Controlling transonic aeroelasticity is a formidable task, not only because of the difficulty in modelling the nonlinear aerodynamic behaviour but also due to an inherent loss of controllability caused by the mixed subsonic‐supersonic flow prevailing on the lifting surfaces. A normal shock wave is the boundary line between such characteristically different flows, which in the steady state is also the mathematical border between elliptic and hyperbolic types of partial differential equations. This chapter investigates how an adaptive control system can be designed to compensate for the lack of modelling accuracy in the transonic plant. Transonic flow is dominated by large pressure variations caused by mixed subsonic‐supersonic local regions, usually with shock waves embedded in the flowfield. The chapter provides an overview of steady and unsteady transonic flow characteristics. It also discusses transonic aeroelastic plant, adaptive control of control‐surface nonlinearity, and adaptive control of limit‐cycle oscillation.
Adaptive Transonic Aeroservoelasticity
Adaptive Aeroservoelastic Control ; 295-330
2016-04-04
36 pages
Article/Chapter (Book)
Electronic Resource
English
Control law design for transonic aeroservoelasticity
Online Contents | 2007
|Control law design for transonic aeroservoelasticity
Elsevier | 2006
|Wiley | 2014
|NTRS | 1990
|AIAA | 1990
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