WO2005051624A2 - Element de raccordement d'un equipement - Google Patents

Element de raccordement d'un equipement Download PDF

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Publication number
WO2005051624A2
WO2005051624A2 PCT/IE2004/000164 IE2004000164W WO2005051624A2 WO 2005051624 A2 WO2005051624 A2 WO 2005051624A2 IE 2004000164 W IE2004000164 W IE 2004000164W WO 2005051624 A2 WO2005051624 A2 WO 2005051624A2
Authority
WO
WIPO (PCT)
Prior art keywords
hole
link member
fibres
mould
commingled
Prior art date
Application number
PCT/IE2004/000164
Other languages
English (en)
Other versions
WO2005051624A3 (fr
Inventor
Conchur O'bradaigh
Original Assignee
Conchur O'bradaigh
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 Conchur O'bradaigh filed Critical Conchur O'bradaigh
Publication of WO2005051624A2 publication Critical patent/WO2005051624A2/fr
Publication of WO2005051624A3 publication Critical patent/WO2005051624A3/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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/0033—Moulds or cores; Details thereof or accessories therefor constructed for making articles provided with holes
    • 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
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
    • B29C43/20—Making multilayered or multicoloured articles
    • B29C43/203—Making multilayered articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/32—Component parts, details or accessories; Auxiliary operations
    • B29C43/36—Moulds for making articles of definite length, i.e. discrete articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • 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
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C7/00—Connecting-rods or like links pivoted at both ends; Construction of connecting-rod heads
    • F16C7/02—Constructions of connecting-rods with constant length
    • F16C7/026—Constructions of connecting-rods with constant length made of fibre reinforced resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3055—Cars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/721—Vibration dampening equipment, e.g. shock absorbers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/737—Articles provided with holes, e.g. grids, sieves

