Investigation of the feasibility of using aluminum honeycomb cores in the design of the fin of the aircraft

Abstract

The issues related to the use of a honeycomb cores in the design, the weight ratio of the empennage units are considered on the example of the fin of an aircraft. The article provides a comparative qualitative assessment of the weight efficiency, manufacturability of the design and design features of the fin with the use of honeycomb panels, compared with the classical frame construction of fin units. In addition, the article discusses the problems associated with the operation and repair of honeycomb core constructions. In the article the calculations of mass determination of honeycomb panel and transverse set for cases the thickness of the profile C=13%, C=8%, C=4% were carried out. Using he method of sequential calculations of each structural part of the honeycomb panel or the frame construction, the resulting masses of units were obtained. Based on the results, we can conclude that the use of three-layer panels in the construction of the fin with a given area and construction height is not justified, since the difference in weight is negligible, and honeycomb panels have several disadvantages.