MATT HAMILTON TRAVIS
Pilots at 317 Pl, Spring Glen, WA

5586065, Dec 17, 1996

May 31, 1994

8/252583

Matt H. Travis - Fall City WA

The Boeing Company - Seattle WA

H04B 1500

364574

Aircraft cabin noise and engine vibration are monitored at selected cabin and engine locations (51a/51b), respectively. An optimizing equation uses aircraft cabin noise information to separately determine for each engine a balance solution (60) that minimizes aircraft cabin noise at the selected cabin locations over the engine RPM range of interest. Next, the balance solutions are used to predict the engine vibration levels (63) that will be produced if the balanced solution is implemented. Then a test (65) is made to determine if the predicted engine vibration levels are acceptable, i. e. , below a predetermined level. If acceptable, the balance solutions are used to select balance weights suitable for the engines being balanced (66) and the result displayed (67) for implementation by engine maintenance personnel. If the predicted vibration level is unacceptable, a new balance solution is determined for each engine (68) using the optimizing equation constrained by the allowable vibration level.

6202960, Mar 20, 2001

Nov 6, 1998

9/187613

Matt H. Travis - Fall City WA
Nathan D. Batts - Edmonds WA
Garrett H. DeVlieg - Bellevue WA

The Boeing Company - Seattle WA

B64C 2532

244103R

A method and apparatus for eliminating aircraft landing gear fore-and-aft vibration is provided. The method includes using a tuned mass absorber attached to the landing gear. The gear walk motion has a peak amplitude motion and a pre-peak amplitude motion. The tuned mass absorber includes a mass and a spring, with the mass being oriented to move in a fore-and-aft direction at a frequency and amplitude that counterbalances the gear fore-and-aft vibration. The mass in one embodiment is of an amount in the range of 1 to 2 percent of the effective landing gear mass. In one embodiment, the tuned mass absorber is attached to a landing gear strut near the strut's distal end. The motion of the tuned mass absorber mass moves at a frequency and amplitude that counterbalances the gear walk pre-peak amplitude motion. Therefore, the absorber mass is of an amount less than the mass required to counterbalance gear walk peak amplitude motion. The tuned mass absorber thereby eliminates the gear walk motion in its formation.

7597038, Oct 6, 2009

Jan 31, 2007

11/701304

Matt H. Travis - Fall City WA, US

The Boeing Company - Chicago IL

B64D 1/04, F41A 21/00, F42B 10/56

89 151, 89 153, 89 154, 89 29, 89 135, 89 1801, 89 1802, 89 1804, 102386, 102395, 102342, 102357

An exemplary stores launch tube includes an outer tube and an inner tube. The inner tube is disposed interior the outer tube and is configured to reduce load as a store exits therefrom. The inner tube may be made of a flexible material. At least one load-reducing device may be disposed between the inner tube and the outer tube. The inner tube may be received within a canister that has an outer casing that is attachable to the outer tube. Alternately, the inner tube may be attached directly to the outer tube. The inner tube may include more than one tube section. If desired, filler material, such as foam, may be disposed between the inner tube and the outer tube. The outer tube may have a substantially circular cross-section, or an oval cross-section, or any cross-section as desired to accommodate structural considerations.

7905169, Mar 15, 2011

Aug 27, 2009

12/548824

Matt H. Travis - Fall City WA, US

The Boeing Company - Chicago IL

B64D 1/04, F41A 21/00, F42B 10/56

89 151, 89 153, 89 154, 89 29, 89 135, 89 1801, 89 1802, 89 1804, 102386, 102395, 102342, 102357

Stores launch tubes and vehicles equipped with stores launch tubes are disclosed. According to a particular illustrative example, a stores launch tube includes a tube member and a flexible seal. The flexible seal couples an exterior of the tube member to a hull. The flexible seal acts as a pressure barrier against an ambient environment.

8297165, Oct 30, 2012

Jan 21, 2011

13/011721

Matt H. Travis - Fall City WA, US

The Boeing Company - Chicago IL

B64D 1/04, F41A 21/00, F42B 10/56

89 151, 89 153, 89 154, 89 29, 89 135, 89 1801, 89 1802, 89 1804, 102386, 102395, 102342, 102357

Apparatuses, vehicles, and methods to reduce loads applied to a store when the store is launched from the vehicle are disclosed. A particular apparatus includes a launch chamber and a flap. The launch chamber has a first portion configured to receive a store. A second portion is configured to be positioned over an opening in a hull of a vehicle. The chamber has a forward end and an aft end. The flap is positioned a distance from the aft end of the launch chamber. The flap has a first end rotatably mounted proximate to the first portion of the launch chamber and has a second end extending toward the second portion of the launch chamber. The flap is configured to rotate about the first end when the store impacts the flap due to the forces applied to the store by the fluid when the store is launched.

7363111, Apr 22, 2008

Feb 20, 2007

11/708437

John L. Vian - Renton WA, US
Matt H. Travis - Fall City WA, US

The Boeing Company - Chicago IL

G01M 1/38

700279, 73 66, 700280, 706 23

Methods and systems for analyzing engine unbalance conditions are disclosed. In one embodiment, a method includes receiving vibrational data from a plurality of locations distributed over an engine and a surrounding engine support structure, and inputting the vibrational data into a neural network inverse model. The neural network inverse model establishes a relationship between the vibrational data and an unbalance condition of the engine, and outputs diagnostic information indicating the unbalance condition of the engine. In a further embodiment, a method further includes subjecting the vibrational data to a Fast Fourier Transformation to extract a desired once per revolution vibrational data prior to input to the neural network inverse model.

7321809, Jan 22, 2008

Dec 30, 2003

10/750294

John L. Vian - Renton WA, US
Matt H. Travis - Fall City WA, US

The Boeing Company - Chicago IL

G01M 1/38

700279, 73 66, 700280, 706 23

Methods and systems for analyzing engine unbalance conditions are disclosed. In one embodiment, a method includes receiving vibrational data from a plurality of locations distributed over an engine and a surrounding engine support structure, and inputting the vibrational data into a neural network inverse model. The neural network inverse model establishes a relationship between the vibrational data and an unbalance condition of the engine, and outputs diagnostic information indicating the unbalance condition of the engine. In a further embodiment, a method further includes subjecting the vibrational data to a Fast Fourier Transformation to extract a desired once per revolution vibrational data prior to input to the neural network inverse model.

7400943, Jul 15, 2008

Feb 20, 2007

11/708208

John L. Vian - Renton WA, US
Matt H. Travis - Fall City WA, US

The Boeing Company - Chicago IL

G01M 1/38

700279, 73 66, 700280, 706 23

Methods and systems for analyzing engine unbalance conditions are disclosed. In one embodiment, a method includes receiving vibrational data from a plurality of locations distributed over an engine and a surrounding engine support structure, and inputting the vibrational data into a neural network inverse model. The neural network inverse model establishes a relationship between the vibrational data and an unbalance condition of the engine, and outputs diagnostic information indicating the unbalance condition of the engine. In a further embodiment, a method further includes subjecting the vibrational data to a Fast Fourier Transformation to extract a desired once per revolution vibrational data prior to input to the neural network inverse model.