EP1260293A1 - Verfahren zur Herstellung einer Metall-Matrix-Composite Rohr-Platte Anordnung - Google Patents
Verfahren zur Herstellung einer Metall-Matrix-Composite Rohr-Platte Anordnung Download PDFInfo
- Publication number
- EP1260293A1 EP1260293A1 EP02291102A EP02291102A EP1260293A1 EP 1260293 A1 EP1260293 A1 EP 1260293A1 EP 02291102 A EP02291102 A EP 02291102A EP 02291102 A EP02291102 A EP 02291102A EP 1260293 A1 EP1260293 A1 EP 1260293A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- tube
- fibrous
- preform
- mold
- cavity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D19/00—Casting in, on, or around objects which form part of the product
- B22D19/14—Casting in, on, or around objects which form part of the product the objects being filamentary or particulate in form
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D19/00—Casting in, on, or around objects which form part of the product
- B22D19/04—Casting in, on, or around objects which form part of the product for joining parts
Definitions
- the invention relates to a manufacturing process. of a structure comprising at least one tube and at least a plate of composite material with a metal matrix, assembled together.
- Such a method can in particular be used for the manufacture of structures intended for the space industry, such as structures in mesh used to support optical instruments on-board space telescopes, or others.
- optical instruments are on board spacecraft such as space telescopes, these instruments are usually mounted on lattice structures.
- Lattice structures include usually one or more parallel plates between them and a plurality of tubes connecting these plates in different directions, so that provide the whole with great stability dimensional.
- tubes and plates that make up the structures in mesh supporting the optical instruments which equip spacecraft must present suitable mechanical characteristics, as well as mass as small as possible. It leads to frequently the designers of these spacecraft to use matrix composite materials metal to make the tubes and plates of lattice structures.
- the tubes and the plates are usually made separately, by injection of a metal alloy into a mold containing a preform of woven fibers.
- the tubes and the plates are then assembled according to different techniques such as gluing, screwing or brazing.
- the subject of the invention is precisely a process for manufacturing a structure comprising at least at least one tube and at least one material plate composite with metallic matrix, not having the disadvantages of existing processes and allowing in particular not to introduce instability thermomechanical at the junction between the tube and the plate.
- a shaped mandrel complementary to the inside of the tube.
- the third fibrous preform is produced in the form of two half shells, each of which has the shaped like a half crown.
- the metal is injected or the metal alloy in the mold cavity substantially along a longitudinal axis of the first fibrous preform, on one side of the second preform fibrous opposite to the first fibrous preform.
- first, second and third fibrous preforms by draping, so that some of the fibers of each of the fiber preforms is substantially aligned when the preforms are placed in the mold.
- the embodiment illustrated as example in the single figure concerns the manufacturing of a matrix composite material structure metallic comprising a single hollow tube and a single plate.
- the invention is not limited to the manufacture of this type of structure but concerns, in general, the manufacture of any structure in metal matrix composite material comprising a or more tubes and one or more plates assembled together.
- the invention can be used as well when the tubes are hollow, like this is usually the case, only when the tubes are full, i.e. when replaced by rods.
- the tube and the plate of the structure to be manufactured are made of in one piece, by molding, incorporating into the structure an annular reinforcement piece which surrounds the part of the tube adjacent to the plate and also forms a single room with structure.
- the structure in composite material with metallic matrix is made in a single mold 10 formed of two parts 12 and 14.
- the first part 12 of the mold 10 ensures the manufacture of the tube and the second part 14 ensures the manufacture of the plate.
- the mold 10 internally delimits a cavity 16 of which a first portion 18 is formed in the part 12 of the mold and a second portion 20 of which is formed in part 14 of the mold.
- the first portion 18 of the cavity 16 has a shape complementary to the shape outside of the tube that one wishes to manufacture.
- the portion of cavity 18 has the shape a cylindrical recess whose diameter is equal to outer diameter of the tube and whose length is equal to the length of the part of the tube located at the exterior of the surrounding annular reinforcement piece the tube in its junction zone with the plate.
- the second portion 20 of the cavity 16 has a shape complementary to the shape outside of the plate that you want to make and the annular reinforcement piece which surrounds the tube in its junction zone with the plate.
