Random Vibration Analysis and Optimization Design of Tail Wing Rudder Surface Suspension Joints
Based on the rudder surface suspension joint structure of UAV,a geometric model is established by using finite element software,and the static analysis is carried out by applying boundary constraints and aerodynamic loads.Then a random vibration response analysis is carried out,the maximum vibration shape variable at different frequencies is investi-gated,and the rudder surface suspension joint structure is designed lightweight through the design method of topology op-timization.The results of topology optimization are imported into the 3D software model for geometrically reconstructed.The results show that the maximum deformation of the rudder suspension joint of the tail wing is 0.495 mm,the maxi-mum stress is 34.6 MPa,the maximum X-direction strain of the composite material in the connection area is 280.6 με,the maximum Y-direction strain is 284.0 με,and the maximum shear strain is 381.2 με;the random vibration response peaks at the frequency of 100 Hz and 200 Hz,and the structure is prone to damage and failure;the volume fraction of the rudder suspension joint is reduced by 26.80%after lightweight design,and the optimized rudder surface suspension joint struc-ture is reasonable and reliable.
国家科技期刊平台
NSTL
万方数据
维普
