Composites sandwich structures certification: A case study

Author:

Arakaki Francisco K1ORCID

Affiliation:

1. Mechanical Engineering Division, Instituto Tecnologico de Aeronautica, São José dos Campos, Brazil

Abstract

The motivation of this work is to show a case study represented by a test article in tapered sandwich structure with a mid-ramp region in order to reduce certification cost of the full-scale structure. Also, this work provides a compelling case for the standardization of Load Enhancement Factor for certification purposes. Therefore, the development of this work is based on the definition of the test article with a manufacturing defect and impact damage, for compliance static and damage tolerance requirements with damage no-growth approach. The results obtained showed a good strategy to reduce risk and cost of the certification development.

Publisher

SAGE Publications

Subject

Mechanical Engineering,Mechanics of Materials,Ceramics and Composites

Reference15 articles.

1. Federal Aviation Administration – FAA. Available at: https://www.faa.gov/

2. European Union Aviation Safety Agency – EASA. Available at: https://www.easa.europa.eu/

3. Wichita State University & SAE International, CMH-17 - Vol 3. Polymer matrix composites materials usage, design, and analysis - Rev G, 2012.

4. Federal Aviation Administration - FAA, Advisory Circular AC 20.107B-Composite Aircraft Structure, 2010.

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