摘要
高空长航时大展弦比飞翼布局无人机在气动载荷的作用下所产生的较大的弹性变形,显著地改变了全机的升阻特性及静稳定性,常规的刚性飞机假设已不能满足其总体气动特性分析的精度要求。基于CFD/CSD松耦合的方法研究了大展弦比飞翼布局无人机的静气动弹性特性问题,结果表明:静气动弹性效应将显著降低这类飞机的升阻特性,并显著增加原设计配平巡航点的俯仰力矩;滚转静稳定性导数可提高41.7%,同时改善了刚体外形设计中存在的纵向静不稳定现象;局部气动载荷显著地向翼根转移,从而有利于结构设计。
High altitude long endurance high-aspect ratio flying wing will undergo large deformation,which will significantly change characteristics of lift and drag as well as static stability. Therefore,conventional rigid aircraft assumption cannot meet the accuracy requirements of the aerodynamic analysis of this type of aircraft. In this paper,based on CFD / CSD coupling,static aeroelasticity of high aspect ratio flying wing was studied. The results show that static aeroelastic effect will significantly reduce the lift drag ratio and increase pitching moment at designed cruise trimming point; On the other hand,lateral static stability derivative will be increased by 41. 7%,and the longitudinal instability inherent in the flying wing will be improved. The aerodynamic loads move towards the wing root after aeroelastic deformation,which is advantageous to the structural design.
出处
《飞行力学》
CSCD
北大核心
2016年第1期40-45,共6页
Flight Dynamics
