壳体断裂力学统一计算理论与飞行器结构设计

庄茁; 王恒; 宁宇; 王翔; 柳占立; 张志楠

doi:10.6052/j.issn.1000-4750.2022.06.ST02

壳体断裂力学统一计算理论与飞行器结构设计

doi: 10.6052/j.issn.1000-4750.2022.06.ST02

庄茁^1, ,,
王恒^2,,
宁宇^3,,
王翔^4,,
柳占立^1,,
张志楠^3,

1.
清华大学航天航空学院，北京 100084
2.
北京航空工程技术研究中心，北京 100076
3.
航空工业第一飞机设计研究院，陕西，西安 710089
4.
北京空间飞行器总体设计部，北京 100094

基金项目: 国家自然科学基金面上项目(10272060)

详细信息

作者简介:
王　恒(1986−)，男，山西文水人，高工，博士，主要从事固体力学研究(E-mail: wang_heng03@126.com)

宁　宇(1982−)，男，福建邵武人，研究员，硕士，副院长，主要从事飞机强度研究(E-mail: ningy001@avic.com)

王　翔(1973−)，男，新疆库尔勒人，研究员，博士，主要从事空间站研究(E-mail: wangxiang0223@gmail.com

柳占立(1981−)，男，河南扶沟人，教授，博士，主要从事固体力学研究(E-mail: liuzhanli@tsinghua.edu.cn)

张志楠(1986−)，男，陕西咸阳人，高工，硕士，主要从事飞机强度研究(E-mail: zhangzhinan198678@126.com)

通讯作者:
庄　茁(1952−)，男，辽宁沈阳人，教授，博士，主要从事固体力学研究(E-mail: zhuangz@tsinghua.edu.cn)

中图分类号: V22；V42
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- 文章访问数: 129
- HTML全文浏览量: 24
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- 被引次数: 0
出版历程
- 收稿日期: 2022-06-15
- 修回日期: 2022-07-15
- 网络出版日期: 2022-11-10
- 刊出日期: 2023-02-01

UNIFIED COMPUTATIONAL THEORY OF FRACTURE MECHANICS IN SHELL AND AIRCRAFT STRUCTURAL DESIGN

ZHUANG Zhuo^{1
, ,},
WANG Heng^2
,,
NING Yu^3
,,
WANG Xiang^4
,,
LIU Zhan-li^1
,,
ZHANG Zhi-nan^3
,

1.
Scholl of Aerospace Engineering, Tsinghua University, Beijing 100084, China
2.
Beijing Aviation Engineering and Technology Research Center, Beijing 100076, China
3.
The first Aircraft Design and Research Institute, Aviation Industry, Xi’an, Shaanxi 710089, China
4.
Beijing Spacecraft Totality Design Department, Beijing 100094, China

摘要

摘要: 断裂力学理论和方法在飞行器结构设计中发挥着不可替代的作用。依据断裂准则划分为阻止或者驱动裂纹扩展。阻止裂纹扩展是避免飞行器结构发生灾难性事故的最后一道防线，如机翼、机身等重要结构的止裂安全性设计、广布疲劳损伤容限设计等；驱动裂纹扩展是实现飞行器结构快速分离的关键技术，如运载火箭级间和星箭分离、飞行员和航天员逃逸救生等。板壳是飞行器结构的主要形式，开展板壳断裂力学研究具有重要的科学意义和工程价值。该文提出了基于连续体的壳体断裂力学统一计算理论，发展了壳体扩展有限元方法。基于该理论和方法，阐述了大变形曲面壳体裂纹扩展与止裂的计算分析过程，展示了在国产大飞机机翼整体结构件设计、天和号核心舱结构研制和高级教练机穿盖弹射救生系统设计等飞行器工程中的成功应用。
- 壳体 /
- 断裂力学 /
- 计算理论 /
- 飞行器结构 /
- 扩展有限元
Abstract: The fracture mechanics theory and methodology have played an irreplaceable role in aircraft structure design. According to fracture criterion, it is divided into preventing and driving crack propagation. The crack arrest is to prevent aircraft structure from catastrophic failure, which is the last safety defense line; for example, the fracture arrested design for wing and fuselage of important structures, damage tolerance design for wide spread fatigue, and so on. The driving crack propagation is the key technology to realize quick separation of structures; for example, interstage separation of carrier rocket, separation between satellite and rocket, escape and life-saving of pilot and astronaut, and so on. The plate and shell are main structural forms of aircraft. There is an important scientific significance and engineering worth for investigating fracture mechanics in plate and shell. The authors have proposed the unified computational theory of fracture mechanics in shell and developed the corresponding extended finite element method. Based on the theory and method, the fracture propagation and arrest analysis are expressed in a large deformation curved shell. The successful applications are exhibited for designing wing monolithic structural component of domestic large airplane, Tianhe kernel cabin structure and opening canopy life-saving system of the advanced trainer.
- shell /
- fracture mechanics /
- computational theory /
- aircraft structure /
- extended finite element method

HTML全文

图 1 传统板壳断裂理论

Figure 1. Classical plate-shell fracture theory

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图 2 基于连续体的壳体断裂及裂纹扩展

Figure 2. Continuum based shell fracture and crack propagation in the shel

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图 3 变厚度壳体结构三维裂纹翼形路径

Figure 3. 3-dimensional wing-crack growth in variable thickness shell structure

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图 4 整体翼板断裂分析和试验验证

Figure 4. Fracture analysis and experiment for integrated wing plate

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图 5 由加筋板整体加工成形的天和号核心舱圆柱壳结构

Figure 5. Cylindrical shell structure of Tianhe core cabin formed by integrated reinforced plate

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图 6 座舱透明件裂纹扩展路径的理论设计

Figure 6. Theoretical design for cracking path in cabin clear parts

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图 7 扩展长度的理论设计与试验验证

Figure 7. Theoretical design and experiment verification of cracking length

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图 8 裂纹扩展长度的模拟

Figure 8. Crack propagation length by simulations

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