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公开(公告)号：US09151581B2
公开(公告)日：2015-10-06
申请号：US13164730
申请日：2011-06-20
Applicant: Jahangir S. Rastegar , Thomas Spinelli
Inventor： Jahangir S. Rastegar , Thomas Spinelli
CPC classification number: F42B10/661 , F42B10/668
Abstract: A method for providing actuation thrust to a projectile. The method including: providing two or more individual actuators movably disposed in a stack housing, each of the two or more individual actuators being separated by a separation layer; accelerating exhaust from the two or more individual actuators with an accelerating nozzle having at least a convergent section terminating at a throat; and maintaining a constant volume in the accelerating nozzle after actuation of each of the two or more individual actuators.
Abstract translation: 一种用于向射弹提供致动推力的方法。 该方法包括：提供可移动地设置在堆叠壳体中的两个或更多个单个致动器，两个或更多个单个致动器中的每一个由分离层分隔开; 加速具有加速喷嘴的两个或更多个单独致动器的排气，所述加速喷嘴至少具有终止于喉部的收敛部分; 并且在致动所述两个或更多个单个致动器中的每个致动器之后，在所述加速喷嘴中保持恒定的体积。
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2.发明授权公开(公告)号：US08190305B1
公开(公告)日：2012-05-29
申请号：US12557599
申请日：2009-09-11
Applicant: Troy S. Prince , Richard Kolacinski , Mehul Patel
Inventor： Troy S. Prince , Richard Kolacinski , Mehul Patel
Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft. The active flow control device or activatable flow effectors of these various embodiments create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.
Abstract translation: 本发明涉及具有分级，模块化，闭环流量控制系统的导弹或飞机，更具体地涉及具有用于增强空气动力学控制，机动性和稳定性的流量控制系统的飞机或导弹。 本发明还涉及一种操作流量控制系统的方法。 本发明的流量控制系统的各种实施例涉及不同的元件，包括流量传感器，主动流量控制装置或可激活流动效应器以及具有闭环控制架构的逻辑装置。 这些各种实施例的传感器用于估计或确定导弹或飞行器的各种表面上的流动状况。 这些各种实施例的主动流量控制装置或可激活的流动效应器在沿着导弹或飞行器的各种空气动力学表面的不同点处产生按需流动干扰，优选微扰动，以实现期望的稳定性或机动性效果。 逻辑器件嵌入了分层控制结构，允许在流表面进行快速，实时的控制。
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公开(公告)号：US07658337B2
公开(公告)日：2010-02-09
申请号：US11354879
申请日：2006-02-16
Applicant: Christopher Stuart Avenell
Inventor： Christopher Stuart Avenell
IPC: B63H25/46
CPC classification number: F02K1/002 , B64C15/02 , B64C21/04 , F02K1/006 , F02K1/28 , F02K9/82 , F05D2250/314 , F05D2270/18 , F15D1/08 , F42B10/668 , Y02T50/166
Abstract: A fluid vectoring nozzle comprises flow vectoring means suitable for selectively producing a fluid dynamic throat in the nozzle in a plane oblique to the axis of the nozzle, such that in operation fluid flow passing through the throat is rotated about an axis parallel to and coincident with the plane of the throat. That is to say, the present invention comprises flow vectoring means suitable for selectively producing a fluid dynamic throat in the nozzle in a plane oblique to the axis of the nozzle, such that, in operation, fluid passing through the fluid dynamic throat is turned towards an angle perpendicular to the plane of the throat. Fluid injection means are provided to inject a control fluid into the nozzle through a perforate region provided in at least one nozzle wall, thereby generating a fluid dynamic restriction which initiates the formation of the fluid dynamic throat.
Abstract translation: 流体矢量喷嘴包括适于在倾斜于喷嘴轴线的平面中选择性地在喷嘴中产生流体动态喉部的流动矢量化装置，使得在操作中，通过喉部的流体流围绕平行于并且与 喉咙的飞机。 也就是说，本发明包括适于在倾斜于喷嘴的轴线的平面中选择性地在喷嘴中产生流体动态喉部的流动矢量装置，使得在操作中，流过流体动态喉部的流体转向 垂直于喉咙平面的角度。 提供流体注射装置以通过设置在至少一个喷嘴壁中的穿孔区域将控制流体喷射到喷嘴中，从而产生流体动力学限制，其启动流体动态喉部的形成。
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4.发明授权Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators 有权用等离子执行器控制飞机，导弹，弹药和地面车辆的方法公开(公告)号：US07624941B1
公开(公告)日：2009-12-01
申请号：US11415535
申请日：2006-05-02
Applicant: Mehul Patel , Tom Corke
Inventor： Mehul Patel , Tom Corke
IPC: F41G7/00
CPC classification number: B64C23/005 , B62D35/007 , B64C2230/12 , F42B10/38 , F42B10/40 , F42B10/668 , Y02T50/166
Abstract: The present invention relates to a method of controlling an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly to controlling fluid flow across their surfaces or other surfaces, which would benefit from such a method. The method includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and more particularly to the method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control provides a means for reducing aircraft, missile's, munition's and ground vehicle's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.
