Damage tolerance allowable calculation for the aircraft design with static ultimate load-Reference-Cited by-同舟云学术

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Damage tolerance allowable calculation for the aircraft design with static ultimate load

Published:2024-02 Issue: Volume:329 Page:117803
ISSN:0263-8223
Container-title:Composite Structures
language:en
Short-container-title:Composite Structures

Author:

Bogenfeld Raffael,Freund Sebastian,Dähne Sascha^ORCID,Wunderlich Tobias,Wille Tobias

Funder

Deutsches Zentrum für Luft- und Raumfahrt

Publisher

Elsevier BV

Subject

Civil and Structural Engineering,Ceramics and Composites

Reference64 articles.

1. AC 25.571-1D damage tolerance and fatigue evaluation of structure;Federal Aviation Administration,2011

2. A study of accidental impact scenarios for composite wing damage tolerance evaluation;Dubinskii;Aeronaut J,2019

3. Handbuch Struktur Berechnung, no. 2016;IASB,1976

4. Advisory circular AC20-107B: Composites aircraft structure;Federal Aviation Administration,2009

5. Goudou P. Decision No 2010/003/R of the executive director of the European Aviation Safety Agency. Tech. rep., Cologne; 2010, URL.

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