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火箭
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  rocket
    THE ANALYSIS FOR STRESS AND DEFORMATION OF SOLID ROCKET ENGINE BY USING THE TOTAL-LAGRANGIAN INCREMENTAL FINITE ELEMENT METHOD
    用Total Lagrangian增量有限元法分析固体火箭发动机的应力和变形
短句来源
    THE QUANTITATIVE VISUALIZATION OF DENSITY FIELD FOR REAL ROCKET EXHAUSTED PLUME
    真实火箭燃气羽流密度场的定量显示
短句来源
    Studies on Energy Flow of a Rocket Motion
    火箭运动的能流研究
短句来源
    A calculation of two-phase flow for descent segment of internal-ballisics in solid rocket moter
    固体火箭发动机内弹道下降段的不定常二相流动计算
短句来源
    AN ANALYSIS OF THE ROCKET FLIGHT FROM THE VIEWPOINT OF ENERGY
    从能量观点分析火箭飞行
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  “火箭”译为未确定词的双语例句
    Emergence and diffusion of the poisonous gas on the ground for liquid launch vehicle explosion
    液体火箭爆炸地面有害气体生成与扩散分析
短句来源
    Research on sled load techniques
    火箭橇加载试验技术研究
    Has provided a direct solution new mentality for the solid propellant engine in flow field simulation.
    为固体火箭发动机的内流场仿真提供了一个直接求解的新思路。
短句来源
    The method appears to be worth recommending, especially while designing solid propellenters.
    本文采用的分析方法和结论可供固体火箭发动机壳体设计工作者参考。
短句来源
    The comparisons between the computations and experiments for the launch vehicle with strap-on boosters C of China and the launch vehicle with strap-on boosters N of Japan denote that the present method can satisfy the necessary accuracy and provide a rapid and economical method in the preliminary design phase.
    对我国C火箭和日本N火箭的计算结果与实验数据比较,说明该方法能满足方案设计阶段精度要求。 是方案设计过程中快速而经济的计算方法。
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  rocket
Microbiological Degradation of Asymmetric Dimethylhydrazine, a Toxic Rocket Fuel Ingredient
      
The possibility of microbiological cleaning of water and soil polluted with asymmetric dimethylhydrazine (ADMH), a highly toxic ingredient of rocket fuel (IRF), was studied.
      
Consideration was given to the controlled solid bodies such as aircraft, rocket, and so on moving in the aerodynamic medium.
      
Peculiarities of Estimating the Aircraft Performance Characteristics of the Rocket-and-Space Facilities under Conditions of Fuzz
      
The method is based on the results of measurements of the state parameters and geophysical conditions of the employment of the rocket-and-space facilities under conditions of uncertainty of the a priori data on measurement errors.
      
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In this paper a system of fundamental equations and calculating method of internal ballistics of solid-propellant rockets is given. Because the effects of transformation between the gaseous phase and the condensed phase are included, the system of fundamental equations is applicable to both equilibrium flow and frozen flow. The calculating method of equilibrium flow in nozzle is described ein detail.The results of calculation show that the size of condensed particles has influence on both specific impulse and...

In this paper a system of fundamental equations and calculating method of internal ballistics of solid-propellant rockets is given. Because the effects of transformation between the gaseous phase and the condensed phase are included, the system of fundamental equations is applicable to both equilibrium flow and frozen flow. The calculating method of equilibrium flow in nozzle is described ein detail.The results of calculation show that the size of condensed particles has influence on both specific impulse and equilibrium combustion pressure. In combustion chamber the relative lag of condensed particles velocity is considerable. Not only the divergence half-angle of nozzle but also the convergence half-angle is very important for specific impulse losses due to the lags between two phases.

本文给出固体火箭发动机内弹道的基本方程组和计算方法。由于考虑了气相和凝相之间转化的效应,因而方程组对于平衡流和冻结流都是适用的。尤其是喷管平衡流的计算方法文中作了详细的阐述。 计算结果表明,凝相质点的尺寸对比冲和平衡压力均有影响。在燃烧室中,凝相质点的相对速度滞后是很可观的。就相间滞后带来的比冲损失而言,不仅喷管扩张半角而且收敛半角都是极其重要的。

This paper describes the nonliear finite element method for structure com posed of fiber winding revolutionary shells and axisymmetric solids. The formulations of the eight nodal isoparametric element and the quasi-conform ing revolutionary shell element with considering axisymmetric large deformation are presented. Corresponding programs for nonlinear analysis (DDJ-FZD)are also developed. The numerical results show a good agreement with the experimental data and the existing analytic solutions.

本文叙述纤维缠绕的或者各向同性的旋转壳体与回转体构成的组合结构在轴对称大变形状态下的有限元分析方法。给出了在轴对称大变形条件下的八结点等参单元和拟协调双曲壳单元的有限元列式,以及相应的有限元非线性分析程序(DDJ—FZD)。算例结果与已知的实验值和理论值均符合较好。复合材料固体火箭发动机体是一个由纤维缠绕的旋转壳体和金属接头等回转体构件组成的轴对称组合结构。由文献[5]和有关实验资料可知,这一结构通常处在大变形状态下工作,因此对其进行大变形非线性分析是有实际意义的。目前国内对这一课题的研究还不多。本文对这一问题进行了研究,其中考虑大变形影响的有限元列式是在固定座标系中推得的,非线性方程采用载荷增量法与Newton—Raphson迭代法相结合的混合法求解。

The stability of thin laminated circular cylindrical shells with clastic core under uniform axial compression, lateral pressure and hydrostatic pressure are analyzed. The Galerkin-difference method is used to simplify the modified Donnell equation into linear equations. Then according to the stability criterion, the critical loads can be found. Some examples are present. The results have shown that the material behavior of the core and the boundary conditions of shell have a great effect on stability. The method...

The stability of thin laminated circular cylindrical shells with clastic core under uniform axial compression, lateral pressure and hydrostatic pressure are analyzed. The Galerkin-difference method is used to simplify the modified Donnell equation into linear equations. Then according to the stability criterion, the critical loads can be found. Some examples are present. The results have shown that the material behavior of the core and the boundary conditions of shell have a great effect on stability. The method appears to be worth recommending, especially while designing solid propellenters.

本文分析了充有弹性介质的多层复合材料圆筒壳在轴压、侧压与水压作用下的稳定性。所采用的方法是用Galerkin—差分法求介改型的Donnell方程,再根据稳定准则确定临界值。若干算例已在文中列出。计算结果表明:内部介质材料性能和壳体的边界条件对临界载荷有较大影响。本文采用的分析方法和结论可供固体火箭发动机壳体设计工作者参考。

 
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