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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.

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。The neural network is adopted to study the burning rate identification of the solid fuel ramjet.

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上方是一个18英尺长，直径双转子叶片进行了10磅冲压发动机燃烧在每个秘诀。On top was an 18-ft diameter, twin- bladed rotor carrying a 10-lb ramjet burner at each of the tips.

冲压式气动激光器是在冲压发动机和气动激光器的基础上发展起来的一个新概念。Air-breathing gas dynamic laser is developed as a new conception based on ramjet and gas dynamic laser.

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.

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。So it is of very important science meaning and practice value to simulate the circle flow field of the ramjet shell.

没有扭矩冲压发动机系统取消了传统的转子需要一个尾巴，使大黄蜂非常简单机械。The no-torque ramjet system eliminated the need for a conventional tail rotor, making the Hornet very mechanically simple.

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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.

中国已经拥有这种分离式火箭助推器和冲压发动机技术，但超音速燃烧冲压发动机是一个更大的挑战。China already has such segmented solid rocket motor and ramjet capabilities today, but scramjets are a much greater challenge.

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.

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。Advanced ramjet technologies are also important for scramjet development, and the Chinese have been active in this area for decades.

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。The investigation lays a fine foundation for realizing stable high efficient combustion based on the thermal throat RBCC ramjet mode.

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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。Ramjet engines have traditionally used liquid fuel which is mixed with atmospheric air and burned to provide thrust for high-speed flight.

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。The necessity of flow regulation system in solid ramjet is presented, and the scheme of gas-fired flux adjustment about generator is analyzed.

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.

冲压发动机具有结构简单、重量轻、体积小、推重比大、成本低等一系列优点。The ramjet engine has many advantages such as simple structure, light weight, little volume, big ratio of pushing and gravity, low cost, and etc.

在对药柱式水冲压发动机内流场进行必要、合理简化的基础上，建立了适用于药柱式水冲压发动机燃烧组织过程研究的数值计算模型。On the basis of predigest the process of fluxion in the engine with reason, numerical model is developed for column-style propellant water ramjet engine.

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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。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.

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.

对于泵压式变推力发动机和先进的冲压发动机，需要涡轮泵变工况工作，涡轮泵变工况性能是该类发动机研究的一个重点。The capability of turbo-pump working in variable conditions is required and important for pump-pressurized variable thrust rocket engine and ramjet propulsion.