密闭燃烧器法是一种能测定很宽压强范围内固体火箭推进剂燃速特性及变化情况的快速测量方法。
Burning rate measurement with closed burner is a rapid method for measuring burning rate character and its change of solid rocket propellants in a wide pressure range.
与高分子包覆单基发射药相比，双层结构变燃速发射药具有较好的燃烧渐增特性和明显的低温度系数效果。
Contrast with single base gun propellant with polymer coating layer, the two-layered variable-burning rate propellant has good properties of progressive combustion and low temperature coefficient.
试验结果表明：NC、NG组成的双基粘合剂与固体添加物rdx在热分解特性上的差异是导致硝胺发射药燃速曲线转折的原因。
The results show that the crook of these propellants burning curves were caused by the difference of thermal decomposition behavior between the solid filler RDX and NC-NG double-base binder.
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