CA1286582C - Method and apparatus for forming corrugated materials using magnetic memory cores - Google Patents
Method and apparatus for forming corrugated materials using magnetic memory coresInfo
- Publication number
- CA1286582C CA1286582C CA000518837A CA518837A CA1286582C CA 1286582 C CA1286582 C CA 1286582C CA 000518837 A CA000518837 A CA 000518837A CA 518837 A CA518837 A CA 518837A CA 1286582 C CA1286582 C CA 1286582C
- Authority
- CA
- Canada
- Prior art keywords
- core
- base layer
- layer
- overlying
- layers
- 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.)
- Expired - Lifetime
Links
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
- B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
- B29C33/48—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
-
- 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
- B29C61/00—Shaping by liberation of internal stresses; Making preforms having internal stresses; Apparatus therefor
-
- 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
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
-
- 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
- B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
- B29C43/12—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies using bags surrounding the moulding material or using membranes contacting the moulding material
Abstract
ABSTRACT OF THE DISCLOSURE
A base layer of fabric sheets impregnated with bonding material is deposited on a mold form. A plurality of parallel spaced hollow cores, fabricated from memory metal alloy, are positioned on the base layer. An overlying layer is then positioned over the cores and the base layer, the overlying layer also being impregnated with bonding material. The assembly is subjected to heat and temperature to cure all the layers. The core is then subjected to a critical temperature causing the core to shrink and permitting its easy removal. The result is a base layer to which the overlying layer is bonded, the overlying layer characterized by corrugations which stiffen the entire structure and increase its structural strength.
A base layer of fabric sheets impregnated with bonding material is deposited on a mold form. A plurality of parallel spaced hollow cores, fabricated from memory metal alloy, are positioned on the base layer. An overlying layer is then positioned over the cores and the base layer, the overlying layer also being impregnated with bonding material. The assembly is subjected to heat and temperature to cure all the layers. The core is then subjected to a critical temperature causing the core to shrink and permitting its easy removal. The result is a base layer to which the overlying layer is bonded, the overlying layer characterized by corrugations which stiffen the entire structure and increase its structural strength.
Description
6~17 PT-T
365~
1 METHOD A~D APPARATUS FOR FORMING CORRUGATED
MAT~RIALS USING MAGNETIC MEMORY CORES
The present invention is related to molding apparatus and more particularly to a method and apparatus for forming corruyated or stiffened sheet materials by utilizing memory cores which are easily removable after molding.
In order to increase the strength and rigidity of sheet materials, corrugations are often formed in the material. This is often the case with aircraEt skin panels wherein the interior surface of the panels has integrally formed corrugations for achieving requisite stiffness and strenyth.
In recent years, increasing use has been made of composite resin-impregnated ~abrics, including graphite, Kevlar*and fiberglass fibers to achieve requisite panel strength at reduced weights and radar cross sectionO In order to form such composite panels, a number of resin-impregnated sheets, constituting a base layer, are positioned over a mold form. Cores are then positioned on top of the base layer, and subsequently, an overlying layer of composite sheets 's positioned over the core. The entixe assembly is loaded into an autoclave where heat and pressure is applied to cause curing o~ the resin in the composite material and achieve superior bonding between the various sheets of the overlying layer and base layer.
A principal disadvantage of the prior art lies in the use of cores which stick to the composite sheets after curing. ~s a result, their attempted removal may weaken or destroy the rormed layers.
.
* Trade ~ark .
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:
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:
365~32 1 The present invention avoids this problem by utilizing cores fabricated from memory alloys.
The present invention is directed to a metho~ for molding material into corrugated form, including the steps of:
posi-tioning a base layer impregnated with bonding material on a molding form;
positioning at least one core of memory metal alloy on the base layer;
posi-tioning an overlying layer impregnated with bonding material over the base layer and the core;
curing the layers;
subjecting the core to a critical temperature to cause contraction of the core; and removing the core;
whereby the overlying layer is bonded to the base layer and wherein the overlying layer includes corrugations integrally formed therein to stiffin the base layer.
The present invention utilizes cores fabri-cated from memory metal alloys. ~he cores are easily removed after a molding process by subjecting each -core to the critical temperature of the alloys wherein the core contracts in all directions, thereby permitting its simple removal from the molded structure. In summary, after the core is between base and overlying layers of resin-impregnated composite material, core expansion pressure has been applied to the interior of the core thereby initially 3 expanding the dimensions oE the core. ~fter curing, t:he core is subjected to the critical temperature - . .
