US3924793A - Forming metals - Google Patents

Forming metals Download PDF

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Publication number
US3924793A
US3924793A US490887A US49088774A US3924793A US 3924793 A US3924793 A US 3924793A US 490887 A US490887 A US 490887A US 49088774 A US49088774 A US 49088774A US 3924793 A US3924793 A US 3924793A
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United States
Prior art keywords
sheet
interior sheet
face
interior
regions
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Expired - Lifetime
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US490887A
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Leo Ewart Arthur Summers
David Sidney Underhill
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BAC AND BRITISH AEROSPACE
BAE Systems PLC
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British Aircraft Corp Ltd
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Assigned to BRITISH AEROSPACE PUBLIC LIMITED COMPANY reassignment BRITISH AEROSPACE PUBLIC LIMITED COMPANY CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). EFFECTIVE JAN. 2, 1981 Assignors: BRITISH AEROSPACE LIMITED
Assigned to BAC AND BRITISH AEROSPACE reassignment BAC AND BRITISH AEROSPACE ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BRITISH AIRCRAFT CORPORATION LIMITED,
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating

Definitions

  • This invention relates to the forming of stiffened panels of metallic alloys having super-plastic characteristics.
  • Metallic alloys having super-plastic characteristics have a composition and microstructure such that, when heated to within an appropriate range of temperature and when deformed within an appropriate range of strain rate, they exhibit the flow characteristics of a viscous fluid.
  • n is numerically of the order of 0.7 to 1.00
  • strain rate extension per unit of original length per unit of time
  • m is the strain rate sensitivity
  • the invention has for an object the ready formation of stiffened panels with a minimum of forming operations.
  • a method of forming a stiffened panel includes the steps of positioning a metal face sheet on each side of an interior sheet of a metallic alloy having superplastic characteristics, attaching spaced regions of the said interior sheet alternately to the face sheet on one side and to the face sheet on the other side of the interior sheet, bringing the assembly to within that temperature range at which the interior sheet exhibits superplastic characteristics, and causing the face sheets to be moved apart and thus to draw the attached regions of the interior sheet with them such that the said interior sheet finally extends from one face sheet to the other in alternate sequence.
  • the metal face sheets have their peripheral edges sealingly joined together and the envelope so formed is inflated to urge the said face sheets apart.
  • FIG. 1 is a scross-sectional view of parts of the components of a panel before forming
  • FIG. 2 is a similar view to that of FIG. 1 subsequent to forming
  • FIG. 3 is a similar view to that of FIG. 2 but illustrating an alternative embodiment.
  • FIG. 4- is a similar view to that of FIG. 1 also illustrating an alternative embodiment
  • FIG. 5 is a similar view to that of FIG. 4 subsequent to forming
  • FIG. 6 is a similar view to that of FIG. 5 but showing an alternative embodiment
  • FIGS. 7 and 8 illustrate a sealed peripheral edge ofa panel respectively before and after forming.
  • a stiffened panel is formed of three metal sheets, two face sheets 1 and 2, respectively, and an interior sheet 3, which is of a superplastic alloy.
  • the interior sheet is placed between the two face sheets 1 and 2 with spacer portions d in the form of strips of metal placed between each face sheet I and 2 and the interior sheet 3.
  • the spacer portions are placed where the sheets are to be attached one to theother in alternate sequence, that is to say from the left hand edge of FIG. 1 the sheets I and 3 have a spacer portion 4 and then the sheets 2 and 3 and so on.
  • the assembly is then subjected to heat and pressure so that those regions of the sheets at the spacer portions become diffusion bonded to the spacer portions 4 and thereby indirectly one to another.
  • the elongated spacer portions 4 are replaced by spacer portions in the form of small disc-like portions 5. These are spaced in alternate sequence between the face sheet 1 and the interior sheet 3 and between the face sheet 2 and the interior sheet 3. Again, the sheets are diffusion bonded to the spacer portions 5 and hence indirectly to one another.
  • FIGS. 4, 5 and 6 are similar to FIGS. 1, 2 and 3, respectively, but illustrate embodiments where the face sheets 1 and 2 are attached directly to the interior sheet 3 without the spacer portions d or 5 being present.
  • the sheets I and 2 are locally attached to the sheet 3 by welded regions.
  • the welded regions, which in FIG. 5 are in the form of lines 6 and in FIG. 6 are in the form of spots 7, are preferably provided by an electron beam welding process.
  • the assembly is brought to within the temperature range at which the interior sheet exhibits superplastic characteristics, if it is not already in that range, and the face sheets 1 and 2 are moved apart thus drawing the attached regions of the interior sheet (that is those regions adjacent the spacer portions 4 or 5 and adjacent the weld regions 6 or 7) with them in alternately opposite directions.
  • the interior sheet 3 thus becomes of corrugated form (as in FIGS. 2 and 5) or of dimpled form (as in FIGS. 3 and 6).
  • the sheet 3 becomes a series of alternate oppositely facing dimples. In both cases the interior sheet 3 zig-zags between the face sheets 1 and 2 bridging the void be tween them.
  • FIGS. 7 and 8 illustrate how the sheets can be subjected to a welding operation around their peripheries to form a sealed envelope.
  • the weld region is shown at 8.
  • the sealed envelope so formed is fed with an inert gas under pressure such that, when the interior sheet 3 is superplastic, the sheets 1 and 2 are moved apart by a predetermined amount to effect the previously described corrugation or dimpling of the interior sheet.
  • the sheets 1 and 2 may be moved apart against oppositely facing plattens of a press (not shown).
  • the interior sheet may be of thinner gauge material than the face sheets.
  • the face sheets I and 2 may also be of a superplastic alloy; this arrangement has advantage where the finished panel required to be of other than a totally flat formation.
  • a method of forming a stiffened panel including the steps of positioning a metal face sheet on each side of an interior sheet of a metallic alloy having superplastic characteristics, attaching spaced regions of the said interior sheet alternately to the face sheet on one side and to the face sheet on the other side of the interior sheet, sealing the said face sheets one to the other to form an inflatable envelope assembly, bringing the assembly to within that temperature range at which the interior sheet exhibits superplastic characteristics, and applying a differential pressure between the interior and the exterior of the envelope assembly thus causing the face sheets to move apart and draw the attached regions of the interior sheet with them so that the said interior sheet finally extends from one face to the other in alternate sequence.

