This Paper represents a physical wing box procedure for estimating the primary wing massof conventional and unconventional airplane configurations, in which the statistical data andempirical formulae may not be applicable. The procedure is developed to include the aeroelasticinteractions and the controllability expectations from the control surfaces over the wingwithin the early stages of the preliminary conceptual aircraft design. A simplified approximatecross-section has been used to calculate the local wing structural properties at everysection based on the assumption that the estimated required material is to withstand the axialand shear stresses. Furthermore, an aeroelastic analysis was performed within the iterativeprocedure to assure that the structural design overcomes all the possible aeroelastic instabilitieswithin the required flight envelop. Finally, the procedure is used for sizing the primarywing mass of a CS-23 class box-wing configuration for regional air taxi services, which hasbeen developed in-house for hybrid-electric flight.
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