WO1999064224A1 - Procede de realisation d'un panneau de structure composite renforcee du type sandwich a ame alveolaire et panneau realise selon un tel procede - Google Patents
Procede de realisation d'un panneau de structure composite renforcee du type sandwich a ame alveolaire et panneau realise selon un tel procede Download PDFInfo
- Publication number
- WO1999064224A1 WO1999064224A1 PCT/FR1999/001302 FR9901302W WO9964224A1 WO 1999064224 A1 WO1999064224 A1 WO 1999064224A1 FR 9901302 W FR9901302 W FR 9901302W WO 9964224 A1 WO9964224 A1 WO 9964224A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- thermoplastic material
- skins
- stack
- panel
- core
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 33
- 239000002131 composite material Substances 0.000 title claims abstract description 15
- 241001466460 Alveolata Species 0.000 title abstract 4
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 39
- 239000012815 thermoplastic material Substances 0.000 claims abstract description 31
- 238000003825 pressing Methods 0.000 claims abstract description 5
- 230000001413 cellular effect Effects 0.000 claims description 27
- 239000003365 glass fiber Substances 0.000 claims description 16
- 238000004519 manufacturing process Methods 0.000 claims description 16
- 239000010410 layer Substances 0.000 claims description 11
- 239000000463 material Substances 0.000 claims description 9
- 239000004743 Polypropylene Substances 0.000 claims description 8
- 239000004744 fabric Substances 0.000 claims description 8
- -1 polypropylene Polymers 0.000 claims description 8
- 229920001155 polypropylene Polymers 0.000 claims description 8
- 229920000098 polyolefin Polymers 0.000 claims description 6
- 239000011247 coating layer Substances 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 abstract description 8
- 230000002787 reinforcement Effects 0.000 description 28
- 238000012360 testing method Methods 0.000 description 26
- 229920005989 resin Polymers 0.000 description 7
- 239000011347 resin Substances 0.000 description 7
- 239000004753 textile Substances 0.000 description 6
- 239000000835 fiber Substances 0.000 description 5
- 229920001187 thermosetting polymer Polymers 0.000 description 4
- 230000000593 degrading effect Effects 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000004873 anchoring Methods 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000003086 colorant Substances 0.000 description 1
- 238000005094 computer simulation Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000005470 impregnation Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011031 large-scale manufacturing process Methods 0.000 description 1
- 230000004807 localization Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000006386 neutralization reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- 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
- B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
- B29C70/088—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of non-plastics material or non-specified material, e.g. supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
- B29C70/887—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced locally reinforced, e.g. by fillers
-
- 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
- B29D24/00—Producing articles with hollow walls
- B29D24/002—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled
- B29D24/005—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled the structure having joined ribs, e.g. honeycomb
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
- B32B5/022—Non-woven fabric
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2305/00—Condition, form or state of the layers or laminate
- B32B2305/08—Reinforcements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2305/00—Condition, form or state of the layers or laminate
- B32B2305/10—Fibres of continuous length
- B32B2305/20—Fibres of continuous length in the form of a non-woven mat
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2309/00—Parameters for the laminating or treatment process; Apparatus details
- B32B2309/12—Pressure
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1089—Methods of surface bonding and/or assembly therefor of discrete laminae to single face of additional lamina
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24149—Honeycomb-like
Definitions
- the present invention relates generally to composite structure panels of the sandwich type with cellular core, in particular for motor vehicles, and more particularly to a method for producing such a panel with locally reinforced structure. It also relates to a reinforced composite structure panel of the sandwich type. honeycomb core, produced by such a process
- the construction of such panels consists in trapping by gluing or welding a honeycomb core of poor mechanical characteristics between two skins having a thickness much less than that of the honeycomb core but having excellent mechanical characteristics.
- Document FR 2 711 573 belonging to the Applicant discloses a method for producing a composite structure panel of the sandwich type with cellular core, according to which said panel is produced in a single step, by pressing in a cold mold, a stack made up of at least a first skin of stampable reinforced thermoplastic material, of a cellular core of thermoplastic material, of a second skin of stampable reinforced thermoplastic material, and of a first external coating layer of woven or non-woven material woven, said skins being previously heated outside the mold to a softening temperature
- Such a process is particularly advantageous in that it allows in a single operation to generate cohesion between the different layers of composite structure and to conform said panel.
- the panel thus produced retains all the mechanical properties due to the sandwich structure with cellular core.
