Forming of preconsolidated metal matrix composites

• US 4,163,380 A
• Filed: 10/11/1977
• Issued: 08/07/1979
• Est. Priority Date: 10/11/1977
• Status: Expired due to Term

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Masoner, Vernon W.
• Primary Examiner(s): Larson, Lowell A.
• Application Number:
  US05/841,005
• Time in Patent Office: 665 Days
• Field of Search: 29/419 R, 29/424, 72/342, 72/364, 72/700, 428/595, 428/608, 428/611, 428/627
• US Class Current: 72/342.1
• CPC Class Codes: B21D 5/01 between rams and anvils or abutments
• CPC Class Codes: Y10S 72/70 Deforming specified alloys or uncommon metal or bimetallic work
• CPC Class Codes: Y10T 29/49801 Shaping fiber or fibered material
• CPC Class Codes: Y10T 428/12465 having magnetic properties, or preformed fiber orientation coordinate with shape

Abstract

A method of hot forming bends or deflections in preconsolidated metal matrix composite panels comprised of unidirectional filaments of boron, borsic, alumina, or graphite in aluminum or titanium base metals without limitation of orientation of the filaments relative to axes of the formed bends or deflections.

Claims

1. A method of forming bends or deflections in a preconsolidated metal matrix composite workpiece consisting of boron, borsic, alumina or graphite filaments in aluminum or titanium base metals, said method comprising the steps of:

(a) locating the composite workpiece between open male and female members of a forming die;

(b) bringing the workpiece and at least the die faces to a temperature of from approximately 910°

F. to approximately 935°

F.; and

,

(c) closing the die members at a rate of from 5 to 12 mils per minute after both male and female die members are in contact with the workpiece and until the die members are completely closed.

2. A method as claimed in claim 1 wherein after complete closure of the die members, they are maintained closed for a post-forming dwell time of from approximately 15 minutes to approximately 30 minutes.

3. A method as claimed in claim 1 wherein prior to location of the composite workpiece in step (a), titanium sheets are secured to the face surfaces of said composite workpiece by a weld line that completely encloses the face surface area of the workpiece being formed, and removal of the titanium sheets and weld line from the formed workpiece after the workpiece is removed from the forming die.

4. A method as claimed in claim 3 wherein the thickness of the titanium face sheets are approximately 0.016 inch.

5. A method as claimed in claim 1 wherein at least part of the surface portions of the die members forming the inner radius of at least one deformation in the formed workpiece is draw polished to a finish of 8-16 RMS.

6. A method as claimed in claim 1 wherein at least one workpiece forming surface of at least one of said die members includes a springback angle of from approximately 3°

to approximately 15°

.

7. A method as claimed in claim 1 wherein the clearance between a forming surface of the male die member and a confronting female die member surface that is traversed by said male die member surface during die closure is from approximately 1.3 to approximately 1.5 times the thickness of the workpiece.

8. A method as claimed in claim 6 wherein the workpiece filament material is of boron, and the springback angle ranges from approximately 3°

to approximately 5°

.

9. A method as claimed in claim 6 wherein the workpiece filament material is of borsic, and the springback angle ranges from approximately 5°

to approximately 10°

.

10. A method as claimed in claim 6 wherein the workpiece filament material consists of alumina or graphite, and the springback angle ranges from approximately 7°

to approximately 15°

.

11. A male and female member tool die set for forming bends or deflections in a preconsolidated metal matrix composite workpiece consisting of boron, borsic, alumina or graphite filaments in aluminum or titanium base metals such that at least one bend or deflection is oriented so that at least some of the filaments of the composite workpiece are angulated to at least one bend or deflection axis with said forming accomplished at a temperature of approximately 910°

F. to approximately 935°

F. for the workpiece and at least the die member forming faces, said tool die set containing the properties of;

(a) at least part of the surface portions of the die members forming the inner radius of at least one deformation in the formed workpiece is polished to a finish of 8-16 RMS;

(b) at least one workpiece forming surface of at least one of said die members includes a springback angle of from approximately 3°

to approximately 15°

; and

,

(c) the clearance between a forming surface of the male die member and a confronting female die member surface that is traversed by said male die member surface during die closure is from approximately 1.3 to approximately 1.5 times the thickness of the workpiece.

12. A formed workpiece of a preconsolidated metal matrix composite consisting of boron, borsic, alumina or graphite filaments in aluminum or titanium base metals having at least one bend or deflection formed in the workpiece with at least some of the filaments of the composite workpiece located at an angle to the axis of the bend or deflection with said forming resulting from:

(a) locating the composite workpiece between open male and female members of a forming die;

(b) bringing the workpiece and at least the die faces to a temperature of from approximately 910°

F. to approximately 935°

F.; and

,

(c) closing the die members at a rate of from 5 to 12 mils per minute after both male and female die members are in contact with the workpiece and until the die members are completely closed.

13. A formed preconsolidated metal matrix composite workpiece as claimed in claim 12 in which the forming of the workpiece included the complete closure of the die members maintained for a post-forming dwell time of from approximately 15 minutes to approximately 30 minutes.

14. A formed preconsolidated metal matrix composite workpiece as claimed in claim 12 in which the forming of the workpiece included before locating the composite workpiece between the open male and female members of the forming die the securing of titanium face sheets to the face surfaces of the workpiece by a weld line that completely enclosed the face surface area of the formed workpiece, and the titanium face sheets and weld line removed from the formed workpiece after removal thereof from the forming die.

15. A formed preconsolidated metal matrix composite workpiece as claimed in claim 14 wherein the thickness of the titanium face sheets were approximately 0.016 inch.

16. A formed preconsolidated metal matrix composite workpiece as claimed in claim 12 wherein at least part of the surface portions of the die members forming the inner radius of at least one deformation in the formed workpiece were draw polished to a finish of 8-16 RMS.

17. A formed preconsolidated metal matrix composite workpiece as claimed in claim 12 wherein at least one workpiece forming surface of at least one of said die members included a springback angle of from approximately 3°

to approximately 15°

.

18. A formed preconsolidated metal matrix composite workpiece as claimed in claim 12 wherein the clearance between a forming surface of the male die member and a confronting female die member surface that was traversed by said male die member surface during the forming die closure was from approximately 1.3 to approximately 1.5 times the thickness of the workpiece.

19. A formed preconsolidated metal matrix composite workpiece as claimed in claim 17 wherein the workpiece filament is of boron, and the springback angle ranged from approximately 3°

to approximately 5°

.

20. A formed preconsolidated metal matrix composite workpiece as claimed in claim 17 wherein the workpiece filament is of borsic, and the springback angle ranged from approximately 5°

to approximately 10°

.

21. A formed preconsolidated metal matrix composite workpiece as claimed in claim 17 wherein the workpiece filament is of alumina or graphite, and the springback angle ranged from approximately 7°

to approximately 15°

.