Definitions

  • the present invention relates to a construction of machinery link member of a fibre reinforced thermoplastics composite material having at least one connector hole for reception of a load transmitting element. It also relates to a process for manufacturing such a link element and a mould for use in such a manufacturing process.
  • Such link members are used extensively in all types of machinery.
  • An example is a suspension rocker used in a motorcar, which suspension rocker, for example, may connect together various elements of a rear suspension such as the push rod, anti- roll bar, damper connection, central spring rod and a bearing connection to allow rotation.
  • the dynamic loads applied by some of these elements can be as high as 50 KN in a racing car and the number of cycles imposed on the rocker are of the order of 60,000 cycles.
  • the operating temperature of the rocker can be as high as 150°C.
  • the first group is for lateral wing and empennage structures. These aircraft assemblies contain numerous movables or control surfaces such as spoilers, ailerons, flaps or rudders. Every one of these components needs to be attached to the wing or empennage via hinges and actuators. At present, the attachment points are metallic. If these metal parts were replaced directly with a thermoplastics link machinery member, there would be a weight saving. Moreover, the thermoplastics link member could be integrated into the control surface thereby reducing the weight further by eliminating the need for fasteners or adhesives, and issues associated with dissimilar materials.
  • the second application relates to the centre wing box where the wings are attached to the aircraft fuselage.
  • this highly loaded region comprises a space frame structure with the top and bottom surfaces connected by a lattice of composite struts.
  • the end fittings of these struts have been metallic.
  • the replacement of the metal end fittings with thermoplastic link members would reduce the weight and eliminate issues associated with dissimilar materials.
  • the third area for consideration is aircraft landing gear components such as side stay fittings or gear ribs. At present, these parts are large aluminium or titanium forgings. It has been recognised that weight savings could be achieved if composite materials were used. However, for typical aerospace composite materials, the load introduction points would typically be metallic inserts. This reduces the weight advantage of employing composite materials and, as before, introduces issues associated with dissimilar materials. The use of thermoplastic link members would ensure that any weigh reductions were maximised.
  • the fourth area of application is in aircraft propellers, which are today largely composite structures, adhesively bonded to a metal machined element, which connects the propeller tp the engine.
  • the use of the metal connector adds greatly to the weight and inertia of the propeller.
  • Use of a steered fibre thermoplastic connector would significantly reduce the weight of the entire propeller and improve the performance.
  • a single-piece propeller of thermoplastic composite material is also a possibility.
  • a further weight critical application is for space vehicles. There are many highly loaded brackets and supports were weight has to be minimised.
  • metallic materials have been used as the service temperature conditions exceed the properties of standard composite materials. Thermoplastics composite machinery members could satisfy both the weight and elevated temperature requirements.
  • Such a lightweight connecting element could be advantageous in space launchers.
  • supports, supporting arms, actuators, connectors and other machine elements used in rocket launch engines are today made from steel, for high stiffness and strength, and from aluminium and titanium for lighter weight.
  • the ability to decrease weight in the launcher means that increased payloads can be carried without the use of heavier, more powerful engines.
  • the high expense of titanium can be compensated for by the lighter weight and higher operating temperatures, as compared to aluminium.
  • thermoplastic composite element could be used to reduce weight in such space launcher engines, while providing similar stiffness to steel elements, similar weight savings as titanium, and enhanced temperature resistance, all at a lower cost than titanium.
  • type of fibre employed in the element can be varied between high modulus (and lower strength) and high strength (and lower modulus), as required to match stiffness and strength of the element.
  • thermoset composite materials or fibre-reinforced thermoplastic composite materials for many such applications.
  • thermoplastic composite materials for many such applications.
  • certain problems with the use of these composite materials Firstly, there is considerable difficulty in many of them operating at temperatures of the order of 150°C. Many of them, at this temperature, have long exceeded their glass transition temperature, meaning that their mechanical properties fall off dramatically at that temperature.
  • a further problem is that composite materials suffer badly in performance terms when the machinery link member has connector holes for reception of a load transmitting element. Such "load-bearing holes”, as they will often be referred to hereunder, suffer badly in performance terms, when the holes are simply machined from the carbon-fibre reinforced composite material. Thus, as mentioned above, there is the necessity to use metal inserts. Such link members are often subjected to alternating tensile and compressive loads which leads to further problems. Thus, a link member of a composite material may operate satisfactorily under tension but buckle and distort under compression.
  • a particularly useful form of material is a commingled or co-blended thermoplastic composite yarn, such as has been disclosed in various patent specifications, for example, European Patent Specification No. 0466,618.
  • both the reinforcing fibre for example, carbon, glass or aramid, and the polymer matrix, are in the form of fibres which can be manipulated using standard textile techniques.
  • the resulting preform has the consistency, or feel of a rope, which can easily conform to curved and complex mould contours and is thus particularly suitable for wrapping around the core of a mould when that core is used to form a hole.
  • the polymer fibres melt and flow between the reinforcing fibres, thus expelling air from the preform.
  • link member is used broadly in this specification to cover not just a member connecting for example a driving member and a driven member but also a member linked to only one member i.e. the driver member. However all transmit a load such as an aircraft propeller does.
  • the present invention is directed towards providing a machinery link member of a thermoplastics composite material having at least one connector hole for reception of a load transmitting element, which machinery link member will overcome some of the problems of conventionally constructed machinery link elements of thermoplastic composite material. Further, the invention is directed towards providing a process for manufacturing such a machinery link element of a thermoplastic composite material and finally to a mould for a manufacturing machinery link element.
  • a machinery link member of a fibre reinforced thermoplastics composite material having at least one connector hole for reception of a load transmitting element characterised in that the member comprises: a plurality of sheets of fibre reinforced thermoplastics composite material forming a laminate; and commingled fibres arranged adjacent the periphery of the hole.
  • the commingled fibres arranged around the periphery of the hole add greatly to the strength of the link member and, in many instances, obviate the need for any metallic reinforcing.
  • the commingled fibres arranged around the hole comprise a commingled yarn.
