Design methods and test process of nozzle closure 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。
Propellant property and nozzle closure 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。
The pressure for opening the nozzle closure 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.
某型号发动机硬质泡沫喷管堵盖打开压强模拟点火试验结果表明，这种硬质泡沫喷管堵盖设计方案可行，并已在实际中得到应用。
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