QUAD LAMINATES AEROELASTIC INSTABILITY'

Resumo

The flutter in panels of rockets, missiles, and vehicles was identified when technological advances al-
lowed these vehicles to reach supersonic and hypersonic speeds. The phenomenon was first noticed and recognized during World War II, when the German V2 rockets were being developed. The initial studies used the Ritz and Galerkin approach based on a linear aerodynamic and structural model intended to determine the critical dynamic pressure. Researchers started using nonlinear structural models with a nonlinear aerodynamic model and obtain-ing the limits cycle oscillation (LCO) due to computer advances and the growing use of matrix techniques, such as finite elements. In the last ten years of the previous century, structural components and aircraft wings began to utilize composite materials like carbon and glass fiber on a large scale. Thus, the researchers began to verify the impact of using these materials on structures subject to this instability. This paper investigates the aeroelastic stability of laminate panels in supersonic flow. It is optimized to obtain the best fiber direction and number of layers to increase the critical dynamic pressure. The researchers discovered that quadriaxial laminates with prede-termined directions have several advantages over others. In order to reduce flutter, the impact of employing quad laminate sets will be examined and contrasted with that of alternative configurations. The analysis is performed using a specially customized program. Finally, the results are compared with the literature, and the differences are
analyzed.