TY - GEN
T1 - Dynamic performance of hygro-thermal-mechanically preloaded variable stiffness composite fairing structures
AU - Sciascia, Giuseppe
AU - Oliveri, Vincenzo
AU - Weaver, Paul M.
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023
Y1 - 2023
N2 - Since the introduction of variable stiffness composites, the design philosophy for highperformance lightweight composite structures has broadened greatly. Indeed, variable stiffness composites have been shown to increase buckling performance and dynamic stability, as well as to modify the dynamic response by tailoring stiffness distributions. Thus, efficient linear analysis tools play a significant role in the early design of variable stiffness structures, allowing designers to identify many viable solutions when considering preloaded dynamically excited aerospace components. To address this need, a Ritz-based method for eigenfrequency and dynamic instability analysis of hygro-thermal and mechanically prestressed variable stiffness laminated doubly-curved payload fairing structures is presented. Flexibility in modeling and design is achieved using Sanders-Koiter based shell kinematics that allow general orthogonal surfaces to be modelled without further assumptions on the shallowness or on the thinness of the structure. The efficiency of the proposed Ritz method is enabled by using Legendre orthogonal polynomials as displacement trial functions. By comparing the present approach with finite element solutions for variable-curvature, variable angle tow fairing shell geometries excellent accuracy is shown accompanied by an order of magnitude reduction in variables by the present method. Original solutions are presented comparing the dynamic behaviour of prestressed constant and variable stiffness composite shell structures, showcasing the viability of the variable stiffness concept to significantly increase the structural performance of critical doubly-curved variable-curvature components such as launch vehicle payload fairings.
AB - Since the introduction of variable stiffness composites, the design philosophy for highperformance lightweight composite structures has broadened greatly. Indeed, variable stiffness composites have been shown to increase buckling performance and dynamic stability, as well as to modify the dynamic response by tailoring stiffness distributions. Thus, efficient linear analysis tools play a significant role in the early design of variable stiffness structures, allowing designers to identify many viable solutions when considering preloaded dynamically excited aerospace components. To address this need, a Ritz-based method for eigenfrequency and dynamic instability analysis of hygro-thermal and mechanically prestressed variable stiffness laminated doubly-curved payload fairing structures is presented. Flexibility in modeling and design is achieved using Sanders-Koiter based shell kinematics that allow general orthogonal surfaces to be modelled without further assumptions on the shallowness or on the thinness of the structure. The efficiency of the proposed Ritz method is enabled by using Legendre orthogonal polynomials as displacement trial functions. By comparing the present approach with finite element solutions for variable-curvature, variable angle tow fairing shell geometries excellent accuracy is shown accompanied by an order of magnitude reduction in variables by the present method. Original solutions are presented comparing the dynamic behaviour of prestressed constant and variable stiffness composite shell structures, showcasing the viability of the variable stiffness concept to significantly increase the structural performance of critical doubly-curved variable-curvature components such as launch vehicle payload fairings.
UR - http://www.scopus.com/inward/record.url?scp=85199509304&partnerID=8YFLogxK
U2 - 10.2514/6.2023-1322
DO - 10.2514/6.2023-1322
M3 - Conference contribution
AN - SCOPUS:85199509304
SN - 9781624106996
T3 - AIAA SciTech Forum and Exposition, 2023
BT - AIAA SciTech Forum and Exposition, 2023
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA SciTech Forum and Exposition, 2023
Y2 - 23 January 2023 through 27 January 2023
ER -