一种折叠翼飞行器动态仿真分析与实验设计

Investigation of a Folding Wing Aircraft Using Dynamic Analysis Simulation and Experimental Method

探讨折叠翼飞行器在飞行过程中的特性,设计一种全尺寸折叠翼飞行器。利用Abaqus软件对该飞行器不同折叠角度状态的模态和动态响应进行分析,结果表明,折叠翼的折叠角度小于90°时,其第3、第4阶模态表现为弯扭组合变形,容易在亚声速条件下发生颤振现象。利用实验方法,设计、制作了试验机并进行试飞,结果发现该试验机后掠角较大,机翼展开后飞行器焦点也相应前移,因此该飞行器在机翼折叠状态下飞行更稳定。

The flight characteristics of a folding wing aircraft arc investigated and on this basis, a full-size folding wing aircraft is designed. The aircraft＇s modes and dynamic characteristics are analyzed by use of CAE software Abaqus. It is shown that when the folding angle is smaller than 90 degree, the wing＇s third and fourth order modes are of＂ bend-torsion-coupled. Thus in the subsonic conditions, the wing would likely be in the flutter state. A folding wing aircraft model is designed. A number of flight characters are obtained by using the model, and it is shown that the focus point of the aircraft moves forward because of its high sweepback angle, thus the aircraft would be more stable.