公开(公告)号：US09783292B2

公开(公告)日：2017-10-10

申请号：US15497055

申请日：2017-04-25

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  George Ryan Decker ,  Andrew G. Baines ,  David R. Bockmiller ,  Erick Wayne Kohler

IPC: B64C29/00 ,  B64D35/00 ,  F16H1/00

CPC classification number: B64C29/0033 ,  B64C27/22 ,  B64D35/00 ,  B64F5/40 ,  F16H1/006 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A support assembly for coupling a first gearbox to an airframe of an aircraft. The first gearbox has an output gear operable to transfer torque to an input gear of a second gearbox via a common shaft rotatable about a longitudinal axis. The support assembly includes a fixed joint proximate the longitudinal axis. A first directional reacting joint remote from the longitudinal axis provides a first radial growth degree of freedom to the first gearbox relative to the longitudinal axis. A second directional reacting joint remote from the longitudinal axis provides a second radial growth degree of freedom to the first gearbox relative to the longitudinal axis. The first radial growth degree of freedom is not parallel with the second radial growth degree of freedom such that the support assembly maintains the output gear of the first gearbox in substantial collinear alignment with the input gear of the second gearbox.

公开(公告)号：US20170259521A1

公开(公告)日：2017-09-14

申请号：US15601640

申请日：2017-05-22

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  George Ryan Decker ,  Keith Alan Stanney ,  Robert Mark Chris

IPC: B32B3/26 ,  B64C3/26 ,  B32B27/08

CPC classification number: B32B3/266 ,  B29C70/00 ,  B29D24/005 ,  B29D99/0021 ,  B32B27/08 ,  B32B2305/024 ,  B32B2305/34 ,  B32B2307/30 ,  B32B2605/18 ,  B64C3/18 ,  B64C3/187 ,  B64C3/26 ,  B64C29/0033 ,  B64F5/10

Abstract: A core stiffened panel includes first and second skins having a large cell core and a solid insert joined therebetween. The solid insert has a side surface at least a portion of which is adjacent to the large cell core and may be joined to the large cell core. The first skin, the second skin and the solid insert may be formed from composite materials such as carbon composite materials and preferably have generally matching coefficients of thermal expansion.

公开(公告)号：US20170158306A1

公开(公告)日：2017-06-08

申请号：US14960648

申请日：2015-12-07

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  Mark Loring Isaac ,  John Elton Brunken, JR. ,  John McCullough

IPC: B64C1/26 ,  B64C1/14 ,  B64C3/18 ,  B64C29/00

CPC classification number: B64C1/26 ,  B64C1/1423 ,  B64C3/187 ,  B64C29/0033

Abstract: According to one embodiment, an aircraft features a fuselage, a wing member, and two fuselage beam. The fuselage features a first plurality of structural supports, a second plurality of structural supports, a first opening disposed between the first plurality of structural supports, and a second opening disposed between the second plurality of structural supports. The wing member is disposed above the first opening and above the second opening. The wing features a plurality of ribs including a first rib and a second rib. The first fuselage beam couples the first rib of the wing member to the fuselage and has an elongated body portion extending across the first plurality of structural supports. The second fuselage beam couples the second rib of the wing member to the fuselage and features an elongated body portion extending across the second plurality of structural supports.

公开(公告)号：US20170137122A1

公开(公告)日：2017-05-18

申请号：US15417113

申请日：2017-01-26

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  George Ryan Decker ,  Andrew G. Baines ,  David R. Bockmiller ,  Erick Wayne Kohler

IPC: B64C29/00 ,  B64F5/40

CPC classification number: B64C29/0033 ,  B64C27/22 ,  B64D35/00 ,  B64F5/40 ,  F16H1/006 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A drive system for a tiltrotor aircraft includes a first gearbox rotatably mounted to the airframe and rotatable about a longitudinal axis to operate the tiltrotor aircraft between helicopter and airplane modes. A second gearbox extends generally normal to the longitudinal axis of the first gearbox. A common shaft, rotatable about the longitudinal axis, transfers torque from an output gear of the second gearbox to an input gear of the first gearbox. A support assembly couples the second gearbox to the airframe and includes a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox that is not parallel with the first radial growth degree of freedom.

