Modelling aileron and spoiler deflections with the linear frequency domain method (LFD) for subsonic flight conditions

Abstract

The modelling of two surrogate models for predicting the aerodynamic responses of aileron and spoiler control surface in subsonic flight is presented. The prepared Reduced Order Models prove useful when quick estimations for a large number of variations are required. The LFD Method was used for the simulation study. Each surrogate contained a database of 100 control surface dynamic responses over a spectrum of 200 harmonics computed with LFD. To interpolate new results, the DLR surrogate modelling toolbox, SMARTy was utilized. The database samples were prepared in a Halton Sequence, making interpolation reliable. The surrogate parameter space was the Mach number, Reynolds number, angle of attack, control surface deflection angle, and the control surface chord length. The LFD Method proved effective for the mentioned purpose: the surrogates were accurate, up to 15% of relative error, in reproducing dynamic responses of aileron and spoiler deflections at low speed, within the limitations of flow field linearity, as well as surrogate prediction capability. The restrictions of the surrogate, and the reasoning thereof are also presented in detail in the study. Future load alleviation studies are a potential of the findings here. LFD is an innovative technique for load prediction and alleviation studies. This paper provides a reference for engineers wishing to use the method for the two mentioned control surfaces, or the like.