1. covering aeroservoelastic testing programs from the 60s to the early eighties (Ref. 13), as well as more recent wind tunnel test programs (Refs. 14-19) of real or realistic configurations, are included in the bibliography. As to actual airplanes - an examination of Refs. 20-29 will reveal that in the course of development (or later modification) of almost every modern airplane with a high authority active control system, there arose a need to face aeroservoelastic problems and aeroservoelastic designchallenges.
2. The workdiscussed hereislimited to airframes and control systems of fixed wing airplanes operating without significant aerodynamic heating. Selected References, which can serve as starting points for the review of developments in aeroservoelasticity and multidisciplinary interactions on panels, hypersonic vehicles, rotary wing aircraft, and also addressing the problem of whirl flutter, can be found in Refs. 31-38.
3. The classification above, while clearly quite general, provides a standard against which the state of the art in airplane modeling for analysis and modeling for design optimization can be evaluated. There have been major developments in recent years in applied computational fluid dynamics, computational structural mechanics, computer graphics and dynamic system simulation, as well as significant improvements in computational hardware. The aerodynamic analysis and shape synthesis of realistic airplane configurations (Refs. 41-47) is becoming more and more practical. Structural analysis and sizing optimization of complete airframes (Refs. 48-58) are already practiced widely. So are the development and simulation of multi-input multi-output nonlinear control systems for the maneuvering airplane, with their variable gains and different limiters.