The Common buildup methods are those which are shared between vehicle types utilizing buildup weight methods.
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| def | SUAVE.Methods.Weights.Buildups.Common.fuselage.fuselage (config, maximum_g_load=3.8, landing_impact_factor=3.5, safety_factor=1.5) |
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| def | SUAVE.Methods.Weights.Buildups.Common.prop.prop (prop, 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) |
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| def | SUAVE.Methods.Weights.Buildups.Common.wing.wing (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) |
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| def | SUAVE.Methods.Weights.Buildups.Common.wiring.wiring (wing, config, cablePower) |
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The Common buildup methods are those which are shared between vehicle types utilizing buildup weight methods.
◆ fuselage()
| def SUAVE.Methods.Weights.Buildups.Common.fuselage.fuselage |
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config, |
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maximum_g_load = 3.8, |
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landing_impact_factor = 3.5, |
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safety_factor = 1.5 |
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) |
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Calculates the structural mass of a fuselage for an eVTOL vehicle,
assuming a structural keel taking bending an torsional loads.
Assumptions:
Assumes an elliptical fuselage. Intended for use with the following
SUAVE vehicle types, but may be used elsewhere:
Electric Multicopter
Electric Vectored_Thrust
Electric Stopped Rotor
Originally written as part of an AA 290 project intended for trade study
of the above vehicle types.
If vehicle model does not have material properties assigned, appropriate
assumptions are made based on SUAVE's Solids Attributes library.
Sources:
Project Vahana Conceptual Trade Study
Inputs:
config SUAVE Vehicle Configuration
max_g_load Max Accelerative Load During Flight [Unitless]
landing_impact_factor Maximum Load Multiplier on Landing [Unitless]
Outputs:
weight: Estimated Fuselage Mass [kg]
Properties Used:
Material Properties of Imported SUAVE Solids
◆ prop()
| def SUAVE.Methods.Weights.Buildups.Common.prop.prop |
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prop, |
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maximum_lifting_thrust, |
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chord_to_radius_ratio = 0.1, |
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thickness_to_chord = 0.12, |
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root_to_radius_ratio = 0.1, |
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moment_to_lift_ratio = 0.02, |
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spanwise_analysis_points = 5, |
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safety_factor = 1.5, |
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margin_factor = 1.2, |
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forward_web_locations = [0.25, 0.35], |
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shear_center = 0.25, |
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speed_of_sound = 340.294, |
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tip_max_mach_number = 0.65 |
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) |
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weight = SUAVE.Methods.Weights.Buildups.Common.prop(
prop,
maximum_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_locationss = [0.25, 0.35],
shear_center = 0.25,
speed_of_sound = 340.294,
tip_max_mach_number = 0.65)
Assumptions:
Calculates propeller blade pass for an eVTOL vehicle based on assumption
of a NACA airfoil prop, an assumed cm/cl, tip Mach limit, and structural
geometry.
Intended for use with the following SUAVE vehicle types, but may be used
elsewhere:
Electric Multicopter
Electric Vectored_Thrust
Electric Stopped Rotor
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 SUAVE's Solids Attributes library.
Sources:
Project Vahana Conceptual Trade Study
Inputs:
prop SUAVE Propeller 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 SUAVE Solids
◆ wing()
| def SUAVE.Methods.Weights.Buildups.Common.wing.wing |
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wing, |
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config, |
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max_thrust, |
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num_analysis_points = 10, |
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safety_factor = 1.5, |
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max_g_load = 3.8, |
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moment_to_lift_ratio = 0.02, |
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lift_to_drag_ratio = 7, |
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forward_web_locations = [0.25, 0.35], |
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rear_web_locations = [0.65, 0.75], |
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shear_center_location = 0.25, |
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margin_factor = 1.2 |
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) |
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weight = SUAVE.Methods.Weights.Buildups.Common.wing(
wing,
config,
maxThrust,
numAnalysisPoints,
safety_factor,
max_g_load,
moment_to_lift_ratio,
lift_to_drag_ratio,
forward_web_locations = [0.25, 0.35],
rear_web_locations = [0.65, 0.75],
shear_center = 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.
Intended for use with the following SUAVE vehicle types, but may be used
elsewhere:
Electric Multicopter
Electric Vectored_Thrust
Electric Stopped Rotor
Originally written as part of an AA 290 project intended for trade study
of the above vehicle types plus an electric multicopter.
If no materials are assigned to vehicle model, appropriate assumptions
are made based on SUAVE's Solids Attributes library.
Sources:
Project Vahana Conceptual Trade Study
Inputs:
wing SUAVE Wing Data Structure [None]
winglet_fraction winglet fraction [Unitless]
motor_spanwise_locations spanwise fraction location of motor [Unitless]
config SUAVE 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]
◆ wiring()
| def SUAVE.Methods.Weights.Buildups.Common.wiring.wiring |
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wing, |
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config, |
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cablePower |
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) |
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weight = SUAVE.Methods.Weights.Buildups.Common.wiring(
wing,
config,
cablePower)
Assumptions:
Calculates mass of wiring required for a wing, including DC power
cables and communication cables, assuming power cables run an average of
half the fuselage length and height in addition to reaching the motor
location on the wingspan, and that communication and sesor wires run an
additional length based on the fuselage and wing dimensions.
Intended for use with the following SUAVE vehicle types, but may be used
elsewhere:
Electric Multicopter
Electric Vectored_Thrust
Electric Stopped Rotor
Originally written as part of an AA 290 project intended for trade study
of the above vehicle types.
Sources:
Project Vahana Conceptual Trade Study
Inputs:
config SUAVE Config Data Structure
motor_spanwise_locations Motor Semi-Span Fractions [Unitless]
max_power_draw Maximum DC Power Draw [W]
Outputs:
weight: Wiring Mass [kg]
1.8.15