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推进剂性能     
相关语句
  propellant performance
     The first and systematical calculation of the temperature coefficients for combustion products of the copper element has been completed. The function ensures the equal values at the cross point of the two temperature intervals(such as 100K). In fact,this method provides the reliable data of the temperature coefficients for the calculation of the propellant performance.
     用该程序系统地算出铜元素各种燃烧产物热力学函数温度系数 ,并保证两个不同温度区间交接处 ( 10 0 0 K)的函数值完全相等 ,为推进剂性能计算进一步发展提供了可靠的数据
短句来源
     The idea and methods of uncertainty optimization design were introduced. In consideration of uncertainty of propellant performance parameter during optimization design process,the investigation on uncertainty optimization design of SRM grain was carried out.
     介绍了不确定性优化设计思想和方法,考虑装药优化设计过程中推进剂性能参数不确定性,开展了固体火箭发动机装药不确定性优化设计研究。
短句来源
  propellant properties
     ADVANCES IN THE RESEARCH OF SOLID PROPELLANT PROPERTIES ABROAD
     国外固体推进剂性能研究的新进展
短句来源
     Effect of Nano/Micro Composite Particles on Solid Propellant Properties
     纳米/微米复合粒子对固体推进剂性能的影响
  “推进剂性能”译为未确定词的双语例句
     Effect of Antioxidant on Properties of High Burning Rate HTPB-IPDI Propellant(Ⅱ)
     防老剂对HTPB-IPDI高燃速推进剂性能影响研究(Ⅱ)
短句来源
     Effect of phase separation on the properties of NEPE propellant
     相分离对NEPE推进剂性能的影响
短句来源
     Performance Rearch of Metallized Gelled Propellant
     金属化胶体推进剂性能研究
短句来源
     Effects of Antioxidant on Properties of HTPB-IPDI High Burning Rate Propellant(Ⅰ)
     防老剂对HTPB-IPDI高燃速推进剂性能影响研究(Ⅱ)
短句来源
     Characteristics of HTPB Propellant with High Solid Contents
     高固体含量丁羟推进剂性能研究
短句来源
更多       
  相似匹配句对
     EVALUATION ON PERFORMANCE OF METALLIZED GELLED PROPELLANT
     金属化凝胶推进剂性能评估
短句来源
     Performance Rearch of Metallized Gelled Propellant
     金属化胶体推进剂性能研究
短句来源
     Plant Performance
     设备性能
短句来源
     How We Test
     性能测试
短句来源
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  propellant performance
It is found that an important parameter determining propellant performance is the quantity of the smokeless powder used for igniting the mixture.
      
Propellant performance of organic explosives and their energy output and detonation velocity limits
      
Methods for determining the propellant performance of high explosives (HEs) are considered.
      
Experimental data on the propellant performance of individual explosives are given.
      
The influence of metal additives on the brisance (propellant performance) and blast effect of explosive compositions is considered.
      
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  propellant properties
The above relations illustrate the importance of propellant properties on thruster performance.
      
The measurements from the 800-pound motor firing indicate that the propellant processed from reclaimed AP has nominal propellant properties.
      


In this paper, a series of isoperformance trigonal diagram of NC—NG (TA、TEGN)—RDX(HMX) smokeless propellant systems are drawn. From the diagram, the relationship between the formulation and the performance and gas composition of the propellant is clearly shown. If the composition of the propellant is given, the values of the performance and the gas composition can be easily determined. Also, from the diagram, the composition of the propellant can be readily determined in accordance of the performance value given....

In this paper, a series of isoperformance trigonal diagram of NC—NG (TA、TEGN)—RDX(HMX) smokeless propellant systems are drawn. From the diagram, the relationship between the formulation and the performance and gas composition of the propellant is clearly shown. If the composition of the propellant is given, the values of the performance and the gas composition can be easily determined. Also, from the diagram, the composition of the propellant can be readily determined in accordance of the performance value given. It is possible to choose an optimum formulation according to the technology required. This method is characterized by simplicity, visualization and convenience in the design and choice of formulation.In addition, the effects of nitrogen content of NC, type of plsticizer used and variation of pressure on the performance of propellant are calculated and discussed. It is suggested that the proper increase of pressure be advantageous to the full utilization of propellant energy.Finally, it is demonstrated that the increase of nitrogen content in propellant formulation is an important approach to raising the energy release rate at low pressure.

