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1.发明公开Ion thruster having grids made of oriented pyrolytic graphite 有权热解石墨石墨（Ionitriebwerk mit Gittern aus gerichtetem）
公开(公告)号：EP1122426A2
公开(公告)日：2001-08-08
申请号：EP01101310.9
申请日：2001-01-20
申请人： THE BOEING COMPANY
CPC分类号： F03H1/0043 , B64G1/405
摘要： An ion thruster (20) includes a source (24) of a plasma of ions and electrons, and an ion-optics system (34) located in sufficient proximity to the source (24) of the plasma to extract ions therefrom. The ion-optics system (34) has at least two domed grids (42, 44, 46) arranged in a facing-but-spaced-apart relationship to each other. Each grid (42, 44, 46) has a local reference vector (58) that is perpendicular to the surface of the grid (42, 44, 46) and a reference plane (60) perpendicular to the reference vector (58). Each of the grids (42, 44, 46) is formed of anisotropic pyrolytic graphite having an "ab" crystallographic plane (64) that lies substantially in the reference plane (60). In one form, the "ab" crystallographic plane (64) lies coplanar with the reference plane (60) at all locations on each domed grid (42, 44, 46) made of pyrolytic graphite. In another form, the "ab" crystallographic plane (64) has a constant orientation at all locations on the domed grid (42, 44, 46). In yet another form, wherein the ion optics system (34) has an axis of thrust (38), the "ab" crystallographic plane (64) of the pyrolytic graphite lies substantially perpendicular to the axis of thrust (38) (Fig. 3A).
摘要翻译： 离子推进器（20）包括离子和电子的等离子体的源（24）和离子光学系统（34），离子光学系统（34）位于足够靠近等离子体的源（24）处以从其中提取离子。 离子光学系统（34）具有至少两个以彼此面对但间隔开的关系排列的圆顶格栅（42,44,46）。 每个网格（42,44,46）具有垂直于网格（42,44,46）的表面和垂直于参考矢量（58）的参考平面（60）的局部参考矢量（58）。 每个栅极（42,44,46）由具有基本上位于参考平面（60）中的“ab”结晶平面（64）的各向异性热解石墨形成。 在一种形式中，“ab”结晶平面（64）在由热解石墨制成的每个圆顶格栅（42,44,46）上的所有位置处与参考平面（60）共面。 在另一种形式中，“ab”结晶平面（64）在圆顶格栅（42,44,46）上的所有位置具有恒定的取向。 在另一种形式中，其中离子光学系统（34）具有推力轴（38），热解石墨的“ab”结晶平面（64）基本上垂直于推力轴线（38）（图3A ）。
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2.发明公开Ion thruster having a hollow cathode assembly with an encapsulated heater, and its fabrication 有权具有封装的加热元件的中空阴极器件，及其制造方法离子推进器
公开(公告)号：EP1122427A3
公开(公告)日：2003-12-03
申请号：EP01101313.3
申请日：2001-01-20
申请人： THE BOEING COMPANY
CPC分类号： B64G1/405 , F03H1/0031
摘要： An ion thruster (20) has a hollow cathode assembly (50) including a heater (72) with an inner ceramic sleeve (52) and an outer ceramic sleeve (58). The outer ceramic sleeve (58) overlies the inner ceramic sleeve (52) with a filament volume (64) between the two sleeves (52, 58). A wound filament (66) has windings disposed within the filament volume (64), and a mass of ceramic powder (68) fills the remaining portion of the filament volume (64) between the windings of the filament (66). A cathode (76) is disposed within the inner ceramic sleeve (52) of the heater (72). The heater (72) is assembled by preparing the filament (66) and forming it into a wound cylinder, and then encapsulating it and the powder between the inner and the outer ceramic sleeves (58). The hollow cathode assembly (50) may serve as a portion of a plasma source (24) or as a portion of a charge neutralizer (40) (Fig. 3).
摘要翻译： 一个离子推进器（20）具有中空的阴极组件（50）包括加热器（72）与内套筒的陶瓷（52）和到外陶瓷套筒（58）。 外陶瓷套筒（58）覆盖所述内陶瓷套筒（52）与所述两个套筒（52，58）之间的丝卷（64）。 伤口灯丝（66）具有灯丝体积（64）内设置的绕组，和陶瓷粉末（68）的质量填充灯丝（66）的绕组之间的灯丝体积（64）的剩余部分。 阴极（76）的加热器（72）的内套筒的陶瓷（52）内设置。 加热器（72）是通过制备该灯丝（66）和使其形成一个伤口气缸，然后包封它与内和外套筒的陶瓷（58）之间的粉末组装。 空心阴极组件（50）可以用作等离子源（24）的一部分或作为电荷中和器（40）（图3）的一部分。
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公开(公告)号：EP1122426A3
公开(公告)日：2003-10-15
申请号：EP01101310.9
申请日：2001-01-20
申请人： THE BOEING COMPANY
CPC分类号： F03H1/0043 , B64G1/405
摘要： An ion thruster (20) includes a source (24) of a plasma of ions and electrons, and an ion-optics system (34) located in sufficient proximity to the source (24) of the plasma to extract ions therefrom. The ion-optics system (34) has at least two domed grids (42, 44, 46) arranged in a facing-but-spaced-apart relationship to each other. Each grid (42, 44, 46) has a local reference vector (58) that is perpendicular to the surface of the grid (42, 44, 46) and a reference plane (60) perpendicular to the reference vector (58). Each of the grids (42, 44, 46) is formed of anisotropic pyrolytic graphite having an "ab" crystallographic plane (64) that lies substantially in the reference plane (60). In one form, the "ab" crystallographic plane (64) lies coplanar with the reference plane (60) at all locations on each domed grid (42, 44, 46) made of pyrolytic graphite. In another form, the "ab" crystallographic plane (64) has a constant orientation at all locations on the domed grid (42, 44, 46). In yet another form, wherein the ion optics system (34) has an axis of thrust (38), the "ab" crystallographic plane (64) of the pyrolytic graphite lies substantially perpendicular to the axis of thrust (38) (Fig. 3A).
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4.发明公开Ion thruster having a hollow cathode assembly with an encapsulated heater, and its fabrication 有权具有封装的加热元件的中空阴极器件，及其制造方法离子推进器
公开(公告)号：EP1122427A2
公开(公告)日：2001-08-08
申请号：EP01101313.3
申请日：2001-01-20
申请人： THE BOEING COMPANY
CPC分类号： B64G1/405 , F03H1/0031
摘要： An ion thruster (20) has a hollow cathode assembly (50) including a heater (72) with an inner ceramic sleeve (52) and an outer ceramic sleeve (58). The outer ceramic sleeve (58) overlies the inner ceramic sleeve (52) with a filament volume (64) between the two sleeves (52, 58). A wound filament (66) has windings disposed within the filament volume (64), and a mass of ceramic powder (68) fills the remaining portion of the filament volume (64) between the windings of the filament (66). A cathode (76) is disposed within the inner ceramic sleeve (52) of the heater (72). The heater (72) is assembled by preparing the filament (66) and forming it into a wound cylinder, and then encapsulating it and the powder between the inner and the outer ceramic sleeves (58). The hollow cathode assembly (50) may serve as a portion of a plasma source (24) or as a portion of a charge neutralizer (40) (Fig. 3).
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