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International Journal for Research Trends and Innovation
International Peer Reviewed & Refereed Journals, Open Access Journal
ISSN Approved Journal No: 2456-3315 | Impact factor: 8.14 | ESTD Year: 2016
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Issue: February 2026
Volume 11 | Issue 2
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Impact Factor : 8.14
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| Paper Title: | Design of Hybridization and Distributed Propulsion for a Regional Turbo-Prop Aircraft |
| Authors Name: | Nirmala T , Rajasai Bhadri , Maithreya J S |
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| Author Reg. ID: |
IJRTI_209176
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| Published Paper Id: | IJRTI2601050 |
| Published In: | Volume 11 Issue 1, January-2026 |
| DOI: | |
| Abstract: | The present work aims at studying the possibility of a distributed propulsion for an ATR-72 Regional Aircraft. Considering the demand a Regional Aircraft is experiencing, its continuous growth and keeping in mind the economic and environmental factors associated with it, the initial part of the project highlights the role of Hybrid and All-Electric Propulsion technology for future aircrafts. A Hybrid Electric Aircraft produces energy by making use of an on board gas-turbine that drives a generator that produces electricity. This electricity is then distributed within the airframe by means of cables to the inverters or the motor controllers that drive the motors. These motors convert the electric energy into kinetic energy by means of a propeller. Since, the series hybrid architecture allows us to have distributed propulsion, we chose this configuration. Simple models have been adopted and designed for the power chain. The validation of these models has been restricted to the literature considering the vast scope of variables involved in their design. These models have been designed in the form of small subsets, so that they can be integrated into future projects for design and optimization under MDAO framework. The gas turbine model for a turboprop engine was generated in order to obtain the shaft power as a function of altitude and velocity which is required for the series hybrid electric model. The models are tested and have been found to give favourable results with respect to the limited literature acquired over the course of our research. They have been tested for 2, 4, 6 and 8 propeller configurations with a Lithium Oxygen battery, having energy capacity of 1000 Wh/Kg. It has been observed that maximum fuel savings are obtained for 4 propellers. Further tests and modifications could be necessary for the practical application of these models. Designers can optimize the power distribution based on individual requirements using these models. The project can now be extended to a feasibility study for lateral control with asymmetric thrust settings and minimized tail design. |
| Keywords: | Series Hybrid Electric Aircraft (SHEA), Distributed Propulsion, Gas Turbine Model. |
| Cite Article: | "Design of Hybridization and Distributed Propulsion for a Regional Turbo-Prop Aircraft", International Journal for Research Trends and Innovation (www.ijrti.org), ISSN:2455-2631, Vol.11, Issue 1, page no.a386-a388, January-2026, Available :http://www.ijrti.org/papers/IJRTI2601050.pdf |
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2456-3315 | IMPACT FACTOR: 8.14 Calculated By Google Scholar| ESTD YEAR: 2016 An International Scholarly Open Access Journal, Peer-Reviewed, Refereed Journal Impact Factor 8.14 Calculate by Google Scholar and Semantic Scholar | AI-Powered Research Tool, Multidisciplinary, Monthly, Multilanguage Journal Indexing in All Major Database & Metadata, Citation Generator |
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Published Paper ID: IJRTI2601050
Registration ID:209176
Published In: Volume 11 Issue 1, January-2026
DOI (Digital Object Identifier):
Page No: a386-a388 Country: Shivamogga, Karnataka, India Research Area: Applied Mathematics Publisher : IJ Publication Published Paper URL : https://www.ijrti.org/viewpaperforall?paper=IJRTI2601050 Published Paper PDF: https://www.ijrti.org/papers/IJRTI2601050 |
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ISSN: 2456-3315
Impact Factor: 8.14 and ISSN APPROVED,
Journal Starting Year (ESTD) : 2016
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