助手标题  
全文文献 工具书 数字 学术定义 翻译助手 学术趋势 更多
查询帮助
意见反馈
   推进剂配方 的翻译结果: 查询用时:0.069秒
图标索引 在分类学科中查询
所有学科
燃料化工
航空航天科学与工程
更多类别查询

图标索引 历史查询
 

推进剂配方     
相关语句
  propellant formulation
     Study on PEPA/AP pasty propellant formulation
     PEPA/AP膏体推进剂配方研究
短句来源
     Design of the Solid Propellant Formulation and Property Database
     固体推进剂配方与性能数据库的设计
短句来源
     Optimization design of aluminized nitramine propellant formulations by the method of orthogonal design has been carried out in this paper. A good propellant formulation with the considration of processing property has been determined.
     利用正交设计方法对含铝硝胺推进剂配方进行了优化设计,并结合工艺性能确定出优选的推进剂配方
短句来源
     The effects of the contents of fine ammonium perchlorate(AP) and plasticizer di-2-ethylhexyl sebacate(DOS) and bonding agent LW1 on mechanical properties of high burning rate HTPB/IPDI propellant at -55 ℃ were studied. A high burning rate HTPB propellant formulation with better comprehensive properties and used in the -55 ℃~+70 ℃ broad temperature range was gained. Propellant formulation has better mechanical properties except for properties of high burning rate and energy.
     研究了细AP含量、增塑剂癸二酸二异辛酯 (DOS)含量和键合剂LW1等因素对HTPB/IPDI高燃速推进剂 - 5 5℃低温力学性能的影响 ,获得了一个使用温度范围广 (- 5 5℃~ + 70℃ )、综合性能优良的丁羟高燃速推进剂配方
短句来源
     RESEARCH OF HTPB PROPELLANT FORMULATION USED FOR TACTICAL ATTACK MISSILE MOTOR
     战术攻击导弹发动机用丁羟推进剂配方研究
短句来源
更多       
  propellant formulations
     After they were added in propellant formulations respectively , the burning-rate can be regulated in the range of 10~100? mm/s (6.86~9.8?MPa).
     在推进剂配方中分别添加它们后 ,燃速可在 10~ 10 0mm/s(6 .86~ 9.8MPa)调节。
短句来源
     Optimization Design of Aluminized Nitramine Propellant Formulations
     含铝硝胺推进剂配方优化设计
短句来源
     A Study of High Burning Rate HTPB Propellant Formulations
     高燃速丁羟推进剂配方研究
短句来源
     Optimization design of aluminized nitramine propellant formulations by the method of orthogonal design has been carried out in this paper. A good propellant formulation with the considration of processing property has been determined.
     利用正交设计方法对含铝硝胺推进剂配方进行了优化设计,并结合工艺性能确定出优选的推进剂配方
短句来源
     The basic concepts and main varieties of thermoplastic elastomers (TPEs) are outlined in the paper and advantages of TPEs over thermoset elastomers and the feasibility of TPEs as solid rocket propellant binders are analyzed in details. The basic requirements for TPEs used in solid propellants and applications of meet and enersetic TPFs to solld propellant formulations are reviewed.
     概述了热塑性弹性体(TPEs)的基本概念和种类,分析了TPEs的优点和在固体推进剂中应用的可能性,指出了固体推进剂对TPEs的基本要求,综述了惰性TPEs和合能TPEs在固体推进剂配方中的应用研究。
短句来源
更多       
  propellant compositions
     THE OPTIMIZATION OF COMPOSITE SOLID PROPELLANT COMPOSITIONS
     复合固体推进剂配方的优化方法
短句来源
     Uniform design method is applied to design a series of“C H O N Cl Al” propellant compositions with restricted condition .
     利用配方均匀试验设计法设计了有约束条件的C H O N Cl Al体系推进剂配方 .
短句来源
     When the propellant compositions, chamber pressure and gas-dynamic conditions are given, these models can be used in the prediction of steady state and erosive burning rates.
     给出推进剂配方、燃烧室压力和气动条件的情况下,可用本文提出的模型比较准确地预估稳态燃速和有侵蚀燃速。
短句来源
  propellant composition
     Investigation on Reduced-signature HTPB Propellant Composition Containing RDX
     含RDX的少烟丁羟推进剂配方研究
     To Improve the combustion efficiency up to a practically acceptable level, not only propellant composition but also,more importantly, proper organization of combustion in engines and optimization of combustion parameters are needed to design well-conceivedly.
     而把燃烧效率能提到实用允许的限度,不仅需要对推进剂配方的周密设计,并且更重要的,还需对发动机的合理组织燃烧、优化燃烧参数等做精心的设计.
短句来源
     This paper introduces several novel or modified munitions practised by US-UK Joint Force in war on Irag, with the emphasis on technical analysis of the solid propellant composition and warhead types, indicating that the propellant and warhead used mainly in the munition in service of US Forces are HTPB propellants and penetration warheads.
     介绍了伊拉克战争中美英联军所使用的几种新型或改型弹药,主要对美军所采用的固体推进剂配方和战斗部类型进行了技术分析,指出美军现装备弹药型号上使用的主要是HTPB推进剂和侵彻战斗部。
短句来源
     Compared with other kinds of ramjet,the marked characteristic of the solid fuel ramjet is that its propellant combustion chamber process is not only concerned with the propellant composition,motor structure and combustion pressure,but also dependent on the air parameter in the combustion air inlet.
     与其它冲压发动机相比,固体燃料冲压发动机一个显著特点是推进剂燃烧过程不仅与推进剂配方、发动机结构和燃烧室压强有关,还取决于燃烧室入口空气参数,因此工作过程较为复杂。
短句来源

