Research On Design Of Conformation And Aerodynamics Layout For Rotary Wing MAV

Nowadays some military and civil departments and researchers pay more attention tomicro air vehicle (MAV), because of its special flight performance and latent application.Different function, conformation and layout of aerodynamic crafts are designed out insuccession, such as fixed wings, rotor aircrafts and ornithopter. Fixed wings aircrafts andornithopter can fly forward fast, and rotary wings aircrafts can vertically take off and land andhover, but the aircrafts which can vertically take off and land，hover and also can fly forwardfast are rare.The thesis integrates the good points of fixed wings and rotary wings and applies ductedrotary wing structure to design out new pattern aerodynamic-layout micro air vehicle whichcan VTOL and hover and also can fly forward fast. First, this paper designs aerodynamiclayout for MAV. Through the design target we estimate flight Reynolds number range ofmicro air vehicle, and choose some right airfoils. And the author analyzes these airfoils byairfoil analysis software for choosing a airfoil according to the requirements. Then the authorimports the data files of elected airfoils into software XFLR5,and input the size of design andairfoil the in software XFLR5, so the whole 3D flying wing type aerodynamic layout isformed; The next step is designing the conformation of micro air vehicle. Because thesoftware XFLR5 can only be used for the overall aerodynamic layout of the design and 3Dpneumatic around the flow analysis, and is not suitable for other conformation design .So theauthor chooses the UG NX6 software which has more powerful function to design lift system,the fuselage, propulsion system and the landing gear.Through the software XFLR5 3D geometric pneumatic around the flow analysis foundthat the wing tip appears eddy current, so the author increases winglets in the wing tip .After the analysis, the author finds the winglet does, indeed, improve the eddy current of thewingtip , and can also improve the flight lift and reduce resistance. Also we use the FLUENTsoftware to analyze the lift of rotary wing of blade. By calculating, we can see that the liftingsystem has enough motive power to provide the micro air vehicle with the holding and airhovering.