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The rocket-based combined cycle(RBCC) propulsion system is a promising combined power scheme. The mode transition phase is critical for RBCC engine operation, directly affecting the overall propulsion system's success and efficiency. Different working modes of RBCC engines show distinct classification characteristics.Two key transition phases, ejector/subsonic combustion and subsonic combustion/supersonic combustion, are focused, with research progress on their characteristics and mechanisms reviewed, and findings from experiments and numerical simulations consolidated. Compared with dual-mode scramjet engines, RBCC engines have advantages in smooth mode transition control due to the presence of rocket jets. Integrated with novel multi-field combustion coupling control methods(e.g., plasma), RBCC engines have become a research focus in supersonic combustion flow control. Based on the reviewed progress, suggestions for future mode transition research are provided.
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Basic Information:
DOI：10.16358/j.issn.1009-1300.20250012
China Classification Code:V438
Citation Information:
[1]Xue Rui,Wu Shenglei,He Ying ,et al.Research progress on mode transition in RBCC engines[J].Tactical Missile Technology,2025,No.232(04):75-89.DOI:10.16358/j.issn.1009-1300.20250012.
Fund Information:
国家自然科学基金面上项目(52376126); 复杂服役环境重大装备结构强度与寿命全国重点实验室自主团队项目(SV2023ZD05)
2025-08-15
2025-08-15