固体火箭技术Issue(6)：814-818,5.DOI:10.7673/j.issn.1006-2793.2014.06.014
高低燃温组合推进剂下喷管喉衬烧蚀实验
Experiment on ablation of nozzle throat-insert by means of high and low temperature combined propellant
吴秋 1陈林泉 1杨玉新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
The ablation experiment of nozzle throat⁃insert by using pure⁃high temperature propellant and high⁃low temperature combined propellant were conducted,and low temperature propellants include HTPB and SCH⁃12 propellant. The results of experi⁃ments indicate that the ablation rate of HTPB and pure⁃high temperature combined propellant is 0.112 mm/s,and that of SCH⁃12 and high temperature combined propellant is 0.115 mm/s,and that of pure⁃high temperature propellant is 0.133mm/s.These results prove the validity and feasibility of reducing the ablation rate of by using high and low temperature combined propellant.Then the in⁃fluence of special impulse in different mass low temperature combined propellant was analyzed,the results show that when using low temperature and little specific impulse propellant,ablation of throat⁃insert can be reduced effectively,and the specific impulse of mo⁃tor is less affected..关键词
固体火箭发动机/高低燃温组合推进剂/喉衬/烧蚀率Key words
SRM/high and low temperature combined propellant/throat-insert/the ablation rate分类
航空航天引用本文复制引用
吴秋,陈林泉,杨玉新..高低燃温组合推进剂下喷管喉衬烧蚀实验[J].固体火箭技术,2014,(6):814-818,5.
