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公开(公告)号：US20090206208A1
公开(公告)日：2009-08-20
申请号：US11387189
申请日：2006-03-22
IPC分类号： B64C27/24 , B64C27/467 , B64C27/18
摘要： In an exemplary variable area nozzle, a fixed duct section has an inlet and an outlet oriented approximately perpendicular to the inlet. A controllable nozzle member is disposed adjacent the outlet of the fixed duct section. The controllable nozzle member has an area that is adjustable to maintain a substantially constant nozzle pressure ratio. The controllable nozzle member may include first and second flap doors hinged and pivotable in opposite directions between an open position and a closed position and that also may be hinged and pivotable in a same direction so thrust from gas exiting the nozzle is vectorable. When disposed in rotor tips of an aircraft capable of rotary wing flight and fixed wing flight, the variable area nozzle may maintain a substantially constant nozzle pressure ratio near an optimized nozzle pressure ratio as the aircraft transitions from rotary wing flight to fixed wing flight.
摘要翻译： 在示例性可变区域喷嘴中，固定管道部分具有大致垂直于入口定向的入口和出口。 可控喷嘴构件邻近固定管段的出口设置。 可控喷嘴构件具有可调节的区域，以保持基本恒定的喷嘴压力比。 可控喷嘴构件可以包括在打开位置和关闭位置之间以相反方向铰接和枢转的第一和第二折翼门，并且也可以在相同方向上铰接和枢转，从而从喷嘴排出的气体的推力是可向量的。 当设置在能够旋转翼飞行和固定翼飞行的飞行器的转子尖端时，随着飞机从旋翼飞行转变到固定翼飞行，可变区喷嘴可以在最佳喷嘴压力比附近保持基本恒定的喷嘴压力比。
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公开(公告)号：US07452156B2
公开(公告)日：2008-11-18
申请号：US11561099
申请日：2006-11-17
申请人： Dennis K. Kennedy
发明人： Dennis K. Kennedy
IPC分类号： F16B7/00
CPC分类号： B29C53/562 , B29C70/86 , B29L2031/75 , F16C3/023 , F16C7/02 , Y10T403/551 , Y10T403/5761
摘要： Composite structural members are provided including a fitting and a tubular shaft. The fitting has a coupling region defining at least one recessed portion bounded by one or more non-recessed portions. The recessed portion may extend circumferentially around the fitting to form a neck. The tubular shaft has a mating region and defines a lumen in which the fitting is disposed. The mating region of the shaft mates with the coupling region of the fitting to create interference between the shaft and fitting. Adhesive may be disposed between the mating region of the fitting and the coupling region of the shaft. The mating region of the shaft may be partially and proximately surrounded by a reinforcing member, and a sleeve may be coupled substantially concentrically to the shaft for discouraging separation of the reinforcing member and the mating region of the shaft. In some cases, adhesive is disposed between the reinforcing member and sleeve.
摘要翻译： 提供了包括配件和管状轴的复合结构构件。 配件具有限定由一个或多个非凹部限定的至少一个凹部的联接区域。 凹部可以围绕配件周向延伸以形成颈部。 管状轴具有配合区域并且限定其中配置件设置在其中的内腔。 轴的配合区域与配件的联接区域配合，以在轴和配件之间产生干涉。 粘合剂可以设置在配件的配合区域和轴的联接区域之间。 轴的配合区域可以被加强构件部分地和近似地围绕，并且套筒可以基本上同心地联接到轴，用于阻止加强构件和轴的配合区域的分离。 在一些情况下，粘合剂设置在加强构件和套筒之间。
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公开(公告)号：US6135713A
公开(公告)日：2000-10-24
申请号：US233986
申请日：1999-01-19
IPC分类号： B64C27/00 , B64C27/615 , B64C9/00
CPC分类号： B64C27/615 , B64C27/001 , B64C2027/7277 , B64C2027/7283 , B64C2027/7288 , Y02T50/34
摘要： An actively controlled helicopter rotor blade includes a trailing edge flap actuated by a fast-acting actuator. A lightweight, rugged, fast-acting actuator suitable for use as the flap actuator comprises a pair of column actuators composed of a smart material such as piezoelectric, magnetostrictive, shape memory alloy or other material that exhibits a shape change when subjected to an external stimulus. Each of the column actuators is composed of multiple piezoelectric ceramic actuator elements bonded together to form the individual columns. Each of the column actuators engages the base of an actuator tube that, in turn, is urged against the column actuators by a tension member. Differential voltage applied to the columns causes a differential elongation of the column actuators, which causes the actuator tube to pivot about an axis proximal the tips of the column actuators. The movement of the actuator tube is coupled by a linkage to the rotor blade flap. Spherical joints are disposed between the column actuators and the actuator tube to prevent transmission of substantial bending loads to the column actuators and a mid-point support is also provided for each of the column actuators to limit the magnitude of acceleration induced bending loads, which would otherwise lead to tensile failure of the ceramic actuator elements.
