ramjet engine

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 operation principles of adjustment programs and circuits of the fuel regulation system for a ramjet engine at high altitude are introduced in detail . The measuring methods are also described .

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。

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

Hardware-in-the-loop simulation of a liquid fuel ramjet engine control system

液体冲压发动机控制系统半实物仿真

Numerical study of the ramjet engine inner flow before ignition

冲压发动机点火前内流场数值仿真研究

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

Dynamic Properties Research of a Liquid Fuel Ramjet Engine at High Altitude and High Speed

高空高速液体燃料亚燃冲压发动机动力特性研究

Fuel rich propellant for adjustable fuel mass flow Solid Ramjet Engine

用于燃气流量可调固冲发动机的贫氧推进剂

Investigation on ground direct-connect test technology for water ramjet engine

水冲压发动机地面直连试验技术研究

Numerical simulation of effect of disturbing on starting state of ramjet engine inlet

扰动对超声速进气道起动状态影响的数值模拟

Design and wind tunnel test of an axisymmetric inlet for ramjet engine

冲压发动机用轴对称进气道设计和试验

A Method of Thrust Regulation for the Solid-Liquid Rocket Ramjet Engine

固液火箭冲压发动机推力调节的一种方法

Geometry and structure of ramjet engine are simple , formed mainly with panel structures .

冲压发动机结构简单，主要由壁板结构构成。

Investigation on the enhanced cooling of combined ramjet engine inlet of space craft

组合式发动机进气道的冷却研究

Calculation of combustion efficiency of dump combustor in ramjet engine

冲压发动机突扩燃烧室燃烧效率的计算方法

As a result , the process of organizing combustion is important to realize the best performance of water ramjet engine .

因此，水冲压发动机燃烧组织过程的好坏是其性能优势能否得到充分发挥的关键。

Effect of aeration parameter on inner thrust of underwater two-phases ramjet engine data logger

通气参数对水下两相冲压式发动机内推力影响的数值模拟研究

Exceeded vibration arises during ramjet engine operation , which affects the safety of ramjet operation significantly .

发动机工作时产生剧烈振动，对发动机的安全运行产生严重影响。

Furthermore , test on the influence of metal content of propellant to the performance of water ramjet engine is carried out .

此外，还进行了不同金属含量推进剂性能的对比试验，试验结果表明今后开展高金属含量水冲压发动机研究的必要性。

The simulator was connected with a real control system of a liquid fuel ramjet engine through the input and output interfaces .

实时数字仿真器通过输入输出接口与液体冲压发动机的实际控制系统进行联接，组成液体冲压发动机、弹体和发动机控制系统半实物仿真系统。

At present , the study of water ramjet engine is in its infancy . The experimental information with small sample characteristics is appeared .

目前国内水冲压发动机研究处于初级阶段，试验信息具有小子样特征。

Ramjet engine is ideal propulsive equipment for new supersonic missile , and supersonic inlets are important components .

冲压发动机是新一代超声速导弹理想的动力装置，超声速空气进气道是它的一个重要部件。

Ramjet engine has been applied to various high-speed vehicle widely because of its light weight , small volume , simple structure , good performance .

冲压发动机独特的高速冲压原理造就了其重量轻、体积小、结构简单、性能好等优点，广泛地应用于各种高速飞行器。

There are three different types of propulsion system in hypersonic aircraft , such as rocket engine , ramjet engine and combination engine .

目前，高超声速飞行器的推进系统主要有三种类型：火箭发动机、冲压发动机和组合发动机。

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。

Beset with attackers or controversy or conflict . The Influence of Attack Angle on the Inlet of the Ramjet Engine

被进攻者围困的或被冲突和争论包围的。攻角对炮射冲压发动机进气性能的影响

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

The ramjet engine has many advantages such as simple structure , light weight , little volume , big ratio of pushing and gravity , low cost , and etc.

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。

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。

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。