. ~ : . . ' , : ' . ': . . ' -.: : . . .
- .
.
. .
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l of the memory metals for con-tracting the core i.n pre-paration of its withdrawal. Due to the fact that the core is easily removed, the integrity of the com-posite materials may be maintained and the core reused for subsequent molding cycles.
The above-mentioned advantages of the present invention will be more clearly understood when considered in conjunction with the accompanying drawings in which:
Figure 1 is a perspective view of a prior art aircraEt skin paneli Figure 2 is a perspective view of a memory metal alloy core employed in the present i.nvention;
Figure 3 is a perspective view of an aircraft skin panel in accordance with the present invention;
Figure 4 is a cross-sectional view of a reusable core positioned between two dies which ensure final dimensional accuracy of the die;
Figure 5 is a perspective view of a memory metal alloy mandrel for use in a filament winding ~ process.
Figure 1 illustrates a prior art finished skin panel assembly generally indicated by reference numeral 10, including a base layer 12 bonded to an overlying layer 14 having corrugations 16 formed therealong due to the insertion of parallel spaced cores within channels lg, during a previous molding process. The base layer 12 may form the external skin surface of an aircraft. The corrugations 16 formed in the overlying layer 14 serve as an integrally 3 formed stiffener :Eor the skin. The process Eor fabri-cating the prior skin panel assembly 10 of Figure 1 , .: . - ' ' ,. -. ~ , ' :
.
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--Ds 1 will now be explained. An initial base layer 12, as shown in Figure 3, is deposited on a mold form 20.
A number of tubular metal cores 22 having the shape shown in Figure 2 are positioned in spaced parallel relationship on base layer 12, as indicated in Figure 3. An overlying layer 16 is then deposited on the cores and the base layer 12. The resulting assembly of parts .
is then positioned in an autoclave where heat and pressure are applied, thereby causing excellent bonding of the overlying layer and base layer, due to curing of a resin CompGnent in layers 12 and 1~ which is necessary for the bonding process.
Afterward, the cores 22 must be removed. In conventional fabrication techniques, this presents a difficulty because the cores have a tendency to stick to the base layer 12 and overlying layer 14. As pre-viously mentioned, the removal step may injure these layers, resulting in a decrease of their strength and integrity.
In the case of the present invention, the core is not made from conventional core metal but, rather, from memory metal alloys. After bonding has been completed, the temperature of the autoclave is adjusted so that the critical temperature of the memory metal alloy is reached, thereby resulting in contraction of the core dimensions in all directlons. .
Consequently, the cores may be easily removed and the bonded overlying and base layers lifted from the mold form 20, resulting in the same finished corrugated skin panel assembly 1~ as was produced by the prior art process.
.
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1 It should be pointed out that, after removal of each core 22, it may be reused an indefinit~ number of times. However, each time the core is to be used, it must be dimensionally initialized. This can be achieved by introducing core expansion pressure within the interior of a memory metal core, as shown in Figure 2, which expands -the walls of the memory metal alloy core 22. Of course, other core expansion pressure pro-cesses may be employed such as by containing solid ice, by solidification of appropriate known metals and alloys that expand upon cooling, or other suitable p~essure methods, includinc3 a two-way memory metal which ca~ be trained to expand at one critical temperature and contract at a different critical temperature.
As shown in Figure 4, final dimensions of a reusable memory metal alloy core are ensured by positioning such a core 22 between dies 26 and 24 which contact one another another along sur~ace 28. When the dies are pressed together, the greatly exaggerated space between the dies and core, as shown in Figure 4, disappears and the final dimensions for the core 22 will be formed.
Then, the core is ready to be placed over the base layer 12 in preparation of a molding procedure, as previously explained in connection with Figure 3~
In a preferred embodiment of the invention, the base layer 12 and overlying layer 14 (Figures 1 and 3)may each be made up from a composite material including epoxy pre-impregnated fabric sheets of graphite, Kevlar or fiberglass. Such pre-impregnated sheets of woven 30 fibers are available from sources .such as CIB~-GEIGY or ~ercules Corporation. Memory metal alloys o~ an appropriate nature are available Erom Memory ~etals, Inc., of Stam~ord, Connecti.cut, and Ray-Chem of l.ondon, England; and the , ~ . .
.
' ~ ' , ' ', : ' . :
, ~ -. , ~ -' ' , ', . ' , , ' ..
