航天推进技术研究院主办
[1]刘博,许健.ANSYS二次开发在火箭发动机法兰结构设计中的应用[J].火箭推进,2016,42(05):39-45.[doi:10.3969/j.issn.1672-9374.2016.05.008]
LIU Bo,XU Jian.Application of ANSYS secondary development in design of flange structure for rocket engine[J].Journal of Rocket Propulsion,2016,42(05):39-45.[doi:10.3969/j.issn.1672-9374.2016.05.008]
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LIU Bo,XU Jian.Application of ANSYS secondary development in design of flange structure for rocket engine[J].Journal of Rocket Propulsion,2016,42(05):39-45.[doi:10.3969/j.issn.1672-9374.2016.05.008]
ANSYS二次开发在火箭发动机法兰结构设计中的应用
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
42
期数:
2016年05期
页码:
39-45
栏目:
研究与设计
出版日期:
2016-10-31
- Title:
- Application of ANSYS secondary development in design of flange structure for rocket engine
- Keywords:
- rocket engine; flange structure; FEM; ANSYS secondary development
- 分类号:
- V431-34
- 摘要:
- 氢氧液体火箭发动机密封连接形式常采用一种法兰面贴合的榫槽式密封法兰结构,设计时主要采用有限元方法进行结构强度和密封性分析.为提高设计效率、简化有限元操作,利用ANSYS提供的用户界面设计语言(UIDL)和参数化设计语言(APDL)二次开发环境,开发结构分析程序模块.该程序模块能够将法兰结构有限元分析的前后处理和计算封装在后台操作,用户只需输入结构和材料参数,程序可自动进行有限元计算.利用有限元计算结果,通过垫片应力预测泄漏率进行密封性分析,结合螺栓和法兰最大应力,可确定垫片规格等结构参数和拧紧力矩等装配参数.通过实际应用验证,根据程序计算结果满足发动机热试车使用要求,验证计算方法合理.
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更新日期/Last Update:
1900-01-01