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Turboelectric Distributed Propulsion System for NASA Next Generation Aircraft

Abada, Hashim H.
http://rave.ohiolink.edu/etdc/view?acc_num=wright1515501052742277

Abstract Details

2017, Master of Science in Aerospace Systems Engineering (MSASE), Wright State University, Mechanical Engineering.
Next generation aircraft, more specifically NASA aircraft concepts, will include new technologies and make many advancements in fuel economy and noise. However, there are some challenges associated with the latest technologies that NASA is planning to use for the next generation aircraft. For example, these aircraft concepts require large amounts of electrical power to generate the required thrust throughout a notional flight profile. One of the new technologies is using advanced propulsion systems, such as the Turboelectric Distributed Propulsion (TeDP) system, which is significantly different from current aerospace high bypass turbofan based propulsion system. The TeDP propulsion system replaces the traditional turbofan engines with a series of embedded electrical fans. The blended wing body aircraft, N3-X (Boeing 777 class), that NASA proposed will have as many as 14 electric fans mounted on the upper aft surface of the aircraft wings. In addition to improved aircraft efficiency, this propulsion system change will significantly reduce noise generation, and provide the capability of short take-off and landing. A dynamic model of the ducted fan distributed propulsion system was developed and simulated for different notional flight profiles. The results show that the ducted fan distributed propulsion system dynamic model and the control system successfully generate the required thrust for the flights and capture the transient behavior of the system throughout the flight profiles. In addition, the dynamic model was used to model a 50 passenger regional aircraft. This study shows the benefit of both the TeDP system and the flexibility of the developed model. The contribution to knowledge is the evolution of the evaluation model that helps researcher’s understand propulsion systems such as the TeDP system of NASA N+3 class aircraft. By identifying and understanding the principal challenges and possibilities provided by the technology, this research further contributes to defining a roadmap of the new technology propulsion system for future research.
Rory Roberts, Ph.D. (Advisor)
Zifeng Yang, Ph.D. (Committee Member)
Mitch Wolff, Ph.D. (Committee Member)
96 p.
Aerospace Engineering; Mechanical Engineering
NASA N3-X; Aircraft Propulsion System; TURBOELECTRIC DISTRIBUTED PROPULSION SYSTEM; Ducted Fan; Distributed Propulsion System; TeDP

Recommended Citations

Citations

  • Abada, H. H. (2017). Turboelectric Distributed Propulsion System for NASA Next Generation Aircraft [Master's thesis, Wright State University]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=wright1515501052742277

    APA Style (7th edition)

  • Abada, Hashim. Turboelectric Distributed Propulsion System for NASA Next Generation Aircraft. 2017. Wright State University, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=wright1515501052742277.

    MLA Style (8th edition)

  • Abada, Hashim. "Turboelectric Distributed Propulsion System for NASA Next Generation Aircraft." Master's thesis, Wright State University, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=wright1515501052742277

    Chicago Manual of Style (17th edition)

wright1515501052742277
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© 2017, some rights reserved.Creative Commons License Turboelectric Distributed Propulsion System for NASA Next Generation Aircraft by Hashim H. Abada is licensed under a Creative Commons Attribution-NonCommercial-NoDerivs 3.0 Unported License. Based on a work at etd.ohiolink.edu.
This open access ETD is published by Wright State University and OhioLINK.