摘要
在固体火箭的发射技术中,常常涉及处在火箭羽流冲刷下发射装置表面热防护材料的烧蚀问题,技术人员需要了解材料的烧蚀机理及其速度的予测。为此,本文对热防护材料在火箭羽流正冲条件下的烧蚀问题进行了理论分析与实验研究,并提出一种能予估材料烧蚀性能的计算方法,计算结果与实例相符。
Jet exhaust of the solid rocket motor has a serious effect on the hot preservative material in rocket plume normal to the surface of material. Important one is metal oxide particle erosion on the material surface.This paper developed a method studing particle erosion, and developed a particle erosion formula..Finaly,a computational example was given,and theoretical results agree fairly with the experiment data.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1993年第4期92-96,共5页
Journal of Astronautics
关键词
烧蚀
粒子侵蚀
火箭发动机
热防护
Combustion erosion, particle erosion, Solid rocket nozzle flow, Heat Preservation of material
