Conceptual Design Method for Solar Powered Aircrafts

*A method for conceptual design of solar powered aircrafts is presented. The method is based on traditional design methodologies modified to include the particular characteristics of solar powered aircrafts. A new parameter representing technology level is introduced and used for estimation of initial value for takeoff weight. Initial wing area is selected from mean wing loading for previous designs. Then parametric estimates for component weights are represented and takeoff weight consistency with technology level is verified . Because of high sensitivity to drag coefficient in these aircrafts it is tried to more precisely determine drag coefficient. Consequently, Airfoil is selected in conceptual design level and drag coefficient is estimated. Constraint diagrams having ratio of solar arrays area to wing area versus wing loading are then drawn for different mission conditions and a point is selected from within the allowed design space resulting a new value for Sw. An iterative procedure is done for convergence of Sw, and aerodynamic coefficients that finally sizes the conceptual design. A typical mission defined and related conceptual design is analyzed to show the applicability of the proposed design method.

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