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1.发明申请RESILIENT AIRCRAFT ENGINE MOUNTS AND AIRCRAFT ENGINE MOUNTING SYSTEMS INCLUDING THE SAME 有权发动机发动机和飞机发动机安装系统，包括它们公开(公告)号：US20130134257A1
公开(公告)日：2013-05-30
申请号：US13308178
申请日：2011-11-30
Applicant: Tim Daniel Barber , Timothy Hindle , Steven Hadden
Inventor： Tim Daniel Barber , Timothy Hindle , Steven Hadden
IPC: B64D27/26
CPC classification number: B64D27/26 , B64D2027/266 , F16F1/10 , F16F3/02
Abstract: Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces.
Abstract translation: 提供弹性飞机发动机支架和包括其的安装系统。 弹性飞机发动机支架包括基座和一对相对的螺旋弹簧，平行地形成与基座的U形夹。 一对相对的螺旋弹簧的第一螺旋弹簧具有延伸穿过其中的第一中心开口。 一对相对的螺旋弹簧的第二螺旋弹簧具有延伸穿过其中的第二中心开口，该第二中心开口与第一中心开口同心，用于接受U形夹销。 第一和第二螺旋弹簧各自由矩形截面梁组成。 弹性飞机发动机支架可以在三个平移轴上调节，以支持三个自由度的隔振。 两个或多个弹性飞机发动机支架提供六个自由度的隔振。 弹性飞机发动机支架将飞机发动机连接到塔架结构，并有助于隔离振动力。
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2.发明申请PASSIVE ISOLATION DEVICES PROVIDING LOW FREQUENCY DAMPING OF LOW MASS PAYLOADS AND SPACECRAFT ISOLATION SYSTEMS EMPLOYING THE SAME 审中-公开提供低质量载荷的低频阻尼的被动隔离装置和使用它的隔离隔离系统公开(公告)号：US20130154170A1
公开(公告)日：2013-06-20
申请号：US13331512
申请日：2011-12-20
Applicant: Porter Davis , Steven Hadden , Pablo Bandera
Inventor： Porter Davis , Steven Hadden , Pablo Bandera
CPC classification number: B64G1/641 , B64G2001/228
Abstract: Embodiments of a low frequency isolation device are provided, as are embodiments of a spacecraft isolation system including a plurality of low frequency isolation devices. In one embodiment, the low frequency isolation device includes a three parameter isolator and a break frequency-reducing series spring mechanically coupled in series with the three parameter isolator and having a predetermined axial stiffness (KS AXIAL) and a predetermined lateral stiffness (KS LATERAL). The predetermined axial stiffness (KS AXIAL) of the break frequency-reducing series spring is less than the predetermined lateral stiffness (KS LATERAL) thereof.
Abstract translation: 提供低频隔离装置的实施例，如包括多个低频隔离装置的航天器隔离系统的实施例。 在一个实施例中，低频隔离装置包括三参数隔离器和与三参数隔离器串联的具有预定轴向刚度（KS AXIAL）和预定侧向刚度（KS LATERAL）的机械耦合的断路减频串联弹簧， 。 断裂减频串联弹簧的预定轴向刚度（KS AXIAL）小于其预定的横向刚度（KS LATERAL）。
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公开(公告)号：US20090243169A1
公开(公告)日：2009-10-01
申请号：US12059933
申请日：2008-03-31
Applicant: Steven Hadden , Paul Buchele , Jim Boyd
Inventor： Steven Hadden , Paul Buchele , Jim Boyd
IPC: F16F15/023
CPC classification number: F16F15/0232
Abstract: Systems are provided for damping vibrations from a payload. In an embodiment, and by way of example only, the system includes an isolation strut and a gas line. The isolation strut includes a bellows and a piston. The bellows has a first end and a second end, the first end being enclosed, and the second end attached to the piston to define a chamber. The piston includes a damping annulus therethrough having a gas inlet and a gas outlet. The gas inlet provides flow communication to the chamber of the bellows. The gas line is coupled to the isolation strut and is in fluid communication with the gas outlet thereof. The system is hermetically sealed to contain a gas therein.
Abstract translation: 提供系统用于阻尼来自有效载荷的振动。 在一个实施例中，仅作为示例，该系统包括隔离支柱和气体管线。 隔离支柱包括波纹管和活塞。 波纹管具有第一端和第二端，第一端被封闭，第二端连接到活塞以限定腔室。 活塞包括通过其的阻尼环，其具有气体入口和气体出口。 气体入口提供与波纹管的腔室的流动连通。 气体管线与隔离支柱相连，并与气体出口流体连通。 该系统被密封以在其中容纳气体。
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4.发明授权Resilient aircraft engine mounts and aircraft engine mounting systems including the same 有权弹性飞机发动机支架和包括其的飞机发动机安装系统公开(公告)号：US08770513B2
公开(公告)日：2014-07-08
申请号：US13308178
申请日：2011-11-30
Applicant: Tim Daniel Barber , Timothy Hindle , Steven Hadden
Inventor： Tim Daniel Barber , Timothy Hindle , Steven Hadden
IPC: B64D27/00
CPC classification number: B64D27/26 , B64D2027/266 , F16F1/10 , F16F3/02
Abstract: Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces.
