航空复合材料结构多层级优化设计：从元件试验到系统化校核

刘子昂; 陈英实; 邓天择; 王国玥; 宗越超; 杨婵; 郑锡涛

doi:10.7643/issn.1672-9242.2026.09.002

PDF(12770 KB)

装备环境工程 ›› 2026, Vol. 23 ›› Issue (9) : 14-28. DOI: 10.7643/issn.1672-9242.2026.09.002

专刊——航空装备结构动力学

航空复合材料结构多层级优化设计：从元件试验到系统化校核

刘子昂^1,2, 陈英实^1,2, 邓天择^1,2, 王国玥^1,2, 宗越超^1,2, 杨婵³, 郑锡涛^1,2,*

作者信息 +

Multi-level Optimization Design of Aeronautical Composite Structures: From Component Testing to Systematic Verification

LIU Ziang^1,2, CHEN Yingshi^1,2, DENG Tianze^1,2, WANG Guoyue^1,2, ZONG Yuechao^1,2, YANG Chan³, ZHENG Xitao^1,2,*

Author information +

文章历史 +

摘要

目的建立一套面向复杂力学性能约束的多层级优化设计方法,以系统解决上述问题。方法采用MODEFRONTIER联合ABAQUS构建逻辑清晰且易于调试的优化流程,分别从组件级、构件级和元件级3个层级展开。组件级对尾段蒙皮进行分区优化,并对比层压板与蜂窝夹层结构;构件级对隔框站位进行参数化建模与布局优化;元件级对开孔板开展铺层厚度与角度优化,并通过拉伸试验验证。结果组件级分区优化使关键区域改用蜂窝夹层结构,减重幅度提升68%,并基于稳定性分析为结构选型提供参考;构件级优化后经强度、刚度、动力学、稳定性及疲劳寿命校核,实现减重10.81%;元件级开孔板优化试验与仿真误差在5%以内,验证了方法的合理性。结论本文形成的多层级优化思路,覆盖了结构形式选择、布局优化和细观参数优化,并经试验验证,为航空复合材料结构减重优化设计提供了系统性的研究基础。

Abstract

The work aims to establish a multi-level optimization design method oriented to complex mechanical performance constraints to address the existing issues. Firstly, an optimization workflow with clear logical structure and easy modification was established by coupling MODEFRONTIER with ABAQUS. The optimization was carried out at assembly level, component level and element level. At the assembly level, partition optimization was performed on the aft-section skin, and laminate structures were compared with honeycomb sandwich structures. At the component level, parametric modeling and layout optimization were conducted for the frame stations. At the element level, ply thickness and ply angle optimization were implemented for the perforated plate, and the results were verified via tensile tests. Partition optimization at the assembly level enabled honeycomb sandwich structures to be adopted in critical regions, achieving a 68% increase in weight reduction margin, and provided references for structural type selection based on stability analysis. After component-level optimization, checks on strength, stiffness, dynamics, stability and fatigue life were performed, resulting in a weight reduction of 10.81%. The error between test and simulation results for the optimized perforated plate at the element level was within 5%, which verified the rationality of the proposed method. The multi-level optimization framework developed in this work covers structural type selection, layout optimization and mesoscopic parameter optimization. Validated by experiments, it provides a systematic research foundation for weight reduction optimization design of aerospace composite structures.

导出引用

刘子昂, 陈英实, 邓天择, 王国玥, 宗越超, 杨婵, 郑锡涛. 航空复合材料结构多层级优化设计：从元件试验到系统化校核[J]. 装备环境工程. 2026, 23(9): 14-28 https://doi.org/10.7643/issn.1672-9242.2026.09.002

LIU Ziang, CHEN Yingshi, DENG Tianze, WANG Guoyue, ZONG Yuechao, YANG Chan, ZHENG Xitao. Multi-level Optimization Design of Aeronautical Composite Structures: From Component Testing to Systematic Verification[J]. Equipment Environmental Engineering. 2026, 23(9): 14-28 https://doi.org/10.7643/issn.1672-9242.2026.09.002

