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火箭设计
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  rocket design
     On the Problems of Gyration Reduction etc in Microgravity Rocket Design
     微重力火箭设计中减旋方案等问题
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  “火箭设计”译为未确定词的双语例句
     The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation, indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design.
     表明在引射火箭设计时,应结合引射火箭的结构和流动参数对二次喷管出口面积进行优化设计,以达到最佳推力性能。
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     Furthermore, it deduces propelling effort magnitude of a propellerand provides a reference to rocket designers and teaching workers.
     可供火箭设计工作者、教学工作者参考。
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  相似匹配句对
     A NEW METHOD OF ROCKET NOZZLE DESIGN
     设计火箭喷管的新方法
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     To design the G.
     在设计G.
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     Design
     设计
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     The rocket general-structure designer who str-died on his own to be expert
     自学成才的火箭设计
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  rocket design
Results from performance and life testing of a 22 N rocket design with N2OJMMH propellants were reported first.
      
Rocket design is further complicated by manufacturing and transportation constraints.
      
The second reason for removing burn time as a criterion is that current regulations unnecessarily drive rocket design.
      


According to the requirements for the high burning rate propellants, which are proposed by "761" sounding rocket dessgn, the present paper has studied how to increase burning rate and other performance of the CTPB propellant. The present paper shows that adding Fe_3O_4 as a burning rate catalyst to base formulation of CTPB propellant and inserting the axial long Ag-line in the propellant grain, may greatly enhance the burning rate and insure other performances. The experimental results prove that the burning...

According to the requirements for the high burning rate propellants, which are proposed by "761" sounding rocket dessgn, the present paper has studied how to increase burning rate and other performance of the CTPB propellant. The present paper shows that adding Fe_3O_4 as a burning rate catalyst to base formulation of CTPB propellant and inserting the axial long Ag-line in the propellant grain, may greatly enhance the burning rate and insure other performances. The experimental results prove that the burning rate of this propellant may arrived at about 40mm/sec. The Combustion performance and other performances of this propellant are steady and reliable. Therefore, this propellant has met the requirements of the"761"sounding rocket. This propellant may also be used to other rocket motor which is burned from the end.

根据“761”探空火箭设计提出的高燃速推进剂要求,本文进行了提高端羧基聚丁二烯推进剂燃速和其他性能的研究。本文提出:在端羧基聚丁二烯推进剂基础配方中加入Fe_3O_4燃速催化剂,并在推进剂药柱轴向嵌入长银丝,可以大幅度地提高燃速,并保证了其他性能。实验结果表明:这种推进剂的燃速可达40毫米/秒左右,燃烧性能及其他性能稳定可靠,满足“761”探空火箭的各项要求,也可以应用于其他端面燃烧的火箭发动机中。

On the basis of theoretical calculation analysis and experiment research,the paper proposes a new raising non-con-control rocket distrubution way.which is a step propulsion plan. It introduces a method which is sued to find some main parameters con-nected with the step propulsion rocket, and a concrete plan to realize themethod. Furthermore, it deduces propelling effort magnitude of a propellerand provides a reference to rocket designers and teaching workers.

本文在理论计算分析和试验研究的基础上提出了提高无控火箭密集度的一个途径,即阶梯推力方案。本文介绍了阶梯推力火箭几个主要参数的确定方法及其具体方案,并提出了助推器的推力范围。可供火箭设计工作者、教学工作者参考。

The National Space Development Agency of Japan(NASDA) is developing the H-Ⅱlaunch vehicle entirely with Japanese technology as the Japan's main launch vehicle in the next generation. It is a two-stage, cryogenic vehicle, augmented by two Solid Rocket Boosters.The payload capability of H-n is 4.0 tons into GTO inclined at 28.5 deg. and 10 tons into Low Earth Orbit and 5 to 6 tons into sun-synchronous orbit. It may meet the demand for larger satellite launches at a lower cost.This article describes the status...

The National Space Development Agency of Japan(NASDA) is developing the H-Ⅱlaunch vehicle entirely with Japanese technology as the Japan's main launch vehicle in the next generation. It is a two-stage, cryogenic vehicle, augmented by two Solid Rocket Boosters.The payload capability of H-n is 4.0 tons into GTO inclined at 28.5 deg. and 10 tons into Low Earth Orbit and 5 to 6 tons into sun-synchronous orbit. It may meet the demand for larger satellite launches at a lower cost.This article describes the status of the H- n launch vehicle in detail.

为了满足以低成本发射大型卫星的要求,日本宇宙开发事业团正在研制H-Ⅱ运载火箭,以作为其90年代的主要运载工具。目前,宇宙开发事业团正在进行该火箭的D阶段的研究和进行多种类型的研制试验。1988年已开始制造H-Ⅱ的地面试验型火箭(GTV)和第一枚飞行型(FM)火箭,第一次试飞计划在1992年初进行。本文将详细介绍H-Ⅱ火箭的设计和研制现状。

 
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