АВТОМАТИЗОВАНЕ ПРОЄКТУВАННЯ ЛОНЖЕРОНУ КРИЛА БЕЗПІЛОТНОГО ПОВІТРЯНОГО СУДНА

Abstract

One of the most crucial objective in designing aircraft structures is to ensure their strength while meeting the requirement for minimal weight. In operation, the structure must withstand loads without failure, as well as be designed with the lowest possible weight and, in most cases, volume.The determined geometric model of the structure based on the minimum weight criteria, reduces the overall weight of the aircraft which leads to: reducing the power requirements of the engine, and thus the cost of the aircraft; decreasing fuel consumption, making the aircraft cheaper in operation.The weight of the wing is equal 30-50% of the aircraft empty weight. Depending on the structural and load-carrying scheme of the wing, the weight of the spars can range 7-30% of the wing`s weight. Wing spar geometric model determination has a significant impact on the weight of the aircraft and thus on its cost and operational expenses.The problems of the wing spar automated design of an unmanned aerial vehicle are considered. The concept of creating a wing spar of an unmanned aerial vehicle according to the minimum mass criterion is presented.This study determines relation between the minimum required volume (weight) of the wing spar and the number of stiffeners as well as relations between the cross-section geometric properties of the spar (thicknesses of the flanges and web, flanges width) along its span.This study proposes approach for determining geometrical model of the wing spar based on the minimum weight criteria, which can serve as a valuable reference for the design process of spars or similar beam elements. The determined geometrical model of the wing spar for unmanned aerial vehicle, derived from analogous aircrafts data, is applicable for preliminary design purposes in this class of aircraft.