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公开(公告)号：US20160221674A1
公开(公告)日：2016-08-04
申请号：US14960482
申请日：2015-12-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Geoffrey C. Latham , Albert G. Brand , Jean-Sébastian Plante , Guifré Julio , Marc Denninger
CPC classification number: B64C27/64 , B64C27/56 , B64C27/68 , B64D31/04 , B64D31/14 , F16D37/02 , F16D2037/001 , F16D2037/007
Abstract: According to one embodiment, a trim actuator for a pilot input device includes a driven member and a driving member configured to receive mechanical energy from a power source. A magnetorheological (MR) fluid is disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member such that the driven member moves in a first direction. An output member configured to be coupled between the driven member and the pilot input device. A spring is in mechanical communication with the output member and configured to apply a force in a second direction opposite of the first direction. A magnetic circuit is configured to control movement of the pilot input device by varying the strength of a magnetic field delivered towards the first MR fluid.
Abstract translation: 根据一个实施例，用于先导输入装置的修整致动器包括从动构件和构造成从动力源接收机械能的驱动构件。 磁流变（MR）流体设置在驱动构件和从动构件之间，并且构造成将可变量的机械能从驱动构件传递到从动构件，使得从动构件沿第一方向移动。 输出构件，被配置为联接在从动构件和导向输入装置之间。 弹簧与输出构件机械连通并且构造成在与第一方向相反的第二方向施加力。 磁路被配置为通过改变朝向第一MR流体传送的磁场的强度来控制先导输入装置的运动。
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公开(公告)号：US20190176980A1
公开(公告)日：2019-06-13
申请号：US15834340
申请日：2017-12-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Albert G. Brand , Mark Loring Isaac , Frank Bradley Stamps , Russell Lee Mueller
CPC classification number: B64C29/0033 , B64C11/28 , B64C11/48 , B64C27/28 , B64C27/30 , B64C27/54 , B64D35/06 , F16H48/10
Abstract: A dual rotor propulsion system for a tiltrotor aircraft having VTOL and forward flight modes. The dual rotor propulsion system includes an engine operable to provide an input torque to a transmission that, responsive thereto, generates an output torque. A first output shaft is coupled to the transmission and is operable to receive a first portion of the output torque. A first rotor assembly is coupled to and rotatable with the first output shaft. A second output shaft is coupled to the transmission and is operable to receive a second portion of the output torque. A second rotor assembly is coupled to and rotatable with the second output shaft. In operation, the first and second rotor assemblies rotate coaxially, the first rotor assembly is a different diameter than the second rotor assembly and the first rotor assembly is stoppable and foldable in the forward flight mode.
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公开(公告)号：US10196151B2
公开(公告)日：2019-02-05
申请号：US15144179
申请日：2016-05-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Martin Peryea , Michael Reaugh Smith , Douglas Hamelwright, Jr. , Albert G. Brand , Nicholas J. Plagianos , Joshua Emrich , Timothy Carr
Abstract: A rotorcraft includes a fuselage having a fuel tank receiving assembly with a fuel tank positioned therein. The fuel tank including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank forming a restraint assembly. The network of straps includes at least one perimeter strap extending at least partially about at least two fuel bags and at least one surrounding strap extending at least partially about the at least two fuel bags. The at least one perimeter strap has at least two intersections with the at least one surrounding strap.
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公开(公告)号：US20170313434A1
公开(公告)日：2017-11-02
申请号：US15144179
申请日：2016-05-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Martin Peryea , Michael Reaugh Smith , Douglas Hamelwright, JR. , Albert G. Brand , Nicholas J. Plagianos , Joshua Emrich , Timothy Carr
Abstract: A rotorcraft includes a fuselage having a fuel tank receiving assembly with a fuel tank positioned therein. The fuel tank including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank forming a restraint assembly. The network of straps includes at least one perimeter strap extending at least partially about at least two fuel bags and at least one surrounding strap extending at least partially about the at least two fuel bags. The at least one perimeter strap has at least two intersections with the at least one surrounding strap.
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公开(公告)号：US11433997B2
公开(公告)日：2022-09-06
申请号：US16399015
申请日：2019-04-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Aaron A. Acee , Albert G. Brand , Frank B. Stamps
Abstract: A method of providing an anti-torque force in a rotorcraft with an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine, and a secondary ducted tail rotor system electrically connected to an electric power supply. The method includes receiving an indication of a change in the operating condition of the anti-torque system based upon a change in a rotorcraft condition input, a feedback input associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and/or a pilot input; responsive to the indication of the change, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force.
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Patent Agency Ranking
公开(公告)号：US10933980B2
公开(公告)日：2021-03-02
申请号：US16054027
申请日：2018-08-03
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric Albert Sinusas , Edward Lambert , Yann Lavallee , Aaron Alexander Acee , Albert G. Brand
Abstract: An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.
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公开(公告)号：US09517842B2
公开(公告)日：2016-12-13
申请号：US14292248
申请日：2014-05-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Albert G. Brand
CPC classification number: B64D33/02 , B64C27/04 , B64D2033/0246 , F02C7/055 , Y02T50/672
Abstract: Some examples of an aircraft engine barrier filtration system include an engine barrier filter layer positioned near an aircraft engine intake. The filter layer filters aircraft engine intake air. The system includes a check valve assembly positioned adjacent to the engine barrier filter layer. The check valve assembly permits the engine intake air to flow into the engine through the filter layer during a first aircraft operation mode and to prevent air flow away from the engine through the filter layer during a second aircraft operation mode that is different from the first aircraft operation mode.
Abstract translation: 飞机发动机障碍物过滤系统的一些示例包括位于飞机发动机进气口附近的发动机阻挡滤清器层。 过滤层过滤飞机发动机进气。 该系统包括邻近发动机阻挡过滤层定位的止回阀组件。 止回阀组件允许发动机进气在第一飞行器操作模式期间通过过滤层流入发动机，并且在与第一飞行器不同的第二飞行器操作模式期间防止空气通过过滤层离开发动机 操作模式。
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公开(公告)号：US20200290735A1
公开(公告)日：2020-09-17
申请号：US16354591
申请日：2019-03-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Aaron Alexander Acee , Andrew Paul Haldeman , Eric Albert Sinusas , Yann Lavallee , Albert G. Brand
Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.
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公开(公告)号：US20200023958A1
公开(公告)日：2020-01-23
申请号：US16399015
申请日：2019-04-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Aaron A. Acee , Albert G. Brand , Frank B. Stamps
Abstract: A method of providing an anti-torque force in a rotorcraft with an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine, and a secondary ducted tail rotor system electrically connected to an electric power supply. The method includes receiving an indication of a change in the operating condition of the anti-torque system based upon a change in a rotorcraft condition input, a feedback input associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and/or a pilot input; responsive to the indication of the change, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force.
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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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