SMC燃烧模式下引射火箭性能影响因素的实验研究

1引言为了降低航天发射费用,迫切需要提高有效载荷在航天器起飞质量中所占的比重。使用吸气式发动机,提高推进剂比冲成为一条有效的途径。为了使吸气式发动机适应航天发射所要经历的宽马赫数区间,使用组合循环推进(CCP)成为必然的选择。引射火箭是组合循环推进在低速起飞阶段的

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 eombustor geometry, ejector rocket in SMC combustion mode can obtain comparable thrust augmentation.