  • the fibres arranged adjacent the hole extend of the order of half of the periphery of the hole.
  • the fibres are adjacent that part of the periphery of the hole under load when a tensile force is exerted on the link member.
  • a sheet of fibre reinforced thermoplastics material comprises unidirectional fibres to form a unidirectional fibre reinforced thermoplastics tape.
  • the tapes may be arranged with the unidirectional fibres oriented relative to each other to form crossing fibres from tape to tape or alternatively the fibres of at least some * of the tapes are aligned at the hole substantially along the axis of the load exerted on the periphery of the hole.
  • the fibres may be one or more of boron, carbon, glass, aramid, para-aramid, ultra- high molecular weight polyethylene (UHMW PE), metal.
  • UHMW PE ultra- high molecular weight polyethylene
  • thermoplastics material may be one or more of PEEK, PEKK, PPS, PEI, PA-6, PA-12, PET, PETI-5, PBT, PP, and PE.
  • the sheet is a woven fabric of commingled yarns.
  • the sheets have different tensile and compressive properties.
  • the invention provides a process for producing a machinery link member of a thermoplastics composite material having at least one connector hole for reception of a load transmitting element comprising not necessarily sequentially in a mould having a hole forming core for the or each hole: laying sheets of fibre reinforced thermoplastics material in the mould; arranging commingled thermoplastics fibres around the or each core; and applying heat and pressure to mould the link member.
  • the sheets may comprise unidirectional fibre reinforced thermoplastics tape with the unidirectional fibres of adjacent tapes oriented to cross each other.
  • the arranging of commingled thermoplastics fibres in the mould comprises laying a commingled yarn around the or each core.
  • the invention provides a mould for carrying out the process comprising a hole forming core of an outer diameter less than that of the subsequent hole which then has to be machined out.
  • a mould for carrying out the process of the invention which comprises a hole forming core substantially semicircular in plan.
  • the upright planar face of the core may be substantially orthogonal to the axis of the application of a subsequent load on the hole and spaced-apart from the part of the subsequent hole under compression.
  • Figs. 1 (a) to 1 (c) are plan views of three test specimens used in accordance with the invention
  • FIGS. 2 and 3 illustrate the results of some tests on the specimens of Fig. 1
  • FIGs. 4 and 5 are perspective views of a composite rear suspension rocker arm, manufactured in accordance with the invention
  • Fig. 6 is a schematic view of portion of a mould used to form the rocker arm
  • Fig. 7 is a plan view showing the orientation of a commingled thermoplastic carbon-fibre yarn in a mould
  • Fig. 8 is a photograph of the layout of the commingled thermoplastic carbon- fibre yarn in the mould
  • Figs. 9(a) to (c) are schematic plan views of carbon-fibre reinforced thermoplastic tapes used in accordance with the invention
  • Fig. 10 is a photograph showing one of the tapes of Figs. 9 in a mould
  • Fig. 11 is a view showing various stress patterns of the rocker arm
  • Fig. 12 illustrates the results of a test on the rocker arm of Figs. 4 and 5.
  • Figs. 13(a) to (c) show the formation of a push rod in accordance with the invention
  • Fig. 14 illustrates some compression tests on the push rod
  • Fig. 15 illustrates some hole tensile strengths on the push rods
  • Fig. 16 diagrammatically illustrates the formation of a hole in a machine link element.
  • PEEK carbon-fibre reinforced polyetheretherketone
  • PEEK is a semi-crystalline thermoplastic polymer which has a glass transition temperature of 145°C. Thus, it can be used at a temperature of 150°C or so, without any serious drop-off in mechanical property.
  • PEEK has a very high melt temperature (343°C) and a high viscosity in the melt, which means it can not be used to liquid mould into a tailored fibre preform, as with more conventional methods.
  • the process according to the invention is to make the part in a press-moulding process, using a combination of unidirectional pre-impregnated tape (in the flat sections of the rocker), with selective use of commingled fibres around the load- bearing holes.
  • the press moulding was obviously done at an elevated temperature.
  • the importance of using the commingled fibres is that testing has shown that their use can increase the tensile strength of a composite load-bearing hole by as much as 30%, as will be described below.
  • Figs. 1 (a) to 1 (c) three types of link member were moulded in a thermoplastics carbon-fibre nylon material.
  • the holes were all to 20.60mm, the diameter of the highest loaded hole in the rocker arm, described below with reference to the other figures.
  • the edge of the hole was located 3.6mm from the outside of the specimen.
  • Seven test specimens were produced. Two were made where the commingled woven fabric was laid up and the hole was machined postproduct ⁇ on. Two more were made where the individual commingled fibres were orientated around the pin and two where a commingled rope fabric was laid around the hole.
  • the final specimen had commingled rope fabric orientated around the outside of the specimen with no pin insert and the hole was then machined out.
  • the specimen layups are shown in the drawings.
  • Figs. 2 and 3 show the full results.
  • FIGs. 4 and 5 there is illustrated the composite rear suspension rocker, indicated generally by the reference numeral 1 , having holes 2, 3, 4 and 5.
  • Fig. 6 shows, in diagrammatic form, a mould 10 having cores 11 for the formation of the rocker arm 1.
  • Fig. 7 shows how commingled yarn is laid around the cores, the yarn is identified by the reference numeral 12 in this drawing.
  • Fig. 8 shows the commingled yarn 12, again laid around the various cores.
  • Fig. 9 there is illustrated sheets of fibre reinforced PEEK forming tapes, indicated generally by the reference numeral 15, with various patterns of layout of the reinforcing, such as, for example, at ⁇ 45°, as shown in Fig. 7(a), ⁇ 20°, as shown in Fig. 7(b) and then at 90° to each other, namely at 0° and 90° in Fig. 7(c).
  • Fig. 10 shows one of the pre-impregnated unidirectional tapes formed laid again in the mould.
  • a plurality of laminated sheets of carbon-fibre reinforced PEEK, namely tapes 15, are laid in the mould 10 and the commingled fibre and thermoplastic yarn 12 is formed around the various cores 11. Then, the mould 10 is subject to heat and pressure, and the rocker arm 1 was formed.
  • Fig. 11 illustrates the stresses experienced by the rocker arm 1 in use in an automobile racing engine and Fig. 12 shows the results of the test on the rocker arm 1.
  • FIG. 13 there is illustrated various push rods, similar in shape to those of Fig. 1 , which were formed using CF/PEEK pre-pregnated.
  • Fig. 13(a) shows commingled CF/PEEK yarn wrapped around a push rod hole and Fig. 13(b) shows commingled CF/PEEK yarn extending into the push rod.
  • Fig. 13(c) shows laminates similar to those of Fig. 9.
  • Table 5 illustrates the test on further push rods of the same construction which were manufactured from 7mm CF/PEEK specimen. It will be seen from Table 4 that the best results were obtained from specimens BB25 and BB26 which had machined holes. These compression tests are illustrated in Fig. 14.
  • Table 4 shows the high tensile strengths achieved using the fibre wrapping illustrated in Fig. 13 (b)
  • Fig. 16 illustrates diagrammatically the formation of the hole in a D-shape, namely, a semi-circular shape. It is proposed that a D-shaped moulded hole as illustrated in Fig 16, with reinforcements of the types shown in Fig. 13. (b) and 13(c) which is subsequently machined as a circular shape, would offer maximum tensile and compressive properties.
  • tape such as illustrated in Fig 13(c) could also be made from what is essentially a woven fabric of false impregnated yarn

