Work

Research on nonlinear instability of blended-wing-body aircraft based on experimental bifurcation analysis

Year: 2024

Type: article

Abstract: Focusing on the nonlinear instability problem of the blended-wing-body aircraft, first, numerical bifurcation analysis is adopted to obtain catastrophe points and branches where the elevator is taken as a continuous parameter. Second, based on virtual flight tests and bifurcation theory, an experimental bifurcation analysis method is developed. Open-loop and closed-loop experiments are carried out, and the corresponding experimental bifurcation diagrams are obtained. The comparative analysis shows that the experimental bifurcation analysis enables the aircraft to make a response that is close to reality under the influence of nonlinear and unsteady aerodynamics and has a more intuitive embodiment of instability characteristics, providing an accurate prediction of departure. The open-loop experiment predicts a sudden longitudinal nose-up at an angle of attack of 7.4°. The closed-loop experiment can transform the open-loop unstable branch into a stable branch. However, roll instability still occurs at a critical angle of attack of 16.0°. These research results provide important dynamic information for the stable flight and the design of the controller.

Source: AIP Advances

DOI: 10.1063/5.0232908

Authors: Junquan Fu, Zhiwei Shi, Xi Geng, Yongliang Chen

Institutions: Nanchang Hangkong University, Nanjing University of Aeronautics and Astronautics

Language: English

Topic: Aerospace and Aviation Technology

Subfield: Aerospace Engineering

Field: Engineering

Domain: Physical Sciences

Open Access status: gold

Estimated APC paid: $1,350

Funders: Nanchang Hangkong University, National Natural Science Foundation of China, Ministry of Industry and Information Technology of the People's Republic of China, Fundamental Research Funds for the Central Universities