Research On Aerodynamic Optimization Of A Flying Wing UAV

Compared with conventional layout aircraft,winged aircraft usually have better aerodynamic performance and higher lift-to-drag ratio.At present,flying wing layout aircraft are widely used in military and civil affairs,and more and more UAVs also use flying wing layout.Although the wing layout has better aerodynamic performance,but for the wing layout,the geometry is also important.Currently,there are not many researches on aerodynamic shape optimization of UAV with wing layout.Therefore,it is necessary to carry out research on aerodynamic optimization of UAV with wing layout.In this paper for the flying wing layout unmanned aerial vehicle(UAV)model of the author’s research group,based on the basic principle of Computational Fluid Dynamics(CFD),using CATIA secondary development technology of UAV parametric modeling,through a Pointwise Glyph scripting language realization of computing grid automatically generated,batch operations by Fluent software,automatic export calculation results,which based on CFD technology of UAV pneumatic analysis process.The accuracy of aerodynamic analysis method based on CFD technology is verified by verifying the flow field simulation example of ONERA M6 wing.For the flying wing layout UAV model,Wing root-to-tip ratio,UAV aspect ratio,UAV central fuselage width,wing leading edge sweep angle and wing undershoot angle,selecte these five geometric parameters to analysis of the influence of each geometric parameter on the lift coefficient,drag coefficient and lift-drag ratio of the UAV in cruise state and give single-parameter optimal results and optimization range for comprehensive optimization.Finally,by using the optimization method based on agent model,through sampling,establishing polynomial agent model and using optimization algorithm to optimize the aerodynamic shape of the UAV model,the process of aerodynamic shape optimization of the UAV is realized,and the final optimization results are given,which improves the lift-drag ratio of the cruise state of the UAV.