介绍了固体火箭冲压发动机地面实验装置及测控系统组成、功能、技术指标和可以开展的研究工作。
The paper presents the composition, functions, technical performance and research of the solid rocket ramjet engine ground test equipment and measurement control system in detail.
分析了固液发动机推进剂的燃烧特性和发动机性能特性、与液体和固体火箭发动机的不同，以及研制的技术难度等。
The propellant feature of burning behavior and engine in hybrid engine, the differences to liquid and solid engine and the difficulties of technology in development were analyzed.
介绍一种应用CAT技术确定固体火箭发动机燃烧时间的新方法。
The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine.
研讨了整体式固体冲压火箭发动机的工作原理及技术难点；
This paper discusses operating principles and technology challenges of the integral solid propellant rocket ramjet.
采用块结构网格与二阶精度流场分区求解技术，对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。
By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out.
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；
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.
此项设计技术对带反向喷管的固体火箭发动机设计具有参考作用。
This technique is available for the design of SRM with reverse nozzle.
此项设计技术对带反向喷管的固体火箭发动机设计具有参考作用。
This technique is available for the design of SRM with reverse nozzle.
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