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公开(公告)号：US07997538B2
公开(公告)日：2011-08-16
申请号：US12047489
申请日：2008-03-13
IPC分类号： B64C23/06
摘要： A fan control effector for an aircraft comprises at least one blade configured to be pivotably deployable in a radially outward direction from a retracted position to a deployed position such that the blade extends out of the aircraft. The fan control effector may be mounted in a symmetrical arrangement about a longitudinal axis on opposing wings of the aircraft. Furthermore, the fan control effector may comprise any number of blades for independent deployment outwardly from the wing. The blades are configured to be angularly deployable along a direction that is non-parallel to the longitudinal axis of the aircraft. The blades may be configured to be deployable sequentially from the wing starting with an initial deployment of an aft-most one of the blades.
摘要翻译： 用于飞行器的风扇控制执行器包括至少一个叶片，其构造成可在径向向外的方向上从缩回位置枢转地展开到展开位置，使得叶片延伸出飞行器。 风扇控制效应器可以围绕飞机的相对翼上的纵向轴线对称地安装。 此外，风扇控制执行器可以包括用于从机翼向外独立部署的任何数量的叶片。 叶片构造成沿着不平行于飞行器的纵向轴线的方向成角度地展开。 叶片可以被构造成从机翼开始以最后一个叶片的初始部署顺序地展开。
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公开(公告)号：US20090230240A1
公开(公告)日：2009-09-17
申请号：US12047489
申请日：2008-03-13
IPC分类号： B64C9/00
摘要： A fan control effector for an aircraft comprises at least one blade configured to be pivotably deployable in a radially outward direction from a retracted position to a deployed position such that the blade extends out of the aircraft. The fan control effector may be mounted in a symmetrical arrangement about a longitudinal axis on opposing wings of the aircraft. Furthermore, the fan control effector may comprise any number of blades for independent deployment outwardly from the wing. The blades are configured to be angularly deployable along a direction that is non-parallel to the longitudinal axis of the aircraft. The blades may be configured to be deployable sequentially from the wing starting with an initial deployment of an aft-most one of the blades.
摘要翻译： 用于飞行器的风扇控制执行器包括至少一个叶片，其构造成可在径向向外的方向上从缩回位置枢转地展开到展开位置，使得叶片延伸出飞行器。 风扇控制效应器可以围绕飞机的相对翼上的纵向轴线对称地安装。 此外，风扇控制执行器可以包括用于从机翼向外独立部署的任何数量的叶片。 叶片构造成沿着不平行于飞行器的纵向轴线的方向成角度地展开。 叶片可以被构造成从机翼开始以最后一个叶片的初始部署顺序地展开。
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3.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：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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公开(公告)号：US08016245B2
公开(公告)日：2011-09-13
申请号：US11583140
申请日：2006-10-18
申请人： Ahmed A. Hassan , Bradley A. Osborne , Scott Schwimley , Garry Billman , Mary Billman, legal representative
CPC分类号： B64C23/04 , B64C2003/148 , Y02T50/12
摘要： A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow through the surface. The jet flow is at a second velocity that is substantially less than the first velocity. A recirculation region is upstream of the normal shockwave and is disposed at least partially in the boundary layer. The recirculation region is established at least by the oscillating jet. A generally oblique wave is established by the recirculation region and weakens the normal shockwave to reduce the overall drag experienced by the surface.
摘要翻译： 用于减少移动平台的整体拖动的系统包括气流形成边界层的表面和通常正常的冲击波。 气流处于跨音速和超音速之一的第一速度。 振荡射流注入并提取穿过表面的喷射流。 射流处于基本上小于第一速度的第二速度。 再循环区域是正常冲击波的上游，并且至少部分地设置在边界层中。 至少通过振荡射流建立再循环区域。 一般倾斜的波浪由再循环区域建立，削弱了正常的冲击波，减少了表面经受的整体阻力。
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公开(公告)号：US20090084906A1
公开(公告)日：2009-04-02
申请号：US11583140
申请日：2006-10-18
IPC分类号： B64C21/08
CPC分类号： B64C23/04 , B64C2003/148 , Y02T50/12
摘要： A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow through the surface. The jet flow is at a second velocity that is substantially less than the first velocity. A recirculation region is upstream of the normal shockwave and is disposed at least partially in the boundary layer. The recirculation region is established at least by the oscillating jet. A generally oblique wave is established by the recirculation region and weakens the normal shockwave to reduce the overall drag experienced by the surface.
摘要翻译： 用于减少移动平台的整体拖动的系统包括气流形成边界层的表面和通常正常的冲击波。 气流处于跨音速和超音速之一的第一速度。 振荡射流注入并提取穿过表面的喷射流。 射流处于基本上小于第一速度的第二速度。 再循环区域是正常冲击波的上游，并且至少部分地设置在边界层中。 至少通过振荡射流建立再循环区域。 一般倾斜的波浪由再循环区域建立，削弱了正常的冲击波，减少了表面经受的整体阻力。
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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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