The Boeing Company

Theboeing Company

Edward John Batt

Antonio C Micale

Farahnaz Sisco

Daniel R Smith

Eric M Reid

Matthew R Desjardien

Darrell Darwin Jones

Clayton Lynn Munk

James Niemann Buttrick

Donald A Mottaz

Scott William Gunther

Azita N Namdaran

Noman S Noor

Chris G Couevas

Jayson J Aquino

Tanni Sisco

Andrew Michael Huckey

Raymond N Henderson

Bernard Karl Manderville

David Michael Kumpf

Craig Roedel

Samuel Edward Antonucci

Randy Woolridge

Mary C Heath

Jamie E Bigley

Farahnaz Tanni Sisco

James N Buttrick

Clayton L Munk

Mario Ramos

An apparatus for automated application of rivets to a part is described, in which an operator is not required to manually align a rivet gun with each hole to be riveted or to manually squeeze the rivet into place. The apparatus includes a frame assembly, a tool positioning assembly attached to the frame assembly, and a movable tool assembly engaged with the tool positioning assembly and configured to be moved with respect to the tool positioning assembly. The tool positioning assembly is adjustable to correspond with a position of a number of rivet holes on a part to be riveted. In this way, the movable tool assembly is able to sequentially align with each of a number of rivet holes via alignment with the tool positioning assembly and to apply a rivet to each of the rivet holes.

Apparatus and method for automated application of rivets

Methods and apparatus to remove frangible fastener remnants are disclosed. A disclosed example apparatus to install a frangible fastener includes a drive tool having a drive socket operable to rotate a separable nut portion of the frangible fastener, and a fastener interface defining an interior for receiving at least the nut portion, the fastener interface being disposed on a drive end of the drive tool, where the drive socket is movable within the fastener interface and operable to rotate the frangible fastener, and where the separable nut portion of the frangible fastener is removed when the frangible fastener is installed. The apparatus also includes a nut-portion removal tube depending from the interior of the fastener interface, and a vacuum generator in fluid communication with the removal tube and configured to cause the separable nut portion to be removed from the interior and through the removal tube.

Methods and apparatus to remove frangible fastener remnants

A method for assembly manufacturing including positioning a workpiece in an assembly position within an operational cell, positioning a fastening machine relative to the workpiece, wherein the fastening machine includes a robot frame comprising a throat, an assembly end effector coupled to the frame about the throat, and a plurality of linear actuators coupled to the frame, moving, by the plurality of linear actuators, the fastening machine about at least one of six degrees of freedom to receive at least a portion of the workpiece within the throat and position the assembly end effector relative to the workpiece, and performing, by the fastening machine, a fastening operation on the workpiece.

System and method for assembly manufacturing

Embodiments herein provide determining blind fastener length. One embodiment is a gauge tool that includes a base plate, and a nose piece including a hollow cylindrical member extending through the base plate and an expandable tip configured to radially expand to circumferentially contact a back rim of a hole. The nose piece is configured to slide with respect to the base plate to retract into the base plate until stopped by the expandable tip pressing the back rim of the hole. The gauge tool further includes a measurement device configured to detect a translating distance of a slidable member moving with retraction of the nose piece, and to display the translating distance for determining a fastener length for the hole.

Gauge tool for determining blind fastener length

A system and method are provided to automate the assembly of a wing panel, such as utilized by commercial aircraft. In the context of a system, a tacking cell is provided that is configured to tack one or more stringers to a skin plank. The system also includes a riveting cell configured to receive a tacked plank from the tacking cell and to rivet the one or more stringers to the skin plank. The system also includes a splicing cell configured to receive a plurality of riveted planks from the riveting cell and to attach one or more splice stringers to the plurality of riveted planks. Further, the system includes a side of body cell configured to receive a spliced panel from the splicing cell and to attach a side of body chord thereto to produce a wing panel.

