 全文文献 工具书 数字 学术定义 翻译助手 学术趋势 更多   structure influence coefficient method 在 航空航天科学与工程 分类中 的翻译结果: 查询用时：1.396秒 在分类学科中查询 所有学科 航空航天科学与工程 力学 更多类别查询 历史查询  structure influence coefficient method 结构影响系数法(1)柔度影响系数法(1)结构影响系数法(1)  结构影响系数法
 It is solved based on Euler/N-S equations with cell-centered finite-volume algorithm. The structure deformation is calculated by a structure influence coefficient method. We use a triangle area weight method and a constant volume transformation(CVT) method to solve the fluid-structure interaction problem. 在C-H网格的基础上,采用Jam eson的中心差分有限体积法求解Eu ler/N-S方程,采用结构影响系数法计算结构的弹性变形,用三角元面积加权法和常体积转换法(CVT)实现流固耦合,计算了弹性后掠机翼在跨音速状态的静气动弹性问题 短句来源 结构影响系数法
 It is solved based on Euler/N-S equations with cell-centered finite-volume algorithm. The structure deformation is calculated by a structure influence coefficient method. We use a triangle area weight method and a constant volume transformation(CVT) method to solve the fluid-structure interaction problem. 在C-H网格的基础上,采用Jam eson的中心差分有限体积法求解Eu ler/N-S方程,采用结构影响系数法计算结构的弹性变形,用三角元面积加权法和常体积转换法(CVT)实现流固耦合,计算了弹性后掠机翼在跨音速状态的静气动弹性问题 短句来源 查询“structure influence coefficient method”译词为用户自定义的双语例句

我想查看译文中含有：的双语例句 没有找到相关例句 A numerical method is presented for predicting the aerodynamic characteristics of elastic aircraft under quasi-static approximation. This method can be used to evaluate the lift distribution and 11 main longitudinal aerodynamic derivatives of elastic aircraft at subsonic speeds. The aerodynamic calculations are based on the Green's function method. The structure deformation is evaluated by the free structure influence coefficient method. The combination of these methods can provide an efficient,... A numerical method is presented for predicting the aerodynamic characteristics of elastic aircraft under quasi-static approximation. This method can be used to evaluate the lift distribution and 11 main longitudinal aerodynamic derivatives of elastic aircraft at subsonic speeds. The aerodynamic calculations are based on the Green's function method. The structure deformation is evaluated by the free structure influence coefficient method. The combination of these methods can provide an efficient, general and flexible aerodynamic tool for design of elastic aircraft.Several numerical examples are given and some dynamical problems of elastic aircraft are also discussed in this paper. The derivatives evaluated in this paper can be directly adopted in analysis of stability and control of elastic aircraft. 本文介绍一种准静弹性飞机气动特性的数值计算方法。可以用它来计算亚音速时弹性飞机的升力分布及11个主要的纵向气动导数。 文中附有算例,并对准静弹性飞机动态特性方面的一些问题进行了分析和讨论。 本文所得的导数可直接用于弹性飞机操纵性与稳定性的分析。 Modern large aircraft have become increasingly flexible, causing its deformation to become increasingly large. We contracted to develop an analysis method for calculating loads acting on flexible aircraft wing with its real deformation considered. In this paper, we explain in much detail the analysis method we developed under contract. Here we give only a briefing of our method. It involves the calculation of aerodynamic loads followed by calculation of deformation; this cycle is repeated again and again until... Modern large aircraft have become increasingly flexible, causing its deformation to become increasingly large. We contracted to develop an analysis method for calculating loads acting on flexible aircraft wing with its real deformation considered. In this paper, we explain in much detail the analysis method we developed under contract. Here we give only a briefing of our method. It involves the calculation of aerodynamic loads followed by calculation of deformation; this cycle is repeated again and again until the actual aerodynamic loads and the actual deformation of wing are both obtained. The aerodynamic loads are calculated by solving Navier-Stokes equations with the second order implicit LU-NND algorithm; the structure deformation is calculated by structure influence coefficient method. In this paper, we take a swept-back wing as numerical example and the numerical simulation results obtained with our method show preliminarily that our method is feasible. The numerical example also contains a number of interesting results that correspond to the discussion of the detailed explanation of our method given in this paper. 以 N- S方程为控制方程计算机翼气动力 ,考虑机翼的结构弹性的影响 ,采用结构影响系数法建立结构平衡方程计算弹性变形 ,两个方程相互迭代耦合求解 ,计算弹性飞机飞行中的真实载荷 ,并在已知弹性机翼飞行时总载荷的情况下 ,确定结构弹性在飞行中对载荷的贡献 In order to study in depth the static aeroelastic characteristics of supercritical wing,we present the analysis method we developed.The feature of our analysis method is that we employ Euler equations for aerodynamic calculations.As usual,our analysis method involves the calculation of aerodynamic loads followed by calculation of deformation;this cycle is repeated again and again until the actual aerodynamic loads and the actual deformation of wing are both obtained.The aerodynamic loads are calculated by solving... In order to study in depth the static aeroelastic characteristics of supercritical wing,we present the analysis method we developed.The feature of our analysis method is that we employ Euler equations for aerodynamic calculations.As usual,our analysis method involves the calculation of aerodynamic loads followed by calculation of deformation;this cycle is repeated again and again until the actual aerodynamic loads and the actual deformation of wing are both obtained.The aerodynamic loads are calculated by solving Euler equations with a finite volume algorithm based on center difference;the structure deformation is calculated by structure influence coefficient method.We take a swept-back wing as numerical example and the numerical simulation results obtained with our method show preliminarily that our method is feasible.We also calculate the static aeroelastic deformation for three wings(swept back wing,straight wing,forward swept wing) that adopt supercritical airfoil(RAE2822) or general airfoil(NACA0012 or NACA64A006) with total lift unchanged;we find that the center of rigidity for the forward swept wing is at the 40.0% of chord,the pressure center for the general-airfoil NACA0012 wing is at the 26.1% of chord,the pressure center for the supercritical-airfoil wing is at the 50.4% of chord.Obviously,the pressure center of supercritical wing shifts backwards;this is the main reason why pitching up deformation of supercritical wing is less than that of general wing. 采用三维Eu ler方程为控制方程,计算机翼所受的气动力与静气动弹性平衡方程耦合求解,研究超临界机翼的静气动弹性规律,并以超临界弹性机翼和普通弹性机翼为算例,计算弹性飞机飞行中的真实载荷和扭转变形,并在已知弹性机翼飞行时总载荷保持不变的情况下,确定超临界机翼结构弹性在飞行中对载荷的影响。 << 更多相关文摘 相关查询

 CNKI小工具 在英文学术搜索中查有关structure influence coefficient method的内容 在知识搜索中查有关structure influence coefficient method的内容 在数字搜索中查有关structure influence coefficient method的内容 在概念知识元中查有关structure influence coefficient method的内容 在学术趋势中查有关structure influence coefficient method的内容
 CNKI主页 |  设CNKI翻译助手为主页 | 收藏CNKI翻译助手 | 广告服务 | 英文学术搜索 2008 CNKI－中国知网 2008中国知网(cnki) 中国学术期刊(光盘版)电子杂志社