Abstract

A method of forming a stiffened panel in which an interior sheet of a superplastic material is placed between two face sheets and attached one to the other in alternate sequence so that, as the face sheets are moved apart, the attached regions of the interior sheet are drawn with them.

Description

O Unlted States Patent 1191 1111 3, 93 Summers et al. Dec. 9, 1975 FORMING METALS 3,200,489 8/1965 Keeleric 29/497.5 x 3,206,847 9/1965 Keeleric 29/480 [75] Inventors- Ewart Summers, Dav! 3,340,101 9/1967 Fields et al 72/364 ux g i gndelhlll, both of Bnstol, 3,345,735 10/1967 Nicholls 29/471.1 x
ng an OTHER PUBLICATIONS [73] Assignee: British Aircraft curporation Backofen Superplasticity Enchants Metallurgy Steel Ltmlted, London, England Dec 15 1969 PP 2548. [22] Filed: July 22, 1974 [21] Appl 490,887 Primary Examiner-Jarhes L. Jones, Jr.
Assistant Examiner-K. J. Ramsey Attorney, Agent, or FirmCushman, Darby & [30] Forelgn Appllcatlon Prlorlty Data Cushman July 24, 1973 United Kingdom 35293/73 57 ABSTRACT [52] US. Cl. .1 228/157; 72/364; 228/181 1 [51] Int. B23K 31/00, 8211) 47/00 A method of formmg a stlffened panel In whlch an 1n- [58] Field 61 Search 2 9/471.1 480 197 5 497 7' erior Sheet a superplastic material is Placed h 8 tween two face sheets and attached one to the other in alternate sequence so that, as the face sheets are [56] References Cited moved apart, the attached regions of the interior sheet UNITED STATES PATENTS are drawn them 2,481,046 9/1949 Scurlock 29/471.1 ux 7 8 Drawmg F'gures US. Patent Dec. 9, 1975 Sheet 1 of 2 3,924,793
5 94- 7 A E b 5 US. Patent Dec. 9, 1975 Sheet 2 of2 3,924,793
roRMiNo METALS This invention relates to the forming of stiffened panels of metallic alloys having super-plastic characteristics. Metallic alloys having super-plastic characteristics have a composition and microstructure such that, when heated to within an appropriate range of temperature and when deformed within an appropriate range of strain rate, they exhibit the flow characteristics of a viscous fluid. Such alloys have characteristics indicated by the formula: f= h s"- where:-
m is numerically of the order of 0.7 to 1.00,
f is applied stress (load per unit area),
h is a constant,
3 is strain rate (extension per unit of original length per unit of time), and,
m is the strain rate sensitivity.
The condition in which these characteristics are attained is known as super-plasticity and large deformations are possible without fracture.
The invention has for an object the ready formation of stiffened panels with a minimum of forming operations.
According to the present invention a method of forming a stiffened panel includes the steps of positioning a metal face sheet on each side of an interior sheet of a metallic alloy having superplastic characteristics, attaching spaced regions of the said interior sheet alternately to the face sheet on one side and to the face sheet on the other side of the interior sheet, bringing the assembly to within that temperature range at which the interior sheet exhibits superplastic characteristics, and causing the face sheets to be moved apart and thus to draw the attached regions of the interior sheet with them such that the said interior sheet finally extends from one face sheet to the other in alternate sequence.
Conveniently, the metal face sheets have their peripheral edges sealingly joined together and the envelope so formed is inflated to urge the said face sheets apart.
Somepreferred embodiments of the invention are now described with reference to the accompanying drawings:
FIG. 1 is a scross-sectional view of parts of the components of a panel before forming,
FIG. 2 is a similar view to that of FIG. 1 subsequent to forming,
FIG. 3 is a similar view to that of FIG. 2 but illustrating an alternative embodiment.
FIG. 4- is a similar view to that of FIG. 1 also illustrating an alternative embodiment,
FIG. 5 is a similar view to that of FIG. 4 subsequent to forming,
FIG. 6 is a similar view to that of FIG. 5 but showing an alternative embodiment, and,
FIGS. 7 and 8 illustrate a sealed peripheral edge ofa panel respectively before and after forming.
