1.前言为了实现固体火箭的推力控制,很久以来就很重视固体推进剂的燃烧中断与再点火问题。急剧降低燃烧室的压力使燃烧中断、利用注入燃烧抑制剂使燃烧中断以及向固体火箭燃烧室喷射反应性流体使燃烧开始并继续燃烧,然后中断喷射使燃烧中断等方法,进行过很多研究,但是都未达到实用水平。 1. INTRODUCTION In order to achieve the thrust control of solid rocket, the problem of burning and re-ignition of solid propellants has long been emphasized. A great deal of research has been done to rapidly reduce the pressure in the combustion chamber to interrupt the combustion, to interrupt the combustion by injecting the combustion inhibitor, to inject the reactive fluid into the solid rocket combustion chamber, to start the combustion, to continue the combustion, and to interrupt the injection to interrupt the combustion Did not reach the practical level.