1. AHMAD SYUKRI MOHAMAD - Electrical Engineering Section, Universiti Kuala Lumpur, British-Malaysian Institute, Batu 8, Jalan
Sungai Pusu, Gombak, Selangor, Malayisa.
2. RUHAIDA ABDUL RASHID - Avionics Section, Universiti Kuala Lumpur, Malaysian Institute of Aviation Technology, Jenderam Hulu, Dengkil, Selangor, Malaysia.
The paper described the aircraft inverter in aircraft electrical systems, the various types of inverter designs and the simulation and experimental analysis of the proposed inverter. The aircraft inverter produces a rated 115V, 400Hz output that is only used in emergency situations primarily caused by loss of main electrical generation systems. But as the aviation world moving towards more electrical aircraft (MEA) and variable speed constant frequency (VSCF) electrical systems, the inverter role will not only limited to emergency power supply only but will be integrated in the main electrical generation system in the future aircraft. The cascaded multilevel inverter topology has the ability to increase the voltage output without the need of a transformer. Thus it offers the design with the space and weight reduction that are always desired in the aircraft systems design. Simulation results for the inverter circuits are given with the load set to up to 1kW, as the common rating for aircraft inverter. The inverter performance is analyzed based on the output waveforms and total harmonic distortions (THD) according to different number of cells and power switching devices used. To validate the simulation, an experimental hardware prototype is built and tested. The experimental results shown that the prototype inverter successfully produced the rated 115V, 400Hz inverter output with THD much less than the 5% limit set by IEEE and aircraft standards.
aircraft inverter, cascaded multilevel inverter, minimum conducting switches.