet shown in Figure 1.
  • Figure 3 is an enlarged perspective view of a composite rod machined from the composite bar shown in Figure 1.
  • Figure 4a is a perspective view of a composite bar cut from the bar of Figure 1.
  • Figure 4b is a perspective view of a fastener blank machined from the bar of Figure 4a or the rod of Figure 3.
  • Figure 4c is a perspective view of a threaded blank formed from the blank of Figure 4b.
  • Figure 4d is a perspective view of a fully-headed fastener.
  • Figure 5 is a cross-sectional view of a composite fastener constructed in accordance with the prior art warm forming process.
  • Figure 6 is a cross-sectional view of a composite fastener constructed in accordance with the present invention.
  • Figure 7 is a cross-sectional view of a fastener blank in the apparatus of the present invention.
  • Figure 8 is a cross-sectional view of a threaded blank shown in the apparatus of Figure 7.
  • Figure 9 is a cross-sectional view of a fully-headed fastener shown in the apparatus of Figure 7.
  • Figure 10 is an enlarged view of the thread portion of the fastener of Figure 6 illustrating the fiber orientation.
  • Figure 11 is an enlarged view of the head portion of the fastener of Figure 6 illustrating a typical fiber orientation.
  • Figure 12 is a bar chart illustrating characteristics of prior fasteners.
  • Figure 13 is a bar chart illustrating characteristics of the fasteners of the present invention.
  • the fastener 6 of the present invention is formed from a composite material. That composite material is initially formed in thin sheet ⁇ like tapes, called plies, containing fibers which add to the strength of the plies.
  • a suitable tape has a thickness of about .005 inch, but other thicknesses can be utilized.
  • Each tape contains a plurality of individual carbon or orther reinforcing fibers which are twisted or otherwise held together in a bundle referred to as a tow.
  • a commonly used fiber is about 7 microns in diameter.
  • a commonly used tow contains 12,000 individual fibers.
  • the tows are arranged parallel to each other and are bonded together using a binder of polymeric resin.
  • thermoplastic polymer polyetheretherketone PEEK
  • the tows each composed of individual filaments, are generally parallel to each other and greatly increase the shear strength of the tape in the direction perpendicular to the fibers. These tows also greatly increase the tension strength in the direction of the fiber flow, but it is the shear strength that is of primary interest in this invention.
  • the tapes can be made into panels 36 such as shown in Figure 1.
  • a number of plies 34 of tape commonly .005 inch in thickness each, are stacked one on top of the other, as more clearly seen in Figure 2.
  • the stack is then heated while applying a compressive load. This process causes the binder in adjacent plies of tape to bind the plies together.
  • the panel 36 is formed, it is cooled. This creates a rigid composite panel 36 having the desirable characteristics discussed above.
  • the physical characteristics of the resulting fastener may be affected by the orientation of the plies, that is the direction of the fibers in the adjacent plies. -1-
  • Orientation of the fibers in the same direction is called a "unidirectional" layup. If a first layer is oriented along the longitudinal axis of the panel, a second layer oriented at -45° from said axis, a third layer oriented at +45° from said axis and a fourth layer is oriented at 90° to said axis, the panel is said to have a "0/+45/-45/90" or "quasi- isotropic" layup. Layup angles and the order in which each layer is stacked, are chosen in order to produce the desired combination of properties in the part being manufactured.
  • a section or bar 40 is cut from the edge of the panel, as indicated in Figure 1.
  • the bar 40 can then be machined by turning it on a lathe or by grinding between centers and cut into shorter pieces to produce a cylindrical rod 50 as shown in Figure 3.
  • the bar 40 may be simply cut into individual shorter pieces of bar stock 42.
  • Figures 4a - 4d show the manufacture of an individual fastener in stages.
  • the square cross-section bar stock 42 or cylindrical rod 50 are turned on a lathe or are ground to produce blanks 52 as shown in Figure 4b.
  • the portion of the blank 52 to be formed into threads is cut down to a diameter approximately .005 inch smaller than the minor diameter of the thread to be formed.
  • the resulting blank 52 is shown in Figure 4b. That blank 52 has a head end 54, shank portion 56 and tail end 58.
  • the machined blank 52 is then inserted into a suitable die.
  • the die and the blank 52 were heated to slightly above the melting point of the binder and pressure was applied to the blank 52 in a single step from the head end of the blank.
  • the melting point of a commonly-used binder, PEEK is approximately 650 ⁇ F.
  • the prior art contemplates heating the entire blank to approximately 725 ⁇ F.
  • Application of pressure caused the blank tail end 58 to form into threads 20 at the fastener tail 16 and caused the blank head end 54 to be formed into the large end of the die to form the head 12.
  • the fastener 10 was then allowed to cool to about 400°F or lower and removed from the die. Any excess material was machined from the top of the head to achieve the required head height.
  • This process has been described as "warm upsetting,” which distinguishes it from cold forming processes such as machining and other warm forming processes such as injection or compression molding which have been used to produce fasteners having average shear strengths in the range of 13-40 ksi.
  • the prior art method above described used to produce fasteners typically having average shear strengths in the range of 30-49 ksi.
  • analysis of shear test results indicated that the shear average strength of the shank of these prior art fasteners was approximately 1 to 18 ksi less than the average shear strength value of the rods 50 which were cut and machined from the original panels. The reason for this is not completely understood.
  • the column chart, Figure 12 shows specific examples of the shear strengths of the rods made from 33 different panels and the shear strength of the pins subsequently fabricated from these rods. All the panels in the chart were made using PEEK with carbon reinforcing fibers, except the last panel which was made using PEEK with quartz reinforcing fiber. It may be seen that the pins made from each panel were 1 to 18 ksi lower in shear strength than the rods in each case with two exceptions. In the two cases where pin shear equaled rod shear, one instance is believed to be due to poor panel processing and the other to a fortuitous choice of samples.
