Experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operation
The rotating detonation engine (RDE) is an innovative pressure-gain combustion device that harnesses detonation waves for efficient fuel combustion. This paper examines the impact of various nozzle and combustor configurations on the operating characteristics of a rotating detonation rocket engine (...
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| Format: | Article |
| Language: | English |
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Elsevier
2025-09-01
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| Series: | Results in Engineering |
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| Online Access: | http://www.sciencedirect.com/science/article/pii/S2590123025020468 |
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| _version_ | 1849472677789564928 |
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| author | Guining Liu Zixuan Wang Yingying Ruan Zewen Zhong Rui Wang Shengbing Zhou Ning Hu |
| author_facet | Guining Liu Zixuan Wang Yingying Ruan Zewen Zhong Rui Wang Shengbing Zhou Ning Hu |
| author_sort | Guining Liu |
| collection | DOAJ |
| description | The rotating detonation engine (RDE) is an innovative pressure-gain combustion device that harnesses detonation waves for efficient fuel combustion. This paper examines the impact of various nozzle and combustor configurations on the operating characteristics of a rotating detonation rocket engine (RDRE) with a pulse operating frequency of 10 Hz. Through experimental analysis,the study investigates the propagation mode and establishment process of rotating detonation waves (RDWs) and the thrust performance across seven different engine structures to identify the optimal combination. The results show that the detonation-wave velocity and stability of cavity combustor are optimal, and the stability of detonation-wave propagation improves with an increasing equivalence ratio. The establishment time of the detonation wave is <10 % of the single pulse duration. At similar equivalence ratios, the RDRE featuring an annular combustor and a plug nozzle achieves the swiftest establishment at under 1 ms. The detonation-wave propagation velocity in RDREs exhibits significant differences between nozzle configurations: 2.1 km/s for Laval nozzles versus 1.8 km/s for plug nozzles. The RDRE with a Laval nozzle has higher detonation-wave propagation velocity than that of the plug nozzle structure. Furthermore, integrating a laval nozzle and a cavity combustor in a high-pulse-frequency operation significantly enhances the engine's propulsion performance. This research aspires to offer valuable insights for the utilization of RDREs in spacecraft attitude control applications. |
| format | Article |
| id | doaj-art-cf76f3828fa842449863d435aeac1f3d |
| institution | Kabale University |
| issn | 2590-1230 |
| language | English |
| publishDate | 2025-09-01 |
| publisher | Elsevier |
| record_format | Article |
| series | Results in Engineering |
| spelling | doaj-art-cf76f3828fa842449863d435aeac1f3d2025-08-20T03:24:28ZengElsevierResults in Engineering2590-12302025-09-012710597410.1016/j.rineng.2025.105974Experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operationGuining Liu0Zixuan Wang1Yingying Ruan2Zewen Zhong3Rui Wang4Shengbing Zhou5Ning Hu6College of Aerospace Engineering, Chongqing University, Chongqing 400044, ChinaCollege of Aerospace Engineering, Chongqing University, Chongqing 400044, ChinaCollege of Aerospace Engineering, Chongqing University, Chongqing 400044, ChinaCollege of Aerospace Engineering, Chongqing University, Chongqing 400044, ChinaCollege of Aerospace Engineering, Chongqing University, Chongqing 400044, ChinaCorresponding author.; College of Aerospace Engineering, Chongqing University, Chongqing 400044, ChinaCollege of Aerospace Engineering, Chongqing University, Chongqing 400044, ChinaThe rotating detonation engine (RDE) is an innovative pressure-gain combustion device that harnesses detonation waves for efficient fuel combustion. This paper examines the impact of various nozzle and combustor configurations on the operating characteristics of a rotating detonation rocket engine (RDRE) with a pulse operating frequency of 10 Hz. Through experimental analysis,the study investigates the propagation mode and establishment process of rotating detonation waves (RDWs) and the thrust performance across seven different engine structures to identify the optimal combination. The results show that the detonation-wave velocity and stability of cavity combustor are optimal, and the stability of detonation-wave propagation improves with an increasing equivalence ratio. The establishment time of the detonation wave is <10 % of the single pulse duration. At similar equivalence ratios, the RDRE featuring an annular combustor and a plug nozzle achieves the swiftest establishment at under 1 ms. The detonation-wave propagation velocity in RDREs exhibits significant differences between nozzle configurations: 2.1 km/s for Laval nozzles versus 1.8 km/s for plug nozzles. The RDRE with a Laval nozzle has higher detonation-wave propagation velocity than that of the plug nozzle structure. Furthermore, integrating a laval nozzle and a cavity combustor in a high-pulse-frequency operation significantly enhances the engine's propulsion performance. This research aspires to offer valuable insights for the utilization of RDREs in spacecraft attitude control applications.http://www.sciencedirect.com/science/article/pii/S2590123025020468Rotating detonation rocket enginePulse operationNozzle structureCombustorSpacecraft attitude control |
| spellingShingle | Guining Liu Zixuan Wang Yingying Ruan Zewen Zhong Rui Wang Shengbing Zhou Ning Hu Experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operation Results in Engineering Rotating detonation rocket engine Pulse operation Nozzle structure Combustor Spacecraft attitude control |
| title | Experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operation |
| title_full | Experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operation |
| title_fullStr | Experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operation |
| title_full_unstemmed | Experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operation |
| title_short | Experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operation |
| title_sort | experimental study on effects of nozzles and combustors on the rotating detonation rocket engine in pulse operation |
| topic | Rotating detonation rocket engine Pulse operation Nozzle structure Combustor Spacecraft attitude control |
| url | http://www.sciencedirect.com/science/article/pii/S2590123025020468 |
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