Abstract translation: 本发明涉及一种利用等离子体致动器来控制飞机，导弹，弹药或地面车辆的方法，更具体地涉及控制流过其表面或其它表面的流体流，这将从这种方法中受益。 该方法包括为了控制在飞机，导弹或地面车辆的控制表面上的气流分离的空气动力学等离子体致动器的设计，并且更具体地涉及为此目的确定等离子体致动器的调制频率的方法 对这些车辆进行流体流量控制。 各种实施例提供了增加飞机，导弹，弹药和地面车辆的效率的步骤。 流量控制方法为减少飞机，导弹，弹药和地面车辆的电力需求提供了一种手段。 这些方法还提供了使用低功率无铰链等离子体致动器装置的空气动力学控制的替代方法。
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5.发明授权Reconfigurable porous technology for fluid flow control and method of controlling flow 失效用于流体流量控制的可重构多孔技术和控制流量的方法公开(公告)号：US06866233B2
公开(公告)日：2005-03-15
申请号：US10336113
申请日：2003-01-03
Applicant: Mehul P. Patel , Jack M DiCocco , Troy Prince
Inventor： Mehul P. Patel , Jack M DiCocco , Troy Prince
CPC classification number: F16K99/0001 , B64C21/025 , B64C21/08 , B64C2230/06 , B64C2230/22 , F15C5/00 , F15D1/12 , F16K99/0011 , F16K99/0051 , F16K2099/0082 , F42B10/668 , Y02T50/166
Abstract: The present invention relates to a reconfigurable porous technology for fluid flow control system and more particularly to reconfigurable porosity fluid flow control system for vehicles such as aircraft, missiles, ground and water vehicles to improve the performance of such vehicles. The present invention further relates to a method of operating the reconfigurable fluid flow control system.In one embodiment, the present invention includes a reconfigurable porosity system for fluid flow control on the surface of an aircraft, missile, water-craft or ground vehicle comprising a porous outer skin comprising individual pores; individually addressable valves corresponding and connected to the individual pores for opening and closing the pores; and a pneumatic system for connecting the pores wherein fluid from a high pressure area of the porous outer skin can be directed to a low pressure area of the porous outer skin by opening and closing the individually addressable valves. In another embodiment, the present invention includes a method of fluid flow control using reconfigurable porosity.
Abstract translation: 本发明涉及一种用于流体流动控制系统的可重构多孔技术，更具体地涉及用于诸如飞机，导弹，地面和水车辆的车辆的可重构孔隙度流体流量控制系统，以改善这种车辆的性能。 本发明还涉及一种操作可重构流体流动控制系统的方法。在一个实施例中，本发明包括一种用于在飞机，导弹，水上工艺或地面车辆的表面上进行流体流动控制的可重新配置的孔隙系统，其包括 包含单个孔的多孔外皮; 对应并连接到用于打开和关闭孔的各个孔的单独可寻址阀; 以及用于连接孔的气动系统，其中来自多孔外皮的高压区域的流体可以通过打开和关闭单独可寻址的阀而被引导到多孔外皮的低压区域。 在另一个实施例中，本发明包括使用可重新配置的孔隙率的流体流量控制的方法。
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Patent Agency Ranking
公开(公告)号：US20110179964A1
公开(公告)日：2011-07-28
申请号：US12870843
申请日：2010-08-29
Applicant: Jahangir S. Rastegar , Thomas Spinelli
Inventor： Jahangir S. Rastegar , Thomas Spinelli
IPC: F42B15/00
CPC classification number: F42B10/661 , F42B10/668
Abstract: A ring portion including: a ring body; and one or more actuators formed therein for providing thrust to a projectile and configured for fastening to a shell of an airborne device to form a portion of the shell. The airborne device can be a projectile.