- Composite structure panels of the sandwich type with cellular core have characteristics of sufficient rigidity making it possible to structurally reinforce mechanical structures subjected to significant stresses without thereby weighing them down excessively. Such panels are then commonly used in the shipbuilding sectors, aeronautics and rail
- thermosetting resins reinforced with glass fibers In order to give and maintain the desired shape of said panels, the glass fibers and the thermosetting resin appearing under the form of prepregs, are deposited layer by layer in a mold, then are then brought to high temperatures to definitively polyme ⁇ ser the resin
- the molds used can include a punch or a die or a punch and a die
- the reinforcing plies are unidirectional mats or fabrics of glass, carbon or natural fibers embedded in a thermosetting resin, with an orientation which is determined by the orientation of the stresses II are cut according to a pattern using machines special for example a water jet cutting machine
- the reinforcement plies are arranged layer by layer in a mold, manually or using a robot with a specific orientation for each ply
- the different layers deposited in the mold are pressed in said mold by creating a vacuum therein.
- the creation of the vacuum allows the materials to be pressed against the matrix or the punch and allows the excess resin to be evacuated.
- the desired shape is thus obtained. with the best possible impregnation of the fibers by the resin
- This so-called layering technique and in particular the draping operation, is characterized by a very low level of automation, and a very large share of labor. Thanks to the concept of localization of rigidity, this technique allows '' achieve high performance levels of the parts thus produced, it requires rigorous quality monitoring
- the present invention therefore proposes a new method for producing in a simple and economical manner panels of reinforced composite structure of the sandwich type with cellular core, which can be implemented at high rate compatible with the production rates of the automotive industry while allowing the production of parts adapted to structural applications which require their rigidity without overweight and without particular additional cost.
- the invention proposes a method for producing a reinforced composite structure panel of the sandwich type with cellular core, characterized in that:
- At least one stack is made of at least one first skin made of reinforced thermoplastic material, a first reinforcing ply made of reinforced thermoplastic material, a cellular core made of thermoplastic material, a second reinforcing ply made of reinforced thermoplastic material, a second skin made of reinforced thermoplastic material, the first and second reinforcing plies having a surface area smaller than that of the first and second skins and being positioned symmetrically with respect to the plane formed by the cellular core, at determined locations against said skins, - we pre -assemble the stack,
- the pre-assembled stack is heated in an oven, and
- - Said panel is formed by pressing said heated stack in a cold mold under a pressure between 1 and 3.10 6 Pa.
- Said stack may include at least one other pair of third and fourth reinforcing plies, each having a surface area smaller than that of the first and second skins, and arranged symmetrically on either side of the cellular core in other places determined against said skins, the stack can comprise three pairs of reinforcing plies arranged in a determined manner, symmetrically on either side of the cellular core,
- the stack can also include at least one layer of external coating of woven or nonwoven material disposed on the second skin and optionally another layer of external coating of woven or nonwoven material placed under the first skin in order of stacking.
- the panel forming pressure is between 15 and 20.10 5 Pa.
- the first and second skins have a forming temperature of between 160 and 200 degrees approximately
- the first and second skins are constituted by a fabric or a mat of glass fibers and a thermoplastic material.
- the reinforcing plies are also constituted by a fabric or a mat of glass fibers of a thermoplastic material.
- the first and second skins preferably have a grammage of glass fibers different from that of the reinforcing plies.
- thermoplastic material used is a polyolefin, preferably polypropylene.
- the honeycomb core has an open cell structure of the tubular structure or honeycomb type mainly made of polyolefin and preferably polypropylene
- the invention also provides a reinforced composite structure panel of the sandwich type with cellular core, produced according to the aforementioned method.
- Figure 1 is a schematic side view of the stack produced in accordance with the method according to the invention.
- Figure 1 there is shown a stack produced during a first step of a method for producing a reinforced composite structure panel of the sandwich type with cellular core
- This stack here successively comprises a first skin 110 made of reinforced thermoplastic material, a first reinforcing ply 120 made of reinforced thermoplastic material, a honeycomb core 130 made of thermoplastic material, a second reinforcing ply 140 made of reinforced thermoplastic material, and a second skin 150 made of reinforced thermoplastic material
- it comprises an outer coating layer 161 of woven or nonwoven material disposed on the second skin 150 and another outer coating layer 162 of woven or nonwoven material placed under the first skin 110 in the stacking order.
- the external covering layers 161, 162 can be a felt or a carpet
- the first and second reinforcing plies 120, 140 have a surface area smaller than that of the first and second skins 110, 150 and are positioned symmetrically with respect to the plane formed by the cellular core at determined locations against said skins. More particularly, they are positioned at predetermined locations on the panel where it is expected to undergo the most intense mechanical stresses.
- the stack can comprise another pair of third and fourth reinforcing plies, each having a surface area smaller than that of the first and second skins, and arranged symmetrically on either side of the core. alveolar at other determined locations against said skins.
