再次，冲压发动机燃油控制回路研究。
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.
提出了超燃冲压发动机燃烧室的性能分析评价方法。
The methodology for scramjet combustor performance analysis and evaluation is build up.
再生冷却技术是超燃冲压发动机燃烧室热防护的关键技术。
Regenerative cooling technology is one of the key technologies to thermally protect scramjet chamber.
隔热层烧蚀冷却、气膜冷却是冲压发动机常用的冷却方式。
Adiabatic ablation cooling, film cooling are the main means and have been used widely.
不过，太空署要如何使得超燃冲压发动机进入持续飞行需要的超音速呢？
But how does NASA plan to get the scramjet to the supersonic speeds necessary for sustained flight?
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。
Thrust regulation is a key technology on the solid liquid rocket ramjet 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 water ramjet based on the reaction of water and fuel is a new kind of underwater engine.
超燃冲压发动机技术是一项新型的、具有广阔发展前景的推进技术。
Scramjet Engine technology is a new type of propulsion technology with bright application prospect.
本文分析及提出了超音速燃烧冲压发动机燃烧室燃烧效率的数学模型。
The model of combustion efficiency for scramjet combustor is analyzed and presented in this paper.
的目的，这些研究是收集数据，使他们能够适应的试验室的冲压发动机试验。
The objective of these studies is to gather data that enable them to adapt the test chamber for ramjet tests.
具体工作如下：1、含有两相流的超燃冲压发动机燃油供给系统模型的建立。
The idiographic work is as follows: 1, the modeling of the scramjet fuel supply system with two phase flow.
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 ramjet performance is calculated and compared with fixed and continuous adjustable structure intake and nozzle in this paper.
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。
Therefore, it is very important and necessary to specially research the heat transfer and ablation properties of insulation in ramjet chamber.
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。
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.
超燃冲压发动机是高超声速飞行器理想的动力装置，是当前高超声速技术领域的研究热点。
Scramjet is the perfect propulsive device to hypersonic vehicle, and is a hot issue in current hypersonic technology area.
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.
这里的一角冲压发动机业务最终的转子，你可以看到燃料线有火花和机制，相当简单的设计。
Here's the business end of the rotor-tip ramjet, you can see where the fuel line comes in and the sparking mechanism, fairly simple design.
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。
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.
提出了一种利用磁悬浮技术提供初始速度、利用冲压发动机实现临近空间飞行的新型发射方法。
A new launch method is introduced, which the primary speed is provided by the magnetism-suspension technology, and can realize the near space flying by using of the ramjet engine.
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。
With the inner combustion and flow analysis of solid fuel ramjet(SFRJ), the internal ballistic model within SFRJ is established.
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.
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。
The performance of supersonic inlet determines the pressure and the air flux in combustor, then affect the work of ramjet.
在一个有突扩台阶的氢燃料高超声速冲压发动机模型内研究了氢燃料喷注方式对点火与燃烧效果的影响。
A dual-mode scramjet model engine with a rear-faced step is experimentally investigated with different hydrogen fuel injection manners.
超燃冲压发动机以其高速、高比冲和工作范围宽广的特点，正逐渐成为当今航空航天动力领域的研究焦点。
The scramjet has some advantages of high flow velocity, high specific impulse and wide operating range which become a viewpoint in the research field of power of Aeronautics and Astronautics.
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。
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.
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.
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.
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