北京航空航天大学学报2026，Vol.52Issue(3)：736-743,8.DOI:10.13700/j.bh.1001-5965.2023.0853
飞机复合材料结构载荷测量的温度修正方法
Temperature correction method for load measurement of aircraft composite structures
李俊 1李文龙 1高腾龙 1李亚南 1刘敬礼1
作者信息
摘要
Abstract
In view of the serious influence of temperature on load measurement results of aircraft composite structures,the influence mechanism of temperature on load measurement of aircraft structure was analyzed,and a temperature correction model including the relative response coefficient and thermal output of the strain bridge is established,and the general relation models of relative response coefficient and thermal output with structural temperature are given respectively.These relation models are verified by the temperature test and the temperature-load combined test of composite laminate coupons and the wing box test component.The findings indicate that,when the adhesive's temperature characteristics are met,the relationship between the thermal output and the structural temperature change is a cubic polynomial with zero intercept,and the reciprocal of the relative response coefficient is a power function of the dimensionless structure temperature.By using this technique,the flight measurement results of an aircraft's composite wing structure load can be corrected.The maximum relative change of the pressure center following modification is 30.68%,which greatly increases load measurement accuracy and yields trustworthy data for aircraft flight load verification.关键词
飞机复合材料结构/载荷测量/应变电桥热输出/应变电桥相对响应系数/温度试验/温度-载荷组合试验Key words
aircraft composite structures/load measurement/thermal output of strain bridge/relative response coefficient of strain bridge/temperature test/temperature-load combined test分类
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李俊,李文龙,高腾龙,李亚南,刘敬礼..飞机复合材料结构载荷测量的温度修正方法[J].北京航空航天大学学报,2026,52(3):736-743,8.