摘要翻译： 主动控制的直升机转子叶片包括由快速作用的致动器驱动的后缘翼片。 一种轻巧，坚固，快速作用的致动器，适合用作翼片致动器，包括一对柱形致动器，其由诸如压电，磁致伸缩，形状记忆合金或其它材料的智能材料组成，当受到外部刺激时，其表现出形状变化 。 每个柱致动器由多个压电陶瓷致动器元件组成，结合在一起以形成各个柱。 每个柱致动器接合致动器管的基部，而致动器管的基部又被张力构件推靠在柱致动器上。 施加到柱的差分电压导致柱致动器的差异伸长，这导致致动器管围绕靠近柱致动器的尖端的轴线枢转。 致动器管的运动通过连接件与转子叶片翼片联接。 球形接头设置在柱致动器和致动器管之间，以防止将实质的弯曲载荷传递到柱致动器，并且还为每个柱致动器提供中点支撑件，以限制加速度引起的弯曲载荷的大小， 否则导致陶瓷致动器元件的拉伸失效。
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公开(公告)号：US20120199271A1
公开(公告)日：2012-08-09
申请号：US13447870
申请日：2012-04-16
申请人： Dennis K. Kennedy
发明人： Dennis K. Kennedy
IPC分类号： B32B7/04
CPC分类号： F16C7/026 , Y10T403/49 , Y10T403/4933 , Y10T403/4941 , Y10T403/4949 , Y10T403/4958 , Y10T403/4966 , Y10T403/4991 , Y10T403/50 , Y10T403/55 , Y10T403/551 , Y10T403/559 , Y10T403/5753 , Y10T403/5761 , Y10T403/5766 , Y10T403/5773 , Y10T403/5781 , Y10T403/5786 , Y10T403/5793 , Y10T403/58 , Y10T464/50
摘要： A composite structural member is provided. The structural member includes a tubular shaft having a mating region of stiffness, and possibly thickness, greater than another region of said shaft. The shaft defines a lumen, and a fitting is disposed in the lumen. The fitting has a coupling region that defines at least one recessed portion bounded by one or more non-recessed portions, and the mating region mates with the coupling region of said fitting. As such, the shaft and fitting are mechanically restrained from at least some relative movement due to interference of the shaft and the fitting. A sleeve may be coupled to said shaft, for example, by including a tubular inner surface that proximately surrounds at least part of said shaft and mating region, for discouraging expansion of the mating region of said shaft.
