导弹尾部外形对发动机水下点火推力的影响  

Influence of outline of missile tail on the thrust of solid motor launching under water

作　　者：张有为[1] 王晓宏[1] 

机构地区：[1]中国科学技术大学热科学和能源工程系,合肥230026

出　　处：《航空动力学报》2008年第5期927-931,共5页Journal of Aerospace Power

基　　金：教育部新世纪优秀人才支持计划

摘　　要：利用球形气泡模型,通过数值求解研究了导弹尾部对发动机水下点火时推力峰值、尾部压力分布以及推力波动特性的影响.计算结果表明:尾部收敛段半锥顶角的变化对推力峰值影响较大,半锥顶角大于45°时,随着半锥顶角的减小,推力峰值缓慢下降;半锥顶角小于45°时,推力峰值随着半锥顶角的减小而加速下降;半锥顶角对推力达到峰值的时间影响较小;推力达到峰值时尾部收敛段压力分布变化较大;半锥顶角对推力波动特性影响很小.By using the sphere model, the influences of outline of missile tail upon the thrust peak, pressure distribution on the tail and the oscillation character of the thrust for solid motor launching under water are numerically studied. Results indicate that the half cone-angle of convergent segment has great effect upon thrust peak. The thrust peak decreases slowly as the half-cone-angle is above 45 degree, and decreases quickly as the half-cone angle is less than 45 degree. But the half-cone-angle has very little effect upon the time for thrust reaching the peak. It is also shown that the pressure distribution varies a lot on the convergent segment of the missile tail as thrust reaches the peak value. The half cone angle has little effect on the oscillation frequency of thrust.

关 键 词：航空、航天推进系统 火箭发动机 水下点火 尾部外形 

分 类 号：E927[军事—军事装备学]