Abstract
DC-DC isolated converters allowing a bidirectional flow of energy between High-Voltage DC and Low-Voltage DC networks have been proposed to be integrated in future on board power distribution systems. These converters must meet the specially stringent efficiency and power density requirements that are typical of the aeronautic industry. This makes it specially challenging to determine which converter topology is best suited for each particular application. This work presents a thorough review of several topologies of bidirectional DC-DC power converters that are considered good candidates to meet certain important aeronautic requirements, as those related with high efficiency and high power density. We perform simulations on virtual prototypes, constructed by using detailed component models, and optimized following design criteria that are in accordance with those typically imposed by aeronautic requirements. This comparative analysis is aimed to clearly identify the advantages and drawbacks of each topology, and to relate them with the required voltage and power levels. As an outcome, we point out the topologies that, for the required power level at the chosen switching frequencies, yield higher efficiency in the whole range of required operation points and that are expected to allow more important weight reductions.
Highlights
In order to respond to the growing needs of energy distribution on board and, at the same time, safeguard the ambitious objectives proposed in the aeronautical sector in terms of cost reduction and reliability of future aircrafts [1], new electric power systems have been proposed
It is interesting to note that in such modular solution, the performance of the modular connection is very close to the performance of the single modules that we have considered in this study, at least in terms of efficiency and power density
We can observe that Si MOSFET models with fast intrinsic diodes can lead to much lower switching losses than their low R DS,on counterparts
Summary
In order to respond to the growing needs of energy distribution on board and, at the same time, safeguard the ambitious objectives proposed in the aeronautical sector in terms of cost reduction and reliability of future aircrafts [1], new electric power systems have been proposed. As a consequence of the increase in electric power, the trends in modern power distribution systems are toward an increase in voltage, with the aim to increase efficiency and decrease the weight of the electric distribution system. One of the preferred proposed solutions consists on replacing the current electric power system, based on a three-phase 115 VAC or 230 VAC at 400 Hz (or variable frequency on more modern aircrafts such as the Boeing 787 or Airbus 380), for a high-voltage DC distribution system (HVDC)
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