公开(公告)号：US5720451A

公开(公告)日：1998-02-24

申请号：US574505

申请日：1995-12-19

申请人： Melvin L. Chazen ,  Thomas J. Mueller ,  William D. Kruse

发明人： Melvin L. Chazen ,  Thomas J. Mueller ,  William D. Kruse

IPC分类号： F02K9/62 ,  B32B15/00

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）。