Longitudinal stability of blended-wing-body aircraft based on experimental bifurcation analysis

被引：0
|
作者：
Fu J. [1 ]
Shi Z. [1 ]
Geng X. [1 ]
Zhu J. [1 ]
Wang L. [1 ]
Wu D. [2 ]
Pan L. [2 ]
机构：
[1] College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] COMAC Shanghai Aircraft Design and Research Institute, Shanghai
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷 / 01期
基金：
中国国家自然科学基金;
关键词：
Blended-Wing-Body (BWB); Experimental bifurcation analysis; Longitudinal stability; Nonlinear dynamic inversion; Virtual flight tests;
D O I：
10.7527/S1000-6893.2020.24931
中图分类号：
学科分类号：
摘要：
Bifurcation analysis and the catastrophe theory are used to study the longitudinal stability of Blended-Wing-Body (BWB) aircraft. Equilibrium branches of the angle of attack with the elevator are obtained, and stability of the branches and the catastrophe points analyzed. Then bifurcation analysis is introduced into the virtual flight tests to physically track the equilibrium branches, enabling the experimental bifurcation analysis research in the wind tunnel. A pseudo-linear controller based on the nonlinear dynamic inverse is designed, with the open-loop and closed-loop experimental bifurcation diagrams obtained and analyzed. The comparative analysis shows that the theoretical bifurcation analysis and the open-loop experimental bifurcation analysis are basically consistent in the range of small angles of attack, verifying the feasibility and accuracy of the experimental bifurcation analysis method. The longitudinal instability of the BWB aircraft is mainly caused by the sudden changes of Cmα. The closed-loop experimental bifurcation analysis realizes the nonlinear global stability control, transforming the unstable equilibrium branch into a stable one through the longitudinal nonlinear controller. © 2022, Beihang University Aerospace Knowledge Press. All right reserved.
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