摘要翻译： 提供复合结构件。 结构构件包括管状轴，其具有大于所述轴的另一区域的刚度和可能的厚度的配合区域。 轴限定了内腔，并且配合件设置在内腔中。 配件具有限定由一个或多个非凹部限定的至少一个凹部的联接区域，并且配合区域与所述配件的联接区域配合。 因此，轴和配件由于轴和配件的干涉而被机械地限制至少一些相对运动。 套筒可以例如通过包括一个管状的内表面来连接到所述轴上，所述管状内表面近似地围绕所述轴和配合区域的至少一部分，以阻止所述轴的配合区域的膨胀。
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公开(公告)号：US07837141B2
公开(公告)日：2010-11-23
申请号：US11387189
申请日：2006-03-22
IPC分类号： B64C27/24 , B05B1/26 , B64C27/615
摘要： In an exemplary variable area nozzle, a fixed duct section has an inlet and an outlet oriented approximately perpendicular to the inlet. A controllable nozzle member is disposed adjacent the outlet of the fixed duct section. The controllable nozzle member has an area that is adjustable to maintain a substantially constant nozzle pressure ratio. The controllable nozzle member may include first and second flap doors hinged and pivotable in opposite directions between an open position and a closed position and that also may be hinged and pivotable in a same direction so thrust from gas exiting the nozzle is vectorable. When disposed in rotor tips of an aircraft capable of rotary wing flight and fixed wing flight, the variable area nozzle may maintain a substantially constant nozzle pressure ratio near an optimized nozzle pressure ratio as the aircraft transitions from rotary wing flight to fixed wing flight.
摘要翻译： 在示例性可变区域喷嘴中，固定管道部分具有大致垂直于入口定向的入口和出口。 可控喷嘴构件邻近固定管段的出口设置。 可控喷嘴构件具有可调节的区域，以保持基本恒定的喷嘴压力比。 可控喷嘴构件可以包括在打开位置和关闭位置之间以相反方向铰接和枢转的第一和第二折翼门，并且也可以在相同方向上铰接和枢转，从而从喷嘴排出的气体的推力是可向量的。 当设置在能够旋转翼飞行和固定翼飞行的飞行器的转子尖端时，随着飞机从旋翼飞行转变到固定翼飞行，可变区喷嘴可以在最佳喷嘴压力比附近保持基本恒定的喷嘴压力比。
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公开(公告)号：US20080118303A1
公开(公告)日：2008-05-22
申请号：US11562605
申请日：2006-11-22
申请人： Dennis K. Kennedy
发明人： Dennis K. Kennedy
IPC分类号： F16B12/36
CPC分类号： F16C7/026 , Y10T403/49 , Y10T403/4933 , Y10T403/4941 , Y10T403/4949 , Y10T403/4958 , Y10T403/4966 , Y10T403/4991 , Y10T403/50 , Y10T403/55 , Y10T403/551 , Y10T403/559 , Y10T403/5753 , Y10T403/5761 , Y10T403/5766 , Y10T403/5773 , Y10T403/5781 , Y10T403/5786 , Y10T403/5793 , Y10T403/58 , Y10T464/50
摘要： A composite structural member is provided. The structural member includes a tubular shaft having a mating region of stiffness, and possibly thickness, greater than another region of said shaft. The shaft defines a lumen, and a fitting is disposed in the lumen. The fitting has a coupling region that defines at least one recessed portion bounded by one or more non-recessed portions, and the mating region mates with the coupling region of said fitting. As such, the shaft and fitting are mechanically restrained from at least some relative movement due to interference of the shaft and the fitting. A sleeve may be coupled to said shaft, for example, by including a tubular inner surface that proximately surrounds at least part of said shaft and mating region, for discouraging expansion of the mating region of said shaft.
摘要翻译： 提供复合结构件。 结构构件包括管状轴，其具有大于所述轴的另一区域的刚度和可能的厚度的配合区域。 轴限定了内腔，并且配合件设置在内腔中。 配件具有限定由一个或多个非凹部限定的至少一个凹部的联接区域，并且配合区域与所述配件的联接区域配合。 因此，轴和配件由于轴和配件的干涉而被机械地限制至少一些相对运动。 例如，套筒可以联接到所述轴上，例如通过包括近似地围绕所述轴和配合区域的至少一部分的管状内表面，以阻止所述轴的配合区域的膨胀。
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7.发明授权Helicopter in-flight rotor tracking system, method, and smart actuator therefor 失效直升机飞行转子跟踪系统，方法和智能执行机构公开(公告)号：US06453669B2
公开(公告)日：2002-09-24
申请号：US09955769
申请日：2001-09-19
IPC分类号： F01B2910
CPC分类号： B64C27/008 , B64C27/001 , B64C2027/7266 , Y02T50/34 , Y10S416/50
摘要： A system for quasi-statically correcting tracking of rotor blades of a helicopter rotor during operation includes a trim tab mounted on each rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade, and a rotor track and balance analyzer that includes sensors for acquiring rotor tracking and balance information and is operable to process the rotor tracking and balance information so as to predetermine a new tab position to which the trim tab should be deflected for bringing the tracking path of a mistracking rotor blade into alignment with a reference path. The trim tab is deflected by an actuator mounted to the rotor blade, the actuator having an actuating element coupled with the trim tab and formed of a smart material such that the actuating element deforms proportional to a stimulus applied to the actuating element. An electrical locking device is included which is operable when de-energized to lock the trim tab against deflection, and operable when energized to unlock to permit the trim tab to be deflected. A trim actuation control system in communication with the rotor track and balance analyzer and the locking device is arranged to energize the locking device and to supply electrical power to the actuator so as to deflect the trim tab to the new tab position predetermined in the rotor track and balance analyzer, and to then de-energize the locking device and cut off the electrical power to the actuator. Thus, electrical power is supplied to the actuator only while the trim tab is being deflected, and is then discontinued once the tab has reached the desired position and the locking device has been de-energized to lock the tab against further movement.
