SPECIAL ISSUE ARTICLE
Foundation of damage tolerance principles in-service for the RRJ-95 aircraft structural components
Andrey A. Shanyavskiy,
Aleksey P. Soldatenkov,
Alexandr A. Toushentsov,
Corresponding Author
Andrey A. Shanyavskiy
Aviation Register for the Russian Federation, Moscow, Russia
Institute of Computer Aided Design, Moscow, Russia
Correspondence
Andrey A. Shanyavskiy, Aviation Register for the Russian Federation, Airport Sheremetievo-1, PO Box 54, Chimkinskiy State, Moscow 141426 Russia.
Email: [email protected]
Search for more papers by this authorAleksey P. Soldatenkov
Aviation Register for the Russian Federation, Moscow, Russia
Search for more papers by this authorAlexandr A. Toushentsov
Aviation Register for the Russian Federation, Moscow, Russia
Search for more papers by this authorAndrey A. Shanyavskiy,
Aleksey P. Soldatenkov,
Alexandr A. Toushentsov,
Corresponding Author
Andrey A. Shanyavskiy
Aviation Register for the Russian Federation, Moscow, Russia
Institute of Computer Aided Design, Moscow, Russia
Correspondence
Andrey A. Shanyavskiy, Aviation Register for the Russian Federation, Airport Sheremetievo-1, PO Box 54, Chimkinskiy State, Moscow 141426 Russia.
Email: [email protected]
Search for more papers by this authorAleksey P. Soldatenkov
Aviation Register for the Russian Federation, Moscow, Russia
Search for more papers by this authorAlexandr A. Toushentsov
Aviation Register for the Russian Federation, Moscow, Russia
Search for more papers by this authorFunding information: Russian Science Foundation, Grant/Award Number: N19-19-00705
Abstract
Fatigue cracks initiated from holes in several zones and structural components of the RRJ-95 aircraft frames were investigated. Using the method of quantitative fractography, the crack growth duration in the wing panels during full-scale bench tests and in the brackets of the in-service airframe was estimated by measuring the spacing of meso-beach-marks (MBM) and fatigue striations. The applied program of bench test consisted of blocks of variable loads that were equivalent to the wing loading in flight and reproducing schematized flight-cycle. It was shown that the duration of fatigue crack propagation in several structural components of the RRJ-95 aircraft frames was approximately the same as for the crack nucleation duration. The total lifetime is sufficiently long for cracks in the structural components to be detected and reliably monitored with a large operating time interval between adjacent inspections.
Open Research
DATA AVAILABILITY STATEMENT
The data that support the findings of this study are available from the corresponding author upon reasonable request.
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