def read_boom_data(boom_name_=""):
values = database.read_aircraft_specifications()
design_type_ = values[objects][boom_name_][design_type]
part = values[objects][boom_name_][boom_type]
if design_type_ == unconventional_design:
return read_boom_values(values[part][boom_name_])
else:
return read_fuselage_values(values["boom"][boom_name_])
def delete_control_surface_objects(value=""):
data = database.read_aircraft_specifications()
try:
array = data[control_surface_objects]
array.remove(value)
data[control_surface_objects] = array
except:
pass
database.write_aircraft_specification(data)
def read_parent_data(surface_name="",key=""):
values = database.read_aircraft_specifications()
design_type_ = values[objects][surface_name][design_type]
surface_type_ = values[objects][surface_name][surface_type]
if design_type_ == unconventional_design:
return values[lifting_surface][surface_name][key]
else:
return values[lifting_surface][surface_name][key]
def write_control_surface_to_objects(surface_name="",parent__=""):
data = database.read_aircraft_specifications()
try:
val = data[objects]
val[surface_name] = {surface_name: {parent_:parent__}}
except Exception as e:
logging.error(e)
data.update({objects: {surface_name: {parent_:parent__}}})
database.write_aircraft_specification(data)
def delete_control_surface_from_objects(surface_name=""):
data = database.read_aircraft_specifications()
try:
array = data[objects]
array.pop(surface_name)
data[objects] = array
except:
pass
database.write_aircraft_specification(data)
def get_parameters_from_conventional_boom(boom_name=""):
values = database.read_aircraft_specifications()[boom][boom_name]
nose_radius_ = values.get(nose_width)
nose_length_ = values.get(nose_length)
nose_position_z_ = values.get(nose_position_z)
cockpit_height_ = values.get(cockpit_height)
cockpit_length_ = values.get(cockpit_length)
cockpit_width_ = values.get(cockpit_width)
cockpit_position_x_ = values.get(cockpit_position_x)
cockpit_position_y_ = values.get(cockpit_position_y)
cockpit_position_z_ = values.get(cockpit_position_z)
tail_tip_position_ = values.get(tail_tip_position)
nose_tip_position_ = values.get(nose_tip_position)
tail_radius_ = values.get(tail_width)
tail_length_ = values.get(tail_length)
tip_radius_ = values.get(tip_width)
tail_position_z_ = values.get(tail_position_z)
section_1_length_ = values.get(section_1_length)
section_1_radius_ = values.get(section_1_width)
section_1_position_z_ = values.get(section_1_position_z)
section_2_radius_ = values.get(section_2_width)
section_2_length_ = values.get(section_2_length)
section_2_position_z_ = values.get(section_2_position_z)
section_3_length_ = values.get(section_3_length)
section_3_radius_ = values.get(section_3_width)
section_3_position_z_ = values.get(section_3_position_z)
radii = list(
np.array([
nose_radius_, section_1_radius_, section_2_radius_,
section_3_radius_, tail_radius_
]) / divider)
x = list(
np.array([
nose_length_,
sum([nose_length_, section_1_length_, section_2_length_]),
sum([
nose_length_, section_1_length_, section_2_length_,
section_3_length_
]),
sum([
nose_length_, section_1_length_, section_2_length_,
section_3_length_, tail_length_
])
]) / divider)
z = list(
np.array([
nose_position_z_, section_1_position_z_, section_2_position_z_,
section_3_position_z_, tail_position_z_
]) / 2000)
return radii, x, z
def write_boom_objects(value=""):
data = database.read_aircraft_specifications()
try:
array = data[boom_objects]
if not array.__contains__(value):
array.append(value)
data[boom_objects] = array
except:
data.update({boom_objects: [value]})
database.write_aircraft_specification(data)
def read_surface_data(surface_name=""):
values = database.read_aircraft_specifications()
design_type_ = values[objects][surface_name][design_type]
surface_type_ = values[objects][surface_name][surface_type]
if design_type_ == unconventional_design:
return read_lifting_surface_params(
values[lifting_surface][surface_name])
else:
return read_w_h_v(values[lifting_surface][surface_name],
part=surface_type_)
def write_control_surface_objects(value=""):
data = database.read_aircraft_specifications()
try:
array = data[control_surface_objects]
if not array.__contains__(value):
