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The objective of this paper is to address the selection of dominant modes of a system that can be used to construct a reduced-order model. This work is motivated by high-fidelity computational models that capture fluid and/or structural dynamics, which are prohibitively complex for real-time control. A variety of techniques for obtaining simplified control-oriented models have been developed, e.g...
Wind turbines in a wind farm operate individually to maximize their own power regardless of the impact of aerodynamic interactions on neighboring turbines. There is the potential to increase power and reduce overall structural loads by properly coordinating turbines. To perform control design and analysis, a model needs to be of low computational cost, but retains the necessary dynamics seen in high-fidelity...
A method to reduce the dynamic order of linear parameter-varying (LPV) systems in grid representation is developed in this paper. It approximates balancing and truncation by an oblique projection onto a dominant subspace. The approach is novel in its use of a parameter-varying kernel to define the direction of this projection. Parameter-varying state transformations in general lead to parameter rate...
This paper proposes a novel discrete time identification method for flexible wing aircraft models from simulated data. The special properties of the dynamics arise from the fact that all the poles are located very close to the unit circle and their location changes with the flight velocity. Using identification criteria based on Euclidean metrics suffers from the problem of obtaining instability in...
We propose a method to compute invariant subsets of the robust region-of-attraction for the asymptotically stable equilibrium points of systems with polynomial nominal vector fields and unmodeled dynamics. The effects of unmodeled dynamics are accounted for as systems satisfying certain gain relations or dissipation inequalities. The methodology is extended to systems with parametric uncertainties...
The design of the airframe of an aircraft is constrained due to aeroelastic effects (generally related to the wings) that induce flexible modes on the structure, and may lead to structural instability. This paper addresses the problem of active mode stabilization in an aircraft with flexible wings. The main objective of closed-loop control is to enlarge the allowable flight envelope by stabilizing...
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