摘要
为解决某型号固体火箭发动机铝合金壳体的热防护功能以及侧面初始通气面积不足等问题,采用等离子热喷涂技术在铝合金壳体内表面喷涂厚度为0.1 mm NiCrAlY与0.3 mm氧化钇稳定的氧化锆(YSZ)涂层作为隔热材料,充分利用YSZ涂层熔点高、热导率低的特点,实现大幅度减小绝热层厚度(0.4 mm)及增加装填空间的目的,结合仿真计算结果表明采用涂层技术可实现铝合金壳体隔热在安全使用的温度范围内;同时解决了软质绝热层在高温燃气流动过程中存在烧蚀、冲刷、脱落等缺陷引起的壳体烧穿的故障。各项试验考核表明采取喷涂YSZ涂层措施达到对铝合金壳体的良好热防护作用,满足固体火箭发动机燃烧室壳体在2200℃、1.5 s的隔热要求;可将该措施应用于工作时间较短、燃温较高的其它固体火箭发动机的隔热防护措施当中。
In order to solve a solid rocket motor(SRM)problems of thermal protection function of aluminum alloy shell and insufficient initial ventilation area on the side,plasma thermal spraying technology is used to spray 0.1 mm NiCrAlY and 0.3 mm ZrO_(2) coating on the inner surface of aluminum alloy shell as heat insulation material,and the advantages of YSZ coating,such as high melting point and low thermal conductivity,were fully utilized to achieve the purpose of greatly reducing the thickness of thermal insulation layer(0.4 mm),and achieved the purpose of increasing the loading space.Combined with the simulation results,it was shown that the aluminum alloy shell can be insulated in a safe temperature range by using the coating technology.At the same time,it solves the problem of burning through the shell caused by the defects of ablation,scouring and falling off of the soft insulation layer in the process of high temperature gasflow.The test results showed that YSZ coating can achieve good thermal protection for aluminum alloy shell and meet the thermal insulation requirements of SRM combustion chamber shell at 2200℃and 1.5 s.This measure can be applied to the thermal insulation protection measures of other SRM with short working time and high combustion temperature.
作者
吴敏
张国涛
党力
陈哲
汪耀源
韩艳松
Wu Min;Zhang Guotao;Dang Li;Chen Zhe;Wang Yaoyuan;Han Yansong(Hubei Institute of Aerospace Chemistry Technology,Xiangyang 441003;Military Representative Office of the Rocket Force Equipment Department in Xiangyang Area,Xiangyang 441003)
出处
《热喷涂技术》
2023年第1期72-76,共5页
Thermal Spray Technology
