Structural Design And Optimization Of Key Components Of In-situ Machining Machine Tool For Composite Material Wings

Inner patch bonding technology is a common method for repairing defects and damages of fiber reinforced plastic(FRP)parts.Among them,the high-quality and efficient processing of concave structure is the key to reliable repair.At present,in the project,the concave structure is still mainly processed by grinder or sandpaper layer by layer,which has the problems of low processing efficiency and poor quality stability.In order to meet the high-quality and high-efficiency repair requirements of a certain type of composite material wing of an aircraft,the subject proposed to design a machine tool with in-situ machining of concave structures during the repair process.The machine tool can be placed directly on the composite material wing to damage the wing surface The area is covered by cutting.This paper takes in-situ adsorption and covering cutting as the basic functional requirements,and mainly completes the overall structural design of in-situ processing machine tools and the optimization of key components.Specifically,the composite material wing of a certain type of aircraft is processed,and the processing requirements of typical damage and defect parts are analyzed in combination with the technical specifications of the internal supplementary handover of the composite material.It is clear that this type of machine tool is conformal adsorption,three-axis linkage,and overlay type.Features such as cutting;its overall size:800mm×800mm×140mm,working stroke:200mm×420mm×200mm;combined with the statistical analysis of the cutting load of such composite parts,the key technical parameters of the machine tool and the overall structural plan are proposed and carried out In order to further improve the static and dynamic performance of the mechanical structure,the static and dynamic characteristics of the key structural parts were analyzed,and the bed was completed by using the topology optimization method in order to further improve the static and dynamic performance of the mechanical structure.Optimized design of weight reduction,the weight of the machine tool was reduced by 11%;finally,the finite element analysis of the deformation of the wing clamping before and after weight reduction was made using cast iron and mineral materials,and the comparison results showed that the use of new materials and structural optimization After the machine tool,the deformation of the wing machining area is reduced to 0.17mm,which is about 55%lower than that of the cast iron machine tool,thereby reducing the impact of the equipment clamping deformation on the machining accuracy,and providing data for the planning of the machining track and parameters reference.