Abstract
The growing interest into hybrid electric propulsion as a possible solution to reduce in-flight emissions has led to the investigations of many innovative propulsive system architectures that couple higher system efficiency with improved aerodynamic propulsion integration strategies. The paper presents amethodology to model and size generic hybrid electric propulsion system at the conceptual level allowing for a rapid exploration of the vast design space. The generalization of the propulsive system using a basic propulsive power unit object is discussed highlighting the control parameters needed to fully define the propulsive system architecture. Three case studies for a 2035 turbo-prop regional aircraft using parallel, series/parallel and distributed series configurations showthat improvements to the fuel and energy consumption are affected by the system morphology, its control strategy and the maturity level assumed for its components. Using conservative estimations for the battery and electric components performances indicate that the best configurations can only provide a fuel reduction of around 5% while weighting 25% more than the reference design. Using more optimistic assumptions leads to a larger feasible design space where the best performing configuration, the series/parallel one, realizes more substantial fuel and energy reductions of 28% and 14% with a 24% higher take-off mass.
| Original language | English |
|---|---|
| Title of host publication | AIAA Scitech 2019 Forum |
| Subtitle of host publication | 7-11 January 2019, San Diego, California, USA |
| Number of pages | 24 |
| ISBN (Electronic) | 978-1-62410-578-4 |
| DOIs | |
| Publication status | Published - 2019 |
| Event | AIAA Scitech Forum, 2019 - San Diego, United States Duration: 7 Jan 2019 → 11 Jan 2019 https://arc.aiaa.org/doi/book/10.2514/MSCITECH19 |
Conference
| Conference | AIAA Scitech Forum, 2019 |
|---|---|
| Country/Territory | United States |
| City | San Diego |
| Period | 7/01/19 → 11/01/19 |
| Internet address |
Bibliographical note
Accepted Author ManuscriptDOI: 10.2514/6.2019-1587.c1
Correction: A Method for the Conceptual Design of Hybrid Electric Aircraft
Author(s) Name: Jacopo Zamboni(1); Roelof Vos(1); Mathias Emeneth(2); Alexander Schneegans(2)
Author(s) Affiliations: 1. Delft University of Technology, Delft, Netherlands. 2. PACE America, Inc., Seattle, WA, United States.
Correction Notice 1:
In the first paragraph of section C.1 “Parallel Architecture” on page 13, the electric power ratio symbol should read φ, not ϕ.
In the first paragraph of section C.1 “Parallel Architecture” on page 13, the shaft power ratio symbol should read ϕ, not φ.
Correction Notice 2:
In the third paragraph of section C.2 “Parallel/Series Architecture” on page 13, the inboard PPU is characterized by a constant shaft power ratio of 0, not 1; the outboard PPU is characterized by a shaft power ratio of 1 (fully electric shaft), not 0.
Correction Notice 3:
In the fifth paragraph of section C.3 “Distributed Series Architecture” on page 14, the shaft power ratio is set permanently to 1, not 0.
Correction Notice 4:
In the caption of Figure 13 on page 19, the upper right sub-figure refers to the results of the series/parallel configuration, not of the parallel configuration. The upper left sub-figure refers to the results of the parallel configuration, not of the series/parallel configuration.
