飞机多天平部件测力风洞试验模型优化设计方法

摘要

By analyzing the inlfuence of the gap between the component and the model about aircraft components force test, an optimization design method on the gap was presented. In order to minimize the inlfuence of the gap, a labyrinthic groove was used on the gap. In Contrast to the older design method, the result of wind tunnel test shows that the lift measurement precision improves 8 percent, and the precision of side force improves 3 percent.%对飞机多天平部件测力试验中测力部件与模型间缝隙的影响进行了分析，提出了一种优化飞机风洞试验模型测力部件缝隙的方法。优化时，将缝隙设计成迷宫槽形式，使气流不能够直接通过该缝隙从而减小了窜流影响。采用该优化设计方法的某飞机结果与未采用优化设计方法的类似构型飞机结果相比，升力准确性提高8%，侧向力准确性提高3%。