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • General Engineering & Computer Science (AREA)
  • Reinforced Plastic Materials (AREA)
  • Laminated Bodies (AREA)
  • Ropes Or Cables (AREA)

Abstract

L'invention porte sur un élément de raccordement d'équipement (1) d'un matériau composite thermoplastique renforcé. Cet élément de raccordement comporte au moins un trou de raccordement (2, 3, 4, 5) pour accueillir un élément de transmission de charge et est constitué d'un stratifié de bandes de feuilles renforcées d'un matériau composite thermoplastique et de fibres mélangées, se présentant souvent sous la forme d'un fil mélangé, ce stratifié se trouvant sur la périphérie des trous (2, 3, 4, 5).
PCT/IE2004/000164 2003-11-27 2004-11-29 Element de raccordement d'un equipement WO2005051624A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IE20030885 2003-11-27
IES2003/0885 2003-11-27

Publications (2)

Publication Number Publication Date
WO2005051624A2 true WO2005051624A2 (fr) 2005-06-09
WO2005051624A3 WO2005051624A3 (fr) 2008-02-14

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IE (2) IE20040797A1 (fr)
WO (1) WO2005051624A2 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007135418A1 (fr) * 2006-05-22 2007-11-29 Advanced Composites Group Limited MatÉriaux de moulage
DE102011006917A1 (de) * 2011-04-07 2012-10-31 Bayerische Motoren Werke Aktiengesellschaft Motortragbock
CN103591125A (zh) * 2013-11-19 2014-02-19 李赵和 一种驱动摇脚
EP3284570A4 (fr) * 2015-04-14 2018-12-05 Mitsubishi Gas Chemical Company, Inc. Procédé de fabrication d'un corps moulé
CN112046036A (zh) * 2020-08-12 2020-12-08 威海光威复合材料股份有限公司 复合材料弹射支臂的制造方法
FR3097282A1 (fr) * 2019-06-13 2020-12-18 Skf Aerospace France Pièce de liaison en matériau composite, en particulier pour rotule
US11192582B2 (en) 2018-08-08 2021-12-07 Skf Aerospace France S.A.S. Lightweight suspension upright or knuckle
US11299201B2 (en) 2018-08-08 2022-04-12 Aktiebolaget Skf Lightweight suspension upright or knuckle
CN114407297A (zh) * 2022-01-13 2022-04-29 宁波市益普乐模塑有限公司 一种汽车门板的注塑模具及其注塑工艺

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019004341A1 (de) * 2019-06-23 2020-12-24 Albany Engineered Composites, Inc. Stangenkopf aus thermoplastischem Faser-Kunststoff-Verbund (FKV)

