Global Stability and Control Derivative Modeling Using Design of Experiments

In this paper, applicability of modeling aircraft nondimensional aerodynamic-propulsive coefficients using a design of experiments technique based on a linear parameter variation model is investigated. A case study is conducted to estimate the stability and control derivatives from the aircraft response. For demonstrating technique feasibility, a nonlinear simulator for an F-16 was used to assess the proposed approach. A set of multiple orthogonal phase-optimized multi-sine inputs (elevator, aileron, rudder, and throttle) is initially executed at different locations over the operational flight envelope. These inputs are designed as optimization problems using a genetic algorithm search technique. The aircraft response is used in identifying the stability and control derivative variations with velocity, altitude, aircraft mass, and center 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 stability and control derivatives. The proposed approach is generally applicable for wind tunnel and flight test.

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