Using the complex potential method in the plane theory of elasticity of an anisotropic body , the series solution of finite anisotropic thin plate containing an elliptical inclusion is proposed with the help of faber series . a hybrid element with an elliptical inclusion for anisotropic materials is obtained by using the hybrid variable principle , and the element efficiency is verified by numerical examples . the state of the damage is modeled by an elliptical soft inclusion , and using the point stress criterion based on characteristic curve and yamada - sun etc . criteria , the prediction of the strength of a composite laminate with damage is set up 首先基于经典层板理论，将复合材料层板的弹性问题化归为均匀各向异性板来求解；采用各向异性体平面弹性理论中的复势方法，以faber级数为工具，给出了有限大含椭圆核各向异性板弹性问题的级数解形式；利用杂交变分原理，成功导出含椭圆核各向异性板杂交应力有限元，并用算例验证了该单元的可行性和有效性；采用含刚度折减椭圆形弹性核的冲击损伤模型，引入基于特征曲线和yamada - sun破坏准则的点应力判据，建立了含损伤复合材料层板剩余强度的分析方法；通过数值计算详细讨论了各种几何参数对损伤层板应力分布、剩余强度的影响，得到了一系列对工程应用具有实用价值的结论。
The direct analysis method has more efficient than the line programming for the shakedown analysis of contact surface layer , therefore , the mentality of shakedown analysis of contact surface layer was introduced based on the direct analysis method as follows : first , the direct method for shakedown analysis was presented and its application to a two - dimensional rolling / sliding contact problem was demonstrated . the direct method consists of operator split technique , which transforms the elastic - plastic problem into a purely elastic problem and a residual problem with prescribed eigenstrains , and an incremental projection method to determine the eigenstrain 这些方法各有创新，其特点是计算速度快、收敛性好及精度可靠，计算规模避免了弹塑性随动强化分析的非线性的影响，并使弹塑性问题转化为残余问题和线弹性问题，适用于滚动、滚滑及滑动接触失效分析，从而有效地解决了接触体安定性分析与裂纹萌生寿命预测的实际问题，也是本文对表面强化接触失效的安定分析成为可能。
The research of this dissertation is focused on how to solve the 3 - dimensional compressible navier - stokes equations by the implicit finite difference algorithm and to simulate numerically the unsteady subsonic and transonic viscous flows around rigid and elastic wings . on the base of them the aeroelastic characterictics of an elastic wing have been studied 本文的主要工作是用隐式有限差分法求解三维非定常紊流n - s方程组，数值模拟刚性机翼及弹性机翼的亚、跨、超音速定常及非定常粘性绕流，并在此基础上研究了弹性机翼的气动弹性问题。
Secondly , the static aeroelastic problems and jig - shape design , as a kind of multi - disciplinary design optimization ( mdo ) , are investigated for sweep wing and super - critical wing . numerical results are in good agreement with other reference data . the method and the program presented in this paper are verified 分别以某后掠机翼和超临界机翼为算例，对机翼的静气动弹性问题以及基于静气动弹性的型架外形优化设计和飞行姿态确定进行研究，计算结果和有关文献的结果进行了比较，吻合很好。
