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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2021, Vol. 42 ›› Issue (5): 524239-524239.doi: 10.7527/S1000-6893.2020.24239

• Article • Previous Articles     Next Articles

Infrared radiation characteristics of CFRP laminate surface under compressive fatigue load

YANG Zhengwei1,2, ZHAO Zhibin1, LI Yin3, SONG Yuanjia3, KOU Guangjie1, LI Lei4, CHENG Pengfei4   

  1. 1. School of Missile Engineering, Rocket Force University of Engineering, Xi'an 710038, China;
    2. School of Mechanical Engineering, Xi'an Jiaotong University, Xi'an 710049, China;
    3. China Aerodynamics Research and Development Center, Mianyang 621000, China;
    4. Aircraft Strength Research Institute, Xi'an 710065, China
  • Received:2020-05-18 Revised:2020-06-16 Online:2021-05-15 Published:2020-07-27
  • Supported by:
    National Natural Science Foundation of China (51575516); China Postdoctoral Science Foundation (2019M650262); Natural Science Foundation of Shaanxi Province (2020 JM-354); Aeronautical Science Foundation of China (201803U8003)

Abstract: To explore the damage evolution rule of impact-damaged CFRP laminates under cyclic alternating load, we studied the surface infrared radiation characteristics of damaged CFRP laminates during fatigue based on the thermodynamic coupling effect. Using the infrared thermal image method, we analyzed the heat map sequences and temperature data of the damaged CFRP laminated plate during fatigue with the pressure-pressure fatigue test simulating the alternating load. Results show that with the increase of fatigue times, the damage evolves along the vertical direction of the fatigue load, the color of the hot spot gradually deepens, the initial impact damage slowly evolves into an elliptical shape, and finally a "sharp point" appears at the end of the hot spot. The maximum surface temperature difference of the specimen as a whole shows the rule of "fast rise-slow rise-fast rise", finally leading to a jump. The "sharp point" on the hot spot and the maximum surface temperature difference jump can be regarded as the precursor of structural fatigue failure. When the CFRP laminates are damaged, the maximum surface temperature difference is mainly related to the types of the fiber and the matrix, while the laying-out mode of the specimens has no significant influence on the types of fiber matrix. The study reveals the damage evolution law of CFRP laminates under fatigue load after impact, laying a foundation for the residual fatigue life evaluation and damage tolerance design of aircraft composite structures.

Key words: CFRP, constant amplitude fatigue tests, infrared thermal imaging, fatigue life, heat map sequences

CLC Number: