Source code for RCAIDE.Library.Methods.Geometry.Planform.populate_control_sections

# RCAIDE/Library/Methods/Geometry/Planform/populate_control_sections.py
#  
# Created: Oct 2024, M. Clarke

# ----------------------------------------------------------------------------------------------------------------------
#  IMPORT
# ----------------------------------------------------------------------------------------------------------------------

# RCAIDE imports   
from RCAIDE.Framework.Core import  Container 

# package imports
import numpy   as np  

# ----------------------------------------------------------------------------------------------------------------------
#  populate_control_sections
# ---------------------------------------------------------------------------------------------------------------------- 


def populate_control_sections(wing):
    """This function takes the control surfaces defined on a wing and appends them to wing segments
    Conditional statements are used to determine where the control surface bounds are in relation 
    to the wing segments. For example, If a control surface extends beyond a wing segment, the bounds 
    on the control surface span fraction are set to be the bounds of the wing section
    
    Assumptions: 
       None

    Source:
       None
 

    Properties Used:
    N/A
    """
    w_cs  = wing.control_surfaces  
    w_seg = wing.segments 

    for i , seg in enumerate(w_seg):
        seg.control_surfaces = Container()
    
    # loop throught the control surfaces on the wing 
    for cs in w_cs :
        sf    = np.zeros(2) # set a temporary data structure to store the span fraction bounds
        sf[0] = cs.span_fraction_start
        sf[1] = cs.span_fraction_end
        
        # loop though the segments on the wing
        for i , seg in enumerate(w_seg):
            append_CS = False
            s_sf = np.zeros(2) 
            if i == 0: # the first segment (root) cannot have any control surfaces 
                pass
            else: # the following block determines where the bounds of the control surface are in relation to the segment breaks
                # Case 1
                prev_seg    =  list(w_seg.keys())[i-1]
                current_seg =  list(w_seg.keys())[i]
                if (sf[0] < w_seg[prev_seg].percent_span_location) and (sf[1] < w_seg[current_seg].percent_span_location) and (sf[1] > w_seg[prev_seg].percent_span_location) :
                    s_sf = np.array([w_seg[prev_seg].percent_span_location,sf[1]])   
                    append_CS = True 
                
                # Case 2
                elif (sf[0] < w_seg[prev_seg].percent_span_location) and (sf[1] == w_seg[current_seg].percent_span_location):
                    s_sf = np.array([w_seg[prev_seg].percent_span_location,w_seg[current_seg].percent_span_location])       
                    append_CS = True 
                    
                # Case 3   
                elif (sf[0] < w_seg[prev_seg].percent_span_location) and (sf[1] > w_seg[current_seg].percent_span_location):
                    s_sf = np.array([w_seg[prev_seg].percent_span_location,w_seg[current_seg].percent_span_location])       
                    append_CS = True                 
                
                # Case 4 
                elif (sf[0] == w_seg[prev_seg].percent_span_location) and (sf[1] < w_seg[current_seg].percent_span_location):
                    s_sf = np.array([w_seg[prev_seg].percent_span_location,sf[1]])   
                    append_CS = True 
                   
                # Case 5 
                elif (sf[0] == w_seg[prev_seg].percent_span_location) and (sf[1] == w_seg[current_seg].percent_span_location): 
                    s_sf = np.array([w_seg[prev_seg].percent_span_location,w_seg[current_seg].percent_span_location])       
                    append_CS = True
                    
                # Case 6 
                elif (sf[0] > w_seg[prev_seg].percent_span_location) and (sf[1] < w_seg[current_seg].percent_span_location):
                    s_sf = np.array([sf[0],sf[1]])
                    append_CS = True
                    
                # Case 7 
                elif (sf[0] > w_seg[prev_seg].percent_span_location) and (sf[1] == w_seg[current_seg].percent_span_location) :
                    s_sf = np.array([sf[0],w_seg[current_seg].percent_span_location]) 
                    append_CS = True                    
                    
                # Case 8
                elif (sf[0] > w_seg[prev_seg].percent_span_location) and (sf[1] > w_seg[current_seg].percent_span_location) and (sf[0] < w_seg[current_seg].percent_span_location):
                    s_sf = np.array([sf[0],w_seg[current_seg].percent_span_location]) 
                    append_CS = True
                    
                else: 
                    append_CS = False
                
                if append_CS == True:
                    # initialize the data structure for control surfaces , store results, and append to the correct segment 
                    control_surface = type(cs)() # control_surface takes came type as cs (Slat, Aileron, Data(for VLM), etc)                                             
                    control_surface.tag                   = cs.tag 
                    control_surface.span                  = cs.span*(s_sf[1]-s_sf[0])/(cs.span_fraction_end-cs.span_fraction_start)
                    control_surface.span_fraction_start   = s_sf[0] 
                    control_surface.span_fraction_end     = s_sf[1]         
                    control_surface.hinge_fraction        = cs.hinge_fraction
                    control_surface.chord_fraction        = cs.chord_fraction
                    control_surface.sign_duplicate        = cs.sign_duplicate
                    control_surface.deflection            = cs.deflection
                    control_surface.configuration_type    = cs.configuration_type
                    control_surface.gain                  = cs.gain                    
                    
                    # for calls from make_VLM_wings
                    if 'cs_type' in cs.keys():
                        control_surface.cs_type           = cs.cs_type
                    
                    w_seg[current_seg].control_surfaces.append(control_surface)        
                
    # returns an updated wing with control surfaces appended onto the wing segments                  
    return wing