Advanced ramjet technologies are also important for scramjet development, and the Chinese have been active in this area for decades.
先进亚燃冲压技术对于超燃冲压技术至关重要，而中国数十年来在这一领域一直很活跃。
Combustion with releasing heat effectively in supersonic flow is one of the most important, as well as the most difficult, technologies in researching and developing supersonic combustion ramjet.
超音速流动状态下的高效燃烧过程是研制超燃冲压发动机最重要也是难度最大的关键技术之一。
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。
The water ramjet based on the reaction of water and fuel is a new kind of underwater engine.
基于水与金属燃料反应的水冲压发动机是一种新型的水下动力装置。
The neural network is adopted to study the burning rate identification of the solid fuel ramjet.
用神经网络技术对固体燃料冲压动机的燃速辨识问题进行了研究。
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；
So it is of very important science meaning and practice value to simulate the circle flow field of the ramjet shell.
因此，对冲压增程炮弹绕流流场的研究具有重要科学意义和实用价值。
The performance of supersonic inlet determines the pressure and the air flux in combustor, then affect the work of ramjet.
超声速进气道的性能优劣决定了补燃室流场内的压强和空气流量，进而影响到冲压发动机的工作性能。
With the inner combustion and flow analysis of solid fuel ramjet(SFRJ), the internal ballistic model within SFRJ is established.
通过分析固体燃料冲压发动机内部燃烧和流动过程，建立了固体燃料冲压发动机内弹道计算模型。
The ramjet performance is calculated and compared with fixed and continuous adjustable structure intake and nozzle in this paper.
本研究对具有固定、连续可调进气道和尾喷管的冲压发动机性能进行了计算和比较。
The investigation lays a fine foundation for realizing stable high efficient combustion based on the thermal throat RBCC ramjet mode.
研究工作为实现基于热力喉道的RBCC亚燃模态稳定高效燃烧提供了良好的基础。
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。
Therefore, it is very important and necessary to specially research the heat transfer and ablation properties of insulation in ramjet chamber.
因此，开展固体冲压发动机补燃室内绝热层传热烧蚀特性研究，就显得非常有意义。
The necessity of flow regulation system in solid ramjet is presented, and the scheme of gas-fired flux adjustment about generator is analyzed.
阐述了固冲发动机燃气流量调节的必要性，对发生器燃气流量调节方案进行了评述。
As a hypersonic propulsion system, turbo-ramjet received recognition because of the widely flight envelope and excellent performance such as Isp.
在高超声速推进系统中，涡轮冲压组合发动机由于有着宽广的飞行范围，良好的比冲性能，受到世界各国的普遍重视。
Cold flow field and simple reaction flow field of the combustion of HTPB and PS within the solid fuel ramjet (SFRJ) are simulated using PHOENICS program.
应用PHOENICS软件模拟了固体燃料冲压发动机(SFRJ)的冷流和以HTPB、PS为推进剂的简单反应流。
The operation principles of adjustment programs and circuits of the fuel regulation system for a ramjet engine at high altitude are introduced in detail.
详细介绍了高空工作的某型冲压发动机燃油调节系统的调节方案和调节线路的工作原理，叙述了该调节系统有关参数的测量方法。
In ejector and ramjet modes, working over a wide Mach number range is very important for the RBCC inlet, so the 2d RBCC inlet should be variable-geometry.
对工作于引射和亚燃模态的RBCC发动机进气道来说，宽马赫数工作的要求显得尤为突出，使得二元进气道应采用变几何结构。
The relations of thrust and specific impulse to inlet air flow and temperature are derived from theoretical analysis of solid fuel ramjet (SFRJ) performance.
在固体燃料冲压发动机性能分析基础上，推导了某发动机的推力和比冲与入口流量和温度之间的关系式。
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。
Thermodynamic calculation method can be used to determine the optimum water-fuel ratio of water ramjet so as to provide reference to design and test of water ramjet.
用热力计算方法可确定水冲压发动机最佳水燃比，进而指导水冲压发动机的设计和试验。
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。
In order to study the fuel mass flow rate regulation characteristics of tube-in-hole for solid fuel ramjet, the flow field of turbulent combustion was numerically analyzed.
为了研究固体燃料冲压发动机内部套管结构调节燃料流量的特性，对某模型发动机的湍流燃烧流场进行了数值分析。
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。
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。
Flow characteristic of supersonic bi-cone inlet of ramjet assisted range projectiles is studied, and reasonable flow structures are also achieved through the wind tunnel experiment.
对某冲压增程弹用超声速双锥进气道流场特性进行研究，在风洞试验中得到合理的流场结构图谱及试验数据。
Flow characteristic of supersonic bi-cone inlet of ramjet assisted range projectiles is studied, and reasonable flow structures are also achieved through the wind tunnel experiment.
对某冲压增程弹用超声速双锥进气道流场特性进行研究，在风洞试验中得到合理的流场结构图谱及试验数据。
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