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公开(公告)号：US5720451A
公开(公告)日：1998-02-24
申请号：US574505
申请日：1995-12-19
CPC分类号： F02K9/62 , F05D2300/15 , Y10T428/12458
摘要： A high temperature thrust chamber for spacecraft (20) is provided herein. The high temperature thrust chamber comprises a hollow body member (12) having an outer surface and an internal surface (16) defining the high temperature chamber (10). The body member (12) is made substantially of rhenium. An alloy (18) consisting of iridium and at least alloying metal selected of the group consisting of rhodium, platinum and palladium is deposited on at least a portion of the internal surface (16) of the body member (12). The iridium and the alloying metal are electrodeposited onto the body member (12). A HIP cycle is performed upon the body member (12) to cause the coating of iridium and the alloying metal to form the alloy (18) which protects the body member (12) from oxidation.
摘要翻译： 本文提供了一种用于航天器（20）的高温推力室。 高温推进室包括具有外表面的中空本体构件（12）和限定高温室（10）的内表面（16）。 主体构件（12）基本上由铼制成。 由铱和至少选自铑，铂和钯的合金金属的合金（18）沉积在主体部件（12）的内表面（16）的至少一部分上。 铱和合金金属电沉积到主体部件（12）上。 对本体构件（12）进行HIP循环，以使铱和合金金属的涂层形成保护体部件（12）免受氧化的合金（18）。
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公开(公告)号：US06655127B2
公开(公告)日：2003-12-02
申请号：US10328909
申请日：2002-12-24
IPC分类号： F02K948
CPC分类号： F02K9/48
摘要： A method is provided for using high concentrations of hydrogen peroxide to drive a turbine (20′) in a turbopump fed rocket engine (12′). The method includes the steps of: (a) receiving fuel into a fuel rich pre-burner (50); (b) receiving high concentrations of hydrogen peroxide into the pre-burner (50); (c) converting the fuel and hydrogen peroxide into a fuel rich gas; and (d) passing the fuel rich gas through a turbine (20′), thereby using high concentrations of hydrogen peroxide to drive the turbine. Thus, by utilizing a fuel rich pre-burner (50) that operates at a very low mixture ratio, the drive gas for a turbine (20′) can be maintained at moderate temperature levels.
摘要翻译： 提供了一种使用高浓度的过氧化氢来驱动涡轮泵送入火箭发动机（12'）中的涡轮机（20'）的方法。 该方法包括以下步骤：（a）将燃料接收到富燃料预燃烧器（50）中; （b）将高浓度的过氧化氢接收到预燃烧器（50）中; （c）将燃料和过氧化氢转化为富燃气体; 和（d）使富燃气体通过涡轮机（20'），由此使用高浓度的过氧化氢来驱动涡轮机。 因此，通过利用以非常低的混合比操作的富燃料预燃烧器（50），用于涡轮（20'）的驱动气体可以保持在中等温度水平。
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公开(公告)号：US06505463B2
公开(公告)日：2003-01-14
申请号：US09761957
申请日：2001-01-17
IPC分类号： F02K948
CPC分类号： F02K9/48
摘要： A method is provided for using high concentrations of hydrogen peroxide to drive a turbine (20′) in a turbopump fed rocket engine (12′). The method includes the steps of: (a) receiving fuel into a fuel rich pre-burner (50); (b) receiving high concentrations of hydrogen peroxide into the pre-burner (50); (c) converting the fuel and hydrogen peroxide into a fuel rich gas; and (d) passing the fuel rich gas through a turbine (20′), thereby using high concentrations of hydrogen peroxide to drive the turbine. Thus, by utilizing a fuel rich pre-burner (50) that operates at a very low mixture ratio, the drive gas for a turbine (20′) can be maintained at moderate temperature levels.
摘要翻译： 提供了一种使用高浓度的过氧化氢来驱动涡轮泵送入火箭发动机（12'）中的涡轮机（20'）的方法。 该方法包括以下步骤：（a）将燃料接收到富燃料预燃烧器（50）中; （b）将高浓度的过氧化氢接收到预燃烧器（50）中; （c）将燃料和过氧化氢转化为富燃气体; 和（d）使富燃气体通过涡轮机（20'），由此使用高浓度的过氧化氢来驱动涡轮机。 因此，通过利用以非常低的混合比操作的富燃料预燃烧器（50），用于涡轮（20'）的驱动气体可以保持在中等温度水平。
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公开(公告)号：US06684622B2
公开(公告)日：2004-02-03
申请号：US10085501
申请日：2002-02-26
IPC分类号： F02K997
CPC分类号： F02K1/08 , Y02T50/672
摘要： Methods and arrangements for tailoring rocket exhaust plume signatures of rocket exhaust systems are disclosed. The tailoring of the rocket exhaust plume signature is accomplished by providing and locating at least one structure having materials and/or additives that modify the radiant intensity pattern of the rocket exhaust plume upon ablation or melting into the rocket exhaust plume. The materials and/or additives can be manufactured or incorporated into preexisting ablative materials of the rocket exhaust system or be provided as stand-alone structures.
摘要翻译： 公开了用于定制火箭排气系统的火箭排气羽流签名的方法和装置。 通过提供和定位至少一个具有材料和/或添加剂的结构来实现火箭排气羽流签名的定制，该结构具有在消融或熔化成火箭排气羽流时改变火箭排气羽流的辐射强度图案。 材料和/或添加剂可以制造或并入到火箭排气系统的预先存在的烧蚀材料中，或者作为独立结构提供。
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公开(公告)号：US06655124B2
公开(公告)日：2003-12-02
申请号：US10085681
申请日：2002-02-26
申请人： Charles A. Vickery , William D. Kruse , Mark Olmos
发明人： Charles A. Vickery , William D. Kruse , Mark Olmos
IPC分类号： F02K997
摘要： Systems and methods are disclosed for tailoring rocket exhaust plume signatures of fuel-propelled vehicles. An uncombusted fuel is injected or sprayed into the exhaust plume of an ignited rocket. The injected or sprayed fuel modifies the rocket exhaust plume to simulate an exhaust plume of a different vehicle. One or more parameters associated with the injected or sprayed fuel can be modified, so that appropriate tailoring can be achieved.
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