  • the inventors devised a method of warm forming the head and threads of the fastener while maintaining a major portion of the shank at a temperature well below the melting point of the binder. This procedure ensured that no cross-sectional redistribution of the fibers would take place, formation of binder-rich areas would be avoided, and no significant departure from fiber straightness would occur in the shank portion.
  • the column chart, Figure 13, shows specific examples of the ksi shear strengths of rods made from 10 different panels and the ksi shear strength of shear pins subsequently made from these rods using the process of the present invention. It may be seen that the shear strength of the pins is equal to the shear strength of the rods in four cases and is only 2 to 4 ksi lower than the rod shear strength in the remaining six cases. It may be seen that, in general, the pins made by the new process retain a arkably higher percentage of the shear value of the original rods than the pins made by the old art WHWSWT process.
  • FIG. 6 A schematic drawing of the fastener 10 made by the method of the invention is depicted in Figure 6.
  • the fibers 30 in the head 12 and tail 16 portions are shown formed into patterns which provide good resistance to head collapse under tension loads and good resistance to thread stripping also under tension loads.
  • the fibers 30 in the shank portion 14 are shown as straight, illustrating the uniform distribution of the fibers throughout the cross-section, the lack of binder- rich regions throughout the cross-section, and the straightness of the fibers. This is the desired fiber configuration for maximum shear strength.
  • a further advantage to the method of the present invention is that the panel can be fabricated in a panel press according to the optimum conditions of temperature and pressure which will result in the optimum condition of crystallinity and fiber "wet out” that will in turn give maximum shear strength properties in the rods. Rate of temperature rise, time at heat and time to cool can be accurately controlled and coordinated independently by a computer. Because the shank portion of each rod remains cool in the subsequent warm forming operation, the ideal "as pressed" structure is maintained. By contrast, in the old art of warm forming, all of the rod including the shank portion, is heated to about the same temperature as that used in the panel press but heating and cooling rates, dwell time at temperature and pressure applied during each stage are difficult to control accurately.
  • FIG. 7 A device for producing the fastener of the present invention is shown in Figures 7-9.
  • the blank 52 with its head end 54, shank portion 56 and tail end 58 is placed into a series of dies, the shank die 100, head die 102, upset die 104, and thread die 120.
  • the shank die 100 surrounds the fastener shank portion 56 and provides support thereto throughout the forming process.
  • An additional purpose of the shank die 100 is to keep the shank portion of the fastener below the melting point of the binder, 650 ⁇ F in the case of PEEK.
  • the shank die may be conveniently formed of a ceramic or other insulative material which limits the conduction of heat into the shank from the remainder of the tooling.
  • the head die 102 Directly above the shank die 100 is the head die 102. Directly above the head die 102 is the upset die 104. The upset die 104 is heated by means of the electrical resistance head heating coil 112 disposed therearound. Of course, one of ordinary skill in the art will recognize that the head end 54 of the blank 52 may be heated by means other than an electrical resistance coil.
  • the upper insulator 110 Directly above the upset die 104 is the upper insulator 110, which may be conveniently made of ceramic or other insulative material. The purpose of this upper insulator is to reduce conduction of heat upward from the upset die 104 into the remainder of the tooling.
  • the upper insulator 110 may be received by an upper jig 114 or any suitable retaining member.
  • Slidably disposed within upset die 104 is head upset pin 106. This pin is urged against the blank head end 54 by the upper ram 116.
  • the thread die 120 Directly beneath the shank die 100 is the thread die 120. Disposed around the thread die 120 is the electrical resistance tail heating coil 130. As with the head heating coil 112, one of ordinary skill in the art will recognize that there are additional equivalent means by which the blank tail end 58 may be heated. Slidably disposed within the thread die 120 is the thread upset pin 122. Thread upset pin 122 is urged against the blank tail end 58 by lower ram 132. Heat from the thread die 120 is contained therein by lower insulator 124, which may be supported by lower jig 126 or any other suitable means.
  • the blank 52 is shown placed in the tooling ready for application of heat and pressure to form the threads and head.
  • a threaded rod 60 is shown, after the lower ram 132 has urged the blank tail end 58 upward so as to deform the blank tail end 58 into the thread forming cavity 134. Accordingly, threads 20 have been formed on the blank 58 to form threaded blank 60.
  • upper ram 116 and head upset pin 106 have remained stationary. Because the head heating coil 112 has not been energized, and no heat has been applied to the blank head end 54, the head end 54 has undergone no appreciable deformation. Upon formation of the threads, the tail heating coil 130 is deenergized and allowed to cool. Next, the head heating coil 112 is energized and the upset die and blank head end 54 are heated. Once the blank head end 54 is heated to the forming temperature of approximately 725°F, the head upset pin 106 is urged forcibly against the blank head end 54 by the upper ram 116. The compression urges the material of the head end 54 to deform and fill the head cavity 108, thereby forming the fastener head 12 as shown in Figure 9. The head heating coil 112 is then deenergized and allowed to cool.
  • the various sections of the tooling may be dismantled and the completed fastener 10 may be removed from the die.
  • Some trimming of the head 12 may be required to remove flash and excess material in order to achieve the precise head dimensions required.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

