Tailoring Failure Interactions for Validation Testing of Composite Laminate Progressive Failure Models

被引:1
作者
Borwankar, Pranav [1 ]
Venkataraman, Satchi [2 ]
机构
[1] Virginia Polytech Inst & State Univ, Dept Aerosp Engn, Blacksburg, VA 24060 USA
[2] San Diego State Univ, Kevin T Crofton Dept Aerosp & Ocean Engn, San Diego, CA 92182 USA
关键词
Design of Experiments; Composite Laminates; Continnum Damage Mechanics; Verification and Validation; Structural Optimization; Bolted Joints; Progressive Failure; Mode Interaction; Sensitivity Analysis; Probabilistic Design; CONTINUUM DAMAGE MODEL; PART II; JOINTS; STRENGTH; OPTIMIZATION; STRESSES; FRACTURE; HOLE;
D O I
10.2514/1.J063540
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Efficient validation of numerical models for predicting failures in composite structures is imperative due to the intricate nature of such failures. The multifaceted aspects, including multimodal, multiscale, and interactive factors, pose challenges in the calibration and validation of models. Constraints in cost and time often limit the comprehensive testing required for model validation across diverse failure response scenarios. This study proposes an optimal test selection approach, building upon previous insights that optimizing measures derived from progressive failure responses can unveil failure mode interactions sensitive to stochastic variations. Calibration designs should minimize interaction while maximizing sensitivity to calibration parameters, whereas validation models must encompass varied interactions to understand predictability limits. However, optimizing progressive failure analyses for composites is computationally intensive. A straightforward design of experiments exploration is demonstrated here, focusing on efficiently identifying designs sensitive to stochastic effects, which reveal mode interactions and suitability for calibration/validation. This method is exemplified using computational models for composite bolted joints subjected to pin-bearing loads, showcasing their intricate failure modes. Designs displaying high sensitivity to parameter changes offer insights into failure mechanisms, aiding in model validation and enhancement. Thus, employing such critical designs as test cases can refine numerical models, resulting in more accurate representations of complex failure behaviors in diverse composite components.
引用
收藏
页码:790 / 805
页数:16
相关论文
共 35 条
  • [1] Effect of clamping force on the delamination onset and growth in bolted composite laminates
    Atas, A.
    Mohamed, G. F.
    Soutis, C.
    [J]. COMPOSITE STRUCTURES, 2012, 94 (02) : 548 - 552
  • [2] Prediction of progressive failure in multidirectional composite laminated panels
    Basu, Shiladitya
    Waas, Anthony M.
    Ambur, Damodar R.
    [J]. INTERNATIONAL JOURNAL OF SOLIDS AND STRUCTURES, 2007, 44 (09) : 2648 - 2676
  • [3] BAZANT ZP, 1984, J ENG MECH-ASCE, V110, P1666
  • [4] Borwankar P., 2018, P AM SOC COMP 33 TEC, DOI [10.12783/asc33/25930, DOI 10.12783/ASC33/25930]
  • [5] A progressive damage model for mechanically fastened joints in composite laminates
    Camanho, PP
    Matthews, FL
    [J]. JOURNAL OF COMPOSITE MATERIALS, 1999, 33 (24) : 2248 - 2280
  • [6] STRENGTH OF MECHANICALLY FASTENED COMPOSITE JOINTS
    CHANG, FK
    SCOTT, RA
    SPRINGER, GS
    [J]. JOURNAL OF COMPOSITE MATERIALS, 1982, 16 (NOV) : 470 - 494
  • [7] Experimental results of quasi-static testing for calibration and validation of composite progressive damage analysis methods
    Clay, Stephen B.
    Knoth, Philip M.
    [J]. JOURNAL OF COMPOSITE MATERIALS, 2017, 51 (10) : 1333 - 1353
  • [8] Collings T.A., 1977, COMPOSITE, V8, P43
  • [9] Stress analysis of single-bolt, single-lap, countersunk composite joints with variable bolt-hole clearance
    Egan, B.
    McCarthy, C. T.
    McCarthy, M. A.
    Frizzell, R. M.
    [J]. COMPOSITE STRUCTURES, 2012, 94 (03) : 1038 - 1051
  • [10] FATIGUE FAILURE CRITERIA FOR UNIDIRECTIONAL FIBER COMPOSITES
    HASHIN, Z
    [J]. JOURNAL OF APPLIED MECHANICS-TRANSACTIONS OF THE ASME, 1981, 48 (04): : 846 - 852