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低燃温
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  low flame temperature
     Adjustment on the Combustion Performance of Low Flame Temperature and Low Burning Rate Double Base Propellant
     低燃速低燃温双基推进剂燃烧性能的调节
短句来源
     The combustion performance, thermal decomposition, and quenched surface appearance and element distribution of double-base (DB) propellant containing general lead and copper salt catalysts with low burning rate and low flame temperature were investigated.
     研究了含普通铅、铜盐催化剂的低燃速、低燃温双基推进剂的燃烧性能、热分解性能及熄火表面形貌特征和元素分布。
短句来源
     The results indicated that general lead and copper salt catalysts used in common DB propellants also had catalytic effect on DB propellant with low burning rate and low flame temperature,and also have great effects on thermal decomposition.
     结果表明,适用于普通双基推进剂的铅、铜盐催化剂在低燃速低燃温双基推进剂中同样具有催化作用,对热分解性能也有重要影响。
短句来源
     A Non-lead Catalyzed Nitramine Modified Double Base Propellant with Low Burning Rate and Low Flame Temperature
     一种非铅催化硝胺改性双基低燃速低燃温推进剂
短句来源
     Effects of Carbon Black on Burning properties of Plateau Double Base Propellant with Low Flame Temperature
     炭黑对低燃温双基平台推进剂燃烧性能的影响
短句来源
更多       
  low burning temperature
     Research on Low Burning Temperature Mesa Double Base Propellant
     低燃温麦撒双基推进剂研究
  “低燃温”译为未确定词的双语例句
     he Performance of nonaluminium composite propellant with low combustion temperature under the condition of spinning burning was investigated.
     启动鱼雷动力系统的固体推进剂药柱系低燃温、无铝复合推进剂,处于旋转状态下燃烧。
短句来源
     The results show that the ST propellant has the characteristics of higher energy,low combustion temperature,low ablation and high overload resistance and can meet the design specification of assorted types of rocket-assisted BB projectile.
     结果表明,ST推进剂具有能量较高(相对总体指标)、低燃温、低烧蚀、抗过载能力强的特点,可以满足不同型号复合增程炮弹火箭增程设计要求。
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  low flame temperature
At low flame temperature, however, nanoparticles are not formed and the particle morphology is similar to the morphology produced by the conventional spray pyrolysis.
      
Generally, conditions of low flame temperature, combined with high air temperature and high relative humidity produce the greatest attenuation.
      
This is mainly due to the low flame temperature caused by the high EGR rate.
      


The energy characteristics of hydroxylammonium nitrate (HAN)-triethanolammonium nitrate(TEAN)-H_2O liquid mon propellants has been evaluatel. It is found that fuel-rich or oxidizer0richmixtres obtain lower combustion temperature and higher voluminal energy density than thefuel / oxidiger ratio at maxiumn impetes.

本文对HAN-TEAN-H_2O单元液体发射药的能量特性进行了研究.提出采用富燃料或富氧化剂配方.比采用最大火药力的配方得到较低的燃温与较高的体积能量密度。

The influence of carbon black (CB)on burning properties of plateau double base propellant with low flame temperaure has been researched by the experiment. It is shown that with the content of CB raised,the burning rate of the propellant is increased and their plateau (or mesa) zone translate into higher pressure;But with the content of CB raised continuouslly more than a centain content,the burning rate is decreased and the plateau zone disappears.In the paper this phenomenon is explained theoretically and the...

The influence of carbon black (CB)on burning properties of plateau double base propellant with low flame temperaure has been researched by the experiment. It is shown that with the content of CB raised,the burning rate of the propellant is increased and their plateau (or mesa) zone translate into higher pressure;But with the content of CB raised continuouslly more than a centain content,the burning rate is decreased and the plateau zone disappears.In the paper this phenomenon is explained theoretically and the relationship of the content of CB with the burning rate is fit.

研究了炭黑对低燃温双基平台推进剂燃烧性能的影响。指出随着炭黑含量的增加,推进剂燃速也增加,平台或麦撒燃烧区向高压移动;但当炭黑达到某一含量后,炭黑含量再增加,燃速反而下降,平台燃烧区消失。对此现象作了理论解释,并用二次多项式拟合出炭黑含量与燃速的关系。

he Performance of nonaluminium composite propellant with low combustion temperature under the condition of spinning burning was investigated. The propellant is used to drive underwater propulsion system. The results show the effect of acceleration on combustion of nonalumiumcomposite propellant: the chamber pressure will increase and the burning time will decreased with theacceleration.

启动鱼雷动力系统的固体推进剂药柱系低燃温、无铝复合推进剂,处于旋转状态下燃烧。本项研究利用旋转燃烧试验台进行了药柱的燃烧试验,显示了加速度对无铝推进剂燃烧的影响。结果表明:在试验条件范围内,推进剂药柱随着加速度增大,燃烧室压强增大、燃烧时间缩短。根据实验数据整理出旋转燃烧条件下燃速公式。

 
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