固体火箭发动机人工脱粘技术研究进展  

Research progress on stress release technology of solid rocket motors

作　　者：王学仁 王广 强洪夫 段磊光 杜莹 WANG Xueren;WANG Guang;QIANG Hongfu;DUAN Leiguang;DU Ying(Rocket Force University of Engineering,Xi’an 710025,China;China Aerospace Science and Technology Transportation Technology Research Institute,Beijing 102308,China)

机构地区：[1]火箭军工程大学,西安710025 [2]中国航天科工运载技术研究院北京分院,北京102308

出　　处：《固体火箭技术》2019年第3期334-339,共6页Journal of Solid Rocket Technology

摘　　要：针对固体火箭发动机人工脱粘技术,将其研究进展分为结构设计与优化、结构破坏机理、试验技术及数值仿真研究,发现在人工脱粘结构局部设计和数值仿真计算方面已取得一定的研究进展,但在有关人工脱粘前缘处脱粘机理和试验方法等方面还缺乏系统性的研究,人工脱粘结构的表征研究和实际工况差距还较大,人工脱粘结构模拟表征和破坏机理是高压强大型固体火箭发动机需要关注的关键技术。综合人工脱粘结构模拟表征、宏细观失效机理、数值模拟、失效准则、结构完整性分析与多因素优化设计以及全尺寸试验验证技术,是未来固体火箭发动机解决人工脱粘问题的发展途径。According to the stress release technology of solid rocket motor,its research progress is divided into four aspects: structural design and optimization,structural failure mechanism,experimental technology and numerical simulation. It is found that some progress has been made in the structural design and numerical simulation of stress release layer,but there is still a lack of sys tematic research on the stress release mechanism, test methods and numerical calculation methods at the leading edge of stress re lease. The characterization of stress release structures and the actual working conditions are still relatively large.The characterization and failure mechanism of the stress release structure is the key technology for the new generation of high pressure powerful solid rocket motors that need to be broken.It is a developing way to solve the problem of stress release of solid rocket motor in the future by integrating structure simulation characterization,macro meso failure mechanism,numerical simulation,failure criterion,structural integrity analysis and multi factor optimization design,as well as full scale test verification technology.

关 键 词：固体火箭发动机 人工脱粘 模拟表征 破坏机理 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]