- the stack may include three pairs of reinforcing plies arranged in a determined manner, symmetrically on either side of the cellular core. According to other variants, the stack can include an even greater number of reinforcing plies.
- the first and second skins 110, 150 consist of a fabric or a mat of glass fibers and of a thermoplastic material.
- the reinforcing plies 120, 140 also consist of a fabric or a mat of glass fibers and of a thermoplastic material.
- the thermoplastic material used is a polyolefin and preferably polypropylene.
- the first and second skins 110, 150 have a grammage of glass fibers different from that of the reinforcing plies 120, 140.
- the materials used for the first and second skins as well as the reinforcing plies of the stack are for example: a 4x1 textile which includes four warp threads for a weft thread with 800 filaments / threads, an 8x2 textile which also includes four warp threads for a weft thread, each thread being composed of 1600 filaments, a balanced textile which includes as many weft threads as warp threads, a long fiber mat whose directions are balanced, a long fiber mat with a preferential orientation for 80% of the long fibers (directional mat ) or even a unidirectional.
- the grammages available are for example for a 4x1 textile: 400 g / m 2 , for an 8x2 textile: 900 g / m 2 , or 1350 g / m 2 , for a balanced textile: 710 g / m 2 or 1420 g / m 2 , for a balanced mast: 1500 g / m 2 , for a directional mast: 500g / m 2 and for a unidirectional: 800 g / m 2 .
- the honeycomb core 130 has here, advantageously an open cell structure of the tubular structure or honeycomb type, mainly consisting of polyolefin and preferably polypropylene.
- the stack is pre-assembled. Then, the pre-assembled stack is heated in an oven.
- the pre-assembled stack is heated in such a way that the first and second skins 110, 150 of the stack have a forming temperature of between 160 and 200 degrees approximately.
- the heating temperatures of the pre-assembled stack are higher than the degradation temperature of the polypropylene constituting the matrix of the first and second skins as well as of the reinforcing plies and of the cellular core. , without surprisingly degrading the mechanical properties of the panel thus formed.
- the heating temperature of the pre-assembled stack according to the method according to the invention is between a low temperature allowing the welding between the first and second skins and the cellular core, in a time compatible with large-scale production. series without consequent weakening of the honeycomb core of said stack, and a maximum temperature avoiding too rapid degradation of the polypropylene.
- reinforcing plies in the stack to be thermoformed to produce the reinforced structure panel according to the method according to the invention is possible because this method has sufficient heating capability to successfully weld the first and second skins d '' different thicknesses (due to the addition of reinforcements).
- the amount of heat transmitted through the skins and the cellular core is inversely proportional to the thickness of the skin, with identical types of reinforcements and colors.
- the heating time of the stack pre -assembled is between 70 and 75 seconds
- said panel is formed by pressing said heated stack in a cold mold under a pressure between 1 and 3.10 6 Pa
- the panel forming pressure is between 15 and 20 10 5 Pa
- the method according to the invention comprises few operations which are simple and quick to perform
- the panels produced according to the invention have a locally optimized rigidity without being overweight compared to the panels having no reinforcing plies, nor an additional manufacturing cost
- rear seat backrests of motor vehicles and in particular the rear seat backrests with on-board belts.
- Such a rear seat backrest comprises in its lower part two articulation hinges on the vehicle body, these two hinges are positioned on the outside and inside sides of the backrest and allow it to be folded forward, and in a region located at the top on the outer side of said hinge backrest, an anchor point thereof on the vehicle body for its maintenance in vertical position
- this rear seat backrest structure an anchor point located in the upper part of the internal side of said backrest, opposite to its point of attachment to the body of the vehicle to allow the installation in the middle rear seat of a three-point seat belt in the same way as for the right and left rear seats
- FIGS. 2a to 2g various test specimens have been shown corresponding to 2/3 rear bench seatbacks, with on-board belt, which include the aforementioned points of articulation, attachment and anchoring, references successively A to D
- the different test pieces shown in FIGS. 2a to 2g were produced according to the method according to the invention, and include a number of pairs of different reinforcement plies.
- the test piece shown in FIG. 2a comprises a single pair of reinforcement plies SE. extending between the upper external attachment point A_on the bodywork and the traction point of the belt D,
- the test piece shown in FIG. 2b comprises a single pair of reinforcement plies IE extending between the external articulation hinge B and the point of traction of the belt D
- the test piece shown in FIG. 2c comprises a single pair of reinforcement plies II extending between the internal articulation hinge C and the point of traction of the belt D
- the test piece shown in FIG. 2d comprises two pairs of reinforcement plies, a first pair of reinforcement plies SE extending between the upper external attachment point A on the carriage and the point of traction of the belt.
