研究了整体式固体火箭冲压发动机的应用性能。
Applications of integral solid propellant rocket ramjets arc researched.
首先建立研究静止增程固体火箭冲压发动机补燃室燃烧特性的物理和数学模型。
Physical and mathematic model of investigating combustion characteristics of secondary combustion chamber for static extended solid rocket ramjet was established.
应用概率密度函数非预混模型，对固体火箭冲压发动机补燃室内的湍流燃烧进行了数值模拟。
The numerical simulation of turbulent combustion in the afterburner of solid rocket ramjet was performed by applying the probability density function non -premixed mode.
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.
应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。
The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD.
硼颗粒在通过固体火箭冲压发动机的燃气发生器喷管进入补燃室的过程中，颗粒通常都会受到高速气流的作用。
The effects of various parameters on boron particle ignition of ducted rocket secondary chamber were studied with the model developed by the King.
贫氧推进剂燃速是固体火箭冲压发动机设计和性能分析的重要参数，也是对推进剂配方进行检验验收的主要指标。
The burning rate of the fuel-rich propellants is the parameter which is important for Ducted Rocket design and performance analysis and is main inspection criterions of propellant prescriptions.
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.
研究了过渡金属氧化物（TMO ）及其复配物对非壅塞固体火箭冲压发动机铝镁贫氧推进剂燃烧特性的影响。研究发现，氧化铁对提高铝镁贫氧推进剂燃速的作用显著。
The effects of TMOs and their mixtures on the burning rate and the pressure exponent of the aluminum magnesium fuel rich propellant for unchoked ducted rocket are investigated.
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.
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.
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