变推力固体火箭发动机喉栓烧蚀试验研究  

Experimental investigation of erosion performance of pintle in thrust-controllable SRM

作　　者：周战锋[1] 胡春波[1] 李江[1] 魏祥庚[1] 刘泽祥[1] 

机构地区：[1]西北工业大学燃烧、流动与热结构国家级实验室,西安710072

出　　处：《固体火箭技术》2009年第2期163-166,170,共5页Journal of Solid Rocket Technology

摘　　要：针对三维C/C和钨渗铜两种不同材质,开展了发动机喉栓的静态烧蚀及动态烧蚀研究,揭示了静态和互变条件下喉栓发动机的烧蚀规律。试验结果表明,高压静态条件与互变过程相比,喉栓烧蚀率有明显差别,高压静态比互变过程烧蚀更严重,互变过程引起的热环境变化没有造成烧蚀异常增大。因此,在工程中可采用高压静态烧蚀试验来考核喉栓材料,简化试验系统;在文中试验条件下,钨渗铜喉栓最大径向烧蚀率为0.085 mm/s,三维编织C/C材料最大径向烧蚀率为0.545 mm/s,钨渗铜比C/C材料更适用于喉栓;发动机非轴对称结构、粒子冲刷和沉积现象对烧蚀影响较大,采用同轴结构可改善流动的对称性,有利于进一步研究其他因素对烧蚀的影响。Static and dynamic ablation experiments were carried out in a pintle rocket motor experimental system to obtain the ablation law for two different materials. The results from these experiments indicate that the ablation of pintle in high-pressure static state is more serious than that in dynamic state. As a result, the high-pressure static state ablation experiment would be more suitable for the test of the pintle material for engineering application. The largest radial ablation rate of W-Cu and 3D C/C composite is 0.085 mm/s and 0.545 mm/s respectively. So W-Cu is validated to be more suitable for the pintle material than C/C composite. The unaxi-symmetry structure, particle erosion and sediment also have great effect on the ablation of pintle, so the symmetry structure of experimental motor could modify the symmetry of flow, which will contribute to study the effect of other factors on ablation.

关 键 词：固体火箭发动机 推力调节 喉栓 烧蚀 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]