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    Energetic detonation propulsion
    1.
    发明授权
    Energetic detonation propulsion 有权
    有力的爆震推进

    公开(公告)号：US07246483B2

    公开(公告)日：2007-07-24

    申请号：US10895777

    申请日：2004-07-21

    Applicant: Alan B. Minick ,  Benjamin Goldberg ,  Larry Knauer

    Inventor： Alan B. Minick ,  Benjamin Goldberg ,  Larry Knauer

    IPC: F02K7/02

    CPC classification number: F02K7/08 ,  F02K7/00 ,  F02K9/95

    Abstract: A propulsion system for creating a propulsive force has a combustion chamber, a pair of electrodes within the combustion chamber and a power supply attached to the electrodes to create a high voltage field within an initiation zone of the combustion chamber, and an injector for introducing a propellant, preferably in atomized form, into the high voltage field for creating the propulsive force. In a preferred embodiment of the present invention, the propellant is hydrogen peroxide. In another embodiment of the present invention, a second propellant is introduced into the combustion chamber for increasing the propulsive force.

    Abstract translation: 用于产生推进力的推进系统具有燃烧室，燃烧室内的一对电极和连接到电极的电源，以在燃烧室的起始区域内产生高电压场，以及用于引入 推进剂，优选以雾化形式进入高压场以产生推进力。 在本发明的优选实施方案中，推进剂是过氧化氢。 在本发明的另一个实施例中，将第二推进剂引入燃烧室以增加推进力。

    Staged emitter-attractor ion drive
    2.
    发明授权
    Staged emitter-attractor ion drive 有权
    分阶段发射极 - 吸引子离子驱动

    公开(公告)号：US07204078B2

    公开(公告)日：2007-04-17

    申请号：US10895775

    申请日：2004-07-21

    Applicant: Alan B. Minick ,  Benjamin Goldberg

    Inventor： Alan B. Minick ,  Benjamin Goldberg

    IPC: F03H1/00

    CPC classification number: F03H1/005 ,  B64G1/405 ,  H05H1/54

    Abstract: An ion drive system for creating a propulsion force or thrust has at least one stage having an emitter and an attractor spaced from the emitter by a gap. An ionizable dielectric media is located within the gap. The drive system further has a propellant source for introducing a propellant in the vicinity of the emitter and a power source for creating a high intensity field in the vicinity of the emitter to ionize the dielectric media and a diffused field in the vicinity of the attractor to accelerate the ions away from the emitter and thereby create a propulsive force. In a preferred embodiment, the ion drive system has a plurality of stages.

    Abstract translation: 用于产生推进力或推力的离子驱动系统具有至少一个级，其具有发射极和与发射极间隔开的吸引子。 可离子化介电介质位于间隙内。 驱动系统还具有用于在发射器附近引入推进剂的推进剂源和用于在发射器附近产生高强度场的电源，以将电介质和吸引子附近的扩散场离子化 将离子加速离开发射器，从而产生推进力。 在优选实施例中，离子驱动系统具有多个级。

    Wing enhancement through ion entrainment of media
    3.
    发明授权
    Wing enhancement through ion entrainment of media 有权
    通过介质的离子夹带来翼增强

    公开(公告)号：US07413149B2

    公开(公告)日：2008-08-19

    申请号：US10895774

    申请日：2004-07-21

    Applicant: Alan B. Minick ,  Benjamin Goldberg ,  Larry Knauer

    Inventor： Alan B. Minick ,  Benjamin Goldberg ,  Larry Knauer

    IPC: B64C21/00

    CPC classification number: B64C23/005 ,  B64C2230/12 ,  F05D2270/172 ,  F15D1/10 ,  Y02T50/166

    Abstract: A system for augmenting the apparent velocity and effectiveness of an airfoil, such as a wing, on a vehicle includes at least one ionizer or emitter positioned relative to the airfoil to ionize a fluid media in which the airfoil travels and at least one attractor/receiver for accelerating the flow of ionized fluid media over the airfoil. The system further includes a voltage source to which each ionizer and each attractor is electrically connected.