中图分类号： V258

参考文献

[1] 姚卫星, 顾怡. 飞机结构设计[M]. 北京:国防工业出版社, 2016.
YAO W X, GU Y.Aircraft Structural Design[M]. Beijing:National Defense Industry Press, 2016.
[2] 刘小川, 马君峰, 白春玉, 等. 航空结构动力学研究的进展与展望[J]. 应用力学学报, 2022, 39(3):409-436.
LIU X C, MA J F, BAI C Y, et al.Progress and Prospect of Aviation Structural Dynamics Research[J]. Chinese Journal of Applied Mechanics, 2022, 39(3):409-436.
[3] 郑锡涛, 陈浩远, 李泽江, 等. 先进复合材料在未来飞行器中的应用[J]. 航空工程进展, 2011, 2(2):181-187.
ZHENG X T, CHEN H Y, LI Z J, et al.Application of Advanced Composite Materials to Future Aircraft[J]. Advances in Aeronautical Science and Engineering, 2011, 2(2):181-187.
[4] 雷凯, 王彬文, 成竹, 等. 飞机多钉壁板混合结构热应力分析与验证[J]. 应用力学学报, 2023, 40(1):40-47.
LEI K, WANG B W, CHENG Z, et al.Thermal Stress Analysis and Verification of Aircraft Multi-Bolt Hybrid Panel Structure[J]. Chinese Journal of Applied Mechanics, 2023, 40(1):40-47.
[5] 刘向民, 姚卫星, 陈方. 复合材料层合板结构冲击损伤数值模拟的损伤力学模型[J]. 航空学报, 2016, 37(10):3054-3063.
LIU X M, YAO W X, CHEN F.Damage Mechanics Model for Simulating Impact Responses of Composite Laminated Structures[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(10):3054-3063.
[6] 黄文俊, 程小全, 赵军. 直升机旋翼复合材料结构损伤容限设计中的问题[J]. 应用力学学报, 2014, 31(1):67-72.
HUANG W J, CHENG X Q, ZHAO J.Some Problems in Damage Tolerance Design of Helicopter Rotor Composite Structures[J]. Chinese Journal of Applied Mechanics, 2014, 31(1):67-72.
[7] 朱继宏, 郭文杰, 张卫红, 等. 多组件结构系统布局拓扑优化中处理组件干涉约束的惩罚函数方法[J]. 航空学报, 2016, 37(12):3721-3733.
ZHU J H, GUO W J, ZHANG W H, et al.A Penalty Function Based Method for Dealing with Overlap Constraints in Integrated Layout and Topology Optimization Design of Multi-Component Systems[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(12):3721-3733.
[8] 张卫红, 郭文杰, 朱继宏. 部件级多组件结构系统的整体式拓扑布局优化[J]. 航空学报, 2015, 36(8):2662-2669.
ZHANG W H, GUO W J, ZHU J H.Integrated Layout and Topology Optimization Design of Multi-Component Systems with Assembly Units[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(8):2662-2669.
[9] 郭中泽, 张卫红, 陈裕泽. 结构拓扑优化设计综述[J]. 机械设计, 2007, 24(8):1-6.
GUO Z Z, ZHANG W H, CHEN Y Z.An Overview on the Topological Optimization Design of Structures[J]. Journal of Machine Design, 2007, 24(8):1-6.
[10] 张卫红, 夏凉, 朱继宏, 等. 飞行器结构系统协同布局优化设计技术[J]. 航空制造技术, 2010, 53(24):32-37.
ZHANG W H, XIA L, ZHU J H, et al.Optimal Design Technology of Collaboration Arrangement for Aircraft Structure[J]. Aeronautical Manufacturing Technology, 2010, 53(24):32-37.
[11] 柏林, 谷云峰, 常楠, 等. 面向航空航天领域的生成式结构拓扑优化设计方法研究综述[J]. 航空制造技术, 2026, 69(11):46-64.
BAI L, GU Y F, CHANG N, et al.A Review of Generative Structural Topology Optimization Design Methods for Aerospace Applications[J]. Aeronautical Manufacturing Technology, 2026, 69(11):46-64.
[12] 王箭飞. 航空发动机典型薄壁加筋结构可靠性高效优化方法研究[D]. 大连:大连理工大学, 2025.
WANG J F.Research on reliability and efficient optimization method of typical thin-walled stiffened structures of aeroengines[D]. Dalian:Dalian University of Technology, 2025.
[13] KIM J S, KIM C G, HONG C S.Optimum Design of Composite Structures with Ply Drop Using Genetic Algorithm and Expert System Shell[J]. Composite Structures, 1999, 46(2):171-187.
[14] MORADI S, VOSOUGHI A R, ANJABIN N.Maximum Buckling Load of Stiffened Laminated Composite Panel by an Improved Hybrid PSO-GA Optimization Technique[J]. Thin-Walled Structures, 2021, 160:107382.
[15] 韩微. 复合材料全动舵面结构优化设计[D]. 南京:南京航空航天大学, 2017.
HAN W.Optimization Design for Composite All-Moved Wing[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2017.
[16] 常楠, 赵美英, 王伟, 等. 基于PATRAN/NASTRAN的复合材料机翼蒙皮优化设计[J]. 西北工业大学学报, 2006, 24(3):326-329.
CHANG N, ZHAO M Y, WANG W, et al.Efficiently Optimizing Skin of Composite Wing Structure with PATRAN/NASTRAN[J]. Journal of Northwestern Polytechnical University, 2006, 24(3):326-329.
