| Summary: | Composite plates in post-buckling regime can experience mode jumping in their buckling shape, suddenly increasing the number of half-waves. This phenomenon can be advantageous, because the shape change could be used for local morphing or structural adaptability in future aerospace structures. A study of this phenomenon under heating is here presented, combining numerical and experimental techniques. At first, a set of parametric analysis was conducted to identify composite panels that present a mode jump when heated. Three plates were selected, one in aluminum alloy <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mn>2024</mn><mi mathvariant="normal">T</mi><mn>3</mn></mrow></semantics></math></inline-formula>, and two in <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>AS</mi><mn>4</mn><mo>/</mo><mn>8552</mn></mrow></semantics></math></inline-formula> composite material, with layup <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mrow><mrow><mo>[</mo><mrow><mn>30</mn><mo>/</mo><mo>−</mo><mn>30</mn><mo>/</mo><mn>5</mn><mo>/</mo><mo>−</mo><mn>5</mn></mrow><mo>]</mo></mrow></mrow><mi>s</mi></msub></mrow></semantics></math></inline-formula> and <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mrow><mrow><mo>[</mo><mrow><mn>35</mn><mo>/</mo><mo>−</mo><mn>35</mn><mo>/</mo><mn>10</mn><mo>/</mo><mo>−</mo><mn>10</mn></mrow><mo>]</mo></mrow></mrow><mi>s</mi></msub></mrow></semantics></math></inline-formula>. The plates were tested in a new test setup for thermal buckling based on low thermal expansion fixtures. The mode jumping was successfully obtained experimentally for both composite plates. Numerical simulations predicted the general trends for all plates, and the mode jumps for the composite plates.
|
|---|
