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固体火箭发动机喷管在工作过程中其内部要承受高温、高压以及高速燃气所携带的固体颗粒冲刷,这些因素会引起喷管内部的烧蚀,进而直接影响其弹道性能,因此喷管喉衬材料的烧蚀性能是固体火箭发动机研究的主要方向之一。金属钼具有抗烧蚀、力学性能好等一系列优良的性能,同时钼喉衬的制备工艺简单,是低温推进剂难熔金属喉衬的首选材料。采用小型固体火箭发动机静态实验台研究钼喉衬在双钴1-a推进剂下沿轴向方向上的平均线烧蚀率,利用扫描电镜(SEM)及其所配置的能谱(EDX)分析钼喉衬的烧蚀特征及其机制。结果表明:在双钴1-a推进剂下钼喉衬烧蚀程度沿轴向方向不断变化,喉衬各部位烧蚀形貌存在明显差别。在收敛段末段区域及整个喉部区域烧蚀最为严重,其主要为热化学烧蚀和粒子剧烈冲蚀,平均最大线烧蚀率为0.1475 mm·s-1;收敛段大部分主要为热化学烧蚀和粒子轻微冲蚀;扩散段主要为热化学烧蚀。钼喉衬5 s后的平均烧蚀量约为喉径面积的4.92%,未超过喉径面积的5%,可满足在试验工况下固体火箭发动机的工作要求。
Solid rocket engine nozzle in the process of its internal to withstand high temperatures, high pressure and high-speed gas carried by the solid particles erosion, these factors will cause the nozzle ablation, which directly affects its ballistic performance, nozzle throat lining material The ablation performance of solid rocket motor research is one of the main directions. Metal molybdenum has a series of excellent performance of anti-ablation, good mechanical properties, etc., while the molybdenum throat lining preparation process is simple, is the preferred material for low temperature propellant refractory metal throat lining. A small solid rocket motor static experimental bench was used to study the average ablation rate of the molybdenum throat lining in the axial direction under the double cobalt 1-a propellant. Scanning electron microscopy (SEM) and EDX analysis Ablation characteristics of molybdenum throat lining and its mechanism. The results show that the ablation level of the molybdenum throat lining in the double cobalt 1-a propellant continuously changes along the axial direction, and there are obvious differences in ablation morphology of the throat lining. At the end of convergence zone and the whole laryngeal area, the ablation was the most serious, which was mainly caused by thermal chemical ablation and particle erosion. The average maximum ablation rate was 0.1475 mm · s-1. Most of the convergence zone was mainly hot Chemical ablation and slight erosion of particles; diffusion section is mainly thermal chemical ablation. After 5 s, the average ablation volume of molybdenum throat lining was 4.92% of the area of the throat diameter and did not exceed 5% of the area of the throat area to meet the working requirements of the solid rocket motor under test conditions.