Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines
Rotating (also termed continuous spin) detonation technology is gaining interest in the global research and development community due to the potential for increased performance. Potential performance benefits, thrust chamber design, and thrust chamber cooling loads are analyzed for propellant applic...
| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2022-10-01
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| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/9/10/581 |
| _version_ | 1827652615184318464 |
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| author | Stephen D. Heister John Smallwood Alexis Harroun Kevin Dille Ariana Martinez Nathan Ballintyn |
| author_facet | Stephen D. Heister John Smallwood Alexis Harroun Kevin Dille Ariana Martinez Nathan Ballintyn |
| author_sort | Stephen D. Heister |
| collection | DOAJ |
| description | Rotating (also termed continuous spin) detonation technology is gaining interest in the global research and development community due to the potential for increased performance. Potential performance benefits, thrust chamber design, and thrust chamber cooling loads are analyzed for propellant applications using liquid oxygen or high-concentration hydrogen peroxide oxidizers with kerosene, hydrogen, and methane fuels. Performance results based on a lumped parameter treatment show that theoretical specific impulse gains of 3–14% are achievable with the highest benefit coming from hydrogen-fueled systems. Assessment of thrust chamber designs for notional space missions shows that both thrust chamber length and diameter benefits are achievable given the tiny annular chamber volume associated with the rotating detonation combustion. While the passing detonation front drastically increases local heat fluxes, global energy balances can be achieved if operating pressures are limited to be comparable to existing or prior space engines. |
| first_indexed | 2024-03-09T20:57:54Z |
| format | Article |
| id | doaj.art-e7eb5edc2d754cc2b9e103c15a21585d |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T20:57:54Z |
| publishDate | 2022-10-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-e7eb5edc2d754cc2b9e103c15a21585d2023-11-23T22:18:42ZengMDPI AGAerospace2226-43102022-10-0191058110.3390/aerospace9100581Rotating Detonation Combustion for Advanced Liquid Propellant Space EnginesStephen D. Heister0John Smallwood1Alexis Harroun2Kevin Dille3Ariana Martinez4Nathan Ballintyn5School of Aeronautics and Astronautics, Purdue University, West Lafayette, IN 47906, USASchool of Aeronautics and Astronautics, Purdue University, West Lafayette, IN 47906, USASchool of Aeronautics and Astronautics, Purdue University, West Lafayette, IN 47906, USASchool of Aeronautics and Astronautics, Purdue University, West Lafayette, IN 47906, USASchool of Aeronautics and Astronautics, Purdue University, West Lafayette, IN 47906, USASchool of Aeronautics and Astronautics, Purdue University, West Lafayette, IN 47906, USARotating (also termed continuous spin) detonation technology is gaining interest in the global research and development community due to the potential for increased performance. Potential performance benefits, thrust chamber design, and thrust chamber cooling loads are analyzed for propellant applications using liquid oxygen or high-concentration hydrogen peroxide oxidizers with kerosene, hydrogen, and methane fuels. Performance results based on a lumped parameter treatment show that theoretical specific impulse gains of 3–14% are achievable with the highest benefit coming from hydrogen-fueled systems. Assessment of thrust chamber designs for notional space missions shows that both thrust chamber length and diameter benefits are achievable given the tiny annular chamber volume associated with the rotating detonation combustion. While the passing detonation front drastically increases local heat fluxes, global energy balances can be achieved if operating pressures are limited to be comparable to existing or prior space engines.https://www.mdpi.com/2226-4310/9/10/581space propulsionrotating detonationcontinuous detonation |
| spellingShingle | Stephen D. Heister John Smallwood Alexis Harroun Kevin Dille Ariana Martinez Nathan Ballintyn Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines Aerospace space propulsion rotating detonation continuous detonation |
| title | Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines |
| title_full | Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines |
| title_fullStr | Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines |
| title_full_unstemmed | Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines |
| title_short | Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines |
| title_sort | rotating detonation combustion for advanced liquid propellant space engines |
| topic | space propulsion rotating detonation continuous detonation |
| url | https://www.mdpi.com/2226-4310/9/10/581 |
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