Sikorsky Aircraft has been under contract since late 1982 to investigate the application of damage tolerance to the H-53 helicopter. This program has involved identification of critical structure, usage spectrum evaluation, loads evaluation, detail stress analyses, material and verification testing, and development of stress intensity solutions. The primary objectives of the program were to develop a computer program for use by Sikorsky and Warner Robins-ALC to perform crack growth analysis of helicopter structure, to evaluate crack growth in a select group of rotor and airframe structure, and to access the feasibility of damage tolerance force management for the H-53 Air Force fleet. A presentation was made at the 1984 Aircraft Subsystems Integrity Program (ASIP) conference to provide an introduction to this program. Since then Sikorsky has completed an initial crack propagation analysis of a select group of rotor and airframe structure. The purpose of this presentation is to review some of the technical issues involved in the crack growth analysis, to present some of the analysis results, and to review conclusions and lessons learned.
Application of Damage Tolerance
1988
22 pages
Report
No indication
English
Aircraft , Logistics Military Facilities & Supplies , Structural Mechanics , Aircraft structures , Crack propagation , Damage , H-53 helicopter , Loads (Forces) , Stress analysis , Tolerances (Mechanics) , Computer programs , Conferences , Aircraft equipment , Airframes , Rotors , Stress intensity factors
Tema Archive | 1994
|British Library Conference Proceedings | 2005
|Application of Damage Tolerance Technology to Type Certification
SAE Technical Papers | 1981
|Application of Damage Tolerance to the EH101 Airframe
British Library Conference Proceedings | 2000
|AIAA | 1970
|