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- Rocket Motor Igniter 火箭发动机点火器
- As the first rocket burns out,the second stage motor ignites. 火箭第一节燃料用完的时候,第二节就点燃了。
- As the first rocket burns out,the second-stage motor ignites. 当第一级火箭燃料烧尽时,第二级火箭的发动机就点燃了。
- As the first rocket burns out, the second-stage motor ignites. 当第一级火箭燃料烧尽时,第二级火箭的发动机就点燃了。
- As the first rocket burns out, the second stage motor ignites. 火箭第一节燃料用完的时候,第二节就点燃了。
- Taking aft-end igniter design for a rocket motor for example,design methods for ignition sequence,amorce quantity estimation and nozzle closure were described respectively. 以某型号发动机尾部点火设计为研究对象,对点火序列设计、点火药量的估算、喷管堵片的设计方法进行了阐述。
- Rocket motor cases and the specially designed production equipment therefor. 四、火箭发动机的壳体及为其专门设计的生产设备。
- Rocket motors have many advantages over other forms of propulsion. 火箭发动机比其他推进器有许多优点。
- Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails. 四个向外倾斜的喷管把固体火箭发动机的排气流分成四个相等的尾巴。
- Design method for aft-end igniter of small-scale solid rocket motor 小型固体火箭发动机尾部点火器设计方法
- There is a rocket motor on the satellite by which the direction of the satellite can be changed if necessary. 在卫星上还有一个火箭马达,必要时可以用它来改变卫星的方向。
- According to the requirement of pasty propellant rocket motor, a composite plasma igniting plan was adopted. 摘要根据膏体推进剂火箭发动机。
- The influence of structure axial vibration on the internal ballistics of solid rocket motor was investigated. 文中研究了固体发动机结构的轴向振动对燃烧室内弹道性能的影响。
- Investigated charring erosive characters of internal insulation of solid rocket motor under flight acceleration. 研究了固体火箭发动机内绝热层在飞行加速度条件下的炭化烧蚀特性。
- The thrust vector control(TVC) performance test of solid rocket motor is presented in this paper. 本文介绍了固体火箭发动机水下推力矢量特性试验。
- A response surface method(RSM) for structure reliability analysis of solid rocket motor(SRM) grain was presented. 发展了一种固体火箭发动机药柱结构可靠度分析的响应面法。
- The preliminary design data for the k APPA-DX rocket motor is presented in this web page. 初步设计数据的K appa -的DX火箭发动机是在这方面的网页。
- Buckling analysis on rear dome of solid rocket motor case was studied by means of ANSYS. 用ANSYS软件对固体发动机壳体后封头进行了外压屈曲分析。
- Crose J G.Reliability of solid rocket motor cases and nozzles[R].NTI S,N93-22103. 王松柏.;固体火箭发动机壳体结构的动态可靠性设计[J]
- Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor. 应用有限单元法研究固体火箭发动机不稳定燃烧中的喷管阻尼,并用波衰减对比法进行了试验研究。