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公开(公告)号：US11286036B2
公开(公告)日：2022-03-29
申请号：US16159178
申请日：2018-10-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson , Matthew Edward Louis , Robert Glenn Vaughn , Michael J. Ryan , Brent Randal Achttien
Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a tip extension affixed at the tip end of the at least one rotor blade, wherein the tip extension is comprised, at least in part, of a flexible material and the rotor blade has a fixed extended length based on the tip extension. The tip extension may provide a clearance distance between the tip extension and the rotor duct.
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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：US20190135427A1
公开(公告)日：2019-05-09
申请号：US15808856
申请日：2017-11-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel B. Robertson , Kirk L. Groninga
Abstract: In one embodiment, a tailsitter aircraft comprises a fuselage; a plurality of wings extending radially from the fuselage; a plurality of rotors coupled to the plurality of wings, wherein each rotor of the plurality of rotors is coupled to a particular wing of the plurality of wings, and wherein the plurality of rotors consists of three rotors; and at least one engine to power the plurality of rotors.
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公开(公告)号：US20140084080A1
公开(公告)日：2014-03-27
申请号：US13624465
申请日：2012-09-21
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Daniel B. Robertson , Dudley E. Smith , Robert M. Laramee
Abstract: A method of managing aircraft exhaust includes providing hot air at a hot air mass flow rate, providing cold air at a cold air mass flow rate, and mixing the hot air and the cold air at a variable hot air mass flow rate to cold air mass flow rate ratio, wherein the variable hot air mass flow rate to cold air mass flow rate ratio is selectively maintained independent of at least one of (1) a variation in the hot air mass flow rate and (2) a variation in a translational speed of the aircraft.
Abstract translation: 管理飞机排气的方法包括以热空气质量流量提供热空气，以冷空气质量流量提供冷空气，并以可变热空气质量流量将热空气与冷空气混合到冷空气质量 流量比，其中可变热空气质量流量与冷空气质量流量比率选择性地保持，独立于（1）热空气质量流量的变化和（2）平移速度的变化中的至少一个 的飞机。
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公开(公告)号：US10589855B2
公开(公告)日：2020-03-17
申请号：US15621686
申请日：2017-06-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson
Abstract: In a first aspect, there is a rotor system for a tiltrotor aircraft, the rotor system including an upper outboard engine in a fixed location on a wing member of the tiltrotor aircraft; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position. In another aspect, there is provided a tiltrotor aircraft including a fuselage; a wing member; an upper outboard engine in a fixed location on the wing member; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position.
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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：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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8.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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公开(公告)号：US11286037B2
公开(公告)日：2022-03-29
申请号：US16159208
申请日：2018-10-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Glenn Vaughn , Michael J. Ryan , Brent Randal Achttien , Kirk L. Groninga , Daniel B. Robertson , Matthew Edward Louis
Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a tip extension affixed at the tip end of the at least one rotor blade, wherein the tip extension comprises a plurality of flexible elements and the rotor blade has a fixed extended length based on the tip extension. The tip extension may provide a clearance distance between the tip extension and the rotor duct.
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10.发明授权公开(公告)号：US10654580B2
公开(公告)日：2020-05-19
申请号：US15625452
申请日：2017-06-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Brent Chadwick Ross , Daniel B. Robertson
Abstract: The present invention includes a rotorcraft drive system, method, and aircraft comprising a fixed engine; a rotating spindle that rotates a proprotor gearbox and rotor pylon between a hover and forward flight position, wherein the rotating spindle rotates about a rotation bearings on two inboard ribs of a wing member; and an interconnect drive shaft connected to the fixed engine, wherein the interconnect drive shaft passes through an aft cove of the wing member and connects to the engine via a forward-aft drive shaft, wherein the forward-aft drive shaft is connected to the proprotor gearbox to provide power to a proprotor.
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