公开(公告)号：US08191833B1

公开(公告)日：2012-06-05

申请号：US11415534

申请日：2006-05-02

申请人： Jack DiCocco ,  Troy Prince ,  Mehul Patel ,  Tsun Ming Terry Ng

发明人： Jack DiCocco ,  Troy Prince ,  Mehul Patel ,  Tsun Ming Terry Ng

IPC分类号： B64C21/00

CPC分类号： B64C21/00 ,  B64C5/12 ,  F41G7/00 ,  F42B10/14 ,  F42B10/60 ,  F42B10/62 ,  F42B15/01 ,  G05D1/0088

摘要： The present invention relates to an afterbody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor each having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.

摘要翻译： 本发明涉及后体流量控制系统，更具体地涉及用于增强机动性和稳定性的飞机或导弹流量控制系统。 本发明还涉及一种操作流量控制系统的方法。 在一个实施例中，本发明包括一个包括后身体和前体的导弹或飞机; 在导弹或飞机后身上至少有一个可激活的流动执行器; 每个具有信号的至少一个传感器，所述至少一个传感器被定位成检测导弹或飞机后身上的力或流动状况; 和闭环控制系统; 其中所述闭环控制系统用于至少部分地基于所述至少一个传感器的信号来激活和去激活所述至少一个可激活的流动效应器。

公开(公告)号：US07977615B1

公开(公告)日：2011-07-12

申请号：US11800606

申请日：2007-05-07

申请人： Troy Prince ,  Frederick J. Lisy ,  Mehul P. Patel ,  Jack M. DiCocco ,  Reed Carver ,  Robert N. Schmidt

发明人： Troy Prince ,  Frederick J. Lisy ,  Mehul P. Patel ,  Jack M. DiCocco ,  Reed Carver ,  Robert N. Schmidt

IPC分类号： F42B15/01 ,  F42B15/10 ,  B64C5/10

CPC分类号： B64C21/00 ,  B64C5/12 ,  F41G7/00 ,  F42B10/14 ,  F42B10/60 ,  F42B10/62 ,  F42B15/01 ,  G05D1/0088

摘要： A forebody flow control system and more particularly to aircraft or missile flow control systems for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one flow effector on the missile or aircraft forebody; at least one sensor having a signal associated therewith, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one flow effector based on at least in part the signal of the at least one sensor.

摘要翻译： 前身流量控制系统，更具体地涉及飞机或导弹流量控制系统，用于在高攻角下增强机动性和稳定性。 本发明还涉及一种操作流量控制系统的方法。 在一个实施例中，本发明包括一个包括后身体和前体的导弹或飞机; 导弹或飞机前身上至少有一个流动执行器; 至少一个传感器具有与之相关联的信号，所述至少一个传感器被定位成检测导弹或飞行器前体上的流动分离; 和闭环控制系统; 其中所述闭环控制系统用于至少部分地基于所述至少一个传感器的信号来激活和去激活所述至少一个流动效应器。

公开(公告)号：US07907038B2

公开(公告)日：2011-03-15

申请号：US12100890

申请日：2008-04-10

申请人： Frank K. Lu ,  Donald R. Wilson ,  J. Craig Dutton

发明人： Frank K. Lu ,  Donald R. Wilson ,  J. Craig Dutton

IPC分类号： H01F3/00 ,  F16K31/02

CPC分类号： B64C21/00 ,  B64C23/005 ,  B64C2230/12 ,  Y02T50/166

摘要： Actuation for control of surfaces is provided through use of a conducting material comprising electrolyte particles electrically charged with electromagnetic fields in boundary layers. Interactions of the electrically charged particles with electromagnetic fields in boundary layers are coordinated for generation of control forces for various applications.

