This study attempts to present a new and comprehensive cycle for the design of fixed wing Micro Air Vehicles (MAV). The idea is to propose a complete cycle containing all MAV design subjects such as aerodynamics, stability, structure and navigation. The main aim of the cycle is to decrease the designing time for an optimum design. In this method the sizing process is started simultaneously and connectively which involves the following cases: 1) Specification of mission and aviation plan 2) Determination of plan form and Aspect Ratio 3) Constraint analysis 4) Estimation of plane weight. Completion of these four phases results in the specification of the geometry and dimensions of the wing in an optimum manner. After determination of the plan form geometry, selection of the airfoil is carried out by complying the defined Criteria. After this stage, the wing of MAV is designed completely and analysis can be carried out to determine the aerodynamics coefficients. Next step is design of the fuselage for the airplane. Then MAC and AC of wing are calculated and stability equations for MAV are simulated. The results of these processes are determination of surfaces, dimensions and airfoils of the tails and CG of the plane. After calculation the controls surfaces, the designed MAV is analyzed in a software such as XFLR5. Next step is selection of electric equipment such as motor, batteries, servo and etc. The final step of design is the optimization of the MAV for increasing its performance and endurance. After design steps of manufacturing will be started.
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