The Boeing Company

Frederick Marvin Swanstrom

Darrell Darwin Jones

Daniel R Smith

Todd Matthew Harris

Pradip Girish Parikh

Henry John Koppelman

Monte D Wright

Melinda Dae Miller

Jeffrey David Blanch

Systems and methods are provided for assembling a structure. The systems and method including micro pulsing a structure along a track in a process direction by less than a length of the structure. The structure is indexed to one or more work stations by mating indexing features in a manufacturing excess of the structure to complementary features at the work stations. The work stations would the perform work on the structure at the work stations while the structure is indexed to the work stations. Iteratively repeating the micro pulsing and indexing and working upon the structure until it is ready to advance to the next assembly process.

Indexing for airframes undergoing pulsed-line assembly

Systems and methods are provided for fabricating a wing panel. Methods include aligning a strongback over a wing panel, vacuum attaching a wing panel surface and pogos extending beneath the strongback, and adjusting the length of pogos to enforce a contour to the wing panel. Systems include a strongback to extend over a wing panel, adjustable-length pogos extending beneath the strongback, and vacuum couplers to attach to a wing panel surface. Other systems include a track, work stations along the track, a strongback to extend over the wing panel and move along the track, adjustable-length pogos extending beneath the strongback, and vacuum couplers to attach to a wing panel surface. Apparatus includes a shuttle having adapters that mate the shuttle with a track, adjustable-length carriers with vacuum couplers to couple with a wing panel surface, and indexing units that interact with indexing features in a manufacturing excess of the wing panel.

Assembly line fabrication and assembly of aircraft wings

Systems and methods are provided for processing composite parts. One embodiment is a method for preparing a composite part for assembly. The method includes receiving a mandrel to which a composite part has been molded, and operating a work station to install an indexing feature into a manufacturing excess of the composite part.

Installation of indexing features onto composite parts

A method may be present for securing a strip in a structure. A first surface of the strip may be masked with a first tape. A surface of the structure may be masked with a second tape, the surface of the structure defining a desired shape. A sealant may be applied in a groove in the structure. The strip may be positioned in the surface such that a second surface of the strip contacts the sealant; and a caul plate may be pressed against the first surface of the strip, the caul plate including a set of ribs that contact the fairing strip, and the plurality of ribs defining a shape that substantially matches the shape of the surface of the structure. Pressing the caul plate against the first surface of the strip may cause sealant to pass between the set of ribs onto the tapes.

Ribbed caul plate for attaching a strip to a panel structure and method for use

An apparatus may comprise a first skin panel having a first surface, a second skin panel having a second surface, a first flange located at an end of the first skin panel, a second flange located at an end of the second skin panel, and a strip having a third surface. The first skin panel may be located adjacent to the second skin panel such that the first flange and the second flange form a channel. The strip may be bonded in the channel. Fluid flow over the third surface of the strip, the first surface of the first skin panel, and the second surface of the second skin panel may have a desired state.

Growing community of inventors

Burien, WA, United States of America

Frederick Marvin Swanstrom