Improved Turboelectric System Modeling for Conceptual Design of HEPS Aircraft

This study presents an improved turboelectric system modeling approach, which incorporates generator and rectifier analysis modules to enable sizing for various power outputs, while considering the electrical characteristics and control strategies of the systems. The developed modules were applied to the vertical take-off and landing (VTOL) conceptual design tool, RISPECT+, to perform sizing for the turboelectric propulsion system aircraft. Through perform the sizing, it was confirmed that modules effectively reflect variations in the efficiency of the generator and rectifier based on mission segments and flight environments. Furthermore, by optimizing the DC-Link voltage between the generating system and propulsion system, the DC-Link voltage that minimizes overall electrical losses and electrical components weight, while maximizing payload was determined. Finally, a comparison of the rotational speeds of the generator and the turboshaft engine was conducted to propose an optimal gear ratio between the two components. This research is expected to contribute to enhancing the reliability of the conceptual design and performance analysis of hybrid electric propulsion system aircraft, including the turboelectric propulsion system.