Experimental study for factors affecting rocket ejector performance in SMC combustion mode

Fuel rich gas oxygen/alcohol gas generator and geometry adjustable ejector combustor were employed to investigate the effect of ejector combustor geometry and primary rocket chamber pressure on ejector rocket performance in SMC combustion mode. The results show that ejector combustor geometry is the key factor to ejector rocket relative thrust in SMC combustion mode, and primary rocket chamber pressure plays a subordination role. By optimizing ejector combustor geometry, ejector rocket in SMC combustion mode can obtain comparable thrust augmentation.