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US4549726A (en) * 1982-10-19 1985-10-29 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Mounting member for mounting an engine or transmission of a motor vehicle
EP0323857A2 (fr) * 1988-01-08 1989-07-12 Fuji Jukogyo Kabushiki Kaisha Lame de flexion pour pale de rotor d'hélicoptère et méthode pour sa fabrication
EP0496695A2 (fr) * 1991-01-15 1992-07-29 United Technologies Corporation Une plaque de flexion unitaire à plusieurs bras en matériaux composites pour rotor à lames et méthode pour la fabriquer
EP0567845A1 (fr) * 1992-04-26 1993-11-03 Institut für Polymerforschung Dresden e.V. Renfort multitaxial formable
EP0818289A2 (fr) * 1996-07-13 1998-01-14 Institut für Polymerforschung Dresden e.V. Multicouche préformée renforcée par des fibres, ayant au moins une partie des renforcements alignées suivant l'axe Z, et procédé pour sa fabrication
US5910361A (en) * 1990-07-13 1999-06-08 Sa Schappe Hybrid yarn for composite materials with thermoplastic matrix and method for obtaining same
EP1308265A1 (fr) * 2001-11-02 2003-05-07 BPW Bergische Achsen Kommanditgesellschaft Pièce moulée allongée de matière composite renforcée par des fibres

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Publication number Priority date Publication date Assignee Title
US4549726A (en) * 1982-10-19 1985-10-29 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Mounting member for mounting an engine or transmission of a motor vehicle
EP0323857A2 (fr) * 1988-01-08 1989-07-12 Fuji Jukogyo Kabushiki Kaisha Lame de flexion pour pale de rotor d'hélicoptère et méthode pour sa fabrication
US5910361A (en) * 1990-07-13 1999-06-08 Sa Schappe Hybrid yarn for composite materials with thermoplastic matrix and method for obtaining same
EP0496695A2 (fr) * 1991-01-15 1992-07-29 United Technologies Corporation Une plaque de flexion unitaire à plusieurs bras en matériaux composites pour rotor à lames et méthode pour la fabriquer
EP0567845A1 (fr) * 1992-04-26 1993-11-03 Institut für Polymerforschung Dresden e.V. Renfort multitaxial formable
EP0818289A2 (fr) * 1996-07-13 1998-01-14 Institut für Polymerforschung Dresden e.V. Multicouche préformée renforcée par des fibres, ayant au moins une partie des renforcements alignées suivant l'axe Z, et procédé pour sa fabrication
EP1308265A1 (fr) * 2001-11-02 2003-05-07 BPW Bergische Achsen Kommanditgesellschaft Pièce moulée allongée de matière composite renforcée par des fibres

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007135418A1 (fr) * 2006-05-22 2007-11-29 Advanced Composites Group Limited MatÉriaux de moulage
CN101489767A (zh) * 2006-05-22 2009-07-22 高级复合材料集团有限公司 模塑材料
CN101489767B (zh) * 2006-05-22 2015-04-29 尤米柯结构材料（德比）有限公司 模塑材料
DE102011006917A1 (de) * 2011-04-07 2012-10-31 Bayerische Motoren Werke Aktiengesellschaft Motortragbock
CN103591125A (zh) * 2013-11-19 2014-02-19 李赵和 一种驱动摇脚
US10828807B2 (en) 2015-04-14 2020-11-10 Mitsubishi Gas Chemical Company, Inc. Method for manufacturing molded article
EP3284570A4 (fr) * 2015-04-14 2018-12-05 Mitsubishi Gas Chemical Company, Inc. Procédé de fabrication d'un corps moulé
US11192582B2 (en) 2018-08-08 2021-12-07 Skf Aerospace France S.A.S. Lightweight suspension upright or knuckle
US11299201B2 (en) 2018-08-08 2022-04-12 Aktiebolaget Skf Lightweight suspension upright or knuckle
US11654963B2 (en) 2018-08-08 2023-05-23 Aktiebolaget Skf Lightweight suspension upright or knuckle
FR3097282A1 (fr) * 2019-06-13 2020-12-18 Skf Aerospace France Pièce de liaison en matériau composite, en particulier pour rotule
CN112046036A (zh) * 2020-08-12 2020-12-08 威海光威复合材料股份有限公司 复合材料弹射支臂的制造方法
CN112046036B (zh) * 2020-08-12 2022-04-19 威海光威复合材料股份有限公司 复合材料弹射支臂的制造方法
CN114407297A (zh) * 2022-01-13 2022-04-29 宁波市益普乐模塑有限公司 一种汽车门板的注塑模具及其注塑工艺
CN114407297B (zh) * 2022-01-13 2022-12-27 宁波市益普乐模塑有限公司 一种汽车门板的注塑模具及其注塑工艺

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