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    • 61. 发明申请
    • Hierarchical closed-loop flow control system for aircraft, missiles and munitions
    • 飞机,导弹和弹药的分层闭环流量控制系统
    • US20150060593A1
    • 2015-03-05
    • US14010909
    • 2013-08-27
    • Troy PrinceRichard KolacinskiMehul Patel
    • Troy PrinceRichard KolacinskiMehul Patel
    • F41G7/00G05D1/00F42B15/01
    • B64C21/00B64C5/12F41G7/00F42B10/14F42B10/60F42B10/62F42B15/01G05D1/0088
    • 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.”
    • 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。
    • 63. 发明申请
    • SYSTEM AND METHOD FOR GENERATING MUSIC VIDEOS FROM SYNCHRONIZED USER-VIDEO RECORDED CONTENT
    • 用于从同步用户视频记录内容生成音乐视频的系统和方法
    • US20130163963A1
    • 2013-06-27
    • US13333321
    • 2011-12-21
    • Cory CroslandMarcel EsserMichael FiedelMehul Patel
    • Cory CroslandMarcel EsserMichael FiedelMehul Patel
    • G11B27/02H04N5/93
    • H04N9/8211G11B27/10G11B27/34
    • A method for automatically generating a master music video comprising a plurality of user-generated videos synchronized against a segment of an audio track. The method includes dividing an audio track into a plurality of segments. A user-recorded video is automatically selected for each of the plurality of segments, where each selected user-recorded video includes a video recording of a user synchronized against an audio clip of a unique one of the plurality of segments. The method further includes concatenating the user-recorded videos in a sequence and into a master music video featuring the user-recorded videos all placed in synch against the entire audio track such that playback of the plurality of segments associated with the user-recorded videos in the sequence corresponds to an original sequence of the audio track in its entirety.
    • 一种用于自动生成主音乐视频的方法,包括与音轨的段同步的多个用户生成的视频。 该方法包括将音轨划分成多个段。 对于多个片段中的每一个,自动选择用户录制的视频,其中每个所选择的用户记录视频包括与多个片段中的唯一片段的音频片段同步的用户的视频记录。 该方法还包括将用户记录的视频按顺序并入主要音乐视频,该主音乐视频的特征在于所有用户记录的视频全部与整个音轨同步,使得与用户录制的视频相关联的多个片段的回放 该序列对应于整个音轨的原始序列。
    • 64. 发明授权
    • Hierarchical closed-loop control system for aircraft, missiles and munitions
    • 用于飞机,导弹和弹药的分层闭环控制系统
    • US08190305B1
    • 2012-05-29
    • US12557599
    • 2009-09-11
    • Troy S. PrinceRichard KolacinskiMehul Patel
    • Troy S. PrinceRichard KolacinskiMehul Patel
    • B64C13/00F41G7/00G01C23/00
    • G05D1/107F42B10/38F42B10/40F42B10/42F42B10/668F42B15/01
    • 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.
    • 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。
    • 65. 发明授权
    • Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators
    • 用等离子执行器控制飞机,导弹,弹药和地面车辆的方法
    • US07624941B1
    • 2009-12-01
    • US11415535
    • 2006-05-02
    • Mehul PatelTom Corke
    • Mehul PatelTom Corke
    • F41G7/00
    • B64C23/005B62D35/007B64C2230/12F42B10/38F42B10/40F42B10/668Y02T50/166
    • 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.
    • 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。
    • 70. 发明授权
    • System and method for decoding optical codes read by an imager-based optical code reader
    • 用于解码由基于成像器的光学代码读取器读取的光学代码的系统和方法
    • US07097102B2
    • 2006-08-29
    • US10901623
    • 2004-07-29
    • Mehul PatelRobert James Pang
    • Mehul PatelRobert James Pang
    • G06K7/10
    • G06K7/10722G06K7/10752
    • A system and method for reading an optical code is provided. The method comprises the steps of imaging at least one target, including acquiring and processing image data corresponding to a series of at least one frame; storing image data corresponding to respective acquired frames of the at least one frame, including at least image data corresponding to a current frame (Frame(N)) and image data corresponding to a previous frame (Frame(N−1)); receiving an actuation signal during Frame(N) indicating initiation of a read operation; retrieving at least a portion of the image data corresponding to Frame (N−1); and performing a decode operation on the retrieved image data.
    • 提供了一种用于读取光学代码的系统和方法。 该方法包括对至少一个目标进行成像的步骤,包括获取和处理与一系列至少一个帧相对应的图像数据; 存储对应于至少一帧的各个获取的帧的图像数据,至少包括对应于当前帧(帧(N))的图像数据和对应于先前帧(帧(N-1))的图像数据; 在指示启动读取操作的帧(N)期间接收致动信号; 检索对应于帧(N-1)的图像数据的至少一部分; 并对所检索的图像数据执行解码操作。