Patents by Inventor Matthew S. Stauffer
Matthew S. Stauffer 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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Patent number: 11919617Abstract: Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.Type: GrantFiled: September 21, 2021Date of Patent: March 5, 2024Assignee: The Boeing CompanyInventors: Patrick J. Macko, Byron James Autry, James R. Kendall, Samuel James Knutson, Brian T. Peters, Michael J. Bailey, Matthew S. Stauffer, Steven Wanthal, Santiago M. Mejia, Sara Murphy
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Patent number: 11618550Abstract: A rotor assembly for a fixed-wing VTOL aircraft. The rotor assembly is configured to provide vertical flight for the fixed-wing VTOL aircraft. In one embodiment, the rotor assembly includes a hub assembly, a first rotor blade affixed to the hub assembly, and a second rotor blade affixed to the hub assembly. The hub assembly orients the second rotor blade in relation to the first rotor blade about an axis of rotation of the hub assembly with the first rotor blade and the second rotor blade vertically stacked when the hub assembly is stopped for wing-borne flight.Type: GrantFiled: April 1, 2021Date of Patent: April 4, 2023Assignee: The Boeing CompanyInventors: Michael J. Duffy, Matthew S. Stauffer
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Publication number: 20220373992Abstract: A method for computer analysis of a quality of an as-programmed surface of a composite laminate. A first data set representing an as-programmed top surface is generated based on as-programmed ply definitions and a tool surface definition. Thereafter, a second data set representing coordinates of points of a first mesh on the as-programmed top surface is generated, which points form a first mesh. Then a third data set representing coordinates of points of a second mesh on a defined tool surface is generated. A respective angle of each mesh element of the first mesh relative to a corresponding mesh element of the second mesh is then calculated. Each angle is compared to a threshold of acceptable angle. In response to an acceptable number of angles exceeding a threshold of acceptable angle, a tow placement machine may be programmed to fabricate a composite structure using the as-programmed ply definitions.Type: ApplicationFiled: March 15, 2022Publication date: November 24, 2022Applicant: The Boeing CompanyInventors: Matthew S. Stauffer, Kayley E. Seawright, Russell A. Strope, Michael S. Lindgren, Daniel E. Gonsor, Ashutosh Mani
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Publication number: 20220194547Abstract: Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.Type: ApplicationFiled: September 21, 2021Publication date: June 23, 2022Inventors: Patrick J. Macko, Byron James Autry, James R. Kendall, Samuel James Knutson, Brian T. Peters, Michael J. Bailey, Matthew S. Stauffer, Steven Wanthal, Santiago M. Mejia, Sara Murphy
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Patent number: 11167848Abstract: System and method for loading cargo onto an unmanned aerial vehicle (UAV). One embodiment is a cargo pod for an unmanned aerial vehicle (UAV). The cargo pod includes a hollow body that forms a section of a fuselage of the UAV, and further includes a latching mechanism that releasably secures the hollow body with the fuselage of the UAV.Type: GrantFiled: March 23, 2018Date of Patent: November 9, 2021Assignee: The Boeing CompanyInventors: Michael James Duffy, Matthew S. Stauffer, Justin Fowler Rogers
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Publication number: 20210237853Abstract: A rotor assembly for a fixed-wing VTOL aircraft. The rotor assembly is configured to provide vertical flight for the fixed-wing VTOL aircraft. In one embodiment, the rotor assembly includes a hub assembly, a first rotor blade affixed to the hub assembly, and a second rotor blade affixed to the hub assembly. The hub assembly orients the second rotor blade in relation to the first rotor blade about an axis of rotation of the hub assembly with the first rotor blade and the second rotor blade vertically stacked when the hub assembly is stopped for wing-borne flight.Type: ApplicationFiled: April 1, 2021Publication date: August 5, 2021Inventors: Michael J. Duffy, Matthew S. Stauffer
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Patent number: 10994829Abstract: A rotor assembly for a fixed-wing VTOL aircraft. The rotor assembly is configured to provide vertical flight for the fixed-wing VTOL aircraft. In one embodiment, the rotor assembly includes a hub assembly, a first rotor blade affixed to the hub assembly, and a second rotor blade affixed to the hub assembly. The hub assembly orients the second rotor blade in relation to the first rotor blade about an axis of rotation of the hub assembly with the first rotor blade and the second rotor blade vertically stacked when the hub assembly is stopped for wing-borne flight.Type: GrantFiled: September 22, 2017Date of Patent: May 4, 2021Assignee: The Boeing CompanyInventors: Michael J. Duffy, Matthew S. Stauffer