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1 critical temperatures for obtaining contraction of the alloys is generally specified by the manufacturer.
The present invention need not be restricted to cores for forming corrugated integrally stiffened aircraft 5 skin panels. l`he concept of the present invention extends to the machining or forming of memory metal cores to be used as cores in a filament winding process. For example, as indicated in Figure 5, a mandrel 30 fabricated from a mernory metal alloy serves as a core for filament 34, which 10 is wound along the exkernal surface of mandrel 30. The Eilament may be of the resin pre-impregnated type which facilitates curing. After curiny, the mandrel may be subjected to a critical temperature which results in the shrinking of the mandrel, thereby permitting its 15 easy removal, in the same manner as that prescribed in connection with a memory metal alloy core 22 (Figure 3).
This leaves a hardened tubular structure that is filament wound, useful in many industrial applications.
Thus, from the previous description of the 20 invention, it will be appreciated -that the ~tilization of a memory metal alloy for a corrugation core or a filament mandrel permits its rapid and effective withdrawal after surrounding resin-impregnated materials have been cured.
It should also be pointed out that the present invention 25 is compatible with room temperature curing resin systems.
It should be understood that the invention is not limited to the exact details of the construction shown and described herein for obvious modifications will occur to persons skilled in the art.
..
: : - . . .
:
: - .
.
365~
1 METHOD A~D APPARATUS FOR FORMING CORRUGATED
MAT~RIALS USING MAGNETIC MEMORY CORES
The present invention is related to molding apparatus and more particularly to a method and apparatus for forming corruyated or stiffened sheet materials by utilizing memory cores which are easily removable after molding.
In order to increase the strength and rigidity of sheet materials, corrugations are often formed in the material. This is often the case with aircraEt skin panels wherein the interior surface of the panels has integrally formed corrugations for achieving requisite stiffness and strenyth.
In recent years, increasing use has been made of composite resin-impregnated ~abrics, including graphite, Kevlar*and fiberglass fibers to achieve requisite panel strength at reduced weights and radar cross sectionO In order to form such composite panels, a number of resin-impregnated sheets, constituting a base layer, are positioned over a mold form. Cores are then positioned on top of the base layer, and subsequently, an overlying layer of composite sheets 's positioned over the core. The entixe assembly is loaded into an autoclave where heat and pressure is applied to cause curing o~ the resin in the composite material and achieve superior bonding between the various sheets of the overlying layer and base layer.
A principal disadvantage of the prior art lies in the use of cores which stick to the composite sheets after curing. ~s a result, their attempted removal may weaken or destroy the rormed layers.
.
* Trade ~ark .
, . ~,~ .
:
. , . , - .
:
365~32 1 The present invention avoids this problem by utilizing cores fabricated from memory alloys.
The present invention is directed to a metho~ for molding material into corrugated form, including the steps of:
posi-tioning a base layer impregnated with bonding material on a molding form;
positioning at least one core of memory metal alloy on the base layer;
posi-tioning an overlying layer impregnated with bonding material over the base layer and the core;
curing the layers;
subjecting the core to a critical temperature to cause contraction of the core; and removing the core;
whereby the overlying layer is bonded to the base layer and wherein the overlying layer includes corrugations integrally formed therein to stiffin the base layer.
The present invention utilizes cores fabri-cated from memory metal alloys. ~he cores are easily removed after a molding process by subjecting each -core to the critical temperature of the alloys wherein the core contracts in all directions, thereby permitting its simple removal from the molded structure. In summary, after the core is between base and overlying layers of resin-impregnated composite material, core expansion pressure has been applied to the interior of the core thereby initially 3 expanding the dimensions oE the core. ~fter curing, t:he core is subjected to the critical temperature - . .
. ~ : . . ' , : ' . ': . . ' -.: : . . .
- .
.
. .
: ' ' ' ' , ' i58Z
l of the memory metals for con-tracting the core i.n pre-paration of its withdrawal. Due to the fact that the core is easily removed, the integrity of the com-posite materials may be maintained and the core reused for subsequent molding cycles.
The above-mentioned advantages of the present invention will be more clearly understood when considered in conjunction with the accompanying drawings in which:
Figure 1 is a perspective view of a prior art aircraEt skin paneli Figure 2 is a perspective view of a memory metal alloy core employed in the present i.nvention;
Figure 3 is a perspective view of an aircraft skin panel in accordance with the present invention;
Figure 4 is a cross-sectional view of a reusable core positioned between two dies which ensure final dimensional accuracy of the die;
Figure 5 is a perspective view of a memory metal alloy mandrel for use in a filament winding ~ process.
