Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket Motors
Hybrid Propellant Rocket Motors (HPRMs) have been advancing rapidly in recent years. These improvements are finally increasing their competitiveness in the global launch-vehicle market. However, some topics, such as the pre-combustion chamber design, still require more in-depth studies. Few studies...
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MDPI AG
2025-06-01
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| Series: | Energies |
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| Online Access: | https://www.mdpi.com/1996-1073/18/12/3123 |
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| author | Maurício Sá Gontijo Olexiy Shynkarenko Artur E. M. Bertoldi |
| author_facet | Maurício Sá Gontijo Olexiy Shynkarenko Artur E. M. Bertoldi |
| author_sort | Maurício Sá Gontijo |
| collection | DOAJ |
| description | Hybrid Propellant Rocket Motors (HPRMs) have been advancing rapidly in recent years. These improvements are finally increasing their competitiveness in the global launch-vehicle market. However, some topics, such as the pre-combustion chamber design, still require more in-depth studies. Few studies have examined this subject. This work proposes a low-computational-cost algorithm that calculates the minimum pre-combustion chamber length, with a vaporization and feed-system coupled instability model. This type of analysis is a key tool for minimizing a vehicle’s size, weight, losses, and costs. Additionally, coupling with internal ballistics codes can be implemented. Furthermore, the results were compared with real HPRMs to verify the algorithm’s reliability. The shortened pre-chamber architecture trimmed the inert mass and reduced the feed-system pressure requirement, boosting overall propulsive energy efficiency by <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mo>≈</mo><mn>8</mn><mo>%</mo></mrow></semantics></math></inline-formula> relative to conventional L*-based designs. These gains can lower stored-gas enthalpy and reduce life-cycle CO and CO<sub>2</sub>-equivalent emissions, strengthening the case for lighter and more sustainable access-to-space technologies. |
| format | Article |
| id | doaj-art-8f84befdb3b548c9ad89104bc5fc5366 |
| institution | OA Journals |
| issn | 1996-1073 |
| language | English |
| publishDate | 2025-06-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj-art-8f84befdb3b548c9ad89104bc5fc53662025-08-20T02:24:43ZengMDPI AGEnergies1996-10732025-06-011812312310.3390/en18123123Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket MotorsMaurício Sá Gontijo0Olexiy Shynkarenko1Artur E. M. Bertoldi2Aeronautical and Space Engineering Division, Aeronautics Institute of Technology, São José dos Campos 12228-900, BrazilFaculty of Science and Engineering Technologies, University of Brasília, Brasília 70910-900, BrazilFaculty of Science and Engineering Technologies, University of Brasília, Brasília 70910-900, BrazilHybrid Propellant Rocket Motors (HPRMs) have been advancing rapidly in recent years. These improvements are finally increasing their competitiveness in the global launch-vehicle market. However, some topics, such as the pre-combustion chamber design, still require more in-depth studies. Few studies have examined this subject. This work proposes a low-computational-cost algorithm that calculates the minimum pre-combustion chamber length, with a vaporization and feed-system coupled instability model. This type of analysis is a key tool for minimizing a vehicle’s size, weight, losses, and costs. Additionally, coupling with internal ballistics codes can be implemented. Furthermore, the results were compared with real HPRMs to verify the algorithm’s reliability. The shortened pre-chamber architecture trimmed the inert mass and reduced the feed-system pressure requirement, boosting overall propulsive energy efficiency by <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mo>≈</mo><mn>8</mn><mo>%</mo></mrow></semantics></math></inline-formula> relative to conventional L*-based designs. These gains can lower stored-gas enthalpy and reduce life-cycle CO and CO<sub>2</sub>-equivalent emissions, strengthening the case for lighter and more sustainable access-to-space technologies.https://www.mdpi.com/1996-1073/18/12/3123hybrid propellant rocket motorpre-combustion chamberdroplet vaporizationcombustion instability |
| spellingShingle | Maurício Sá Gontijo Olexiy Shynkarenko Artur E. M. Bertoldi Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket Motors Energies hybrid propellant rocket motor pre-combustion chamber droplet vaporization combustion instability |
| title | Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket Motors |
| title_full | Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket Motors |
| title_fullStr | Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket Motors |
| title_full_unstemmed | Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket Motors |
| title_short | Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket Motors |
| title_sort | droplet vaporization combustion stability based design of pre combustion chambers for hybrid propellant rocket motors |
| topic | hybrid propellant rocket motor pre-combustion chamber droplet vaporization combustion instability |
| url | https://www.mdpi.com/1996-1073/18/12/3123 |
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