Tube_Wing

Provides structural weight correlations for a tube and wing aircraft. More...

Functions
def	SUAVE.Methods.Weights.Correlations.Transport.tail_horizontal.tail_horizontal (vehicle, wing)
def	SUAVE.Methods.Weights.Correlations.Transport.tail_vertical.tail_vertical (vehicle, wing, rudder_fraction=0.25)
def	SUAVE.Methods.Weights.Correlations.Transport.tube.tube (vehicle, fuse, wt_wing, wt_propulsion)

Detailed Description

Provides structural weight correlations for a tube and wing aircraft.

Function Documentation

tail_horizontal()

def SUAVE.Methods.Weights.Correlations.Transport.tail_horizontal.tail_horizontal	(		vehicle,
			wing
	)

Calculate the weight of the horizontal tail in a standard configuration

Assumptions:
    calculated weight of the horizontal tail including the elevator
    Assume that the elevator is 25% of the horizontal tail 

Source: 
    Aircraft Design: A Conceptual Approach by Raymer
    
Inputs:
    wing.spans.projected - span of the horizontal tail                                              [meters]
    wing.sweeps.quarter_chord - sweep of the horizontal tail                                        [radians]
    Nult - ultimate design load of the aircraft                                                     [dimensionless]
    S_h - area of the horizontal tail                                                               [meters**2]
    vehicle.mass_properties.max_takeoff - maximum takeoff weight of the aircraft                    [kilograms]
    vehicle.wings['main_wing'].origin[0] - mean aerodynamic chord of the wing                       [meters]
    wing.aerodynamic_center[0]  - mean aerodynamic chord of the horizontal tail                     [meters]
    wing.thickness_to_chord  - thickness-to-chord ratio of the horizontal tail                      [dimensionless]
    wing.areas.exposed - exposed surface area for the horizontal tail                               [m^2]
    wing.areas.wetted - wetted surface area of tail

Outputs:
    weight - weight of the horizontal tail                                                          [kilograms]
   
Properties Used:
    N/A

tail_vertical()

def SUAVE.Methods.Weights.Correlations.Transport.tail_vertical.tail_vertical	(		vehicle,
			wing,
			rudder_fraction = 0.25
	)

Calculate the weight of the vertical fin of an aircraft without the weight of 
the rudder and then calculate the weight of the rudder 

Assumptions:
    Vertical tail weight is the weight of the vertical fin without the rudder weight.
    Rudder occupies 25% of the S_v and weighs 60% more per unit area.     
    
Source: 
    N/A 
    
Inputs:
    S_v - area of the vertical tail (combined fin and rudder)                      [meters**2]
    vehicle.envelope.ultimate_load - ultimate load of the aircraft                 [dimensionless]
    wing.spans.projected - span of the vertical                                    [meters]
    vehicle.mass_properties.max_takeoff - maximum takeoff weight of the aircraft   [kilograms]
    wing.thickness_to_chord- thickness-to-chord ratio of the vertical tail         [dimensionless]
    wing.sweeps.quarter_chord - sweep angle of the vertical tail                   [radians]
    vehicle.reference_area - wing gross area                                       [meters**2]
    wing.t_tail - factor to determine if aircraft has a t-tail                     [dimensionless]
    rudder_fraction - fraction of the vertical tail that is the rudder             [dimensionless]

Outputs:
    output - a dictionary with outputs:
        wt_tail_vertical - weight of the vertical fin portion of the vertical tail [kilograms]
        wt_rudder - weight of the rudder on the aircraft                           [kilograms]
  
Properties Used:
    N/A

tube()

def SUAVE.Methods.Weights.Correlations.Transport.tube.tube	(		vehicle,
			fuse,
			wt_wing,
			wt_propulsion
	)

Calculate the weight of a fuselage in the state tube and wing configuration

Assumptions:
    fuselage in a standard wing and tube configuration         

Source: 
    N/A 
    
Inputs:
    fuse.areas.wetted - fuselage wetted area                                                            [meters**2]
    fuse.differential_pressure- Maximum fuselage pressure differential                                  [Pascal]
    fuse.width - width of the fuselage                                                                  [meters]
    fuse.heights.maximum - height of the fuselage                                                       [meters]
    fuse.lengths.total - length of the fuselage                                                         [meters]
    vehicle.envelope.limit_load - limit load factor at zero fuel weight of the aircraft                 [dimensionless]
    vehicle.mass_properties.max_zero_fuel - zero fuel weight of the aircraft                            [kilograms]
    wt_wing - weight of the wing of the aircraft                           [kilograms]
    wt_propulsion - weight of the entire propulsion system of the aircraft                              [kilograms]
    vehicle.wings.main_wing.chords.root - wing root chord                                               [meters]
    
Outputs:
    weight - weight of the fuselage                                                                     [kilograms]
        
Properties Used:
    N/A