Aeroelastic methodology for flight vehicles

• Main Author: Bach, Can T.
• Published: Swansea University 2004
• Subjects: 629.13
• Online Access: https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.635997

This thesis is set out as follows: In Chapter 1, the definition of flutter is given, together with a brief history and a short summary of some of the well know methods used in modeling and formulating the components of the equations of motion that have been employed previously. Chapter 2 includes the formulation of the numerical equations of motion for different types of structure and the numerical techniques used to solve these system of equations to obtain the structural characteristic eigensolution. Chapter 3 demonstrates the linear methods used in the panel method to compute the components of aerodynamic forces in the equations of motion, and their application in the solution of aeroelastic and aeroservoelastic problems. Chapter 4 shows the formulation of the nonlinear aerodynamic force component and its integration with the aeroelastic and aeroservoelastic multidiscipline. The formulation of the sensor and control systems and their integration are also detailed in this chapter. Chapter 5 gives the example test cases used for the aeroelastic and aeroservoelastic analysis. Chapter 6 is a short conclusion and is a summary of the study presented herein. A Matlab independent modeling of the aeroservoelastic integration is included in Appendix A. Appendix B and C give the example problem modeling data and formats.