Referring to FIGS. I and 2, a stiffened panel is formed of three metal sheets, two face sheets 1 and 2, respectively, and an interior sheet 3, which is of a superplastic alloy. The interior sheet is placed between the two face sheets 1 and 2 with spacer portions d in the form of strips of metal placed between each face sheet I and 2 and the interior sheet 3. The spacer portions are placed where the sheets are to be attached one to theother in alternate sequence, that is to say from the left hand edge of FIG. 1 the sheets I and 3 have a spacer portion 4 and then the sheets 2 and 3 and so on. The assembly is then subjected to heat and pressure so that those regions of the sheets at the spacer portions become diffusion bonded to the spacer portions 4 and thereby indirectly one to another.
In the alternative of FIG. 3, the elongated spacer portions 4 are replaced by spacer portions in the form of small disc-like portions 5. These are spaced in alternate sequence between the face sheet 1 and the interior sheet 3 and between the face sheet 2 and the interior sheet 3. Again, the sheets are diffusion bonded to the spacer portions 5 and hence indirectly to one another.
FIGS. 4, 5 and 6 are similar to FIGS. 1, 2 and 3, respectively, but illustrate embodiments where the face sheets 1 and 2 are attached directly to the interior sheet 3 without the spacer portions d or 5 being present. In this case the sheets I and 2 are locally attached to the sheet 3 by welded regions. The welded regions, which in FIG. 5 are in the form of lines 6 and in FIG. 6 are in the form of spots 7, are preferably provided by an electron beam welding process.
To bring the assembly from the condition of FIGS. 1 and 4 to that of FIGS. 2 and 5 or 3 and 6 respectively, it is brought to within the temperature range at which the interior sheet exhibits superplastic characteristics, if it is not already in that range, and the face sheets 1 and 2 are moved apart thus drawing the attached regions of the interior sheet (that is those regions adjacent the spacer portions 4 or 5 and adjacent the weld regions 6 or 7) with them in alternately opposite directions. The interior sheet 3 thus becomes of corrugated form (as in FIGS. 2 and 5) or of dimpled form (as in FIGS. 3 and 6). As can be seen in FIGS. 3 and 6, the sheet 3 becomes a series of alternate oppositely facing dimples. In both cases the interior sheet 3 zig-zags between the face sheets 1 and 2 bridging the void be tween them.
FIGS. 7 and 8 illustrate how the sheets can be subjected to a welding operation around their peripheries to form a sealed envelope. The weld region is shown at 8. The sealed envelope so formed is fed with an inert gas under pressure such that, when the interior sheet 3 is superplastic, the sheets 1 and 2 are moved apart by a predetermined amount to effect the previously described corrugation or dimpling of the interior sheet.
To maintain flat outer surfaces, the sheets 1 and 2 may be moved apart against oppositely facing plattens of a press (not shown). To further aid the maintaining of flat outer surfaces, the interior sheet may be of thinner gauge material than the face sheets.
The face sheets I and 2 may also be of a superplastic alloy; this arrangement has advantage where the finished panel required to be of other than a totally flat formation.
We claim:
l. A method of forming a stiffened panel including the steps of positioning a metal face sheet on each side of an interior sheet of a metallic alloy having superplastic characteristics, attaching spaced regions of the said interior sheet alternately to the face sheet on one side and to the face sheet on the other side of the interior sheet, sealing the said face sheets one to the other to form an inflatable envelope assembly, bringing the assembly to within that temperature range at which the interior sheet exhibits superplastic characteristics, and applying a differential pressure between the interior and the exterior of the envelope assembly thus causing the face sheets to move apart and draw the attached regions of the interior sheet with them so that the said interior sheet finally extends from one face to the other in alternate sequence.
2. A method according to claim 1 wherein the spaced attachment regions of the interior sheet are indirectly attached to the face sheets by means of metallic spacer portions metallurgically bonded both to a face sheet and to the interior sheet.
3. A method according to claim 1 wherein the spaced regions of the interior sheet are directly attached to the face sheets by means of a metallurgical bond.
claiml.