公开(公告)号：US11059561B2

公开(公告)日：2021-07-13

申请号：US15870977

申请日：2018-01-14

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  David G. Carlson ,  George Ryan Decker ,  Jeffrey Matthew Williams ,  Douglas K. Wolfe

IPC: B64C3/18 ,  B64C29/00 ,  B64C3/26

Abstract: A torque box rib includes an upper rib cap configured to be coupled to an upper skin of a wing, a lower rib cap configured to be coupled to a lower skin of the wing, a forward post configured to be coupled to a forward spar of the wing, an aft post configured to be coupled to an aft spar of the wing, and a rib web configured to be coupled to the upper rib cap, the lower rib cap, the forward post, and the aft post.

公开(公告)号：US10994839B2

公开(公告)日：2021-05-04

申请号：US16050185

申请日：2018-07-31

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  Michael E. Rinehart ,  Jeffrey Matthew Williams

IPC: B64C29/00

Abstract: A tiltrotor aircraft includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. The actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.

公开(公告)号：US10850474B2

公开(公告)日：2020-12-01

申请号：US15878301

申请日：2018-01-23

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  David M. Carlson ,  Douglas K. Wolfe ,  Jonathan Alexander Freeman

IPC: B32B3/26 ,  B32B3/12 ,  B32B37/10 ,  B64C3/26 ,  B32B27/06 ,  B29C70/34 ,  B32B38/00 ,  B32B37/14

Abstract: A method of fabricating a panel includes laying up a first laminate on a tooling surface, laying a first layer of thermoplastic on an inner surface of the first laminate, laying a large cell carbon core on the first layer of thermoplastic, laying a second layer of thermoplastic across the large cell carbon core, laying a second laminate on the second layer of thermoplastic, creating a sealed core pocket by bonding the edges of the first and second layers of the thermoplastic surrounding a perimeter of the core, increasing pressure within the core pocket, increasing pressure on the outer surface of the second laminate, heating the panel to a desired curing temperature, and maintaining the increased pressures and temperature for a desired curing duration.

公开(公告)号：US10793285B2

公开(公告)日：2020-10-06

申请号：US15895619

申请日：2018-02-13

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  Greg Alan Whittaker ,  Bryan Keith Sugg

IPC: B64D37/04 ,  B64C1/06 ,  B64C39/02

Abstract: One embodiment is a system comprising fuel tank comprising a pressure vessel for storing fuel for a vehicle, the fuel tank disposed within a fuselage of the vehicle and extending a majority of a length of the fuselage, wherein a center of gravity of the fuel tank is substantially aligned with a center of gravity of the fuselage. The fuel tank may be disposed within the fuselage such that the fuel tank bears at least a portion of a load borne by the fuselage. Alternatively, the fuel tank may be disposed within the fuselage such that the fuel tank is isolated from loads borne by the fuselage. In certain embodiments, the fuel tank comprises a filament wound pressure vessel.

公开(公告)号：US20200156803A1

公开(公告)日：2020-05-21

申请号：US15895619

申请日：2018-02-13

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  Greg Alan Whittaker ,  Bryan Keith Sugg

IPC: B64D37/04 ,  B64C39/02 ,  B64C1/06

Abstract: One embodiment is a system comprising fuel tank comprising a pressure vessel for storing fuel for a vehicle, the fuel tank disposed within a fuselage of the vehicle and extending a majority of a length of the fuselage, wherein a center of gravity of the fuel tank is substantially aligned with a center of gravity of the fuselage. The fuel tank may be disposed within the fuselage such that the fuel tank bears at least a portion of a load borne by the fuselage. Alternatively, the fuel tank may be disposed within the fuselage such that the fuel tank is isolated from loads borne by the fuselage. In certain embodiments, the fuel tank comprises a filament wound pressure vessel.

公开(公告)号：US20200039642A1

公开(公告)日：2020-02-06

申请号：US16050185

申请日：2018-07-31

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  Michael E. Rinehart ,  Jeffrey Matthew Williams

IPC: B64C29/00 ,  B64D27/26

Abstract: One example of a tiltrotor aircraft includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. In an example, the actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.