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Patent number: 10745098Abstract: A composite structural member and an arrangement of such composite structural members are constructed to provide a multi-functional under-floor airframe that reacts flight, handling and internal cargo loads, and is capable of absorbing energy when subjected to vertically applied compression loads, such as loads that may be applied in hard landing or crash situations. The composite structural member and arrangement of such composite structural members adds no parasitic weight to the aircraft, i.e., there is no need for additional energy-absorbing systems, structures or mechanism; and is lighter weight as compared to metal. The composite structural member and related parts of the arrangement of such composite structural members are designed to progressively collapse throughout the stroke (or displacement) that occurs when a dynamic compressive load is applied to the structural member and to work together with crashworthy seats to mitigate injuries to occupants.Type: GrantFiled: September 5, 2017Date of Patent: August 18, 2020Assignee: The Boeing CompanyInventors: Douglas R. Ludin, Matthew S. Stauffer, Akif Bolukbasi, Eric Schulze
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Patent number: 10598251Abstract: A vibration damper including a frame having at least a first cavity, a frame first end and a frame second end spaced from the frame first end; a shaft slidably coupled to and extending into the frame where the shaft extends through the first cavity; a first vibration isolator disposed within the first cavity where the shaft extends through the first vibration isolator so as to capture the first vibration isolator within the first cavity where the first vibration isolator interfaces with the frame second end; and a second vibration isolator disposed on the shaft, where the shaft extends through the second vibration isolator so as to capture the second vibration isolator on the shaft where the second vibration isolator interfaces with the frame second end opposite the first vibration isolator, where the first vibration isolator and the second vibration isolator act only in compression.Type: GrantFiled: April 14, 2017Date of Patent: March 24, 2020Assignee: The Boeing CompanyInventors: Douglas R. Ludin, Matthew S. Stauffer
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Publication number: 20190291626Abstract: System and method for loading cargo onto an unmanned aerial vehicle (UAV). One embodiment is a cargo pod for an unmanned aerial vehicle (UAV). The cargo pod includes a hollow body that forms a section of a fuselage of the UAV, and further includes a latching mechanism that releasably secures the hollow body with the fuselage of the UAV.Type: ApplicationFiled: March 23, 2018Publication date: September 26, 2019Inventors: Michael James Duffy, Matthew S. Stauffer, Justin Fowler Rogers
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Publication number: 20190092461Abstract: A rotor assembly for a fixed-wing VTOL aircraft. The rotor assembly is configured to provide vertical flight for the fixed-wing VTOL aircraft. In one embodiment, the rotor assembly includes a hub assembly, a first rotor blade affixed to the hub assembly, and a second rotor blade affixed to the hub assembly. The hub assembly orients the second rotor blade in relation to the first rotor blade about an axis of rotation of the hub assembly with the first rotor blade and the second rotor blade vertically stacked when the hub assembly is stopped for wing-borne flight.Type: ApplicationFiled: September 22, 2017Publication date: March 28, 2019Inventors: Michael J. Duffy, Matthew S. Stauffer
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Publication number: 20190071163Abstract: A composite structural member and an arrangement of such composite structural members are constructed to provide a multi-functional under-floor airframe that reacts flight, handling and internal cargo loads, and is capable of absorbing energy when subjected to vertically applied compression loads, such as loads that may be applied in hard landing or crash situations. The composite structural member and arrangement of such composite structural members adds no parasitic weight to the aircraft, i.e., there is no need for additional energy-absorbing systems, structures or mechanism; and is lighter weight as compared to metal. The composite structural member and related parts of the arrangement of such composite structural members are designed to progressively collapse throughout the stroke (or displacement) that occurs when a dynamic compressive load is applied to the structural member and to work together with crashworthy seats to mitigate injuries to occupants.Type: ApplicationFiled: September 5, 2017Publication date: March 7, 2019Applicant: The Boeing CompanyInventors: Douglas R. Ludin, Matthew S. Stauffer, Akif Bolukbasi, Eric Schulze
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Patent number: 10118347Abstract: A tool for laying up composite material to form a workpiece having a target contour is disclosed. The tool includes a support structure including an elongated member having a longitudinal axis, and support plates connected to the elongated member and spaced apart from each other along the longitudinal axis. The elongated member includes a metallic material. The tool also includes a non-metallic backing structure connected to the support plates, the non-metallic backing structure comprising a working surface that includes a backing contour complementary to the target contour.Type: GrantFiled: March 6, 2017Date of Patent: November 6, 2018Assignee: The Boeing CompanyInventors: Matthew S. Stauffer, Douglas R. Ludin
