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目的探索固体火箭发动机装药低温老化试验方法和机理,为固体发动机寿命预测和延寿提供支撑。方法设计方便取样测试的结构试验器,通过仿真计算确定具有一定应变水平的装药内孔尺寸,开展-10℃和-35℃低温老化试验。老化后首先对结构试验器进行无损检测,再取出药柱制取推进剂标准试样,进行常温和低温快速拉伸力学性能测试。结果设计完成三段连接式结构试验器,既不破坏药柱所承受的应力载荷,又保证取样方便、安全。无损探伤表明,经过低温长期贮存的结构试验器药柱没有产生裂纹和脱粘现象。推进剂的常温力学性能无明显变化,低温的最大抗拉强度有所升高,最大伸长率降低明显,-10℃和-35℃低温老化试验后,最大伸长率分别降低了24%和40%。结论推进剂内部产生了微损伤,承受低温快速应变(对应低温点火冲击状态)能力下降明显,应引起高度关注。
Objective To explore the low temperature aging test method and mechanism of solid rocket motor charge to provide support for the life prediction and longevity of solid engine. Methods The structural tester which is convenient for sampling and testing is designed. The bore size of the charge with a certain strain level is determined by simulation calculation, and the low temperature aging test at -10 ℃ and -35 ℃ is carried out. After aging, the structural tester is firstly non-destructively tested, then the drug column is taken out to prepare a standard sample of propellant, and the rapid tensile mechanical property test is conducted at normal temperature and low temperature. Results The design of three-section connected structure tester did not destroy the stress load on the column and ensured the convenience and safety of sampling. Nondestructive testing shows that cracks and debonding have not occurred in the structure tester pellets after long-term storage at low temperature. The mechanical properties of propellants at room temperature showed no significant change, the maximum tensile strength at low temperature increased, the maximum elongation decreased significantly, -10 ℃ and -35 ℃ low temperature aging test, the maximum elongation decreased by 24% and 40%. CONCLUSIONS Micro-damage was generated in the propellants. The ability to withstand rapid low-temperature strain (corresponding to low-temperature ignition shock conditions) decreased significantly and should be highly concerned.