航空兵器
航空兵器
항공병기
HANGKONG BINGQI
2014年
1期
33-36
,共4页
高过载%固体火箭发动机%非均匀燃面计算方法%内弹道性能
高過載%固體火箭髮動機%非均勻燃麵計算方法%內彈道性能
고과재%고체화전발동궤%비균균연면계산방법%내탄도성능
high overload%solid rocket motor%irregular burning surface calculation method%inter-nal ballistics performance
针对高过载条件下固体火箭发动机的燃烧特性，利用燃速方程编程计算，得出了过载条件下含铝复合推进剂燃速增加系数，分析了过载与燃速增大变化规律，并采用非均匀燃面计算方法模拟不同过载条件下发动机的内弹道性能，结果表明，过载对发动机内弹道性能影响不明显，但会影响特定部位燃速增大导致的装药偏烧，有必要加强该部位的热防护。
針對高過載條件下固體火箭髮動機的燃燒特性，利用燃速方程編程計算，得齣瞭過載條件下含鋁複閤推進劑燃速增加繫數，分析瞭過載與燃速增大變化規律，併採用非均勻燃麵計算方法模擬不同過載條件下髮動機的內彈道性能，結果錶明，過載對髮動機內彈道性能影響不明顯，但會影響特定部位燃速增大導緻的裝藥偏燒，有必要加彊該部位的熱防護。
침대고과재조건하고체화전발동궤적연소특성，이용연속방정편정계산，득출료과재조건하함려복합추진제연속증가계수，분석료과재여연속증대변화규률，병채용비균균연면계산방법모의불동과재조건하발동궤적내탄도성능，결과표명，과재대발동궤내탄도성능영향불명현，단회영향특정부위연속증대도치적장약편소，유필요가강해부위적열방호。
Based on the combustion characteristic of solid rocket motor under high overload , the data of the burning rate augmentation of the HTPB propellants on the overload is acquired by computing burn-ing rate equation, and the law of burning rate augmentation changed with overload is analyzed .The inter-nal ballistic performance under different overload is computed by the irregular burning surface calculation method.The result shows that, the overload has little effect on the internal ballistics performance , but could increase the burning rate of specific areas and lead to the grain burning eccentrically .it is necessary to strengthen heat safety design for these areas .
