No Crack Growth Approach for Analyzing a Helicopter Main Rotor Blade
Publish place: 27th Annual Conference of Mechanical Engineering
Publish Year: 1398
نوع سند: مقاله کنفرانسی
زبان: English
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شناسه ملی سند علمی:
ISME27_617
تاریخ نمایه سازی: 8 مرداد 1398
Abstract:
In this article, no crack growth approach is used for analyzing the main rotor blade of a helicopter. The blade is comprised of many different parts such as spar, skin, abrasive strip, doublers, box beam doublers, etc. and it supports complex random load spectra. At first,threshold stress intensity range of the spar is obtained based on ASTM E647 test method. Then, a finite element analysis is carried out to extract the stress distribution in the blade parts. Afterwards, crack growth analysis is done for the main parts of the blade using Zencrack software. In order to calculate the length of the smallest growing cracks, no crack growth approach were used. A comprehensive investigation was carried out on the effect of initial crack length and aspect ratio on growth or no growth of cracks in the blade. Safety factor against the crack growth diagrams were obtained for different initial crack lengths and aspect ratios considering the critical maneuvers
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Authors
S Mohammadi
Assistant professor, Faculty of Engineering, University of Kurdistan
A.R Shahani
Professor, Faculty of Mechanical Engineering, K. N. Toosi University of Technology