飞行器机翼变形驱动机构研究

Study on Deformation Driving Mechanism of Aircraft Wing

为了优化飞行器气动特性,提升飞行效率,研究用于连续变弯度机翼的多级连杆驱动机构。采用ANSYS流体分析功能研究最大弯曲角度下变弯度机翼的气动特性;采用ANSYS静力学分析功能研究极限载荷条件下驱动机构的结构强度;并通过仿真分析与样机测试对驱动机构的运动情况进行研究。研究结果表明:变形机翼获得升力系数为1.4,所受最大气流动压1 078 Pa,小于下表面屈服气流动压4 916 Pa;驱动机构所受最大应力37.3 MPa,小于结构屈服强度55.2 MPa;机翼弯曲变形角度可达±25°,满足了飞行器对改善飞行特性方面的需要。

For the purpose of optimizing the aerodynamic characteristics and improving the flight efficiency of aircraft,a variable camber wing with multi-stage linkage driving mechanism is studied.The aerodynamic characteristics of the wing at the maximum deformation angle are studied by the fluid analysis function of ANSYS.The structural strength of the driving mechanism under the limit load condition is studied by the static analysis function of ANSYS.The motion of the driving mechanism is studied through simulation analysis and prototype test.The results indicate that the maximum lift coefficient of the deformed wing is 1.4,and the maximum aerodynamic pressure is 1078 Pa,which is less than the yield aerodynamic pressure of the lower surface of 4916 Pa.The maximum stress of the driving mechanism is 37.3 MPa,which is less than the structural yield strength of 55.2 MPa.The wing deformation angle is greater than±25°,which meets the requirement of improving aerodynamic characteristics of aircraft.