固体火箭发动机喷流中电子密度的实验研究  

Experimental research on electron density in solid-rocket motor plume

作　　者：陈伟芳[1] 王志坚[1] 吴其芬[1] 陈逖[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2005年第4期253-255,共3页Journal of Solid Rocket Technology

摘　　要：研究如何利用固体火箭发动机工作产生的非均匀等离子体喷流流场,改变飞行器的目标光电特性是导弹等飞行器突防的一个重要课题.对此进行了一些初步的探索性实验,获得了两种不同固体火箭发动机喷流流场电子密度的有关数据,其中双基推进剂约为109cm-3量级,复合推进剂1010～1011cm-3量级.试验表明,将固体火箭发动机作为等离子体发生器是一种行之有效的方法,可以获得需要的电子密度值.One important subject how to utilize the inhomogeneous plasma flow field generated by solid rocket motor to change the object photoelectric properties was investigated for aircraft penetration. Some preliminary exploratory experiments were finished. The relevant data of electron density in two different rocket motor plumes were obtained, those of double base propellant are about 10^9cm^-3 magnitude and those of composite propellant are about 10^10-10^11 cm^-3 magnitude. The experiments indicate that the method making the solid rocket motor as plasma ionizer is effective, and the required electron density value can be gained.

关 键 词：固体推进剂火箭发动机 电子密度 静电探针 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]