Modernization of the airframe design of an advanced aerial vehicle utilizing high-performance computing solutions

Аuthors

Samsonov K. S.^*, Medved V. S.^**, Kulik P. V.^***

Tactical Missile Corporation, 7, Lenin str., Korolev, Moscow region, 105005, Russia

*e-mail: sams1@bk.ru
**e-mail: vsmedved@list.ru
***e-mail: kulikpv@mail.ru

Abstract

Modern high-tech gliders place high demands on tactical, technical, weight, and operational characteristics, as well as on reliability, quality, and maintainability. Improvements in the weight-to-strength ratio of structures are achieved primarily through the use of new materials with high specific physical and mechanical properties. The use of polymer composite materials, primarily carbon fiber composites, allows for a reduction in the aircraft’s structural mass by up to 40–50%, as well as the fabrication of components with specified strength and stiffness characteristics.
One of the promising approaches to reducing the mass of large-span lifting surfaces is the creation of all-composite structures with a high reinforcement ratio. The objective of this work is to develop and conduct a computational and experimental study of the design of an all-composite wing cantilever for a promising aircraft, manufactured from domestic materials.
The study analyzes the aerodynamic loads acting on the airfoil and performs numerical simulation of the structure using the ANSYS software package. The developed finite element model allowed determining the stress-strain state of the structure under operational loads. The maximum calculated displacements amounted to 156.33 mm.

Keywords:

High-Performance Computing solutions; aircraft; composite materials, computational and experimental studies, HPC

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