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    MISSILE CONTROL SYSTEM AND METHOD
    1.
    发明申请
    MISSILE CONTROL SYSTEM AND METHOD 有权
    MISSILE控制系统和方法

    公开(公告)号：US20060284006A1

    公开(公告)日：2006-12-21

    申请号：US11113511

    申请日：2005-04-25

    申请人： Daniel Chasman ,  Michael Leal ,  Stephen Haight

    发明人： Daniel Chasman ,  Michael Leal ,  Stephen Haight

    IPC分类号： B64B1/36

    CPC分类号： F42B10/666 ,  F02K9/30 ,  F02K9/805 ,  F02K9/86 ,  F05D2240/128 ,  F05D2250/323 ,  F05D2250/324 ,  F05D2250/41 ,  F05D2260/60 ,  F16K3/085 ,  F42B10/663

    摘要： A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.

    摘要翻译： 导弹包括具有转向和姿态控制系统推进器的控制系统，其具有控制阀。 每个控制阀具有在其中具有多个小喷嘴的喷嘴板。 喷嘴板包括一对部分，其中一个部分可相对于另一个部分旋转。 通过喷嘴板的流动的控制可以通过喷嘴板的部分的相对定位来实现。 喷嘴板的上游收敛部分可以相对于导弹固定，喷嘴板的下游喉部和/或发散部分可移动。 可以通过使用在导弹体外部的致动器来实现喷嘴板的可移动部分的移动。 控制阀提供了一种控制来自转向推进器的流量的简单，轻便和紧凑的方式。

    Rocket multi-nozzle grid assembly and methods for maintaining pressure and thrust profiles with the same
    2.
    发明授权
    Rocket multi-nozzle grid assembly and methods for maintaining pressure and thrust profiles with the same 有权
    火箭多喷嘴格栅组装和保持压力和推力轮廓的方法相同

    公开(公告)号：US08596040B2

    公开(公告)日：2013-12-03

    申请号：US13049024

    申请日：2011-03-16

    申请人： Daniel Chasman ,  Stephen D. Haight ,  Daniel V. MacInnis

    发明人： Daniel Chasman ,  Stephen D. Haight ,  Daniel V. MacInnis

    IPC分类号： F02K3/10

    CPC分类号： F02K9/978 ,  F02K9/86 ,  F02K9/974 ,  Y10T29/49229

    摘要： A rocket multi-nozzle grid assembly includes an insulator grid, a plurality of refractory nozzle fittings and a grid support plate. The grid support plate braces the plurality of refractory nozzle fittings and the insulator grid. The insulator grid includes insulator orifices, each of the nozzle fittings includes a fitting orifice and the grid support plate includes a plurality of plate orifices. The rocket multi-nozzle grid assembly includes a plurality nozzles. Each nozzle includes a plate orifice aligned with one insulator orifice and one fitting orifice. Exhaust gases are directed through the plurality of nozzles. The multi-nozzle grid assembly substantially maintains its surface area throughout operation of a rocket motor.

    摘要翻译： 火箭多喷嘴格栅组件包括绝缘体格栅，多个耐火喷嘴配件和格栅支撑板。 网格支撑板支撑多个耐火喷嘴配件和绝缘子网格。 绝缘体栅格包括绝缘子孔，每个喷嘴配件包括配合孔，并且栅格支撑板包括多个板孔。 火箭多喷嘴格栅组件包括多个喷嘴。 每个喷嘴包括与一个绝缘体孔口和一个配件孔口对准的板孔。 废气被引导通过多个喷嘴。 多喷嘴格栅组件在火箭发动机的操作过程中基本保持其表面积。

    PROPULSION SYSTEM WITH CANTED MULTINOZZLE GRID
    4.
    发明申请
    PROPULSION SYSTEM WITH CANTED MULTINOZZLE GRID 有权
    具有可选多点网格的推进系统

    公开(公告)号：US20100313544A1

    公开(公告)日：2010-12-16

    申请号：US11593440

    申请日：2006-11-06

    申请人： Daniel Chasman ,  Stephen D. Haight

    发明人： Daniel Chasman ,  Stephen D. Haight

    IPC分类号： F02K9/84

    CPC分类号： F42B10/665 ,  F02K9/97 ,  F05D2240/128 ,  F05D2250/30 ,  F05D2250/323 ,  F05D2250/324

    摘要： A propulsion system includes a canted multinozzle plate, which has a multitude of small nozzles angled (not perpendicular) to major surfaces of the multinozzle grid plate. The multinozzle plate may be a cylindrical section or plate, and the multitude of nozzles may be substantially axisymmetric about the cylindrical plate. The propulsion system includes a pressurized gas source which may be placed either forward or aft of the multinozzle grid plate. The propulsion system may have a conical insert, an internal flow separator cone, to aid in changing directions of flow from the pressurized gas source, to divert the flow through the multiple nozzles.

