基于飞行实测的大型飞机机翼载荷静气弹修正  

Static aeroelastic correction of large aircraft wing load based on flight measurement

作　　者：张建刚 余建虎 牛孝飞 赵冬强 ZHANG Jiangang;YU Jianhu;NIU Xiaofei;ZHAO Dongqiang(The First Aircraft Institute of the Aviation Industry Corporation of China,710089 Xi'an,China;Chinese Flight Test Establishment,710089 Xi'an,China)

机构地区：[1]航空工业第一飞机设计研究院,西安710089 [2]中国飞行试验研究院,西安710089

出　　处：《应用力学学报》2023年第6期1263-1269,共7页Chinese Journal of Applied Mechanics

摘　　要：大型飞机结构弹性会显著的影响到机体的载荷大小及分布,准确计算结构弹性引起的载荷变化对提高飞机设计水平具有重要意义。首先给出了一种机翼气动载荷静气弹理论修正方法,该方法应用工程梁理论计算机翼变形,应用涡格法计算变形引起的气动力增量,然后进行迭代直至收敛,用升力面理论对NACA-TN3030报告中的升力线理论进行了改进提高。通过风洞试验证明了该理论方法的准确性。在飞行试验中测量得到了机翼变形和飞行参数两方面的数据,分别以这两方面的数据为输入各自进行弹性修正计算,两种途径得到的结果相互验证,修正结果吻合较好,经过载荷修正后翼根弯矩降低了大约3%,该方法易于在工程中推广使用,对于减轻机翼结构重量有显著意义。The structural elasticity of large aircraft will significantly affect the load size and distribution of the airframe.It is important to calculate the load variation caused by structural elasticity accurately for improving the design level of aircraft.In this paper,a modified method of aeroelastic theory for aerodynamic load of wing is presented,which uses the theory of engineering beam to calculate the aerodynamic increment caused by the deformation,then iterates to converge,and improves the lift line theory in NACA-TN3030 report by using the theory of lift surface.The accuracy of the method is proved by wind tunnel test.In flight test,the data of wing deformation and flight parameters are measured,and the elastic correction calculation is carried out respectively with the data of these two aspects as input.The results of the two methods are verified by each other,and the correction results are in good agreement with each other.After load correction,the bending moment of wing root is reduced by about 3%.This method is easy to be popularized in engineering.It is significant to lighten the weight of wing structure.

关 键 词：机翼载荷 弹性修正 风洞试验 飞行试验 

分 类 号：V215.1[航空宇航科学与技术—航空宇航推进理论与工程]