Claims (7)

1. A method of forming a stiffened panel including the steps of positioning a metal face sheet on each side of an interior sheet of a metallic alloy having superplastic characteristics, attaching spaced regions of the said interior sheet alternately to the face sheet on one side and to the face sheet on the other side of the interior sheet, sealing the said face sheets one to the other to form an inflatable envelope assembly, bringing the assembly to within that temperature range at which the interior sheet exhibits superplastic characteristics, and applying a differential pressure between the interior and the exterior of the envelope assembly thus causing the face sheets to move apart and draw the attached regions of the interior sheet with them so that the said interior sheet finally extends from one face to the other in alternate sequence.
2. A method accoRding to claim 1 wherein the spaced attachment regions of the interior sheet are indirectly attached to the face sheets by means of metallic spacer portions metallurgically bonded both to a face sheet and to the interior sheet.
3. A method according to claim 1 wherein the spaced regions of the interior sheet are directly attached to the face sheets by means of a metallurgical bond.
4. A method according to claim 1 wherein the said spaced attachment regions are in the form of lines and the interior sheet is finally of generally corrugated form.
5. A method according to claim 1 wherein the said spaced attachment regions are in the form of spots and the interior sheet is finally of generally dimpled form.
6. A method according to claim 1 wherein the said face sheets are sealed one to the other by a peripherally extending metallurgical bond.
7. A stiffened panel formed by the method defined in claim 1.
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Cited By (40)

