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Analysis of Combustion Characteristics of HTPB, Graphite, Aluminum, Iron, and Gaseous Oxygen-Based Hybrid Rocket Propellant

Analysis of Combustion Characteristics of HTPB, Graphite, Aluminum, Iron, and Gaseous... Nowadays, the need for high specific impulse, characteristic velocity, and a good combustion chamber temperature at a moderate O/F ratio which can exhibit better performance for a hybrid rocket engine is desired. At the same time, a low-cost, highly effective, and eco-friendly propellant is always desired for a sustainable ecosystem. In this regard, we have proposed Hydroxyl-Terminated Polybutadiene in the paper as a better substitute for the existing fuels in the industry. To enhance the combustion characteristics of propellant, we have combined fuel Hydroxyl-Terminated Polybutadiene, Graphite, Aluminum, and Iron in some percentage with the oxidizer, i.e., Gaseous Oxygen. These additives are highly reactive, so the combustion properties will enhance. HTPB breaks into butadiene when mixing with oxygen and giving a better reaction mechanism. The observation of this paper is that HTPB mixed with additives will enhance the combustion characteristic and increasing the percentage of iron will decrease the combustion characteristics. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical and Space Sciences Springer Journals

Analysis of Combustion Characteristics of HTPB, Graphite, Aluminum, Iron, and Gaseous Oxygen-Based Hybrid Rocket Propellant

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References (15)

Publisher
Springer Journals
Copyright
Copyright © The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences 2023. Springer Nature or its licensor (e.g. a society or other partner) holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-023-00636-x
Publisher site
See Article on Publisher Site

Abstract

Nowadays, the need for high specific impulse, characteristic velocity, and a good combustion chamber temperature at a moderate O/F ratio which can exhibit better performance for a hybrid rocket engine is desired. At the same time, a low-cost, highly effective, and eco-friendly propellant is always desired for a sustainable ecosystem. In this regard, we have proposed Hydroxyl-Terminated Polybutadiene in the paper as a better substitute for the existing fuels in the industry. To enhance the combustion characteristics of propellant, we have combined fuel Hydroxyl-Terminated Polybutadiene, Graphite, Aluminum, and Iron in some percentage with the oxidizer, i.e., Gaseous Oxygen. These additives are highly reactive, so the combustion properties will enhance. HTPB breaks into butadiene when mixing with oxygen and giving a better reaction mechanism. The observation of this paper is that HTPB mixed with additives will enhance the combustion characteristic and increasing the percentage of iron will decrease the combustion characteristics.

Journal

International Journal of Aeronautical and Space SciencesSpringer Journals

Published: Jan 1, 2024

Keywords: Graphite; Aluminum; Iron; Hybrid rocket engine; HTPB; GOX; CEA

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