Rhenium and iridium engine combustion chamber inner wall protective platinum and rhodium ring production method

Abstract

The invention relates to a rhenium and iridium engine combustion chamber inner wall protective platinum and rhodium ring production method. The method designs the thickness of a platinum and rhodium ring through an internal spinning mode, produces the platinum and rhodium ring of the inner wall of a combustion chamber in the steps of tooling mold designing, spinning forming, mold stripping and assembly and ensures that the platinum and rhodium ring is in tight combination with the inner wall of the combustion chamber. According to the platinum and rhodium ring produced through the method, a propellant and an intermediate product of the oxidized propellant are ensured to be not in contact with iridium coating when a rhenium and iridium engine works, the production of hot pits is prevented, and the engine is ensured to work to the required service life. When the platinum and rhodium ring is used for the rhenium and iridium combustion chamber, the corrosion of methyl hydrazine to the iridium coating is completely eliminated in the process of an experiment, and a platinum and rhodium alloy is in good surface condition and does not have any corrosion or erosion phenomenon after the experiment, so that the rhenium and iridium engine is ensured to work reliably and stably.

Description

technical field [0001] The invention relates to a preparation method of a rhenium-iridium engine combustion inner wall protective platinum-rhodium ring, which belongs to the technical field of surface engineering. Background technique [0002] Small-thrust dual-component liquid rocket engines are mainly used in the attitude and orbit control of space vehicles and strategic and tactical weapons. The fuel combustion temperature in the thrust chamber can reach 2700°C. After adopting the liquid film active cooling technology on the inner wall, the wall temperature is still higher than 1000°C Therefore, in order to ensure the high-temperature strength requirements of the engine thrust chamber, high-temperature refractory metals (Nb, Ta, W, Mo, Re, and platinum, etc.) must be used as body materials, but these materials have poor high-temperature oxidation resistance, such as Niobium alloys will undergo "pest" catastrophic oxidation above 600 °C, and cannot directly face the combus...

AI Technical Summary

Problems solved by technology

The current problem is that the engines using rhenium-iridium materials all use hydrazine propellant, and the propellant will undergo a miscibility reaction when in contact with iridium, resulting in the rapid failure of the iridium coating and the exposure of the rhenium base material, resulting in failure of the thrust chamber.

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