CAJ | 학술논문

为了对高能固体火箭发动机进行冲击安全性评价，进行了?480 mm×640 mm高能发动机的火箭橇冲击试验，试验结果表明，高能发动机在冲击作用下存在无反应、燃烧和爆炸3个反应级别，且明显受到推进剂损伤程度的影响，测试获得了各反应级别对应的冲击速度区间，并分析了推进剂损伤对反应剧烈程度的影响规律。建立了高能发动机冲击起爆的数值仿真模型，该模型基于计算单元压力大小作为是否起爆的判据，可用于分析冲击起爆的初始位置，计算结果与试验基本吻合，验证了仿真模型的正确性。该项研究可为高能发动机冲击安全性研究与评价提供参考。
위료대고능고체화전발동궤진행충격안전성평개，진행료?480 mm×640 mm고능발동궤적화전취충격시험，시험결과표명，고능발동궤재충격작용하존재무반응、연소화폭작3개반응급별，차명현수도추진제손상정도적영향，측시획득료각반응급별대응적충격속도구간，병분석료추진제손상대반응극렬정도적영향규률。건립료고능발동궤충격기폭적수치방진모형，해모형기우계산단원압력대소작위시부기폭적판거，가용우분석충격기폭적초시위치，계산결과여시험기본문합，험증료방진모형적정학성。해항연구가위고능발동궤충격안전성연구여평개제공삼고。
On the purpose of evaluating the safety of high energy solid rocket motor,the rocket sled experiments with high ener?gy SRM on the scale of ?480 mm× 640 mm was conducted,the results show that:there are three phenomena such as no reaction, burn and blast when the high energy SRM is shocked,these phenomena are influenced by the extent of damage on propellant. The shock velocity interval of every action level with rocket sled experiment was tested,and the relationship between propellant damage and reaction level was found.Based on calculating the pressure of cells as the judgment of ignition,numerical simulation on shock ig?nition of high energy SRM was modelled ,which can be used for analyzing the initial location of ignition.The calculating results fit the experiment results well,which shows that the numerical model is right.This research can be used for studying and evaluating the safety of high energy SRM for reference.