本文绘制了NC—NG(TA、FEGN)—RDX(HMX)系无烟推进剂一系列等性能三角图,由图可清晰的看出主成分的配方与性能,燃气成分的关系。若知主成分的配方可从图上读出各种性能及燃气成分值,也可由性能指标从图中迅速的找出各种组份的含量,并结合工艺选择最佳配方。其特点是简便、直观、便于配方设计与选择。本文还对不同含氮量的硝化棉(NC)、不同增塑剂及压力变化给推进剂性能的影响进行了计算和讨论;提出了适当增加压力对充分利用推进剂能量是有利的。最后,论证了适当增加配方中的氮含量是提高低压下能量释放率的重要途径。

Burning rate adjusting and pressure exponent reducing both are the key techniques to improve combustion properties of smokeless propeilant RDX-CMDB. Four DB system propeilant including RDX with specific impulses of 2000 to 2200N-s/kg added same Pb-Cu-CB catalyst are tested in a 50mm diameter rocket motor. The experement results indicate that with this combustion catalyst plateau or mesa combustion property can be obtained in the middle and highter pressure range, and the plateau burning rate can be adjusted...

Burning rate adjusting and pressure exponent reducing both are the key techniques to improve combustion properties of smokeless propeilant RDX-CMDB. Four DB system propeilant including RDX with specific impulses of 2000 to 2200N-s/kg added same Pb-Cu-CB catalyst are tested in a 50mm diameter rocket motor. The experement results indicate that with this combustion catalyst plateau or mesa combustion property can be obtained in the middle and highter pressure range, and the plateau burning rate can be adjusted within 14 to 29 mm/s for DB and RDX-CMDB propellants. Meanwhile, the width of plateau pressure range is over 8.0 MPa.

调节燃速和降低压力指数是RDX-CMDB推进剂性能改善的技术关键之一.用同一种有机铅、铜盐催化剂对实测比冲为2000~2200N·s/kg的四种双基及RDX-CMDB推进剂进行试验研究表明:铅-铜-炭黑三种燃烧催化剂组合使用也可在RDX-CMDB无烟推进剂中获得良好的平台或麦沙效应.这里炭黑的加入起了关键作用,可用燃烧催化的铅-碳理论作进一步的解释.所述的铅、铜催化剂与四种碳黑搭配,可使所研究的四种推进剂燃速在14~29mm/s范围内调节.

Temperature coefficients for themodynamic function are determined by means of a simultaneous least-squares fitting of heat-capacity,enthalpy、entropy,which are described as polynomical equations in temperature.After some mathematical treatments and programming,exact numerical solutions can be obtained.Even some of solution errors are less than those given in reference[1]、[2].The first and systematical calculation of the temperature coefficients for combustion...

Temperature coefficients for themodynamic function are determined by means of a simultaneous least-squares fitting of heat-capacity,enthalpy、entropy,which are described as polynomical equations in temperature.After some mathematical treatments and programming,exact numerical solutions can be obtained.Even some of solution errors are less than those given in reference[1]、[2].The first and systematical calculation of the temperature coefficients for combustion products of the copper element has been completed.The function ensures the equal values at the cross point of the two temperature intervals(such as 100K).In fact,this method provides the reliable data of the temperature coefficients for the calculation of the propellant performance.

利用热容、熵、焓与温度关系的方程 [1] ,采用解最小二乘联立方程组的方法 ,编制了计算程序。可算出各种物质热力学函数温度系数。以此经验方程求得各种温度下的函数值与标准值非常接近 ,偏差小 ,精度高于文献 [1、 2 ]。用该程序系统地算出铜元素各种燃烧产物热力学函数温度系数 ,并保证两个不同温度区间交接处 ( 10 0 0 K)的函数值完全相等 ,为推进剂性能计算进一步发展提供了可靠的数据

 
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