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中文摘要：
针对某连结翼布局无人机,采用松耦合方式,耦合计算流体力学（CFD）和计算结构动力学（CSD）对其静气动弹性进行了计算研究;CFD求解模块采用非定常雷诺平均N-S方程,CSD模块采用直接积分法求解结构动力学方程,在时域内推进求解,收敛后获得静气弹计算结果。研究表明：连结翼静气弹变形后,前翼发生负扭转,后翼发生正扭转,前翼升力损失,后翼升力增加;无论是刚体构型还是静气弹变形后,前翼和后翼的展向升力系数分布规律均存在很大差异;静气弹变形使得连结翼升力线斜率增大4.3%,纵向静稳定性导数增大145.8%,但会带来较大的低头力矩增量;与单独前翼对比表明,连结翼后翼大大限制了前翼的负扭转变形,使得升力损失降低为单独前翼的21%;与单独后翼对比表明,连结翼前翼大大限制了后翼的正扭转变形,降低了后翼扭转发散的风险;研究结果揭示了连结翼布局特殊的静气动弹性特性,对连结翼的气动/结构设计具有一定的工程指导价值。
英文摘要：
With a joined wing configuration UAV as the study object,static aeroelasticity was numerically investigated by coupling CFD and CSD using loosely-coupled algorithm. CFD module adopts unsteady Reynolds Averaging N-S equations and CSD module adopts direct integration method to solve structural dynamic equation. Advancing solution in time domain,the static aeroelastic results are then obtained after convergence. Research shows that after static aeroelastic deformation of joined wing,the front wing twists negatively while the rear wing positively; the lift of front wing decreases while rear wing increases; the spanwise lift coefficient distribution differs greatly between front wing and rear wing; after static aeroelastic deformation,the lift curve slope and the longitudinal static stability derivative both increase,but large increment of nose down moment is produced; compared to single front wing,rear wing of joined wing restricts the deformation of front wing largely,leading to the loss of lift far less than single front wing; compared to single rear wing,front wing of joined wing restricts the positive torsional deformation of rear wing largely,which reduces the risk of divergence of rear wing. The results revealed the particular aeroelastic characteristics of joined wing configuration,which is to be of certain value to the aerodynamic and structural design of joined wing.
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