Zijian Zhu, Ying Bi, Chen Zhu, Zhuolin Ying, Jian Zhang

DOI Number: N/A

Conefernce number: IFASD-2024-039

The Unmanned multi-body aircraft (MBA) presents significant advantages for enhancing aspect ratio, optimizing aerodynamic performance, and reducing the challenges
associated with takeoff and landing. Despite its potential, current research on this configuration predominantly addresses the rigid body aspect, entirely overlooking the geometric nonlinearity arising from aeroelastic deformation during flight. This study investigates the MBA configuration by employing the substructure method and modal reduction techniques to develop a reduced-order nonlinear structural model. Subsequently, the surface dipole lattice method is utilized to formulate the nonlinear aerodynamic model. By coupling the explicit nonlinear structural equations with the explicit aerodynamic equations via Lagrange equations, we derive an explicit dynamic representation of a high-dimensional aeroelastic system encompassing both geometric and concentrated nonlinear factors. Based on the established aeroelastic system equations, we perform a parametric analysis and mechanistic study of flutter characteristics. The results reveal that the flutter speed of the MBA configuration decreases as the number of modular aircraft increases.
Additionally, nonlinear factors significantly influence the flutter characteristics across various configurations and cannot be disregarded.

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In Categories: 1. IFASD 2024, 1.Events, Computational Aeroelasticity
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