本文介绍了一种升降副翼铰链力矩实验技术研究的进展情况。采用弹簧片铰链力矩天平所作的标模实验表明,所测升降副翼的铰链力矩特性与文献值基本一致,各导数值随 M 数的变化趋势合理,天平工作性能稳定,测量精度较高,实验技术是成功的。 This paper introduces the progress of research on a kind of lifting aileron hinge moment experiment technique. The model experiments using the spring hinge moment scale show that the hinge torque characteristics of the lifting aileron are basically the same as those in the literature. The trend of the derivative values ​​with M numbers is reasonable, the working performance of the balance is stable and the measurement accuracy is high. The experiment Technology is successful.