Patents by Inventor Matt H. Travis
Matt H. Travis has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20170266691Abstract: A riblet forming system incorporates a gantry which supports a laser and a paint applicator is positioned and moved over an aerodynamic surface. A computer control system is connected for control of the gantry on a predetermined path over the aerodynamic surface and further connected to the laser to control cutting a riblet topography along the predetermined path in a predeposited paint layer.Type: ApplicationFiled: June 8, 2017Publication date: September 21, 2017Inventor: Matt H. Travis
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Publication number: 20160243586Abstract: A riblet forming system incorporates a print head with an array of print jets. A gantry supports the print head and is positioned and moved over an aerodynamic surface. A computer control system is connected for control of the gantry on a predetermined path over the aerodynamic surface and further connected to the print head to control the print jets to sequentially apply print dots from the array of print jets forming a riblet profile along the predetermined path.Type: ApplicationFiled: August 1, 2014Publication date: August 25, 2016Inventor: Matt H. Travis
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Patent number: 8297165Abstract: 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.Type: GrantFiled: January 21, 2011Date of Patent: October 30, 2012Assignee: The Boeing CompanyInventor: Matt H. Travis
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Publication number: 20120118212Abstract: 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.Type: ApplicationFiled: January 21, 2011Publication date: May 17, 2012Applicant: The Boeing CompanyInventor: Matt H. Travis
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Patent number: 7905169Abstract: 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.Type: GrantFiled: August 27, 2009Date of Patent: March 15, 2011Assignee: The Boeing CompanyInventor: Matt H. Travis
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Publication number: 20100083816Abstract: 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.Type: ApplicationFiled: August 27, 2009Publication date: April 8, 2010Applicant: The Boeing CompanyInventor: Matt H. Travis
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Patent number: 7597038Abstract: 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.Type: GrantFiled: January 31, 2007Date of Patent: October 6, 2009Assignee: The Boeing CompanyInventor: Matt H. Travis
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Publication number: 20080178729Abstract: 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.Type: ApplicationFiled: January 31, 2007Publication date: July 31, 2008Inventor: Matt H. Travis
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Patent number: 7400943Abstract: 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.Type: GrantFiled: February 20, 2007Date of Patent: July 15, 2008Assignee: The Boeing CompanyInventors: John L. Vian, Matt H. Travis
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Patent number: 7363111Abstract: 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.Type: GrantFiled: February 20, 2007Date of Patent: April 22, 2008Assignee: The Boeing CompanyInventors: John L. Vian, Matt H. Travis
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Patent number: 7321809Abstract: 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.Type: GrantFiled: December 30, 2003Date of Patent: January 22, 2008Assignee: The Boeing CompanyInventors: John L. Vian, Matt H. Travis
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Patent number: 6202960Abstract: 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.Type: GrantFiled: November 6, 1998Date of Patent: March 20, 2001Assignee: The Boeing CompanyInventors: Matt H. Travis, Nathan D. Batts, Garrett H. DeVlieg
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Patent number: 5586065Abstract: 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.Type: GrantFiled: May 31, 1994Date of Patent: December 17, 1996Assignee: The Boeing CompanyInventor: Matt H. Travis