CAJ | 학술논문

为了研究某固体火箭发动机装药的贮存寿命，采用加速老化试验的方法，分别考核了某固体火箭发动机装药推进剂和壳体/绝热层/衬层/推进剂界面在四个老化温度下性能随老化时间变化的趋势。试验发现，随着老化时间延长，推进剂强度升高，最大伸长率下降，而界面剪切强度老化初期升高，老化后期下降的趋势较为明显。但是，无论在哪种老化温度下，界面剪切强度都高于技术指标要求。由此得出推进剂是影响该发动机装药贮存寿命的关键因素，按照标准规定的方法对试验结果进行了处理，预测该发动机装药在25℃下的贮存寿命为13浇．7年。
위료연구모고체화전발동궤장약적저존수명，채용가속노화시험적방법，분별고핵료모고체화전발동궤장약추진제화각체/절열층/츤층/추진제계면재사개노화온도하성능수노화시간변화적추세。시험발현，수착노화시간연장，추진제강도승고，최대신장솔하강，이계면전절강도노화초기승고，노화후기하강적추세교위명현。단시，무론재나충노화온도하，계면전절강도도고우기술지표요구。유차득출추진제시영향해발동궤장약저존수명적관건인소，안조표준규정적방법대시험결과진행료처리，예측해발동궤장약재25℃하적저존수명위13요．7년。
In order to obtain the storage life of a certain solid rocket motor charge , using accelerated aging test method , the characteristic changing trends of the propellant and the case i/nsulator /liner/pro-pellant interface under four aging temperatures with the aging time are studied .With aging time increas-ing, the propellant strength increases and the maximum elongation of propellant decreases , the shear strength increases at the early aging and decreases at the later aging .But the interfacial shear strength is higher than the technical index at various aging times .So concludes that the motor charge storage life is determined by the propellant .According to the standard , the test results are processed , and it is predic-ted that the charge storage life at 25 ℃is 13.7 years.