Xiaomin An, Bin Deng

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-31

Nonlinear aeroelastic behaviours of three cylindrical composite panels of a rocket skin, which have two
different curvatures as R=2.5 and R=5, as well as two layer orientations, cross-ply and angle-ply are
studied in a low supersonic flow. The finite element co-rotational theory is applied to model
geometrically nonlinear shell panels, and an Euler solver, instead of piston theory or other simplified
aerodynamic theories, is utilized to solve unsteady aerodynamic. A fluid-structure staggered coupling
program is applied to simulate the nonlinear response. The results, static aeroelastic deformation, limit
cycle oscillations and non-periodic oscillations behaviours have been obtained. Flutter dynamic pressure,
amplitudes and spectra of limit cycle oscillations are analysed.

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In Categories: 1.Events, HiSST 2022, Materials and Structures
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