Unsteady aerodynamic identification of aircraft at high angles of attack

ZHANG Wanxin; ZHU Jihong

doi:10.16511/j.cnki.qhdxxb.2017.25.021

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Journal of Tsinghua University(Science and Technology) ›› 2017, Vol. 57 ›› Issue (7) : 673-679. DOI: 10.16511/j.cnki.qhdxxb.2017.25.021

COMPUTER SCIENCE AND TECHNOLOGY

Unsteady aerodynamic identification of aircraft at high angles of attack

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Abstract

Existing models cannot accurately identify aircraft at high angles of attack due to the unsteady aerodynamic characteristics high angle of attack flight. This paper presents a model using a dynamic block with a static block based on a general aerodynamic derivatives model, which was inspired by the modelling structure of the Wiener model. The model identification is then based on a squared correlation coefficient that estimates the contribution of each model term. The data processing procedure for the parameter estimations is given. Wind tunnel tests with a model similar to an F-22 are used to verify the method. The results show that the method is able to accurately identify the unsteady aerodynamic parameters with a relative error below 5%. The model can effectively describe the unsteady aerodynamic parameters.

Key words

unsteady aerodynamic / high angles of attack / modeling / parameter identification / wind tunnel test / aerodynamic derivative / block oriented / squared correlation coefficient

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ZHANG Wanxin, ZHU Jihong. Unsteady aerodynamic identification of aircraft at high angles of attack[J]. Journal of Tsinghua University(Science and Technology). 2017, 57(7): 673-679 https://doi.org/10.16511/j.cnki.qhdxxb.2017.25.021

References

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