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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

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。

4. 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。

5. 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.

6. 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。

7. 发明授权

US09429400B1 Flow control device and method for aircraft and missile forebody 有权
标题翻译：飞机和导弹前体的流量控制装置和方法
公开(公告)号：US09429400B1
公开(公告)日：2016-08-30
申请号：US12615218
申请日：2009-11-09
申请人： Zak Sowle , Srikanth Vasudevan , Russell Stucke , Frederick J. Lisy , Robert N. Schmidt
发明人： Zak Sowle , Srikanth Vasudevan , Russell Stucke , Frederick J. Lisy , Robert N. Schmidt
IPC分类号： F42B10/02 , F42B10/14
CPC分类号： F42B10/02 , B64C5/12 , F42B10/14 , F42B10/60 , F42B10/62 , F42B10/64 , F42B15/01 , G05D1/0816
摘要： A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization utilizes various types of sensors and various types of activatable flow effectors to maneuver the aircraft or missile with the help of a control system. A method of operating the flow control system is also disclosed.
摘要翻译：前身流量控制系统，更具体地，用于增强机动性和稳定性的飞行器或导弹流量控制系统利用各种类型的传感器和各种类型的可激活流动效应器来借助控制系统来操纵飞行器或导弹。还公开了一种操作流量控制系统的方法。

8. 发明授权

US07032302B1 Dry physiological recording device 有权
标题翻译：干生理记录装置
公开(公告)号：US07032302B1
公开(公告)日：2006-04-25
申请号：US10923648
申请日：2004-08-20
申请人： Robert N. Schmidt , Frederick J. Lisy , Gerard G. Skebe , Troy S. Prince
发明人： Robert N. Schmidt , Frederick J. Lisy , Gerard G. Skebe , Troy S. Prince
IPC分类号： H01R43/00
CPC分类号： A61B5/685 , A61B5/04025 , A61B5/411 , Y10T29/49117
摘要： The present invention relates to a dry physiological recording electrode that can be used without skin preparation or the use of electrolytic gels. The dry physiological recording electrode comprising a substrate having an upper and a lower surface, and at least one penetrator(s) protruding from the upper surface of the substrate. The penetrator(s) is capable of piercing through the stratum corneum or outer layer of the skin, and transmitting an electric potential from the lower layers of the epidermis through the penetrator(s) which can be measured, or detecting agents from the lower layers of the epidmermis primarily the stratum germinativum layer. At least one epidermis stop may be provided resulting in the formation of detritus troughs interposed between adjacent penetrator(s) and epidermis stops. The present invention also includes a method of sensing biopotentials in the skin.
摘要翻译：本发明涉及无需皮肤制备或使用电解凝胶即可使用的干性生理记录电极。干燥的生理记录电极包括具有上表面和下表面的基底和至少一个从基底的上表面突出的穿透器。穿透器能够刺穿皮肤的角质层或外层，并且通过可测量的穿透器或从下层检测试剂将表面的下层透过电位，的皮肤主要是生殖层。可以提供至少一个表皮停止物，导致形成插入在相邻穿透器和表皮停止物之间的碎屑槽。本发明还包括一种感测皮肤中生物电位的方法。

9. 发明授权

US07032301B1 Dry physiological recording electrode 有权
公开(公告)号：US07032301B1
公开(公告)日：2006-04-25
申请号：US10874075
申请日：2004-06-22
申请人： Robert N. Schmidt , Frederick J. Lisy , Gerard G. Skebe , Troy S. Prince
发明人： Robert N. Schmidt , Frederick J. Lisy , Gerard G. Skebe , Troy S. Prince
IPC分类号： H01R43/00
CPC分类号： A61B5/0408 , A61B5/04025 , A61B5/0478 , A61B5/0492 , A61B5/411 , A61B5/685 , A61B2562/125 , Y10T29/49117
摘要： The present invention relates to a dry physiological recording electrode that can be used without skin preparation or the use of electrolytic gels. The dry physiological recording electrode comprising a substrate having an upper and a lower surface, and at least one penetrator(s) protruding from the upper surface of the substrate. The penetrator(s) is capable of piercing through the stratum corneum or outer layer of the skin, and transmitting an electric potential from the lower layers of the epidermis through the penetrator(s) which can be measured, or detecting agents from the lower layers of the epidmermis primarily the stratum germinativum layer. At least one epidermis stop may be provided resulting in the formation of detritus troughs interposed between adjacent penetrator(s) and epidermis stops. The present invention also includes a method of sensing biopotentials in the skin.

10. 发明授权

US6105904A Deployable flow control device 失效
标题翻译：可部署流量控制装置
公开(公告)号：US6105904A
公开(公告)日：2000-08-22
申请号：US50303
申请日：1998-03-30
申请人： Frederick J. Lisy , Robert N. Schmidt
发明人： Frederick J. Lisy , Robert N. Schmidt
IPC分类号： B64C3/58 , B64C23/06
CPC分类号： B64C3/58 , B64C23/06 , Y02T50/162
摘要： A deployable flow control device for a flow surface over which fluid having a fluid boundary layer flows which fluid boundary layer exhibits certain dynamics is disclosed. The deployable flow control device comprises a flow effector which is movably attached to a housing which is attachable, either initially or retrofitably, to a flow surface. The flow effector can position in a modular sub-housing removably attachable to the housing. The flow effector is deployed into and retracted out of the boundary layer on the flow surface and thereby controls the boundary layer dynamics. Devices (including devices utilizing a sealable, flexible element) operably connect to the flow effector and deploy and retract it. The sealable, flexible element has two elastic states defined as quiescent and deformed such that, when the sealable, flexible element is utilized, the flow effector is deployed into and retracted out of the fluid boundary layer based upon the elastic state of the sealable, flexible element.
摘要翻译：公开了一种用于流动表面的可展开的流量控制装置，流体边界层流过具有流体边界层的流体，流体边界层表现出一定的动态。可展开的流量控制装置包括流动执行器，该流动执行器可移动地附接到壳体，该壳体可以初始地或可更新地附接到流动表面。流动执行器可以位于可拆卸地附接到壳体的模块化子壳体中。流动执行器部署到流动表面上的边界层中并从中缩出，从而控制边界层动力学。设备（包括使用可密封的柔性元件的设备）可操作地连接到流动执行器并且部署和收回它。可密封的柔性元件具有两个弹性状态，这些弹性状态被定义为静止和变形，使得当使用可密封的柔性元件时，基于可密封，柔性的弹性状态将流动效应器展开到流体边界层中并从流体边界层缩回元件。

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