To investigate the combustion enhancement effect of the dual combustor ramjet engine (DCR) configuration on boron-based propellants and its contribution to engine performance, this study selects the scramjet engine (SCR) as a comparison. The results indicate that, compared to SCR, the DCR effectively promotes the combustion of boron-based propellants under the conditions of Ma 5 at H28 km (Case 1) and Ma 6 at 30 km (Case 2), benefiting from the high-temperature and high-pressure environment of the subsonic combustor, while maintaining relatively low total pressure loss and better engine performance. In Case 1, the com-bustion efficiency of DCR is higher than that of SCR by 26.6 %, 27.2 %, and 23.8 % for engine lengths of 1.5 m, 2 m, and 2.5 m, respectively, with specific impulses of 1964 m/s, 1970 m/s, and 1406 m/s. In Case 2, DCR shows combustion efficiencies higher than SCR by 27.9 %, 22.3 %, and 22.9 %, with specific impulses of 1615 m/s, 1393 m/s, and 960 m/s, respectively. The shorter the engine length, the more pronounced the performance advantage of DCR over SCR, indicating that DCR is preferable in space-constrained application scenarios.
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