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Development of a Thermal Management System for Electrified AircraftThis paper describes the development and optimization of a conceptual thermal management system for electrified aircraft. Here, a vertical takeoff and landing (VTOL) vehicle is analyzed with the following electrically sourced heat loads considered: motors, generators, rectifiers, and inverters. The vehicle will employ liquid-cooling techniques in order to acquire, transport, and reject waste heat from the vehicle. The purpose of this paper is to threefold: 1) Present a potential modeling framework for system level thermal management system simulation, 2) Analyze typical system characteristics, and 3) Perform optimization on a system developed for a specific vehicle to minimize weight gain, power utilization, and drag. Additionally, the paper will study the design process, specifically investigating the differences between steady state and transient sizing, comparing simulation techniques with a lower fidelity option and quantifying expected error.
Document ID
20200001620
Document Type
Technical Memorandum (TM)
Authors
Chapman, Jeffryes W. (NASA Glenn Research Center Cleveland, OH, United States)
Schnulo, Sydney L. (NASA Glenn Research Center Cleveland, OH, United States)
Nitzsche, Michael P. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
March 16, 2020
Publication Date
March 1, 2020
Subject Category
Aeronautics (General)
Report/Patent Number
E-19786
AIAA–2020–0545
GRC-E-DAA-TN77515
NASA/TM-2020-220473
Meeting Information
AIAA SciTech Forum(Orlando, FL)
Funding Number(s)
CONTRACT_GRANT: NNC16QA09D
WBS: 109492.02.03.01.10
Distribution Limits
Public
Copyright
Public Use Permitted.

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NameType 20200001620.pdf STI