MIL-STD-704 compatible power topology design for avionics

The thesis focuses on the design, production, and testing processes of avionic units used in military aircraft in accordance with the power structure compliant with the MIL-STD-704 standard. During the thesis process, existing electrical systems used in aircraft were investigated. Requirements created within the scope of the standard for the aircraft, system architecture, power topology simulation, detailed design, and model validation studies were conducted. The studies within the scope of the thesis begin with research activities on electrical power system architecture. In this context, requirements and system architecture studies were carried out for the aircraft electrical power topology model. In the requirements study, the processes of defining, evaluating, and verifying the requirements were addressed. Additionally, the management of the requirements throughout the entire design process is detailed. A power system architecture that defines relationships for overvoltage and overcurrent protection structures and behaviors was created using the model-based LTSpice design tool. Thus, the preliminary design phase for the simulation model is completed. Following the preliminary design, the model infrastructure for detailed design was established using Altium Designer. This allowed for the project-specific design to be carried out and the protection structure to be ensured. In the power topology studies, the structures of the model elements, components, data, and configurations are described to effectively perform the simulation model and its verification. In detailed design studies, components suitable for military standards and series and parallel protection structures were selected. After this stage, schematic and PCB design work was carried out using the Altium Designer program. Necessary documents were transferred to the PCB manufacturing company, and production was carried out.Design verification studies are conducted experimentally with original design and production. Validation of power topology models was performed by establishing an experimental environment and defining and verifying the output obtained under the given input using a test device. Additionally, a climatic chamber test was conducted at the necessary temperatures to verify that the designed circuit meets the operational altitude values of the aircraft. During the test process, a power supply, oscilloscope, multimeter, climatic chamber, camera, and necessary ESD protection equipment were used. As a result, a verified power topology model-based design compliant with military standards for aircraft was obtained.