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create_fuselage.py
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create_fuselage.py
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from utils import *
from list_utils import*
# set centers, normals, heights, widths of fuselage
def shape_fuselage(fuselage, centers, normals, heights, width):
# set the wing section elements
for idx in range(0,fuselage.get_section_count()) :
s = fuselage.get_section(idx+1);
e = s.get_section_element(1);
ce = e.get_ctigl_section_element();
ce.set_center(centers[idx]);
ce.set_normal(normals[idx]);
ce.set_height(heights[idx])
ce.set_width(width[idx])
def nose_std():
number_of_section = 7;
centers = points_list_delta(number_of_section);
centers[0] = geometry.CTiglPoint(0,0,-0.4)
centers[1] = geometry.CTiglPoint(0.1,0,-0.4)
centers[2] = geometry.CTiglPoint(0.4,0,-0.36)
centers[3] = geometry.CTiglPoint(0.9,0,-0.09)
centers[4] = geometry.CTiglPoint(1.6,0,0)
centers[5] = geometry.CTiglPoint(1.8,0,0)
centers[6] = geometry.CTiglPoint(2,0,0)
normals = points_list_const(number_of_section, geometry.CTiglPoint(1,0,0) )
heights = double_list_const(number_of_section,2)
heights[0] = 0;
heights[1] = 0.6;
heights[2] = 1
heights[3] = 1.7
widths = double_list_const(number_of_section,2)
widths[0] = 0;
widths[1] = 0.6
widths[2] = 1
widths[3] = 1.7
return [centers, normals, heights, widths];
def nose_sharp(length):
start_dia = 0;
end_dia = 2;
start_center = geometry.CTiglPoint(0,0,0);
end_center = geometry.CTiglPoint(length,0,0);
return cone(start_dia,end_dia, start_center, end_center,6);
def middle_cylinder(last_center, length):
number_of_section = 4;
delta = geometry.CTiglPoint(length/number_of_section,0,0);
centers = points_list_delta(number_of_section, last_center + delta, delta );
normals = points_list_const(number_of_section, geometry.CTiglPoint(1,0,0) )
heights = double_list_const(number_of_section, 2.0)
widths = double_list_const(number_of_section, 2.0)
return [centers, normals, heights, widths];
def tail_std(last_center, length):
start_dia = 2;
end_dia = 0.5;
number_of_section = 6;
start_center= last_center+ geometry.CTiglPoint(1,0,0);
final_center_z = (start_dia/2 - end_dia) + (end_dia/2)
end_center= last_center + geometry.CTiglPoint(length, 0,final_center_z);
return cone(start_dia,end_dia, start_center, end_center, number_of_section)
def create_std_fuselage(aircraft,uid):
fuselages = aircraft.get_fuselages()
# parameters of the form centers, nomrals, heights, widths
parameters = nose_std()
ret = middle_cylinder(get_last_center(parameters), 9)
extend_lists(parameters, ret);
ret = tail_std(get_last_center(parameters), 3.5);
extend_lists(parameters, ret);
section_count = len(parameters[0])
print("requiered number of section: " + str(section_count))
fuselages.create_fuselage(uid, section_count, "fuselageCircleProfileuID")
shape_fuselage(fuselages.get_fuselage(uid), parameters[0], parameters[1], parameters[2], parameters[3])
def create_space_ship_fuselage(aircraft,uid):
cone_length =4
fuselages = aircraft.get_fuselages()
# parameters of the form centers, nomrals, heights, widths
parameters = nose_sharp(cone_length)
ret = middle_cylinder(get_last_center(parameters), 9)
extend_lists(parameters, ret);
start_center= get_last_center(parameters)+ geometry.CTiglPoint(1,0,0);
end_center= start_center + geometry.CTiglPoint(cone_length, 0,0);
ret = cone(2,0, start_center, end_center, 6)
extend_lists(parameters, ret);
section_count = len(parameters[0])
print("requiered number of section: " + str(section_count))
fuselages.create_fuselage(uid, section_count, "fuselageCircleProfileuID")
shape_fuselage(fuselages.get_fuselage(uid), parameters[0], parameters[1], parameters[2], parameters[3])
def main():
tigltixi = open_cpacs("Data/empty.cpacs3.xml")
tigl_h = tigltixi[0]
tixi_h = tigltixi[1]
aircraft = get_aircraft(tigl_h)
create_std_fuselage(aircraft, "mainFuselage");
create_space_ship_fuselage(aircraft, "mainFuselageShip");
save(tixi_h, aircraft, "out-test.xml")
tigl_h.close()
tixi_h.close()
if __name__ == '__main__':
main();