引射式火箭冲压组合推进系统的数值仿真

为了研究利用火箭作为引射器的引射式火箭冲压发动机的性能及内部流动机理,建立了一维总体性能计算模型,对火箭冲压组合发动机的性能参数进行了数值计算;此外,又基于CFD技术,对火箭冲压组合发动机的内部流场进行了数值仿真。总体性能计算结果表明,引射式火箭冲压发动机可以产生推力增益和提高比冲;流场计算结果表明,火箭主流与二次空气流在引射掺混过程中参数匹配是合理的。由此可见,所建立的计算模型是正确合理的,采用火箭发动机和亚燃冲压发动机的组合方式是可行的。

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.