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A rhenium-iridium-carbon-carbon engine thrust chamber and its integrated preparation method

A thrust chamber and engine technology, which is applied in the direction of machines/engines, rocket engine devices, mechanical equipment, etc., can solve the problems of thrust chamber weight increase, etc., and achieve the effects of strong adaptability, high temperature strength, and stable performance

Active Publication Date: 2022-02-01
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

While the rhenium-iridium material engine has excellent performance, it also has a significant weakness, that is, the densities of both rhenium and iridium are as high as 21g / cm3, resulting in an increase in the weight of the thrust chamber

Method used

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  • A rhenium-iridium-carbon-carbon engine thrust chamber and its integrated preparation method

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0046] Thrust chamber material structure design

[0047] The thicknesses of iridium coating, rhenium transition layer and carbon-carbon composite materials are determined according to the operating conditions of the engine thrust chamber. The thickness range of the iridium coating is 80 μm, the thickness range of the rhenium transition layer is 0.8 mm, and the thickness of the carbon-carbon composite material is 3 mm.

[0048] (a) Machining mandrel

[0049] According to the inner surface of the thrust chamber of the engine, the processing size of the core mold is designed, and the three-high graphite is selected as the raw material, and the graphite core mold of the combustion chamber section is processed separately by mechanical processing technology (such as figure 1 (a) Shown) and extension graphite mandrel.

[0050] (b) deposition pretreatment

[0051] The graphite mandrel of the combustion chamber section is pretreated before depositing the iridium coating. The specifi...

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Abstract

The invention relates to a rhenium-iridium-carbon-carbon engine thrust chamber and an integrated preparation method. The thrust chamber is sequentially composed of an iridium coating, a rhenium transition layer and a carbon-carbon composite material from the inside to the outside; the thickness of the iridium coating is The range is 50-150 μm, the thickness of the rhenium transition layer is 0.8-1.5mm, and the thickness of the carbon-carbon composite material is 2-6mm. The present invention starts from the characteristics of the rhenium-iridium-carbon-carbon engine thrust chamber and adopts a "from inside to outside" "The preparation process route. The invention has strong adaptability, high repeatability, can reduce cost and improve production efficiency.

Description

technical field [0001] The invention relates to an integrated preparation method for a rhenium-iridium-carbon-carbon engine thrust chamber. It is mainly used in the field of preparation of thrust chambers of high-performance lightweight rhenium-iridium-carbon-carbon engines. Background technique [0002] The low-thrust dual-component liquid rocket engine is mainly used in the attitude and orbit control of space vehicles and strategic and tactical weapons. The fuel combustion temperature in the thrust chamber is as high as 2700°C, and the inner wall temperature is still higher than 1000°C by using the liquid film active cooling technology on the inner wall surface. In order to ensure the high-temperature strength requirements of the engine thrust chamber, refractory metals (W, Mo, Ta, Nb, Re, etc.) or metal platinum must be used as body materials, but these materials have poor high-temperature oxidation resistance, such as niobium alloys in Catastrophic oxidation will occur ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/62C23C14/32C23C14/08C23C28/00C23C16/52C23C16/14C23C16/26
CPCF02K9/62C23C14/325C23C14/08C23C28/322C23C28/345C23C16/52C23C16/14C23C16/26
Inventor 闫旭波焦星剑李夏明刘宇峰姚草根张绪虎
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH