Experimental investigation of rocket ejector in SMC combustion mode

Experimental investigation is carried out to explore the factors affecting rocket ejector performance. This paper mainly investigates the effect of ejector combustor geometry and primary rocket chamber pressure to ejector rocket performance in SMC combustion mode, for which fuel rich gas oxygen/alcohol gas generator and geometry adjustable ejector combustor are adopted. The experimental results show that ejector combustor geometry is the key factor to ejector rocket relative thrust in SMC combustion mode, but primary rocket chamber pressure play a subordination role. By optimizing ejector combustor geometry, ejector rocket in SMC combustion mode can obtain comparable thrust augmentation.