Abstract translation: 提供弹性飞机发动机支架和包括其的安装系统。 弹性飞机发动机支架包括基座和一对相对的螺旋弹簧，平行地形成与基座的U形夹。 一对相对的螺旋弹簧的第一螺旋弹簧具有延伸穿过其中的第一中心开口。 一对相对的螺旋弹簧的第二螺旋弹簧具有延伸穿过其中的第二中心开口，该第二中心开口与第一中心开口同心，用于接受U形夹销。 第一和第二螺旋弹簧各自由矩形截面梁组成。 弹性飞机发动机支架可以在三个平移轴上调节，以支持三个自由度的隔振。 两个或多个弹性飞机发动机支架提供六个自由度的隔振。 弹性飞机发动机支架将飞机发动机连接到塔架结构，并有助于隔离振动力。
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5.发明申请公开(公告)号：US20120292476A1
公开(公告)日：2012-11-22
申请号：US13111842
申请日：2011-05-19
Applicant: Dennis Wayne Smith , Steven Hadden
Inventor： Dennis Wayne Smith , Steven Hadden
IPC: F16F15/023 , F16M13/00 , F16F15/04
Abstract: Embodiments of a thermally-conductive vibration isolator are provided, as are embodiments of a spacecraft isolation employing a plurality of thermally-conductive vibration isolators. In one embodiment, the thermally-conductive vibration isolator includes a first end portion, a second end portion substantially opposite the first end portion, and first and second load transfer paths from the first end portion to the second end portion. The first and second load transfer paths comprise a main spring and a damper in parallel with the main spring, respectively. An elongated thermal conduit, which has a thermal conductivity exceeding that of first load transfer path and the second load transfer path, extends from the first end portion to the second end portion.
Abstract translation: 提供导热隔振器的实施例，其中采用多个导热隔振器的航天器隔离件的实施例。 在一个实施例中，导热隔振器包括第一端部，与第一端部大致相对的第二端部，以及从第一端部到第二端部的第一和第二负载传递路径。 第一和第二负载传递路径分别包括与主弹簧平行的主弹簧和阻尼器。 具有超过第一载荷传递路径和第二载荷传递路径的热导率的细长热导管从第一端部延伸到第二端部。
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Patent Agency Ranking
6.发明授权Three parameter, multi-axis isolators, isolation systems employing the same, and methods for producing the same 有权三参数，多轴隔离器，采用其的隔离系统及其制造方法公开(公告)号：US09103403B2
公开(公告)日：2015-08-11
申请号：US13093573
申请日：2011-04-25
Applicant: Steven Hadden , Dale Thomas Ruebsamen , Ryan Goold
Inventor： Steven Hadden , Dale Thomas Ruebsamen , Ryan Goold
CPC classification number: F16F15/06 , F16F9/3214 , F16F9/361 , F16F15/02 , Y10T29/49826
Abstract: Embodiments of a three parameter, multi-axis isolator configured to limit the transmission of vibrations between a mass and a base are provided. In one embodiment, the three parameter, multi-axis isolator includes an isolator housing configured to be mounted to the base, opposing bellows sealingly mounted within the isolator housing, and a damper piston movably suspended within the isolator housing between the opposing bellows. The damper piston is configured to be coupled to the mass. The opposing bellows deflect with movement of the damper piston along multiple axes to limit the transmission of vibrations between the mass and the base.
Abstract translation: 提供了被配置为限制质量块和基座之间的振动传播的三参数多轴隔离器的实施例。 在一个实施例中，三参数多轴隔离器包括被配置为安装到基座的隔离器壳体，密封地安装在隔离器壳体内的相对的波纹管以及在相对的波纹管之间可移动地悬挂在隔离器壳体内的阻尼器活塞。 阻尼器活塞构造成联接到质量块。 相反的波纹管随着阻尼器活塞沿着多个轴线的运动而偏转，以限制质量块和基座之间的振动传播。
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7.发明授权Gas turbine engines including broadband damping systems and methods for producing the same 有权燃气涡轮发动机包括宽带阻尼系统及其制造方法公开(公告)号：US08992161B2
公开(公告)日：2015-03-31
申请号：US13219287
申请日：2011-08-26
Applicant: Timothy Hindle , Steven Hadden , Torey Davis
Inventor： Timothy Hindle , Steven Hadden , Torey Davis
CPC classification number: F01D25/04 , F01D5/10 , F05D2250/41 , F05D2260/96 , F16F15/022 , F16F15/023 , Y02T50/671 , Y10T29/4932
Abstract: Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine.
