The Design Improvement of a Rotary-Wing Aircraft Frame Considering Fatigue Life and Fracture Characteristics

Author:

Kim Mantae,Ryu Hyunseung,Kim Taekyung,Kim Younggoo,Doh JaehyeokORCID,Kim Sanghoon

Funder

Chonnam National University (Smart Plant Reliability Center) grant

National Research Foundation of Korea

Publisher

Springer Science and Business Media LLC

Subject

Electrical and Electronic Engineering,Aerospace Engineering,General Materials Science,Control and Systems Engineering

Reference17 articles.

1. Hwang DY (1995) Damage tolerance design and prediction of fatigue life in aircraft structure. KSME Int J 35:468–480

2. Lazzeri RA (2002) Comparison between safe life damage tolerance and probabilistic approaches to aircraft structure fatigue design. Aerotecnica Missili e Sapazio 81

3. Wanhill RJH (2017) Fatigue requirements for aircraft structures. Aerospace materials and material technologies. Springer, Singapore, pp 331–352

4. Handbook ERD (2003) Military handbook. MIL-HDBK-5H: metallic materials and elements for aerospace vehicle structures (Knovel interactive edition). US Department of Defense, pp 6–55

5. Standard M 1530C (MIL-STD-1530C) Aircraft Structural Integrity Program (ASIP)

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