摘要翻译： 用于在运行期间对直升机转子的转子叶片进行准静态校正跟踪的系统包括安装在每个转子叶片上并相对于转子叶片可偏转的修剪翼片，以便改变转子叶片的跟踪路径，以及转子轨道和 平衡分析器，其包括用于获取转子跟踪和平衡信息的传感器，并且可操作以处理转子跟踪和平衡信息，以便预先确定修剪片应该偏转到的新的突片位置，以使错误的转子叶片的跟踪路径进入 与参考路径对齐。 调节片由安装在转子叶片上的致动器偏转，致动器具有与调节片接合并由智能材料形成的致动元件，使得致动元件与施加于致动元件的刺激成比例地变形。 包括电锁定装置，其在断电时可操作以将修剪接片锁定以防止偏转，并且在通电时可操作以解锁以允许修剪突片被偏转。 与转子轨道和平衡分析器和锁定装置连通的调整致动控制系统被布置成对锁定装置通电并且向致动器提供电力，以便将调整片偏转到预定在转子轨道中的新的突片位置 和平衡分析仪，然后使锁定装置断电并切断致动器的电力。 因此，仅当调整片被偏转时才向致动器提供电力，并且一旦突片已经到达期望的位置并且锁定装置已经被断电以锁定突片以防止进一步的运动，则电功率被中断。
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公开(公告)号：US08419887B2
公开(公告)日：2013-04-16
申请号：US13447870
申请日：2012-04-16
申请人： Dennis K. Kennedy
发明人： Dennis K. Kennedy
IPC分类号： F16B7/00
CPC分类号： F16C7/026 , Y10T403/49 , Y10T403/4933 , Y10T403/4941 , Y10T403/4949 , Y10T403/4958 , Y10T403/4966 , Y10T403/4991 , Y10T403/50 , Y10T403/55 , Y10T403/551 , Y10T403/559 , Y10T403/5753 , Y10T403/5761 , Y10T403/5766 , Y10T403/5773 , Y10T403/5781 , Y10T403/5786 , Y10T403/5793 , Y10T403/58 , Y10T464/50
摘要： A composite structural member is provided. The structural member includes a tubular shaft having a mating region of stiffness, and possibly thickness, greater than another region of said shaft. The shaft defines a lumen, and a fitting is disposed in the lumen. The fitting has a coupling region that defines at least one recessed portion bounded by one or more non-recessed portions, and the mating region mates with the coupling region of said fitting. As such, the shaft and fitting are mechanically restrained from at least some relative movement due to interference of the shaft and the fitting. A sleeve may be coupled to said shaft, for example, by including a tubular inner surface that proximately surrounds at least part of said shaft and mating region, for discouraging expansion of the mating region of said shaft.
