复合材料机翼载荷的地面标定方法

Ground calibration method of composite wing load

为测量复合材料机翼载荷,提升飞机机体结构的安全性,以复合材料机翼为研究对象,基于机翼载荷-电桥响应方程的基本原理,采用回归分析逐步后退法确定机翼载荷方程系数,给出了机翼载荷方程分析方法。结果表明,双梁载荷方程可以较为精确地计算双梁承受的实际载荷,载荷方程的计算最大误差均小于2.52%。复合材料机翼载荷方程可较为精确地计算复合材料机翼承受的实际载荷,载荷方程的计算最大误差均小于1.7%,验证了载荷方程标定方法的正确性。

This paper aims to measure the composite wing load and improve the safety of aircraft fuselage structure.Based on the basic principle of the construction of the wing load-bridge response equation,the study,taking the composite wing as the research object,determines the coefficients of the wing load equation by using the regression analysis step-by-step backward method,and gives the analyzing method of wing load equation.The results show that the double-beam load equation can calculate the actual load borne of the double-beam more accurately,and all the maximum calculating errors of the load equation are less than 2.52%.The composite wing load equation can calculate the actual load of the composite wing more accurately,and the maximum error of the load equation is less than 1.7%,which verifies the correctness of the calibration method of the load equation.