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- Article name
- Optimization of attachment point lug of helicopter blade from composite materials considering durability conditions
- Authors
- DUDCHENKO A. A., , a_dudchenko@mail.ru, Moscow Aviation Institute (National Research University), Moscow, Russia
LARIONOVA A. A., , a.larionova@inbox.ru, Moscow Aviation Institute (National Research University), Moscow, Russia
- Keywords
- bearing blade of helicopter / attachment point of blade / polymeric composite materials / metal part of transition device / fatigue life / fatigue strength / resource
- Year
- 2019 Issue 4 Pages 8 - 16
- Code EDN
- Code DOI
- Abstract
- The solution of the optimization problem for determining the rational zone of fastening of the butt of the composite blade to the metal node of the transition device using the method of calculating the static strength and fatigue life of the rotor from the loads arising in a typical flight is presented. Formulas that allow one to optimize the distribution of power load in the attachment point of the blade and thereby increase the life of the structure are obtained. The blade attachment node is modeled and a static calculation of the structural strength by the finite element analysis method is performed. The fatigue life of the helicopter blade and bolt fasteners was calculated. It was found that the use of bolts of smaller diameter can significantly reduce the size of the cut fibers of the material, which increases the strength of the material of structures and reduces the stress concentration in the region of the holes. The calculation of the blade attachment site showed that structures with bolts with a diameter of 8 and 30 mm have the fatigue strength necessary to fulfill the design life of 60.000 flights.
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