 

查询“推进剂配方”译词为其他词的双语例句

     

    查询“推进剂配方”译词为用户自定义的双语例句

        我想查看译文中含有:的双语例句
    例句
    为了更好的帮助您理解掌握查询词或其译词在地道英语中的实际用法,我们为您准备了出自英文原文的大量英语例句,供您参考。
      propellant formulation
    A new approach to propellant formulation: minimizing life-cycle costs through science-based design
          
    The work presented here demonstrates the first phases of a newly-proposed gun propellant formulation process that will minimize life-cycle costs through science-based design.
          
    Here the optical as well as electrical properties of nanotubes may be important in generating an improved propellant formulation.
          
    Ivanov et 1 reported that by adding aluminum nanoparticles in a propellant formulation, the burning rate could be enhanced by a factor of 5-10.
          
    Long-term storage stability is one of the key elements of a successful propellant formulation.
          
    更多          
      propellant formulations
    Triamino guanidinium azotetrazolate (TAGAZ) was incorporated into solid propellant formulations in order to establish the compatibility of this class of compounds.
          
    The burning rate data obtained indicated that TAGAZ acts as an efficient energetic additive in composite modified double base (CMDB) propellant formulations in high-pressure region.
          
    Triamino guanidinium azotetrazolate (TAGAZ) was incorporated into solid propellant formulations in order to establish the compatibility of this class of compounds.
          
    The burning rate data obtained indicated that TAGAZ acts as an efficient energetic additive in composite modified double base (CMDB) propellant formulations in high-pressure region.
          
    CL-20 is a recently synthesized component of energetic propellant formulations.
          
    更多          
      propellant compositions
    The determination of gases evolved from stored propellant compositions by gas-chromatography
          
    A knowledge of the nature and amount of gas evolved from stored propellant compositions provides valuable information on the stability, compatibility, handling and storage characteristics of such compositions.
          
    The determination of residual solvents in propellant compositions by gas chromatography
          
    The determination of gases evolved from propellant compositions by gas chromatography
          
    Thermal decomposition studies on double-base propellant compositions
          
    更多          
      propellant composition
    Estimation of the pressure built up in a nonhermetic vessel upon combustion of a solid-propellant composition
          
    We have developed an approximate mathematical model that allows one to calculate the pressure in a nonhermetic vessel upon combustion of a solid-propellant composition in it.
          
    It is shown that a maximum pressure is attained long before the combustion of the solid-propellant composition in a nonhermetic room.
          
