Ritz Solution for Transient Analysis of Variable-Stiffness Shell Structures

AIAA Journal ◽  
2020 ◽  
Vol 58 (4) ◽  
pp. 1796-1810
Author(s):  
Giuseppe Sciascia ◽  
Vincenzo Oliveri ◽  
Alberto Milazzo ◽  
Paul M. Weaver
Keyword(s):  
Transient Analysis ◽  
Variable Stiffness ◽  
Shell Structures

VIBRATIONS OF PRESTRESSED VARIABLE STIFFNESS COMPOSITE AEROSPACE STRUCTURES BY RITZ APPROACH

2021 ◽  
Author(s):  
GIUSEPPE SCIASCIA ◽  
VINCENZO OLIVERI ◽  
PAUL WEAVER
Keyword(s):  
Composite Structures ◽  
Transient Analysis ◽  
Design Space ◽  
Ritz Method ◽  
Shear Deformation Theory ◽  
Variable Stiffness ◽  
Shell Structures ◽  
Integration Scheme ◽  
Aerospace Structures ◽  
Rational Bézier Surface

With the introduction of the variable stiffness concept, the design space for highperformance lightweight composite structures has expanded significantly. A larger design space, in particular, allows designers to find more effective solutions with higher overall stiffness and fundamental frequency when considering prestressed dynamically excited aerospace components. In this context, an efficient and versatile Ritz method for the transient analysis of prestressed variable stiffness laminated doubly-curved shell structures is presented. The considered theoretical framework is the first-order shear deformation theory without further assumptions on the shallowness or on the thinness of the structure. A rational Bézier surface representation is adopted for the description of the shell allowing general orthogonal surfaces to be represented. General stacking sequences are considered and the unknown displacement field is approximated by Legendre orthogonal polynomials. Stiffened variable angle tow shell structures are modelled as an assembly of shell-like domains and penalty techniques are used to enforce the displacement continuity of the assembled multidomain structure and the kinematical boundary conditions. For the transient analysis of prestressed variable stiffness structures, classical Rayleigh damping is considered and solutions are obtained through the Newmark integration scheme. The proposed approach is validated by comparison with literature and finite elements results and original solutions are presented for prestressed free and forced vibrations of VS stiffened shell structure, proving the ability of the present method in dealing with the analysis of complex aerospace structures.

Design of Variable Stiffness Cylinder with Holes Under Bending for Maximum Buckling Load Using Lamination Parameters

2019 ◽  
Author(s):  
Mazen Albazzan ◽  
Brian Tatting ◽  
Ramy Harik ◽  
Zafer Gürdal ◽  
Adriana Blom-Schieber ◽  
...  
Keyword(s):  
Variable Stiffness ◽  
Buckling Load ◽  
Lamination Parameters
Sign in / Sign up

Export Citation Format

Share Document