摘要翻译： 通过使用包含在边界层中带有电磁场的电解质颗粒的导电材料来提供用于控制表面的致动。 带电粒子与边界层中的电磁场的相互作用被协调以产生用于各种应用的控制力。

公开(公告)号：US20040011923A1

公开(公告)日：2004-01-22

申请号：US10156205

申请日：2002-07-22

发明人： John Daniel Romo

IPC分类号： B64C015/02 ,  B64C029/00

CPC分类号： B64C11/001 ,  B64C3/00 ,  B64C21/00 ,  B64C29/0025 ,  Y02T50/166

摘要： To obtain an augmented lift coefficient for a given airfoil set at a maximum angle of attack (null), in a steady state airflow system, a shrouded motorized propeller is installed normal to its upper side, creating additional airflow. An outlet for the additional airflow is provided including a horizontal motorized propeller placed at the trailing edge of the airfoil. The motorized propeller converts the additional air flow into a down-wash generating additional lift. Neither the first nor the second installation alone will produce the augmented lift efficiently. Therefore, the combination of the first and the second installation is needed. The propeller-wing arrangement is implement in the airfoils.

摘要翻译： 为了获得在最大迎角（α）下的给定翼型组的增强升力系数，在稳态气流系统中，被覆盖的电动螺旋桨安装在其上侧，产生额外的气流。 提供了用于附加气流的出口，包括放置在翼型的后缘处的水平电动螺旋桨。 电动螺旋桨将额外的空气流转换成下洗生成附加升降机。 单独的第一和第二安装不能有效地产生增强升力。 因此，需要第一和第二安装的组合。 螺旋桨翼结构在机翼中实现。

公开(公告)号：US06484971B2

公开(公告)日：2002-11-26

申请号：US09748255

申请日：2000-12-27

申请人： Thombi Layukallo

发明人： Thombi Layukallo

IPC分类号： B64C138

CPC分类号： B64C23/005 ,  B64C9/00 ,  B64C21/00 ,  Y02T50/166

摘要： Method and apparatus for suppressing fluid flow separation from a surface of a body during flow of a fluid along the surface of the body. At least one barrier member (for example, at least one tab) is provided extending away from the surface of the body and into a separated flow region adjacent the body surface, but not into a smooth flow region beyond the separated flow region. Where a plurality of barrier members are used, the barrier members are located spaced from each other along the direction of flow of the fluid. The barrier member suppresses upstream movement of the separation point between smooth flow along the body surface and separated flow. A chamber extending from the body surface and into the body can be positioned at the barrier member, to provide a place for vortices in the fluid flow to settle down. The barrier member can be moved from a position where it is co-planar with the body surface to a position where it extends away from the surface into the separated flow region.

公开(公告)号：US6059236A

公开(公告)日：2000-05-09

申请号：US99852

申请日：1998-06-19

申请人： Stanley I. Tsunoda

发明人： Stanley I. Tsunoda

IPC分类号： B64C21/00 ,  F15D1/12

CPC分类号： F15D1/12 ,  B64C21/00 ,  B64C2230/12 ,  F05D2270/172 ,  Y02T50/166

摘要： Magnetic and electric fields are used in a controlled manner to create equal and oppositely-directed Lorentz forces tangential to the surface of a control tile that affect the flow of a conductive fluid near the boundary layer of the control tile, or a matrix of control tiles, immersed in a conductive fluid. The control tiles are combined to form control cells, with each control cell including a pair of electrodes and at least one permanent magnet. The pair of electrodes are coupled to a current source which biases the electrodes to cause an electrical current to flow from a positive electrode (anode), through the conductive fluid in which the cell electrodes are immersed, to a negative electrode (cathode). The current source may be time multiplexed to better control the direction of the current flow between adjacent electrodes. The permanent magnet generates a magnetic field which is positioned to interact with the electrical current where the magnetic field is strongest, thereby creating a strong tangential Lorentz force. Such force influences the flow of the conductive fluid, near the boundary of the control tile, e.g., reduces drag of the fluid as it flows over the tile surface. The invention may be used, e.g., within the hull of an ocean-going ship to reduce the drag of the sea water passing over the surface of the hull.

