By employing the gaseous oxygen as oxidizer and gaseous hydrogen as fuel, hot-firing tests were performed for aerospike nozzle and dual-bell nozzle test engines with altitude compensating features.

采用气氧作氧化剂、气氢作燃料，对具有高度补偿特性的塞式喷管和双钟型喷管进行了点火热试。

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Experiments test the influences of pressure, height, nozzle aperture and frog momentum on the fire control effect of fine water mist.

实验主要通过测定压力、高度、喷头孔径的大小和雾动量对细水雾灭火效果的影响。

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A new type of dual-pulse solid rocket motor concept with an intermediate nozzle is presented and a test motor with changeable structural parameters was designed.

提出了一种带有中间喷管的新型双脉冲固体火箭发动机技术方案，设计了一台结构参数可调的试验发动机；

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