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    Electric thruster made with surface treatments for improved thermal management
    1.
    发明授权
    Electric thruster made with surface treatments for improved thermal management 有权
    电动推进器采用表面处理方式进行热管理

    公开(公告)号：US06619028B2

    公开(公告)日：2003-09-16

    申请号：US10011159

    申请日：2001-12-05

    申请人： Kurt B. Kreiner ,  John R. Beattie

    发明人： Kurt B. Kreiner ,  John R. Beattie

    IPC分类号： H05H100

    CPC分类号： F03H1/0037 ,  F03H1/0031

    摘要： An electric thruster has at least a portion of a surface of at least one of the component elements of its housing surface treated to increase the thermal transmission at the surface. The surface treatment is selected to increase the thermal absorption and thence the absorption of heat at the interiorly facing surfaces of the treated component, and/or to increase the thermal emissivity and thence radiation heat loss at the exteriorly facing surfaces of the treated component, and/or to increase the effective surface area through which heat is absorbed or emitted. The surface-treated housing components are assembled together with a cathode assembly, an ionization chamber, a propellant gas source, and a magnetic structure to form an electric thruster.

    摘要翻译： 电推进器具有处理其壳体表面的至少一个构成元件的表面的至少一部分，以增加表面处的热传递。 选择表面处理以增加热处理部件的内表面处的热吸收和热吸收，和/或增加处理部件的外表面处的热辐射率和辐射热损失，以及 /或增加吸收或发射热量的有效表面积。 表面处理的壳体部件与阴极组件，电离室，推进剂气体源和磁性结构组装在一起以形成电推进器。

    Ion thruster with ion-extraction grids having compound contour shapes
    2.
    发明授权
    Ion thruster with ion-extraction grids having compound contour shapes 失效
    离子推进器具有复合轮廓形状的离子提取网格

    公开(公告)号：US06250070B1

    公开(公告)日：2001-06-26

    申请号：US09569708

    申请日：2000-05-09

    申请人： Kurt B. Kreiner ,  John R. Beattie ,  Alois Wittmann ,  Lewis S. Pilcher

    发明人： Kurt B. Kreiner ,  John R. Beattie ,  Alois Wittmann ,  Lewis S. Pilcher

    IPC分类号： F03H100

    CPC分类号： H05H1/54 ,  F03H1/0043 ,  H01J27/024

    摘要： An ion thruster has a source of a plasma, and an ion-optics system located in sufficient proximity to the source of the plasma to extract ions therefrom. The ion-optics system includes at least two grids arranged in a facing-but-spaced-apart relationship to each other, with each grid being axisymmetric about a grid axis. Each grid includes a peripheral region defining a grid plane perpendicular to the grid axis, a first region of curvature adjacent to the peripheral region, and a second region of curvature along the grid axis such that the first region of curvature lies between the second region of curvature and the peripheral region. The first region of curvature is a convexly curved segment of a first sphere relative to the grid plane, and the second region of curvature is a concavely curved segment of a second sphere relative to the grid plane.

    摘要翻译： 离子推进器具有等离子体源，离子光学系统位于足够靠近等离子体源的位置以从其中提取离子。 离子光学系统包括至少两个彼此相对且间隔开的关系布置的网格，每个网格围绕网格轴线是对称的。 每个网格包括限定垂直于网格轴的网格平面的周边区域，与周边区域相邻的第一曲率区域和沿着网格轴线的第二曲率区域，使得第一曲率区域位于第二区域 曲率和周边区域。 所述第一曲率区域是第一球体相对于所述格子平面的凸曲面段，并且所述第二曲率区域是相对于所述格子平面的第二球体的凹曲曲线段。

    Rocket engine with internal chamber step structure
    3.
    发明授权
    Rocket engine with internal chamber step structure 有权
    火箭发动机具有内腔梯级结构

    公开(公告)号：US06269630B1

    公开(公告)日：2001-08-07

    申请号：US09144376

    申请日：1998-08-31

    申请人： Kurt B. Kreiner ,  David Bronson ,  Carl R. Stechman ,  Peter E. Woll ,  Joel M. Neiderman

    发明人： Kurt B. Kreiner ,  David Bronson ,  Carl R. Stechman ,  Peter E. Woll ,  Joel M. Neiderman

    IPC分类号： F02K942

    CPC分类号： F02K9/60 ,  F02K9/62 ,  F05D2230/90 ,  F05D2250/231 ,  F05D2250/70 ,  F05D2300/133 ,  F05D2300/143 ,  F05D2300/502

    摘要： A rocket engine includes a generally cylindrical annular combustion chamber, an injector attached to an injector end of the combustion chamber, a generally cylindrical annular step collar fitting within the combustion chamber at the injector end thereof, and an attachment of the combustion chamber, the injector, and the step collar. The maximum outer diameter of the step collar is from about 0.020 inches to about 0.024 inches smaller than the inner diameter of the combustion chamber, and has a length of from about 21 to about 31 percent of the length of the combustion chamber. The step collar is made of a material having a melting point greater than that of the combustion chamber. The attachment preferably includes a clip structure joining the combustion chamber and the step collar. The clip structure includes a C-shaped annular clip having a first leg extending parallel to the chamber length and with an inner diameter of about that of the outer diameter of the combustion chamber and affixed thereto, a second leg extending parallel to the chamber length and with an outer diameter of no greater than that of the outer diameter of the step collar and affixed thereto, and a web extending between the first leg and the second leg.

    摘要翻译： 火箭发动机包括大致圆柱形的环形燃烧室，附接到燃烧室的喷射器端的喷射器，在其燃烧室的喷射器端处装配在燃烧室内的大致圆柱形的环形阶梯环，以及燃烧室，喷射器 ，和步领。 阶梯环的最大外径比燃烧室的内径小约0.020英寸至约0.024英寸，并且具有燃烧室长度的约21至约31％的长度。 阶梯环由具有大于燃烧室的熔点的材料制成。 附件优选地包括接合燃烧室和阶梯环的夹子结构。 夹子结构包括C形环形夹具，其具有平行于腔室长度延伸的第一腿部，并且内径大约为燃烧室的外径并且固定到其上，第二腿部平行于腔室长度延伸， 其外径不大于台阶轴环的外径并且固定到其上，以及在第一腿和第二腿之间延伸的腹板。