高能固体发动机火箭橇试验及数值模拟  

Rocket sled experiment and numerical simulate on high energy SRM

作　　者：王宇[1] 刘凯[1] 孙利清[1] 李侃[1] 陈朗[2] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]北京理工大学机电学院,北京100081

出　　处：《固体火箭技术》2014年第6期873-876,共4页Journal of Solid Rocket Technology

摘　　要：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。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＆#215; 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.

关 键 词：高能发动机 安全性 火箭橇 冲击起爆 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]