Robust Aerodynamic Parameter Estimation of Unmanned Aircraft Based on Two-step Identification

This paper presents the estimation of stability and control derivatives an unmanned aircraft. The aerodynamics are described using regressors composed velocity, angular rates, flow angles surface deflections. flight data is generated from numerical simulation postulated equations motion describing model. Least squares based on equation error method used to estimate parameters representing different force moment aerodynamic coefficients. Statistical analysis done estimates determine accuracy adequacy describe A dynamic identified model improve parameter through regression errors between response. aircraft under consideration a scaled Yak-54 fixed wing aerial vehicle.