Thrust regulation is a key technology on the solid liquid rocket ramjet engine.
推力调节是整体式固液火箭冲压发动机研究的一项关键技术。
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；
Numerical calculation model and method are applicable to analyzing reacting flow field of the solid rocket ramjet with central air-inlet mode.
采用的数值计算模型和方法适用于分析中心进气式固冲发动机反应流场。
The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD.
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。
Physical and mathematic model of investigating combustion characteristics of secondary combustion chamber for static extended solid rocket ramjet was established.
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。
The combustion flow field in secondary combustion chamber for static and spinning extended solid rocket ramjet were studied experimentally and numerically in detail.
本文从实验和数值模拟两方面，对静止和旋转增程固体火箭发动机补燃室燃烧流场进行了研究。
The numerical simulation of turbulent combustion in the afterburner of solid rocket ramjet was performed by applying the probability density function non -premixed mode.
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。
As the air-breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition.
作为吸气式发动机，其性能不仅取决于发动机本身结构和推进剂性能，与飞行状态也有密切的联系。
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.
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。
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.
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。
The flow chart of optimizing ASP climb track is designed by adjusting some parameters of Euler angle, attack angle, turbine and rocket-ramjet combined cycle work models, etc.
以涡轮和火箭冲压组合动力的工作模式以及飞行器飞行航迹角、迎角等为调参量，构造空天飞行器爬升轨迹优化流程。
The flow chart of optimizing ASP climb track is designed by adjusting some parameters of Euler angle, attack angle, turbine and rocket-ramjet combined cycle work models, etc.
以涡轮和火箭冲压组合动力的工作模式以及飞行器飞行航迹角、迎角等为调参量，构造空天飞行器爬升轨迹优化流程。
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