Design of experiments-based stability and control derivative modelling

Abstract

This article investigates modelling aircraft non-dimensional aerodynamic-propulsive coefficients by using a design of experiment technique based on a linear parameter variation model. A case study is conducted to estimate the stability and control derivatives from aircraft response behaviour in longitudinal motion. For demonstrating technique feasibility, a non-linear simulator for the F-16 was used to assess the proposed approach. A set of doublet elevator and throttle inputs is initially executed at different locations over the operational flight envelope. Then, the aircraft response is used in identifying the derivative variations with velocity, altitude, aircraft mass, and centre of gravity position. A sequential experiment using a factorial design and augmented face central axial points was employed to model the variation. The validity of the proposed method was evaluated by comparing the estimated and actual variation of the derivatives. The proposed approach is generally applicable for wind tunnel and flight tests.