A framework for electrified propulsion architecture and operation analysis

Abstract

Purpose The purpose of this paper was to create a generic and flexible framework for the exploration, evaluation and side-by-side comparison of novel propulsion architectures. The intent for these evaluations was to account for varying operation strategies and to support architectural design space decisions, at the conceptual design stages, rather than single-point design solutions. Design/methodology/approach To this end, main propulsion subsystems were categorized into energy, power and thrust sources. Two types of matrices, namely, the property and interdependency matrices, were created to describe the relationships and power flows among these sources. These matrices were used to define various electrified propulsion architectures, including, but not limited to, turboelectric, series-parallel and distributed electric propulsion configurations. Findings As a case study, the matrices were used to generate and operate the distributed electric propulsion architecture of NASA’s X-57 Mod IV aircraft concept. The mission performance results were acceptably close to the data obtained from the literature. Finally, the matrices were used to simulate the changes in the operation strategy under two motor failure scenarios to demonstrate the ease of use, rapidness and automation. Originality/value It was seen that this new framework enables rapid and analysis-based comparisons among unconventional propulsion architectures where solutions are driven by requirements.

System-level Trade Study of Hybrid Parallel Propulsion Architectures on Future Regional and Thin Haul Turboprop Aircraft

“…In order to model the hybrid propulsion architecture, the propulsion module used in this study employs unique characteristics from Electrified Propulsion Architecture Sizing and Synthesis (E-PASS) [21,22], which defines any propulsion system architecture by categorizing each propulsion subsystem into three general groups:…”

“…• Energy sources represent subsystems which store energy to be used by the primary power sources (e.g., fossil fuel, battery, hydrogen, etc.) The logical connectivity between these components and the power management at each mission segment can be described using a set of matrices [21,22]. These matrices allow the computation of thrust requirement, power requirement, and energy consumption in power management functions, which are queried in the mission analysis module.…”

Feasibility Assessments of a Hybrid Turboelectric Medium Altitude Long Endurance Unmanned Aerial Vehicle

“…The interested reader is referred to Ref. [27,28] for more information on this aircraft design tool.…”

“…The interested reader can refer to Ref. [28] for a detailed explanations and definitions regarding the power splits between thrust, power and energy sources. In the context of this hybrid turboelectric architecture, power can be split between the energy and power sources in the following scenarios: i.…”

Performance Assessment of a Distributed Electric Propulsion System for a Medium Altitude Long Endurance Unmanned Aerial Vehicle

“…More information on the sizing and synthesis tool is available in Ref. [3,4] The series architecture allows for a source of power to be carried on the vehicle which does not lapse with altitude like an internal combustion engine and can be recharged and used again during the mission. The turboelectric variant does not provide an additional source of power but allows the turboprop engine to be decoupled from the propeller and thus allows both the engine and propeller to be operated more efficiently.…”