固体火箭技术Issue(2)：203-207,213,6.DOI:10.7673/j.issn.1006-2793.2015.02.010
固体发动机低温点火适应性模拟试验技术
Simulation experiment technology for low temperature ignition adaptability of solid rocket motor
刘中兵 1张兵 2周艳青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
- 2. 中国航天科技集团公司四院，西安 710025
- 折叠
摘要
Abstract
Considering three key factors influencing solid rocket motor low temperature ignition adaptability,including low tem-perature mechanical property of solid propellant,grain strain induced by curing cooling down process,grain strain induced by ignition pressurization,the ϕ202 mm simulation solid motors were devised to investigate low temperature ignition adaptability of full-scale solid rocket motor.By choosing appropriate designing parameters of grain and initial operation pressure of simulation motors,the grain strain situation of full-scale solid rocket motors at low temperature ignition was simulated.The simulation motors were used to investi-gate low temperature ignition adaptability for A,B and C full-scale solid rocket motors at -40 ℃ or -50 ℃.The structure safety margin of each full-scale solid motor at low temperature ignition was gotten.The results can be widely used to investigate low temper-ature ignition adaptability for more solid motors.关键词
固体火箭发动机/推进剂药柱/低温点火/结构完整性/粘弹性Key words
solid rocket motor/propellant grain/low temperature ignition/structural integrity/viscoelasticity分类
航空航天引用本文复制引用
刘中兵,张兵,周艳青..固体发动机低温点火适应性模拟试验技术[J].固体火箭技术,2015,(2):203-207,213,6.
