高平尾布局民用飞机平尾非对称载荷研究  

Asymmetric load of horizontal tail in civil aircraft with T-tail configuration

作　　者：黄一桓 尼早[1] 宋鑫 HUANG Yihuan;NI Zao;SONG Xin(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《民用飞机设计与研究》2024年第1期34-39,共6页Civil Aircraft Design & Research

摘　　要：民用飞机高平尾布局可减小平尾处的下洗与速度阻滞,具有更高的平尾效率,同时高平尾的非对称载荷会构成垂尾载荷的严重情况。提出高平尾飞机侧滑工况下平尾升力的理论计算公式,得到了平尾升力随侧滑角变化的计算方程。然后,采用CFD方法对非对称侧滑来流下的高平尾载荷进行了仿真分析,验证了所提出计算公式的正确性。进一步结合理论计算方程和全机CFD流场仿真结果,确定了不同变量对高平尾非对称载荷的影响程度,可为高平尾飞机的非对称载荷设计提供设计依据。The T-tail configuration in civil aircraft can reduce downwash and speed inhibition at the horizontal tail,and has higher efficiency.However,this configuration also leads to can constitute a serious asymmetric load situa-tion on the vertical tail.This paper proposes a theoretical calculation formula for the horizontal tail lift under side-slip conditions about T-tail aircraft,obtaining an equation describing the variation of the horizontal tail lift with sideslip angle.Subsequently,the CFD method is employed to simulate and analyze the asymmetric load on the T-tail under crossflow,verifying the accuracy of the proposed calculation formula.Furthermore,by combining the theoretical calculation equation with the results of CFD flow field simulation of the whole aircraft,the impact of dif-ferent variables on the asymmetric load of the T-tail is determined,providing a basis for the design of asymmetric load for T-tail aircraft.

关 键 词：飞行载荷 高平尾 侧滑 非对称载荷 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]