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US4292375A (en) * 1979-05-30 1981-09-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Superplastically formed diffusion bonded metallic structure
US4304821A (en) * 1978-04-18 1981-12-08 Mcdonnell Douglas Corporation Method of fabricating metallic sandwich structure
US4351470A (en) * 1978-09-29 1982-09-28 British Aerospace Public Limited Company Method of making a stiffened panel
US4393987A (en) * 1981-09-30 1983-07-19 The Boeing Company Superplastically formed structure and method of making
US4538756A (en) * 1981-10-15 1985-09-03 Texas Instruments Incorporated Process for producing reinforced structural members
US4769968A (en) * 1987-03-05 1988-09-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Truss-core corrugation for compressive loads
US5118571A (en) * 1990-12-21 1992-06-02 Ltv Aerospace And Defense Company Structure and method for forming structural components
US5156327A (en) * 1990-04-03 1992-10-20 Mitsubishi Jukogyo Kabushiki Kaisha Procedure for molding composite materials
US5287918A (en) * 1990-06-06 1994-02-22 Rolls-Royce Plc Heat exchangers
US5344063A (en) * 1991-10-04 1994-09-06 British Aerospace Public Limited Company Method of making diffusion bonded/superplastically formed cellular structures with a metal matrix composite
US5385204A (en) * 1989-08-25 1995-01-31 Rolls-Royce Plc Heat exchanger and methods of manufacture thereof
US5410132A (en) * 1991-10-15 1995-04-25 The Boeing Company Superplastic forming using induction heating
US5437936A (en) * 1991-05-13 1995-08-01 Johnson; Jeffrey D. Honeycomb core structure and method and apparatus relating thereto
US5505256A (en) * 1991-02-19 1996-04-09 Rolls-Royce Plc Heat exchangers and methods of manufacture thereof
US5587098A (en) * 1991-04-05 1996-12-24 The Boeing Company Joining large structures using localized induction heating
US5624594A (en) * 1991-04-05 1997-04-29 The Boeing Company Fixed coil induction heater for thermoplastic welding
US5641422A (en) * 1991-04-05 1997-06-24 The Boeing Company Thermoplastic welding of organic resin composites using a fixed coil induction heater
US5645744A (en) * 1991-04-05 1997-07-08 The Boeing Company Retort for achieving thermal uniformity in induction processing of organic matrix composites or metals
US5683607A (en) * 1991-10-15 1997-11-04 The Boeing Company β-annealing of titanium alloys
US5687900A (en) * 1995-03-28 1997-11-18 Mcdonnell Douglas Corporation Structural panel having a predetermined shape and an associated method for superplastically forming and diffusion bonding the structural panel
US5705794A (en) * 1991-10-15 1998-01-06 The Boeing Company Combined heating cycles to improve efficiency in inductive heating operations
US5710414A (en) * 1991-04-05 1998-01-20 The Boeing Company Internal tooling for induction heating
US5723849A (en) * 1991-04-05 1998-03-03 The Boeing Company Reinforced susceptor for induction or resistance welding of thermoplastic composites
US5728309A (en) * 1991-04-05 1998-03-17 The Boeing Company Method for achieving thermal uniformity in induction processing of organic matrix composites or metals
US5793024A (en) * 1991-04-05 1998-08-11 The Boeing Company Bonding using induction heating
US5808281A (en) * 1991-04-05 1998-09-15 The Boeing Company Multilayer susceptors for achieving thermal uniformity in induction processing of organic matrix composites or metals
US5847375A (en) * 1991-04-05 1998-12-08 The Boeing Company Fastenerless bonder wingbox
US5914064A (en) * 1991-10-15 1999-06-22 The Boeing Company Combined cycle for forming and annealing
US5955207A (en) * 1997-11-24 1999-09-21 Mcdonnell Douglas Corporation Structural panel having boron reinforce face sheets and associated fabrication method
US5994666A (en) * 1996-01-12 1999-11-30 The Boeing Company Multisheet metal sandwich structures
EP0962268A1 (en) * 1998-06-02 1999-12-08 Solistor B.V. A method for manufacturing a storage vessel for storing a medium, as well as a storage vessel manufactured in accordance with this method
US6087640A (en) * 1991-10-15 2000-07-11 The Boeing Company Forming parts with complex curvature
US6508394B1 (en) 1996-01-12 2003-01-21 The Boeing Company Method for making multisheet metal sandwich structure with throughholes
US20040256383A1 (en) * 2003-06-18 2004-12-23 Fischer John R. Apparatus and methods for single sheet forming using induction heating
US20060199031A1 (en) * 1999-04-23 2006-09-07 The Boeing Company Multisheet sandwich panel using superplastic forming and adhesive bonding
FR2913107A1 (en) * 2007-02-23 2008-08-29 Pierre Vironneau Heat exchanger forming method for use in e.g. e.g. industrial building, involves applying for separating upper and lower flat plates from each other such that weak bridges are broken and separation walls form non zero angle with plates
EP2110189A1 (en) * 2008-04-18 2009-10-21 ETH Zürich Method for dieless forming of sheet metal
CN103331513A (en) * 2013-07-03 2013-10-02 北京科技大学 Manufacturing method of superplasticity duplex stainless steel sandwich structure
US20190101003A1 (en) * 2017-09-29 2019-04-04 Rolls-Royce Plc Blades and vanes for gas turbine engines and the manufacture thereof
US11260952B2 (en) * 2019-09-26 2022-03-01 The Boeing Company Reinforced superplastic formed and diffusion bonded structures

