TY - GEN
T1 - Dynamic System Modeling and Stability Assessment of an Aircraft Distribution Power System using Modelica and FMI
AU - Konstantinopoulos, Stavros
AU - Nademi, Hamed
AU - Vanfretti, Luigi
N1 - KAUST Repository Item: Exported on 2022-06-30
Acknowledged KAUST grant number(s): OSR-2019-CoE-NEOM-4178.12
Acknowledgements: This work was supported in part by NASA under award number 80NSSC19M0125 as part of the Center for High-Efficiency Electrical Technologies for Aircraft (CHEETA), by the Engineering Research Center Program of the National Science Foundation and the Department of Energy under Award EEC-1041877, by the CURENT Industry Partnership Program, and by the Center of Excellence for NEOM Research at the King Abdullah University of Science and Technology under grant OSR-2019-CoE-NEOM-4178.12.
This publication acknowledges KAUST support, but has no KAUST affiliated authors.
PY - 2020/8/17
Y1 - 2020/8/17
N2 - In this work, the electrical distribution system of a Boeing 747 aircraft is implemented in Modelica. The electrical system is modeled in detail as far as generation and loads are concerned, aiming to capture any relevant dynamics and instabilities that can ensue during the aircraft's operation; while the power electronic interfaces of the loads are represented using averaged models. Small signal analysis is conducted at different operating points, aiming to capture relevant dynamics. Additionally, small signal analysis and time domain simulations are carried out to identify operational regions where low damping of unstable oscillations can occur, in order to characterize control loops interactions and system states. Finally, this paper proposes countermeasures for load startup and required controls that can alleviate any potential instabilities.
AB - In this work, the electrical distribution system of a Boeing 747 aircraft is implemented in Modelica. The electrical system is modeled in detail as far as generation and loads are concerned, aiming to capture any relevant dynamics and instabilities that can ensue during the aircraft's operation; while the power electronic interfaces of the loads are represented using averaged models. Small signal analysis is conducted at different operating points, aiming to capture relevant dynamics. Additionally, small signal analysis and time domain simulations are carried out to identify operational regions where low damping of unstable oscillations can occur, in order to characterize control loops interactions and system states. Finally, this paper proposes countermeasures for load startup and required controls that can alleviate any potential instabilities.
UR - http://hdl.handle.net/10754/679512
UR - https://arc.aiaa.org/doi/10.2514/6.2020-3544
UR - http://www.scopus.com/inward/record.url?scp=85096613550&partnerID=8YFLogxK
U2 - 10.2514/6.2020-3544
DO - 10.2514/6.2020-3544
M3 - Conference contribution
SN - 9781624106057
BT - AIAA Propulsion and Energy 2020 Forum
PB - American Institute of Aeronautics and Astronautics
ER -