轴棒法编织C/C喉衬烧蚀性能缩比试验评价方法  

Subscale test method for ablative properties of throat insert using C /C composites woven with axial carbon rods

作　　者：王周成[1] 张飞[1] 陈慧[1] 史宏斌[1] 陈妮[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2014年第4期583-586,共4页Journal of Solid Rocket Technology

基　　金：国家973项目(973-61391)

摘　　要：针对新型喉衬用轴棒法编织C/C复合材料的结构特点,建立了一种采用圆形喉衬缩比烧蚀发动机评价全尺寸发动机喉衬烧蚀性能的缩比试验方法。依据该方法进行了多发缩比烧蚀发动机试验,并结合全尺寸发动机喉衬烧蚀试验数据,给出了与发动机工况、结构尺寸和推进剂类型相关的轴棒法编织C/C喉衬烧蚀性能评价公式。利用其他批次喉衬在不同型号发动机的烧蚀数据,对评价公式进行了校验和分析,预示结果与试验结果较一致,表明建立的试验方法和评价公式能够体现缩比烧蚀发动机与全尺寸发动机烧蚀性能的相关性。Based on the braided structure of new throat insert material C/C composite material with axial carbon rods, the subscale test method on evaluating full-scale motor throat insert ablative properties using a subscale motor with circle throat insert was developed.Several subscale ablation motor tests were performed.The formula for evaluating ablative properties of throat insert using C/C composites with axial carbon rods which relate to motor work condition, structural dimension and propellant type were obtained by combining the ablation data of subscale motor and full-scale motor.The formula was verified by using ablation data of other batch throat insert in different type motors.Results show that the relativity of ablative properties between subscale motor and full-scale motor could be represented by the developed test method and the evaluating formula.

关 键 词：轴棒法编织C/C复合材料 烧蚀性能 圆形喉衬 缩比烧蚀发动机 全尺寸发动机 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]