ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Thermo-electrical Coupling Effect on Tensile and Fatigue Strength of Composite Materials for Aeronautical Application
Received date: 2014-01-07
Revised date: 2014-02-20
Online published: 2014-03-17
Supported by
CAUC Research Foundation (06kym10, 07kym07); Pre-research Major Project of CAUC (3122014P002)
In order to determine the characteristics of electrical conductivity and thermo-electrical coupling effect on the tensile and fatigue strength of carbon fiber reinforced polymer (CFRP) composite laminates, the present paper focuses on two composite materials ([0]8 UD and [45/90/-45/0]s QI)which are prepared for the electrical and thermo-electrical fatigue experiments, direct current (DC) and alternating current (AC) from 1 A to 8 A are injected to the samples, and their temperature field and maximum temperature are monitored simultaneously in order to find itheir effect on the electrical resistance change. A simplified thermo-electrical analysis model is established based on the experimental phenomena and then the experimental results are compared with simulation results and a good agreement is found between them. The model is effective in describing the thermo-electrical phenomena at a steady state of temperature. In the condition of injecting of current, fatigue tests are prepared for different states of samples, the results show that the electrical current—no matter DC or AC or chang the value of current/frequency—has no obvious effect on the fatigue number of cycles, and has no obvious effect on the evolution of fatigue damage, but the temperature will raise while the current increases. Simutaneously, by monitoring the longitudinal resistance, it can be found that at certain loading level the resistance will augment while the number of cyclic increase. This phenomena shows inside of of sample may have some damage accumulating until the fracture of the specimen. Two models considering the relationship between electric resistance and strain based on the experiments are proposed to simulate the experiments, Model-1 is used to calculate the linear stage of strain (εxx≤0.4%) while Model-2 could be better used to simulate the nonlinear stage until the break of samples (εxx>0.4%).
Key words： fuselage skin; composites; thermoelectricity; electric resistance; fatigue
LIN Yueguo , Macro GIGLIOTTI , Marie Christine LAFARIE-FRENOT , Jinbo BAI . Thermo-electrical Coupling Effect on Tensile and Fatigue Strength of Composite Materials for Aeronautical Application[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014 , 35(12) : 3315 -3323 . DOI: 10.7527/S1000-6893.2013.0549
[1] Ma H, Zhang D L, Meng F X, et al. Experiment of electro-thermal anti-icing on a composite assembly[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(8): 1846-1853. (in Chinese) 马辉, 张大林, 孟繁鑫, 等. 复合材料部件电加热防冰性能试验[J]. 航空学报, 2013, 34(8): 1846-1853.
[2] Xia Z H, Okabe T, Park J B, et al. Quantitative damage detection in CFRP composites: coupled mechanical and electrical models[J]. Composites Science and Technology, 2003, 63(2): 1411-1422.
[3] Curtin W A. Stochastic damage evolution and failure in fiber-reinforced composites[J]. Advances in Applied Mechanics, 2000, 36(9): 162-253.
[4] Vavouliotis A, Kostopoulos P V. On the fatigue life prediction of CFRP laminates using the electrical resistance change method[J]. Composites Science and Technology, 2011, 71(18): 630-642.
[5] Schulte K, Baron C. Load and failure analysis of CFRP laminates by means of electrical resistively measurements[J]. Composites Science and Technology, 1989, 36(19): 63-76.
[6] Schulte K, Wittich H. The electrical response of strained and or damaged polymer-matrix composites[C]//Proceedings of ICCM-10th, 1995: 349-356.
[7] Sierakowski R L, Telitchev I Y, Zhupanska O I. On the impact response of electrified carbon fiber polymer matrix composites: effects of electric current intensity and duration[J]. Composites Science and Technology, 2008, 68(15): 639-649.
[8] Snyder D R, Sierakowski R L, Chenette E R, et al. Preliminary assessment of electro-thermo-magnetically loaded composite panel impact resistance/crack propagation with high speed digital laser photography[C]//24th International Congress on High-speed Photography and Photonics, Proceedings of SPIE, 2001: 488-513.
[9] Zhupanska O I, Sierakowski R L. Effects of an electromagnetic field on the mechanical response of composites[J]. Composites Materials, 2007, 41(10): 633-652.
[10] Park J B, Okabe L T. Electromechanical modeling of unidirectional CFRP composites under tensile loading condition[J]. Composites: Part A, 2002, 33(1): 267-275.
[11] Abry J C, Bochard S, Chateauminois A, et al. In situ detection of damage in CFRP laminates by electrical resistance measurements[J]. Composites Science and Technology, 1999, 59(16): 925-935.
[12] Yang J N, Lee L J, Sheu D Y. Modulus reduction and fatigue damage of matrix dominated composite laminates[J]. Composite Structures, 1992, 21(19): 92-100.
[13] Seo D C, Lee J J. Damage detection of CFRP laminates using electrical resistance measurement and neural network[J]. Composite Structures, 1999, 47(10): 525-530.
[14] Gigliotti M, Lafarie M C, Grandidier J C. Development of experimental and modeling tools for the characterization of the thermo-electro-mechanical behavior of composite materials for aircraft applications[J]. Mécanique & Industries, 2011, 12(11): 87-101.
[15] Gigliotti M, Grandidier J C, Lafarie-Frenot M C, et al. Development of experimental and modeling tools for electro-mechanical fatigue tests in composite materials for aircraft applications[C]//The 14th European Conference on Composite Materials, 2010: 99-113.
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