- the joint plane 22 between the two portions 18 and 20 of the cavity 16 is is thus located at the face of the part annular reinforcement opposite the plate.
- first fibrous preform 24 which has substantially the shape of the tube to be manufactured
- second fibrous preform 26 which has substantially the shape of the plate to be manufactured
- third fibrous preform 28 which has substantially the shape of the annular reinforcement piece surrounding the tube in its area adjacent to the plate.
- first preform fibrous 24 is placed in the cavity portion 18 and protrudes through one of its ends in the second portion of cavity 20.
- the second preform fibrous 26 is placed in the second portion of cavity 20 so that the aforementioned end of the first fibrous preform 24 is in abutment against she.
- the third fibrous preform 28 is also placed in the second portion of cavity 20, around the projecting part of the first preform fibrous 24 and pressing against the second preform fibrous 26.
- the third fibrous preform 28 is preferably produced under the shape of two half shells each of which has the shape half a crown.
- Each of the fiber preforms 24, 26 and 28 consists of long fibers whose nature and the orientation are chosen according to the characteristics mechanical properties desired for the structure to be manufactured. These choices are made by those skilled in the art by the simple implementation of his usual knowledge. It is therefore not part of the invention.
- the orientation of the fibers in the different preforms 24, 26 and 28 are advantageously determined so that some of the fibers of each of the preforms are substantially aligned from one preform to another when all the preforms are placed in the mold cavity 16.
- each of the preforms 24, 26 and 28 the fibers are joined together by all appropriate means.
- An assembly technique consists particular to drape over each other a certain number of dry fabrics made in fibers desired, to bind the fabrics together, for example by sewing, then compact the preform thus obtained, in order to obtain the desired fiber content.
- the metal or the metal alloy is injected into the cavity 16 by an orifice 32 formed in the part 14 of the mold 10. From more precisely, the orifice 32 opens into the portion of cavity 20, along the longitudinal axis common to the portion of cavity 18 and at the first preform fibrous 24, on one side of the second preform fibrous 26 opposite the first fibrous preform 24 and to the cavity portion 18.
- the injection parameters are determined by those skilled in the art taking into account in particular the thermal inertia and the geometry of the structure. This data comes under the simple implementation of his knowledge usual. They are therefore not part of the invention.
- the mold 10 is opened.
- the structure extracted from the mold is a monolithic piece which seamlessly integrates the tube, plate and reinforcement piece.
- the structure obtained has a lower mass than the structures of the prior art in which the tube and the plate are assembled by screwing.
- the manufacture of the structure is ensured by a simple molding operation, i.e. that the implementation of the method according to the invention is significantly simpler than that of the prior art that the tube and the plate are assembled by gluing or welding.
- the structure to be manufactured includes several tubes and / or several plates, the mold and the fibrous reinforcements are changed to result.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Golf Clubs (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0106882 | 2001-05-25 | ||
FR0106882A FR2825041B1 (fr) | 2001-05-25 | 2001-05-25 | Procede de fabrication d'une structure tube-plaque en materiau composite a matrice metallique |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1260293A1 true EP1260293A1 (de) | 2002-11-27 |
EP1260293B1 EP1260293B1 (de) | 2007-01-17 |
Family
ID=8863646
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291102A Expired - Lifetime EP1260293B1 (de) | 2001-05-25 | 2002-05-02 | Verfahren zur Herstellung einer Metall-Matrix-Composite Rohr-Platte Anordnung |
