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公开(公告)号：US20150274287A1
公开(公告)日：2015-10-01
申请号：US14202826
申请日：2014-03-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel B. Robertson , Dudley E. Smith , Carlos A. Fenny , Walter West Riley
Abstract: A speed control assembly includes an input drive shaft coupled to a first gear subassembly having a rotatable gear, a second gear subassembly coupled to an output drive shaft, and a linkage coupling the first and second gear subassemblies, wherein the input drive shaft, the first and second gear subassemblies, and the linkage are configured such that a rotational speed of the rotatable gear adjusts a ratio of a rotational speed of the output drive shaft to a rotational speed of the output drive shaft. In some embodiments, the first gear subassembly includes a sun gear coupled to the input drive shaft, one or more planet gears, and a ring gear as the rotatable gear. In some embodiments, the second gear subassembly includes a sun gear coupled to the output drive shaft, one or more planet gears, and a fixed ring gear.
Abstract translation: 速度控制组件包括联接到具有可旋转齿轮的第一齿轮子组件的输入驱动轴，联接到输出驱动轴的第二齿轮子组件和联接第一和第二齿轮组件的联动器，其中输入驱动轴，第一 和二档组件，并且所述连杆构造成使得所述可旋转齿轮的旋转速度调节所述输出驱动轴的旋转速度与所述输出驱动轴的旋转速度的比率。 在一些实施例中，第一齿轮子组件包括联接到输入驱动轴，一个或多个行星齿轮和作为可旋转齿轮的齿圈的太阳齿轮。 在一些实施例中，第二齿轮子组件包括联接到输出驱动轴，一个或多个行星齿轮和固定齿圈的太阳齿轮。
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公开(公告)号：US10730622B2
公开(公告)日：2020-08-04
申请号：US15623328
申请日：2017-06-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , John Lloyd , Daniel B. Robertson
Abstract: In a first aspect, there is a personal air vehicle including a body having a forward portion, a central portion and an aft portion; a first ducted fan supported by the forward portion of the body; a second ducted fan supported by the aft portion of the body; and third and fourth ducted fans supported by the left and right sides of the body and pivotable relative to the body. An aspect provides a method of flying the personal air vehicle.
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Patent Agency Ranking
公开(公告)号：US10427780B2
公开(公告)日：2019-10-01
申请号：US15298959
申请日：2016-10-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos A. Fenny , Daniel B. Robertson , Kirk L. Groninga , Troy C. Schank
Abstract: A rotorcraft capable of a hover mode and a forward cruise mode including a fuselage, a first electric propulsion system, a second electric propulsion system, and an electric power control unit to control power to the first and second electric propulsion systems in the hover and forward cruise modes. The first electric propulsion system is a tip jet cold flow system that imparts rotation on a pair of rotor blades disposed above a top surface of the fuselage, and a first electric motor configured to drive the tip jet cold flow system. The second electric propulsion system includes a propeller disposed in the rear of the fuselage and a second electric motor configured to drive the propeller.
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24.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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25.发明申请公开(公告)号：US20180362180A1
公开(公告)日：2018-12-20
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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公开(公告)号：US20180044012A1
公开(公告)日：2018-02-15
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
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：US20160229531A1
公开(公告)日：2016-08-11
申请号：US14566844
申请日：2014-12-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel B. Robertson , Dudley E. Smith
CPC classification number: B64C29/0033 , B64C11/28 , B64C39/04 , B64D35/04
Abstract: A rotorcraft includes a proprotor coupled to the wing and a pusher propeller. Power is transferred from the proprotor to the pusher propeller with the use of a torque splitter. The torque splitter contains several gears, including a ring gear which rotates on an axis. The power outputted by the torque splitter is increased or decreased by selectively slowing down the rotation of the ring gear by the use of a clamp.
Abstract translation: 旋翼航空器包括联接到机翼的推进器和推进推进器。 使用转矩分配器将动力从推进器传送到推进式推进器。 扭矩分配器包含几个齿轮，包括在轴上旋转的齿圈。 通过使用夹具选择性地减慢环形齿轮的旋转，由转矩分配器输出的功率增加或减小。
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