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<p>Aeroelastic effects arise from coupling aerodynamic, elastic, and inertial forces in structures, critically influencing the design and performance of small unmanned aerial vehicles (sUAVs). This study investigates the dynamic aeroelastic behavior of a 1.3 m-span flying wing sUAV constructed from lightweight, unconventional materials—Styrofoam and aluminum tubing—to assess structural integrity under aerodynamic loads. A two-way fluid-structure interaction (FSI) methodology was employed under inviscid flow conditions to analyze the wing’s response at angles of attack ( 5°, 7°, 10°) and cruise velocities (20 m/s, 80 m/s). A 3-DOF computational model focused on lift-oriented dynamics, revealing increased wingtip displacement with rising angle of attack and velocity due to amplified aerodynamic lift. Oscillation frequencies approached the wing’s natural frequency of 150 Hz, with only the first vibrational mode observed. Damping ratios exhibited an incremental trend with higher angles and speeds, suggesting enhanced energy dissipation under elevated loads. A phase difference nearing 90° between lift and displacement confirmed expected fluid-solid interaction behavior. The results demonstrate that integrating aluminum tubing with Styrofoam effectively augments stiffness, mitigating excessive deformation while maintaining low weight. This material combination proves viable for small fixed-wing UAVs, balancing aeroelastic stability with structural efficiency. The study underscores the behavior of aeroelastic effect in sUAV design, particularly when employing non-traditional materials and provides a validated framework for optimizing lightweight airframe performance under operational loads.</p>

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Aeroelastic Analysis of a sUAV Half Span Wing within Pre-Stall Region using a Two-Way Closely Coupled FSI Model

  • 期刊论文

  • 发表日期：

    2026年2月11日

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  • Bibek Dhungana,
  • Sudip Bhattrai,
  • Siddhartha Paudel

摘要

Aeroelastic effects arise from coupling aerodynamic, elastic, and inertial forces in structures, critically influencing the design and performance of small unmanned aerial vehicles (sUAVs). This study investigates the dynamic aeroelastic behavior of a 1.3 m-span flying wing sUAV constructed from lightweight, unconventional materials—Styrofoam and aluminum tubing—to assess structural integrity under aerodynamic loads. A two-way fluid-structure interaction (FSI) methodology was employed under inviscid flow conditions to analyze the wing’s response at angles of attack ( 5°, 7°, 10°) and cruise velocities (20 m/s, 80 m/s). A 3-DOF computational model focused on lift-oriented dynamics, revealing increased wingtip displacement with rising angle of attack and velocity due to amplified aerodynamic lift. Oscillation frequencies approached the wing’s natural frequency of 150 Hz, with only the first vibrational mode observed. Damping ratios exhibited an incremental trend with higher angles and speeds, suggesting enhanced energy dissipation under elevated loads. A phase difference nearing 90° between lift and displacement confirmed expected fluid-solid interaction behavior. The results demonstrate that integrating aluminum tubing with Styrofoam effectively augments stiffness, mitigating excessive deformation while maintaining low weight. This material combination proves viable for small fixed-wing UAVs, balancing aeroelastic stability with structural efficiency. The study underscores the behavior of aeroelastic effect in sUAV design, particularly when employing non-traditional materials and provides a validated framework for optimizing lightweight airframe performance under operational loads.