解算器的英文

• ik
• resolver
• revolver
• solver

• "解算"英文翻译    resolving; calculating
• "器"英文翻译    implement; utensil; ware
• "解算机 解算器 解算装置" 英文翻译 :    solver
• "ik解算器" 英文翻译 :    ik solvers
• "传输解算器" 英文翻译 :    transolver
• "定位解算器" 英文翻译 :    position resolver
• "方程解算器" 英文翻译 :    equation solver
• "刚体解算器" 英文翻译 :    rigid body solver
• "航向解算器" 英文翻译 :    course resolver
• "球体解算器" 英文翻译 :    ball resolver
• "球形解算器" 英文翻译 :    ball resolver
• "求根解算器" 英文翻译 :    root solver
• "矢量解算器" 英文翻译 :    vector solver
• "数字解算器" 英文翻译 :    digital resolver; dr
• "同步解算器" 英文翻译 :    synchroresolver
• "解算器分解器" 英文翻译 :    resolver
• "平片式解算器" 英文翻译 :    flat-card resolver
• "有限元解算器" 英文翻译 :    ug/fea solver ug
• "代数方程解算器" 英文翻译 :    algebraic equation solver
• "电位器式解算器" 英文翻译 :    potentiometer resolver
• "独立域问题解算器" 英文翻译 :    domain-independent problem solver
• "多项式方程解算器" 英文翻译 :    polynomial equation solver
• "模拟方程解算器" 英文翻译 :    analog equation solver
• "实际真空速解算器" 英文翻译 :    true airspeed resolver
• "同步解算器变压器" 英文翻译 :    synchro resolver transformator; synchro resolver transformer

• After defining the model of fem and the corresponding loads , we begin to take the advantage of the software of fem the method of spectrum analysis to calculate and analyze its responses of the whole model ' s structures
  当用于应力分析的结构有限元模型确定以及加载完成之后，就开始使用nastran解算器以及谱分析的方法来计算和分析其结构的整体响应。
• The transonic steady / unsteady navier - stokes / euler flow solvers based on ausm + scheme have been developed in this dissertation . the structured grids are generated using transfinite interpolation . a cell - centered finite volume approach is used
  因此，研究开发高效、高精度、高鲁棒性、实用的跨音速定常、非定常navier - stokes euler方程解算器至关重要。
• Furthermore , numerical simulations for steady or unsteady transonic flow of rae2822 and dfvlr - r2 supercritical airfoils and a supercritical wings are investigated . the numerical results are in good agreement with experimental data where available
  进而，应用该解算器对超临界翼型rae2822 、 dfvlr - r2及某超临界机翼的定常或非定常流场进行了数值计算研究，得出了良好、合理的结论。
• This deforming method coupled with ale euler solver is applied to simulate unsteady transonic flow about oscillating airfoil ( 2 - d ) and oscillating rigid rectangular wing ( 3 - d ) . computational results are in good agreement with experimental data
  本文将网格变形方法与数值解算器耦合起来求解了二维振动翼型绕流和三维振动矩形机翼绕流，计算结果与实验结果一致，证明本文的数值方法具有较高的准确性。
• For unsteady - state calculations , jameson ' s dual - time method is used . to confirm the validity , effectivity and reliability of developed flow solvers based on ausm + scheme , test cases of steady / unsteady transonic flow of naca0012 airfoil and onera m6 wings are investigated first
  本文首先以naca0012翼型、 oneram6机翼为算例，验证了本文发展的基于ausm +格式的跨音速定常、非定常navier - stokes euler方程解算器是正确、有效和可靠的。
• This paper describes the development and trend of the weapon bay which the fighter plane equipped with at home and abroad , especially the missile ejection mechanism ; the kinematics and dynamics analysis about a sort of missile ejection mechanism is discussed and the model of the system is simulated by the tools in matlab , such as solver and so on
  本文在讲述国内外飞机武器舱，特别是导弹弹射系统的发展现状和发展趋势的基础上，对现有引进的某型系统机构进行了运动学和主要部件的动力学分析，并通过matlab提供的解算器等工具对建立的系统模型进行了仿真。
• In spite of these advantages , we should concentrate on how to extend the representation of modes , how to apply to unstructured grids , etc . and when combining pod and saa , it is necessary to know how to represent the shape and how to control the range of seeking and iteration number
  但在研究的过程中,我们发现正交分解方法也存在如下问题:如何增强基模态的表达能力,如何将该方法应用于非结构网格的计算等。在利用模拟退火算法结合解算器进行翼型反设计时,则需要考虑如何表达几何外形形状,怎样控制搜索范围以及如何减小搜索次数等实际问题。
• We also compute naca0012 airfoil and certain three - foil flow field separately with explicit 4 - step runge - kutta scheme and the implicit lu - sgs scheme and results show the latter is much more efficient . in the end , the capability of the algorithm to deal with multi - bodies in relative movements is demonstrated by a dropping drank problem . it turns out that the unstructured overset grid is valuable and promising in practical application
  同时为了验证隐式lu - sgs格式的收敛效果,我们对基于单块网格的naca0012翼型与某三段翼型在不同的来流条件下,分别用带隐式的lu - sgs格式与显式的四步runge - kutta格式的解算器进行了数值模拟。
• However , the simulated annealing algorithm will expand too much time to estimate the values of objective function when applied to aerodynamics optimizations . the way to remedy this problem in this dissertation is by improving the efficiency of optimizer and the cfd - solver . our cfd - solver is base on the modification to the proper orthogonal decomposition ( pod ) method that can produce a finite series of basis functions or modes through the solution of snapshots
  但对于气动外形优化设计问题来说,由于评估需要解决的问题的目标函数值需要多次调用流场解算器,会导致用模拟退火算法进行优化设计的计算工作量过大,因此需要我们对流场解算器和优化方法两个方面进行研究以寻找此问题的解决办法。