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公开(公告)号：US20090159756A1
公开(公告)日：2009-06-25
申请号：US11960326
申请日：2007-12-19
IPC分类号： B64C13/04
CPC分类号： B64C13/044 , B64C25/44 , B64C27/56 , Y02T50/44
摘要： A user interface fluid linkage system includes first and second user interfaces that are linked by a single, constant volume fluid line. The system includes identically configured, but oppositely mounted hydraulic fluid chambers to link motion between the first and second user interfaces.
摘要翻译： 用户界面流体联动系统包括通过单个恒定体积流体管线链接的第一和第二用户界面。 该系统包括相同配置但相对安装的液压流体室，以连接第一和第二用户界面之间的运动。
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公开(公告)号：US20090056507A1
公开(公告)日：2009-03-05
申请号：US11848699
申请日：2007-08-31
IPC分类号： B25B13/18
CPC分类号： F16D3/04 , Y10T74/19702
摘要： Assemblies and methods are provided for use in coupling a component to an actuator, where the component includes a stem and a drive nut, and the stem is configured to be rotated by the actuator and to move linearly through an opening in the drive nut. In an embodiment, the assembly includes a coupling mechanism, a drive ring, and a carrier, where the coupling mechanism and the carrier each include slots and the drive ring includes projections that correspond with the slots.
摘要翻译： 提供组件和方法用于将部件联接到致动器，其中部件包括杆和驱动螺母，并且杆构造成由致动器旋转并且直线地移动通过驱动螺母中的开口。 在一个实施例中，组件包括联接机构，驱动环和载体，其中联接机构和载体各自包括槽，并且驱动环包括与槽对应的突起。
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公开(公告)号：US07493691B2
公开(公告)日：2009-02-24
申请号：US10851973
申请日：2004-05-20
IPC分类号： B23P15/00
CPC分类号： C25D1/02 , Y10T29/49346
摘要： A method is provided for manufacturing a missile component for use in a high temperature environment, where the missile component has a flow passage therethrough and the flow passage has a shape. An apparatus manufactured by the inventive method is provided as well. The method includes the steps of depositing a first metal onto a mandrel having the shape of the flow passage to create a first metal layer, applying an insulating material on to the first metal layer to create an insulating layer, machining a predetermined shape into at least a portion of the insulating layer, and applying a second metal onto the machined insulating layer to create an outer shell layer.
摘要翻译： 提供一种用于制造在高温环境中使用的导弹部件的方法，其中导弹部件具有穿过其中的流动通道，并且流动通道具有形状。 还提供了通过本发明方法制造的装置。 该方法包括以下步骤：将第一金属沉积到具有流动通道形状的心轴上以产生第一金属层，将绝缘材料施加到第一金属层上以形成绝缘层，至少将预定形状加工成 绝缘层的一部分，并将第二金属施加到加工的绝缘层上以形成外壳层。
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4.发明申请Electromechanical linear actuator including an environmental control and air management system 审中-公开机电线性执行器，包括环境控制和空气管理系统公开(公告)号：US20080141803A1
公开(公告)日：2008-06-19
申请号：US11588688
申请日：2006-10-26
IPC分类号： F16H27/02
CPC分类号： F16H25/20 , F16H25/2418 , F16H57/027 , Y10T74/18712
摘要： An actuator that at least inhibits the deleterious effects of corrosive fluids, such as salt-laden air, does not rely on relatively expensive materials. At least a portion of the actuator housing is sealed from the surrounding salt-laden air, and is in fluid communication with an air reservoir that includes a supply of relatively salt-free, or substantially salt-free, air. The actuator is configured to exchange air between the air reservoir and the actuator housing, thereby at least substantially inhibiting the ingress of salt-laden air into much of the actuator.
