民机机身CFRP C型隔框弯曲失效机理与吸能设计

  • 牟浩蕾 ,
  • 郑庆溢 ,
  • 赵祎明
展开
  • 中国民航大学

收稿日期: 2025-11-05

  修回日期: 2026-01-05

  网络出版日期: 2026-01-09

基金资助

中央高校基本科研业务费项目;天津市应用基础研究多元投入基金项目;国家自然科学基金项目;国家重点研发计划项目

Bending failure mechanisms and energy absorption design of CFRP C-frames for civil aircraft fuselage

  • MOU Hao-Lei ,
  • ZHENG Qing-Yi ,
  • ZHAO Yi-Ming
Expand

Received date: 2025-11-05

  Revised date: 2026-01-05

  Online published: 2026-01-09

Supported by

Fundamental Research Funds for the Central Universities;Tianjin Applied Basic Research Multi-Input Fund Project;National Natural Science Foundation of China;National Key R&D Program of China

摘要

针对民机机身碳纤维增强复合材料(CFRP)C型隔框弯曲吸能不足的问题,通过准静态四点弯曲数值模拟与试验对标,揭示了其失效机理与能量耗散机制,并提出了基于失效模式调控的钛合金局部加强设计方法。研究表明:CFRP C型隔框弯曲失效源于上缘条屈曲与腹板鼓曲的耦合变形,诱发上拐角处产生高层间应力及初始分层,失效后结构承载力骤降至峰值的12%,严重制约吸能。能量耗散呈现区域差异性,腹板是核心吸能区(占比50.2%),上缘条次之(占比24.1%),作为失效起点的上拐角仅占13.8%。在钛合金局部加强中,上拐角局部加强(UC构型)效果最优,通过钛合金塑性变形有效延缓了初始失效,在结构增重仅3.4%的前提下,总吸能和比吸能分别提升了26.1%和22.3%。钛合金局部加强设计实现了轻量化与耐撞性之间的最佳平衡,为民机机身结构适坠性设计提供了理论依据与工程指导。

本文引用格式

牟浩蕾 , 郑庆溢 , 赵祎明 . 民机机身CFRP C型隔框弯曲失效机理与吸能设计[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.33046

Abstract

To address the issue of insufficient bending energy absorption in carbon fiber reinforced polymer (CFRP) C-frames for civil aircraft fuselages, this study reveals the failure mechanisms and energy dissipation characteristics through quasi-static four-point bending numerical simulations and experimental benchmarking. Furthermore, the titanium alloy local reinforcement design method is proposed based on the failure mode control. The results indicate that the bending failure of the CFRP C-frame originates from the coupling effect between upper flange buckling and web bulging, which induces high interlayer stress and initial delamination at the upper corner. Consequently, the load-bearing capacity plummets to 12% of the peak load after failure, significantly constraining energy absorption. Energy dissipation exhibits significant regional heterogeneity: the web acts as the core energy absorption zone (accounting for 50.2%), followed by the upper flange (24.1%), while the upper corner, serving as the failure initiation point, contributes only 13.8%. Among the titanium alloy local reinforcement strategies, the upper corner local reinforcement (UC configuration) yields optimal performance. By leveraging the plastic deformation of titanium alloy to effectively delay initial failure, this configuration achieves a 26.1% increase in total energy absorption and a 22.3% increase in specific energy absorption, with a structural weight increase of only 3.4%. The titanium alloy local reinforcement design achieves the best balance between lightweighting and crashworthiness, providing a theoretical basis and engineering guidance for the crashworthiness design of civil aircraft fuselage structures.

