Nonlinear transient response analysis of rotating carbon nanotube reinforced composite cylindrical shells with initial geometrical imperfection

• Published in: Archives of Civil and Mechanical Engineering Vol. 24; no. 3; p. 161
• Main Authors: Li, Yin-Ping, She, Gui-Lin
• Format: Journal Article
• Language: English
• Published: London Springer London 27.05.2024; Springer Nature B.V
• Subjects: Aircraft; Behavior; Blast loads; Boundary conditions; Carbon; Carbon nanotubes; Civil Engineering; Cylindrical shells; Defects; Deformation; Dynamic models; Engineering; Equations of motion; Finite element analysis; Forced vibration; Hamilton's principle; Initial geometric imperfections; Literature reviews; Load; Material properties; Mechanical Engineering; Nonlinear equations; Nonlinear response; Numerical analysis; Original Article; Rotation; Runge-Kutta method; Shell theory; Structural design; Structural Materials; Thin walled shells; Transient response; Velocity; Vibration control; Transient response; Rotating cylindrical shells; Initial geometrical imperfections; Carbon nanotube reinforced
• ISSN: 2083-3318; 1644-9665; 2083-3318
• DOI: 10.1007/s43452-024-00973-y

At present, the dynamic studies of cylindrical shells are mostly limited to free- and forced vibration, the transient response of which is very limited. It is worth noting that no one has conducted research on the transient response of cylindrical shells with rotating speed and initial geometrical imperfection. Based on this fact, the present article is dedicated to discussing the transient response of rotating carbon nanotubes reinforced composite cylindrical shells with initial geometrical imperfection for the first time. Firstly, four distribution patterns of carbon nanotubes are taken into consideration, in which the material properties are calculated with the help of the mixing rule. Subsequently, considering the effect of initial geometric imperfection, the dynamic model is built according to Love's thin shell theory. Then, the motion equation of the shell is derived based on the Hamilton principle. Assuming three different boundary conditions, the Galerkin principle is applied to reduce the dimensionality of the motion equation, which leads to a nonlinear equation containing central radial displacement, pulse load, and time. Simultaneously, two comparative analyses are developed to confirm the validity of this article, and the results indicate that there is no significant difference between the current results and existing literature. By summarizing the characteristics of four pulse loads, the blast load is determined for numerical analysis. Finally, the Runge–Kutta method is employed to acquire the transient response with various influence factors. The current research provides theoretical guidance for structural design and vibration reduction of the spacecrafts subjected to pulse loads.