Conceptual Design of the Parallel Electric-Gas Architecture with Synergistic Utilization Scheme (PEGASUS) Concept

Antcliff, Kevin R.; Capristan, Francisco M.

doi:10.2514/6.2017-4001

Cited by 85 publications

(55 citation statements)

References 13 publications

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“…A variation of this concept is an architecture with two electric-driven wingtip propellers and a conventionally placed gas turbine on each wing (Figure 1). This wingtip propeller architecture described by DLR [15] and NASA [13] promises better lift properties of the aircraft and limited weight as well as cost increases. A larger number of engines can lead to lower oversizing factors of the power rating for each propulsor which is sized due to the one engine inoperative (OEI) case.…”

Section: Propulsion Architecturementioning

confidence: 99%

“…According to the design of the reference aircraft 95 kg per PAX are chosen [46]. A NASA study of regional (<900 NM) air transportation demand in the US in 2030 depicts that 85% of all trips will be less than 350 NM long [13]. Hence, a design range of 350 NM is chosen for this simulation, which equals 648 km.…”

Section: Aircraft Top-level Requirementsmentioning

confidence: 99%

“…The values of c i can be selected by detailed engine modeling with a typical combination of {2.88, 0.025, 0.2}, as suggested by Howe [56]. In this model, higher drag parameters caused by idling propellers are neglected, which could be achieved by introducing a blade folding mechanism [13]. The described input parameters and models are taken for a first initial aircraft sizing, which delivers minimal power-to-weight and weight-to-wing-ratios ( Figure 3).…”

Section: Simulation Structurementioning

confidence: 99%

“…In the LEAPtech project, distributed propulsion, its aerodynamic effects [11] and larger aircraft with aft fuselage propulsors [12] are investigated. In their PEGASUS concept [13,14] a wingtip propeller architecture is applied for a regional aircraft, highlighting the propulsion system and different fixed battery energy settings. The PEGASUS concept shows that battery hybrid to conventional propulsion vehicles offer a limited economic competitiveness for low battery specific energy (<600 Wh/kg) and high electricity costs.…”

Section: Introductionmentioning

confidence: 99%

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Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

et al. 2018

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Ambitious targets to reduce emissions caused by aviation in the light of an expected ongoing rise of the air transport demand in the future drive the research of propulsion systems with lower CO 2 emissions. Regional hybrid electric aircraft (HEA) powered by conventional gas turbines and battery powered electric motors are investigated to test hybrid propulsion operation strategies. Especially the role of the battery within environmentally friendly concepts with significantly reduced carbon footprint is analyzed. Thus, a new simulation approach for HEA is introduced. The main findings underline the importance of choosing the right power-to-energy-ratio of a battery according to the flight mission. The gravimetric energy and power density of the electric storages determine the technologically feasibility of hybrid concepts. Cost competitive HEA configurations are found, but do not promise the targeted CO 2 emission savings, when the well-to-wheel system is regarded with its actual costs. Sensitivity studies are used to determine external levers that favor the profitability of HEA.

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Section: Propulsion Architecturementioning

confidence: 99%

Section: Aircraft Top-level Requirementsmentioning

confidence: 99%

Section: Simulation Structurementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

et al. 2018

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“…A second emerging trend is the push toward more electric propulsion systems concepts. For example, the PEGASUS [15], N-3X [16], and STARC-ABL [12] all propose some form of more electric propulsion.…”

Section: Introductionmentioning

confidence: 99%

pyCycle: A Tool for Efficient Optimization of Gas Turbine Engine Cycles

Hendricks

Gray

2019

Aerospace

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Aviation researchers are increasingly focusing on unconventional vehicle designs with tightly integrated propulsion systems to improve overall aircraft performance and reduce environmental impact. Properly analyzing these types of vehicle and propulsion systems requires multidisciplinary models that include many design variables and physics-based analysis tools. This need poses a challenge from a propulsion modeling standpoint because current state-of-the-art thermodynamic cycle analysis tools are not well suited to integration into vehicles level models or to the application of efficient gradient-based optimization techniques that help to counteract the increased computational costs. Therefore, the objective of this research effort was to investigate the development a new thermodynamic cycle analysis code, called pyCycle, to address this limitation and enable design optimization of these new vehicle concepts. This paper documents the development, verification, and application of this code to the design optimization of an advanced turbofan engine. The results of this study show that pyCycle models compute thermodynamic cycle data within 0.03% of an identical Numerical Propulsion System Simulation (NPSS) model. pyCycle also provides more accurate gradient information in three orders of magnitude less computational time by using analytic derivatives. The ability of pyCycle to accurately and efficiently provide this derivative information for gradient-based optimization was found to have a significant benefit on the overall optimization process with wall times at least seven times faster than using finite difference methods around existing tools. The results of this study demonstrate the value of using analytic derivatives for optimization of cycle models, and provide a strong justification for integrating derivatives into other important engineering analyses.Aerospace 2019, 6, 87 2 of 36 design process with cycle analysis serving as the key analysis method for initializing, guiding the development of, and then ultimately confirming the final engine design [6].Cycle analysis techniques have been studied since the conception of the gas turbine engine in the 1930s. While the fundamental equations governing cycle analysis are rooted in the laws of thermodynamics for a steady one-dimensional flow, the implementation of these equations has changed substantially over the years. These different implementations, predominantly in the form of various computer codes, can be organized into several major eras as shown in Figure 1. This history was pieced together from several sources [6][7][8] with incomplete or conflicting information, so it should be noted that the dates defining the start and end of these eras are approximate.

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