参考文献

[1]MOU H L, XIE J, FENG Z Y, et al.Review on the crashworthiness design and evaluation of fuselage structure for occupant survivability[J].Progress in Aerospace Sciences, 2024, 148:- [2]MOU H L, XIE J, FENG Z Y.Research status and future development of crashworthiness of civil aircraft fuselage structures: An overview[J].Progress in Aerospace Science, 2020, 119:- [3]牟浩蕾, 解江, 冯振宇.民机机身结构适坠性研究[J].交通运输工程学报, 2020, 20(3):17-39 [4]WILLIAMS M S, HAYDUK R J.Vertical drop test of a transport fuselage section located forward of the wing: 19840002543[J]., 1983, :- [5]WILLIAMS M S, HAYDUK R J.Vertical drop test of a transport fuselage center section including the wheel wells: NASA TM-85706[J]., 1983, :- [6]ABRAMOWITZ A, SMITH T G, VU T.Vertical drop test of a narrow-body transport fuselage section with a conformable auxiliary fuel tank onboard: 0148-7191[J]., 2000, :- [7]JACKSON K E, FASANELLA E L.Crash simulation of vertical drop tests of two Boeing 737 fuselage sections: DOT/FAA/AR-02/62[J]., 2022, :- [8]KUMAKURA I, MINEGISHI M, IWASAKI K, et al.Vertical drop test of a transport fuselage section[J]., 2002, :- [9]KUMAKURA I, MINEGISHI M, IWASAKI K, et al.Summary of vertical drop tests of YS-11 transport fuselage sections[J]., 2003, :531-540 [10]LE PAGE F, CARCIENTA R.A320 fuselage section vertical drop test, Part 2: Test result: S955776/2[J]., 1995, :- [11]GRANSDEN D I, ALDERLIESTEN R.Development of a finite element model for comparing metal and composite fuselage section drop testing[J].International Journal of Crashworthiness, 2017, 22(4):401-414 [12]CLIMENT H, AERONáUTICAS C.Non-linear response of metallic and composite aeronautical fuselage structures under crash loads and comparison with full scale test[J].European Congress on Computational Methods in Applied Sciences and Engineering, 2000, :11-14 [13]LIU X C, GUO J, BAI C Y, et al.Drop test and crash simulation of a civil airplane fuselage section[J].Chinese Journal of Aeronautics, 2015, 28(2):447-456 [14]MOU H L, FENG Z Y, XIE J, et al.Collapse mechanism and occupant injury analysis under vertical impact of the aircraft fuselage structure[J].Nonlinear Dynamics, 2025, 113:1083-1105 [15]牟浩蕾, 谢威威, 解江, 等.坠撞环境下乘员伤害分析及飞机适坠性评估[J].航空学报, 2024, 45(3):- [16]惠旭龙, 刘小川, 白春玉, 等.民机机身框段和全机坠撞响应对比[J].航空学报, 2025, 46(15):- [17]刘小川, 惠旭龙, 张欣玥, 等.典型民用飞机全机坠撞实验研究[J].航空学报, 2024, 45(5):- [18]牟浩蕾, 解江, 冯振宇, 等.大型运输类飞机典型机身框段坠撞特性分析[J].航空学报, 2023, 44(9):- [19]MOSTAFA R.Virtual test & simulation[J]., 2013, :- [20]PALMA L D, CAPRIO F D, CHIARIELLO A, et al.Vertical drop test of composite fuselage section of a regional aircraft[J].AIAA Journal, 2020, 58(1):474-487 [21]RICCIO A, SAPUTO S, SELLITTO A, et al.An insight on the crashworthiness behavior of a full-scale composite fuselage section at different impact angles[J].Aerospace, 2019, 72(6):1-14 [22]WAIMER M, SCHATROW P.Crash concept for composite transport aircraft using mainly tensile and compressive absorption mechanisms[J].CEAS Aeronautical Journal, 2016, 7:471-482 [23]GUIDA M, MARULO F, ABRATE S.Advances in crash dynamics for aircraft safety[J].Progress in Aerospace Sciences, 2018, 98:106-123 [24]WAIMER M, FESER T, SCHATROW P, et al.Crash concepts for CFRP transport aircraft–comparison of the traditional bend frame concept versus the developments in a tension absorbers concept[J].International Journal of Crashworthiness, 2017, 23(2):193-218 [25]WAIMER M.Development of a kinematics model for the assessment of global crash scenarios of a composite transport aircraft fuselage[J]., 2013, :1-274 [26]ROZYLO P.Limit states of thin-walled composite structures with closed sections under axial compression[J].Composites Part B: Engineering, 2024, 287:- [27]HEIMBS S, HOFFMANN M, WAIMER M, et al.Dynamic testing and modelling of composite fuselage frames and fasteners for aircraft crash simulations[J].International Journal of Crashworthiness, 2013, 18(4):406-422 [28]LIU XC, JIANG H Y, REN Y R, et al.Effects of global and local ply-reinforcements of critical components on crush performances of 2D tri-axially braided CFRP J-shaped fuselage frame[J].International Journal of Crashworthiness, 2020, 27(3):759-771 [29]MOU H L, ZHAO Y M, FENG Z Y.Comparative analysis of the bending crashworthiness of CFRP, metal and CFRP/metal hybrid C-frames[J].Aerospace Science and Technology, 2025, 165:- [30]WAIMER M, KOHLGRüBER D, KECK R, et al.Contribution to an improved crash design for a composite transport aircraft fuselage-development of a kinematics model and an experimental component test setup[J].CEAS Aeronautical Journal, 2013, 4:265-275 [31]STURM R, HEIECK F.Energy absorption capacity of braided frames under bending loads[J].Composite Structures, 2015, 134:957-965 [32]高宾华, 任毅如.编织复合材料机身隔框的冲击动力学特性[J].复合材料学报, 2017, 34(8):1780-1787 [33]MOU H L, SU X, XIE J, et al.Parametric analysis of composite sinusoidal specimens under quasi-static crushing[J].The Aeronautical Journal, 2018, 122(1254):1244-1262 [34]ROZYLO P, DEBSKI H, Failure study of compressed thin-walled composite columns with top-hat cross-section[J].Failure study of compressed thin-walled composite columns with top-hat cross-section[J].Thin-Walled Structures, 2022, 180:- [35]HEIMBS S, HELLER S, MIDDENDORF P, et al.Low velocity impact on CFRP plates with compressive preload: Test and modelling[J].International Journal of Impact Engineering, 2009, 36:1182-1193 [36]惠旭龙, 牟让科, 白春玉, 等.钛合金动态力学性能及本构模型研究[J].振动与冲击, 2016, 35(22):161-168
文章导航

/