飞机水平尾翼水滴撞击特性及防冰热载荷计算  

Impingement characteristics and anti-icing heat load calculation of certain tailplane

作　　者：赵勇[1,2] 杨新亮[3] 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]中国航空工业集团公司机电系统有限公司,北京100028 [3]中国飞行试验研究院航空电子与机载设备飞行试验技术研究所,西安710089

出　　处：《航空动力学报》2012年第11期2401-2407,共7页Journal of Aerospace Power

摘　　要：建立了利用欧拉法求解水滴撞击特性的方法,并基于Messinger质量和能量守恒方程建立了热载荷计算模型,以某型飞机三维水平尾翼为研究对象,展开了撞击特性和热载荷的计算.结果显示水平尾翼的局部水收集系数极值从翼根到翼尖逐渐增加,不同截面水滴收集系数的分布为设计防冰系统范围提供了依据.驻点附近及机翼上、下表面各存在一个热载荷较大的区域,进而确定该尾翼电加热防冰分为3个区域:中间连续加热区和上、下表面驻点附近的各一个间断加热区.To obtain water droplet impingement characteristics by Eulerian method, a math model was built. Also, a computational model of the heat load was established, which was based on the Messinger conservation of mass and energy. Focusing on the three- dimensional tailplane of a certain aircraft, the calculation of impingement characteristics and heat load was performed. It was found that the local water collection efficiency of tailplane raised from wing root to wing tip. The water local collection efficiency distributions of dif- ferent slices provided a basis for the design of anti-icing system region. The results show that heat load is higher near the stagnation point, top airfoil and lower airfoil. It is conclu- ded from the results that three electricity heating anti-icing regions are designed on the tail- plane： the middle continuous heating region and the intermittent heating regions near the stagnation on the top airfoil and the lower airfoil.

关 键 词：欧拉方法 尾翼 撞击特性 热载荷 电加热防除冰系统 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]