Isogeometric analysis for simulation of progressive damage in composite laminates
Abstract
The increasing popularity of composite materials in aerospace applications is creating the need for a new class of predictive methods and tools for the simulation of progressive damage in laminated fiber-reinforced composite structures. The unique challenges associated with modeling damage in these structures may be addressed by means of thin-shell formulations which are naturally developed in the context of Isogeometric Analysis. In this paper, we further validate our recently developed Isogeometric Analysis-based multi-layer shell model for progressive damage simulations using experimental data for low-velocity impact on a 24-ply flat panel. The validation includes a careful comparison of delamination and matrix damage patterns predicted by the Isogeometric Analysis-based simulation and those obtained from post-impact non-destructive evaluation of the damaged coupon. The Isogeometric Analysis-based formulation is then deployed on two additional examples: a stiffened panel and a full-scale UAV wing, to demonstrate its suitability for, and ease of application to, typical aerospace composite structures.
Document Details
- Document Type
- Pub Defense Publication
- Publication Date
- Apr 22, 2018
- Source ID
- 10.1177/0021998318770723
Entities
People
- Andrew Ellison
- Hyonny Kim
- Marco S. Pigazzini
- Yuri Bazilevs
Organizations
- Air Force Office of Scientific Research
- Brown University
- Langley Research Center
- University of California