1)rocket nozzle火箭喷管
1.Calibration equipment for rocket nozzle motion testing and its error analysis火箭喷管三维运动测试的校准装置及误差分析
2.Numerical simulation of subsonic,transonic and supersonic flow fields of rocket nozzle are completed using two-dimensional unsteady bicharacteristic method.采用二维非定常特征线法数值模拟火箭喷管亚、跨和超音速流场,克服了三维定常特征线法不能求解亚、跨音速的缺陷,获得火箭喷管侧向推力随时间、压强的变化曲线。
3.In this paper,we analyze the property of nonequilibrium flow of chemical reactioninside rocket nozzle and design a accessible plan for stiff equation by continent method.本文分析了火箭喷管跨音速化学非平衡流的流体和化学特性、一元动力流的计算方法ＯＤＫ，对刚性比很大的Ｓｔｉｆｆ方程组采用组合方法设计了求解方案，并与ＤａｖｉｄＡ。
英文短句/例句
1.A NEW METHOD TO REDUCE ABLATIVE HARM ON THROAT FOR SMALL ROCKET NOZZLE减轻小型固体火箭喷管喉部烧蚀危害的新措施
2.Calibration equipment for rocket nozzle motion testing and its error analysis火箭喷管三维运动测试的校准装置及误差分析
3.The design of the rocket nozzle also has much to do with the behavior of the exhaust and the resulting velocity of the vehicle itself.火箭喷管的设计与排气的性能及飞行器本身的有效速度也有很大关系。
4.nozzle diaphragm喷管挡栅板 -固体火箭发动机的
5.A METHOD FOR DESIGN OF SMALL BEVEL NOZZLE OF ROCKET ENG INES火箭发动机小斜切角喷管的设计方法
6.The Development of Integral Design of Solid Rocket Motor Nozzle;固体火箭发动机喷管热结构CAD设计
7.Research progress of CMC used in rocket motor nozzle and nozzle throat火箭发动机喷管喉衬用CMC研究进展
8.Application of functional link neural networks to machining rocket jet函数链神经网络在火箭大喷管加工中的应用
9.Investigation of Aft-End Internal Flows in Solid Rocket Motors with Submerged Nozzle;固体火箭发动机潜入喷管背壁区流动研究
10.Study on Canted Scarfed Flow-backward Multi-nozzle SRM;小型斜置倒流多喷管固体火箭发动机研究
11.Mechanical Capability Study on Conical Nozzle of Rocket Engine by ANSYS火箭发动机锥形喷管ANSYS力学性能分析研究
12.Numerical simulation of gas-particle flow in nozzle of solid rocket motor固体火箭发动机喷管气固两相流动的数值模拟
13.Simulation and Experiment of Thrust Performance for Solid Rocket Motor with Angle-cut Nozzle斜切喷管固体火箭发动机推力特性仿真与试验
14.effect of rocket exhaust on radio wave propagation火箭喷焰电波传播效应
15.air-breathing rocket engine空气喷气火箭发动机
16."supersonic ""rocket"" burner""超音速""火箭式""喷燃器"
17.Thermal and Thermal-Structural Couple Analysis of the Rosette Carbon-Carbon Nozzle in SRM;碳/碳固体火箭发动机柔性喷管热及热－结构耦合作用研究
18.The Particle Parameter and Temperature Measurement for the Wake of Solid Propellant Rocket Motor(SRM)固体火箭发动机喷管出口粒子参数和尾流温度测量方法研究
相关短句/例句
double nozzled rocket双喷管火箭(火)
3)Rocket engine nozzle火箭发动机喷管
4)Solid rocket nozzle固体火箭喷管
5)rocket nozzle火箭发动机喷管
6)rocket engine throat火箭发动机喷管喉部<火>
延伸阅读
固液混合火箭推进剂(见火箭推进剂)固液混合火箭推进剂(见火箭推进剂)solid-liguid hybrid rocket propellant guye hunhe huoiian tui)in)i固液混合火箭推进剂(s olid一Iiguid hy-brid rocket proPellant)见火箭推讲齐，}_
