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1. 发明授权

US06685143B1 Aircraft and missile forebody flow control device and method of controlling flow 有权
标题翻译：飞机和导弹前身流量控制装置及流量控制方法
公开(公告)号：US06685143B1
公开(公告)日：2004-02-03
申请号：US10336117
申请日：2003-01-03
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： B64C2306
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 a forebody flow control system and more particularly to aircraft or missile flow control system 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 deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, 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 deployable flow effector based on at least in part the signal of the at least one sensor.
摘要翻译：本发明涉及一种前身体流量控制系统，更具体地涉及用于在高攻角下提高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，本发明包括一种包括后身体和前体的导弹或飞机; 导弹或飞机前体上至少有一个可部署的流动执行器; 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可展开的流动效应器。

2. 发明授权

US07226015B1 Aircraft and missile forebody flow control device and method of controlling flow 有权
标题翻译：飞机和导弹前身流量控制装置及流量控制方法
公开(公告)号：US07226015B1
公开(公告)日：2007-06-05
申请号：US10766225
申请日：2004-01-28
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： B64C5/10 , 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 a forebody flow control system and more particularly to aircraft or missile flow control system 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 deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, 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 deployable flow effector based on at least in part the signal of the at least one sensor.
摘要翻译：本发明涉及一种前身体流量控制系统，更具体地涉及用于在高攻角下提高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; 导弹或飞机前体上至少有一个可部署的流动执行器; 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可展开的流动效应器。

3. 发明授权

US10137979B1 Aircraft and missile forebody flow control device and method of controlling flow 有权
公开(公告)号：US10137979B1
公开(公告)日：2018-11-27
申请号：US13151640
申请日：2011-06-02
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： B64C5/12 , B64C23/06 , F42B15/01 , F42B10/64
摘要： A forebody flow control system and more particularly an aircraft or missile flow control system 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 deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.

4. 发明授权

US07334760B1 Flow control device and method of controlling flow 有权
标题翻译：流量控制装置及流量控制方法
公开(公告)号：US07334760B1
公开(公告)日：2008-02-26
申请号：US11523161
申请日：2006-09-19
申请人： Frederick J. Lisy , Mohammed Modarreszadah , Mehul P. Patel , Jack M. DiCocco , Reed Carver , Robert N. Schmidt , Troy Prince
发明人： Frederick J. Lisy , Mohammed Modarreszadah , Mehul P. Patel , Jack M. DiCocco , Reed Carver , Robert N. Schmidt , Troy Prince
IPC分类号： B64C13/16
CPC分类号： B64C23/06 , Y02T50/162
摘要： The present invention relates to a flow control device and more particularly to reactive self-contained modular flow control device with deployable flow effectors. The present invention further relates to a method of operating the flow control device.One embodiment of the present invention includes a method of controlling air flow across a surface of an aircraft under certain flight conditions comprising the steps of sensing fluid separation from the surface by measuring the pressure on the surface; determining a standard deviation of the pressure measurements over a period of time; and deploying a flow effector in response to the standard deviation of the pressure measurements exceeding a predetermined threshold number.
摘要翻译：本发明涉及一种流量控制装置，更具体地涉及具有可部署的流动效应器的反应式独立模块化流量控制装置。本发明还涉及一种操作流量控制装置的方法。本发明的一个实施例包括一种在某些飞行条件下控制穿过飞行器表面的空气流的方法，包括以下步骤：通过测量表面上的压力来感测与表面的流体分离; 确定一段时间内压力测量的标准偏差; 以及响应于超过预定阈值的压力测量的标准偏差部署流量效应器。

5. 发明授权

US07977615B1 Aircraft and missile forebody flow control device and method of controlling flow 有权
标题翻译：飞机和导弹前身流量控制装置及流量控制方法
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。

6. 发明授权

US06837465B2 Flow control device and method of controlling flow 失效
标题翻译：流量控制装置及流量控制方法
公开(公告)号：US06837465B2
公开(公告)日：2005-01-04
申请号：US10336114
申请日：2003-01-03
申请人： Frederick J. Lisy , Mohammed Modarreszadah , Mehul P. Patel , Jack M. DiCocco , Reed Carver , Robert N. Schmidt , Troy Prince
发明人： Frederick J. Lisy , Mohammed Modarreszadah , Mehul P. Patel , Jack M. DiCocco , Reed Carver , Robert N. Schmidt , Troy Prince
IPC分类号： B64C23/06
CPC分类号： B64C23/06 , Y02T50/162
摘要： The present invention relates to a flow control device and more particularly to reactive modular flow control device with deployable flow effectors. The present invention further relates to a method of operating the flow control device. One embodiment of the present invention includes a method of controlling air flow across a surface of an aircraft under certain flight conditions comprising the steps of sensing fluid separation from the surface by measuring the pressure on the surface; determining a standard deviation of the pressure measurements over a period of time; and deploying a flow of effector in response to the standard deviation of the pressure measurements exceeding a predetermined threshold number.
摘要翻译：流量控制装置技术领域本发明涉及一种流量控制装置，更具体地涉及具有可部署的流动效应器的反应性模块化流量控本发明还涉及一种操作流量控制装置的方法。本发明的一个实施例包括一种在某些飞行条件下控制穿过飞行器表面的空气流的方法，包括以下步骤：通过测量表面上的压力来感测与表面的流体分离; 确定一段时间内压力测量的标准偏差; 以及响应于超过预定阈值的压力测量的标准偏差来展开效应流。

7. 发明授权

US06866233B2 Reconfigurable porous technology for fluid flow control and method of controlling flow 失效
标题翻译：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
申请人： Mehul P. Patel , Jack M DiCocco , Troy Prince
发明人： Mehul P. Patel , Jack M DiCocco , Troy Prince
IPC分类号： B64C21/02 , B64C21/08 , F15C5/00 , F15D1/12 , F16K99/00 , F42B10/66
CPC分类号： F16K99/0001 , B64C21/025 , B64C21/08 , B64C2230/06 , B64C2230/22 , F15C5/00 , F15D1/12 , F16K99/0011 , F16K99/0051 , F16K2099/0082 , F42B10/668 , Y02T50/166
摘要： 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.
摘要翻译：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。

8. 发明授权

US09664485B1 Aircraft, missile, projectile, or underwater vehicle with improved control system and method of using 有权
公开(公告)号：US09664485B1
公开(公告)日：2017-05-30
申请号：US14322548
申请日：2014-07-02
申请人： Mehul P. Patel , T. Terry Ng , Paul Suchy
发明人： Mehul P. Patel , T. Terry Ng , Paul Suchy
IPC分类号： F42B10/12 , F42B15/01 , F42B19/06 , B64C9/08
CPC分类号： F42B10/12 , B64C9/02 , B64C9/08 , F42B15/01 , F42B19/06
摘要： An aircraft, missile, projectile, or underwater vehicle with an improved control system, an improved control system, or a method of maneuvering an aircraft, missile, projectile, or underwater vehicle uses control surfaces that are movable along a track. The control system on a track (or “tracked control surface”) advantageously enables the aircraft, missile, projectile, or underwater vehicle to have an unlimited number of configurations, each configuration being tailored to the specific stability or maneuverability requirements during a specific portion of the flight by adjusting the center of pressure of the aircraft, missile, projectile, or underwater vehicle relative to its center of gravity.

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