Preliminary Sizing Method for Hybrid-Electric Distributed-Propulsion Aircraft

Aero-Propulsive Efficiency Requirements for Turboelectric Transport Aircraft

“…The power flow across the powertrain can be computed based on ϕ for a given throttle setting or propulsive-power requirement following the matrix formulation of Ref. [23]. This power-control parameter has to be chosen by the designer for each flight condition.…”

“…Refs. [23,24]), contrary to some other classifications which make a distinction between hybrid-electric (electrical and non-electrical energy storage) and turboelectric (only non-electrical energy storage) propulsion [25]. When analyzing the existing literature, it becomes evident that, for large passenger aircraft, hybrid-electric propulsion can be used in two ways to improve aircraft efficiency.…”

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

“…A blended wing body (BWB) airframe is considered in the N3-X design [23]. Though the common understanding is that a DEP system in serial or turboelectric configuration gives additional aerodynamic benefits, there are few studies made on hybrid electric configuration with a DP approach [54,55].…”

“…Different studies use different control parameters to define the classification of the hybrid electric configurations. The study by Reynard et al [55] used three control parameters: supply power ratio, ϕ shaft power ratio, and gas turbine throttle ratio, to define the electric operation. Shaft power ratio defines the amount of shaft power produced by the electrical source and gas turbine throttle ratio represents the share of power produced by the gas turbine with respect to the maximum power it can produce.…”

“…Reynard et al [55] formulated sizing methodology where the design space is created with a point performance matching scheme in a power-to-weight ratio and wing-loading domain at first, on which various aircraft top-level driven constraints are imposed in order to segregate between the viable/unviable design spaces. A random point located on this design space represents the degree of hybridization to be optimized for the power-to-weight value for a given wing-loading (W/S).…”