array.append(value)
data[control_surface_objects] = array
except Exception as e:
data.update({control_surface_objects: [value]})
database.write_aircraft_specification(data)
def get_surface_type(surface_name = ""):
_type=""
values = get_parent_name(surface_name)
surface_type_=database.read_aircraft_specifications()[values][surface_type]
if surface_type_==wing:
_type=aileron_
elif surface_type_==tailplane:
_type=elevator_
elif surface_type_==fin:
_type=rudder_
return _type
def get_parameters_from_conventional_wing(surface_name=""):
values = database.read_aircraft_specifications(
)[lifting_surface][surface_name]
root_chord = values.get(chord)
dihedral_ = values.get(dihedral)
sweep_ = values.get(sweep)
twist_ = values.get(twist)
span_ = values.get(span)
taper_ratio_ = values[taper_ratio]
profile_ = values.get(profile)
tip_chord = root_chord / taper_ratio_
return span_ / divider, tip_chord / divider, root_chord / divider, dihedral_, sweep_, profile_
def read_surface_data(surface_name=""):
values=database.read_aircraft_specifications()[control_surface][surface_name]
root_location_x_ = values.get(root_le_position_x)
root_location_y_ = values.get(root_le_position_y)
root_location_z_ = values.get(root_le_position_z)
rot_x_ = values.get(rotation_x)
rot_y_ = values.get(rotation_y)
rot_z_ = values.get(rotation_z)
parent__=values.get(parent_)
span_ = values.get(span)
chord_ = values.get(chord)
return root_location_x_, root_location_y_, root_location_z_, rot_x_, rot_y_, rot_z_, span_, chord_,parent__
def write_boom_to_objects(boom_name="", boom_type_="", design_type_=""):
data = database.read_aircraft_specifications()
try:
val = data[objects]
val[boom_name] = {boom_type: boom_type_, design_type: design_type_}
except Exception as e:
logging.error(e)
data.update({
objects: {
boom_name: {
boom_type: boom_type_,
design_type: design_type_
}
}
})
database.write_aircraft_specification(data)
def read_landing_gear_values():
values = database.read_aircraft_specifications()
values = values[landing_gear]
landing_gear_type_ = values.get(landing_gear_type)
struct_length_main_gear_ = values.get(struct_length_main_gear)
tire_diameter_ = values.get(tire_diameter)
wheel_diameter_ = values.get(wheel_diameter)
struct_length_aux_ = values.get(struct_length_aux)
aux_gear_position_x_ = values.get(aux_gear_position_x)
aux_gear_position_y_ = values.get(aux_gear_position_y)
aux_gear_position_z_ = values.get(aux_gear_position_z)
rol_gear_position_x_ = values.get(rol_gear_position_x)
rol_gear_position_y_ = values.get(rol_gear_position_y)
rol_gear_position_z_ = values.get(rol_gear_position_z)
return landing_gear_type_, struct_length_main_gear_, struct_length_aux_, \
aux_gear_position_x_, aux_gear_position_y_, aux_gear_position_z_, \
rol_gear_position_x_, rol_gear_position_y_, rol_gear_position_z_,wheel_diameter_,tire_diameter_,
def write_lifting_surface_to_objects(surface_name="",
surface_type_="",
design_type_=""):
data = database.read_aircraft_specifications()
try:
val = data[objects]
val[surface_name] = {
surface_type: surface_type_,
design_type: design_type_
}
except Exception as e:
logging.error(e)
data.update({
objects: {
surface_name: {
surface_type: surface_type_,
design_type: design_type_
}
}
})
database.write_aircraft_specification(data)
def get_parameters_from_sections_lifting_surface(surface_name=""):
values = database.read_aircraft_specifications()
parameters = values[lifting_surface][surface_name]
profile_ = values[lifting_surface][surface_name][profile]
x_list = [
parameters[section_1_x], parameters[section_2_x],
parameters[section_3_x], parameters[section_4_x],
parameters[section_5_x]
]
y_list = [
parameters[section_1_y], parameters[section_2_y],
parameters[section_3_y], parameters[section_4_y],
parameters[section_5_y]
]
chords = [
parameters[section_1_chord], parameters[section_2_chord],
parameters[section_3_chord], parameters[section_4_chord],
parameters[section_5_chord]
]
z_list = [[
parameters[section_1_z], parameters[section_2_z],
parameters[section_3_z], parameters[section_4_z],
parameters[section_5_z]
]]
avg_chord = np.average(np.array(chords))
y = np.array(y_list, dtype=float)
z = np.array(z_list, dtype=float)