Abstract translation: 环形部分，包括：环体; 以及形成在其中的一个或多个致动器，用于向射弹提供推力并且构造成用于紧固到机载装置的壳体以形成壳体的一部分。 机载装置可以是射弹。
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7.发明授权Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators 有权用等离子执行器控制飞机，导弹，弹药和地面车辆的方法公开(公告)号：US07954768B1
公开(公告)日：2011-06-07
申请号：US12604903
申请日：2009-10-23
Applicant: Mehul Patel , Thomas C. Corke
Inventor： Mehul Patel , Thomas C. Corke
CPC classification number: B64C23/005 , B62D35/007 , B64C2230/12 , F42B10/38 , F42B10/40 , F42B10/668 , Y02T50/166
Abstract: A method of controlling an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly of controlling fluid flow across their surfaces or other surfaces which would benefit from such a method, includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and a method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. Various embodiments provide steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control reduces the power requirements of the aircraft, missile, munition or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.
Abstract translation: 使用等离子体致动器控制飞机，导弹，弹药或地面车辆的方法，更具体地说是控制流过其表面或将受益于这种方法的其它表面的流体流动的方法包括设计空气动力学等离子体致动器，目的在于 控制飞机，导弹或地面车辆的控制表面上的气流分离，以及为了在这些车辆上进行流体流动控制的目的，确定等离子体致动器的调制频率的方法。 各种实施例提供了增加飞机，导弹，弹药和地面车辆的效率的步骤。 流量控制的方法降低了飞机，导弹，弹药或地面车辆的电力需求。 这些方法还提供使用低功率无铰链等离子体致动器装置的替代空气动力学控制。
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公开(公告)号：US06883747B2
公开(公告)日：2005-04-26
申请号：US10402644
申请日：2003-03-28
Applicant: Joseph A. Ratkovic , Allan J. Brockstein , Robert J. Buchler
Inventor： Joseph A. Ratkovic , Allan J. Brockstein , Robert J. Buchler
CPC classification number: F41G7/36 , F41G7/346 , F42B10/64 , F42B10/663 , F42B10/668 , F42B15/01 , G01C21/165
Abstract: A projectile guidance system without gyros in which the projectile has an orthogonal body coordinate system. The projectile has a triax of accelerometers providing x, y and z acceleration data measured along the x, y and z axes respectively. A GPS antenna and receiver means provides onboard GPS position and velocity data in earth referenced navigational coordinates. A computer and program means stores and accesses time indexed GPS position and GPS velocity data and transforms x, y and z axis acceleration data from body to navigation coordinates. The program means is responsive to corresponding time indexed acceleration data and to GPS velocity and position data for calculating and outputting an estimated projectile roll, pitch and yaw angle via optimal smoothing techniques with respect to local level for each time index iteration of present position to a flight control system, which actuates a divert propulsion system for guiding the projectile to a predetermined location.
Abstract translation: 没有陀螺仪的射弹引导系统，其中射弹具有正交身体坐标系。 射弹具有三轴加速度计，提供沿x，y和z轴测量的x，y和z加速度数据。 GPS天线和接收器装置提供地面参考导航坐标中的GPS位置和速度数据。 计算机和程序意味着存储和访问时间索引的GPS位置和GPS速度数据，并将x，y和z轴加速度数据从身体转换为导航坐标。 程序装置响应相应的时间索引加速度数据和GPS速度和位置数据，用于通过针对当前位置的每次时间索引迭代的局部级别的最优平滑技术来计算和输出估计的射弹卷，俯仰角和偏航角 飞行控制系统，其驱动用于将射弹引导到预定位置的转向推进系统。
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公开(公告)号：US3636710A
公开(公告)日：1972-01-25
申请号：US3636710D
申请日：1965-10-22
Applicant: THIOKOL CHEMICAL CORP
Inventor： LOVINGHAM JOSEPH J , KIRCHER HARTMANN J
CPC classification number: F02K9/97 , F02K9/62 , F02K9/80 , F02K9/95 , F02K9/972 , F05D2240/1281 , F42B10/668
Abstract: 1. A rocket engine comprising, in combination, a manifold for introducing propellants into a combustion chamber, a wall having a hemispherical deflecting surface fixed to an intermediate portion of said manifold and extending aft therearound, a conical combustion chamber fixed to and communicating with the aft end of said manifold and having its larger open end positioned adjacent but spaced from said surface to define an expansion exhaust nozzle and throat therewith, apertures formed in the apex of said chamber for bleeding combustion gases therethrough, and means for deflecting a portion of said gases to vary the thrust vector of said engine in operation.
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公开(公告)号：US3482404A
公开(公告)日：1969-12-09
申请号：US3482404D
申请日：1962-12-18
Applicant: THIOKOL CHEMICAL CORP
Inventor： LOVINGHAM JOSEPH J , KIRCHER HARTMANN J
CPC classification number: F42B10/668 , F02K9/62 , F02K9/80 , F02K9/95 , F02K9/97 , F05D2240/1281
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