Treatment of High-Cycle Vibratory Stress in Rotorcraft Damage Tolerance Design
Abstract
Fixed wing aircraft manufacturers have adopted the damage tolerance design philosophy with great success for both military and commercial aircraft. However, rotorcraft manufacturers currently still primarily use the classical safe life approach or a modification thereof. One reason for this is that, at this time, no clearly defined damage tolerance design criteria exist for rotorcraft structures because of the analysis and test problems associated with the high cycle loading environment. This paper describes a study performed by the United States Air Force (USAF) to assess the impact of the damage tolerance approach on the design of a rotorcraft component affected by high-cycle vibratory stresses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 2000
- Accession Number
- ADP010648
Entities
People
- Hsing C. Yeh
- John W. Lincoln
Organizations
- Aeronautical Systems Center