摘要翻译： 至少抑制腐蚀性液体（例如含盐的空气）的有害影响的致动器不依赖于相对昂贵的材料。 致动器壳体的至少一部分与周围的含盐空气密封，并且与包括相对无盐或基本上无盐的空气的空气储存器流体连通。 致动器构造成在空气储存器和致动器壳体之间更换空气，从而至少基本上禁止含盐空气进入致动器的大部分。
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5.发明授权Thrust reverser actuator with an automatic relock and lock drop prevention mechanism 有权具有自动重锁和锁下降防止机构的推力反向器执行器公开(公告)号：US06786039B2
公开(公告)日：2004-09-07
申请号：US10233752
申请日：2002-09-03
IPC分类号： F02K170
CPC分类号： F16D63/006 , F02K1/766 , F16D2121/22 , F16H25/2454
摘要： A thrust reverser system includes one or more actuators each having a locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators additionally includes a lock inhibitor assembly that engages the lock and prevents it from moving to its locked position until the actuator is moved into a stow position. Upon movement to the stow position, the lock inhibitor assembly disengages the lock, and the lock automatically moves into its locked position.
摘要翻译： 推力反向器系统包括一个或多个致动器，每个致动器具有防止意外的致动器运动以及因此意外的推力反向器运动的锁定机构。 每个致动器还包括锁定抑制器组件，其接合锁并防止其移动到其锁定位置，直到致动器移动到收起位置。 在移动到收起位置时，锁定抑制器组件脱离锁定，并且锁自动地移动到其锁定位置。
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公开(公告)号：US08979019B2
公开(公告)日：2015-03-17
申请号：US13192084
申请日：2011-07-27
CPC分类号： B64C25/405 , Y02T50/823
摘要： An aircraft taxi drive system includes a motor that is configured to transfer power to an aircraft wheel via a drive chain, such that the motor rotates the aircraft wheel via the drive chain. In some examples, the drive chain is movable between first and second positions. In the first position, the drive chain, such as an exterior surface of the drive chain, is engaged with a driven sprocket that is mechanically connected to an aircraft wheel. In the second position, the drive chain is disengaged from the driven sprocket.
摘要翻译： 飞机出租车驱动系统包括被配置为经由驱动链将动力传递到飞行器轮的马达，使得马达经由驱动链旋转飞行器轮。 在一些示例中，驱动链可在第一和第二位置之间移动。 在第一位置，驱动链，例如驱动链的外表面，与机械连接到飞机轮的从动链轮接合。 在第二位置，驱动链与从动链轮分离。
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公开(公告)号：US08528856B2
公开(公告)日：2013-09-10
申请号：US12959717
申请日：2010-12-03
IPC分类号： B64C25/42
CPC分类号： B64C25/405 , Y02T50/823
摘要： A electric taxi system (ETS) for an aircraft may comprise drive units mounted coaxially with wheels of the aircraft and dedicated motor control units for the drive units. The motor control units may be operable independently of one another so that a first one of the drive units can be operated at a speed different from an operating speed of a second one of the drive units. Independent operability of the drive units may provide enhanced maneuverability of the aircraft during taxiing.
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8.发明授权Solid propellant burn rate, propellant gas flow rate, and propellant gas pressure pulse generation control system and method 失效固体推进剂燃烧速率，推进剂气体流量和推进剂气体压力脉冲发生控制系统及方法公开(公告)号：US07886519B2
公开(公告)日：2011-02-15
申请号：US11683170
申请日：2007-03-07
IPC分类号： F02K9/00
CPC分类号： F02K9/26
摘要： Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on pulse width modulation of a control valve duty cycle. A control valve that is movable between a closed position and a full-open position is disposed downstream of, and in fluid communication with, a solid propellant gas generator. The solid propellant in the solid propellant gas generator is ignited, to thereby generate propellant gas. The control valve is moved between the closed position and the full-open position at an operating frequency and with a valve duty cycle. The valve duty cycle is the ratio of a time the control valve is in the full-open position to a time it takes the valve to complete one movement cycle at the operating frequency. The valve duty cycle is controlled to attain a desired solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and/or propellant gas flow rate.