System and method for manufacturing a wing panel

A method for assembly manufacturing may include the steps of: (1) positioning, by a material-handling system, an unassembled workpiece in a first assembly position within a tacking cell, (2) performing, by a first plurality of fastening machines, a tack fastening operation on the unassembled workpiece to form a partially assembled workpiece, (3) transferring, by the material-handling system, the partially assembled workpiece from the tacking cell to a fastening cell, (4) positioning, by the material-handling system, the partially assembled workpiece in a second assembly position within the fastening cell, and (5) performing, by a second plurality of fastening machines, a final fastening operation on the partially assembled workpiece to form an assembled workpiece.

A blind tack fastener includes a pull stem having an elongated shaft with an extended tail portion. The blind tack fastener also includes a crush-initiating washer, a crush sleeve, and a swage collar, surrounding the elongated shaft of the pull stem. The elongated shaft has a breakaway groove configured to create a predictive fracture point below the head-end surface of the swage collar, such that a hole in the swage collar serves as a centering lead-in for a drill that can be used to remove the blind tack fastener.

Blind track bolt with higher clamp-up strength

A method of assembling a detail to a flexible member includes positioning the detail against a plurality of reader pogos, and axially displacing the plurality of reader pogos to substantially conform to a detail contour. The method additionally includes recording reader pogo position data representing the detail contour, clamping a flexible member against a plurality of positioning pogos, and axially displacing the plurality of positioning pogos complementary to the reader pogo position data. In addition, the method includes deflecting, using the positioning pogos, the flexible member into a contour corresponding to the reader pogo position data, and assembling the detail to the flexible member.

Method of assembling components

A method and an end effector for installing an element over a member associated with an object. An end effector may be attached to the object. The element may be loaded onto an element installer by an element loader of the end effector. The element may be installed onto the member associated with the object by the element installer.

Automated installation of frangible elements

A method and apparatus for installing a frangible collar onto a fastener installed in a hole using an end effector in which rotation of the fastener is not restricted by the hole. Rotation of the fastener may be restricted using the end effector. A frangible collar may be installed onto the fastener by an element installer of the end effector while the while restricting rotation of the fastener. A frangible portion of the frangible collar may be sheared off by torqueing the frangible portion using the end effector.

Blind tack bolt with higher clamp-up strength

In an example, a clamp foot for a clamp assembly includes a housing having a distal end for engaging a workpiece, an aperture in the distal end of the housing, and a cavity in the housing extending proximally from the aperture. The clamp foot also includes a flapper in the cavity and adjacent to the distal end. The clamp foot further includes a pneumatic port in the cavity configured to direct a pneumatic force from a pneumatic source to the flapper, and a vacuum port in the cavity for coupling the cavity to a vacuum source. Responsive to the pneumatic force, the flapper is movable within the cavity to separate debris from the workpiece. The vacuum port is configured to remove from the cavity, via a vacuum force from the vacuum source, the debris separated from the workpiece by the flapper.

Systems and methods for control of foreign object debris

A method and apparatus are presented. A first roller has a sensor that senses a speed of the workpiece while the workpiece is in contact with the first roller and moving relative to the first roller causing the first roller to rotate. The sensor senses the speed of the workpiece from a rotation of the first roller. A second roller causes the sealant on the second roller to be applied to a surface of the workpiece when the workpiece is in contact with the second roller and moving relative to the second roller. The second roller is rotationally linked to the first roller. A third roller causes the sealant on the surface of the workpiece to spread on the surface when the workpiece is in contact with the third roller and moving relative to the third roller. The third roller is rotationally linked to the second roller.

Method and system for applying a coating

A method for assembling an aircraft engine nacelle inlet lip includes automatically positioning, with a controller an automated workstation in two degrees of freedom to position an articulated assembly fixture docking station in at least two predetermined joining positions, and effecting, with the controller, an ordered assembly of at least a forward bulkhead joint, a forward bulkhead to lipskin joint, a chord member to lipskin joint, an inner barrel to lipskin joint, an aft bulkhead to lipskin joint and an outer barrel to lipskin joint through an interface between an automated assembly tool and at least one of a plurality of assembly fixtures interchangeably mounted on the docking station, where each assembly fixture corresponds to an assembly step of the aircraft engine nacelle inlet lip and at least one of the assembly fixtures is common to more than one assembly step of the aircraft engine nacelle inlet lip.

Growing community of inventors

Bothell, WA, United States of America

Edward John Batt