Abstract
To study the effects of ice accretion on the longitudinal aerodynamic characteristics of an aircraft, a two-part method for predicting longitudinal aerodynamic derivatives of iced aircraft is proposed. For the aircraft with a flight test, a parameter identification system based on maximum likelihood criterion and a longitudinal nonlinear flight dynamics model is established. For the aircraft without a flight test, an engineering prediction method of aerodynamic derivatives based on an individual component CFD calculation and narrow strip theory is established. According to the flight test data of DHC-6 Twin Otter aircraft from NASA, the longitudinal aerodynamic parameters of both clean and artificially iced aircraft are obtained. Additionally, the longitudinal aerodynamic derivatives of the iced aircraft are calculated. Then, the correctness of the prediction method is verified by comparing the calculated results with the identification results. The comparison of these results shows that the prediction method is correct and accurate, and it can be used to calculate the effects of icing on the aircraft longitudinal aerodynamic parameters.
Highlights
Aircraft icing is the phenomena of ice accretion on the aircraft
Ratvasky and Ranaudo [5] studied the effects of ice accretion on Twin Otter stability and control derivatives with flight test data of clean and artificially iced aircraft, and a modified stepwise regression algorithm was used to obtain pitching and yawing derivatives
According to the National Aeronautics and Space Administration (NASA) flight test data [17,18], the longitudinal aerodynamic parameters of both clean and artificially iced aircraft are obtained by the maximum likelihood identification method
Summary
Aircraft icing is the phenomena of ice accretion on the aircraft. Aircraft icing will change the air flow around the lift surface, reducing the performance and control ability of the aircraft. Ranaudo et al [4] compared the stability and control derivatives between clean and naturally iced aircraft, using a modified maximum likelihood estimation method with flight test data of Twin Otter. Ratvasky and Ranaudo [5] studied the effects of ice accretion on Twin Otter stability and control derivatives with flight test data of clean and artificially iced aircraft, and a modified stepwise regression algorithm was used to obtain pitching and yawing derivatives. According to the NASA flight test data [17,18], the longitudinal aerodynamic parameters of both clean and artificially iced aircraft are obtained by the maximum likelihood identification method. For the aircraft without flight test, an engineering prediction method of aerodynamic derivatives based on individual component CFD calculation and narrow strip theory is established. Compared with the complete CFD method, this method reduces a lot of calculation and can provide fast estimation results for engineering
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