Country Status (4)
Country | Link |
---|---|
US (1) | US6595264B2 (de) |
EP (1) | EP1260293B1 (de) |
DE (1) | DE60217575T2 (de) |
FR (1) | FR2825041B1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004039306A1 (de) * | 2004-08-12 | 2006-02-23 | Bayerische Motoren Werke Ag | Verfahren zum Herstellen eines Verbundgussteils |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7141310B2 (en) * | 2002-04-17 | 2006-11-28 | Ceramics Process Systems Corporation | Metal matrix composite structure and method |
US6884522B2 (en) * | 2002-04-17 | 2005-04-26 | Ceramics Process Systems Corp. | Metal matrix composite structure and method |
US9417013B2 (en) * | 2010-11-12 | 2016-08-16 | Toyota Motor Engineering & Manufacturing North America, Inc. | Heat transfer systems including heat conducting composite materials |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4671336A (en) * | 1984-05-03 | 1987-06-09 | Kabushiki Kaisha Toyoda Jidoshokki Seisakusho | Method for manufacturing a fiber reinforcement body for a metal matrix composite |
EP0513685A1 (de) * | 1991-05-08 | 1992-11-19 | Schmitt, Theodor, Dipl.-Ing. | Verfahren zum Tränken von porösen, faserigen oder pulver- förmigen Werkstoffen mit der Schmelze eines Metalls oder einer Legierung |
EP0610020A1 (de) * | 1993-02-05 | 1994-08-10 | Clifford Youngs | Metallische Schiebetore und Zäune und Herstellungsverfahren |
EP0882534A1 (de) * | 1997-06-02 | 1998-12-09 | Toyota Jidosha Kabushiki Kaisha | Verfahren zum Herstellen eines Zylinderblockes einer Brennkraftmaschine |
US6048432A (en) * | 1998-02-09 | 2000-04-11 | Applied Metallurgy Corporation | Method for producing complex-shaped objects from laminae |
US6216763B1 (en) * | 1998-10-05 | 2001-04-17 | R. J. Tower Corporation | Cast node and method for casting nodes |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5542471A (en) * | 1993-11-16 | 1996-08-06 | Loral Vought System Corporation | Heat transfer element having the thermally conductive fibers |
EP0739668A2 (de) * | 1995-04-26 | 1996-10-30 | Ryobi Ltd. | Zylinderblock und Zylinderbuchse und Verfahren zur deren Herstellung |
AUPN496195A0 (en) * | 1995-08-22 | 1995-09-14 | Aci Operations Pty. Limited | Improved process for mould replacement |
-
2001
- 2001-05-25 FR FR0106882A patent/FR2825041B1/fr not_active Expired - Fee Related
-
2002
- 2002-05-02 EP EP02291102A patent/EP1260293B1/de not_active Expired - Lifetime
- 2002-05-02 DE DE60217575T patent/DE60217575T2/de not_active Expired - Lifetime
- 2002-05-24 US US10/153,810 patent/US6595264B2/en not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4671336A (en) * | 1984-05-03 | 1987-06-09 | Kabushiki Kaisha Toyoda Jidoshokki Seisakusho | Method for manufacturing a fiber reinforcement body for a metal matrix composite |
EP0513685A1 (de) * | 1991-05-08 | 1992-11-19 | Schmitt, Theodor, Dipl.-Ing. | Verfahren zum Tränken von porösen, faserigen oder pulver- förmigen Werkstoffen mit der Schmelze eines Metalls oder einer Legierung |
EP0610020A1 (de) * | 1993-02-05 | 1994-08-10 | Clifford Youngs | Metallische Schiebetore und Zäune und Herstellungsverfahren |
EP0882534A1 (de) * | 1997-06-02 | 1998-12-09 | Toyota Jidosha Kabushiki Kaisha | Verfahren zum Herstellen eines Zylinderblockes einer Brennkraftmaschine |
US6048432A (en) * | 1998-02-09 | 2000-04-11 | Applied Metallurgy Corporation | Method for producing complex-shaped objects from laminae |
US6216763B1 (en) * | 1998-10-05 | 2001-04-17 | R. J. Tower Corporation | Cast node and method for casting nodes |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004039306A1 (de) * | 2004-08-12 | 2006-02-23 | Bayerische Motoren Werke Ag | Verfahren zum Herstellen eines Verbundgussteils |
Also Published As
Publication number | Publication date |
---|---|
DE60217575T2 (de) | 2007-10-18 |
US20020174969A1 (en) | 2002-11-28 |
EP1260293B1 (de) | 2007-01-17 |
DE60217575D1 (de) | 2007-03-08 |
US6595264B2 (en) | 2003-07-22 |
FR2825041B1 (fr) | 2003-08-29 |
FR2825041A1 (fr) | 2002-11-29 |
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