Analysis Of Center-Outer Wing Joint Of Composite Civil Aircraft

One of the essential parts in aircraft design is the design of center-outer wing joint structure,different joint configurations have different force transferring modes,which clearly plays a significant role in the lifetime and assembly technology of aircrafts.The joint structure transmits aerodynamic loads imposed on the wings to the fuselage in the form of forces and moments,the joint configuration and the construction of the fuselage influence each other.Hence,the efficiency of joint structure has an extremely significant effect on the weight of the aircraft structure.Therefore,in order to acquire reasonable configurations of center-outer wing joint structure,both the loads in the joint area and the design approach for composite specialty should be taken into account.By this way,it is effective to improve the design level of composite joint structure under the safety assurance of the joint structure.Consequently,this article carried out the following research:(1)A brief introduction of present research situation in the field of composite mechanical joint was summarized.Then after comparing several kinds of typical center-outer wing joint configurations of advanced composite civil airplanes,the joint configurations of the upper panel and lower panel that this article has researched were introduced;(2)Analyzing and comparing the composite laminate single-blot shear models with experiments by means of finite element analysis methods,and applying these methods in the center-outer wing joint configurations after verifying the effectiveness of these methods;(3)According to the different load forms of the upper and the lower panels of composite wing joint area,analyzing the strengthes of the typical center-outer wing joint configurations.By means of comparing the stability,the structure efficiency and the bearing capacity of each configuration,finally choosing one reasonable joint configuration for both the upper panel and the lower panel of composite wing.