Dispositif de fixation en matériau composite comportant une partie de tête (12), une partie de queue (16) et interposée entre celles-ci une tige cylindrique (14). Tandis que les fibres (30) se trouvant dans les parties de tête et de queue ont été déformées de leur orientation droite initiale pendant le processus de formation, les fibres se trouvant dans la partie de tige restent droites afin d'améliorer la résistance au cisaillement du dispositif de fixation. Ledit dispositif de fixation (10) est formé par refoulement à chaud des fils et de la tête, tout en maintenant la tige relativement froide, bien au-dessous du point de fusion du liant composite. Ledit dispositif de fixation peut être formé à l'aide d'un dispositif comportant un moule de tête (102), un moule de fils (120), un moyen permettant de chauffer sélectivement les extrémités de queue et de tête de l'ébauche avant de leur appliquer une compression, ainsi qu'un moyen permettant de conserver la tige au-dessous de la température à laquelle elle se déforme.
PCT/US1990/004803 1989-08-23 1990-08-22 Dispositf de fixation composite ameliore ainsi que son procede et son appareil de fabrication WO1991002906A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US39765989A 1989-08-23 1989-08-23
US397,659 1989-08-23

Publications (1)

Publication Number Publication Date
WO1991002906A1 true WO1991002906A1 (fr) 1991-03-07

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996019336A1 (fr) * 1994-12-19 1996-06-27 Amsler, Peter Procede de fabrication de composants en matieres thermoplastiques renforcees par des fibres et composants fabriques selon ce procede
DE202010015746U1 (de) * 2010-11-23 2011-12-05 Thomas Hausmann Verbindungsvorrichtung zum Verbinden von zwei vorzugsweise plattenartigen Teilen sowie Nadel mit integriertem Widerlagerhaken für derartige Verbindungsvorrichtungen
DE102013001144A1 (de) * 2013-01-23 2014-07-24 Thomas Hausmann Heftnadel aus faserverstärktem Kunststoff für eine Verbindungsvorrichtung zum temporären Verbinden von wenigstens zwei vorzugsweise plattenartigen Teilen sowie Verfahren zur Herstellung der Heftnadel
DE102013001145A1 (de) * 2013-01-23 2014-07-24 Thomas Hausmann Heftnadel aus Kunststoff, insbesondere aus einem faserverstärken Kunststoff, für eine Verbindungsvorrichtung zum temporären Verbinden von wenigstens zwei vorzugsweise plattenartigen Teilen
US20200378430A1 (en) * 2017-12-12 2020-12-03 Hardlock Industry Co., Ltd. Member having screw thread made from carbon fiber-reinforced composite material