摘要翻译： 控制固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和推进剂气体流量的系统和方法依赖于控制阀占空比的脉宽调制。 可在关闭位置和全开位置之间移动的控制阀设置在固体推进剂气体发生器的下游并且与固体推进剂气体发生器流体连通。 固体推进剂气体发生器中的固体推进剂被点燃，从而产生推进剂气体。 控制阀在工作频率和阀门占空比下在关闭位置和全开位置之间移动。 阀门占空比是控制阀处于全开位置的时间与阀门在工作频率下完成一个运动循环所需的时间之比。 控制阀占空比以获得所需的固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和/或推进剂气体流速。
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公开(公告)号：US20090294240A1
公开(公告)日：2009-12-03
申请号：US11847862
申请日：2007-08-30
IPC分类号： F16D11/14
CPC分类号： F16D1/101 , F16D2001/103
摘要： A drive shaft is configured to be disposed between a drive mechanism and a plurality of driven mechanisms and to transfer a drive torque generated by the drive mechanism to one of the plurality of driven mechanisms. The drive shaft includes a first shaft section and a second shaft section. The first shaft section has a first outer diameter, and is dimensioned to be disposed within the drive mechanism, within one of the plurality of driven mechanisms, or simultaneously within the drive mechanism and one of the plurality of driven mechanisms. The first shaft section is also configured to at least selectively engage, and thereby at least selectively receive the drive torque generated in, the drive mechanism. The second shaft section is coupled to the first shaft section and has a second outer diameter that is less than the first outer diameter. The second shaft section is dimensioned to be disposed within either the drive mechanism or one of the plurality of driven mechanisms.
摘要翻译： 驱动轴构造成设置在驱动机构和多个从动机构之间，并将由驱动机构产生的驱动力传递到多个驱动机构中的一个。 驱动轴包括第一轴部和第二轴部。 第一轴部分具有第一外径，并且其尺寸被设置在驱动机构内，在多个从动机构中的一个内，或同时位于驱动机构内，以及多个驱动机构中的一个。 第一轴部分还构造成至少选择性地接合，并且因此至少选择性地接收在驱动机构中产生的驱动转矩。 第二轴部分联接到第一轴部分并且具有小于第一外径的第二外径。 第二轴部的尺寸被设计成设置在驱动机构或多个驱动机构中的一个中。
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10.发明申请SOLID PROPELLANT BURN RATE, PROPELLANT GAS FLOW RATE, AND PROPELLANT GAS PRESSURE PULSE GENERATION CONTROL SYSTEM AND METHOD 失效固体推进剂燃烧速率，推进剂气体流量和推进剂气体压力脉动发生控制系统和方法公开(公告)号：US20080216462A1
公开(公告)日：2008-09-11
申请号：US11683170
申请日：2007-03-07
IPC分类号： F02K9/26
CPC分类号： F02K9/26
摘要： Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on pulse width modulation of a control valve duty cycle. A control valve that is movable between a closed position and a full-open position is disposed downstream of, and in fluid communication with, a solid propellant gas generator. The solid propellant in the solid propellant gas generator is ignited, to thereby generate propellant gas. The control valve is moved between the closed position and the full-open position at an operating frequency and with a valve duty cycle. The valve duty cycle is the ratio of a time the control valve is in the full-open position to a time it takes the valve to complete one movement cycle at the operating frequency. The valve duty cycle is controlled to attain a desired solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and/or propellant gas flow rate.
摘要翻译： 控制固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和推进剂气体流量的系统和方法依赖于控制阀占空比的脉宽调制。 可在关闭位置和全开位置之间移动的控制阀设置在固体推进剂气体发生器的下游并且与固体推进剂气体发生器流体连通。 固体推进剂气体发生器中的固体推进剂被点燃，从而产生推进剂气体。 控制阀在工作频率和阀门占空比下在关闭位置和全开位置之间移动。 阀门占空比是控制阀处于全开位置的时间与阀门在工作频率下完成一个运动循环所需的时间之比。 控制阀占空比以获得所需的固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和/或推进剂气体流速。
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