飞翼无人机进舰下滑纵向固有模态特性研究

Intrinsic Mode Characteristic Research on the Flying-Wing UAV During Carrier Landing

针对舰载飞翼布局无人机与常规布局飞行器不同的气动外形,建立无人机飞行状态下附近流场的网格模型,并计算了该型无人机的气动参数。基于插值函数计算得出该型无人机的升力系数、阻力系数和俯仰力矩系数对于迎角变化的曲线。建立纵向小扰动方程进行仿真计算,求解出该型无人机在进舰下滑状态时的固有模态特性。计算结果表明,该模型在配平条件下可用于舰载飞翼布局无人机的着舰气动适配性研究。

A grid model of flow field around UAV flying was established for the flying-wing configuration different from the conventional configuration aerodynamic shape, and the UAV aerodynamic parameters could be calculated. The lift coeffi- cient, drag coefficient and pitching moment coefficients for angles of attack curve of the UAV by was got the interpolation function. The equation of longitudinal direction small-disturbance motion could be simulated, and the natural mode fea- ture of the flying-wing UAV was solved when the UAV was during in carrier landing. The results of the calculation showed that the model could be used in a simulation research of a carrier landing pneumatic suitability of carrier flying-wing UAV Under trimmed condition.