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2901455A (en) * 1954-08-09 1959-08-25 Union Carbide Corp Molding composition comprising synthetic resin and metallic filaments, articles molded therefrom and method of making same
US2949054A (en) * 1954-07-19 1960-08-16 Glastic Corp Threaded shaft of glass fiber reinforced plastic
GB1155708A (en) * 1965-06-25 1969-06-18 Hans Heumann Improvements in or relating to Composite Materials
GB1364076A (en) * 1972-08-29 1974-08-21 British Aircraft Corp Ltd Structural materials
US4362042A (en) * 1980-10-01 1982-12-07 The Lamson & Sessions Co. Method of forming a fastener
US4473738A (en) * 1981-10-05 1984-09-25 Dayton Superior Corporation Method and apparatus for hot forming a polygonal head on a snap tie rod
US4863330A (en) * 1987-07-15 1989-09-05 Northrop Corporation Composite fastener and method of manufacture

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2949054A (en) * 1954-07-19 1960-08-16 Glastic Corp Threaded shaft of glass fiber reinforced plastic
US2901455A (en) * 1954-08-09 1959-08-25 Union Carbide Corp Molding composition comprising synthetic resin and metallic filaments, articles molded therefrom and method of making same
GB1155708A (en) * 1965-06-25 1969-06-18 Hans Heumann Improvements in or relating to Composite Materials
GB1364076A (en) * 1972-08-29 1974-08-21 British Aircraft Corp Ltd Structural materials
US4362042A (en) * 1980-10-01 1982-12-07 The Lamson & Sessions Co. Method of forming a fastener
US4473738A (en) * 1981-10-05 1984-09-25 Dayton Superior Corporation Method and apparatus for hot forming a polygonal head on a snap tie rod
US4863330A (en) * 1987-07-15 1989-09-05 Northrop Corporation Composite fastener and method of manufacture

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996019336A1 (fr) * 1994-12-19 1996-06-27 Amsler, Peter Procede de fabrication de composants en matieres thermoplastiques renforcees par des fibres et composants fabriques selon ce procede
AU700281B2 (en) * 1994-12-19 1998-12-24 Sepitec Foundation Process for manufacturing components made of fibre-reinforced thermoplastic materials and components manufactured by this process
CN1078128C (zh) * 1994-12-19 2002-01-23 Otg斯特·盖伦股份公司 用于制造纤维加强热塑性塑料构件的方法
DE202010015746U1 (de) * 2010-11-23 2011-12-05 Thomas Hausmann Verbindungsvorrichtung zum Verbinden von zwei vorzugsweise plattenartigen Teilen sowie Nadel mit integriertem Widerlagerhaken für derartige Verbindungsvorrichtungen
DE102013001144A1 (de) * 2013-01-23 2014-07-24 Thomas Hausmann Heftnadel aus faserverstärktem Kunststoff für eine Verbindungsvorrichtung zum temporären Verbinden von wenigstens zwei vorzugsweise plattenartigen Teilen sowie Verfahren zur Herstellung der Heftnadel
DE102013001145A1 (de) * 2013-01-23 2014-07-24 Thomas Hausmann Heftnadel aus Kunststoff, insbesondere aus einem faserverstärken Kunststoff, für eine Verbindungsvorrichtung zum temporären Verbinden von wenigstens zwei vorzugsweise plattenartigen Teilen
US20200378430A1 (en) * 2017-12-12 2020-12-03 Hardlock Industry Co., Ltd. Member having screw thread made from carbon fiber-reinforced composite material
EP3726073A4 (fr) * 2017-12-12 2020-12-16 HARDLOCK INDUSTRY CO., Ltd. Élément ayant un filetage en matériau composite renforcé par des fibres de carbone

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