Tail Sizing Considerations for Wingtip Propulsor Driven Aircraft Applied to the Parallel Electric-Gas Architecture with Synergistic Utilization Scheme (PEGASUS) Concept

Blaesser, Nathaniel J.; Frederick, Zachary J.

doi:10.2514/6.2020-2633

Cited by 8 publications

(2 citation statements)

References 17 publications

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“…The combined parallel and series hybrid propulsion system for the concept aircraft includes wingtip propellers. Similar results have been found by Antcliff and Capristan (2017) and Blaesser and Frederick (2020) from NASA, who have investigated a regional aircraft with a parallel hybrid propulsion system including wingtip propellers. Both studies of German Aerospace Center and NASA assume that the battery has an energy density of 500 Wh/kg.…”

Section: Aircraft and Propulsion System Conceptsupporting

confidence: 84%

Preliminary Design of Integrated Partial Turboelectric Aircraft Propulsion Systems

Pohl

Kohler

Kellermann

et al. 2022

J. Glob. Power Propuls. Soc.

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This paper presents a novel tool for the modeling of partial turboelectric propulsion systems together with a corresponding case study for a commercial single-aisle aircraft. In order to reduce the environmental impact of air traffic, radically new aircraft and propulsion concepts with a high market penetration are needed. Partial turboelectric propulsion systems seem to offer a promising option to achieve this. For the development of these propulsion systems, a preliminary design tool with a homogeneous and sufficiently high fidelity, both for turbomachinery and electric components, is needed. To address this, the authors of this publication have developed a tool based on the GasTurb software. The models developed, in particular for the electric components which together form the electric powertrain, are described here. In the case study, which demonstrates the coupling of the developed tool with an aircraft design environment, a conventional turboprop baseline aircraft is compared to a derived aircraft which features a partial turboelectric propulsion system with wingtip propellers. The latter are intended to reduce the induced drag, enabling a reduction of the aircraft's total shaft power demand compared to the conventional baseline aircraft. The comparison between the partial turboelectric aircraft and the baseline aircraft indicates that fuel reduction increases with power split. However, primarily increasing electric powertrain masses and a stagnating drag reduction result in lower additional fuel reductions for higher power splits. Despite these conclusions, the predicted induced drag reductions need further refinement as they were found to be optimistic. In summary, this publication presents a methodology and a set of physics-based component models for the preliminary design of partial turboelectric propulsion systems, so that the electric components can be investigated and optimized at the same high level of detail as the gas turbine.

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Section: Aircraft and Propulsion System Conceptsupporting

confidence: 84%

Preliminary Design of Integrated Partial Turboelectric Aircraft Propulsion Systems

Pohl

Kohler

Kellermann

et al. 2022

J. Glob. Power Propuls. Soc.

View full text Add to dashboard Cite

show abstract

“…Several reference passenger aircraft designed for the nextgeneration Short-Range mission, including Saeed-007.1 [6], PEGA-SUS [43], TU Delft [44], and TPR70neo+ [45], were chosen for reference and comparison. ATR72-600 was selected as the baseline aircraft for the SR mission.…”

Section: Initial Aircraft Sizingmentioning

confidence: 99%

Conceptual design and comparative study of strut-braced wing and twin-fuselage aircraft configurations with ultra-high aspect ratio wings

Karpuk

Elham

2021

Aiaa Aviation 2021 Forum

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Ultra-high aspect ratio wing Strut-braced wing Twin-fuselage Advanced airframe technology Conceptual designSustainable and fuel-efficient next-generation air transportation demands a step change in aircraft performance. The ultra-high aspect ratio wings (UHARW) configuration is one key enabling strategy for improving aircraft aerodynamic efficiency and reducing fuel consumption and emissions. Unconventional aircraft configurations and advanced airframe technologies are required to address the large bending moment and shear stresses in the UHARW structure. This paper considers two promising unconventional configurations for adopting UHARW design, including strut-braced-wing (SBW) and twin-fuselage (TF), with advanced airframe technologies, i.e., active flow control, active load alleviation, and advanced airframe structures and materials. Three typical missions, including short-range (SR), medium-range (MR), and long-range (LR), are considered for aircraft design. A conceptual design and performance analysis framework for SBW and TF configurations is developed in this paper. According to the mission profile and top-level requirements proposed for each mission, an SBW and a TF configuration are designed, respectively. A comparative study is carried out to determine the best-in-class configuration of the corresponding mission to evaluate the potential of SBW and TF configurations for next-generation sustainable aviation applications. The results showed that the TF configuration has a better wing weight reduction effect than the SBW configuration, and the MR-TF and LR-TF aircraft have lower takeoff weight and fuel weight than those of the SBW aircraft for the same mission. However, due to the adjustment of the cabin dimensions for the SR-TF aircraft, the SBW configuration outperforms the TF configuration in this mission.

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Conceptual design and comparative study of strut-braced wing and twin-fuselage aircraft configurations with ultra-high aspect ratio wings

Karpuk

Elham

2022

Aerospace Science and Technology

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Tail Sizing Considerations for Wingtip Propulsor Driven Aircraft Applied to the Parallel Electric-Gas Architecture with Synergistic Utilization Scheme (PEGASUS) Concept

Cited by 8 publications

References 17 publications

Preliminary Design of Integrated Partial Turboelectric Aircraft Propulsion Systems

Preliminary Design of Integrated Partial Turboelectric Aircraft Propulsion Systems

Conceptual design and comparative study of strut-braced wing and twin-fuselage aircraft configurations with ultra-high aspect ratio wings

Conceptual design and comparative study of strut-braced wing and twin-fuselage aircraft configurations with ultra-high aspect ratio wings

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