Study On The Aerodynamic Forces Of Flapping-wing MAV

Flapping-wing Micro Air Vehicles (FMAV) is a new aircraft as an imitation ofbirds or insects, It has the advantages of high flight efficiency, small size, light weight,easy to carry, easy to be hidden, and it can make hte Vertical Take Off and Landing,etc., hence it has been widely used in military applications, environmental monitoringand other aspects, and also got much attention of scholars and researchers. In order todesign high-performance FMAV, the unsteady flow and aerodynamic characteristicsof flapping wing flight must be calculated are concerned.The traditional numerical methods to analyze aerodynamic characteristicsare:The Finite Difference Method (FD), Finite Volume Method (FV), Finite ElementMethod (FEM), Surface/Boundary element method (BEM), but mostly in the processof solving the equation, the unit cell or grid has been used, lead to low accuracy of thecalculated stress and the difficulties of self adaptive analysis. In order to solve theseproblems, in this paper we introduce the meshfree weak-strong method(MWS), andby establishing the three-dimensional point interpolation (PIM) shape function, andby using the method of generalized integrations by parts, we extend it to be able toanalyze the three-dimensional numerical problems, so we use it to analyze theunsteady aerodynamic characteristics of flapping-wing MAV.In addition, we use a FMAV model with flight ability, write the flapping wingaerodynamic force analysis program based on the the MWS numerical calculationmethod by Matlab software, and by setting the different flight parameters, such as thethe different flapping wing frequency, stream velocity, angle of attack, we analysis thevariation of the flapping aerodynamic force parameters, and get some useful results,and provide some support for flapping-wing aerodynamic numerical research.Finally, because of the new piezoelectric materials: polyvinylidene fluoride(short for PVDF) has the Characteristics of wide frequency response, large dynamicrange, high sensitivity force electrical conversion, high mechanical intensity, lightweight, soft but none brittle, good impact of resistant, easily made into any shape, soit is suited for measuring deformation of the structure and mechanical properties, inthis paper we use the PVDF piezoelectric film to be the piezoelectric sensor and pasteit on the flapping-wing surface, and make an experiment to measure the aerodynamicforce of the flapping-wing aircraft by a wind tunnel, and we got some experimental data, it’s not only help to provides a new method for the flapping wing aerodynamicexperiments, but also offer some support for the flapping-wing aerodynamicnumerical analysis.