Avionics Design for a Subsonic Rocket Carrying a Scientific Experiment Unit

In this study, the avionics system of a solid propellant rocket flying at subsonic speed, which can carry, distribute and safely recover a payload carrying out a scientific experiment unit at an altitude of 10000 feet, is designed within the scope of the specified functionality and requirements of the system. The main avionics system is designed to contain components used to document flight data, transmit them instantaneously to the ground station, and perform recovery. In addition, a redundant avionics system has been designed to ensure safe operation and recovery in case of potential problems. Based on the analysis of the system requirements, an avionics system scheme has been proposed that offers efficient, low-cost, reliable flight and mission capability. Methods of minimizing the effects of in-flight vibrational effects on the payload and avionics system were also discussed. All analyzes and tests of the designed systems are provided to ensure that engineers extract as much information as possible to verify the design, ensure a safe flight and a successful payload mission.