Abstract translation: 提供燃气涡轮发动机，宽带阻尼系统以及生产宽带阻尼式燃气轮机的方法。 在一个实施例中，燃气涡轮发动机包括发动机壳体，安装在发动机壳体内用于围绕旋转轴线旋转的转子组件以及设置在转子组件和发动机壳体之间的宽带阻尼系统。 宽带阻尼系统包括围绕旋转轴线成角度地间隔开的第一组三个参数轴向阻尼器，以及第二组三个参数轴向阻尼器，其围绕旋转轴线成角度地间隔开并与第一组三个参数轴向阻尼器并联。 第一组和第二组三参数轴向阻尼器被调谐以在不同的旋转频率处提供峰值阻尼，以增加燃气涡轮发动机运行期间宽带阻尼系统的阻尼带宽。
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8.发明授权公开(公告)号：US08899389B2
公开(公告)日：2014-12-02
申请号：US13111842
申请日：2011-05-19
Applicant: Dennis Wayne Smith , Steven Hadden
Inventor： Dennis Wayne Smith , Steven Hadden
Abstract: Embodiments of a thermally-conductive vibration isolator are provided, as are embodiments of a spacecraft isolation employing a plurality of thermally-conductive vibration isolators. In one embodiment, the thermally-conductive vibration isolator includes a first end portion, a second end portion substantially opposite the first end portion, and first and second load transfer paths from the first end portion to the second end portion. The first and second load transfer paths comprise a main spring and a damper in parallel with the main spring, respectively. An elongated thermal conduit, which has a thermal conductivity exceeding that of first load transfer path and the second load transfer path, extends from the first end portion to the second end portion.
Abstract translation: 提供导热隔振器的实施例，其中采用多个导热隔振器的航天器隔离件的实施例。 在一个实施例中，导热隔振器包括第一端部，与第一端部大致相对的第二端部，以及从第一端部到第二端部的第一和第二负载传递路径。 第一和第二负载传递路径分别包括与主弹簧平行的主弹簧和阻尼器。 具有超过第一载荷传递路径和第二载荷传递路径的热导率的细长热导管从第一端部延伸到第二端部。
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公开(公告)号：US08444121B2
公开(公告)日：2013-05-21
申请号：US12059933
申请日：2008-03-31
Applicant: Steven Hadden , Paul Buchele , Jim Boyd
Inventor： Steven Hadden , Paul Buchele , Jim Boyd
CPC classification number: F16F15/0232
Abstract: Systems are provided for damping vibrations from a payload. In an embodiment, and by way of example only, the system includes an isolation strut and a gas line. The isolation strut includes a bellows and a piston. The bellows has a first end and a second end, the first end being enclosed, and the second end attached to the piston to define a chamber. The piston includes a damping annulus therethrough having a gas inlet and a gas outlet. The gas inlet provides flow communication to the chamber of the bellows. The gas line is coupled to the isolation strut and is in fluid communication with the gas outlet thereof. The system is hermetically sealed to contain a gas therein.
Abstract translation: 提供系统用于阻尼来自有效载荷的振动。 在一个实施例中，仅作为示例，该系统包括隔离支柱和气体管线。 隔离支柱包括波纹管和活塞。 波纹管具有第一端和第二端，第一端被封闭，第二端连接到活塞以限定腔室。 活塞包括通过其的阻尼环，其具有气体入口和气体出口。 气体入口提供与波纹管的腔室的流动连通。 气体管线与隔离支柱相连，并与气体出口流体连通。 该系统被密封以在其中容纳气体。
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10.发明申请GAS TURBINE ENGINES INCLUDING BROADBAND DAMPING SYSTEMS AND METHODS FOR PRODUCING THE SAME 有权包括宽带阻尼系统的气体涡轮发动机及其生产方法公开(公告)号：US20130051981A1
公开(公告)日：2013-02-28
申请号：US13219287
申请日：2011-08-26
Applicant: Timothy Hindle , Steven Hadden , Torey Davis
Inventor： Timothy Hindle , Steven Hadden , Torey Davis
CPC classification number: F01D25/04 , F01D5/10 , F05D2250/41 , F05D2260/96 , F16F15/022 , F16F15/023 , Y02T50/671 , Y10T29/4932
Abstract: Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine.
Abstract translation: 提供燃气涡轮发动机，宽带阻尼系统以及生产宽带阻尼式燃气轮机的方法。 在一个实施例中，燃气涡轮发动机包括发动机壳体，安装在发动机壳体内用于围绕旋转轴线旋转的转子组件以及设置在转子组件和发动机壳体之间的宽带阻尼系统。 宽带阻尼系统包括围绕旋转轴线成角度地间隔开的第一组三个参数轴向阻尼器，以及第二组三个参数轴向阻尼器，其围绕旋转轴线成角度地间隔开并与第一组三个参数轴向阻尼器并联。 第一组和第二组三参数轴向阻尼器被调谐以在不同的旋转频率处提供峰值阻尼，以增加燃气涡轮发动机运行期间宽带阻尼系统的阻尼带宽。
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