Design methods and test process of nozzleclosure made of hard foamed plastics for SRM are introduced.
介绍了固体火箭发动机喷管硬质泡沫塑料堵盖的设计方法与试验过程。
2
Propellant property and nozzleclosure opening pressure have an important effect on the ignition transient.
推进剂的燃烧特性及喷管堵盖打开压强对点火升压过程有较大影响。
3
The pressure for opening the nozzleclosure was determined in the simulated ignition test. The results show that the design scheme is reasonable. This kind of closure has been used in the practice.