Selected aspects of electronic hardware development and testing for the flight reconfiguration system in accordance with the RTCA DO-160G standard

Purpose The purpose of this paper is to discuss the importance of testing avionics systems during the development phase according to standard procedures outlined in documents such as RTCA DO-160G. Specifically, it focuses on the necessity of correctly designing electronic devices to successfully pass tests for environmental conditions. Design/methodology/approach During the development of the flight reconfiguration system (FRS) within the Clean Sky 2/Clean Aviation cost optimized avionics System (COAST) project, this paper applied solutions for input power protection in electronic design. The methods discussed are aimed at protecting circuits from input power disturbances following Sections 16 and 17 of DO-160G. The approach includes both computer simulations and laboratory testing to analyze the effectiveness of the applied methods. Findings The paper presents the findings of the applied methods for input power protection in the electronic design of the FRS. Through computer simulations and laboratory tests, it was observed that the developed electronic eqty -35uipment worked correctly after completing environmental and input power testing. The achieved results indicate that the applied methods of circuits’ protection ensured proper functionality. Practical implications The findings of this study have practical implications for the design and development of airborne electronic equipment. By adhering to standard procedures outlined in DO-160G and implementing appropriate input power protection methods, electronic devices can reliably operate in harsh environmental conditions encountered during aircraft operations. Originality/value This paper contributes to the field by presenting practical solutions for input power protection in electronic design, specifically within the context of the FRS by discussing methods of circuits’ protection in accordance with DO-160G and providing analysis of computer simulations and laboratory test results, this paper offers valuable insights into ensuring the proper functionality of avionic equipment in challenging environmental conditions.