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   计算气动力 的翻译结果: 查询用时:0.181秒
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计算气动力
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  aerodynamics calculation
     The Viscous Correction Research During the Aerodynamics Calculation Via Euler Equation
     欧拉方程计算气动力时的粘性修正研究
短句来源
  “计算气动力”译为未确定词的双语例句
     The analysis of numerical examples proves that the numerical procedure of this paper can be used to qualitative research, but cannot get accurate aerodynamics force when applying to engineering .
     计算实例分析说明了本文数值方法在定性研究上已经可用,在定量计算气动力上还需进一步提高改进。
短句来源
     The software package have some functions as follows: calculating the shrapnel's diagnostic parameters such as the mass and the pole moment of inertia, the inner and outer ballistic characteristic, the aerodynamic force and power, and so on.
     该榴弹CAD软件具有以下一些功能模块:计算弹丸质量、极转动惯量等构造特征数,计算内、外弹道特性,计算气动力,威力等。
短句来源
     This article expounds a method for calculation of the water wave effect on aerodynamics of a three-dimensional vehicle flying close to water surface. The method is based on the boundary element method, and under the assumption of linear wave.
     本文以边界元法为基础 ,在线性水波的假定下 ,对贴近水面飞行的三维飞行器 ,提出了一种计算气动力中水波效应的方法。
短句来源
     The influence factor of computational speed about elements was researched in this paper,by using the method of parallel compute,and of aerodynamic property was analyzed in the condition of different boundary condition.
     文中采用了并行计算来研究单元数对计算速度的影响; 分析了不同的边界条件对计算气动力特性的影响;
短句来源
  相似匹配句对
     Calculation of Flow Field of Automobile
     汽车气动力计算
短句来源
     We also give a new correction factor to simplify the calculation of the Unstatistic.
     的计算
短句来源
     AERODYNAMIC COMPUTATIONS FOR LAUNCH VEHICLE WITH STRAP-ON BOOSTERS
     捆绑式运载火箭气动力计算
短句来源
     Calculation of Skewed Plates
     斜板的计算
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The features of various kinds of super caliber stabilized assembly of fin stabilized projectile are reviewed and analyzed in this thesis. A new idea that to abandon the traditional cylinder and to take the aerodynamic force of the muzzle blast as the only fin extending force is put forward based on the above analysis and is implemented in a projectile. In conclusion, both the theoretical analysis and the result of the caculation have shown that the idea of unfolding the fins in the intermediate period is...

The features of various kinds of super caliber stabilized assembly of fin stabilized projectile are reviewed and analyzed in this thesis. A new idea that to abandon the traditional cylinder and to take the aerodynamic force of the muzzle blast as the only fin extending force is put forward based on the above analysis and is implemented in a projectile. In conclusion, both the theoretical analysis and the result of the caculation have shown that the idea of unfolding the fins in the intermediate period is practicable.

应用二维流场理论开辟高速滑膛尾翼弹后效开翼的新途径.在分析现有国内外弹丸尾翼稳定装置的结构特点及优缺点的基础上,提出了稳定装置的改进方向,并设计出了一种新型稳定装置结构,对新型稳定装置进行了结构分析、强度计算、气动力分析及膛内自锁可靠性的计算,并用二维流场理论分析了弹丸尾翼的张开过程.证明了尾翼弹后效开翼途径的可行性.

In this thesis, the maneuver missiles with a blunt bent nose and a bicone body are selected as an example to analyze the reentry trajectory pattern of the missiles. Many problems are mainly studied, such as the formation principle of gyroidal trajectory, the effects of the roll angular velocity and geometry parameters on the gyroidal trajectory. Finally, the gyroidal trajectory control method through adjusting the motion of additive weight blocks is developed.

针对弯头双锥机动弹头 ,采用内伏流牛顿方法和Euler方程数值方法计算气动力 ,并与六自由度弹道方程组耦合计算 ,分析了再入过程中的螺旋弹道特性以及滚转角速度和弹头几何参数等对螺旋弹道的影响 ,最后分析了利用控制质心横向运动来控制弹头滚转的方法。

This article expounds a method for calculation of the water wave effect on aerodynamics of a three-dimensional vehicle flying close to water surface. The method is based on the boundary element method, and under the assumption of linear wave. The paper consists of three parts: Ⅰ. Analyzing the difficulty in calculating the distribution of unsteady pressure when using BEM and the reason for it. We point out that for unsteady problem there can’t be a difference of an arbitrary function of time between the solutions...

This article expounds a method for calculation of the water wave effect on aerodynamics of a three-dimensional vehicle flying close to water surface. The method is based on the boundary element method, and under the assumption of linear wave. The paper consists of three parts: Ⅰ. Analyzing the difficulty in calculating the distribution of unsteady pressure when using BEM and the reason for it. We point out that for unsteady problem there can’t be a difference of an arbitrary function of time between the solutions of intensity distribution and the solution must be unique. So there is only one proper way to impose the boundary condition at infinity. On this, a method to overcome the difficulty is given. Ⅱ. The methematical description of wave effect, including all kinds of initial or/and boundary conditions and the final boundary integral formula of solution. We give the differential-integral equation that is satisfied by the wave height under the impact of pressure field generated by the flight. The basic solution method and the process of solution are also given. Ⅲ. Calculating the aerodynamic characteristics with the effect of water wave of an airplane. The airplane has a 3D complex shape and flies close to water surface. The 3D shape includes the body, the wings, the end plates, the vertical-tail and the horizontal-tail. The change of wave effect with the angle of attack, the height of the airplane, the wave amplitude, the wave length, and the direction of the wave are given. Useful conclusions are drawn. At the same time it is proved that the method of computing the distribution of the strength of unsteady vortex is correct.

本文以边界元法为基础 ,在线性水波的假定下 ,对贴近水面飞行的三维飞行器 ,提出了一种计算气动力中水波效应的方法。本文共分三部分 :Ⅰ .分析了用边界元法计算非定常压力分布的困难和产生这一困难的原因 ,指出了对非定常问题 ,强度分布函数解必须保证唯一性而不能差一个随时间变化的常数。为此对无穷远条件必须有一个正确提法 ,并在此基础上给出了克服这一困难的方法。Ⅱ .水波效应问题的数学提法 ,包括各种定解条件和解的最后边界积分形式 ,导出了在飞行器形成的压力场的作用下波高应满足的微分—积分方程 ,给出了求解的基本方法和步骤。Ⅲ .对于一个包含有复杂外形的机身、机翼、端板、垂尾和平尾的三维机型在贴近水面飞行时 ,作了包括水波效应在内的全机气动力计算 ,给出了水波效应随攻角、飞行高度、波幅、波长及波的入射方向等的变化 ,得到了有意义的结果 ,同时也证明了本文提出的计算非定常涡强分布函数的方法是正确的

 
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