Aero electric propulsion system control and hardware-in-loop simulation

A loss minimization current control (LMC) and DC bus voltage feedforward control for a novel aero electric propulsion system with limited power supply were researched. The optimal magnetizing current expression was derived from a Γ equivalent circuit, with taking the iron losses of permanent magnet synchronous motor (PMSM) into account. Adapting rotor field oriented control, the d and q_axis decoupling current control was designed based on an approximate expression of d and q_axis current. As the output voltage sag of battery packs, the sampled value of DC bus voltage was used in the space vector modulation generation algorithm. Hardware-in-loop (HIL) simulation system for this electric propulsion system, based on dSPACE is constructed and the HIL system structure design and real time control module under MATLAB/Simulink were proposed. A variety of experiments was carried out. And experiments result shows that LMC can extend the PMSM operation area with high efficiency as well as restrain the influence caused by the DC bus voltage sags.