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为研究装药结构对固体火箭发动机烤燃特性的影响,以装填HTPE推进剂的固体火箭发动机为研究对象,建立了复合、单孔管形及星孔形3种装药结构的固体发动机烤燃模型。以1和2℃/min的升温速率对小尺寸HTPE推进剂烤燃试样进行烤燃实验,以实验结果为基础,修正了推进剂材料参数。利用Fluent软件对3种装药结构在不同升温速率(β)下的烤燃行为进行了数值模拟。结果表明:装药结构对固体火箭发动机的烤燃响应时间、点火点和快/慢速烤燃的划分都有影响;星孔形装药会导致点火点出现跳跃性变化的临界升温速率效应,而单孔管形装药不存在此现象。在本研究条件下,包含星孔段的复合装药发动机的临界升温速率为0.2℃/min,星孔形装药发动机的临界升温速率为0.3和0.5℃/min,即当0.3℃/min≤β≤0.5℃/min时点火点发生跳跃变化。
In order to study the effect of charge structure on the characteristics of roasting combustion of solid rocket motors, a solid rocket motor with HTPE propellants was used as the research object to establish a solid-state engine with three types of composite structure, single-hole tubular shape and star- model. The combustion experiment of small size HTPE propellant was carried out at a heating rate of 1 ℃ and 2 ℃ / min, and the propellant material parameters were revised based on the experimental results. Fluent software was used to simulate the firing behavior of three kinds of charge structures at different heating rates (β). The results show that the charge structure affects the fuming response time, the ignition point and the fast / slow burning combustion of the solid rocket motor. The star-shaped charge can lead to the critical heating rate effect when the ignition point changes dramatically. The single-hole tubular charge does not exist in this phenomenon. Under the conditions of this study, the critical heating rate of the composite charge engine with the star-hole section is 0.2 ℃ / min, the critical heating rate of the star-charge charge engine is 0.3 and 0.5 ℃ / min, β≤0.5 ℃ / min when the ignition point jump changes.