Composite Sandwich Beam Optimization And Design Of A Certain Type Of Solar UAV

The content of this paper is the optimization of the sandwich beam of solar UAVcomposites.B ecause of its unique power source,solar UAV must meet their flight long-haulrequirements by reducing the weight of the structure.Advanced carbon fibercomposites are used widelyin aerospace structures due to their high specific strength and specific modulus,itprovides more options for improving the overall efficiency of solar drones.As the main bearing member of the wing is related to the carrying capacity of the whole UAV,the importance of carrying out the research on composite beam optimization is self-evident.In this paper,the solar UAV composite beam is taken as the research object,First of all,Defining the weight of the wing as the main goal of the optimization design,taking into account the complexity of the composite material optimization design,drawing on the commonly used composite material equivalent theory methods,through the design test,the sandwich panel theory is the best comprehensive effect.Secondly,based on the design requirements of the solar UAV wing and wing beam,a reasonable configuration of the wing finite element model is carried out by considering many factors,and the influence of the external load of the UAV on the wing structure is analyzed.And through the multi-point row equivalent method to achieve the conversion of the load from the aerodynamic field to the structure field;The finite element software was used to analyze the mechanical properties of the three kinds of spars of the beam,box beam and I-beam,and the comprehensive mechanical properties of the three spars were obtained.In addition,based on the Multi-Island Genetic Algorithm to construct the optimization model with the weight of the wing structure as the objective function,the optimization of the composite wing beam size is carried out.With the powerful optimization platform Isight and finite element software,the joint of the bean is realized.Simulation analysis shows that the weights of the tube beam,box beam and I-beam are reduced by 9.4%,5.1%and 6.2%,which improves the utilization of composite materials.Finally,with the deformation of the wing as the optimization target,the section height and width of the box beam are distributed reasonably,and the maximum deformation of the box beam wing is reduced to 127.3mm;After the optimization is completed,the composite box-type beam sample is prepared.The three-point bending test and the cantilever beam bending test are designed to verify the strength and deformation ability of the sample.The results show that the box-shaped beam meets the design requirements by optimization.It provides reference and ideas for the subsequent optimization and research of composite wing of solar UAV.