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    Design and Performance Analysis of Spread Spectrum Non—Coherent Multi—station Transponder
    扩频型相参多站应答机的设计与性能分析
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    The Laminated Thick Walled Cylinder in a State of Non plane Strain
    平面应变状态下的叠层厚壁筒
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    Non Meteorologic Applications of Meteorological Satellite Data in China
    我国气象卫星气象领域遥感应用的发展与展望
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    The physiological assessment of the non pressure oxygen supply system with lower absolute pressure.
    低总压加压供氧装备生理试验评价
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    NEW PRINCIPLE OF FIBER GYROSCOPE IN NON SAGNAC EFFECT VIEWED PHYSICAL METHODOLOGY
    从物理学方法论谈SAGNAC效应光纤陀螺新原理
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    NUMERICAL STUDY ON BIFURCATION PHENOMENON IN A COMBUSTOR WITH A NON SLOT CONICAL SWIRLER
    隙锥形旋流器燃烧室流场分叉现象的数值研究
短句来源
    By means of declinate optical triangulation measuring instrument structure which is firstly proposed, the measured area and resolution of this measuring system are greatly increased, and the high accuracy non contact measurement of the planeness of a large area plane is realized.
    首次提出斜光学三角形测量结构 ,使得测量系统的测量面积和分辨率大大提高 ,从而实现了对大面积平面平面度的高精度接触测量 .
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    ③After correction for the influence of sex and age, the MNF and MNCF of smokers(6.12±0.42‰, 5.50±0.40‰ respectively) were slightly higher than non smokers(5.19±0.50‰, 4.48±0.46‰ respectively), but there was no statistical significance ( P >0.05) in the flight personnel.
    在性别和年龄可比条件下 ,吸烟飞行人员 MNF(6 .12± 0 .42‰ )、MNCF(5 .5 0± 0 .40‰ )略高于不吸烟飞行人员 MNF(5 .19± 0 .5 0‰ )、MNCF(4 .48± 0 .46‰ ) ,但差异显著性意义 (P>0 .0 5 )。 结论 宇宙辐射引起民航飞行人员染色体损伤。
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    The morbidity rate of dental caries was 28.6% among the pilots with a mean DMFT (decayed missing filled tooth) of 2.32,and 30.1% among the ground crew with a mean DMFT of 2.18. The difference between two groups was non significant.
    2 2 0名飞行人员患龋率 2 8 6 % ,龋均 2 32 ,与地勤人员的患龋率 (30 1% )、龋均 (2 18)相比差异显著性意义 (P >0 0 5 ) ;
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    The results show that the action of the TMO mixtures on burning rate of the propellants can be divided into three kinds:positive,non and negative coordination effects.
    实验结果表明,TMO复合催化剂对推进剂燃速的影响可分为正协同效应、协同效应和负协同效应3类;
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  非线性
    NUMERICAL STUDY OF THE TURBULENT FLOW IN THE PLANE CASCADE USING A NON LINEAR k ε MODEL
    非线性 k-ε 紊流模型在平面叶栅紊流计算中的应用
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    NON LINEAR THROTTLING ANALYSIS OF THRUST AND MIXTURE RATIO FOR A LIQUID OXYGEN/KEROSENE ROCKET ENGINE
    液氧/煤油火箭发动机推力和混合比的非线性调整研究
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    The Approximation of Navier Stokes Equation by Penalty Non linear Galerkin Method
    N-S方程的加罚非线性Galerkin方法近似
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    On Non Linear Vibration Characteristics of Blade with Fatigue Crack
    疲劳裂纹叶片振动的非线性特性研究
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    Numerical calculation of non linear wave using Boussinesq equation in water of arbitrarily varying depths
    任意水深变化Boussinesq型方程非线性波数值计算
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    LP 15 polyimide is a new generation of NON MDA polyimide resins.
    LP-15聚酰亚胺是一种含MDA的新型PMR聚酰亚胺树脂。
短句来源
    LP 15 polyimide is a new generation Non MDA Polyimide resin.
    LP-15聚酰亚胺是新一代含MDA的PMR聚酰亚胺树脂体系。
短句来源
    ③After correction for the influence of sex and age, the MNF and MNCF of smokers(6.12±0.42‰, 5.50±0.40‰ respectively) were slightly higher than non smokers(5.19±0.50‰, 4.48±0.46‰ respectively), but there was no statistical significance ( P >0.05) in the flight personnel.
    在性别和年龄可比条件下 ,吸烟飞行人员 MNF(6 .12± 0 .42‰ )、MNCF(5 .5 0± 0 .40‰ )略高于吸烟飞行人员 MNF(5 .19± 0 .5 0‰ )、MNCF(4 .48± 0 .46‰ ) ,但差异无显著性意义 (P>0 .0 5 )。 结论 宇宙辐射引起民航飞行人员染色体损伤。
短句来源
    Two groups 23 motor tests with propellant on slot surface and non propellant on slot surface, have been done.
    进行了翼槽带药和翼槽带药的共23 发点火实验;
短句来源
    This method possesses the desirable properties of high accuracy,inherent numerical stability(no wiggles),non numerical damping and algorithm simplicity.
    方法具有高阶精度,呈现数值振荡,带有可感受的数值衰减,计算过程稳定,计算方法简便等优点。
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The method applies to the standard arithmetic subgroups ofSO(n,1) (a case which was proved previously by Millson [Mi]), to the non-arithmetic lattices inSO(n,1) constructed by Gromov and Piatetski-Shapiro [GPS] and to groups generated by reflections.
      
