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.

The paper presents mathematical models of the key components onboard autonomous power supply system (ASE) plane "conventional" and more electric aircraft MEA "More Electric Aircraft". The subject, and also the aim of this work is the analysis and simulation of selected components of the power system of modern aircraft (synchronous generator, integrated starter/generator, voltage regulator, as device control and regulation of the generator and power electronic rectifiers multi-pulse). Simulation tests of key components confirmed the results obtained by the analytical and based on their mathematical models. The final part of the paper presents the main conclusions of the analysis and simulation based on the mathematical models of the selected components of the ASE system in accordance with the concept of a more electric aircraft.

This article focuses on power electronic multi-pulse 12-, 24- and 36-impulse rectifiers based on multi-winding rectifier transformers. The effectiveness of voltage processing with different variants of supply voltage sources is discussed and arguments are formulated for limiting oneself to 24-pulse processing, which is used in the latest technological solutions of modern aviation technology. The main purpose of this article is to conduct a study (analysis, mathematical models, simulations) of selected multi-pulse rectifiers in the context of testing their properties in relation to the impact on the electrified power supply network. The secondary objective of the article is to assess the possibility of using Matlab/Simulink to analyze the work of rectifier circuits implemented in aircraft networks compliant with the more/all electric aircraft (MEA/AEA) concept. The simulation tests included designing a typical auto-transformer rectifier unit (ATRU) system in the Simulink program and generating output voltage waveforms in this program in the absence of damage to the rectifier elements. In the final part of this work, based on a critical analysis of the literature on the subject of the study, simulations were made of exemplary rectifiers in the Matlab/Simulink programming environment along with their brief analysis. Practical conclusions resulting from the implementation of the MEA/AEA concept in modern aviation were formulated.

The subject of this paper is to make an analysis of advanced autonomous power systems (EPS, PES). This in particular includes to simulate the operation of a model of the Auxiliary Power Unit (APU) in the field of the power supply system EPS (Electric Power System). It ensures the proper operation of basic equipment and systems powered by electricity on board of a modern aircraft compatible with the More Electric Aircraft (MEA) concept. The modern onboard Autonomous Electric Power System (ASE) includes two systems: PES (Power Electronics System) and the Electric Power System (EPS). They are equipped with additional sources in the form of an emergency air turbine RAT (Ram Air Turbine) as well as an auxiliary source of APU, which will be subject to detailed analysis in the presented paper (model, simulation). The above systems are among the most modern systems in the field of onboard power supply of modern aircraft. It concerns both civil aviation companies Boeing and Airbus (A-380 and A-350XWB, B-787), as well as military Lockheed Martin (F-22 Raptor) and JSF (Joint Strike Fighter) F-35. Based on the above, on the basis of analysis and simulation made, the selected component (e.g. APU), will be presented justification for the implementation of the More Electric Aircraft concept for modern aviation. In the final part the practical conclusions will be drawn.

The subject of this paper is to present modern technological solutions in terms of architectural generation/processing, and transmission and distribution of electricity. It concerns both “classic” civil aircraft (Airbus, Boeing) and aircraft compatible with the trend of the aircraft fully/partially electric MEA/AEA (“More/All Electric Aircraft”), as well as military aircraft (Lockheed Martin) of “conventional” and “More Electric Aircraft”. The solutions will be presented based on the analysis, a mathematical model and simulation of the sample architecture for generation, transmission and distribution of electricity on-board modern aircraft. The final part of the paper presents the main conclusions arising from the analysis of simulation and imitation of selected components of the power supply system EPS (Electric Power System) for “conventional” and “more electric” aircrafts.

The key goal of this work was to develop a functional mathematical model of a 4-rotor UAV, including regulatory apparatus and identification of its parameters. The functionality of a quadrocopter traffic control has been reduced to solving differential equations that define the motion and dynamics of an unmanned aerial vehicle. It should be noted that the synthesis of the quadrocopter control system is not an easy task, due to the non-linear nature of the dynamics of this object and its structural instability. Therefore, in this article the tested object UAV was accepted as a physical model, which may cause potential material damage resulting from damage to the device as well as other elements that are located in its immediate surroundings. In addition, the article discusses the problem of improving the quality of the estimation rate of climb of unmanned aircraft of vertical takeoff and landing UAV, this problem was considered for the object in the low-ceiling range, i.e. in the range of 0-6 m, so the issue concerns autonomous take-off and landing. For the presentation of the results, the 4-rotor UAV was used, with the use of a proportional-integral-derivative PID controller in the context of the control system. The obtained results were supported by research and analysis of real results - the discussed algorithm was implemented in the 4-rotor UAV driver.