Calculation and Application of an Integrated Wing Structure Made of Polymer Composite Materials in Aerospace Vehicles
Published: 02.06.2026
Authors: Basharov E.A.
Published in issue: #6(174)/2026
Category: Aviation and Rocket-Space Engineering | Chapter: Design, Construction, Production, Testing, and Operation of Aircraft
The development and testing of a simplified calculation method with optimization using the criterion of equal strength in layers, as well as an analysis of the prospects for the use of integrated wing structures made of polymer composite materials (PCM) in aerospace vehicles are presented. The main computational cases of loading of the wing caisson of an integral structure at the initial design stage are considered, as well as the calculated expressions used in the constraints of the projected structures are given. The result approbation of the technique is shown using the example of calculating the wing caisson of an integral carbon fiber structure of the KMU-7L-300 type. It is noted that the results obtained showed good accuracy in determining the stiffness and strength of the composite wing box, taking into account the binder, sufficient for engineering calculations.
EDN MRCOTJ
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