Realizing data exchange to reflect coupling between fluid and structures is essential to solving static aeroelasticity problems.

Three force equilibrium methods of static aeroelasticity are compared with.

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.

On this base, the static aeroelastics problems of wing and aircraft are investigated by coupled with structure dynamic equation.

In the study,the aerodynamic analysis of wing is achieved by solving 3D unstructured Euler equations,which integrated static aeroelastic effect.

As a function of flight dynamic pressure, angle of attack, deflection of horizontal tail and longitudinal acceleration, the longitudinal static aeroelastic response characteristics of an aircraft are analyzed by using two static aeroelastic analysis methods, i.

A method that the application of the coupled technique of CFD simulation and structural finite element model to static aeroelasticity correction after a general wind tunnel test has been introduced in the study.

The Role of Research on Servoaeroelasticity in Design of UAV;

A New Interface Mapping and Marching Method for Aeroelasticity;

A new interface mapping method for aeroelasticity;