考虑螺旋桨滑流影响的垂尾飞行载荷设计  

Flight Loads Design of Vertical Tail under Influence of Propeller Slipstream

作　　者：荆志伟[1] 侯宗团 唐朕 肖启之 

机构地区：[1]中航工业第一飞机设计研究院,陕西西安710089

出　　处：《航空计算技术》2016年第2期76-79,共4页Aeronautical Computing Technique

摘　　要：依据CCAR-25部偏航机动的设计准则,研究了螺旋桨滑流对垂尾载荷设计的影响。以T型尾翼布局、桨叶右旋的某支线客机为例,分析了螺旋桨滑流对飞机气动特性的影响:拉力系数越大,则滑流对飞机侧向力系数和偏航力矩系数的影响越大;在负侧滑时,滑流对飞机气动特性数据的影响显著;正侧滑时,滑流对飞机气动特性的影响较小。基于飞行力学六自由度非线性微分方程,开展了有/无滑流影响情况下偏航机动仿真和垂尾载荷设计。结果表明:螺旋桨滑流使得飞机的响应幅值增大,算例飞机的垂尾侧向力、弯矩和扭矩限制载荷分别增大5.21%、8.21%和4.85%。According to the yaw maneuver criteria in CCAR - 25, the influence of propeller slipstream on vertical tail＇s flight loads design was studied. Taking the regional aircraft with T- Tail and clockwise pro- pellers as an example, the effect of propeller slipstream on aerodynamic characteristic was analyzed. The greater the thrust coefficient is, the greater the influence of propeller slipstream on the aerodynamic char- acteristic is. The influence of the propeller slipstream on the aerodynamic characteristic is significant when sideslip angle is minus, and the influence is relatively small while sideslip angle is positive. Based on the 6 degree- of- freedom nonlinear differential equations of flight dynamics, the yaw maneuver simulation and vertical tail＇ s loads design with and without slipstream influence were carried out. The results indicate that the aircraft＇s response amplitude ascends after taking propeller slipstream influence into account, and the lateral load,root bending moment and torsion moment increase by 5.21% ,8.21% and 4.85% , re- spectively.

关 键 词：垂尾 飞行载荷 螺旋桨 滑流 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程] V211.44