The design and control of aviation starter/generator

In recent years More Electric Aircraft (MEA) attracts attention in order to reduce greenhouse gas emission and fuel consumption, defines as common usage of electrical systems instead of pneumatic, hydraulic and mechanical systems. To meet with increased demand for electrical power in MEAs and cranking gas turbine engine fault tolerant, highly efficient, light weighted starter/generators (SG) that requires low maintenance are needed. Interior permanent magnet synchronous motor (IPMSM) comes forward for SG designs due to its advantages such as high power and torque density, flux weaking ability, low inertia and high efficiency in wide operating speed. The IPMSM has a hybrid structure that benefits from magnet and reluctance torque. The machine performance varies with flux bridges, flux bariers, magnet arrangements and sizes used in rotor and requires an multiobjective optimization. For high speed IPMSM, the temperature sustained by the magnets placed in rotor, mechanical limitations and fault tolerance are the constraints of optimization and require multiobjective approach. The proper materials such as high thermal tolerant SmCo magnets, amorphous metals that have high magnetic permeability and low iron losses should be used in aviation due to harsh environment conditions. In this thesis, the multiobjective Pareto optimization of efficient IPMSM with high power density and 5 phases is realized for prototype and driver manufacturing. The dimensions of SG are optimized with differantial evolution algorithm which uses analytical models created for starter and generator operation separately. The prototype of SG is tested with self-designed driver circuit and test bed.