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公开(公告)号：US10336443B2
公开(公告)日：2019-07-02
申请号：US15627373
申请日：2017-06-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Matthew E. Louis , Michael John Ryan , Daniel B. Robertson , Frank B. Stamps
Abstract: In one embodiment, an apparatus comprises a shaft, a rotor, and a cam surface. The shaft comprises a spiral spline along a length of the shaft. The rotor comprises a blade extending from the rotor and a tubular hole extending into the rotor. The tubular hole comprises a spiral groove configured to mate with the spiral spline on the shaft. Relative rotation between the spiral spline and the spiral groove causes the rotor to linearly move along the shaft. The cam surface comprising a recession. The blade nesting in the recession to constrains rotation of the rotor about the shaft and allows linear movement of the rotor along the shaft.
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公开(公告)号：US10421541B2
公开(公告)日：2019-09-24
申请号：US15483541
申请日：2017-04-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson , Matthew E. Louis
IPC: B64D31/00 , B64C29/00 , F04D29/28 , B64C15/12 , B64D27/24 , F04D17/04 , F04D27/00 , F04D29/30 , B64C3/38 , B64D35/02 , B64D35/04 , B64D27/02
Abstract: An aspect provides an aircraft including a fuselage and a cross-flow fan system attached to the fuselage. The cross-flow fan system including a cross-flow fan assembly associated with a rotatable wing member having an exterior aerodynamic surface. In one aspect, there is provided an aircraft with a fuselage having a forward portion and an aft portion; a first cross-flow fan system rotatably attached to the left side of the forward portion of the fuselage; a second cross-flow fan system rotatably attached to the right side of the forward portion of the fuselage; a third cross-flow fan system rotatably attached to the left side of the aft portion of the fuselage; and a fourth cross-flow fan system rotatably attached to the right side of the aft portion of the fuselage.
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公开(公告)号：US20190135423A1
公开(公告)日：2019-05-09
申请号：US15808801
申请日：2017-11-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Frank B. Stamps , Daniel B. Robertson , Matthew E. Louis
Abstract: In one embodiment, a tiltrotor aircraft may comprise a fuselage; a biplane wing coupled to the fuselage, wherein the biplane wing comprises an upper wing structure and a lower wing structure; a plurality of tiltrotors coupled to the biplane wing; and at least one engine to power the plurality of tiltrotors.
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公开(公告)号：US20180273167A1
公开(公告)日：2018-09-27
申请号：US15468069
申请日：2017-03-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Matthew R. Carr , Matthew E. Louis , Kirk L. Groninga , Daniel B. Robertson , Frank B. Stamps , Albert G. Brand , Eric A. Sinusas
CPC classification number: B64C27/82 , B64C2027/8245 , B64C2027/8254 , F04D17/16 , F04D29/462
Abstract: In one embodiment, a rotorcraft comprises a fuselage, a tail boom, a rotor system, and a centrifugal blower system. The centrifugal blower system comprises a centrifugal blower configured to generate thrust using an airflow, wherein the centrifugal blower is located within the tail boom. The centrifugal blower system also comprises a plurality of ducts configured to control the thrust generated by the centrifugal blower, wherein the plurality of ducts is located on a portion of the tail boom surrounding the centrifugal blower, and wherein the plurality of ducts comprises one or more adjustable ducts configured to vary a size of an associated duct opening.
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公开(公告)号：US20180044010A1
公开(公告)日：2018-02-15
申请号：US15483652
申请日：2017-04-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson , Matthew E. Louis
Abstract: In one aspect, there is provided an aircraft, including a fuselage having a longitudinal axis extending from a front portion through an aft portion; first and second tail members extending from the aft portion; a first cross-flow fan system rotatably mounted to the first tail member; and a second cross-flow fan system rotatably mounted to the second tail member. The first and second cross-flow fan systems are configured to provide a forward thrust vector and an anti-torque vector on the aircraft. The first and second cross-flow fan systems can have a rotational axis oriented generally vertically. In another aspect, there is an aircraft including a fuselage having a front portion and a tail portion; and a cross-flow fan system supported by the tail portion. Embodiments include a cross-flow fan system retrofittable onto an aircraft and methods for retrofitting an aircraft with a cross-flow fan system.
