固体火箭技术2017，Vol.40Issue(4)：403-408,6.DOI:10.7673/j.issn.1006-2793.2017.04.001
下颌式进气道固冲发动机二次燃烧性能研究
Performance investigation of the secondary combustionfor ducted rocket with chin inlet
杨玉新 1段艳娟 1平丽 1何俊卿1
作者信息
- 1. 中国航天科技集团公司四院四十一所,西安 710025
- 折叠
摘要
Abstract
Computation model was developed for the secondary combustion performance of ducted rocket with chin inlet.The secondary combustion performance was simulated,and the results showed that the mixing homogeneity of the first gas and the air in the ducted rocket combustion could be improved with mixing device.The configuration of the mixing device was optimized through simulation investigation.The mixing and combustion performance with and without mixing device were compared through the direct-connect experiments based on the configuration optimization.The secondary combustion performance could be increased with optimized mixing device.The combustion efficiency at a characteristic velocity was above 93％.The engine impulse at high altitude was improved by 55％ with the air/fuel ratio between 6 and 20,and it was improved by 75％ with the air/fuel ratio between 20 and 30.关键词
下颌式进气道/掺混装置/二次燃烧/比冲Key words
chin inlet/mixing device/secondary combustion/impulse分类
航空航天引用本文复制引用
杨玉新,段艳娟,平丽,何俊卿..下颌式进气道固冲发动机二次燃烧性能研究[J].固体火箭技术,2017,40(4):403-408,6.
