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In this paper, the activities at the German Aerospace Center (DLR) related to the conceptual design studies of aircraft configurations with hybrid electric propulsion for a typical short range commercial transport mission in the scope of the European Clean Sky 2 program in the project "Advanced Engine and Aircraft Configurations" (ADEC) are described. The configurations analyzed incorporate different hybrid powertrain architectures consisting of gas turbines, electric machines, and batteries. Technologies as distributed propulsion are utilized for the boundary layer ingestion at the fuselage and for the powered yaw control. The synergetic effects of a canard configuration and a BLI propulsor at the rear of the fuselage are investigated. The focus of this paper is on the quantitative evaluation of configurations utilizing a conceptual aircraft sizing workflow built in the DLR's "Remote Component Environment" incorporating semi-empirical and low level physics based methods. In order to depict the rationale behind the investigated aircraft configurations, a brief overview of the foregone downselection process is given. The concepts evaluated in the scope of this work are shown. The multi-disciplinary overall aircraft sizing workflow is described. An overview of reference configurations is given. The design space studies of configurations with hybrid electric propulsion are presented. The most promising configurations are shown in detail and compared to the advanced reference aircraft. Finally, a conclusion is drawn and an outlook is presented.

This paper describes the current activities at the German Aerospace Center (DLR) and an associated consortium related to conceptual design studies of an aircraft configuration with hybrid electric propulsion for a typical short range commercial transport mission. The work is implemented in the scope of the European Clean Sky 2 program in the project "Advanced Engine and Aircraft Configurations" (ADEC) and "Turbo electric Aircraft Design Environment" (TRADE). The configuration analyzed incorporates parallel hybrid architecture consisting of gas turbines, electric machines, and batteries that adds electric power to the fans of the engines. A conceptual aircraft sizing workflow built in the DLR's "Remote Component Environment" (RCE) incorporating tools of DLR that are based on semi-empirical and low level physics based methods. The TRADE consortium developed a simulation and optimization design platform with analysis models of higher fidelity for an aircraft with hybrid electric propulsion architecture. An implementation of the TRADE simulation and optimization design platform into the DLR's RCE workflow by replacing the DLR models was carried out. The focus of this paper is on the quantitative evaluation of the "Boosted Turbofan" configuration utilizing the resulting workflow. In order to understand the cooperation between the DLR and TRADE consortium, a brief overview of the activities is given. Then the multi-disciplinary overall aircraft sizing workflow for hybrid electric aircraft built in RCE is shown. Hereafter, the simulation and optimization models of the TRADE design platform are described. Subsequently, an overview of the aircraft configurations considered in the scope of this work is given. The design space studies of the "Boosted Turbofan" configuration are presented. Finally, the deviations of the results between the workflows with and without the TRADE modules are discussed.

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