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demonstration test
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  验证试验
    According to concrete conditions of the wing flapretraction-extension system of the 18 trainer aircraft, this paperca nes out a research into the relibility demonstration test and thelife test plans of the system, and deals with some key issuesrelated to the test in a deep manner, such as relation between thereliability test parameters and the reliability indexes, convertingfrom working time(frequency), composite test profiles, themathod determining reliability test parameters for success ratioand so on.
    本文针本对L8机襟翼收放系统的具体情况,研究了其可靠性验证试验和寿命试验方案,并深入研究了涉及试验的关键问题,例如:可靠性试验参数与可靠性指标之间的关系,工作时间与工作次数的折算,合成试验剖面,确定成败型可靠性试验参数的方法等等。
短句来源
    In adddition, the integrated testdesign of the reliability demonstration test and the life test isdiscussed in the paper.
    此外,还根据需要对可靠性验证试验和寿命试验进行了综合试验设计。
短句来源
    First, briefly stated the developed history of reliability research and current situation at home and abroad, the reliability test method and the developing trend of reliability demonstration test, the statistical analysis method, the developing history and current situation of demonstration theory, the current situation and existing problems of electrical connectors reliability researched.
    首先,回顾和评述了国内外可靠性研究的发展历史和现状,可靠性试验的方法和可靠性验证试验的发展趋势,可靠性统计分析方法和验证理论的发展历史与现状,以及航天电连接器可靠性研究的现状和存在的问题。
短句来源
    Proposed the way of how to estimate the reliability level further according to the demonstration test result.
    同时给出了可靠性验证试验的验证指标和质量水平。
短句来源
    Eventually, gave a conclusion to research content of entire dissertation, proposed the directions of electrical connectors reliability demonstration test, and the way of how to improve the inherent reliability level of electrical connectors.
    最后,本章对全文的研究内容进行了总结,并提出了电连接器可靠性验证试验发展的方向和提高电连接器固有可靠性的方法。
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  “demonstration test”译为未确定词的双语例句
    The status and results of flight demonstration test about DS-1、MUSES-C 和 SMART-1 spacecraft used solar-electric propulsion system as primary propulsion is also presented simply in the paper.
    文中还简要地介绍了目前采用太阳电推进系统作主推进的DS-1、MUSES-C和SMART-1三个空间探测器的证实飞行试验情况和结果。
    Research on Y11X Electrical Connectors Reliability Demonstration Test Method
    航天电连接器失效率验证试验方法的研究
短句来源
    In the dissertation, the model Y11X-1419 electrical connector as the object, reliability demonstration test method is researched deeply.
    本文以Y11X圆形低频电连接器为研究对象,对航天电连接器的贮存可靠性验证试验方法进行了系统、深入的研究。
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  demonstration test
The product was used as a substitute for chemical surfactants in a clean-up demonstration test carried out by Cargo Fleet Chemical Company Ltd.
      
Demonstration test of AgX-10 adsorbent using radioactive methyl iodide tracer was performed.
      
The probability generating function of number of trials for the start-up demonstration test with rejection upon d failures is derived.
      
The joint probability generating function of some random variables appearing in the Markov dependence model of the start-up demonstration test with corrective actions is derived by the method of probability generating function.
      
A general probability model for a start-up demonstration test is studied.
      
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The flying qualities of the aircraft with FBW FCS is determined by the varied parameters of the system. This paper deals with some problems with were pat forward during the design and test of the control system parameters, and the demonstration test-flight of flying qualities in CAS mode.

具有电传飞行控制系统的飞机,其飞行品质取决于系统参数.本文就控制系统参数设计、试验研究中的个别问题以及CAS功能下的飞行品质的验证试飞做简单的叙述.

The paper presents a brief introduction to the concepts of advanced aero-engine control and a tendency of the control system development in recent years, with emphasis on the high stability engine control (HISTEC) technology. HISTEC features control on individual engine components, i.e. by reducing stability margin of a component or widening the range of component stable operation to increase engine performance and realize system control benefit. Flight demonstration tests show that engine inlet distortion...

The paper presents a brief introduction to the concepts of advanced aero-engine control and a tendency of the control system development in recent years, with emphasis on the high stability engine control (HISTEC) technology. HISTEC features control on individual engine components, i.e. by reducing stability margin of a component or widening the range of component stable operation to increase engine performance and realize system control benefit. Flight demonstration tests show that engine inlet distortion will be accurately estimated, accommodated and controlled in real time using HISTEC. Hence the design stall margin could be reduced, the engine performance and stability enhanced considerably.

简要介绍了近年来航空发动机控制概念和设计思想的发展趋势 ,着重分析说明了高稳定性发动机控制技术。高稳定性发动机控制技术的特点是将控制的重点放在单个部件上 ,通过减小部件稳定裕度要求或扩大部件稳定性工作范围来提高部件的性能并实现系统收益。飞行试验结果表明 ,这种控制方法可以较精确地估算和适应发动机进气道畸变并进行实时控制 ,降低了对设计失速裕度的要求 ,提高了发动机性能和稳定性。

A repair process study has been conducted to delay the occurrence and propagation of fatigue cracks which are likely to exist in the welded area around the air chamber union on the wall of accumulator fuel tank in a certain-type aircraft to prolong the service life of the tank. A local repair scheme using glass fabric reinforced epoxy resin composite patch bonded to the inside wall of the tank is discussed. Results of specimen comparison fatigue tests and performance demonstration tests, including...

A repair process study has been conducted to delay the occurrence and propagation of fatigue cracks which are likely to exist in the welded area around the air chamber union on the wall of accumulator fuel tank in a certain-type aircraft to prolong the service life of the tank. A local repair scheme using glass fabric reinforced epoxy resin composite patch bonded to the inside wall of the tank is discussed. Results of specimen comparison fatigue tests and performance demonstration tests, including high/low temperature storage, vibration, pressurization and airtightness tests, are given. The results indicate that the repair process can provide a prolonged service life and improved safety of operation for the accumulator tank.

针对某型飞机蓄压油箱气腔管嘴处焊接部位易产生疲劳裂纹的问题, 对超期蓄压油箱采用局部修补方案, 以便延缓裂纹的产生和扩展, 达到延长使用寿命的目的。通过各种方案论证, 选择了用环氧树脂/玻璃布复合材料胶接修补方法, 并进行了工艺方法研究, 论述了该方法对外场飞机蓄压油箱修补的可行性;通过进行模拟件对比疲劳试验及局部修补后蓄压油箱的高、低温贮存、振动、爆破及气密性等验证试验, 论述了该修补方法可延长超期蓄压油箱的使用寿命, 提高安全性。

 
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