x = np.array([0., 1., 1.5, 3.5, 4., 6.], dtype=float)
dihedral_ = 0
try:
dihedral_ = np.arctan(max([np.gradient(z, y)]))
except:
pass
sweep_ = max(np.arctan(np.gradient(y_list, x_list)))
span_ = max(y_list)
tip_chord = min(chords)
root_chord = max(chords)
return span_ / divider, tip_chord / divider, root_chord / divider, dihedral_, sweep_, profile_
def read_control_surface_objects():
data = database.read_aircraft_specifications()
return data[control_surface_objects]
def get_sweep_and_dihedral(part=""):
values = database.read_aircraft_specifications()[part]
sweep_ = values[part + "_sweep"]
dihedral_ = values.get(part + "_dihedral")
return sweep_, dihedral_
def get_parent_name(surface_name = ""):
values = database.read_aircraft_specifications()[control_surface][surface_name]
return values.get(parent_)
def read_lifting_surface_objects():
data = database.read_aircraft_specifications()
return data[lifting_surface_objects]
def read_root_position(part=""):
values = database.read_aircraft_specifications()[part]
root_location_x_ = values[part + "_root_position_x"]
root_location_y_ = values.get(part + "_root_position_y")
root_location_z_ = values.get(part + "_root_position_z")
return root_location_x_, root_location_y_, root_location_z_
def get_surface_object_data(boom_name_=""):
values = database.read_aircraft_specifications()
design_type_ = values[objects][boom_name_][design_type]
part_type_ = values[objects][boom_name_][surface_type]
return design_type_, part_type_
def get_parameters_from_unconventional_boom(boom_name=""):
values = database.read_aircraft_specifications()[boom][boom_name]
fuselage_length = values.get(boom_length)
fuselage_diameter = values.get(boom_diameter)
root_position_x_ = values.get(root_position_x)
root_position_y_ = values.get(root_position_y)
root_position_z_ = values.get(root_position_z)
nose_width_ = values.get(nose_width)
nose_height_ = values.get(nose_height)
nose_length_ = values.get(nose_length)
nose_position_z_ = values.get(nose_position_z)
xz_mirror_ = values.get(xz_mirror)
xy_mirror_ = values.get(xy_mirror)
yz_mirror_ = values.get(yz_mirror)
cockpit_height_ = values.get(cockpit_height)
cockpit_length_ = values.get(cockpit_length)
cockpit_width_ = values.get(cockpit_width)
cockpit_position_x_ = values.get(cockpit_position_x)
cockpit_position_y_ = values.get(cockpit_position_y)
cockpit_position_z_ = values.get(cockpit_position_z)
tail_tip_position_ = values.get(tail_tip_position)
nose_tip_position_ = values.get(nose_tip_position)
tail_profile_ = values.get(tail_profile)
nose_profile_ = values.get(nose_profile)
section_1_profile_ = values.get(section_1_profile)
section_2_profile_ = values.get(section_2_profile)
section_3_profile_ = values.get(section_3_profile)
tail_length_ = values.get(tail_length)
tail_width_ = values.get(tail_width)
tip_width_ = values.get(tip_width)
tail_height_ = values.get(tail_height)
tip_height_ = values.get(tip_height)
tail_position_z_ = values.get(tail_position_z)
section_1_length_ = values.get(section_1_length)
section_1_width_ = values.get(section_1_width)
section_1_height_ = values.get(section_1_height)
section_1_position_z_ = values.get(section_1_position_z)
section_2_width_ = values.get(section_2_width)
section_2_height_ = values.get(section_2_height)
section_2_length_ = values.get(section_2_length)
section_2_position_z_ = values.get(section_2_position_z)
section_3_length_ = values.get(section_3_length)
section_3_width_ = values.get(section_3_width)
section_3_height_ = values.get(section_3_height)
section_3_position_z_ = values.get(section_3_position_z)
s = list(
np.array([
get_area(nose_width_, nose_height_),
get_area(section_1_width_, section_1_height_),
get_area(section_2_width_, section_2_height_),
get_area(section_3_width_, section_3_height_),
get_area(tail_width_, tail_height_)
]) / divider)
x = list(
np.array([
nose_length_,
sum([nose_length_, section_1_length_, section_2_length_]),
sum([
nose_length_, section_1_length_, section_2_length_,
section_3_length_
]),
sum([
nose_length_, section_1_length_, section_2_length_,
section_3_length_, tail_length_
])
]) / divider)
return s, x
def read_boom_objects():
data = database.read_aircraft_specifications()
return data[boom_objects]