- the test piece shown in FIG. 2e comprises two pairs of reinforcement plies a, a first pair of reinforcement plies IE extending between the external articulation hinge B and the point of traction of the belt D, and a second pair of reinforcement plies II between the internal articulation hinge C and the point of traction of the belt D
- the test piece shown in FIG. 2f comprises two pairs of reinforcement plies, a first pair of reinforcement plies SE extending between the upper external attachment point A_ and the traction point of the belt D, and a second pair of reinforcement plies II extending between the internal articulation hinge C and the point of traction of the belt D
- the test piece shown in FIG. 2g comprises three pairs of reinforcement plies, a first pair of reinforcement plies SE extending between the external attachment point A and the point of traction of the belt D, a second pair of reinforcement plies IE extending between the external articulation hinge B and the point of traction of the belt D, and a third pair of reinforcement plies II extending between the internal articulation hinge C and the point of belt pull D
- a first sensor is fixed on the frame of hoist support, on the one hand and at the traction point on the back of the test piece to be tested on the other hand II must measure the displacement of the traction point
- a second sensor is fixed on the hoist support frame on the one hand, and at the free corner on the back of the test piece to be tested on the other hand, it must measure the displacement of the non-fixed free corner of the structure
- a force sensor is inserted between the hook of the hoist and the test piece to be tested so as to measure the tensile force
- test pieces The results of tests on the various abovementioned test pieces have shown that the use of a single pair of reinforcing plies did not make it possible to significantly improve the results of the test of test pieces formed by stacks without reinforcing plies.
- test pieces comprising two pairs of reinforcement plies seem to clearly improve the test results. The most obvious improvement is the production of three pairs of reinforcement plies (see test tube in figure
- a back seat backrest achieves with skins of grammage of glass fibers equal to 1420 g / m 2 with reinforcement plies made in unidirectional with a grammage of glass fibers equal to 800 g / m 2 has a weight of 1.31 kg and a cost of 33.32 FF
- reinforcements according to the present invention makes it possible to reduce both the cost and the weight of the part for equivalent mechanical characteristics.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Textile Engineering (AREA)
- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99923657A EP1001875B1 (fr) | 1998-06-05 | 1999-06-03 | Procede de realisation d'un panneau de structure composite renforcee du type sandwich a ame alveolaire et panneau realise selon un tel procede |
DE69902735T DE69902735T2 (de) | 1998-06-05 | 1999-06-03 | Verfahren zur herstellung einer sandwichverbundplatte mit wabenförmigem kern und eine so hergestellte platte |
US09/485,142 US6537413B1 (en) | 1998-06-05 | 1999-06-03 | Method of making a reinforced composite panel of the cellular-core sandwich type, and a panel obtained by performing such a method |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9807075A FR2779379B1 (fr) | 1998-06-05 | 1998-06-05 | Procede de realisation d'un panneau de structure composite renforcee du type sandwich a ame alveolaire et panneau realise selon un tel procede |
FR98/07075 | 1998-06-05 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1999064224A1 true WO1999064224A1 (fr) | 1999-12-16 |
Family
ID=9527048
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR1999/001302 WO1999064224A1 (fr) | 1998-06-05 | 1999-06-03 | Procede de realisation d'un panneau de structure composite renforcee du type sandwich a ame alveolaire et panneau realise selon un tel procede |
Country Status (5)
Country | Link |
---|---|
US (1) | US6537413B1 (fr) |
EP (1) | EP1001875B1 (fr) |
DE (1) | DE69902735T2 (fr) |
FR (1) | FR2779379B1 (fr) |
WO (1) | WO1999064224A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10200750A1 (de) * | 2002-01-10 | 2003-07-24 | Peguform Gmbh & Co Kg | Fahrzeugdach aus transparentem oder transluzentem Kunststoff |
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US6843525B2 (en) * | 2001-10-30 | 2005-01-18 | Patent Holding Company | Reinforced composite vehicle load floor of the cellular core sandwich-type |
DE10200750A1 (de) * | 2002-01-10 | 2003-07-24 | Peguform Gmbh & Co Kg | Fahrzeugdach aus transparentem oder transluzentem Kunststoff |
DE10200750B4 (de) * | 2002-01-10 | 2006-10-26 | Peguform Gmbh | Fahrzeugdach aus transparentem oder transluzentem Kunststoff |
Also Published As
Publication number | Publication date |
---|---|
DE69902735T2 (de) | 2003-08-07 |
EP1001875A1 (fr) | 2000-05-24 |
FR2779379B1 (fr) | 2000-08-25 |
US6537413B1 (en) | 2003-03-25 |
DE69902735D1 (de) | 2002-10-10 |
EP1001875B1 (fr) | 2002-09-04 |
FR2779379A1 (fr) | 1999-12-10 |
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