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公开(公告)号：US08016247B2
公开(公告)日：2011-09-13
申请号：US11753876
申请日：2007-05-25
IPC分类号： B64C21/00
CPC分类号： B64C23/005 , B64C2230/12 , F15D1/12 , H05H1/54 , Y02T50/166
摘要： A plasma actuator system and method especially well adapted for use on airborne mobile platforms, such as aircraft, for directional and/or attitude control. The system includes at least one plasma actuator having first and second electrodes mounted on a surface of an aircraft. The first and second electrodes are arranged parallel to a boundary layer flow path over the surface. A third electrode is mounted between the first and second electrodes and laterally offset from the first and second electrodes. A high AC voltage signal is applied across the first and third electrodes, which induces a fluid flow between the energized electrodes that helps to delay separation of the boundary layer. Applying the AC voltage across the second and third electrodes causes an induced fluid flow that creates the opposite effect of influencing the boundary layer flow to separate from the surface. A plurality of the actuators can be selectively placed at various locations on the aircraft, and selectively energized to provide directional control and/or attitude control over the aircraft.
摘要翻译： 等离子体致动器系统和方法特别适用于用于定向和/或姿态控制的诸如飞机的机载移动平台上。 该系统包括至少一个等离子体致动器，其具有安装在飞机表面上的第一和第二电极。 第一和第二电极平行于表面上的边界层流动路径布置。 第三电极安装在第一和第二电极之间并且横向偏离第一和第二电极。 跨越第一和第三电极施加高交流电压信号，这引起在通电的电极之间的流体流动，这有助于延迟边界层的分离。 施加交流电压跨越第二和第三电极导致引起的流体流动，其产生影响边界层流动与表面分离的相反作用。 可以将多个致动器选择性地放置在飞机上的各个位置，并且选择性地通电以提供飞机上的方向控制和/或姿态控制。
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2.发明申请DIELECTRIC BARRIER DISCHARGE FLIGHT CONTROL SYSTEM THROUGH MODULATED BOUNDARY LAYER TRANSITION 审中-公开通过调制边界层过渡的电介质障碍物放电控制系统公开(公告)号：US20130292511A1
公开(公告)日：2013-11-07
申请号：US13462170
申请日：2012-05-02
IPC分类号： B64C21/00
CPC分类号： B64C23/005 , Y02T50/166
摘要： An aerodynamic control system incorporates multiple Dielectric Barrier Discharge (DBD) flow control actuators adjacent a surface of an airborne vehicle in a path of laminar boundary layer flow over the surface. A control computer receives a control input and selectively distributes power to an activation array selected from the DBD flow control actuators for transition to a first operating condition tripping the laminar boundary layer at selected streamwise locations for turbulent flow. When the control computer removes the distributed power the DBD flow control actuators return to a second operating condition restoring the laminar boundary layer.
摘要翻译： 空气动力学控制系统将多个介质阻挡放电（DBD）流量控制致动器与表面上的层流边界层流动相邻的机载车辆的表面相邻。 控制计算机接收控制输入并且选择性地将功率分配到从DBD流量控制致动器中选择的激活阵列，以转换到第一操作条件，以在选定的流动位置跳过层流边界层以进行湍流。 当控制计算机移除分布式电力时，DBD流量控制致动器返回恢复层流边界层的第二操作状态。
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公开(公告)号：US20100133386A1
公开(公告)日：2010-06-03
申请号：US11753876
申请日：2007-05-25
CPC分类号： B64C23/005 , B64C2230/12 , F15D1/12 , H05H1/54 , Y02T50/166
摘要： A plasma actuator system and method especially well adapted for use on airborne mobile platforms, such as aircraft, for directional and/or attitude control. The system includes at least one plasma actuator having first and second electrodes mounted on a surface of an aircraft. The first and second electrodes are arranged parallel to a boundary layer flow path over the surface. A third electrode is mounted between the first and second electrodes and laterally offset from the first and second electrodes. A high AC voltage signal is applied across the first and third electrodes, which induces a fluid flow between the energized electrodes that helps to delay separation of the boundary layer. Applying the AC voltage across the second and third electrodes causes an induced fluid flow that creates the opposite effect of influencing the boundary layer flow to separate from the surface. A plurality of the actuators can be selectively placed at various locations on the aircraft, and selectively energized to provide directional control and/or attitude control over the aircraft.
