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卫星推进剂在射弹超高速撞击下面临着爆炸的风险,就此问题进行研究。在分析卫星推进系统组成的基础上,以单组元液体肼推进剂为研究对象建立了射弹撞击推进剂贮箱的模型;结合典型撞击起爆判据对国外液体肼撞击起爆试验数据进行分析,定义液体肼撞击起爆的功率密度阈值,建立液体肼撞击起爆模型;依据一维冲击波和不定常流理论,建立撞击冲击波压力及其持续时间的求解模型。分别采用本模型和光滑粒子流体动力学算法对同一案例进行仿真分析,两种方法得到功率密度值均高于起爆阈值,二者误差为4.5%,这一结果验证了本模型的有效性可行性。研究成果对于空间撞击事件效果分析与影响评估具有重要的工程参考价值。
Satellite propellants are exposed to the risk of explosion under very high-speed projectile impact and the issue is studied. Based on the analysis of the composition of satellite propulsion system, a model of projectile propellant tank was established with single-component liquid hydrazine propellant as a research object. According to the typical impact initiation criteria, the experimental data of hydrazine collision initiation in foreign countries were analyzed. The threshold of power detonation detonation is defined, and a liquid hydrazine striking detonation model is established. According to the theory of one-dimensional shock wave and unsteady flow, a solution model of impinging shock wave pressure and its duration is established. The model and the smooth particle hydrodynamics algorithm are respectively used for the simulation analysis of the same case. The power densities obtained by the two methods are both higher than the detonation threshold, and the error between the two is 4.5%. This result verifies the feasibility of this model . The research results have important engineering reference value for the impact analysis and impact assessment of space impact events.