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DE2813635C2 (en) * 1978-03-30 1983-05-05 Theodor Wuppermann Gmbh, 5090 Leverkusen Method and device for the production of profiles, hollow bodies and the like from several metal strips of constant thickness
GB8821222D0 (en) * 1988-09-09 1988-12-14 British Aerospace Double curvature structures by superplastic forming & diffusion bonding
GB9117546D0 (en) * 1991-08-14 1992-02-19 British Aerospace Manufacture of structures by diffusion bonding and superplastic forming

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* Cited by examiner, † Cited by third party
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US4304821A (en) * 1978-04-18 1981-12-08 Mcdonnell Douglas Corporation Method of fabricating metallic sandwich structure
US4351470A (en) * 1978-09-29 1982-09-28 British Aerospace Public Limited Company Method of making a stiffened panel
US4292375A (en) * 1979-05-30 1981-09-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Superplastically formed diffusion bonded metallic structure
US4393987A (en) * 1981-09-30 1983-07-19 The Boeing Company Superplastically formed structure and method of making
US4538756A (en) * 1981-10-15 1985-09-03 Texas Instruments Incorporated Process for producing reinforced structural members
US4769968A (en) * 1987-03-05 1988-09-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Truss-core corrugation for compressive loads
US5385204A (en) * 1989-08-25 1995-01-31 Rolls-Royce Plc Heat exchanger and methods of manufacture thereof
US5156327A (en) * 1990-04-03 1992-10-20 Mitsubishi Jukogyo Kabushiki Kaisha Procedure for molding composite materials
US5287918A (en) * 1990-06-06 1994-02-22 Rolls-Royce Plc Heat exchangers
US5118571A (en) * 1990-12-21 1992-06-02 Ltv Aerospace And Defense Company Structure and method for forming structural components
US5505256A (en) * 1991-02-19 1996-04-09 Rolls-Royce Plc Heat exchangers and methods of manufacture thereof
US5793024A (en) * 1991-04-05 1998-08-11 The Boeing Company Bonding using induction heating
US5808281A (en) * 1991-04-05 1998-09-15 The Boeing Company Multilayer susceptors for achieving thermal uniformity in induction processing of organic matrix composites or metals
US7126096B1 (en) 1991-04-05 2006-10-24 Th Boeing Company Resistance welding of thermoplastics in aerospace structure
US5587098A (en) * 1991-04-05 1996-12-24 The Boeing Company Joining large structures using localized induction heating
US5728309A (en) * 1991-04-05 1998-03-17 The Boeing Company Method for achieving thermal uniformity in induction processing of organic matrix composites or metals
US5624594A (en) * 1991-04-05 1997-04-29 The Boeing Company Fixed coil induction heater for thermoplastic welding
US5641422A (en) * 1991-04-05 1997-06-24 The Boeing Company Thermoplastic welding of organic resin composites using a fixed coil induction heater
US5645744A (en) * 1991-04-05 1997-07-08 The Boeing Company Retort for achieving thermal uniformity in induction processing of organic matrix composites or metals
US6040563A (en) * 1991-04-05 2000-03-21 The Boeing Company Bonded assemblies
US5847375A (en) * 1991-04-05 1998-12-08 The Boeing Company Fastenerless bonder wingbox
US5723849A (en) * 1991-04-05 1998-03-03 The Boeing Company Reinforced susceptor for induction or resistance welding of thermoplastic composites
US5710414A (en) * 1991-04-05 1998-01-20 The Boeing Company Internal tooling for induction heating
