1)LOX /kerosene rocket engine液氧/煤油火箭发动机
1.The procedure of the throttle valve core contour optimized design for LOX /kerosene rocket engine was described in this paper.简要叙述了液氧/煤油火箭发动机节流阀阀芯型面优化设计的方法。
2)LOX / kerosene staged combustion cycle rocket engine液氧/煤油补燃火箭发动机
1.Low frequency characteristics analysis of LOX / kerosene staged combustion cycle rocket engine液氧/煤油补燃火箭发动机氧路低频动特性分析
英文短句/例句
1.Low frequency characteristics analysis of LOX / kerosene staged combustion cycle rocket engine液氧/煤油补燃火箭发动机氧路低频动特性分析
2.ADVANCED MODEL OF STATIC CHARACTERISTIC FOR LIQUID OXYGEN/KEROSENE液氧/煤油高压补燃火箭发动机非线性稳态模型——考虑推进剂温升与密度变化
3.Study on start-up of the staged combustion LOX/kerosene rocket engine液氧/煤油补燃循环发动机起动过程研究
4.Research on the low frequency characteristics of LOX/kerosene staged combustion cycle engine液氧/煤油补燃发动机低频频率特性研究
5.Cycle Power Balance Analysis for Liquid Rocket Engine with LO_2/RP-1 Propellant Combination液氧/煤油推进剂液体火箭发动机循环动力平衡分析
6.Investigation of GO_2/kerosene thrust chamber of the main rocket engine for the RBCC propulsion systemRBCC推进系统主火箭发动机气氧/煤油推力室研究
7.Numerical Simulation of Combustion Instability of a LOX/GH_2 Rocket Engine氢氧火箭发动机不稳定燃烧数值研究
8.The Research on Characteristic Performance of Combustion Flow Field in Secondary Combustion Chamber for Extended Range Solid Rocket Ramjet增程固体火箭冲压发动机补燃室燃烧特性研究
9.Influence of mass flux of oxidizer on regression rate of solid fuel in hybrid rocket motors氧化剂质量通量对固液火箭发动机中固体燃料退移速率的影响
10.Techniques of kerosene booster turbopump for LOX/kerosene staged combustion cycle engine液氧/煤油发动机煤油预压涡轮泵技术
11.An Innovative Partition Model of Liquid Rocket Engine Combustion Chambers液体火箭发动机燃烧室的一种分区模型
12.Numerical Simulation of Working Process of Combustion in Hybrid Rocket Motor;固液火箭发动机燃烧室工作过程数值模拟
13.The rocket engine carries with it the oxygen of its own .火箭发动机自带氧气。
14.Effects of Jet Rotational Angle on the Second Combustor of Boron-based Propellant Solid Rocket Ramjets含硼固体火箭冲压发动机中燃气旋流角对补燃室的影响
15.High and low temperature test technology of kerosene of the LOX/kerosene engine液氧/煤油发动机煤油高低温试验工艺技术
16.The liquids employed for rocket propulsion are called propergols.用于火箭发动机的液体称为液体火箭推进剂。
17.Research on the Secondary Combustion Chamber Operation Process of Boron-Based Propellant Ducted Rockets;含硼推进剂固体火箭冲压发动机补燃室工作过程研究
18.Three-Dimensional Numerical Simulation of Afterburner Flow Field of Solid Rocket Ramjet固体火箭冲压发动机补燃室流场三维数值计算研究
相关短句/例句
LOX / kerosene staged combustion cycle rocket engine液氧/煤油补燃火箭发动机
1.Low frequency characteristics analysis of LOX / kerosene staged combustion cycle rocket engine液氧/煤油补燃火箭发动机氧路低频动特性分析
3)liquid-oxygen motor液氧火箭发动机<火>
4)LH_2/LOX rocket engine液氢液氧火箭发动机
1.Non-linear static charactersitic simulation and analysis for large LH_2/LOX rocket engine;液氢液氧火箭发动机非线性静态特性仿真与分析
5)LOX/kerosene engine液氧/煤油发动机
1.Waste water reclamation for LOX/kerosene engine test;液氧/煤油发动机试验废水的循环使用
6)hydrogen/oxygen liquid propellant rocket engine氢/氧液体火箭发动机
1.Mass analysis of pump-pressurized hydrogen/oxygen liquid propellant rocket engine;泵压式氢/氧液体火箭发动机质量分析
延伸阅读
液氧分子式：O2CAS号：性质：淡蓝色透明液体。用作低温液体推进剂的氧化剂。沸点-183℃。冰点-218.9℃。沸点时密度1.14g/cm3。无毒，化学稳定。借助压缩与冷却交替循环进行的方法将空气液化，再将液化空气精馏，即得液氧。与液氢组成的高能低温液体推进剂，已用于发射通讯卫星、宇宙飞船、航天飞机等的运载火箭中。