摘要翻译： 等离子体致动器系统和方法特别适用于用于定向和/或姿态控制的诸如飞机的机载移动平台上。 该系统包括至少一个等离子体致动器，其具有安装在飞机表面上的第一和第二电极。 第一和第二电极平行于表面上的边界层流动路径布置。 第三电极安装在第一和第二电极之间并且横向偏离第一和第二电极。 跨越第一和第三电极施加高交流电压信号，这引起在通电的电极之间的流体流动，这有助于延迟边界层的分离。 施加交流电压跨越第二和第三电极导致引起的流体流动，其产生影响边界层流动与表面分离的相反作用。 可以将多个致动器选择性地放置在飞机上的各个位置，并且选择性地通电以提供飞机上的方向控制和/或姿态控制。
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公开(公告)号：US20130001368A1
公开(公告)日：2013-01-03
申请号：US13523761
申请日：2012-06-14
IPC分类号： B64C21/00
CPC分类号： B64C23/005 , B64C2230/04 , B64C2230/12 , F15D1/12 , Y02T50/166
摘要： Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along, a surface of an it vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. Representative actuators discharging the energy can be arranged in a two-dimensional array of individually addressable actuators.
摘要翻译： 公开了用于控制飞行器边界层气流的系统和方法。 代表性的方法可以包括沿着车辆的表面在边界层中以纳秒脉冲施加电能脉冲串和/或其他能量脉冲串。 在特定实施例中，电能被排放到边界层中以减少边界层分离和/或降低边界层从层流向湍流转变的趋势。 排出能量的代表性执行器可以被布置成可独立寻址的致动器的二维阵列。
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公开(公告)号：US20100140418A1
公开(公告)日：2010-06-10
申请号：US12619028
申请日：2009-11-16
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0226 , B64D2033/0286 , F01D5/145 , F02C7/04 , F02C7/057 , F05D2270/172 , Y02T50/671 , Y02T50/673
摘要： Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the engine. The inlet has a longitudinal axis generally aligned with a direction of flow of the air as the air approaches the inlet. The aircraft also includes at least one first dielectric barrier discharge generator positioned to apply a first force to the air prior to the air being received by the engine. The first force acts in a first direction. The aircraft further includes at least one second dielectric barrier discharge generator positioned to apply a second force to the air prior to the air being received by the engine. The second force acts in a second direction that is non-parallel to the first direction.
摘要翻译： 提供飞机的空气感应控制系统和方法。 特定的飞机包括机身，一对机翼和发动机。 飞行器还包括限定孔径的入口以接收用于输送到发动机的空气。 当空气接近入口时，入口具有大致与空气流动方向对准的纵向轴线。 该飞机还包括至少一个第一介质阻挡放电发生器，其定位成在发动机接收空气之前向空气施加第一力。 第一个力作用在第一个方向。 飞机还包括至少一个第二电介质阻挡放电发生器，定位成在发动机接收空气之前向空气施加第二力。 第二力沿不平行于第一方向的第二方向作用。
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公开(公告)号：US07975961B2
公开(公告)日：2011-07-12
申请号：US12619028
申请日：2009-11-16
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0226 , B64D2033/0286 , F01D5/145 , F02C7/04 , F02C7/057 , F05D2270/172 , Y02T50/671 , Y02T50/673
摘要： Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the engine. The inlet has a longitudinal axis generally aligned with a direction of flow of the air as the air approaches the inlet. The aircraft also includes at least one first dielectric barrier discharge generator positioned to apply a first force to the air prior to the air being received by the engine. The first force acts in a first direction. The aircraft further includes at least one second dielectric barrier discharge generator positioned to apply a second force to the air prior to the air being received by the engine. The second force acts in a second direction that is non-parallel to the first direction.
摘要翻译： 提供飞机的空气感应控制系统和方法。 特定的飞机包括机身，一对机翼和发动机。 飞行器还包括限定孔径的入口以接收用于输送到发动机的空气。 当空气接近入口时，入口具有大致与空气流动方向对准的纵向轴线。 该飞机还包括至少一个第一介质阻挡放电发生器，其定位成在发动机接收空气之前向空气施加第一力。 第一个力作用在第一个方向。 飞机还包括至少一个第二电介质阻挡放电发生器，定位成在发动机接收空气之前向空气施加第二力。 第二力沿不平行于第一方向的第二方向作用。
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公开(公告)号：US08220753B2
公开(公告)日：2012-07-17
申请号：US12339674
申请日：2008-12-19
CPC分类号： B64C23/005 , B64C2230/04 , B64C2230/12 , F15D1/12 , Y02T50/166
摘要： Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. In other embodiments, energy can be discharged via pulses having a pulse width of about 100 nanoseconds or less, and an amplitude of about 10,000 volts or more. Actuators discharging the energy can be arranged in a two-dimensional ray of individually addressable actuators. Energy can be delivered to the boundary layer via a laser emitter, and energy can be received in a receiver after having transited over at least a portion of the airflow surface. In another embodiment, high energy electrons can be injected into the boundary layer using a hollow cathode array at the airflow surface. In still another embodiment, energy can be introduced at the surface of the air vehicle at a rate sufficient to heat the flow and cause shock waves to propagate into the flow.