US5437936A (en) * 1991-05-13 1995-08-01 Johnson; Jeffrey D. Honeycomb core structure and method and apparatus relating thereto
US5609288A (en) * 1991-05-13 1997-03-11 Johnson; Jeffrey D. Honeycomb core structure and method and apparatus relating thereto
US5344063A (en) * 1991-10-04 1994-09-06 British Aerospace Public Limited Company Method of making diffusion bonded/superplastically formed cellular structures with a metal matrix composite
US5705794A (en) * 1991-10-15 1998-01-06 The Boeing Company Combined heating cycles to improve efficiency in inductive heating operations
US5683607A (en) * 1991-10-15 1997-11-04 The Boeing Company β-annealing of titanium alloys
US5700995A (en) * 1991-10-15 1997-12-23 The Boeing Company Superplastically formed part
US5821506A (en) * 1991-10-15 1998-10-13 The Boeing Company Superplastically formed part
US5410132A (en) * 1991-10-15 1995-04-25 The Boeing Company Superplastic forming using induction heating
US5914064A (en) * 1991-10-15 1999-06-22 The Boeing Company Combined cycle for forming and annealing
US6087640A (en) * 1991-10-15 2000-07-11 The Boeing Company Forming parts with complex curvature
US5687900A (en) * 1995-03-28 1997-11-18 Mcdonnell Douglas Corporation Structural panel having a predetermined shape and an associated method for superplastically forming and diffusion bonding the structural panel
US5797239A (en) * 1995-03-28 1998-08-25 Mcdonnell Douglas Corporation Titanium reinforced structural panel having a predetermined shape
US5994666A (en) * 1996-01-12 1999-11-30 The Boeing Company Multisheet metal sandwich structures
US6508394B1 (en) 1996-01-12 2003-01-21 The Boeing Company Method for making multisheet metal sandwich structure with throughholes
US6656603B2 (en) 1996-01-12 2003-12-02 The Boeing Company Multisheet sandwich structures with throughholes
US5955207A (en) * 1997-11-24 1999-09-21 Mcdonnell Douglas Corporation Structural panel having boron reinforce face sheets and associated fabrication method
EP0962268A1 (en) * 1998-06-02 1999-12-08 Solistor B.V. A method for manufacturing a storage vessel for storing a medium, as well as a storage vessel manufactured in accordance with this method
US7146727B2 (en) * 1999-04-23 2006-12-12 The Boeing Company Multisheet sandwich panel using superplastic forming and adhesive bonding
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WO2008125755A2 (en) * 2007-02-23 2008-10-23 Cazères, Pascal Method of making a heat exchanger and heat exchanger obtained according to this method
WO2008125755A3 (en) * 2007-02-23 2008-12-11 Pierre Vironneau Method of making a heat exchanger and heat exchanger obtained according to this method
JP2010519494A (en) * 2007-02-23 2010-06-03 ヴィロノ，ピエール Heat exchanger and manufacturing method thereof
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CN101611286B (en) * 2007-02-23 2011-03-09 皮埃尔·维罗洛 Method of making a heat exchanger and heat exchanger obtained according to this method
EP2110189A1 (en) * 2008-04-18 2009-10-21 ETH Zürich Method for dieless forming of sheet metal
CN103331513A (en) * 2013-07-03 2013-10-02 北京科技大学 Manufacturing method of superplasticity duplex stainless steel sandwich structure
US20190101003A1 (en) * 2017-09-29 2019-04-04 Rolls-Royce Plc Blades and vanes for gas turbine engines and the manufacture thereof
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