离格
航天飞机热防护系统
固体燃料火箭
材料科学
热的
烧蚀
航空航天工程
核工程
机械工程
火箭(武器)
气动加热
热保护
机械
复合材料
推进剂
热力学
工程类
物理
传热
内科学
医学
放射治疗
作者
Ramin Shilav,Savely Khosid
出处
期刊:International Journal of Energetic Materials and Chemical Propulsion
[Begell House Inc.]
日期:2020-01-01
卷期号:19 (4): 275-292
被引量:2
标识
DOI:10.1615/intjenergeticmaterialschemprop.2020033869
摘要
A one-dimensional material response computer code has been developed for the ethylene-propylene-dien-monomer (EPDM)-based thermal protection system, designated as PARC. This surface ablation and pyrolysis code uses blowing wall boundary conditions and a dynamic coordinate system, and is coupled with computational fluid dynamics and thermodynamics programs' databases. A code-to-code comparison with NASA's PATO model shows very good agreement. Validation results are shown to be in good agreement with ablation gauges embedded in a subscale rocket motor. This modeling capability can improve modeling of ablative material performance in solid rocket motors.
科研通智能强力驱动
Strongly Powered by AbleSci AI