def load_surfaces(self):
try:
surface_list = read_lifting_surface_objects()
if len(surface_list) == 0:
self.new_surfaces()
else:
for l in surface_list:
design_type_, surface_type_ = get_surface_object_data(l)
if design_type_ == unconventional_design:
self.surfaca_tab_ = lifting_surface_pane(
l, surface_type_, design_type_)
self.surfaces.append(self.surfaca_tab_)
self.inputArea.addTab(self.surfaca_tab_, l)
self.indexes.append(l)
elif design_type_ == conventional_design:
if surface_type_ == fin:
self.surfaca_tab_ = v_stab_tab(
l, surface_type_, design_type_)
self.surfaces.append(self.surfaca_tab_)
self.inputArea.addTab(self.surfaca_tab_, l)
self.indexes.append(l)
elif surface_type_ == tailplane:
self.surfaca_tab_ = h_stab_tab(
l, surface_type_, design_type_)
self.surfaces.append(self.surfaca_tab_)
self.inputArea.addTab(self.surfaca_tab_, l)
self.indexes.append(l)
else:
self.surfaca_tab_ = wing_tab(
l, surface_type_, design_type_)
self.surfaces.append(self.surfaca_tab_)
self.inputArea.addTab(self.surfaca_tab_, l)
self.indexes.append(l)
except:
self.new_surfaces()
def update_surface_lower_3d(config=None):
surface_list = read_lifting_surface_objects()
lofts = {}
for l in surface_list:
design_type_, surface_type_ = get_surface_object_data(l)
lofts.update({
l:
generate_wing_lower_3D(config, l, surface_type_, design_type_)
})
return lofts
def get_surface_for_vlm():
from aerosandbox_legacy_v0 import WingXSec, Wing, Airfoil
from Utils.data_objects.lifting_surface_placeholder import wing
wings = []
surface_list = read_lifting_surface_objects()
for l in surface_list:
design_type_, surface_type_ = get_surface_object_data(l)
if design_type_ == unconventional_design:
from aerosandbox_legacy_v0 import Wing
x, y, z, chords, twist_, profile_, root_location_x, root_location_y, root_location_z, xz_mirror_ = get_parameters_for_unconventional(
l)
xsecs = []
for x_, y_, z_, chord_, t in zip(x, y, z, chords, twist_):
xsecs.append(
WingXSec( # Root
xyz_le=[x_, y_, z_],
chord=chord_,
twist=t,
airfoil=Airfoil(name=profile_)))
wings.append(
Wing(
name=l,
xyz_le=[root_location_x, root_location_y, root_location_z],
# Coordinates of the wing's leading edge
symmetric=xz_mirror_,
xsecs=xsecs))
elif design_type_ == conventional_design:
x, y, z, chords, twist, profile_, root_location_x, root_location_y, root_location_z = get_parameters_for_conventional(
l, surface_type_)
xsecs = []
for x_, y_, z_, chord_ in zip(x, y, z, chords):
if surface_type_ == wing or surface_type_ == tailplane:
xsecs.append(
WingXSec( # Root
xyz_le=[x_, y_, z_],
chord=chord_,
twist=twist,
airfoil=Airfoil(name=profile_)))
elif surface_type_ == fin:
print(fin)
xsecs.append(
WingXSec( # Root
xyz_le=[x_, z_, y_],
chord=chord_,
twist=twist,
airfoil=Airfoil(name=profile_)))
wings.append(
Wing(
name=l,
xyz_le=[root_location_x, root_location_y, root_location_z],
symmetric=True if surface_type_ == wing
or surface_type_ == tailplane else False,
xsecs=xsecs))
return wings
def build_datcom_input():
surface_list = read_lifting_surface_objects()
ls_statements = []
boom_statements = []
synths={}
for l in surface_list:
design_type_, surface_type_ = get_surface_object_data(l)
span_, tip_chord, root_chord, dihedral_, sweep_ = 0, 0, 0, 0, 0
profile_="0012"
if design_type_ == unconventional_design:
span_, tip_chord, root_chord, dihedral_, sweep_,profile_ = get_parameters_from_sections_lifting_surface(l)
elif design_type_ == conventional_design:
print(l)
span_, tip_chord, root_chord, dihedral_, sweep_,profile_ = get_parameters_from_conventional_wing(l)
print(profile_.split("naca"))
if surface_type_ == wing:
synths.update({"wing": span_ / 2})
ls_statements.append(set_planform_parameters(
type_1="W,G", tip_chord=tip_chord,
root_chord=root_chord, semi_span=(span_ / 2), sweep_angle=sweep_,
dihedral_=1.2,
profile=profile_.split("naca")[1]
))
elif surface_type_ == fin:
synths.update({"vtp":span_ / 2})
ls_statements.append(set_planform_parameters(
type_1="V,T", tip_chord=tip_chord,
root_chord=root_chord, semi_span=(span_ / 2), sweep_angle=sweep_,
dihedral_=1.3,
profile=profile_.split("naca")[1]
))
else:
synths.update({"vtp": span_ / 2})
ls_statements.append(set_planform_parameters(
type_1="H,T", tip_chord=tip_chord,
root_chord=root_chord, semi_span=(span_ / 2), sweep_angle=sweep_,
dihedral_=1.3,
profile=profile_.split("naca")[1]
))
try:
boom_list = read_boom_objects()
for l in boom_list:
design_type_, surface_type_ = get_boom_object_data(l)
if design_type_ == unconventional_design:
pass
elif design_type_ == conventional_design:
radii, x, z = get_parameters_from_conventional_boom(l)
boom_statements.append(set_body_parameters_radius(section_positions=x, radius_of_sections=radii,
iter_=(boom_list.index(l) + 1)))
except:
pass
mesh = get_center_of_mass()
try:
value=synths["vtp"]
except:
synths.update({"vtp":0})
try:
value=synths["htp"]
except:
synths.update({"htp":0})
input_ = "".join([set_flight_conditions(mach_numbers=get_mach_number(), angle_of_attack=get_aoa_range(), altitude=get_altitude()),
set_synths_parameters(center_of_gravity_x=round(mesh["x"],2),center_of_gravity_z=round(mesh["z"],2),
vtp_tip_position_x=round(synths.get("vtp"),2),
htp_tip_position_x=round(synths.get("htp"),2)),
"".join(ls_statements),
"".join(boom_statements),
create_footer()])
database.write_datcom_input(input=input_)
def update_surface_3D(workflow=None):
surface_list = read_lifting_surface_objects()
for l in surface_list:
design_type_, surface_type_ = get_surface_object_data(l)
generate_wing_3D(workflow, l, surface_type_, design_type_)