摘要翻译： 提供复合结构件。 结构构件包括管状轴，其具有大于所述轴的另一区域的刚度和可能的厚度的配合区域。 轴限定了内腔，并且配合件设置在内腔中。 配件具有限定由一个或多个非凹部限定的至少一个凹部的联接区域，并且配合区域与所述配件的联接区域配合。 因此，轴和配件由于轴和配件的干涉而被机械地限制至少一些相对运动。 套筒可以例如通过包括一个管状的内表面来连接到所述轴上，所述管状内表面近似地围绕所述轴和配合区域的至少一部分，以阻止所述轴的配合区域的膨胀。
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公开(公告)号：US5938404A
公开(公告)日：1999-08-17
申请号：US869372
申请日：1997-06-05
CPC分类号： B64C27/001 , B64C23/04 , B64C2230/02 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/18 , B64C2230/22 , B64C2230/28 , Y02T50/166 , Y10S416/50
摘要： An active control device for use on an aerodynamic structure is provided. The aerodynamic structure includes an outer aerodynamic skin and an interior volume, wherein the outer aerodynamic skin surrounds the interior volume. The active control device includes at least one aperture disposed on the outer aerodynamic skin and a diaphragm disposed in the interior volume of the aerodynamic structure. The at least one aperture connects the outer aerodynamic skin to the interior volume, and the diaphragm in the interior volume is movable between a first position and a second position. Movement of the diaphragm from the first position to the second position pushes air through the at least one aperture and out of the interior volume. Movement of the diaphragm from the second position to the first position draws air through the at least one aperture and into the interior volume. The diaphragm may be circular, or may be oval-shaped.
摘要翻译： 提供了一种用于空气动力学结构的主动控制装置。 空气动力学结构包括外部空气动力学皮肤和内部空间，其中外部空气动力学皮肤围绕内部空间。 主动控制装置包括设置在外部空气动力学皮肤上的至少一个孔和设置在空气动力结构的内部空间中的隔膜。 至少一个孔将外部空气动力学皮肤连接到内部空间，并且内部空间中的隔膜可在第一位置和第二位置之间移动。 隔膜从第一位置到第二位置的移动推动空气穿过至少一个孔并离开内部空间。 隔膜从第二位置到第一位置的移动通过至少一个孔吸入空气并进入内部空间。 隔膜可以是圆形的，或者可以是椭圆形。
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10.发明授权
公开(公告)号：US5813625A
公开(公告)日：1998-09-29
申请号：US727980
申请日：1996-10-09
IPC分类号： B64C23/06 , B64C27/467 , B64C27/00
CPC分类号： B64C27/467 , B64C23/06 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/22 , B64C2230/28 , Y02T50/162 , Y02T50/166
摘要： A pressurized porous surface near the leading edge of a rotorcraft blade, is designed to be used as an active control device which alleviates the aerodynamics of blade vortex interactions (BVI) and thus the impulsive BVI noise levels and signature. The pressurized porous surface can be actuated on an azimuth-dependent deployment schedule or actuated continuously. The pressurized porous surface is supplied with either positively pressurized air, negatively pressurized air, or a combination of both, when actuated. The pressurized porous surface targets the local blade aerodynamics, rather than the vortex strength or blade/vortex separation distance. This targeting can be achieved through use of negatively pressurized air (suction) blowing in a direction normal to the blade surface to reduce the rotor blade's effective thickness resulting in a smaller leading edge radius as perceived by the vortex wake, and positively pressurized air (blowing) to increase the effective thickness resulting in an increase in the leading edge radius of the blade.
摘要翻译： 旋翼飞机叶片前缘附近的加压多孔表面被设计为用作主动控制装置，其减轻叶片涡流相互作用（BVI）的空气动力学，从而减轻脉冲BVI噪声水平和签名。 加压的多孔表面可以在依赖于方位的部署计划上被致动或连续致动。 被加压的多孔表面在被致动时被供应有正压空气，负压空气或两者的组合。 加压多孔表面针对局部叶片的空气动力学，而不是涡流强度或叶片/涡流分离距离。 这种瞄准可以通过在垂直于叶片表面的方向上使用负压空气（吸入）吹气来实现，以减小转子叶片的有效厚度，从而导致由涡流尾迹感知到的较小的前缘半径，以及正压的空气 ）以增加有效厚度，导致叶片的前缘半径增加。
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