公开(公告)号：US11618550B2

公开(公告)日：2023-04-04

申请号：US17220097

申请日：2021-04-01

Applicant: The Boeing Company

Inventor： Michael J. Duffy ,  Matthew S. Stauffer

IPC: B64C11/28 ,  B64C39/02 ,  B64C11/04 ,  B64C27/30 ,  B64C29/00 ,  B64C27/26 ,  B64C27/473 ,  B64U30/10 ,  B64U30/20 ,  B64U70/80

Abstract: 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.

公开(公告)号：US20220194547A1

公开(公告)日：2022-06-23

申请号：US17480880

申请日：2021-09-21

Applicant: The Boeing Company

Inventor： 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

IPC: B64C1/06 ,  B64F5/10 ,  B64C1/12

Abstract: 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.

公开(公告)号：US20190092461A1

公开(公告)日：2019-03-28

申请号：US15713432

申请日：2017-09-22

Applicant: The Boeing Company

Inventor： Michael J. Duffy ,  Matthew S. Stauffer

IPC: B64C27/473 ,  B64C29/00

Abstract: 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.

公开(公告)号：US20190071163A1

公开(公告)日：2019-03-07

申请号：US15695052

申请日：2017-09-05

Applicant: The Boeing Company

Inventor： Douglas R. Ludin ,  Matthew S. Stauffer ,  Akif Bolukbasi ,  Eric Schulze

IPC: B64C1/06

Abstract: 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.

公开(公告)号：US20150328842A1

公开(公告)日：2015-11-19

申请号：US14278205

申请日：2014-05-15

Applicant: THE BOEING COMPANY

Inventor： Matthew S. Stauffer ,  Douglas R. Ludin

IPC: B29C70/30 ,  B29C33/38 ,  B29C33/40

CPC classification number: B29C70/30 ,  B29C33/0011 ,  B29C33/38 ,  B29C33/3842 ,  B29C33/40 ,  B29C33/76 ,  B29C41/40 ,  B29C53/82 ,  B29C70/32 ,  B29C70/38 ,  B29K2079/085 ,  B29K2879/085 ,  B29K2905/02 ,  B29K2995/0017 ,  B29L2031/3076 ,  B29L2031/3082 ,  B33Y10/00 ,  B33Y80/00 ,  Y02T50/43 ,  Y10T29/49842

Abstract: 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.

Abstract translation: 本公开的一个示例涉及用于铺设复合材料以形成具有目标轮廓的工件的工具。 该工具包括支撑结构，其包括具有纵向轴线的细长构件和连接到细长构件并沿着纵向轴线彼此间隔开的支撑板。 细长构件包括金属材料。 该工具还包括连接到支撑板的非金属背衬结构，非金属背衬结构包括工作表面，该工作表面包括与目标轮廓互补的背衬轮廓。

公开(公告)号：US11919617B2

公开(公告)日：2024-03-05

申请号：US17480880

申请日：2021-09-21

Applicant: The Boeing Company

Inventor： 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

IPC: B64C1/06 ,  B64C1/12 ,  B64F5/10

CPC classification number: B64C1/069 ,  B64C1/12 ,  B64F5/10

Abstract: 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.

公开(公告)号：US20220373992A1

公开(公告)日：2022-11-24

申请号：US17695430

申请日：2022-03-15

Applicant: The Boeing Company

Inventor： Matthew S. Stauffer ,  Kayley E. Seawright ,  Russell A. Strope ,  Michael S. Lindgren ,  Daniel E. Gonsor ,  Ashutosh Mani

IPC: G05B19/4097

Abstract: 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.

公开(公告)号：US20210237853A1

公开(公告)日：2021-08-05

申请号：US17220097

申请日：2021-04-01

Applicant: The Boeing Company

Inventor： Michael J. Duffy ,  Matthew S. Stauffer

IPC: B64C11/28 ,  B64C39/02 ,  B64C11/04 ,  B64C27/30 ,  B64C29/00 ,  B64C27/26

Abstract: 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.

公开(公告)号：US10994829B2

公开(公告)日：2021-05-04

申请号：US15713432

申请日：2017-09-22

Applicant: The Boeing Company

Inventor： Michael J. Duffy ,  Matthew S. Stauffer

IPC: B64C11/28 ,  B64C39/02 ,  B64C11/04 ,  B64C27/30 ,  B64C29/00 ,  B64C27/26

Abstract: 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.

公开(公告)号：US10745098B2

公开(公告)日：2020-08-18

申请号：US15695052

申请日：2017-09-05

Applicant: The Boeing Company

Inventor： Douglas R. Ludin ,  Matthew S. Stauffer ,  Akif Bolukbasi ,  Eric Schulze

IPC: E04C3/02 ,  B64C1/18 ,  B64C1/06 ,  B64C1/00 ,  E04C3/04

Abstract: 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.