Once the forms of the free energy function and dissipation potential function have been specified,the corresponding yield surface,flow rule,hardening rule as well as the elasticity law are deduced in a systematic manner.

The program calculates four axial symmetryviscoelastic examples. Some rules on viscoelastic body are found, the most important ofwhich is: the result of continuous creep is changing pressure distribution, viz, the pointof the maximum pressure changing from central parts to boundary, gradually apart fromelastic principles.

After researching of the yielding function, suitable flow rule and harden law and elastic law of structured soil, a structured soil constituted model has been proposed.

The complete saturation area is described by Kelvin-Voigt's viscoelastic model, and the dry area, by Hooke's elasticity law.

Application of a dynamic market inverse elasticity law with linear and log-linear demand models

To describe this effect, a new finite elasticity law is developed on the basis of a hyperelastic strain energy function, thus governing the constraint of material incompressibility for the solid material.

A study of the stress state near curvilinear holes in shells with a nonlinear elasticity law

The analogy is established by a correspondence between the line representing the elasticity law for the equilibrium stress in viscoelasticity and the axis of kinematic hardening for the plasticity models defined in this paper.

In order to eliminate the influence of static aeroelastics deformation and satisfy the flying characteristic requirement of aircraft, a new approach to the jig-shape elastic wing design problem is presented. The aerodynamic analysis is carried out with solving the 3-dimensional Navier-Stokes equations. On the basis of analysis and coupling with static aeroelastic balancing equation, the jig-shape design of elastic wing is investigated. Throughout the whole optimization process, the accuracy of result is raised...

In order to eliminate the influence of static aeroelastics deformation and satisfy the flying characteristic requirement of aircraft, a new approach to the jig-shape elastic wing design problem is presented. The aerodynamic analysis is carried out with solving the 3-dimensional Navier-Stokes equations. On the basis of analysis and coupling with static aeroelastic balancing equation, the jig-shape design of elastic wing is investigated. Throughout the whole optimization process, the accuracy of result is raised because of the numerical simulation of flowing field around the wing with solutions of N-S equations, and the computation time is reduced significantly because the time averaged compressible N-S equations are solved by the implicit LU-NND algorithm. The design of a swept wing is presented as an example to demonstrate the efficacy of the approach, and the results show that it is correct and effective.

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.

A model based on ideas of thermomechanics,the first and second laws of thermodynamics,is introduced to describe the elasto-plastic behavior of soil deformation,and the method of determining model parameters is provided.Once the forms of the free energy function and dissipation potential function have been specified,the corresponding yield surface,flow rule,hardening rule as well as the elasticity law are deduced in a systematic manner.The plastic work and dissipation energy are distinguished explicitly.Not all...

A model based on ideas of thermomechanics,the first and second laws of thermodynamics,is introduced to describe the elasto-plastic behavior of soil deformation,and the method of determining model parameters is provided.Once the forms of the free energy function and dissipation potential function have been specified,the corresponding yield surface,flow rule,hardening rule as well as the elasticity law are deduced in a systematic manner.The plastic work and dissipation energy are distinguished explicitly.Not all plastic work is dissipated,but some are stored and can be recovered under reversed plastic loading.The physical meaning and range of model parameters are discussed.The parameters can be determined by fitting the triaxial test curves,and the genetic algorithm is adopted by using obtained parameters,and a group of drained triaxial tests are computed,and compared with the experimental results to verify the validity of the model.The model automatically satisfies the laws of thermodynamics,and there is no need to invoke any other postulations.