Generation of a reduced-order LPV/LFT model from a set of large-scale MIMO LTI flexible aircraft models

Parametric reduced order model approach for rapid dynamic loads prediction

“…In this work the approach of PMOR by state-space matrices interpolation is chosen. This method has been successfully applied in the past in aeroelasticity, for fast flutter clearance of a wing-store configuration [33], in control system design of a flexible aircraft [34], in unsteady CFD [35] and in other engineering domains [36], but not for gust and manoeuvre loads prediction. Hereafter, the PMOR framework proposed in [37] is followed.…”

“…As the Balanced Truncation is not a physics-based reduction, the states of the ROMs at different parameter values lie in unrelated subspaces and, before the interpolation, must be transformed, through a similarity transformation 8 ,5 = 5 8 ,¡ ¢ , to a congruent common subspace, spanned by the column of the matrix B ∈ ℝ › • x oe . The choice of this reference subspace is critical for the accuracy of the entire procedure; it is problem-dependent and various options have been proposed [30], [34]. A solution that, for the application considered, is robust and delivers accurate results is adopting the first !…”

“…The reduced state-space matrices are interpolated elementwise through a simple yet efficient bilinear interpolant and FOMs are constructed at each validation point to assess the accuracy of the procedure. Time simulations of the gust response, considering ten gust gradients chosen to cover evenly the entire range defined by the airworthiness regulations (9m -107m) [1], [34], and pitching manoeuvres are then carried out using a state-transition matrix integration method.…”

Parametric reduced-order model approach for simulation and optimization of aeroelastic systems with structural nonlinearities

“…The procedure applied herein is based on the construction of a database of ROMs at few selected sampling points C Q R , ; S T in the parameter domain and by interpolation of the reduced state-space matrices at all the other points of interest for the simulation C > G , ; ̅ U . This method has been successfully applied in the past in aeroelasticity, for fast flutter clearance of a wing-store configuration 22 , in control system design of a flexible aircraft 23 and unsteady CFD 24 . This paper presents its extension to the transient response and loads prediction of aeroelastic systems with concentrated structural nonlinearities and its application in an optimization framework.…”

Cessna Citation X Business Aircraft Eigenvalue Stability– Part 1: a New GUI for the LFRs Generation

“…In order to facilitate the modeling and the use of LFR systems, a toolbox was developed by ONERA, which used Matlab® software that contained several useful features [35].…”