摘要
现代亚音速飞机的柔性较大,其静气动弹性对载荷分布有重要影响。为此,基于全机地面共振试验结果建立机翼的结构有限元模型,利用颤振风洞试验测量的弹性变形对基于偶极子格网法的定常气动力进行下洗修正,建立了直机翼的静气动弹性模型,分析了静气动弹性对直机翼飞行载荷分布的影响。结果表明:静气动弹性使直机翼存在"弹性加载"效应。直机翼结构设计时,应考虑静气动弹性引起的飞行载荷分布问题。
Static aeroelastic is a very influential factor on flight load distribution because of the high configuration flexibility of subsonic aircraft. The finite element model of wing was present- ed based on the results of global vibration test. The correction fac- tors to downwash were obtained by using elastic deformation of model wind tunnel test and the steady aerodynamic influence ma- trix based on double lattice method was corrected. The influence of wing static aeroelastic to flight load distribution was studied by the aeroelastic model. Results show that the flight load of wing was in- crescent because of the aeroelastic effect. The flight load distribu- tion of unswept-wing under static aeroelastic should be considered at the structural design stage.
出处
《机械设计》
CSCD
北大核心
2014年第4期93-96,共4页
Journal of Machine Design
关键词
直机翼
静气动弹性
飞行载荷
unswept-wing
static aeroelastic
flight load
