The Boeing Company

Robert M Kay

Thomas D Harrison

Dwight A Burford

Edwin H Fenn

Danny R High

Mark K Venskus

Tory R Whitcomb

Kent Grantham

Rose Christie, Legal Representative

Michael R Kuss

William W Turnmire

A multi-pass friction stir weld joint and method for forming such joints are provided. The multi-pass weld joint is formed of at least first-pass and second-pass friction stir weld joints that are disposed in the workpiece in a substantially parallel configuration. The first- and second-pass joints define transversely opposite advancing and retreating sides, and the second-pass joint is disposed to at least partially overlap the retreating side of the first-pass joint. Thus, at least some of the material of the workpiece in the first-pass joint is processed during the formation of the second-pass joint.

Multi-pass friction stir welding

A system and associated friction stir welding (FSW) assembly, controller and method for performing a friction stir welding operation are provided. The friction stir welding system includes a FSW device, such as a CNC machine, that includes an actuator capable of moving a FSW tool relative to a workpiece. The system also includes a controller capable of controlling the FSW device to drive the actuator to move the FSW tool. In this regard, the actuator is capable of being driven such that the FSW tool is capable of performing a friction stir welding operation on the workpiece. The controller is capable of monitoring a torque of the actuator to thereby control the FSW device to drive the actuator such that the torque is maintained within a range about a torque setting.

System and associated friction stir welding (FSW) assembly, controller and method for performing a friction stir welding operation

Structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin having at least one offset surface. The structural panel can further include at least first and second stiffeners. The first stiffener can have a first flange portion mated to the skin adjacent to the offset surface. The second stiffener can be spaced apart from the first stiffener and can similarly have a second flange portion mated to the skin adjacent to the offset surface. The structural panel of this embodiment can additionally include a support member mated to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin.

Structural panels for use in aircraft fuselages and other structures

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Wichita, KS, United States of America

Robert M Kay