可变后掠翼联动驱动机构设计与尺寸综合

Design and dimensional synthesis of a variable wing sweep mechanism

可变后掠翼飞行器通过改变其机翼后掠角,可实现在不同飞行速度条件下,达到最佳飞行状态。为了实现在单驱动下机翼后掠角变化时,同时实现机翼部分蒙皮的展收,基于平面复合连杆机构,提出一种可变后掠翼联动驱动机构。为了解决该机构函数生成与运动生成综合相结合的尺寸综合问题,将复合连杆机构拆分为3个子机构,通过矢量方程法对机构进行分析,建立复合连杆机构的矢量环路方程,并对机构的可动性进行分析。结合机构矢量环路方程,提出一种利用优化算法与运动学分析软件判断机构可动性、优化机构性能的尺寸综合方法。结合相应实例,使用所提方法对机构进行设计,获得了满足可动性要求、尺寸约束,且包络面积最小的机构尺寸构型,证明了所提方法的有效性。

By changing the wing sweep angle,the variable wing sweep aircraft can achieve the best flight state under different flight speeds.To complete the folding and unfolding movements of the wing skin when the wing sweep angle changes under the single drive condition,we present a new driving mechanism for the variable sweep aircraft based on the planar compound linkage mechanism.To solve the problem of the combination of function generation and motion generation,the compound mechanism is divided into three sub-mechanisms.Furthermore,the vector loop equation of the compound mechanism is established and the movability of the mechanism is analyzed.Based on the vector loop equation,we propose a synthesis method to judge the movability and optimize the performance of the mechanism by using the optimization algorithm and kinematic analysis software.Finally,an example is presented to validate the effectiveness of the proposed method.The driving mechanism for the variable sweep aircraft is designed by using the proposed method.The designed mechanism meets the movability requirement and size constraint,and has the minimum envelope area,which prove the effectiveness of the method.