Piloted and batch simulations of the aeroservoelastic response of flight vehicles are essential tools in the development of advanced flight control systems. In these simulations the number of differential equations must be sufficiently large to yield the required accuracy, yet small enough to enable real- time evaluations of the aircraft flying qualities and rapid batch simulations for control law design. The challenge of these conflicting demands is made especially difficult by the limited accuracy of the analytical modeling techniques used, nonlinearities in the quasi-steady equations of motion and by the complex characteristics of the unsteady aerodynamic forces. In this paper, a brief survey of some of the techniques that have been used at Boeing to develop aeroservoelastic math models for control system design and evaluation are presented, along with a discussion of the strengths and weaknesses of the various techniques. The modeling techniques discussed include frequency response fitting methods, rational function approximation methods, and the P- Transform technique. Integration of the aeroservoelastic structural dynamic model with a nonlinear flight simulation is also discussed.