为了研究金属材料在疲劳载荷下的温度变化，采用红外热像系统对高周疲劳载荷下6061－T6铝合金的温度演化进行分析，用热像图对疲劳裂纹尖端的塑性区进行测量．结果显示，疲劳加载作用下，循环次数达到107次时6061－T6铝合金试样表面温度的变化分为四个阶段：初始温升阶段、温度缓降阶段、温度二次缓慢上升阶段和温度快速上升阶段．结合热弹性理论、铝合金塑性变形的微观机制分析并预测疲劳载荷下温度的演化和宏观裂纹扩展时裂纹尖端塑性区域大小．宏观裂纹开始扩展时，裂纹尖端的塑性区域可达3．6 mm2，红外热像仪测得结果为3．46 mm2，测试结果与理论结果吻合．
The temperature evolution of 6061-T6 aluminum alloy under high cyclic fatigue loading was investigated by infrared thermography, and the plastic zone at crack tip was measured afterward by thermograph. The results indicated that four stages of temperature profiles were recorded when loaded up to 107 cycles:an initial increasing stage, the gradual decreasing stage, the gradual increasing stage, and the abruptly rising stage. The thermoelastic theory and micromechanism of aluminum alloy plastic deformation were used to explain and predict the temperature evolution under fatigue loading and the plastic region at crack tip during macrocrack propagating. The plastic region at crack tip was predicted to be 3.46 mm2 , while the theoretical result was 3.6 mm2 .
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