The article presents a comparative characterization of the structural materials (composites and metals) used in modern aviation structures, focusing on the airframe structure of the most modern aircraft (Airbus A-380, Boeing B-787, and JSF F-35). Selected design and operational problems were analysed, with particular emphasis on composites and light metals (aluminium). For this purpose, the Shore’s method was used for the analysis of the obtained strength results and the programming environment (ANSYS, SolidWorks) required to simulate the GLARE 3 2/1-04 composite. The focus was on highlighting the differences in the construction and modelling of these materials resulting from their various structures (isotropy and anisotropy), e.g., by analyzing the mechanics of metal destruction and comparing it with the composite material. In terms of solving the problems of finite element analysis FEM, tests have been carried out on two samples made of an aluminium alloy and a fiberglass composite. The focus was on highlighting the differences in the construction and modelling of these materials resulting from their various structures (isotropy and anisotropy), e.g., by analyzing the mechanics of metal destruction and comparing it with the composite material. On the basis of the obtained results, the preferred variant was selected, in terms of displacements, stresses, and deformations. In the final part of the work, based on the conducted literature analysis and the conducted research (analysis, simulations, and tests), significant observations and final conclusions, reflected in practical applications, were formulated.

Experimental tests regarding the M-346 aircraft model made via 3D printing were carried out in order to obtain numerical data and characteristics in the form of graphs of basic aerodynamic forces and coefficients. The tests were carried out for the left side of the airframe model in a clean configuration, without additional suspension equipment; the flight control surfaces and the aerodynamic brake were in neutral positions. Based on the scan of the base model in 1:48 scale using a Nikon Model Maker MMDx laser scanning head, followed by the generation and optimization of some of the airframe elements in SolidWorks software, a test model ready for printing was prepared. Using the MakerBot Print program, the printing parameters were set, and the process itself was completed using a MakerBot Replicator Z18 3D printer. The next step was manual treatment in order to remove the material excess from the melted thermoplastic material, join the elements and appropriately polish the surface of the tested model in order to obtain the desired quality. The test was carried out using a Gunt HM 170 wind tunnel for fixed airflow velocities at variable angles of attack. On this basis, the numerical values of lift force, Pz, and drag force, Px, were obtained; then, the lift force indices, Cz, and drag force indices, Cx, were computed for the steady states, which were for angle α from −12 to 16°. The use of 3D printing contributed to the generation of geometry, which, for research purposes, was scaled down in order to fully use the available measurement space of the wind tunnel. The final stage of the work was to compare the obtained curves of particular characteristics with the literature data.

Stability is a key aspect for aircraft as it directly affects its flight balance and manoeuvre capabilities. This numerical research with Ansys Fluent investigates an airflow around a model of the designed gyrocopter – Aduster to examine its static longitudinal stability for the given ranges of horizontal stabilizer angles and angles of attack. Our calculations give certain aerodynamic forces and moments. The paper investigates drag, lift, a pitching moment at the given angles as well as gives the calculated coefficients of those forces and the pitching moment. The research results and the stability criterion enable us to analyse our gyrocopter's static longitudinal stability.

This paper describes the research gyrocopter and presents the methodology of numerical calculations for this type of research objects. There are also the results of an ANSYS Fluent three-dimensional simulation of an airflow around a gyrocopter, excluding an airflow around its main rotor and propeller blades. The calculations enabled basic aerodynamic characteristics. The analysis of the numerical calculations focuses on the impact of gyrocopter individual sections like a fuselage, tail, tail boom, etc., on aerodynamic forces and moments, as well as coefficients of aerodynamic forces and moments. The research scope covers an angle of attack α ranging between -20° and 25° at a sideslip angle equal to 0.

All aircraft structures are exposed to both fatigue and static loads. Damage caused by fatigue loads is much more dangerous because it can cause damage at a level lower than the ad hoc strength. Fatigue testing requires both a large number of samples and machine time, which generates considerable costs. In the case of tests performed on prototypes, it is sometimes impossible to make a large number of samples. In such a situation, as well as in a situation when results are sufficient, the accelerated methods described by the co-author in [3] may be used to study with some approximation. In the standard tests, only the number of cycles measured under a predetermined regime is used. Many signals can be used in accelerated studies: e.g. piston displacement, force, strain gauge, thermographic measurement [4].

This paper deals with the flight testing and measuring of the GNSS (RNAV) with flying laboratory – AeroLab 1 at the University of Žilina. The paper focusses on the comparative aerial measurements of the GNSS RNP APCH which is approved and published at the Žilina airport. The GNSS procedure was put into operation in May 2017 and is subjected to regular checks. Results of flight checking must be within the limits of the prescribed tolerances defined in the ICAO Annex 10. Our practical measurements were divided into two flights. The displayed outputs on the console were compared with the reference values and subsequently evaluated in the conclusion in this paper. Our practical comparative measurements show results that comply with ICAO standards and thus the tested RNP APCH is functional and can be used in mountains and river areas.