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   飞机座舱盖 的翻译结果: 查询用时:0.328秒
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飞机座舱盖
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  aircraft canopy
     Analysis of K8 Aircraft Canopy Plexiglass Shattering
     K8飞机座舱盖有机玻璃破裂原因分析
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  “飞机座舱盖”译为未确定词的双语例句
     The fatigue behaviour of PMMA is very important for the aircraft windshield structure.
     有机玻璃结构的疲劳性能是一个重要指标,飞机座舱盖的疲劳定寿工作是飞机结构疲劳定寿的重要内容之一。
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     Failure Analysis of Canopy for 700732# Aircraft
     700732号飞机座舱盖爆破故障分析
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     Failure Analysis of Canopy for 36 ̄# Aircraft
     36号飞机座舱盖空中爆破故障分析
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     Analyses & Validation of an Aircraft Cockpit Canopy Finite Element Model
     某型飞机座舱盖有限元模型分析及验证
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     After analyzing the causes of the crack in plexiglass' back arc flower groove in some main force Fighter Plane which is on active service in China,this paper proposes some repairing solution,and the main technical parameters and assembly methods after refitting are determined.
     分析我军某型现役主力战机飞机座舱盖有机玻璃后弧花槽裂纹产生的原因,提出修理中的解决方法,确定改装后的主要技术参数及装配方法。
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  相似匹配句对
     Failure Analysis of Canopy for 700732# Aircraft
     700732号飞机座舱盖爆破故障分析
短句来源
     Analysis of K8 Aircraft Canopy Plexiglass Shattering
     K8飞机座舱盖有机玻璃破裂原因分析
短句来源
     Cable Arrangement in an Aircraft
     飞机电缆敷设
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     RESEARCH ON AIRCRAFT SUPPORTABILITY
     飞机保障性
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  aircraft canopy
Compliant motion using a mobile manipulator: an operational space formulation approach to aircraft canopy polishing
      
In this paper, we discuss its implementation on a mobile manipulator programmed to polish an aircraft canopy with a curved surface of unknown geometry.
      


A graphic method based on principle of superposition and self-equilibrium of residual stress is used for cliscriminating the thermal stress fringe quantitatively from the frozen stress fringe in PMMA. The residual stress caused by forming can be calculated from the thermal stress fringe in transparent airplane canopi es according to the earlier work of the author. The method has been applied in engineering.

本文基于叠加原理和残余应力的自平衡特性,建立了一种将有机玻璃热应力条纹与冻结应力条纹进行定量分离的图解法。根据热应力条纹,应用作者早期的工作,可计算出飞机座舱盖玻璃成型残余应力。该方法己获得工程应用。

This paper described experiment investigation of tran-sonic drag characteristics and design of theoretic calculation programfor close cabin,and established the methods of parameter choice,engi-neering estimation,an pre-estimate property with theoretic calculationfor high speed close cabin.Theoretic design was completed before test.Experimental study of effect of maximum height and width,slen-derness ratio and backward angle of dip of window of close cabin ondrag characteristics was conducted respectively with...

This paper described experiment investigation of tran-sonic drag characteristics and design of theoretic calculation programfor close cabin,and established the methods of parameter choice,engi-neering estimation,an pre-estimate property with theoretic calculationfor high speed close cabin.Theoretic design was completed before test.Experimental study of effect of maximum height and width,slen-derness ratio and backward angle of dip of window of close cabin ondrag characteristics was conducted respectively with 4 series and 13close cabin models.It provided general criteria for parameter choice ofaerodynamic design of close cabin of high speed aircraft and applica-tion curves for engineering calculation of transonic drag of close cabin.In this paper the programs of pressure distribution and aerodynam-ic calculation applied to different configurations for body-close cabinwere given by finite difference method.

本文通过座舱盖跨声速阻力的试验研究及理论计算程序的设计,建立了高速座舱盖参数选择、工程估算及理论计算预测性能的方法,完成了试验前的理论设计工作。经4个系列13个座舱盖模型的试验,分别研究了座舱盖最大高度、最大宽度、细长比及风挡后倾角对阻力特性的影响,为高速飞机座舱盖气动设计的参数选择提供了一般准则;并为座舱盖跨声速阻力的工程估算提供了应用曲线。本文用有限差分法建立了可适用于不同外形的机身-座舱盖的压力分布及气动力计算的程序。

An investigation on opening and throwing of aeroplane canopy by using solid rocket engine is made in order to save pilot's life in an emergency. The design parameters of SPRM are determined according to the demand of total project for aeroplane canopy being thrown out. Ground tests verity that the design is practicable, and that the performance of engine can satisfy the demand of total project.

文中对用固体火箭发动机应急打开并抛弃座舱盖方案进行了探索。并根据飞机座舱盖抛放总体方案的要求,确定了固体火箭发动机的设计参数。通过地面试验说明该方案是切实可行的。所设计的固体火箭发动机,其性能满足总体要求。

 
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