T型尾翼布局的垂尾载荷测量技术

针对T型尾翼布局下平尾影响垂尾载荷的特点，提出了一套适用于T型尾翼布局的垂尾载荷实测试飞方法。该方法通过分析平尾载荷对垂尾的影响，设计平尾非对称校准加载工况，将其引入垂尾载荷方程建模，并使用该垂尾载荷方程测量了某型飞机型号合格审定试飞的垂尾飞行载荷。试验结果表明，载荷方程测量误差由5.3%降低到3.14%，平尾不对称弯矩载荷对垂尾弯矩影响显著，偏航机动严重受载状态时可达到垂尾弯矩的57.6%，滚转机动严重受载状态时可达到垂尾弯矩的61.9%。

Measuring technology for vertical fin load of T-shaped empennage layout

Considering that the lower horizontal stabilizer set on the T-shaped empennage affects the load of the vertical fin, a method for measuring the vertical fin load of the T-shaped empennage in the actual flight test is proposed. By analyzing the effect of the horizontal stabilizer load on the vertical fin, an asymmetric calibration loading mode for the horizontal stabilizer is designed, and is introduced into the vertical fin load equation modeling. The equation is used to measure the vertical fin flight load of a certain type of aircraft in the type certificate flight test. The flight test results show that the measuring error of the load equation is decreased from 5.3% to 3.14%, horizontal stabilizer asymmetric bending load has severe effect on bending of the vertical fin, yaw maneuver can reach 57.6% of the bending of the vertical fin when the aircraft is highly loaded, and roll maneuver can reach 61.9% of the bending of the vertical fin when the aircraft is highly loaded.