摘要翻译： 以受控的方式使用磁场和电场来产生与控制瓦片的表面相切的相等且相反导向的洛伦兹力，所述洛伦兹力影响控制瓦片的边界层附近的导电流体的流动，或控制瓦片矩阵 浸入导电流体中。 控制瓦片被组合以形成控制单元，每个控制单元包括一对电极和至少一个永磁体。 一对电极耦合到电流源，该电流源偏置电极以使电流从正电极（阳极）流过其中浸入电池电极的导电流体流向负电极（阴极）。 电流源可以被时间复用以更好地控制相邻电极之间的电流的方向。 永磁体产生磁场，其被定位成与磁场最强的电流相互作用，从而产生强的切向洛伦兹力。 这种力影响导流流体在控制瓦片边界附近的流动，例如当流体流过瓦片表面时减少流体的阻力。 本发明可以用于例如在远洋船的船体内，以减少通过船体表面的海水的阻力。

公开(公告)号：US5779189A

公开(公告)日：1998-07-14

申请号：US619831

申请日：1996-03-19

申请人： Jeffrey William Hamstra ,  Thomas Gerard Sylvester

发明人： Jeffrey William Hamstra ,  Thomas Gerard Sylvester

IPC分类号： B64C7/00 ,  B64C21/00 ,  B64D33/02

CPC分类号： B64C21/00 ,  B64C7/00 ,  B64D33/02 ,  B64D2033/026 ,  Y02T50/166 ,  Y10T137/0536

摘要： A diverterless engine inlet system that integrates a "bump" surface with a forward swept, aft-closing cowl to divert substantially all of the boundary layer air from the inlet. The bump includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The cowl couples to the body of the aircraft to form the remaining surfaces of the inlet and closes against the body of the aircraft at the aft-most points of the inlet opening. The bump and the cowl work together to divert low energy boundary layer air from the inlet during aircraft operation, thus eliminating the requirement for a boundary layer diverter. The diverterless inlet provides a lower cost, reduced complexity air induction system that can be used on a supersonic aircraft engine.

摘要翻译： 一种无差别的发动机进气系统，其将“凸起”表面与前扫掠的后关闭整流罩相集合，以从入口基本上转移所有边界层空气。 凸块包括从飞行器主体向外凸起的等熵压缩表面，以形成入口内表面的一部分。 整流罩耦合到飞机的主体以形成入口的剩余表面，并且在入口开口的最后部分处关闭飞机的主体。 碰撞和整流罩在飞行器运行期间一起工作，从入口转移低能量边界层空气，从而消除了对边界层分流器的要求。 无歧管进气口提供了更低成本，更低复杂度的空气感应系统，可用于超音速飞机发动机。

公开(公告)号：US5320309A

公开(公告)日：1994-06-14

申请号：US986257

申请日：1992-12-07

申请人： Daniel M. Nosenchuck ,  Garry L. Brown

发明人： Daniel M. Nosenchuck ,  Garry L. Brown

IPC分类号： B63B1/34 ,  B64C21/00 ,  F15D1/12 ,  F28F13/02

CPC分类号： B64C21/00 ,  F28F13/02 ,  B64C2230/12 ,  F05D2270/172 ,  Y02T50/166

摘要： The boundary layer of a fluid travelling in a mean-flow direction relative to a surface of a wall of a body is controlled by generating in a near-wall region of the flow a magnetic field B having flux lines parallel to the surface of the wall and an electric current density J traversing the magnetic flux lines in the fluid. An electrolyte or other conductivity-enhancing material is introduced into the flow to provide an electrical conductivity gradient in the near-wall region. The magnetic field B and the electric current density J create in the fluid a force J.times.B having a component normal to the surface of the wall that because of the increased conductivity gradient near the surface can stabilize or destabilize flow in the boundary layer. Numerous aspects of the fluid flow and its interaction with the body can thus be controlled. As examples, shear stress in the fluid at the wall can be decreased, with a corresponding reduction in viscous drag, the characteristics of the acoustic and pressure fields in the fluid surrounding the body can be controlled to reduce noise and fatigue, and boundary layer separation can be inhibited or induced.