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Patent Agency Ranking
公开(公告)号：US10479495B2
公开(公告)日：2019-11-19
申请号：US15483652
申请日：2017-04-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson , Matthew E. Louis
Abstract: In one aspect, there is provided an aircraft, including a fuselage having a longitudinal axis extending from a front portion through an aft portion; first and second tail members extending from the aft portion; a first cross-flow fan system rotatably mounted to the first tail member; and a second cross-flow fan system rotatably mounted to the second tail member. The first and second cross-flow fan systems are configured to provide a forward thrust vector and an anti-torque vector on the aircraft. The first and second cross-flow fan systems can have a rotational axis oriented generally vertically. In another aspect, there is an aircraft including a fuselage having a front portion and a tail portion; and a cross-flow fan system supported by the tail portion. Embodiments include a cross-flow fan system retrofittable onto an aircraft and methods for retrofitting an aircraft with a cross-flow fan system.
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公开(公告)号：US20190225321A1
公开(公告)日：2019-07-25
申请号：US15880216
申请日：2018-01-25
Applicant: Bell Helicopter Textron Inc.
Inventor： Stephen Yibum Chung , Matthew E. Louis
Abstract: One embodiment is a method including defining a maximum deflection for a first axis of a control surface axis of an aircraft; defining a maximum deflection for a second axis of the control surface; and creating a graphical representation of the maximum deflection for the first and second control surface axes. The method further includes determining an angle of rotation of a structure on which the control surface is carried, wherein the angle of rotation is relative to a body of the aircraft; rotating the graphical representation in accordance with the determined angle of rotation; calculating a distance between a point representing a selected combination of roll moment and yaw moment and each edge of the graphical representation; and calculating a control surface deflection based on the calculated distances.
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公开(公告)号：US20180362154A1
公开(公告)日：2018-12-20
申请号：US15627373
申请日：2017-06-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Matthew E. Louis , Michael John Ryan , Daniel B. Robertson , Frank B. Stamps
CPC classification number: B64C27/30 , B64C11/28 , B64C2201/108 , B64C2201/165
Abstract: In one embodiment, an apparatus comprises a shaft, a rotor, and a cam surface. The shaft comprises a spiral spline along a length of the shaft. The rotor comprises a blade extending from the rotor and a tubular hole extending into the rotor. The tubular hole comprises a spiral groove configured to mate with the spiral spline on the shaft. Relative rotation between the spiral spline and the spiral groove causes the rotor to linearly move along the shaft. The cam surface comprising a recession. The blade nesting in the recession to constrains rotation of the rotor about the shaft and allows linear movement of the rotor along the shaft.
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9.发明申请公开(公告)号：US20180044013A1
公开(公告)日：2018-02-15
申请号：US15483602
申请日：2017-04-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson , Matthew E. Louis
CPC classification number: B64C29/0033 , B64C3/32 , B64C15/12 , B64C23/02 , B64C39/005 , B64D27/24 , B64D2027/026 , F04D17/04 , F04D29/282 , F04D29/287
Abstract: A variable thrust cross-flow fan system for an aircraft including a rotatable wing member having a first housing member; an actuator assembly operably coupled to the first housing member; and a variable thrust cross-flow fan assembly including a first and second driver plates having a plurality of blades rotatably mounted therebetween. The plurality of blades has a circular path of travel when rotating and includes a control assembly coupled to the plurality of blades to generate a variable thrust force. The control assembly includes a control cam that is substantially non-rotatable relative to the first and second driver plates and a hinge member that is fixedly connected to the control cam and to the first housing member at a hinge axis. Rotation of the first housing member by the actuator assembly imparts rotation of the control cam about the hinge axis, thereby changing the direction of the variable thrust force.
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10.发明授权公开(公告)号：US10377480B2
公开(公告)日：2019-08-13
申请号：US15483602
申请日：2017-04-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson , Matthew E. Louis
IPC: B64C15/12 , B64C29/00 , B64C3/32 , B64D27/24 , F04D17/04 , F04D29/28 , B64C23/02 , B64C39/00 , B64D27/02
Abstract: A variable thrust cross-flow fan system for an aircraft including a rotatable wing member having a first housing member; an actuator assembly operably coupled to the first housing member; and a variable thrust cross-flow fan assembly including a first and second driver plates having a plurality of blades rotatably mounted therebetween. The plurality of blades has a circular path of travel when rotating and includes a control assembly coupled to the plurality of blades to generate a variable thrust force. The control assembly includes a control cam that is substantially non-rotatable relative to the first and second driver plates and a hinge member that is fixedly connected to the control cam and to the first housing member at a hinge axis. Rotation of the first housing member by the actuator assembly imparts rotation of the control cam about the hinge axis, thereby changing the direction of the variable thrust force.
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