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热防护技术
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  thermo-protection technology
     On the basis of aerothermal traits of the late-model super-speeding air-defense missile, the structure thermo-protection technology and connected thermo-structure analysis and experiment technology are discussed. They include radome, each section of body, wing and air rudder.
     根据新一代超高速防空导弹气动加热特征 ,讨论了防空导弹弹体结构 ,包括天线罩、弹身各舱段、弹翼和空气舵的结构热防护技术以及相关的热结构分析与试验技术
短句来源
  “热防护技术”译为未确定词的双语例句
     Thermal protection techniques of ramjet combustor
     冲压发动机燃烧室热防护技术
短句来源
     Thus the property of erosion of hot preservative materials is of importance in hot preservative technology.
     而材料的烧蚀速度是热防护技术中希望得到的重要参数。
短句来源
     The test results show that this prototype was reasonable,the specific impulse of cruise stage was higher than that similar to engines abroad,and the integrated booster performance and thermal protection technique were satisfactory
     样机结构合理,主级比冲比国外同类型号导弹发动机有较大提高,助推级综合性能和热防护技术也优于后者。
短句来源
     The effect of transpiration cooling on the heat transfer characteristics for flow through a porous plate was experimentally investigated using sintered porous plates made of uniform or non uniform bronze particles with different diameters to develop an effective thermal protection technique.
     为开发有效的热防护技术,分别采用均匀青铜颗粒和不均匀青铜颗粒烧结而成的多孔板作为实验段,对平板发汗冷却进行了实验研究。
短句来源
  相似匹配句对
     Thermal protection techniques of ramjet combustor
     冲压发动机燃烧室防护技术
短句来源
     AGRO-ENVIRONMENTAL PROTECTION 1997,VOl.16,No.3 Heat lnjury on Citrus and lts Prevention.
     柑桔高温害及防护技术
短句来源
     On Hot runner Technology
     流道技术
短句来源
     Thermal Release Technology
     分离技术
短句来源
     Combustor thermal protection is one of key techniques of ramjets.
     冲压发动机燃烧室防护是其关键技术之一。
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The application of hot preservative materials is widely accepted in aeroand space-technology.Thus the property of erosion of hot preservative materials is of importance in hot preservative technology.The paper develops a method for the study of gaseous erosion and particle erosion.Results from this study agree well with expermental data.

在航空、航天中,烧蚀材料作为热防护层得到了广泛应用。而材料的烧蚀速度是热防护技术中希望得到的重要参数。本文对耐热烧蚀材料的烧蚀问题进行了分析和研究,给出了气相烧蚀速度和粒子侵蚀速度的计算方法,与实例比较,数据基本吻合。

This paper presents the ablative thermal protection techniques of re-entry module of manned spacecraft. Investigations and experiments indicate that charring ablators provide the most efficient thermal protection shield for the re-entry vehicles. An analytical model and calculated method for predicting the thermal performance of typical charring ablators have been described. Good agreement are obtained between the numerical results with arc wind tunnel tests and flight verification testing results.

载人飞船返回舱的烧蚀热防护技术研究和试验表明,碳化烧蚀材料是再入飞行器最有效的热防护层。对典型的碳化烧蚀体的热性能的预测分析模型和计算方法作了阐述。数值计算结果分别与电弧风洞试验和阿波罗的飞行验证试验作了比较,结果符合得很好。

An integral solid rocket ramjet engine in China is introduced.The design,manufacture and test of the whole engine(both sustainer and booster),components and sub systems during ground and flight test phases were described.The test results show that this prototype was reasonable,the specific impulse of cruise stage was higher than that similar to engines abroad,and the integrated booster performance and thermal protection technique were satisfactory

概要介绍了我国第一种整体式固体火箭冲压发动机试验研究样机的研制,讨论了样机地面试验研究和飞行试验研究两大阶段中,整机(含主级和助推级)、各部件及分系统的设计、试制和试验工作。样机结构合理,主级比冲比国外同类型号导弹发动机有较大提高,助推级综合性能和热防护技术也优于后者。

 
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