    Thus, to deduce the burning rate from the recoil force, the parameters of the fitting law must be determined for each propellant composition under a particular set of external conditions.
          
    Ignition was predictable based on propellant composition, metered volume, number of actuations, and spacer capacity.
          
    更多          


    In this paper a model has been developed to calculate burning rate as a fun-ction of propellant composition and pressure. By means of the model, the bur-ning rate, the pressure exponent and their variable range can be predicted foruncatalyzed both double-base and composite-modified double-base propellant(with the addition of HMX or RDX).A comparison with more than one hundredtest results shows that the quantitative predictions of the model, varying thepropellant composition, appear to be basically consistent...

    In this paper a model has been developed to calculate burning rate as a fun-ction of propellant composition and pressure. By means of the model, the bur-ning rate, the pressure exponent and their variable range can be predicted foruncatalyzed both double-base and composite-modified double-base propellant(with the addition of HMX or RDX).A comparison with more than one hundredtest results shows that the quantitative predictions of the model, varying thepropellant composition, appear to be basically consistent wit hexperimentalresults.

    本文提出一种以推进剂配方比例和压力为自变量的燃速计算模型。由此可以估算非催化双基推进剂和改性双基推进剂(填加HMX或RDX)的燃速、压力指数和它们的可调性。已对一百多个推进剂配方进行计算,所有计算值与实测结果基本符合。

    This paper adopts the free energy minimigation technigue for The calculation of theoretical rocket performance under equilibrium flow condition. According to the analysis of optimization theory, the direct search method is employed in combination with computer program. A solid propellant ingredient is obtained for maximum specific impulse and maxmium characteristic velocity.

    本文在最小自由能法精确计算固体火箭推进剂能量特性程序的基础上,运用模式搜索优化方法,编制了电子计算机程序,用该程序能算出已知组分在最高比冲或最高特征速度下的最佳配方。优化计算结果和图象法(或精确计算)所得的结果是一致的。这证明固体推进剂能量特性的优化设计是成功的,为固体推进剂配方设计提供了一种有效的计算方法。

    The present paper has summed up the main research achievements in the field of transient combustion of a solid metallized propellant in an acceleration field and discussed their improprieties in the aspects of size distribution of metallic particles and the relations between the deformation parameters and strain modulus of the metallic fused blocks.A set of equations for calculating the transient combustion performance of metallized propellant in a acceleration field have been established and solved. The results...

    The present paper has summed up the main research achievements in the field of transient combustion of a solid metallized propellant in an acceleration field and discussed their improprieties in the aspects of size distribution of metallic particles and the relations between the deformation parameters and strain modulus of the metallic fused blocks.A set of equations for calculating the transient combustion performance of metallized propellant in a acceleration field have been established and solved. The results obtained by the equation are satisfied.

    本文综述了含金属固体推进剂在加速度场中燃烧时瞬态燃烧领域的一些主要研究成果,指出了其中存在的某些阴显的不妥之处,如:金属颗粒的尺寸分布,金属球团变形参数与变形模量的关系.本文在综合有关模型的基础上,提出了含金属推进剂在加速度场中燃烧的计算方程组,并求解确定了其瞬态燃烧特性,所得结果比较满意,可供发动机设计和推进剂配方设计时参考.

     
    << 更多相关文摘    
    图标索引 相关查询

     


     
    CNKI小工具
    在英文学术搜索中查有关推进剂配方的内容
    在知识搜索中查有关推进剂配方的内容
    在数字搜索中查有关推进剂配方的内容
    在概念知识元中查有关推进剂配方的内容
    在学术趋势中查有关推进剂配方的内容
     
     

    CNKI主页设CNKI翻译助手为主页 | 收藏CNKI翻译助手 | 广告服务 | 英文学术搜索
    版权图标  2008 CNKI-中国知网
    京ICP证040431号 互联网出版许可证 新出网证(京)字008号
    北京市公安局海淀分局 备案号:110 1081725
    版权图标 2008中国知网(cnki) 中国学术期刊(光盘版)电子杂志社