撞击载荷作用下固体火箭发动机安全性分析

Nmerical analysis of SRM's safety under nmechanic impact

Institute of Aerospace and Material Engineering, National University of Defence Technology, Changsha 410073, China

摘要: 以机械撞击载荷下固体推进剂裂纹摩擦热点细观模型为基础,考虑推进剂基体粘性加热,结合热粘弹理论和动力有限元法,分析计算发动机结构撞击变形及装药内部热点形成,确定产生高温热点撞击临界速度。通过对含能材料Steven撞击试验、小型试验发动机撞击试验分析计算及结果对比,证明了理论模型及计算方法的有效性。
- 航空、航天推进系统 /
- 固体火箭发动机 /
- 机械撞击 /
- 热点 /
- 安全性
Abstract: Based on the meso-scale model for the hot-spot of crack friction in solid propellant,with the consideration of the theory of thermo-visco-elasticity and using the method of hydrodynamic finite elements,numerical investigations of solid rocket motor(SRM) structural deformation and hot-spot formation in SRM's grain under mechanic impact were carried out,in which the effect of viscous heating in the solid propellant matrix was also considered.Critical impact velocities for the solid propellant ignition were determined.In comparison with the results of impact tests of the energetic material samples and small SRM,it is showed that results obtained through numerical analysis agree reasonably well with that of experiments.
- aerospace propulsion system /
- solid rocket motor /
- mechanical impact /
- hot-spot /
- safety of solid rocket motor

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