火箭发动机

The ignition of the solid rocket motor is a very complex physical and chemistry process, which is composed of three component phases: ignition delay, flame spreading and chamber filling.

固体火箭发动机的点火是一个十分复杂的物理化学过程，包括三个阶段：点火延迟、火焰传播和燃烧室气体充填。

The flow field of exhaust gas in Rocket Motor is a very complex physical and chemical process.

火箭发动机的燃气流是一个非常复杂的物理化学过程，其中的混合组分在高温，高压下，彼此间存在相互反应，混合气体常数、比热、绝热指数等都随温度和组分浓度等因素不断变化。

According to the character of the B/KNO3 fire composition,three igniters with different charging structure are comparative tested and analyzed,and aimed at the parameters of the electric igniter,calculation and design are made for the ignition charge,intermediate charge and igniter charge ring,then the charging structure of electric igniter for a certain solid rocket motor is determined.

基于B/KNO3点火药的特性，采用三种不同药型的点火具装药进行对比试验和分析，并针对电点火具的性能指标要求，分别对传火药、过渡药、点火药环进行了计算和设计，确定了适用于某固体火箭发动机用电点火具装药的药型。

Jet flow ; rocket motor ; double nozzle jet ; computational fluid dynamics

燃气射流；火箭发动机；双喷管射流；计算流体力学

3D two-phase internal flow field of SRM with long-tail nozzle was simulated by means of Eulerian-Lagrangian two-phase method.

采用欧拉-拉格朗日两相方法模拟了带长尾喷管的固体火箭发动机三维两相内流场。

In the area of high technology of China, the developing technology of cryogenic thermodynamic process and heat transfer has resulted in the Shenzhou-V man-carrying space ship, Fengyun-III meteorological satellite and magnetic suspension train. Manufacturing of fuel (liquid hydrogen and liquid oxygen) of a cryogenic rocket, the cryocooler used to cool down infrared sensors, cryogenic-condensation vacuum pump used in manufacturing of semiconductors, super-conduct quantum interferometer and liquefied natural gas technology are all outcomes of the studies on cryogenic thermodynamic process and heat transfer. In these areas, there are many unexploited sub-areas. Therefore, cryogenic thermodynamic process and heat transfer is a developing study area, and is await more jobs by the younger generation.

在高科技领域，我国空间探索用&神州五号&载人飞船的成功发射、&风云三号&气象卫星的可靠运转以及磁悬浮列车技术等都与低温热力过程与传热技术的研究进展密切相关的，低温火箭发动机液氢液氧燃料的生产、红外传感器冷却的低温制冷机、半导体制造业用的低温冷凝真空泵、超导量子干涉仪与液化天然气的储运等技术都是低温热力过程与传热技术研究发展的产物，且有很多新技术有待于开发，是一个与时俱进、不断开拓的领域，有待于有志者去开发。

In our country the crafts of mandril mold stripping of the solid-rocket engine is all in the artificial state for a long time.Thus there is no guarantee in the production.

我国固体火箭发动机顶芯脱模工艺长期以来都处于人工借助器械脱模的状态，安全生产没有保障。

It is quite straightforward to determine the rocket motor Total Impulse and propellant Specific Impulse from a thrust-time curve obtained from static testing.

这是很简单，以确定火箭发动机的总冲和推进剂的具体冲动从一个推力时间曲线所得的静态测试。

To reveal aft end internal flow feature of a solid rocket motor with submerged nozzle, a two dimension cold flow test model with rectangular channel was designed The cold gas simulation was based on geometric similarity and aerodynamic analogy Mean and fluctuating velocity field was measured using phase doppler particle analyzer It showed that the flow separates at upstream of the submerged nozzle and reattaches on the tip of the nozzle nose A relatively steady recirculation zone formed in...

为了揭示含潜入喷管的固体火箭发动机尾部流动特征，按照几何相近和气动相似原则设计了通道为矩形的二维冷流实验模型，利用相位多普勒粒子分析仪对燃烧室尾部气流的时均速度和湍流脉动速度进行了测量。实验结果表明气流在潜入喷管入口上游发生分离，再附点位于喷管前端部外侧，背壁空腔内形成一个较为稳定的回流区，流场的轴向和横向湍流强度都比较大

NC cloth winding machine is special equipment that wind SRM's nozzle and prats of bearing ablation , heat protection , missile cone , emitter and astro navigation aircraft parts with bakelite .

数控布带缠绕机是用碳/酚醛，高硅氧/酚醛预浸胶带缠绕固体火箭发动机喷管，耐烧蚀，防热材料零部件，导弹鼻锥，发射筒以及宇航飞行器防热零部件的专用设备。

For a big chunk of credit-card losses; the number of filings (and thus charge-off rates) would be rising again, whether

年美国个人破产法的一个改动使得破产登记急速下降，而后引起了信用卡大规模的亏损。

Eph. 4:23 And that you be renewed in the spirit of your mind

弗四23 而在你们心思的灵里得以更新