Low Velocity Impact of Composite Aerostructures.
Abstract
While considerable effort has been put into understanding the low velocity impact of composite laminates, there is still considerable uncertainty concerning the analysis tools required to give accurate predictions of stresses and strains for design purposes. It has been determined that elastic bending solutions are inaccurate, and that several phenomena may explain the differences observed between elastic theory and experiment. These are: 1. Contact deformations, 2. Transverse shear deformations, 3. Viscoelasticity, 4. Large deflections and membrane effects. The objective of this project is to determine if and under what conditions each of the four phenomena must be modeled in analyses of low velocity impact of fiber composite laminated structures. The program has shown that the flexural viscoelasticity is negligible, but that viscoelastic transverse shear and contact deformations are important for short composite plates. It appears that membrane effects may be important for longer plates where strains are significantly underpredicted by elastic small deflection analysis. These results will give guidance to analysts who must predict strains and stresses in order to achieve safe, efficient,impact resistant composite structures. Keywords: Military aircraft, Penetrator, Delamination, Laminates, Arsenic, Airfoils.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1986
- Accession Number
- ADA188513
Entities
People
- Philip V. Mclauglin Jr
Organizations
- Villanova University