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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：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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5.发明授权Plasma actuator system and method for use with a weapons bay on a high speed mobile platform 有权等离子致动器系统和方法，用于高速移动平台上的武器舱公开(公告)号：US08016246B2
公开(公告)日：2011-09-13
申请号：US11753869
申请日：2007-05-25
CPC分类号： B64C21/00 , Y02T50/166
摘要： A system and method for controlling a freestream air flow over a surface of an airborne mobile platform, for example an aircraft. In one implementation the system includes a plurality of plasma actuators used on an undersurface of a fuselage of an aircraft upstream of a weapons bay of the aircraft. When the plasma actuators are energized an induced flow is created adjacent the actuators. The induced flow operates to deflect the shear layer created when the freestream air flow moves over the weapons bay (while the bay doors are open), away from the weapons bay. This significantly reduces the oscillating acoustic pressure waves that would normally be produced if the shear layer turns into the weapons bay. The system and method significantly reduces acoustic noise inside the weapons bay and improves separation of ordnance from the weapons bay.
摘要翻译： 一种用于控制在空中移动平台（例如飞行器）的表面上的自由气流的系统和方法。 在一个实施方案中，该系统包括多个等离子体致动器，其用于在飞行器的武器舱上游的飞机的机身的下表面上。 当等离子体致动器通电时，在致动器附近产生感应流。 诱导流动操作以使当自由气流在武器舱（当舱门打开时）移动时产生的剪切层偏离武器舱。 这显着地减少了如果剪切层变成武器舱通常会产生的振荡声压波。 该系统和方法显着降低了武器舱内的声学噪声，并改善了武器与武器舱的分离。
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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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7.发明申请PLASMA ACTUATOR SYSTEM AND METHOD FOR USE WITH A WEAPONS BAY ON A HIGH SPEED MOBILE PLATFORM 有权在高速移动平台上使用武器舱的等离子体执行器系统和方法公开(公告)号：US20080290218A1
公开(公告)日：2008-11-27
申请号：US11753869
申请日：2007-05-25
IPC分类号： B64C1/38
CPC分类号： B64C21/00 , Y02T50/166
摘要： A system and method for controlling a freestream air flow over a surface of an airborne mobile platform, for example an aircraft. In one implementation the system includes a plurality of plasma actuators used on an undersurface of a fuselage of an aircraft upstream of a weapons bay of the aircraft. When the plasma actuators are energized an induced flow is created adjacent the actuators. The induced flow operates to deflect the shear layer created when the freestream air flow moves over the weapons bay (while the bay doors are open), away from the weapons bay. This significantly reduces the oscillating acoustic pressure waves that would normally be produced if the shear layer turns into the weapons bay. The system and method significantly reduces acoustic noise inside the weapons bay and improves separation of ordnance from the weapons bay.
摘要翻译： 一种用于控制在空中移动平台（例如飞行器）的表面上的自由气流的系统和方法。 在一个实施方案中，该系统包括多个等离子体致动器，其用于在飞行器的武器舱上游的飞机的机身的下表面上。 当等离子体致动器通电时，在致动器附近产生感应流。 诱导流动操作以使当自由气流在武器舱（当舱门打开时）移动时产生的剪切层偏离武器舱。 这显着地减少了如果剪切层变成武器舱通常会产生的振荡声压波。 该系统和方法显着降低了武器舱内的声学噪声，并改善了武器与武器舱的分离。
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