Gregory J Sweers

8645113, Feb 4, 2014

Jul 9, 2008

12/170317

Gregory J. Sweers - Renton WA, US

The Boeing Company - Chicago IL

G06G 7/48

703 8, 703 7

A method for evaluating a lightning/HIRF protection effectiveness of a vehicle design is provided. The method is performed using a computer system coupled to a database. The method includes storing in the database design service life goals and critical characteristics for at least one lightning/HIRF protection component. The method also includes storing in the database a potential for degradation of the at least one component. The potential for degradation is based at least partially on a position where the component is to be installed. The method also includes determining continued functionality of the at least one component using the computer system to compare the vehicle design to the stored design service life goals.

20100153051, Jun 17, 2010

Dec 15, 2008

12/335202

Gary E. Georgeson - Federal Way WA, US
Gregory J. Sweers - Renton WA, US
Nathan P. Renaud - Mountlake Terrace WA, US
James J. Troy - Issaquah WA, US
Scott W. Lea - Renton WA, US

G01P 21/00

702 95

A first method locates a component positioned underneath a surface of a target object using a pointing instrument, wherein a position of the component in the target object coordinate system is known. The first method includes calculating an orientation of the aim point axis of the instrument in the instrument coordinate system for the aim point axis of the instrument to be aligned with the component using at least an inverse calibration matrix, the position of the component in the target object coordinate system, and inverse kinematics of the instrument. The first method also includes rotating the aim point axis of the instrument to the calculated orientation. Second and third methods also are described for locating an access panel for accessing the component and/or maintenance zones in which the component resides.

20220406098, Dec 22, 2022

May 31, 2022

17/829123

- Chicago IL, US
Gregory J. SWEERS - Renton WA, US

G07C 5/00
G07C 5/06
G07C 5/08

Certain aspects of the present disclosure provide techniques for a method, including: receiving multi-dimensional event data associated with a vehicle event; determining, based on the multi-dimensional event data, an inspection classification for the vehicle event; receiving multi-dimensional analysis data associated with the inspection classification for the vehicle event; determining, based on the multi-dimensional analysis data, a repair classification for the vehicle event; receiving multi-dimensional action data associated with the repair classification for the vehicle event; and determining, based on the multi-dimensional action data, a monitoring classification for the vehicle event.

20230073587, Mar 9, 2023

Sep 9, 2021

17/469999

- Chicago IL, US
Peter John Karpinski - Middletown DE, US
Robert Stephen Kanematsu Baker - Lynnwood WA, US
Gregory James Sweers - Renton WA, US

The Boeing Company - Chicago IL

G06T 7/00
H04N 5/232
G06T 15/08
G05D 3/20
G05D 1/10
G01N 21/88

Systems and methods provide technology for inspections including receiving image data from a sensor, the sensor operable to scan an object, where the object is a manufactured object, generating a 3D image record for the object based on the image data, comparing the 3D image record with a stored design model for the object and/or a stored baseline image record of the object, and generating findings data based on the comparing, where the findings data is indicative of a discrepancy identified between the 3D image record and the one or more of the stored design model for the object or the stored baseline image record of the object. The sensor can be mounted on a moving platform such as a robotic arm, a track mounted assembly or a drone. The technology can further include a motion or flight plan for moving the sensor relative to the object.

20230075574, Mar 9, 2023

Sep 8, 2021

17/469167

- Chicago IL, US
Gregory J. Sweers - Renton WA, US
Gary E. Georgeson - Tacoma WA, US
James J. Troy - Issaquah WA, US
Phillip R. Riste - Everett WA, US
Armando X. Membrila - Bothell WA, US

The Boeing Company - Chicago IL

G06K 9/00
G06K 9/62
B64C 39/02

Systems and methods for tracking the location of a non-destructive inspection (NDI) scanner using scan data converted into images of a target object. Scan images are formed by aggregating successive scan strips acquired using one or two one-dimensional sensor arrays. An image processor computes a change in location of the NDI scanner relative to a previous location based on the respective positions of common features in partially overlapping scan images. The performance of the NDI scanner tracking system is enhanced by: (1) using depth and intensity filtering of the scan image data to differentiate features for improved landmark identification during real-time motion control; and (2) applying a loop-closure technique using scan image data to correct for drift in computed location. The enhancements are used to improve localization, which enables better motion control and coordinate accuracy for NDI scan data.

20230051276, Feb 16, 2023

Sep 26, 2022

17/953146

- Chicago IL, US
Joseph L. Hafenrichter - Seattle WA, US
James J. Troy - Issaquah WA, US
Gregory J. Sweers - Renton WA, US

The Boeing Company - Chicago IL

H04B 5/00
H02J 50/80

A method for wirelessly coupling respective transducers of an automated motion platform and a sub-surface sensor node through a skin of a limited-access structure for the purpose of wireless power and data transfer. Coordinates of an as-designed position of the transducer of the sensor node in a local coordinate system of the limited-access structure are retrieved from a non-transitory tangible computer-readable storage medium. Then coordinates of a target position on an external surface of the skin of the limited-access structure are estimated. The target position is calculated to be aligned with the as-designed position of the transducer of the sensor node. The motion platform is moved under computer control so that the transducer onboard the motion platform moves toward the target position. Movement ceases when the transducer onboard the motion platform is at the target position. Then wave energy is transferred between the aligned transducers.

20210394902, Dec 23, 2021

Jun 19, 2020

16/907056

- Chicago IL, US
Gary E. Georgeson - Tacoma WA, US
Gregory J. Sweers - Renton WA, US

The Boeing Company - Chicago IL

B64C 39/02
B64F 5/30
B64F 5/40

Methods and apparatus for UAV-enabled marking of surfaces during manufacture, inspection, or repair of limited-access structures and objects. A UAV is equipped with a marking module that is configured to apply marking patterns (e.g., alignment features) of known dimensions to surfaces. The marking module may include a 2-D plotter that enables free-form drawing capability. The marking process may involve depositing material on the surface. The marking material may be either permanent or removable. A “clean-up” module may be attached to the UAV platform instead of the marking module, and may include solvents and oscillating or vibrating pads to remove the marks via scrubbing. The clean-up module can also be used for initial surface preparation.

20210237381, Aug 5, 2021

Feb 5, 2020

16/782331

- Chicago IL, US
Gary E. Georgeson - Tacoma WA, US
James J. Troy - Issaquah WA, US
Gregory J. Sweers - Renton WA, US

The Boeing Company - Chicago IL

B29C 73/12
B64C 39/02
B64D 1/02
B29C 73/10
C09J 5/06

Methods and apparatus for performing repair operations using an unmanned aerial vehicle (UAV). A UAV carries a repair patch ensemble containing all repair materials (including a repair patch, a heating blanket and other ensemble materials) in a prepackaged form to the repair area. During flight of the UAV, the repair patch is vacuum adhered to the heating blanket. Vacuum pressure is also used to hold the repair patch ensemble in position on the composite surface of the structure. Then the hot bond process is enacted to bond the repair patch to the repair area. In accordance with one embodiment, the hot bond process involves heating the repair patch to adhesively bond the repair patch while applying vacuum pressure to consolidate the composite material. Then the repair patch is released from the ensemble and residual ensemble materials (heating blanket, bleeder material, and release films) are removed by the UAV.