Thirdly, fuel control loop of ramjet is studied.
再次，冲压发动机燃油控制回路研究。
A simple, essentially tubular jet engine, such as a ramjet.
压式喷气发动机一种简单的，主要为管道式的喷气发动机，如。
A simple, essentially tubular jet engine, such as a ramjet.
冲压喷气发动机是这三种最简单的一种。
At present, the ramjet engine jet for military purposes to be optimistic.
目前，冲压式喷气发动机的军事用途被看好。
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。
A complete line of Horizontal Wet Process Equipment Incorporating Ramjet Technology.
结合冲压式技术，一条完整的湿流程设备水平线。
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。
In order to track and attack the aim effectively, the ramjet must meet the different attack-angles.
在实际飞行中为了有效的跟踪和攻击目标，必然要面对带攻角的情况。
The objective of these studies is to gather data that enable them to adapt the test chamber for ramjet tests.
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。
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。
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。
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。
Ramjet engines have traditionally used liquid fuel which is mixed with atmospheric air and burned to provide thrust for high-speed flight.
传统的冲压喷气发动机使用液体燃料并与大气中的空气混合燃烧，以提供高速飞行的推力。
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.
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。
MODEL 79 Meanwhile, McDonnell continued to seek an outlet for the principles and design simplicity developed in the XH-20 ramjet helicopter.
模型79与此同时，麦继续寻求出路的原则和设计开发的简单新华- 20喷气直升机。
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。
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。
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。
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。
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