RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Electric.Common.compute_rotor_weight
compute_rotor_weight#
- compute_rotor_weight(rotor, maximum_lifting_thrust, chord_to_radius_ratio=0.1, thickness_to_chord=0.12, root_to_radius_ratio=0.1, moment_to_lift_ratio=0.02, spanwise_analysis_points=5, safety_factor=1.5, margin_factor=1.2, forward_web_locations=[0.25, 0.35], shear_center=0.25, speed_of_sound=340.294, tip_max_mach_number=0.65)[source]#
Calculates propeller blade pass for an eVTOL vehicle based on assumption of a NACA airfoil rotor, an assumed cm/cl, tip Mach limit, and structural geometry.
Assumptions: Originally written as part of an AA 290 project inteded for trade study of the above vehicle types.
If vehicle model does not have material properties assigned, appropriate assumptions are made based on RCAIDE’s Solids Attributes library.
Sources: Project Vahana Conceptual Trade Study
Inputs:
rotor RCAIDE Rotor Data Structure maximum_thrust Maximum Design Thrust [N] chord_to_radius_ratio Chord to Blade Radius [Unitless] thickness_to_chord Blade Thickness to Chord [Unitless] root_to_radius_ratio Root Structure to Blade Radius [Unitless] moment_to_lift_ratio Coeff. of Moment to Coeff. of Lift [Unitless] spanwise_analysis_points Analysis Points for Sizing [Unitless] safety_factor Design Safety Factor [Unitless] margin_factor Allowable Extra Mass Fraction [Unitless] forward_web_locationss Location of Forward Spar Webbing [m] shear_center Location of Shear Center [m] speed_of_sound Local Speed of Sound [m/s] tip_max_mach_number Allowable Tip Mach Number [Unitless]
Outputs:
weight: Propeller Mass [kg]
Properties Used: Material properties of imported RCAIDE Solids