某中央翼盒对飞行载荷实测的影响

使用应变法测量某具有中央翼盒平尾的飞行载荷时，在地面校准试验中发现：左翼面载荷可使右翼面根部应变计有较大的响应，反之亦然。该现象可使根部载荷测量精度下降。分析了中央翼盒对根部载荷测量影响的机理，给出了一种考虑异侧载荷影响的载荷方程建立方法，讨论了不同类型剪力载荷方程对异侧载荷影响的敏感性，并将修正前后的方程应用于飞行载荷实测。结果发现：本文方法一定程度上可提高根部载荷方程的精度；对上述平尾结构，由两个剪力一个弯矩组建的载荷方程对异侧载荷影响不敏感，修正前后实测的飞行载荷差异在5.7%之内，由两个剪力和两个弯矩组建的载荷方程对异侧载荷影响敏感，修正前后实测的飞行载荷差异达到78.6%。

Effect of central wing on root flight load measurement of certain airfoil

For flight load measurement using strain gage of certain horizontal stabilizer with central wing, it has been found that right root strain response is large when loading left airfoil in ground calibration test, and vice versa, which could lower flight load measurement accuracy. The mechanism of central wing effects on root flight load measurement was analyzed. Also a method of eliminating opposite load effects on flight load measurement was proposed. Further, the sensitivity of different type load equations to opposite load effects was discussed. Moreover, the corrected load equations were used to measure flight loads. The results show that for above horizontal tail with central wing,the proposed method in this paper could improve root load equation accuracy. The built shear load equation using 2 shear and 1 bending-moment strain bridges is not sensitive to opposite load effects where the measured flight shears through load equations before and after correction have differences under 5.7%, while the built shear load equation using 2 shear and 2 bending-moment strain bridges is sensitive to opposite load effects where the measured flight shear using load equations before and after correction have large differences of 78.6%.