摘要
为研究固体火箭发动机点火器工作过程中火药燃烧和输出压力规律,通过建立点火器点火药燃烧数学模型,对某点火器在密闭测压容器内燃烧过程进行了数值计算研究。分析了点火器内点火药燃烧规律和燃烧过程中测压容器内压力分布规律,计算得到的P-t曲线与试验结果具有较好的一致性,验证了所建立的点火药燃烧模型及计算方法的合理性和正确性。
In order to research the law of propellant combustion and output pressure during the working process of the solid rocket motor igniter,a numerical calculation study is carried out on the combustion process of a certain igniter in a closed pressure measuring vessel by establishing a mathematical model of the ignition powder combustion of the igniter.The combustion law of the ignition powder in the igniter and the pressure distribution law in the pressure measuring vessel during the combustion process are analyzed.The calculated P-t curve is in good agreement with the test results,indicating that the established ignition powder combustion model and calculation method are reasonable and correct.
作者
湛赞
薛太旭
蒋超达
王宇
王玉强
ZHAN Zan;XUE Taixu;JIANG Chaoda;WANG Yu;WANG Yuqiang(Xi’an Aerospace Propulsion Technology Institute,Xi’an 710025,China)
出处
《弹箭与制导学报》
北大核心
2022年第5期6-9,14,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家自然科学基金(U1530135)资助。
关键词
固体火箭发动机
点火
火药燃烧
数值分析
solid rocket motor
ignition
gunpowder combustion
numerical analysis
