Aeroelastic optimization of composite wings subjected to fatigue loads

Rajpal, D.; Kassapoglou, C.; De Breuker, R.

doi:10.2514/6.2018-0227

Aeroelastic optimization of composite wings subjected to fatigue loads

Title

Aeroelastic optimization of composite wings subjected to fatigue loads

Author

Rajpal, D. (TU Delft Aerospace Structures & Computational Mechanics)
Kassapoglou, C. (TU Delft Aerospace Structures & Computational Mechanics)
De Breuker, R. (TU Delft Aerospace Structures & Computational Mechanics)

Date

2018

Abstract

An analytical model to predict the fatigue life of a composite laminate is discussed. It is based on the method developed by Kassapoglou to predict fatigue failure. The analytical model calculates stresses in each ply using classical lamination theory, degrades the residual strength using the linear degradation law and predicts failure based on Tsai Wu failure theory. The cycles to failure are predicted using the updated cycle-by-cycle probability of failure. The predictions are validated for both a constant amplitude and a variable amplitude loading on a Glass/Epoxy laminate. Furthermore the analytical model is extended to work with laminates described using lamination parameters instead of ply angles and stacking sequence. The analytical fatigue model is then integrated in the TU Delft aeroelastic and structural optimization tool PROTEUS. A thickness and stiffness optimization of the NASA Common Research Model (CRM) wing has been carried out. Results show that fatigue may play an important role in the aeroelastic optimization of a composite wing.

To reference this document use:

http://resolver.tudelft.nl/uuid:e5c576ef-23f2-4000-b645-51351bb701b8

DOI

https://doi.org/10.2514/6.2018-0227

Publisher

American Institute of Aeronautics and Astronautics Inc. (AIAA)

Embargo date

2019-02-01

ISBN

9781624105326

Source

AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials (210049)