RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Electric.VTOL.Physics_Based.compute_wing_weight

compute_wing_weight

compute_wing_weight(wing, config, max_thrust, num_analysis_points=10, safety_factor=1.5, max_g_load=3.8, moment_to_lift_ratio=0.02, lift_to_drag_ratio=7, forward_web_locations=[0.25, 0.35], rear_web_locations=[0.65, 0.75], shear_center_location=0.25, margin_factor=1.2)

Calculates the structural mass of a wing for an eVTOL vehicle based on assumption of NACA airfoil wing, an assumed L/D, cm/cl, and structural geometry.

Assumptions: If no materials are assigned to vehicle model, appropriate assumptions are made based on RCAIDE’s Solids Attributes library.

Shear moment is calculated by adding thrust from each motor to each analysis point that’s closer to the wing root than the motor. Accomplished by indexing Vt according to a boolean mask of the design points that area less than or aligned with the motor location under consideration in an iterative loop

Sources: Project Vahana Conceptual Trade Study

Inputs:

wing RCAIDE Wing Data Structure [None]

winglet_fraction winglet fraction [Unitless] motor_spanwise_locations spanwise fraction location of motor [Unitless]

config RCAIDE Config Data Structure [None] maxThrust Maximum Thrust [N] numAnalysisPoints Analysis Points for Sizing [Unitless] safety_factor Design Safety Factor [Unitless] max_g_load Maximum Accelerative Load [Unitless] moment_to_lift_ratio Coeff. of Moment to Coeff. of Lift [Unitless] lift_to_drag_ratio Coeff. of Lift to Coeff. of Drag [Unitless] forward_web_locations Location of Forward Spar Webbing [m] rear_web_locations Location of Rear Spar Webbing [m] shear_center Location of Shear Center [m] margin_factor Allowable Extra Mass Fraction [Unitless]

Outputs:

weight: Wing Mass [kg]