    摘要翻译： 推进系统包括倾斜多喷嘴板，其具有与多喷嘴格栅板的主表面成角度（不垂直）的多个小喷嘴。 多喷嘴板可以是圆柱形部分或板，并且多个喷嘴可以围绕圆柱形板基本上是轴对称的。 推进系统包括可以放置在多喷嘴格栅板的前方或后方的加压气体源。 推进系统可以具有锥形插入件，内部流动分离器锥体，以帮助改变来自加压气体源的流动方向，以便将流动转移通过多个喷嘴。

    Hybrid missile propulsion system with reconfigurable multinozzle grid
    6.
    发明授权
    Hybrid missile propulsion system with reconfigurable multinozzle grid 有权
    混合导弹推进系统与可重构多喷嘴网格

    公开(公告)号：US08117847B2

    公开(公告)日：2012-02-21

    申请号：US12044227

    申请日：2008-03-07

    申请人： Stephen D. Haight ,  Daniel Chasman ,  Juan A. Perez

    发明人： Stephen D. Haight ,  Daniel Chasman ,  Juan A. Perez

    IPC分类号： F02K1/00

    CPC分类号： F02K1/52 ,  F02K9/30

    摘要： A propulsion system, such as for use in a missile, includes a multinozzle grid having a pair of plates that are separably mechanically coupled together. When coupled together in a first configuration, the plates provide multiple nozzles in a first nozzle configuration (geometry). Separation of the plates, such as by separating an aft plate from a forward plate that remains with the missile, reconfigures the multinozzle grid to a second configuration that has nozzles in a second nozzle configuration (geometry). The nozzle configurations may be suitable for different types of propulsion mechanisms. The hybrid propulsion system utilizing the multinozzle grid may include a pair of pressurized gas sources, for example a solid rocket fuel and a combustion chamber for a ramjet.

    摘要翻译： 诸如用于导弹的推进系统包括具有可分离地机械联接在一起的一对板的多喷嘴格栅。 当以第一配置联接在一起时，板在第一喷嘴构型（几何形状）中提供多个喷嘴。 板的分离，例如通过将尾板与由导弹保留的前板分离，将多喷嘴格栅重新配置为具有第二喷嘴构型（几何形状）的喷嘴的第二构型。 喷嘴构造可适用于不同类型的推进机构。 利用多喷嘴格栅的混合推进系统可以包括一对加压气体源，例如固体火箭燃料和用于冲压喷气的燃烧室。

    MISSILE CONTROL SYSTEM AND METHOD
    7.
    发明申请
    MISSILE CONTROL SYSTEM AND METHOD 有权
    MISSILE控制系统和方法

    公开(公告)号：US20050011989A1

    公开(公告)日：2005-01-20

    申请号：US10289651

    申请日：2002-11-07

    申请人： Daniel Chasman ,  Stephen Haight ,  Andrew Facciano

    发明人： Daniel Chasman ,  Stephen Haight ,  Andrew Facciano

    IPC分类号： F42B10/64 ,  F41G7/00

    CPC分类号： F42B10/64 ,  F42B10/663

    摘要： A jet propulsion outlet device is disclosed that has a grid plate having a plurality of densely clustered nozzlettes, the nozzlettes of the grid plate being configured to operably couple to a pressurized gas source to efficiently expand the pressurized gas.

    摘要翻译： 公开了一种具有多个密集聚集的喷嘴的格栅板的喷射推进出口装置，格栅板的喷嘴构造成可操作地连接到加压气体源以有效地膨胀加压气体。

    ROCKET MULTI-NOZZLE GRID ASSEMBLY AND METHODS FOR MAINTAINING PRESSURE AND THRUST PROFILES WITH THE SAME
    9.
    发明申请
    ROCKET MULTI-NOZZLE GRID ASSEMBLY AND METHODS FOR MAINTAINING PRESSURE AND THRUST PROFILES WITH THE SAME 有权
    ROCKET多喷嘴网组件和用于维护压力和扭矩分布的方法

    公开(公告)号：US20120233979A1

    公开(公告)日：2012-09-20

    申请号：US13049024

    申请日：2011-03-16

    申请人： Daniel Chasman ,  Stephen D. Haight ,  Daniel V. MacInnis

    发明人： Daniel Chasman ,  Stephen D. Haight ,  Daniel V. MacInnis

    IPC分类号： F02K9/97 ,  B23P11/00

    CPC分类号： F02K9/978 ,  F02K9/86 ,  F02K9/974 ,  Y10T29/49229

    摘要： A rocket multi-nozzle grid assembly includes an insulator grid, a plurality of refractory nozzle fittings and a grid support plate. The grid support plate braces the plurality of refractory nozzle fittings and the insulator grid. The insulator grid includes insulator orifices, each of the nozzle fittings includes a fitting orifice and the grid support plate includes a plurality of plate orifices. The rocket multi-nozzle grid assembly includes a plurality nozzles. Each nozzle includes a plate orifice aligned with one insulator orifice and one fitting orifice. Exhaust gases are directed through the plurality of nozzles. The multi-nozzle grid assembly substantially maintains its surface area throughout operation of a rocket motor. In one example, the surface area is maintained through ablation of the insulator grid. In another example, the surface area is maintained through cooling of the plurality of nozzle fittings with the ablated fragments passing through the nozzles.

    摘要翻译： 火箭多喷嘴格栅组件包括绝缘体格栅，多个耐火喷嘴配件和格栅支撑板。 网格支撑板支撑多个耐火喷嘴配件和绝缘子网格。 绝缘体栅格包括绝缘子孔，每个喷嘴配件包括配合孔，并且栅格支撑板包括多个板孔。 火箭多喷嘴格栅组件包括多个喷嘴。 每个喷嘴包括与一个绝缘体孔口和一个配件孔口对准的板孔。 废气被引导通过多个喷嘴。 多喷嘴格栅组件在火箭发动机的操作过程中基本保持其表面积。 在一个示例中，通过绝缘体栅格的消融来维持表面积。 在另一示例中，通过冷却多个喷嘴配件来保持表面积，其中烧蚀的碎片通过喷嘴。