[17] 梁海州, 张元龙. 复合材料蜂窝夹层结构翼梁优化设计[J]. 机械制造与自动化, 2009, 38(3):3-5.
LIANG H Z, ZHANG Y L.Optimal Design of Composite Wing Beam with Honeycomb Sandwich[J]. Machine Building & Automation, 2009, 38(3):3-5.
[18] 王想生, 赵彬, 李永刚, 等. 基于ISIGHT/NASTRAN的机翼翼梁的结构优化设计[J]. 飞机设计, 2008, 28(4):23-27.
WANG X S, ZHAO B, LI Y G, et al.Structure Optimization of Airfoil Based on ISIGHT/NASTRAN[J]. Aircraft Design, 2008, 28(4):23-27.
[19] LI D C, XIANG J W.Optimization of Composite Wing Structure for a Flying Wing Aircraft Subject to Multi Constraints[M]. Boston:American Institute of Aeronautics and Astronautics, 2000.
[20] 陈牛. RTM复合材料平尾结构优化设计与分析[D]. 西安:西北工业大学, 2021.
CHEN N.Structural optimization design and analysis of RTM composite horizontal tail[D]. Xi'an:Northwestern Polytechnical University, 2021(in Chinese).
[21] 王栋, 张卫红, 姜节胜. 桁架结构形状与尺寸组合优化[J]. 应用力学学报, 2002, 19(3):72-76.
WANG D, ZHANG W H, JIANG J S.Combined Shape and Sizing Optimization in Truss Design[J]. Chinese Journal of Applied Mechanics, 2002, 19(3):72-76.
[22] 刘攀, 周鹏帅, 张远舰. 基于拓扑优化的航空发动机支架结构优化设计[J]. 机械工程师, 2026(5):4-9.
LIU P, ZHOU P S, ZHANG Y J.Optimal Design of Aero-Engine Bracket Structure Based on Topology Optimization[J]. Mechanical Engineer, 2026(5):4-9.
[23] 刘晓娇, 李世琛. 基于有限元的航空轮胎试验工装结构设计及优化[J]. 装备制造技术, 2026(3):118-122.
LIU X J, LI S C.Structural Design and Optimization of Aviation Tire Test Fixture Based on Finite Element Method[J]. Equipment Manufacturing Technology, 2026(3):118-122.
[24] 梁智元. 基于轻量化设计的航空减速器壳体结构优化[J]. 中国机械, 2025(3):21-24.
LIANG Z Y.Structural Optimization of Aviation Reducer Shell Based on Lightweight Design[J]. Machine China, 2025(3):21-24.
[25] 王毅, 姚卫星, 刘梦. 机翼结构布局优化的并行子空间方法[J]. 航空工程进展, 2019, 10(5):593-600.
WANG Y, YAO W X, LIU M.Concurrent Subspace Optimization Method for Wing Layout Design[J]. Advances in Aeronautical Science and Engineering, 2019, 10(5):593-600.
[26] 张立丰, 姚卫星, 邹君. 模块化飞机结构优化设计的等效多工况法[J]. 航空学报, 2015, 36(3):834-839.
ZHANG L F, YAO W X, ZOU J.Equivalent Multi-Case Optimization Architecture for Modular Aircraft Structures[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(3):834-839.
[27] 王伟, 杨伟, 赵美英, 等. 基于神经网络与杂交算法的机翼结构优化设计[J]. 机械设计, 2007, 24(8):49-52.
WANG W, YANG W, ZHAO M Y, et al.Optimization Design of Aerofoil Structure Based on Neural Network and Hybridization Algorithm[J]. Journal of Machine Design, 2007, 24(8):49-52.
[28] 邓扬晨, 张卫红, 章怡宁. 基于分级优化的飞机翼面结构布局综合技术研究[J]. 强度与环境, 2005, 32(1):27-35.
DENG Y C, ZHANG W H, ZHANG Y N.Aircraft Wing Structural Layout Study Based on Hierarchy Optimization[J]. Structure & Environment Engineering, 2005, 32(1):27-35.
[29] PARK J H, HWANG J H, LEE C S, et al.Stacking Sequence Design of Composite Laminates for Maximum Strength Using Genetic Algorithms[J]. Composite Structures, 2001, 52(2):217-231.
[30] 程文渊, 常艳, 崔德刚, 等. 基于分布式计算的复合材料机翼优化设计[J]. 复合材料学报, 2007, 24(1):167-171.
CHENG W Y, CHANG Y, CUI D G, et al.Composite Wing Optimization Design Based on Distributed Computing[J]. Acta Materiae Compositae Sinica, 2007, 24(1):167-171.
[31] 冯雁, 郑锡涛, 吴淑一, 等. 轻型复合材料机翼铺层优化设计与分析[J]. 航空学报, 2015, 36(6):1858-1866.
FENG Y, ZHENG X T, WU S Y, et al.Layup Optimization Design and Analysis of Super Lightweight Composite Wing[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(6):1858-1866.
[32] 张铁亮, 刘利阳, 景禄路, 等. 蜂窝夹层结构稳定性模拟研究[J]. 飞机设计, 2015, 35(5):13-16.
ZHANG T L, LIU L Y, JING L L, et al.Research on Stability Problem of Honeycomb Sandwich Structures[J]. Aircraft Design, 2015, 35(5):13-16.
[33] 周祝林. 蜂窝夹层板的极限强度[J]. 力学学报, 1983, 15(1):62-69.
ZHOU Z L.Ultimate Strength of Sandwich Panels with Honeycomb Core[J]. Chinese Journal of Theoretical and Applied Mechanics, 1983, 15(1):62-69.