ramjet

Influence of air mass flow rate ratio on combustion efficiency of solid rocket ramjet with two air inlets

二次进气流量比对固冲发动机燃烧效率的影响

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 purpose of the paper is to study the interior ballistics in nozzleless booster with solide propellant rocket ramjet engine with one dimension quasi steady equations.

采用一维准定常方法，对整体式固体火箭冲压发动机的无喷管助推器内弹道进行了计算。

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。

Using k-ε turbulence model and one step eddy-dissipation model, numerical studies on the reacting flow field of solid rocket ramjet with secondary air inlets were carried out. Influence of mass flow ratio on combustion efficiency and temperature field was analyzed.

采用k-ε湍流模型及单步涡扩散化学反应模型，对二次进气结构的固体冲压发动机补燃室的反应流场进行数值模拟，分析了二次进气流量比对燃烧效率与温度场分布的影响。

Boron particle combustion model and turbulent no-premixed combustion model were established by using King theory and probability density function in order to study the reacting fuel-rich flow field laden with boron particle in the ramjet combustor. Some obtained numerical results were tested by examination.

以King模型模化硼粒子燃烧，以几率密度模型模化湍流燃烧，对含硼贫氧推进剂固体火箭冲压发动机补燃室流场进行数值研究，并与试验结果进行了对比。

research of new conceptive rotated ramjet

新概念旋转冲压发动机的研究与分析

The theoretical specific impulse formula for two-phase flow in nozzle of rocket-ramjet engine is derived on the basis of similarity to that used for rocket engine.

本文导出了类似于火箭发动机的火箭冲压发动机喷管的两相流动理论比冲公式；

The flux vector splitting method is adopted to solve the 2-D Euler equations and a numerical simulation is conducted for the division-flow inlet of Dual Combustor Ramjet ( DCR) as well as the cold-mixing flow field of both flows from a dump combustor and from a supersonic inlet.

采用矢通量分裂法求解2D－Euler方程组，对亚燃／超燃双重燃烧冲压发动机（DCR）进气分流流场及其双重燃烧的冷态掺混流场进行了数值模拟。

Effect of structure pattern of pasty propellant ramjet motors on combustion efficiency

膏体冲压发动机构型对燃烧效率的影响研究

Thermodynamic calculation method of chemical equilibrium and chemical non-equilibrium for water ramjet together with corresponding applicable conditions were introduced. Then the temperature in the ramjet combustor was calculated and compared with experimental data. Thermodynamic calculation method of tailrace tunnel ventilation process in hydropower stations

简述了水冲压发动机化学平衡与非化学平衡热力计算方法及相应的适用条件，计算了试验发动机补燃室温度，并与试验数据进行了对比分析。水电站无压尾水洞引风过程热工计算方法

The use of solid fuel ramjet assisted range projectiles can greatly improve artillery range. The projectile has a high flying speed, which can shorten the whole ballistic flight time, increase the ability of penetration, and it has a good utilization prospect.

利用固体燃料冲压发动机增程的炮弹，能够很大程度的提高炮弹的射程，且炮弹拥有较高的飞行速度，缩短全弹道飞行时间，提高突防能力，具有很好的利用前景。

experimental study of a variable-area propelling nozzle dual-mode ramjet

可调喷口双模态冲压发动机试验研究

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。

Theoretical specific impulse for two-phase flow in nozzle of rocket-ramjet engine& a simple estimation method

火箭冲压发动机喷管的两相流动理论比冲&一种简单估算方法

performance analysis of the liquid fuel ramjet

液体冲压发动机特性分析

numerical simulation for ramjet cruising stage fuel-supplied oscillation

某型弹用冲压发动机巡航段供油振荡的数值仿真

Hypersonic ramjet engine Research on the Atomization Characteristics and Mechanism of Air-blast Nozzles and Development of the CWS Burner for Gasification

高超音速冲击式空气喷气发动机气力式喷嘴雾化机理研究及水煤浆气化喷嘴的开发

on top was an 18-ft diameter, twin-bladed rotor carrying a 10-lb ramjet burner at each of the tips.

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。

The research of thermal protection system for the ramjet combustor of the integral solid ducted rocket motor is an important component of the development of the solid ducted rocket motor.

补燃室热防护系统研究是飞航导弹固冲发动机研究的一项重要内容。

numerical study of the throttle characteristic about the ramjet inlet and mixing section

冲压发动机进气道和掺混段节流特性数值研究

one answer could come from a supersonic combustion ramjet, known as a scramjet, which would scoop oxygen from the atmosphere as it ascends.

有一个可能的解决方法，就是超音速燃烧冲压喷射引擎（supersoniccombustionramjet，简称scramjet），它在升空时会努力从大气吸入氧氧。

The analysis results show that the calculation method is appliable for water ramjet.

分析结果表明，该热力计算方法适用于水冲压发动机。

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 rockets give the planes and missiles enoughspeed to make the ramjet engine workable.

这种助推火箭为飞机和导弹提供足够的速度,以使冲压式喷气发动机可以开动工作.

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.

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。

effect of structure parameter on nozzle performance of bubbly water ramjet engine

结构参数对两相冲压发动机喷管性能影响分析

Study of Ramjet Thrust Control System

冲压发动机推力控制系统研究

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。

digital electronic control system of a liquid fuel ramjet engine

液体冲压发动机数字电子控制系统换