氢氧发动机

氢氧发动机上阶跃式混合比调节&新型液体推进技术

A new propulsion technique-step control of mixture ratio in hydrogen-oxygen rocket engine

高压补燃氢氧发动机中的低温技术

Cryogenic technique of high pressure closed cycle hydrogen oxygen engine

氢氧发动机试验台低温系统设计与试验研究

Design and Test Research of Cryogenic System for Hydrogen Oxygen Engine Test Bed

氢氧发动机实现单级入轨的优化分析

Optimal Analysis of Hydrogen - Oxygen Engine for SSTO

氢氧发动机气液同轴式喷嘴流量特性研究氢氧同轴式喷嘴燃烧性能试验研究

A study on flowrate characteristics of gas-liquid coaxial atomizers in hydrogen / oxygen rocket engine

氢氧发动机试验低温管路绝热影响的研究

Research on the Effect of Cryogenic Pipeline Thermal Insulation in Hydrogen / Oxygen Engine Test

氢氧发动机试验安全技术

Safety method in hydrogen-oxygen rocket engine test

国外氢氧发动机研制的一些近况

Development Status of Foreign Hydrogen Oxygen Engines

氢氧发动机推力室化学反应流场计算

Numerical Simulation of Chemical Reacting Flow in H 2 / O 2 Rocket Engine Thrust Chamber

周日，高推力氢氧发动机进行了100秒测试。

The ground test of the high thrust hydrogen oxygen engine lasted 100 seconds on Sunday .

结果显示：三组元发动机性能比氢氧发动机高10%。

Results show that the performance of tripropellant engine is 10 % higher than that of LH / LOX engine .

根据现有的氢氧发动机的研制现状，针对全流量补燃发动机进行了系统参数的平衡计算。

Based on the development status of the H_2 / O_2 rocket engine , the system parameter balance calculations were executed .

火炬式电点火器在国外氢氧发动机上得到了广泛应用。电点火器烟火特性的研究

Spark igniter is widely used in cryogenic liquid rocket engines in the world . Pyrotechnic Characteristics Research on a Electric Igniter

最后还提出一种渐变式氢氧发动机，用该发动机实现单级入轨，能使起飞质量降低16.7%。

At last , the gradual hydrogen oxygen engine is put forward . The launch mass will be reduced 16.7 % by using this engine .

应用所建立的模型与算法对双工氢氧发动机内部喷雾燃烧流动与传热过程进行了数值仿真。

The spray combustion flow and heat transfer progresses of dual-operation LOX / Hydrogen engine are simulated with the models and method founded in this paper .

介绍了系统动态仿真技术在我国高压补燃氢氧发动机研制中的应用。

The application of system dynamic simulation technology to the development of LOX LH 2 staged combustion rocket engine in our country is introduced in this paper .

提出应加快我国大推力氢氧发动机的研制，并积极开展各项先进技术的预先研究工作。

The suggestion of speeding up the development of a large thrust LOX / LH2 engine and taking vigorous action to research advanced propulsion technology are proposed .

文中对发动机的一些研制情况作了回顾，对YF－73和YF－75氢氧发动机的设计特点、飞行结果作了简单叙述。

This paper presents a brief description of these engines . The design features and flight results of YF 73 and YF 75 hydrogen oxygen engines are summarized .

根据现有材料和技术，分析了给定任务下氢氧发动机实现单级入轨的最小起飞质量。

The least launch mass of hydrogen oxygen engine for single stage engine under the certain conditions is determined on the basis of the present technology in this paper .

一种低温导热绝缘胶粘剂用于氢氧发动机系统表面温度传感器的端封和胶接安装。

The adhesive of low temperature heat conduction and insulation is utilized to the seal end and bend to install the surface temperature sensor of the hydrogen oxygen engine system .

论述了全流量补燃循环氢氧发动机的工作过程，并给出了基于这种循环方式的发动机的系统简图。

The working process of the H_2 / O_2 engine full-flow staged combustion cycle is discussed , and the system sketch of the rocket engine based on this cycle is presented .

结果表明：渐变式三组元发动机比传统双模式发动机或渐变式氢氧发动机的性能分别高25%和11%。

Results show that performance of gradual tripropellant engine was 25 % higher than that of traditional tripropellant engine and 11 % higher than that of gradual LOX / LH_2 engine .

由单级入轨弹道、运载器质量和氢氧发动机性能计算模型，优化得到为实现单级入轨的氢氧发动机基本参数。

The basic parameters of the engine to single stage to orbit are optimized by the trajectory model of single stage to orbit , the mass model of reusable launch vehicle and the performance model of hydrogen oxygen engine .

氢氧火箭发动机预燃室喷注器特性研究

The Study of Preburner Injector Characteristics for the Hydrogen Oxygen Engine

氢氧火箭发动机不稳定燃烧数值研究

Numerical Simulation of Combustion Instability of a LOX / GH_2 Rocket Engine

低温技术在氢氧火箭发动机试车台上的应用

The Application of Cryogenic Technology in LOX / LH 2 Rocket Engine Test Stand

氢氧火箭发动机高速氧涡轮泵转子动力学特性研究

Reactive oxygen species Research on Rotor Dynamics of LOX Turbopump of LH_2 / LOX Engine

基于气动谐振点火器的氢氧变轨火箭发动机地面点火试验

Ground Ignition Test of an Orbit Maneuver H_2 / O_2 Thruster Based on Gas Dynamic Resonance Igniter

结合气动谐振点火器进行头部设计的氢氧变轨火箭发动机是一项新颖化学火箭推进技术，尤其适于空间站应用。

Orbit maneuver hydrogen-oxygen thruster based on gas dynamic resonance igniter is a novel chemical propulsion technology especially prospective in space station application .

为研究轻型、可靠、环保的空间站机动变轨发动机，在氢氧液体火箭发动机头部设计中引入了新型气动谐振点火技术。

To develop light , reliable , sanitary space station maneuverable orbital transfer thruster , the novel gas dynamic resonance ignition method was applied .