摘要
采用电加热器和水冷真空舱近似模拟发动机内外的高温燃气和低温真空环境 ,以敷辐射涂层的不锈钢代替铌合金 ,在地面进行了飞船变轨发动机组缩比试验件的高温辐射模拟试验。结果表明 :在喉部温度为 90 0℃ ,喷口温度为 2 5 0℃的试验工况下 ,四机并联工作引起的最大周向温差在喉部和喷口分别约为 2 1℃和 15 0℃ ,两机工况时周向温度不均匀性不及四机严重 ,喉部温差基本可忽略。
Electric heaters and vacuum cabin were used to simulate the hot combustion gas and the cryogenic vacuum environment. Stainless steel coated with radiation of the orbit maneuvering engine group was performed on the ground. The result proves that on the condition of throat temperature being 900°C and exit temperature being 250°C, the circular temperature change caused by parallel connection arrangement of the four engines is about 21°C at throat and 150°C at the exit of the nozzle. The circular temperature nonuniformity of two working engines is less than that of four working engines, so the temperature change at throat can be omitted.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2001年第3期207-210,共4页
Journal of Propulsion Technology
