固体火箭推进剂侵蚀燃烧动态实时测试方法  

An Instantaneous Measuring Method of Erosive Burning Rate of Solid Rocket Propellant

作　　者：夏静[1] 

机构地区：[1]南京理工大学机械学院

出　　处：《南京理工大学学报》1997年第2期141-144,共4页Journal of Nanjing University of Science and Technology

基　　金：国防科技预研行业基金

摘　　要：该文描述了一种固体火箭推进剂侵蚀燃烧的测试方法。将被测推进剂试件置于一特殊结构的发动机中，当发动机点火后，实验发动机中的气体发生器产生高速气流，经过渡段流入试验段使推进剂试件点燃。试件的燃烧是沿燃烧表面的法向进行的。通过安装在试验段的石英窗，用固态图像传感器对燃面的退移进行光电转换，所输出电信号由计算机进行采集和处理。An experimental test apparatus and procedure for measuring erosive burning rates of solid rocket propellant is described in the present paper.A gas generator in the test motor produces a high velocity gas flowing through a transition section into a rectangular channel which contains the test propellant sample.The sample is ignited by cross flow and burns along the normal direction of the burning surface.The burning rate is directly measured by photographing the ablating grain with CCD through a quartz window mounted on the test section.The electrical signal translated from image of the flame is sampled and proceeded by a computer,which makes it possible to determinen instantaneous burning rates of the test propellant as a function of time.

关 键 词：固体推进剂 侵蚀燃烧 测试 火箭 实时测试 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]