针对传统的载荷校准约束方法影响有起落架布置的翼身整体结构机翼根剖面载荷测量的问题，提出了一种适用于该结构形式的机翼载荷实测方法。首先，分析地面载荷校准时主起落架载荷变化对机翼根部测载剖面应变电桥响应的影响，提出了一种主动约束方法来模拟空中飞机机翼真实受载状态。其次，采用主动约束和传统的起落架约束方法进行机翼载荷校准对比试验，通过对试验数据进行分析，分别建立了2种约束方法的飞行载荷方程，表面上2种方法的地面检验误差均在3%以内，满足一般的工程误差要求。最后，选取对称拉起机动试飞状态，对2种约束方法的机翼飞行载荷测量结果进行分析研究，验证了有起落架布置的翼身整体结构机翼载荷测量方法的有效性，并给出了传统的起落架约束方法载荷测量误差大的原因。

The traditional load calibration constraint method affects the measurement of wing root load on the wing-body integrated structure with landing gear layout. In this paper， a wing load measurement method suitable for this structure is proposed. Firstly， the impact of the change in main landing gear load during ground load calibration on the strain bridge response of the wing root load measurement section is analyzed. An active constraint method is proposed to simulate the actual loading state of the aircraft wing in the air. Secondly， comparative test of wing load calibration is conducted using the active constraint and the traditional landing gear constraint methods. By analyzing the test data， the flight load equations for the two constraint methods are established. The ground checking error of both methods is within 3%， which meets the general requirement for engineering errors. Finally， the symmetrical pull-up maneuver flight test state is selected to verify the effectiveness of the wing load measurement method for the wing-body integrated structure with landing gear layout， and the reason for the large error in load measurement using the traditional landing gear constraint method is also given.