三角翼机翼摇滚主动控制多学科耦合数值模拟

Multidisplinary interactions numerical simulation for active control of delta wing rock

细长机身和大后掠机翼气动构型的飞行器大攻角飞行时,由于缺少横向阻尼,易发生以绕体轴滚转振动为主的摇滚运动,飞行安全受到严重威胁。针对三角翼摇滚问题,采用动网格技术,建立了气动、运动和控制多学科耦合的数值模拟方法。通过耦合非定常Navier-Stokes方程、刚体运动方程和经典控制律,采用控制面差动偏转的方式对三角翼摇滚主动控制过程进行了数值模拟,并分析了不同控制状态下三角翼受控滚转的运动特性。在来流马赫数为0.3的条件下,实现了80°后掠三角翼摇滚现象的有效控制。

Modern aircraft with delta wings and small thickness ratios of inner fuselages often fly at high angles of attack, resulting in wing rock motion due to the lack of lateral damp, which seriously threaten the flight safety. A multidisciplinary numerical simulation method has been established to control the wing rock motion, integrating aerodynamics, flight mechanics and flight control characteristics. The active control progress of delta wing with trailing-edge control surfaces is investigated by solving unsteady Navier-Stokes equations on moving grids and rigid body motion functions with one degree of freedom under classical control laws. Furthermore, the kinetic characteristics of the controlled delta wing in different control states are analyzed. The numerical results indicate that the wing rock motion of the 80° sweep delta wing has been controlled effectively with the inlet Mach number of 0.3.