摘要翻译： 通过在流体的近壁区域中产生具有平行于所述流体的表面的磁通和上杠B的通量线来控制流体在平均流动方向上相对于身体壁表面行进的边界层 壁和电流密度和上限和J横穿流体中的磁通线。 将电解质或其它导电性增强材料引入流中以在近壁区域中提供导电梯度。 磁场和上升和下降B以及电流密度和上限＆J在流体中产生一个与上述表面垂直的分量的力和上升与上升和下降B，由于表面附近的增加的电导率梯度可以稳定或不稳定边界的流动 层。 因此可以控制流体流动的许多方面及其与身体的相互作用。 作为示例，可以减少壁中的流体中的剪切应力，同时相应地减小粘性阻力，可以控制围绕身体的流体中的声学和压力场的特性以减少噪声和疲劳，并且边界层分离 可以被抑制或诱导。

公开(公告)号：US4836473A

公开(公告)日：1989-06-06

申请号：US58511

申请日：1987-06-05

申请人： Felix Aulehla ,  Hans-Peter Genssler

发明人： Felix Aulehla ,  Hans-Peter Genssler

IPC分类号： B64C21/00 ,  B64C23/06

CPC分类号： B64C23/06 ,  B64C21/00 ,  Y02T50/162 ,  Y02T50/166

摘要： The pressure drag on the skin of an aircraft is reduced by rigidly securing boundary layer influencing members to the skin of the aircraft, including the wings, the elevantor and fin/rudder assemblies, and the body near the tail end. These members may be vortex generators and boundary layer diverters and are always located in the attached flow. In addition, if the members are placed upstream of any air intakes, especially flush air intakes, the air intake efficiency is also improved. The influencing members have an effective height above the surface corresponding, at the most, to the displacement thickness portion of the boundary layer.

摘要翻译： 通过将边界层影响构件刚性地固定到飞行器的皮肤上，包括机翼，前翼和翼/舵组件以及尾端附近的身体，使飞机皮肤上的压力减小。 这些构件可以是涡流发生器和边界层转向器，并且总是位于附接的流中。 另外，如果这些构件放置在任何进气口的上游，特别是冲洗进气口，进气效率也得到提高。 所述影响部件具有在与所述边界层的位移厚度部分最相对应的表面上的有效高度。

公开(公告)号：US4555079A

公开(公告)日：1985-11-26

申请号：US566753

申请日：1983-12-28

申请人： John K. Harvell ,  Milton E. Franke

发明人： John K. Harvell ,  Milton E. Franke

IPC分类号： B64C21/00 ,  B64C21/04

CPC分类号： B64C21/00 ,  Y02T50/166 ,  Y10S415/914

摘要： A circulation controlled airfoil has a body structure with leading and trailing ends and upper and lower surfaces extending therebetween, and a cylindrical member disposed along the trailing end of the body structure between the upper and lower surfaces thereof so as to form a rounded, blunt trailing edge surface on the airfoil. A first blowing jet slot is defined between the outer surface of the cylindrical member and the trailing end of the body structure adjacent its upper surface. A second blowing jet slot is defined in a tubular wall of the cylindrical member. The latter member can be rotated to vary the distance of the second jet slot from the first jet slot and thereby adjust the point of separation of air flow along the airfoil from the outer surface of the blunt trailing edge surface formed by the cylindrical member. In such manner the lift generated by the airfoil can be optimized by providing blowing that is specifically tailored to given flight conditions. Also, the separate plenums are provided for supplying air flow to the respective jet slots.

摘要翻译： 循环受控的翼型件具有主体结构，其具有前端和后端以及在其之间延伸的上表面和下表面;以及圆柱形构件，其沿主体结构的后端设置在其上表面和下表面之间，以形成圆形，钝的尾随 翼面上的边缘表面。 第一吹气喷嘴狭缝限定在圆柱形构件的外表面和身体结构的靠近其上表面的后端之间。 在筒状构件的管状壁中限定第二喷射喷口。 可以旋转后一个构件以改变第二喷射狭缝与第一喷射狭缝的距离，从而从由圆柱形构件形成的钝的后缘表面的外表面沿翼型调节空气流的分离点。 以这种方式，可以通过提供专门针对给定的飞行条件的吹风来优化由翼型产生的升力。 而且，单独的通气室被设置用于将空气流供应到各个喷射槽。