Integrated Propulsive and Thermal Management System Design for Optimal Hybrid Electric Aircraft Performance-Reference-Cited by-同舟云学术

Integrated Propulsive and Thermal Management System Design for Optimal Hybrid Electric Aircraft Performance

Published:2020-08-17 Issue: Volume: Page:
ISSN:
Container-title:AIAA Propulsion and Energy 2020 Forum
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Author:

Abolmoali Philip C.¹,Donovan Adam B.¹,Patnaik Soumya S.¹,McCarthy Patrick²,Dierker Dominic²,Jones Nick²,Buettner Robert³

Affiliation:

1. Air Force Research Laboratory

2. PC Krause and Associates

3. UES, Inc.

Publisher

American Institute of Aeronautics and Astronautics

Reference19 articles.

1. A Survey of Hybrid Electric Propulsion for Aircraft

2. Hiserote, R. M. "Analysis of Hybrid Electric Propulsion Designs for Small Unmanned Aircraft Systems," M.S. Thesis, Aeronautics and Astronautics Dept.Air Force Institute of Technology, Wright Patterson Air Force Base, OH,2010.

3. Cinar, G. "A Methodology for Dynamic Sizing of Electric Power Generation and Distribution Architectures," Ph.D. Dissertation, School of Aerospace Engineering,Georgia Tech, Atlanta,GA, 2018

4. An Initial Sizing Methodology for Hybrid-Electric Light Aircraft

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