Development of a modular FADEC for small scale turbojet engine

Gas turbines are widely spread in the aviation industry to propel both commercial and military aircraft. The stable and efficient operation of these units is an essential question of flight safety; therefore the high level control system is inevitable. Nowadays all newly designed aircraft engines incorporate Full Authority Digital Electronic Control (FADEC) for the fault tolerant behavior to reduce the workload of the pilots. The goal of the present article is to describe the development process of a modular FADEC system for a small scale experimental turbojet engine used for both university education and research purposes.