专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08548650B1 Hierarchical closed-loop control system for aircraft, missiles and munitions 有权
标题翻译：用于飞机，导弹和弹药的分层闭环控制系统
公开(公告)号：US08548650B1
公开(公告)日：2013-10-01
申请号：US13455182
申请日：2012-04-25
申请人： Troy S. Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S. Prince , Richard Kolacinski , Mehul Patel
IPC分类号： B64C13/00 , F41G7/00 , G01C23/00
CPC分类号： G05D1/107 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/668 , F42B15/01
摘要： The present invention relates to a missile or munition with a hierarchical, modular, closed-loop flow control system, more particularly to aircraft or munition with 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 involve elements including flow sensors, active flow control devices or activatable flow effectors, and logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on the surfaces of a missile or munition. The active flow control device or activatable flow effectors 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.
摘要翻译：本发明涉及具有分级，模块化，闭环流量控制系统的导弹或弹药，更具体地涉及具有用于增强的空气动力学控制，机动性和稳定性的流量控制系统的飞机或弹药。本发明还涉及一种操作流量控制系统的方法。流量控制系统的各种实施例涉及包括流量传感器，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的元件。传感器用于估计或确定导弹或弹药表面的流动状况。主动流量控制装置或可激活流动效应器沿着导弹或飞行器的各种空气动力学表面在不同点处产生按需的流动干扰，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。

2. 发明授权

US10974812B1 Hierarchical closed-loop flow control system for aircraft missiles and munitions 有权
公开(公告)号：US10974812B1
公开(公告)日：2021-04-13
申请号：US16166230
申请日：2018-10-22
申请人： Troy S Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S Prince , Richard Kolacinski , Mehul Patel
IPC分类号： B64C5/12 , F42B15/01 , B64C23/06 , F42B10/64 , G05D1/00 , F41G7/00 , B64C21/00 , G05D1/08 , F42B10/62 , F42B10/02 , F42B10/14 , F42B10/60 , F42B10/00
摘要： 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 flow control system involving different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The active flow control device or activatable flow effectors of these various embodiments are adapted to be activated, controlled, and deactivated based on signals from the sensors 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.

3. 发明授权

US09310166B2 Hierarchical closed-loop flow control system for aircraft, missiles and munitions 有权
公开(公告)号：US09310166B2
公开(公告)日：2016-04-12
申请号：US14010909
申请日：2013-08-27
申请人： Troy S Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S Prince , Richard Kolacinski , Mehul Patel
IPC分类号： F42B10/02 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , F41G7/00 , B64C5/12 , G05D1/00 , F42B10/00
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 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.

4. 发明授权

US08190305B1 Hierarchical closed-loop control system for aircraft, missiles and munitions 有权
标题翻译：用于飞机，导弹和弹药的分层闭环控制系统
公开(公告)号：US08190305B1
公开(公告)日：2012-05-29
申请号：US12557599
申请日：2009-09-11
申请人： Troy S. Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S. Prince , Richard Kolacinski , Mehul Patel
IPC分类号： B64C13/00 , F41G7/00 , G01C23/00
CPC分类号： G05D1/107 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/668 , F42B15/01
摘要： 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.
摘要翻译：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。

5. 发明授权

US10139209B1 Hierarchical closed-loop flow control system for aircraft, missiles and munitions 有权
公开(公告)号：US10139209B1
公开(公告)日：2018-11-27
申请号：US15057211
申请日：2016-03-01
申请人： Troy S Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S Prince , Richard Kolacinski , Mehul Patel
IPC分类号： F42B15/01 , B64C5/12 , F42B10/14 , F42B10/62 , F42B15/00 , F42B10/00
摘要： 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 and methods of operating the flow control system. Various embodiments of the flow control system of the present invention involve flow sensors, active flow control device or activatable flow effectors and/or logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on 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 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.

