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- W2318242721 abstract "Historically, during aircraft conceptual design, only limited consideration has been given to the aircraft subsystems, which have traditionally been addressed in the subsequent design phases. However, the design of future All Electric Aircraft or More Electric Aircraft will require a paradigm shift due to the lack of historical data and the presence of significant interactions among subsystems. As a result, the conceptual phase designer of such aircraft will seek the capability to perform subsystem sizing and analysis in parallel with traditional aircraft and propulsion system sizing and analysis. However, a significant challenge arises from the fact that the conceptual phase designer has limited and incomplete information regarding the design. This work presents a methodology to integrate subsystem sizing with conceptual design phase aircraft and propulsor sizing, while utilizing only the limited information that is available during this phase. The sizing of subsystem components is driven by requirements definition and the identification of critical or constraining operating scenarios. The subsystems considered include the environmental control system and ice protection system, actuation subsystems for flight control surfaces, landing gear, braking, and nose-wheel steering, and an innovative electric taxiing concept. Using a single-aisle narrowbody aircraft as a test case, the proposed methodology is demonstrated by comparing a conventional subsystem architecture to an electric one at the vehicle and mission level, and feeding back subsystem characteristics to the vehicle and propulsor sizing process." @default.
- W2318242721 created "2016-06-24" @default.
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- W2318242721 date "2014-06-13" @default.
- W2318242721 modified "2023-09-27" @default.
- W2318242721 title "A Requirements-driven Methodology for Integrating Subsystem Architecture Sizing and Analysis into the Conceptual Aircraft Design Phase" @default.
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- W2318242721 doi "https://doi.org/10.2514/6.2014-3012" @default.
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