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1.发明授权公开(公告)号：US08548650B1
公开(公告)日：2013-10-01
申请号：US13455182
申请日：2012-04-25
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 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.
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。
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公开(公告)号：US10974812B1
公开(公告)日：2021-04-13
申请号：US16166230
申请日：2018-10-22
Applicant: Troy S Prince , Richard Kolacinski , Mehul Patel
Inventor： Troy S Prince , Richard Kolacinski , Mehul Patel
IPC: 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
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 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.
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公开(公告)号：US09310166B2
公开(公告)日：2016-04-12
申请号：US14010909
申请日：2013-08-27
Applicant: Troy S Prince , Richard Kolacinski , Mehul Patel
Inventor： Troy S Prince , Richard Kolacinski , Mehul Patel
IPC: F42B10/02 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , F41G7/00 , B64C5/12 , G05D1/00 , F42B10/00
CPC classification number: B64C21/00 , B64C5/12 , F41G7/00 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , G05D1/0088
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.
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Patent Agency Ranking
公开(公告)号：US10139209B1
公开(公告)日：2018-11-27
申请号：US15057211
申请日：2016-03-01
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 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.
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5.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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6.发明申请Hierarchical closed-loop flow control system for aircraft, missiles and munitions 审中-公开飞机，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
Applicant: Troy Prince , Richard Kolacinski , Mehul Patel
Inventor： Troy Prince , Richard Kolacinski , Mehul Patel
CPC classification number: B64C21/00 , B64C5/12 , F41G7/00 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , G05D1/0088
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, 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.”
Abstract translation: 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。
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7.发明授权Hierarchical closed-loop flow control system for aircraft, missiles and munitions 有权用于飞机，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
Applicant: Troy Prince , Richard Kolacinski , Mehul Patel
Inventor： Troy 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：US10112700B1
公开(公告)日：2018-10-30
申请号：US13185508
申请日：2011-07-19
Applicant: Matthew C. Birch , Richard Kolacinski
Inventor： Matthew C. Birch , Richard Kolacinski
Abstract: A multi-mode mobility micro air vehicle (MAV) accomplishes ground locomotion by hopping on a retractable leg. The hopping is translated into forward locomotion when aided by the forward thrust of propellers, and the orientation of locomotion is directed by aerodynamic controls like ailerons, rudders, stabilators, or plasma actuators. The foot of the leg is convexly curved so as to produce hopping that is statically and passively dynamically stable. The MAV is also equipped for vertical takeoff so that it may conduct multiple idling missions in sequence and may return home for recovery and reuse. Structural integration of power storage and photovoltaic generation systems into the aerodynamic surface of the MAV lightens the weight of the MAV while also providing a strong structure and permitting the MAV to harvest its own energy. The MAV may autonomously conduct surveillance missions and/or serve as a flying platform for self-healing sensor or communications networks, especially when multiple MAVs are used in concert.
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