We also show how to distinguish examples of open subsets with a good quotient coming from Mumford's theory and give examples of open subsets with non-quasi-projective quotients.
      
An algebraicG-varietyX is called "wonderful", if the following conditions are satisfied:X is (connected) smooth and complete;X containsr irreducible smoothG-invariant divisors having a non void transversal intersection;G has 2r orbits inX.
      
Lichtenstein in the caseu =(n, ?) or(n?), we prove that ?(q).ζ1/2 is non zero for all harmonic polynomialsq ∈S() \ {0}.
      
In [Ka1] its geometric counterpart was applied to construct contractible smooth affine varieties non-isomorphic to Euclidean spaces.
      
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This paper makes an analysis of the relations between J6@ series inlet cowl lip geometry and the flow separation of the lip on the basis of reference [1]. In the paper, three geometrical parameters ase analysed:the lip contraction ratio, the ratio of the long elliptic axis to the short axis, and the super-elliptical exponent, and their effect on the flow separation Zone. It is asserted in the paper that the non-separation can be obtained if only the three geometrical parameters are put into a good combination...

This paper makes an analysis of the relations between J6@ series inlet cowl lip geometry and the flow separation of the lip on the basis of reference [1]. In the paper, three geometrical parameters ase analysed:the lip contraction ratio, the ratio of the long elliptic axis to the short axis, and the super-elliptical exponent, and their effect on the flow separation Zone. It is asserted in the paper that the non-separation can be obtained if only the three geometrical parameters are put into a good combination oven though the throat Mach number is rather high.

本文是在文献的试验基础上,分析了J6Ⅲ系列进气道唇口几何形状和唇口气流分离的关系.文中分析了唇口三个几何参数:收缩比,椭圆长短轴比及超越椭圆指数n对气流分离区大小的影响。并提出只要此三个唇口几何参数组合得好,即使喉道M数较高,述是可以得到无分离的气流。

Based on an analysis of the nature of heat transfer during nucleate boiling, the convection-evaporation mechanism of heat transfer in nucleate boiling is proposed. General equations for the criterion of nucleate boiling are obtained: N_u= A(G_rP_r)~m[Eξ(P)]~n, N_u=AP_r~(m_1)R_c~(m_2)[Eξ(P)]~(m_3), which prove to be satisfactory when used to correlate experimental results. Based on the theory of non-equlibrium thermodynamics and statistical physics, the formation of vapor bubbles on heeting surface is analysed,...

Based on an analysis of the nature of heat transfer during nucleate boiling, the convection-evaporation mechanism of heat transfer in nucleate boiling is proposed. General equations for the criterion of nucleate boiling are obtained: N_u= A(G_rP_r)~m[Eξ(P)]~n, N_u=AP_r~(m_1)R_c~(m_2)[Eξ(P)]~(m_3), which prove to be satisfactory when used to correlate experimental results. Based on the theory of non-equlibrium thermodynamics and statistical physics, the formation of vapor bubbles on heeting surface is analysed, and the effects of various factors on the formaton of bubble are discussed.

本文根据不可逆过程热力学及统计物理学的理论,分析了加热表面上汽泡的产生,讨论了各种因素对汽泡产生的影响。提出了泡状沸腾放热的对流汽化机理,获得了描述泡状沸腾放热的普遍准则方程式 N_u=A(G_rP_r)~m[Eξ(P)]~n; N_u=AP_r~(m_1)R_e~(m_2)[Eξ(P)]~(m_3)。用本文的准则方程式能满意地综合实验结果。

A simplified model for the disign of hypergolic liquid propellant rocket engine combustors is presented.In contrast with Priem's basic model,the effects of decomposition reaction of fuel,secondary atomization of droplets and non-uniformity of mixture ratio and flow flux in the cross-section of the chamber on the combustion efficiency have been considered.All equations required for the calculation of combustion efficiency are derived and the computer program is given.As an example of the application of...

A simplified model for the disign of hypergolic liquid propellant rocket engine combustors is presented.In contrast with Priem's basic model,the effects of decomposition reaction of fuel,secondary atomization of droplets and non-uniformity of mixture ratio and flow flux in the cross-section of the chamber on the combustion efficiency have been considered.All equations required for the calculation of combustion efficiency are derived and the computer program is given.As an example of the application of this method,the combustion efficiency of “C” engine is calculated.Comparison of calculated Combustion efficiencies with experimental results shows satisfactory agreement with errors within 1-5%.Curves of total vaporization rate of fuel and vaporization rate per unit length as functions of the axial distance of combustor for given rocket engine are also presented.These curves show that the effects of decomposition reaction,secondary atomization of droplets and drop size distribution on vaporization rate are very substantial.Finally, the conditions,under which this model can be used,are discussed

本文提出了一个自燃推进剂液体火箭发动机燃烧室设计简化模型。与 Priem 基本模型不同,本文考虑了燃料分解反应,液滴二次雾化以及燃烧室截面上混合比和流强的不均匀性对燃烧效率的影响。文中导出了计算所需的全部公式,提出了计算程序。应用本方法计算了 C 发动机的燃烧效率。计算效率与试验结果相当符合,其误差在1~5%以内。文中还给出了燃料总蒸发速率和单位长度上的蒸发速率随该发动机燃烧室轴向距离变化的曲线。曲线表明,分解反应,液滴二次雾化和液滴尺寸分布对蒸发速率的影响很大。最后讨论了本模型使用的条件。

 
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