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火箭结构
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  rocket structure
     THE ANALYSIS OF RELIABILITY DESIGN FOR ROCKET STRUCTURE
     火箭结构可靠性设计分析
短句来源
     A New Method for Evaluating the Design of Rocket Structure
     一种评估火箭结构设计的新方法
短句来源
     This paper is a comprehensive report of reliability design for rocket structure.
     本文为火箭结构可靠性设计分析的综合性报告。
短句来源
     As to the large liquid launch vehicle and missile,it is so easy to occur the coupled vibration of the rocket structure with the propulsion system,leading to a disastrous consequences. This kind of coupled vibration is specially called in an English word POGO.
     对大型液体运载火箭和导弹来说,火箭结构的纵向振动与动力装置的振动很容易耦合而产生毁灭性后果,这种耦合有一个专门的名字,POGO。
短句来源
     Many engineers usually utilize a simplified criterion or objective function (e.g.full stress,minimum cost) to optimize the design of rocket structure.
     在火箭结构优化设计时,常采用一个简化的标准或目标函数(如全应力、最低费用)着手设计。
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  “火箭结构”译为未确定词的双语例句
     Strap-on carrier rocket is a kind of complex space structure.
     捆绑式火箭结构是一种复杂的航天结构。
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     Applying 3-D turbulent finite volume numerical algorithm validated, different operation status of Rocket Based Combined Cycle (RBCC) model with different structures and working conditions of primary rocket were simulated in ejector mode.
     应用经过校验的三维湍流有限体积数值算法,对引射模态下RBCC模型不同一次引射火箭结构和工作参数条件下的多种工作状态进行了模拟。
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  相似匹配句对
     Structure and Package of Rocket Firework
     火箭烟花的结构和包装
短句来源
     Compared the actuality of the structure of th
     *; 结构;
短句来源
     Using AFS algebra and AFS structure, any human ordinary fuzzy concept can be represented.
     结构
短句来源
     THE ANALYSIS OF RELIABILITY DESIGN FOR ROCKET STRUCTURE
     火箭结构可靠性设计分析
短句来源
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  rocket structure
The unique Fin-LokTM fin mounting system carries and distributes aerodynamic and thrust loads throughout an integrated rocket structure.
      


This paper is a comprehensive report of reliability design for rocket structure.For practical purposes, considering the reasonableness of reliability design and the convenience of traditional safety factor, the method of reliability safety factor is presented. These introduced factors are often smaller than tiaditional safety factors, therefore, the smaller weight of structure can be obtained on condition that reliability index required will be. satisfied.The structural reliability index and its division, general...

This paper is a comprehensive report of reliability design for rocket structure.For practical purposes, considering the reasonableness of reliability design and the convenience of traditional safety factor, the method of reliability safety factor is presented. These introduced factors are often smaller than tiaditional safety factors, therefore, the smaller weight of structure can be obtained on condition that reliability index required will be. satisfied.The structural reliability index and its division, general method of reliability design are briefly introduced. By virtue of reliability safety factor, the reliability design may be directly connected with experimental checks and some formulae of check are given, too. In addition, some concrete problems for structural strength in statistic are described. Some variation coefficients of structural strength and figures of reliability safety factor are given.

本文为火箭结构可靠性设计分析的综合性报告。从实用观点,考虑到可靠性设计的合理性以及传统安全系数设计的方便性,提出可靠性安全系数法。可靠性安全系数常比传统安全系数小,因而,在满足所要求的可靠性指标情况下,常可使结构重量减轻。 文中讨论了结构可靠性设计指标与分配;简介了可靠性设计的一般方法;通过可靠性安全系数,把可靠性设计与试验检验直接相联系,列出了试验检验算式。此外,综述了结构强度统计中的一些具体问题。文中给出了有关结构强度变差系数及可靠性安全系数图表,供查用。

According to the characteristics of the construction elasticity, liquid shaking and upright body moving of a launch vehicle, and by zeroes and poles of the transfer function of every parallel branch for platform, rate gyroscope and horizontal or vertical acce-lerometer etc., it determines automatically the biggest coefficient item of multi-item formula of the open-loop or closed-loop transfer function for the attitude system, and the value of this item. Then, it solves an optimal coefficient K* for pressing...

According to the characteristics of the construction elasticity, liquid shaking and upright body moving of a launch vehicle, and by zeroes and poles of the transfer function of every parallel branch for platform, rate gyroscope and horizontal or vertical acce-lerometer etc., it determines automatically the biggest coefficient item of multi-item formula of the open-loop or closed-loop transfer function for the attitude system, and the value of this item. Then, it solves an optimal coefficient K* for pressing roots, by the biggest value and the byte length of the computer to be used. And finally, it presses the roots by K* and successfully solves in no time the open-loop or closed-loop transfer function for the attitude system, and the zeroes and poles of the transfer function.

根据大型运载火箭的结构弹性,液体晃动和刚体运动的特性,由平台、速率陀螺和横(法)向加速度表等并联支路的传递函数零、极点,自动确定姿态系统开环或闭环传递函数多项式的最大系数项及其值,再由最大系数值和所用计算机的字长介出最佳压根系数K~*。最后用K~*进行压根,一次成功地求出姿态系统开环或闭环传递函数及其零、极点。

The Long March 2E (LM-2E) launch vehicle, a new member of the Chinese LongMarch family, is based on the highly reliable LM-2C. With four strap-on liquidboosters attached to the stretched core stage, it has a payload capabality of about 1 / 4 ofthe US Shuttle's, and is being offered to the world space launching market mainly as a launcher of the second generation of commercial communication satellites in the 1990s. The program will lay down the technical foundation for the development of new larger launch vehicles....

The Long March 2E (LM-2E) launch vehicle, a new member of the Chinese LongMarch family, is based on the highly reliable LM-2C. With four strap-on liquidboosters attached to the stretched core stage, it has a payload capabality of about 1 / 4 ofthe US Shuttle's, and is being offered to the world space launching market mainly as a launcher of the second generation of commercial communication satellites in the 1990s. The program will lay down the technical foundation for the development of new larger launch vehicles.

中国目前正在研制的长征二号E运载火箭是长征火箭家族中的新的一员,它以可靠性很高的长征二号C为基础,加大芯级,并捆绑四个液体助推器,运载能力相当于美国航天飞机的 1/4。长征二号E面向国际航天发射市场,主要将用于发射第二代商用通信卫星。这项研制计划将为我国大型新型运载火箭的研制打下基础。本文介绍了该火箭的结构、工艺、运载能力及发射等问题。

 
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