固体火箭技术
固體火箭技術
고체화전기술
JOURNAL OF SOLID ROCKET TECHNOLOGY
2014年
4期
583-586
,共4页
王周成%张飞%陈慧%史宏斌%陈妮
王週成%張飛%陳慧%史宏斌%陳妮
왕주성%장비%진혜%사굉빈%진니
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
軸棒法編織C/C複閤材料%燒蝕性能%圓形喉襯%縮比燒蝕髮動機%全呎吋髮動機
축봉법편직C/C복합재료%소식성능%원형후츤%축비소식발동궤%전척촌발동궤
C/C composites with axial carbon rods%ablation properties%circle throat insert%subscale ablation motor%full-scale motor
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。
針對新型喉襯用軸棒法編織C/C複閤材料的結構特點,建立瞭一種採用圓形喉襯縮比燒蝕髮動機評價全呎吋髮動機喉襯燒蝕性能的縮比試驗方法。依據該方法進行瞭多髮縮比燒蝕髮動機試驗,併結閤全呎吋髮動機喉襯燒蝕試驗數據,給齣瞭與髮動機工況、結構呎吋和推進劑類型相關的軸棒法編織C/C喉襯燒蝕性能評價公式。利用其他批次喉襯在不同型號髮動機的燒蝕數據,對評價公式進行瞭校驗和分析,預示結果與試驗結果較一緻,錶明建立的試驗方法和評價公式能夠體現縮比燒蝕髮動機與全呎吋髮動機燒蝕性能的相關性。
침대신형후츤용축봉법편직C/C복합재료적결구특점,건립료일충채용원형후츤축비소식발동궤평개전척촌발동궤후츤소식성능적축비시험방법。의거해방법진행료다발축비소식발동궤시험,병결합전척촌발동궤후츤소식시험수거,급출료여발동궤공황、결구척촌화추진제류형상관적축봉법편직C/C후츤소식성능평개공식。이용기타비차후츤재불동형호발동궤적소식수거,대평개공식진행료교험화분석,예시결과여시험결과교일치,표명건립적시험방법화평개공식능구체현축비소식발동궤여전척촌발동궤소식성능적상관성。
Based on the braided structure of new throat insert material C/C composite material with axial carbon rods, the sub-scale 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 mo-tor could be represented by the developed test method and the evaluating formula.