Figure 1 illustrates a prior art finished skin panel assembly generally indicated by reference numeral 10, including a base layer 12 bonded to an overlying layer 14 having corrugations 16 formed therealong due to the insertion of parallel spaced cores within channels lg, during a previous molding process. The base layer 12 may form the external skin surface of an aircraft. The corrugations 16 formed in the overlying layer 14 serve as an integrally 3 formed stiffener :Eor the skin. The process Eor fabri-cating the prior skin panel assembly 10 of Figure 1 , .: . - ' ' ,. -. ~ , ' :
.
': -. ~ ' .. . . , ' .
,,, ' ~ ' ' ' ~ ' .,, ~" . . . . .. .
36S~3Z
--Ds 1 will now be explained. An initial base layer 12, as shown in Figure 3, is deposited on a mold form 20.
A number of tubular metal cores 22 having the shape shown in Figure 2 are positioned in spaced parallel relationship on base layer 12, as indicated in Figure 3. An overlying layer 16 is then deposited on the cores and the base layer 12. The resulting assembly of parts .
is then positioned in an autoclave where heat and pressure are applied, thereby causing excellent bonding of the overlying layer and base layer, due to curing of a resin CompGnent in layers 12 and 1~ which is necessary for the bonding process.
Afterward, the cores 22 must be removed. In conventional fabrication techniques, this presents a difficulty because the cores have a tendency to stick to the base layer 12 and overlying layer 14. As pre-viously mentioned, the removal step may injure these layers, resulting in a decrease of their strength and integrity.
In the case of the present invention, the core is not made from conventional core metal but, rather, from memory metal alloys. After bonding has been completed, the temperature of the autoclave is adjusted so that the critical temperature of the memory metal alloy is reached, thereby resulting in contraction of the core dimensions in all directlons. .
Consequently, the cores may be easily removed and the bonded overlying and base layers lifted from the mold form 20, resulting in the same finished corrugated skin panel assembly 1~ as was produced by the prior art process.
.
.. ,, ~ - , . . ..... . . . .
., . ,, . ,. .. . .. :
': ~ ' ~ .' ; ' " '. .
, .
. ~ . . .
1 It should be pointed out that, after removal of each core 22, it may be reused an indefinit~ number of times. However, each time the core is to be used, it must be dimensionally initialized. This can be achieved by introducing core expansion pressure within the interior of a memory metal core, as shown in Figure 2, which expands -the walls of the memory metal alloy core 22. Of course, other core expansion pressure pro-cesses may be employed such as by containing solid ice, by solidification of appropriate known metals and alloys that expand upon cooling, or other suitable p~essure methods, includinc3 a two-way memory metal which ca~ be trained to expand at one critical temperature and contract at a different critical temperature.
As shown in Figure 4, final dimensions of a reusable memory metal alloy core are ensured by positioning such a core 22 between dies 26 and 24 which contact one another another along sur~ace 28. When the dies are pressed together, the greatly exaggerated space between the dies and core, as shown in Figure 4, disappears and the final dimensions for the core 22 will be formed.
Then, the core is ready to be placed over the base layer 12 in preparation of a molding procedure, as previously explained in connection with Figure 3~
In a preferred embodiment of the invention, the base layer 12 and overlying layer 14 (Figures 1 and 3)may each be made up from a composite material including epoxy pre-impregnated fabric sheets of graphite, Kevlar or fiberglass. Such pre-impregnated sheets of woven 30 fibers are available from sources .such as CIB~-GEIGY or ~ercules Corporation. Memory metal alloys o~ an appropriate nature are available Erom Memory ~etals, Inc., of Stam~ord, Connecti.cut, and Ray-Chem of l.ondon, England; and the , ~ . .
.
' ~ ' , ' ', : ' . :
, ~ -. , ~ -' ' , ', . ' , , ' ..
~l2~`3658~
1 critical temperatures for obtaining contraction of the alloys is generally specified by the manufacturer.