摘要翻译： 公开了用于控制飞行器边界层气流的系统和方法。 代表性的方法可以包括沿着空中交通工具的表面在边界层中以纳秒脉冲施加电能脉冲串和/或其他能量脉冲串。 在特定实施例中，电能被排放到边界层中以减少边界层分离和/或降低边界层从层流向湍流转变的趋势。 在其他实施例中，能够通过具有约100纳秒或更小的脉冲宽度以及大约10,000伏特或更高的振幅的脉冲放电能量。 排出能量的致动器可以排列成可独立寻址的致动器的二维光线。 能量可以通过激光发射器被传送到边界层，并且在经过气流表面的至少一部分之后，可以在接收器中接收能量。 在另一个实施例中，高能电子可以在气流表面使用空心阴极阵列注入边界层。 在另一个实施例中，可以以足以加热流动并引起冲击波传播到流中的速率将能量引入空中交通工具的表面。
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公开(公告)号：US20090196765A1
公开(公告)日：2009-08-06
申请号：US12023697
申请日：2008-01-31
IPC分类号： F04B53/00
CPC分类号： H05H1/2406
摘要： A dielectric element barrier discharge pump for accelerating a fluid flow. In one embodiment the pump has a first dielectric layer having a first electrode embedded therein and a second dielectric layer having a second electrode embedded therein. The first and second dielectric layers are further supported apart from one another to form an air gap therebetween. A third electrode is disposed at least partially in the air gap upstream of the first and second electrodes, relative to a direction of flow of the fluid flow. A high voltage supplies a high voltage signal to the third electrode. The electrodes cooperate to generate opposing asymmetric plasma fields in the gap that create an induced air flow within the gap. The induced air flow operates to accelerate the fluid flow as the fluid flow moves through the gap.
摘要翻译： 一种用于加速流体流动的介质元件阻挡排放泵。 在一个实施例中，泵具有第一电介质层，其具有嵌入其中的第一电极和第二电介质层，其中嵌有第二电极。 第一和第二电介质层彼此分开地被支撑以在它们之间形成气隙。 第三电极相对于流体流动的流动方向至少部分地设置在第一和第二电极的上游的空气间隙中。 高电压向第三电极提供高电压信号。 电极配合以在间隙中产生相对的不对称等离子体场，其在间隙内产生感应空气流。 当流体流动通过间隙时，感应空气流动来加速流体流动。
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公开(公告)号：US08727286B2
公开(公告)日：2014-05-20
申请号：US13523761
申请日：2012-06-14
IPC分类号： B64C23/04
CPC分类号： B64C23/005 , B64C2230/04 , B64C2230/12 , F15D1/12 , Y02T50/166
摘要： Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. Representative actuators discharging the energy can be arranged in a two-dimensional array of individually addressable actuators.
摘要翻译： 公开了用于控制飞行器边界层气流的系统和方法。 代表性的方法可以包括沿着空中交通工具的表面在边界层中以纳秒脉冲施加电能脉冲串和/或其他能量脉冲串。 在特定实施例中，电能被排放到边界层中以减少边界层分离和/或降低边界层从层流向湍流转变的趋势。 排出能量的代表性执行器可以被布置成可独立寻址的致动器的二维阵列。
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公开(公告)号：US08172547B2
公开(公告)日：2012-05-08
申请号：US12023697
申请日：2008-01-31
IPC分类号： F04B37/04
CPC分类号： H05H1/2406
摘要： A dielectric element barrier discharge pump for accelerating a fluid flow. In one embodiment the pump has a first dielectric layer having a first electrode embedded therein and a second dielectric layer having a second electrode embedded therein. The first and second dielectric layers are further supported apart from one another to form an air gap therebetween. A third electrode is disposed at least partially in the air gap upstream of the first and second electrodes, relative to a direction of flow of the fluid flow. A high voltage supplies a high voltage signal to the third electrode. The electrodes cooperate to generate opposing asymmetric plasma fields in the gap that create an induced air flow within the gap. The induced air flow operates to accelerate the fluid flow as the fluid flow moves through the gap.
摘要翻译： 一种用于加速流体流动的介质元件阻挡排放泵。 在一个实施例中，泵具有第一电介质层，其具有嵌入其中的第一电极和第二电介质层，其中嵌有第二电极。 第一和第二电介质层彼此分开地被支撑以在它们之间形成气隙。 第三电极相对于流体流动的流动方向至少部分地设置在第一和第二电极的上游的空气间隙中。 高电压向第三电极提供高电压信号。 电极配合以在间隙中产生相对的不对称等离子体场，其在间隙内产生感应空气流。 当流体流动通过间隙时，感应空气流动来加速流体流动。
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