某发动机石墨喉衬的裂纹成因分析  

Graphite throat insert cracks analysis of a solid rocket motor

作　　者：熊波[1] 白彦军[2] 唐敏[2] 

机构地区：[1]中国航天科技集团公司四院,西安710025 [2]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2016年第2期179-183,共5页Journal of Solid Rocket Technology

摘　　要：确保石墨喉衬在工作期间的结构完整性是某级间分离固体发动机设计的重要任务,初步设计方案经试车考核后,部分石墨喉衬出现了裂纹。针对该发动机喷管进行了喉衬热结构仿真分析,获得了不同危险点的应力大小和状态,并探讨了该喉衬裂纹的成因。结果表明,喷管仿真分析结果与实际试车结果吻合较好,点火初期石墨喉衬在大梯度的温度和压力冲击下,内部易产生较大的热应力,若石墨材料轴向拉伸强度不足,将可能导致裂纹出现。A solid rocket motor is used for the separation of new launch vehicle stage. One of the important tasks is to ensure the integrality of graphite throat insert in the firing time. After experiment of the initial design, crack was observed in some of the throat insert was proposed. A simulation analysis method for throat insert thermal structure was proposed. The reason for the crack was explored. The results show that, in the initial time of firing, interior of graphite throat may produce great thermal stress under large gradient temperature and pressure, and the insufficiency of tensile strength in axial direction gives birth to the crack.

关 键 词：石墨喉衬 裂纹 热结构 强度 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]