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Publication number: 20180298978Abstract: A vibration damper including a frame having at least a first cavity, a frame first end and a frame second end spaced from the frame first end; a shaft slidably coupled to and extending into the frame where the shaft extends through the first cavity; a first vibration isolator disposed within the first cavity where the shaft extends through the first vibration isolator so as to capture the first vibration isolator within the first cavity where the first vibration isolator interfaces with the frame second end; and a second vibration isolator disposed on the shaft, where the shaft extends through the second vibration isolator so as to capture the second vibration isolator on the shaft where the second vibration isolator interfaces with the frame second end opposite the first vibration isolator, where the first vibration isolator and the second vibration isolator act only in compression.Type: ApplicationFiled: April 14, 2017Publication date: October 18, 2018Inventors: Douglas R. LUDIN, Matthew S. STAUFFER
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Patent number: 9895836Abstract: Technologies for fused filament fabrication using multi-directional layering are disclosed herein. According to aspects of the disclosure, a component may be strengthened using a multi-directional layering manufacturing technique. In some implementations, one or more portions of the component are manufactured in different orientations. In still further implementations, one layer of a component is laid down in a first orientation and a second layer of the component is laid down in a second orientation.Type: GrantFiled: September 16, 2014Date of Patent: February 20, 2018Assignee: The Boeing CompanyInventor: Matthew S. Stauffer
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Publication number: 20170173896Abstract: One example of the present disclosure relates to a tool for laying up composite material to form a workpiece having a target contour. The tool includes a support structure including an elongated member having a longitudinal axis, and support plates connected to the elongated member and spaced apart from each other along the longitudinal axis. The elongated member includes a metallic material. The tool also includes a non-metallic backing structure connected to the support plates, the non-metallic backing structure comprising a working surface that includes a backing contour complementary to the target contour.Type: ApplicationFiled: March 6, 2017Publication date: June 22, 2017Applicant: THE BOEING COMPANYInventors: Matthew S. Stauffer, Douglas R. Ludin
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Patent number: 9597843Abstract: One example of the present disclosure relates to a tool for laying up composite material to form a workpiece having a target contour. The tool includes a support structure including an elongated member having a longitudinal axis, and support plates connected to the elongated member and spaced apart from each other along the longitudinal axis. The elongated member includes a metallic material. The tool also includes a non-metallic backing structure connected to the support plates, the non-metallic backing structure comprising a working surface that includes a backing contour complementary to the target contour.Type: GrantFiled: May 15, 2014Date of Patent: March 21, 2017Assignee: THE BOEING COMPANYInventors: Matthew S. Stauffer, Douglas R. Ludin
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Patent number: 9593740Abstract: An energy absorbing fitting is constructed to absorb tension, shear and compression loads at a joint between two composite material beams of a composite material frame. The fitting is constructed with a band of composite material having an inverted U-shape, a panel of composite material having a U-shaped cross-section configuration that is assembled into the inverted U-shaped configuration of the band, and a sheet of composite material having an inverted L-shape configuration that is secured to the band and to the panel. The fitting is positioned at the intersection of the beams and is secured to the joint between the beams, thereby reinforcing the joint against tension, shear and compression loads.Type: GrantFiled: May 13, 2015Date of Patent: March 14, 2017Assignee: The Boeing CompanyInventors: Matthew S. Stauffer, Douglas R. Ludin, Eric J. Schulze
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Patent number: 9500249Abstract: An apparatus and method for a composite structural aircraft transmission support link having an integral energy-absorbing feature is disclosed. The link is a two-force member that can carry structural loads up an ultimate load. When loaded beyond ultimate load the design allows sections of the link to fail in a controlled and progressive manner, so that energy is absorbed over a defined stroking distance.Type: GrantFiled: March 9, 2015Date of Patent: November 22, 2016Assignee: THE BOEING COMPANYInventors: Douglas R. Ludin, Matthew S. Stauffer, Akif O. Bolukbasi, Terrence S. Birchette
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Publication number: 20160333960Abstract: An energy absorbing fitting is constructed to absorb tension, shear and compression loads at a joint between two composite material beams of a composite material frame. The fitting is constructed with a band of composite material having an inverted U-shape, a panel of composite material having a U-shaped cross-section configuration that is assembled into the inverted U-shaped configuration of the band, and a sheet of composite material having an inverted L-shape configuration that is secured to the band and to the panel. The fitting is positioned at the intersection of the beams and is secured to the joint between the beams, thereby reinforcing the joint against tension, shear and compression loads.Type: ApplicationFiled: May 13, 2015Publication date: November 17, 2016Applicant: The Boeing CompanyInventors: Matthew S. Stauffer, Douglas R. Ludin, Eric J. Schulze