The present invention need not be restricted to cores for forming corrugated integrally stiffened aircraft 5 skin panels. l`he concept of the present invention extends to the machining or forming of memory metal cores to be used as cores in a filament winding process. For example, as indicated in Figure 5, a mandrel 30 fabricated from a mernory metal alloy serves as a core for filament 34, which 10 is wound along the exkernal surface of mandrel 30. The Eilament may be of the resin pre-impregnated type which facilitates curing. After curiny, the mandrel may be subjected to a critical temperature which results in the shrinking of the mandrel, thereby permitting its 15 easy removal, in the same manner as that prescribed in connection with a memory metal alloy core 22 (Figure 3).
This leaves a hardened tubular structure that is filament wound, useful in many industrial applications.
Thus, from the previous description of the 20 invention, it will be appreciated -that the ~tilization of a memory metal alloy for a corrugation core or a filament mandrel permits its rapid and effective withdrawal after surrounding resin-impregnated materials have been cured.
It should also be pointed out that the present invention 25 is compatible with room temperature curing resin systems.
It should be understood that the invention is not limited to the exact details of the construction shown and described herein for obvious modifications will occur to persons skilled in the art.
..
: : - . . .
:
: - .
.
Claims (6)
1. A method for molding material into corrugated form, including the steps of:
positioning a base layer impregnated with bonding material on a molding form;
positioning at least one core of memory metal alloy on the base layer;
. positioning an overlying layer impregnated with bonding material over the base layer and the core;
curing the layers;
subjecting the core to a critical temperature to cause contraction of the core; and removing the core;
whereby the overlying layer is bonded to the base layer and wherein the overlying layer includes corru-gations integrally formed therein to stiffen the base layer.
positioning a base layer impregnated with bonding material on a molding form;
positioning at least one core of memory metal alloy on the base layer;
. positioning an overlying layer impregnated with bonding material over the base layer and the core;
curing the layers;
subjecting the core to a critical temperature to cause contraction of the core; and removing the core;
whereby the overlying layer is bonded to the base layer and wherein the overlying layer includes corru-gations integrally formed therein to stiffen the base layer.
2. The method set forth in Claim 1 wherein the base layer is comprised of stacked sheets of resin impregnated fabric.
3. The method set forth in Claim 1 wherein the overlying layer is comprised of stacked sheets of resin impregnated fabric.
4. The method set forth in Claim 1 wherein the base and overlying layers are comprised of stacked sheets of resin impregnated fabric.
5. The method set forth in Claims 1, 2 or 3, further including the step of subjecting the layers to pressure during curing for optimizing the bonding between the layers.
6. The method set forth in Claims 1, 2 or 3, further including the initial steps of mechanically expanding the core and positioning the expanded core in between die members to control the exterior dimensions of the core.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US779,765 | 1985-09-24 | ||
| US06/779,765 US4675061A (en) | 1985-09-24 | 1985-09-24 | Method for forming corrugated materials using memory metal cores |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1286582C true CA1286582C (en) | 1991-07-23 |
Family
ID=25117480
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000518837A Expired - Lifetime CA1286582C (en) | 1985-09-24 | 1986-09-23 | Method and apparatus for forming corrugated materials using magnetic memory cores |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US4675061A (en) |
| EP (1) | EP0237566A4 (en) |
| JP (1) | JPS63501004A (en) |
| CA (1) | CA1286582C (en) |
| ES (1) | ES2002367A6 (en) |
| IL (1) | IL80130A0 (en) |
| WO (1) | WO1987001650A1 (en) |
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| US5021109A (en) * | 1989-12-29 | 1991-06-04 | Xerox Corporation | Method of preparing a multilayered belt |
| US5061428A (en) * | 1990-01-04 | 1991-10-29 | Davidson Textron Inc. | Method for plastic coating foam molding insert |
