The evolution of aircraft power systems has been driven by increasing electrical demands and advancements in aviation technology. Background: This study provides a comprehensive review and experimental validation of on-board electrical network development, analyzing power management strategies in both conventional and modern aircraft, including the Mi-24 helicopter, F-22 multirole aircraft, and Boeing 787 passenger airplane. Methods: The research categorizes aircraft electrical systems into three historical phases: pre-1960s with 28.5 V DC networks, up to 2000 with three-phase AC networks (3 × 115 V/200 V, 400 Hz), and post-2000 with 270 V DC networks derived from AC generators via transformer–rectifier units. Beyond theoretical analysis, this work introduces experimental findings on hybrid-electric aircraft power solutions, particularly evaluating the performance of the Modular Power System for Aircraft (MPSZE). The More Electric Aircraft (MEA) concept is analyzed as a key innovation, with a focus on energy efficiency, frequency stability, and ground power applications. The study investigates the integration of alternative energy sources, including photovoltaic-assisted power supplies and fuel-cell-based auxiliary systems, assessing their feasibility for aircraft system checks, engine startups, field navigation, communications, and radar operations. Results: Experimental results demonstrate that hybrid energy storage systems, incorporating lithium-ion batteries, fuel cells, and photovoltaic modules, can enhance MEA efficiency and operational resilience under real-world conditions. Conclusions: The findings underscore the importance of MEA technology in the future of sustainable aviation power solutions, highlighting both global and Polish research contributions, particularly from the Air Force Institute of Technology (ITWL).

The article presents selected results of analytical and design works undertaken at the Air Force Institute of Technology (AFIT) in the field of building a computer support and software lifecycle management system that is critical for flight safety. The aim of the work undertaken is to develop methods and carry out verification and testing in order to detect errors in the developed avionics software for compliance with the requirements of the DO-178C standard and its production, certification, and implementation on board aircraft. The authors developed an original computer system within the implemented requirements used in the construction and certification of avionic onboard devices and their software (among others, DO-254, DO-178C, AQAP 2210, ARP 4761, ARP 4754A). The conducted analysis involved three basic groups of avionics software development processes, i.e., software planning, creation, and integration. Examples of solutions implemented in the constructed computer system were presented for each of these process groups. The theoretical basis of the new method for predicting vulnerabilities in the software implemented within integrated avionic systems using branching processes is discussed. It was demonstrated that the possibility of predicting vulnerabilities in future software versions could have a significant impact on assessing the risk associated with software safety in the course of its lifecycle. It was indicated that some of the existing quantitative models for analyzing software vulnerabilities were developed based on dedicated software data, which is why actual scenario implementation may be limited. DO-178C standard requirements for the process of developing avionics software were implemented in the helmet-mounted flight parameter display system constructed at AFIT. The requirements of the DO-178C and AQAP 2210 standards were shown to be met in the example of the software developed for a graphics computer, managing the operating modes of this system.

Experimental results of the usefulness of the fiber-optic Sagnac interferometer for a measurement of angular position as motion uniformity of slow-speed rotating objects are presented. The system contains GS-13P/SR device with modified signal processing unit. The results of an investigation of this system, and their application for rotation angle and uniformity motion of object in inertial space are shown. A new slow-speed platforms generate constant angular motion (M19-03 stand made by COBRABiD Optica) and harmonic variable motion (STW-1 stand made by AFIT) have been used as forces source. The Fourier and wavelets analyses have been used as mathematical description of GS-13P/SR application for technical diagnostic of slow- speed platforms.

The paper presents an analysis of false triggers of fire protection systems installed on aircraft. They not only cause task interruption but also have a direct impact on flight safety, forcing the crew to land in a risky area. Simulation models of electronic actuators were developed to determine the conditions under which false alarms occur. Testing of the simulation models was carried out in the computational package Matlab-Simulink and Circum-Maker for different electrical disturbance generation conditions. The simulation of overvoltage, voltage drops and voltage decays in the on-board electrical network supplying the fire protection system, occurring during the start-up of aircraft engines and during the switching on and off of on-board high-power devices, was studied. The conducted studies have practical applications since the simulation results are an important element for planning experimental tests of the SSP-FK-BI executive blocks under electrical disturbance conditions. Based on the simulation and experimental studies, the conditions causing false tripping of the fire protection system and the parameters for selected disturbance factors have been determined.

The paper has been intended to present a research/testing tool used in the Air Force Institute of Technology (AFIT) to build, actuate, test, and optimise integrated communication systems as far as both a set of devices the system is composed of and the applied software are concerned. Particular attention has been paid to the so-called integration station (built under the Mi-8, Mi-17, Mi-24 upgrade project), i.e. the laboratory equipment to optimise and unify communication systems integrated on the basis of digital data buses (following the MIL-1553B standard, among other ones). Such equipment has allowed AFIT to integrate new communication devices/systems while upgrading the W-3PL helicopter. Some selected tasks performed with this equipment engaged have been discussed. Also, problems arising while actuating and testing the developed software to integrate communication devices/systems (including digitally controlled radio stations of the RRC, HARRIS, and MR6000 types, communication control panels of the PSŁ-1 type and multifunction displays of the MW-1 type) have been given consideration in the scope of the software functionality and reliability. Presented are also additional monitoring and measuring systems used to test this software, just to mention the M230 rugged laptop computer used to diagnose the system and prepare plans of the radio communication.

The paper has been intended to present research tools used at the Air Force Institute of Technology (AFIT) to activate and test hardware and software implemented in the integrated avionics systems. Particular attention has been paid to the research stand (built under the R&D project of the Ministry of Science and Higher Education) intended to optimize avionics systems integrated with digital data buses employed (according to, among other things, MIL-1553B and ARINC-429 standards). Specialized research equipment/test devices used to test software, including - apart from other things - test-patterns generators (within the range of display capability of the secondary head-up display (SHUD)) and information efficiency testers (for the SHUD and up-front control panel (UFCP) thereof) have also been presented.