Numerical simulation of ejector-ram-rocket propulsion system

To investigate the performance and internal flow mechanism of ejector-ram-rocket engine in which the rocket was used as the ejector, one-dimensional performance computational model was established. Its performance parameters along the flight trajectory were calculated. Based on computational fluid dynamics technology, the numerical simulation of ejector-ram-rocket engine internal flow was processed. The performance results indicate that ejector-ram-rocket engine performance is strengthened. Internal flow results indicate that parameter matching is reasonable during the process of ejection and mixing between primary rocket flow and secondary air flow. This shows that the computational model is reasonable and the combination of rocket and ramjet engine is feasible.