| US5265456A (en) * | 1992-06-29 | 1993-11-30 | Grumman Aerospace Corporation | Method of cold working holes using a shape memory alloy tool |
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| US7422714B1 (en) | 2001-01-24 | 2008-09-09 | Cornerstone Research Group, Inc. | Method of using a shape memory material as a mandrel for composite part manufacturing |
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| US20030051434A1 (en) * | 2001-09-20 | 2003-03-20 | Lockheed Martin Corporation | Composite structure and method for constructing same |
| DE10210517B3 (en) * | 2002-03-09 | 2004-01-29 | Airbus Deutschland Gmbh | Process for the production of a component in fiber composite construction |
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| US10239141B2 (en) | 2013-10-10 | 2019-03-26 | Rohr, Inc. | Forming a complexly curved metallic sandwich panel |
| US10654230B2 (en) * | 2017-08-28 | 2020-05-19 | The Boeing Company | Methods of forming a cored composite laminate |
| CN109822933B (en) * | 2019-03-25 | 2020-09-11 | 大连理工大学 | Magnetic field auxiliary pressurizing method for composite material structure forming |
Family Cites Families (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1349372A (en) * | 1920-08-10 | Method of making hollow bodies | ||
| US1433728A (en) * | 1916-05-26 | 1922-10-31 | Westinghouse Electric & Mfg Co | Propeller |
| US1281258A (en) * | 1917-02-13 | 1918-10-15 | B R Greenblatt | Contracting metal core for ring-molds. |
| US2454719A (en) * | 1943-11-11 | 1948-11-23 | Studebaker Corp | Method of making cored laminated plastic sheets |
| US3379591A (en) * | 1961-06-22 | 1968-04-23 | Richard C. Bradley | Filament winding of tubular articles with incorporation of cut lengths of roving during winding |
| US4035007A (en) * | 1970-07-02 | 1977-07-12 | Raychem Corporation | Heat recoverable metallic coupling |
| BE788517A (en) * | 1971-09-07 | 1973-03-07 | Raychem Corp | VERY LOW TEMPERATURE CHUCK EXPANSION PROCESS |
| US3913444A (en) * | 1972-11-08 | 1975-10-21 | Raychem Corp | Thermally deformable fastening pin |
| US4012266A (en) * | 1972-08-21 | 1977-03-15 | Magee Donald L | Method and apparatus for filament winding on a corrugated form to produce a cylindrical corrugated glass fiber part |
| US4001928A (en) * | 1973-01-04 | 1977-01-11 | Raychem Corporation | Method for plugging an aperture with a heat recoverable plug |
| US4198081A (en) * | 1973-10-29 | 1980-04-15 | Raychem Corporation | Heat recoverable metallic coupling |
| US3900939A (en) * | 1973-10-31 | 1975-08-26 | Combustion Eng | Method of plugging steam generator tubes |
| US3872573A (en) * | 1973-12-19 | 1975-03-25 | Raychem Corp | Process and apparatus for making heat recoverable composite couplings |
| US4338970A (en) * | 1975-06-16 | 1982-07-13 | Raychem Corporation | Recoverable sleeve |
| US4172562A (en) * | 1976-12-23 | 1979-10-30 | Union Carbide Corporation | Process for winding filaments on a mandrel |
| GB1599999A (en) * | 1977-01-24 | 1981-10-14 | Raychem Ltd | Heat-recoverable articles |
| US4384913A (en) * | 1979-09-25 | 1983-05-24 | Ameron, Inc. | Mandrel for filament winding of plastic articles |
| US4369934A (en) * | 1981-02-03 | 1983-01-25 | Spies Henry J | Helical filament winding apparatus |
| US4374170A (en) * | 1981-11-09 | 1983-02-15 | Ford Motor Company | Room temperature cure polyester laminates |
| US4433567A (en) * | 1981-11-12 | 1984-02-28 | Grumman Aerospace Corporation | Method for working holes |
| JPS5973937A (en) * | 1982-10-20 | 1984-04-26 | Toyota Motor Corp | Preparation of curved rubber hose |
| JPS60139434A (en) * | 1983-12-28 | 1985-07-24 | Toshiba Corp | Fiber-reinforced plastics molding die |
-
1985
- 1985-09-24 US US06/779,765 patent/US4675061A/en not_active Expired - Fee Related
-
1986
- 1986-09-23 IL IL80130A patent/IL80130A0/en unknown
- 1986-09-23 ES ES8602089A patent/ES2002367A6/en not_active Expired
- 1986-09-23 CA CA000518837A patent/CA1286582C/en not_active Expired - Lifetime
- 1986-09-24 WO PCT/US1986/002012 patent/WO1987001650A1/en not_active Application Discontinuation
- 1986-09-24 JP JP61505174A patent/JPS63501004A/en active Pending
- 1986-09-24 EP EP19860906166 patent/EP0237566A4/en not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| US4675061A (en) | 1987-06-23 |
| IL80130A0 (en) | 1986-12-31 |
| EP0237566A4 (en) | 1988-04-18 |
| JPS63501004A (en) | 1988-04-14 |
| EP0237566A1 (en) | 1987-09-23 |
| WO1987001650A1 (en) | 1987-03-26 |
| ES2002367A6 (en) | 1988-08-01 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed | ||
| MKLA | Lapsed |
Effective date: 19940125 |