The Boeing Company

Scientific Games International, Inc.

Other

Battelle Memorial Institute

Theboeing Company

Scientific Games Royalty Corporation

University of Washington

Scientific Games Corporation

James C Kennedy

Gary E Georgeson

William Paul Motzer

Barry Allen Fetzer

Jill Paisley Bingham

Jeffry J Garvey

Michael C Hutchinson

James J Troy

Alan Frank Stewart

Steven Kenneth Brady

Scott Wesley Lea

Dennis P Sarr

Steven Ray Walton

Michael J Duncan

Thomas E Riechers

Mark L Little

Hien T Bui

Clyde T Uyehara

Matthew N O'Donnell

Jeffrey Reyner Kollgaard

Fred D Young

Ivan Pelivanov

Martin L Freet

Navpreet S Grewal

Ronald E VonWahlde

Darrell Darwin Jones

Daniel R Smith

Michael Robert Chapman

Michael D Fogarty

Clarence Lavere Gordon, Iii

Jay R Sayre

Jeremy Evan Justice

Mark A Lee

Chuck A Plaxico

Roy Martin Gagnon

William D Meade

Michael D Horky

Joseph Lawrence Hafenrichter

Roger W Engelbart

Vincent Daniel McGinniss

Richard Henry Bossi

Daniel James Wright

Mark Alan Negley

Hong Hue Tat

William F Behm

Yuan-Jye Wu

William Joseph Tapia

Joseph R Preston

John Z Lin

Wayne E Woodmansee

Michael R Kennedy

David A Lilienthal

Megan Moore

Kary L Valentine

Carl B Gifford

Mark Stasik

Carl J Serman

Charles R Miele

Richard C Krotzer

Sadie Lee Fieni

Edward L Puckett

Steven J Kennedy

W Scott Versluis

John William Adams

Mark Daniel Winters

James E Cook

John M Pryor

Walter Jefferson Harris

Daniel Johnson

Kristofer Logan Peterson

William M Lankelis

Benjamin Eric Mitchell

Martin Kennedy

Clayton M Little

Christopher L Mares

Aman Safaei

Edward W Wahler

Wen Rong

Kathryn T Moore

Ronald E Vonwahlde

Clarence Lavere Iii Gordon

Michael Joseph Duncan

Micheal C Hutchinson

Jessica Offutt

Sadie L Fieni

Hue Tat Hong

Mark D Winters

Gary Ernest Georgeson

Jill P Bingham

Systems and methods are provided for inspecting aircraft fuselages. Non-Destructive Inspection (NDI) stations inspect sections of a fuselage via pulsed-line assembly techniques. After each pulse, a section of fuselage is moved by less than its length, and one or more NDI stations disposed at different portions of the section to inspect the section of fuselage for out-of-tolerance conditions. A method for inspecting a structure for inconsistencies which includes advancing a structure along a track in a process direction through a Non-Destructive Inspection (NDI) station, indexing the structure to the NDI station and inspecting the structure with the NDI station.

Non-destructive inspection station for aircraft fuselage sections fabricated in an assembly line

The present invention provides a taser alarm system that comprises a taser housing that includes laser sights, a red light, an alarm system, and a circuit board, a cartridge system, and a remote lock communicatively connected to the circuit board included in the taser housing, the remote lock includes a button that, when pressed, sends a signal to the circuit board to remotely turn on or off the taser alarm system.

Taser safety system

Systems and methods are provided for inspecting a wing panel. Some methods include advancing a wing panel through a Non-Destructive Inspection (NDI) station, and inspecting the wing panel with inspection heads at the NDI station. The wing panel may be suspended beneath a strongback during inspection and/or advancement, such as by using vacuum couplers and/or adjustable-length pogos of the strongback, and suspending may include enforcing a contour to the wing panel using the vacuum couplers and/or pogos. Other methods include receiving a wing panel at an NDI station and inspecting a portion thereof during movement through the NDI station. Some systems include a track, a strongback to suspend a wing panel beneath it and to advance along the track, and an NDI station disposed at the track to inspect the wing panel while suspended.

Assembly line fabrication and assembly of aircraft wings

Disclosed herein is an ultrasonic inspection probe for inspecting parts. The ultrasonic inspection probe comprises a probe body that comprises an ultrasonic array and a plate attachment surface. The ultrasonic array comprises a plurality of ultrasound elements, each selectively operable to generate an ultrasonic beam and each fixed relative to the plate attachment surface. The ultrasonic inspection probe also comprises an interface plate, comprising a body attachment surface, removably attachable to the plate attachment surface of the probe body, and a part inspection surface, shaped to complement a shape of one of the parts.

Ultrasonic inspection probe, system, and method

A method for testing a structure includes steps of: identifying a three-dimensional position of a surface of the structure relative to a reference frame; transmitting laser light from an output of a transmitter onto the surface of the structure to form ultrasonic waves in the structure and to detect a response to the ultrasonic waves; based on the three-dimensional position of the surface, moving the laser light over the structure along a scan path so that the output of the transmitter is located at a constant offset distance from the surface and that the laser light, transmitted from the output of the transmitter, is directed onto the surface at a constant angle of projection; and based on the response to the ultrasonic waves, determining whether an inconsistency is present in the structure.