    Abstract translation: 一种用于增强车辆上的翼面（如机翼）的表观速度和有效性的系统包括至少一个相对于翼型件定位的离子发生器或发射器，以离子化其中翼型件行进的流体介质和至少一个吸引子/接收器 用于加速翼型上的电离流体介质的流动。 该系统还包括每个电离器和每个吸引子电连接的电压源。

    Augmenter for compound compression engine
    7.
    发明授权
    Augmenter for compound compression engine 有权
    复合压缩发动机增压器

    公开(公告)号：US08839761B2

    公开(公告)日：2014-09-23

    申请号：US12830604

    申请日：2010-07-06

    Applicant: Alan B. Minick ,  Alfred Little

    Inventor： Alan B. Minick ,  Alfred Little

    IPC: F02B53/08 ,  F02B53/04 ,  F02B53/00 ,  F02B41/06 ,  F01C11/00 ,  F01C1/22

    CPC classification number: F02B53/00 ,  F01C1/22 ,  F01C11/004 ,  F02B41/06 ,  Y02T10/17

    Abstract: A rotary engine includes a first rotary unit operable to provides a first phase of compression to a fresh air charge drawn in through an inlet port to the first rotary unit. A second rotary unit in communication with the first rotary unit through a first passage, the second rotary unit operable to provide a second phase of compression to the first phase of compression, a combustion phase and a first phase of expansion, the second rotary unit in communication with the first rotary unit through a second passage such that the first rotary unit provides a second phase of expansion to the first phase of expansion and an exhaust phase that exhausts the first rotary unit via an exhaust port. A first fuel injector is in communication with the second rotary unit operable to initiate the combustion phase and a second fuel injector is in communication with the first rotary unit operable to selectively initiate augmented operation.

    Abstract translation: 旋转发动机包括第一旋转单元，其可操作以将第一相压缩提供给通过第一旋转单元的入口吸入的新鲜空气。 第二旋转单元，其通过第一通道与第一旋转单元连通，第二旋转单元可操作以向第一压缩阶段，燃烧阶段和第一膨胀阶段提供第二压缩阶段，第二旋转单元 通过第二通道与第一旋转单元连通，使得第一旋转单元向第一膨胀阶段提供第二膨胀阶段，以及通过排气口排出第一旋转单元的排气相。 第一燃料喷射器与可操作以启动燃烧阶段的第二旋转单元连通，并且第二燃料喷射器与第一旋转单元连通，可操作以选择性地启动增强操作。

    Aircraft fluid diversion inlet louver
    8.
    发明授权
    Aircraft fluid diversion inlet louver 有权
    飞机液体导流通风台

    公开(公告)号：US08322981B2

    公开(公告)日：2012-12-04

    申请号：US12395849

    申请日：2009-03-02

    Applicant: Stacey H. Light ,  Alan B. Minick

    Inventor： Stacey H. Light ,  Alan B. Minick

    IPC: F01D1/02

    CPC classification number: F02C7/32 ,  F02C7/042 ,  F02C7/047 ,  F02C7/055

    Abstract: An inlet system, including for an auxiliary power unit includes an inlet louver mounted to an inlet duct, the inlet louver defines a multiple of vanes positioned to shield the inlet duct from fluids which fall in direction generally transverse to a free stream airflow.

    Abstract translation: 包括用于辅助动力单元的入口系统包括安装到入口管道的入口百叶窗，入口百叶窗限定了多个叶片，其被定位成将入口管道屏蔽掉，该流体沿着大致横向于自由流气流的方向落下。

    AUGMENTED EXPANDER CYCLE
    9.
    发明申请
    AUGMENTED EXPANDER CYCLE 审中-公开
    增加扩展周期

    公开(公告)号：US20120204535A1

    公开(公告)日：2012-08-16

    申请号：US13027868

    申请日：2011-02-15

    Applicant: Alan B. Minick ,  David C. Gregory

    Inventor： Alan B. Minick ,  David C. Gregory

    IPC: F02K9/48

    CPC classification number: F02K9/46 ,  F02K9/48 ,  F02K9/64 ,  F05D2260/10 ,  F05D2270/051

    Abstract: A rocket engine includes a thrust chamber having a cooling channel, which is adapted to provide sustained cracking conditions for a fluid (e.g., kerosene) within the cooling channel under steady-state engine operating conditions. An augmenter having a fluid input communicates with an output of the cooling channel, and an output of the augmenter is in fluid communication with a turbine. A pump is mechanically coupled to the turbine, and provides fluid flow to the inlet of the cooling channel.

    Abstract translation: 火箭发动机包括具有冷却通道的推力室，其适于在稳态发动机运行条件下为冷却通道内的流体（例如煤油）提供持续的裂解条件。 具有流体输入的增压器与冷却通道的输出连通，增压器的输出与涡轮流体连通。 泵机械地联接到涡轮机，并且将流体流动提供给冷却通道的入口。

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