Rockwell International Corporation

United States of America as Represented by the Secretary of the Air Force

Leonard A Ascani, Jr

C Howard Hamilton

Merle E Riggs

Andrew R Shoemaker

Billy A Burroughs

Burton C Rickey

A method of making filamentary reinforced metallic structures is disclosed. The method uses a stack of workpieces having two principal opposed surfaces. At least one of the outer workpieces comprises at least one inner sheet made of a metal matrix material reinforced with filamentary material and two cover sheets which sandwich the inner sheets and which extend beyond the periphery of the at least one inner sheet. Selected area of the workpieces are treated to prevent bonding at those areas. The workpieces are stacked and positioned between shaping members such that they enclose at least one chamber of at least one of the shaping members. The workpieces are heated to a temperature sufficient to produce diffusion bonding at preselected untreated areas and compressive pressure is applied, both of which are maintained for a sufficient time so as to consolidate the at least one outer workpiece into a single sheet workpiece comprising an interior reinforced portion with a peripheral monolithic portion and to diffusion bond the stack at the untreated areas. Alternately the stack can be press diffusion bonded prior to insertion into the forming apparatus. After bonding, tensile stress is induced, preferably by gas pressure, in at least one consolidated workpiece causing at least a portion of the peripheral monolithic portion to expand superplastically against and into intimate contact with at least one of the shaping members.

Method of making filamentary reinforced metallic structures

A wing pivot assembly for variable sweep wing aircraft for movably securing a wing of the aircraft to the fuselage. The wing pivot assembly has a pivot pin supported by a pair of inboard lugs secured to the fuselage of the aircraft. The wing is, in turn, movably secured to the pivot pin by bearings interposed between the pivot pin and a pair of outboard lugs. In addition an outboard shear fitting located between the wing and the pivot pin movably supports the wing and transfers shear loads to the pivot pin. An inboard shear fitting and anti-rotation device secures and transfers shear loads between the pivot pin and the fuselage. As a result of the above arrangement a multi-load path structure provides for a fail-safe pivot assembly.

Wing pivot assembly for variable sweep wing aircraft

A method for fabricating metallic structures, especially those having intricate shapes, utilizes a combination of flow forming and bonding. A metal preform having flow forming characteristics is positioned relative to a shaping member and a metal workpiece to be joined to the preform. The preform is heated to a temperature range suitable for flow forming. Pressure is applied to cause the preform to flow form against the shaping member and the workpiece. The preform and workpiece are maintained under coordinated temperature-pressure-time duration conditions to produce metallurgical bonding of the preform to the workpiece.

Method of making a metallic structure by combined flow forming and

A method for fabrication of honeycomb metallic structures combining superplastic forming and metallurgical bonding wherein a face sheet is formed and bonded to another face sheet and a core to form the desired structure. A metal honeycomb core is positioned between the first and second metal face sheets. The first face sheet, which has superplastic characteristics, is brought to within a temperature range suitable for superplastic forming. A pressure loading is applied to the first face sheet causing it to deform against the core and second metal face sheet. The face sheets and core are maintained under coordinated temperature-pressure-time duration conditions to produce metallurgical bonding to one another to form the desired honeycomb structure.

Method for fabrication of honeycomb structures

A method for making metallic structures especially those having a complex variable thickness, utilizing superplastic forming and forging. A metal preform having superplastic characteristics is positioned relative to a shaping member which substantially defines the final configuration of the preform. The preform is superplastically expanded and forged against the shaping member to produce the final structure.

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Palos Verdes Estates, CA, United States of America

Leonard A Ascani, Jr