6. 发明申请

US20150060593A1 Hierarchical closed-loop flow control system for aircraft, missiles and munitions 审中-公开
标题翻译：飞机，导弹和弹药的分层闭环流量控制系统
公开(公告)号：US20150060593A1
公开(公告)日：2015-03-05
申请号：US14010909
申请日：2013-08-27
申请人： Troy Prince , Richard Kolacinski , Mehul Patel
发明人： Troy Prince , Richard Kolacinski , Mehul Patel
IPC分类号： F41G7/00 , G05D1/00 , F42B15/01
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 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, and to a method of operating the flow control system.Various embodiments 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 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 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.”
摘要翻译：本发明涉及具有分层，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的空气动力学控制，机动性和稳定性的流量控制系统的飞机或导弹，以及一种操作流量的方法控制系统。本发明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的流动效应器以及具有闭环控制架构的逻辑装置。传感器用于估计或确定导弹或飞机各个表面上的流量状况。主动流量控制装置或可激活流动效应器沿着导弹或飞行器的各种空气动力学表面在不同点处产生按需的流动干扰，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，允许在流表面快速，实时地进行控制。

7. 发明授权

US08417395B1 Hierarchical closed-loop flow control system for aircraft, missiles and munitions 有权
标题翻译：用于飞机，导弹和弹药的分层闭环流量控制系统
公开(公告)号：US08417395B1
公开(公告)日：2013-04-09
申请号：US10725266
申请日：2003-12-01
申请人： Troy Prince , Richard Kolacinski , Mehul Patel
发明人： Troy Prince , Richard Kolacinski , Mehul Patel
IPC分类号： B64C13/00 , G01C23/00 , F41G7/00
CPC分类号： G05D1/107 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/668 , F42B15/01
摘要： 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.
摘要翻译：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。

8. 发明授权

US10161742B2 Range finder 有权
公开(公告)号：US10161742B2
公开(公告)日：2018-12-25
申请号：US12963466
申请日：2010-12-08
申请人： Mehul Patel , Edward Douglas Hatton , Xinping Liu , Paul R. Poloniewicz
发明人： Mehul Patel , Edward Douglas Hatton , Xinping Liu , Paul R. Poloniewicz
IPC分类号： G01B11/06 , G01B11/25
摘要： A system and method for measuring a height of objects on a moving surface comprising providing a linear image sensor positioned transverse to a direction of travel of the moving surface, and at least one light source positioned collinear to the linear image sensor and proximate to an edge of the moving surface so that the light source projects a unique patterned light sequence across a width of the moving surface, detecting a transverse shift in a portion of the unique patterned light sequence with respect to the direction of travel of the moving surface as an object passes through the unique patterned light sequence, determining an amount of shift of the portion of the unique patterned light sequence, and determining a height of the object based on the portion of the unique patterned light sequence shift.

9. 发明申请

US20170173015A1 PRODRUGS OF HIV REVERSE TRANSCRIPTASE INHIBITORS 有权
公开(公告)号：US20170173015A1
公开(公告)日：2017-06-22
申请号：US15300405
申请日：2015-03-27
申请人： Christopher S. BURGEY , Jeffrey F. FRITZEN , Jaume BALSELLS , Mehul PATEL , Merck Sharp & Dohme Corp.
发明人： Christopher S. Burgey , Jeffrey F. Fritzen , Jaume Balsells , Mehul Patel
IPC分类号： A61K31/506 , C07D403/06 , A61K45/06
CPC分类号： A61K31/506 , A61K31/501 , A61K31/513 , A61K45/06 , C07D237/22 , C07D239/47 , C07D403/06
摘要： Compounds of Formula I are described: wherein R1 and R2 are defined herein. The compounds of Formula I are useful in the inhibition of HIV reverse transcriptase, the prophylaxis and treatment of infection by HIV, and the prophylaxis, delay in the onset or progression, and treatment of AIDS. The compounds can be employed as ingredients in pharmaceutical compositions, optionally in combination with other antivirals, immunomodulators, antibiotics or vaccines.

10. 发明授权

US09541106B1 Plasma optimized aerostructures for efficient flow control 有权
标题翻译：等离子体优化航空结构，实现有效的流量控制
公开(公告)号：US09541106B1
公开(公告)日：2017-01-10
申请号：US11710750
申请日：2007-02-26
申请人： Mehul Patel , Thomas Corke , Alan B. Cain
发明人： Mehul Patel , Thomas Corke , Alan B. Cain
IPC分类号： B64C29/00 , F15D1/00 , B64C21/00
CPC分类号： F15D1/0065 , B64C15/14 , B64C21/00 , B64C2230/12 , F15D1/0075 , Y02T50/166
摘要： The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.
摘要翻译：本发明涉及一种设计或优化用于控制飞机，导弹，弹药或汽车的等离子体致动器的控制表面的方法，更具体地涉及使用等离子致动器来控制流过其表面或其它表面的流体，这将有利于从这样的方法。各种实施例提供了增加飞机，导弹，弹药和汽车的效率的步骤。流量控制方法还为减少飞机，导弹，弹药和汽车的电力需求提供了手段。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。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式