微小型固体火箭发动机点火效率影响研究  

Research of Impact on Micro Solid Rocket Motor Ignition Efficiency

作　　者：张明[1] 涂四华[1] 邢一星[1] 黄强[1] 张秋芳[1] 吴秋[1] 

机构地区：[1]中国航天科技集团公司第四研究院第41所,西安710025

出　　处：《弹箭与制导学报》2015年第5期92-94,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对微小型固体火箭发动机点火过程出现的未点燃、点火延时过长等问题进行了理论与试验研究,得到了微小型固体火箭发动机篓式点火器结构的点火药量计算改进公式。研究结果表明,对于微小型固体火箭发动机,点火效率明显偏低于常规发动机,在应用常规点火药量计算公式时,应考虑效率影响因素;另外,对于相同的点火药量,环状药片式结构优于药粒式结构。Focused on ignition delay or ignition failure in micro solid rocket motors,ignition theoretical analysis and experimental research were finished and an improved formula was put forward. The research shows that ignition efficiency of micro solid rocket motors is lower than that of routine-scale motors apparently; it means that ignition efficiency must be considered when calculating the mass of ignition charge by general formula. In addition,the structure of annular tablet is better than the structure of medicine for the same ignition dose.

关 键 词：微小型发动机 点火效率 点火可靠性 

分 类 号：TJ760.2[兵器科学与技术—武器系统与运用工程]