Reengineering Technique with Transition to the Composite Material of the Outer Wing Monoblock–to–Aircraft Centre-Section Connection Assemblage

Design of the Flying Vehicles Elements from Polymer Composite Materials


Аuthors

Kostin V. A.1*, Lukankin A. S.1**, Odinokov S. A.1***, Lukankin S. A.1***, Sultanov L. U.2****, Fedorenko, O. G.3

1. Kazan National Research Technical University named after A.N. Tupolev, Kazan, Russia
2. Kazan Federal University, 35, Kremlevskaya str., Kazan, 420008, Russia
3. JSC “Specdetal”, Ufa, Russia

*e-mail: VAKostin@kai.ru
**e-mail: lukankin_a@inbox.ru
***e-mail: lukankin.sergej@yandex.ru
****e-mail: lenar.sultanov@kpfu.ru

Abstract

As is known, aircraft engineering development is a costly, labor-intensive, and time-consuming process. At the same time, the existing aircraft engineering samples typically possess a significant modernization potential, which is being currently exploited by design bureaus to obtain the upgraded models with a new set of performance and operational characteristics. Retrofitting of the secondary airframe structures (typically fuselage components) by replacing them with composite materials without altering the structural-power scheme is straightforward and relatively simple to execute. Transition within the framework of modernization activities of the load bearing aviation structures, such as of wing or fuselage load bearing sets, to composite materials compared to the above said is non-trivial and labor intensive task associated among all in principle with assessment of the carrying capacity with the new structure as a whole. The adduced reasons substantiate the absence of analytical information on the results of works on the load bearing elements of the aircraft structures transition to composite materials. 
The presented article levels the lack of the said data and allows determining in general the totality of tasks arising whilel solving the problem of the load bearing structural elements modernization. The authors consider the issues arising with the complete transition of the bolted flange joint, connecting components of a monolithic wing, to composite materials for an aircraft with a maximum takeoff weight exceeding five tons. Structural solutions, evaluation of their load bearing capacity and experimental substantiation of their resource potential are considered. Inferences by the results of the conducted research are adduced as well.

Keywords:

carbon fiber composite “black” wing, load-bearing structural configuration, composite aircraft, monoblock model, all-composite fitting assemblage, structural weight efficiency

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