Sizing, Integration and Performance Evaluation of Hybrid Electric Propulsion Subsystem Architectures

Abstract

This paper presents a methodology for the sizing and synthesis of power generation and distribution (PG&D) subsystems. The PG&D subsystem models developed in a previous work done by the authors were applied within a parallel hybrid electric propulsion architecture using the Dornier 328 as the baseline aircraft. The hybridization took place only during the cruise segment. Analyses were performed in Pacelab SysArc, a system architecture design tool, to assess the impact of different hybrid electric propulsion architectures and changing PG&D subsystem characteristics at aircraft and mission levels. To this end, sensitivity analysis was conducted to reveal the sensitivity to the subsystem level characteristics. Moreover, six different architectures were compared in terms of their mission level performance. These architectures included the PG&D subsystems with current state of the art technology, NASA 15-year technology goals and a more advanced battery technology. Although neither the current state of the art PG&D subsystems nor NASA 15-year technology goals were advanced enough to match the design range requirement of the baseline aircraft, some of the competing architectures met the practical range target while enjoying substantial amount of fuel reductions. Finally, it was observed that in order to reach a break-even point in terms of the design mission range, a battery specific energy of 5 kWh/kg was necessary for a 50% level of hybridization during cruise. In this work the Dornier 328 was used as a testbed, however the methodology can be generalized for all parallel hybrid electric propulsion applications.

Speed profile optimization of catenary-free electric trains with lithium-ion batteries

“…These models provide enough accuracy needed for the battery management application, while avoiding unnecessary complexities of the electrochemical models [34]. Due to their simplicity, electrical models are widely used for battery management applications, such as the application for electrical vehicles (e.g., [35,36]) and even hybrid propulsion systems for aviation purposes [37,38]. Electrical models have also been used for other applications such as the modeling of renewable energy systems [39].…”

Exploration and Sizing of a Large Passenger Aircraft with Distributed Ducted Electric Fans

“…Algorithm 1 details the different steps based on the input given by the work of Pornet et al 13 and Cinar et al, 14 which describe a sizing process for electric aircrafts. Respect to the original version, a new analysis is added at step 2; all the other blocks have been indirectly modified due to the presence of the new propulsive architecture.…”

“…3. In previous works on hybrid architectures 13,14 , an hybrid factor has been defined in order to control how much of the total power had to be supplied by each source. In this work, there is no factor splitting the power required from the two sources: with the law presented in Eq.…”

A Review of Concepts, Benefits, and Challenges for Future Electrical Propulsion-Based Aircraft

“…As an initial development, a sizing methodology for fully electric aircraft is proposed for general aviation applications [130][131][132][133][134], where the Breguet-range equation is modified for a battery sourced propulsion system. In further developments, Nam et al [135] and Cinar et al [136][137][138] proposed power-based sizing methods featuring multiple but generalized energy source paths. These are considered as very elementary design environments, with mere modifications in the existing propulsion system, and with added features of electrical energy source.…”