The Study On Bonding Performance Of Helicopter' Rotor Blade Tab On Trailing Edge

In this paper,based on the study of the stripping performance of the laminar structure of an unmanned helicopter blade trailing edge,the effective method to enhance the strength of stripping is discussed.In principle not affecting the structure of the helicopter and the performance of the flight,design secondary reinforcement scheme.Make the adjustment piece not off,thus the stability and safety of the helicopter flight status are ensured.This paper starts with the analytic solution of the quasi-two-dimensional linear model of the single-lap joint structure.The stress and strain distribution of the gluing layer and the adhesion are predicted by the joint area and the area of the adhesion is arbitrary section of the load.The initial stage design of the non-equilibrium joint and the strength prediction of the joint are helpful.Three schemes to improve the stripping performance of the adjustment chip are designed.Secondly,this paper uses finite element software Abaqus to perform finite element simulation calculation based on the cohesion model for three kinds of strengthened specimens and un-strengthened specimens.The interface parameters in the simulation are obtained by flattening,double-sided cutting,DCB,ENF Tests were taken to observe the structural failure modes and damage evolution processes of different reinforcement schemes.The accuracy of the finite element simulation was verified with the comparison of experiments,and the enhancement rates of the initial failure loads of the adjusting pieces under different schemes were obtained.By contrasting and analyzing the above enhancement schemes,this paper finally selected the double reinforcement method to enhance the helicopter blade blade bonding performance,this scheme has been used in the actual production,but also for the helicopter blade blades and other single lap joints enhanced peel Strength provides an effective way of thinking and methods.