CAJ | 학술논문

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900 ℃，喷口温度为250 ℃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21 ℃和150 ℃，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。
채용전가열기화수랭진공창근사모의발동궤내외적고온연기화저온진공배경，이부복사도층적불수강대체니합금，재지면진행료비선변궤발동궤조축비시험건적고온복사모의시험。결과표명：재후부온도위900 ℃，분구온도위250 ℃적시험공황하，사궤병련공작인기적최대주향온차재후부화분구분별약위21 ℃화150 ℃，량궤공황시주향온도불균균성불급사궤엄중，후부온차기본가홀략。
Electric heaters and vacuum cabin were used to simulate the hot combustion gas and the cryogenic vacuum environment. Stainless steel coated with radiation coat replaces niobium alloy. The simulation test of high temperature radiation of the orbit maneuvering engine group was performed on the ground.The result proved that on the condition of throat temperature being 900 ℃ and exit temperature being 250 ℃, the circular temperature change caused by parallel connection arrangement of the four engines is about 21 ℃ at throat and 150 ℃ 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.