System and method for testing a structure using laser ultrasound

An ultrasonic inspection device for inspection of a structure. The device includes a body with a first side and a second side that are on opposing sides of a gap. The gap is sized to receive the structure. A probe is attached to the first side and transmits ultrasonic signals at the structure. A reflector plate is attached to the second side and is fixed relative to the probe and reflects the signals that pass through the structure. The probe is configured to detect the signals that reflect off the structure and to detect the signals that pass through the structure and reflect off the reflector plate. The received signals provide for pulse echo and through transmission inspection of the structure.

Ultrasonic inspective device for simultaneous pulse echo and through transmission inspection

Methods that provide wrinkle characterization and performance prediction for wrinkled composite structures using automated structural analysis. In accordance with some embodiments, the method combines the use of B-scan ultrasound data, automated optical measurement of wrinkles and geometry of cross-sections, and finite element analysis of wrinkled composite structure to provide the ability to assess the actual significance of a detected wrinkle relative to the intended performance of the structure. The disclosed method uses an ultrasonic inspection system that has been calibrated by correlating ultrasonic B-scan data acquired from reference standards with measurements of optical cross sections (e.g., micrographs) of those reference standards.

Wrinkle characterization and performance prediction for composite structures

Systems, methods, and apparatus for ultrasonic inspection of parts are disclosed. A method for inspection of a part comprises transmitting, by a source, an initial signal towards the part. The method further comprises reflecting, off of a surface of the part, the initial signal to generate a surface reflection signal. Also, the method comprises receiving, by a receiver, the surface reflection signal. In addition, the method comprises determining, by a processor(s), a shape of the surface of the part by using a magnitude of the surface reflection signal and an echo travel time of the initial signal with respect to the surface reflection signal. Additionally, the method comprises determining, by a processor(s), a surface inspection signal commensurate with the shape of the surface of the part. Further, the method comprises transmitting, by the source, the surface inspection signal towards the part for inspection of the surface of the part.

Ultrasonic inspection of parts

Described herein is an apparatus, for shielding light generated by a laser during non-destructive inspection of an object. The apparatus includes a light shield at least partially enveloping the laser and defining a first opening through which light generated by the laser passes from the laser to the object. The light shield is opaque and includes at least one first biasing mechanism. The apparatus also includes at least one first light seal coupled to the light shield about the first opening of the light shield. The at least one first biasing mechanism is configured to urge resilient deformation of the at least one first light seal against the object. When the at least one first light seal is resiliently deformed against the object, light generated by the laser is constrained within a light containment space defined between the light shield, the at least one first light seal, and the object.

Apparatus, systems, and methods for inspecting a part

Systems and methods according to one or more embodiments are provided for performing rotorcraft based non-destructive physical inspection and/or testing. In one example, a system includes a rotorcraft and a rotating arm coupled to the rotorcraft. An inspection sensor is coupled to a first end of the rotating arm and configured to be placed in close proximity to and/or in physical contact with a surface of an object.

Rotorcraft inspection systems and methods

A lottery ticket dispenser array includes a frame and a plurality of separate bins contained within the frame. Each bin includes a housing having a front side that faces a purchaser in operational use of the dispenser array, an opposite back side, and an internal space for receipt of a supply of interconnected lottery tickets, wherein each lottery tickets contains a code printed thereon. Each bin has an electronic drive mechanism that dispenses the lottery tickets therefrom. The bins are separately removable and insertable into the array. A printer module is provided in the array and has a size and configuration so as to be insertable into the array in place of at least one of the bins.

Smart bin lottery ticket dispenser with modular printer bin

A lottery ticket dispenser array includes a frame and a plurality of separate bins contained within the frame. Each bin includes a housing having a front side that faces a purchaser in operational use of the dispenser array, an opposite back side, and an internal space for receipt of a supply of interconnected lottery tickets, wherein each lottery tickets contains a code printed thereon. Each bin has an electronic drive mechanism that dispenses the lottery tickets therefrom. A controller is in communication with each of the drive mechanisms to initiate a dispense sequence upon receipt of a ticket dispense command from the controller. The controller is configured on the frame and is variably positional relative to the frame between different operational positions.

Smart bin lottery ticket dispenser with integrated controller

A method and system may be provided for determining a set of parameters for preparing a skin for assembly to a substructure. The skin may be nondestructively inspected to gather a data set relating to the skin thickness. Sets of as-built thickness values for the skin and of deviations from a nominal map of the skin thickness may be calculated. A mating area for the skin and substructure and a set of one or more locations for fastener holes in the mating area may be determined. A set of parameters for the one or more fastener holes and a set of one or more fastener lengths may be generated using the deviations. A tool may cut the one or more fastener holes using the set of parameters and the skin and substructure may be fastened using fasteners selected according to the generated set of one or more fastener lengths. The system may be used with a numerically-controlled machine, a nondestructive inspection system, and may include a computer coupled to the nondestructive inspection system for calculating the parameters for preparing the holes and the lengths of the one or more fasteners.

Predictive preparation of material for joint assembly

A method of detecting local material changes in a composite structure is presented. A pulsed laser beam is directed towards the composite structure comprised of a number of composite materials. Wide-band ultrasonic signals are formed in the composite structure when radiation of the pulsed laser beam is absorbed by the composite structure. The wide-band ultrasonic signals are detected to form data. The data is processed to identify a local frequency value for the composite structure. The local frequency value is used to determine if local material changes are present in the number of composite materials.

Composite inspection

Growing community of inventors

Renton, WA, United States of America

James C Kennedy