柔性体飞翼无人机着舰动力学仿真研究

Research on the Dynamics Simulation of Landing Ship of the Flexible Flying Wing UAV

为研究将飞翼无人机机体考虑为柔性体对无人机气动特性和着舰过程的影响,采用双向流固耦合的方式计算气动力、结构重心和惯性矩,然后建立飞翼无人机的着舰动力学模型,分别对将飞翼无人机考虑为刚体和柔性体时的动力学模型进行仿真。算例表明:将飞翼无人机考虑为柔性体后,其着舰滑跑时间增加了大约0.5秒,着舰滑跑距离增加了大约14.27米,相对于将无人机考虑为刚体时,着舰滑跑时间和着舰滑跑距离分别增加了14.3%和21.2%。结果表明在将无人机考虑为柔性体后对拦阻着舰的性能有很大影响,因此在精确仿真时不能忽略无人机柔性体对仿真结果的影响,在研发舰载无人机的过程中应当对机体柔性产生的影响给予足够重视。

To order to research on the influence of the aerodynamic characteristics of UAV and the landing process,when the flying wing UAV body is considered as a flexible body. Calculation of aerodynamic force, gravity center of gravity and moment of inertia by two way fluid solid coupling. Then a dynamic model of landing a flying wing UAV is set up. When the flying wing UAV is simulated by considered as rigid and flexible body respectively. When the flying wing UAV is considered as a flexible body, the landing taxiing time increased by about 0. 5 seconds, the landing roll distance increased about 14. 27 meters. Compared to the UA~ is considered as a rigid body, the land- ing taxiing time and landing distance were respectively increased by 14. 3% and 21.2%. The results indicate that the UAV is considered as a flexible body, which has a great influence on the performance of the landing, so it can not be ignored in the simulation. The study has some significance on carrierbased aircraft design considering the effect of flexible deformation during landing.