民用飞机反尾旋研究与尾旋风洞试验

Anti-Spin Research and Spin Tunnel Tests for Civil Aircraft

为了研究某民用飞机A采用舵面组合偏转法的尾旋改出特性,对大攻角静态测力试验结果进行了详细分析,并利用美国NASA兰利研究中心所研发的TDPF～[(I_x-I_y)/mb^2]判据法对飞机的尾旋改出特性进行了评判。通过尾旋风洞试验对采用舵面组合偏转法飞机尾旋改出特性进行了试验验证,试验结果表明反舵推杆法对常规布局运输飞机改出尾旋效果最佳。此外,为了提高飞机的试飞安全,需要加装反尾旋伞系统,而研制一款合适的反尾旋伞对保证飞机试飞安全是至关重要的。通过使用国际上公开的研制反尾旋伞资料中所提供的方法研制了不同面积大小,不同伞绳长度的反尾旋伞,并通过尾旋风洞试验检验了这些反尾旋伞的效果。结果显示:随着反尾旋伞面积的增大,改出效果越好;中等反尾旋伞伞绳长度改出尾旋效果最佳。

It is necessary to investigate a civil aircraft spin recovery characteristics by using multiple control surface deflection. Normal wind tunnel static model force measurement results were detailed analyzed firstly. TDPF～[（ Ix-Iy）/mb^2]method which was studied by NASA Langley research center was also used to judge the aircraft spin recovery characteristics. A dynamic similarity scaled model was tested in spin tunnel,the best spin recovery action was found,that is to reverse rudder and forward stick. Furthermore,to increase the safety of aircraft flight test,it is also necessary to add an anti-spin parachute system,so it is important to design an appropriate anti-spin parachute. Based on the open information around the world,several anti-spin parachutes with different size and different rope length were designed,and the effect of these anti-spin parachutes was demonstrated by spin tunnel tests. The results show that the larger the parachute size is,the better the recovery effect could be,and middle length rope should be considered as the best results.