def test_to_file_exists(self):
file_name = join(this_directory, "test_file.txt")
trim_case = avl.TrimCase(1)
trim_case.to_file(file_name)
self.assertTrue(exists(file_name))
remove(file_name)
def test_missing_kwarg_instance(self):
"""
test that an invalid kwarg raises an error when instancing
"""
try:
trim_case = avl.TrimCase(1, hey = 5)
except avl.InvalidCaseParamError:
pass
def test_error_getting_missing_param(self):
"""
test that an invalid kwarg raises an error
"""
trim_case = avl.TrimCase(1, velocity = 5)
try:
trim_case["hey"]
except avl.InvalidCaseParamError:
pass
def test_error_setting_cl(self):
"""
test that an invalid kwarg raises an error
"""
trim_case = avl.TrimCase(1, velocity = 5)
try:
trim_case["cl"] = 5
except avl.InvalidCaseParamError:
pass
def create(self):
# create a surface file ------------------------------------------------
surface = avl.Surface("main")
surface.define_mesh(20, 30, 1.0, 1.0)
cord1 = 0.8
section1 = avl.Section(cord1)
section1.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
0.2, -0.2, 0.2, 0.5, 0)
cord2 = 0.3
section2 = avl.Section(cord2)
section2.translation_bias(cord1 - cord2, 0.3, 0)
section2.twist_angle = -1
section2.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
0.2, -0.2, 0.2, 0.5, 0)
cord3 = 0.05
section3 = avl.Section(cord3)
section3.twist_angle = -1
section3.translation_bias(cord1 - cord3, 0.85, 0)
section3.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
0.2, -0.2, 0.2, 0.5, 0)
control_surface = avl.ControlSurface(
"elevator", 0.3, [0, 1, 0], avl.ControlDeflectionType.SYMMETRIC)
surface.add_section(section1, section2, section3)
surface.add_control_surface(control_surface, 1, 2)
surface.reflect_surface = True
plane = avl.Plane("UAV", surface)
# create a mass file ---------------------------------------------------
# create sustructure from wing
structure_creator = layout.StructureFactory(
layout.StructuralModelType.HOLLOWFOAM)
structural_model = structure_creator(surface, wall_thickness=1)
structural_clone = structural_model.clone(reflect_y=True)
# add some more weights and arrangement
battery = layout.MassObject(layout.Cuboid(0.1, 0.1, 0.1), 1)
battery.location = layout.Point(0, -0.05, -0.05)
arrangement = layout.Arrangement("plane arrangement", battery,
structural_model, structural_clone)
# create case file -----------------------------------------------------
case = avl.TrimCase(surface.area * 2,
velocity=22,
mass=arrangement.total_mass)
return plane, case, arrangement
def test_to_file_content(self):
file_name = join(this_directory, "test_file.txt")
trim_case = avl.TrimCase(1)
trim_case.to_file(file_name)
expected_string = get_resource_content("case_to_file.txt")
with open(file_name) as open_file:
actual_string = open_file.read()
self.maxDiff = None
self.assertEqual(expected_string.strip(), actual_string.strip())
remove(file_name)
def test_cl_update(self):
"""
test that the coefficient of lift updates when kwargs update
"""
trim_case = avl.TrimCase(1, velocity = 1, mass = 1, gravity = 1, density = 1)
self.assertEqual(trim_case["cl"], 2)
def test_kwargs(self):
"""
tests that key word arguments update the case parameter dictionary
"""
trim_case = avl.TrimCase(1, velocity = 5)
self.assertEqual(trim_case._case_parameters["velocity"], 5)
def create(self, input_dict, name = "UAV"):
surface = avl.Surface("main_wing")
surface.define_mesh(15, 20, 1.0, 1.0)
main_cord1 = input_dict["cord_1"]
section1 = avl.Section(main_cord1)
thickness = input_dict["aerofoil_1_thickness"]
section1.aerofoil = aerofoil.Aerofoil.develop_aerofoil(thickness,
-1 * thickness,
input_dict["aerofoil_1_thickness"],
input_dict["aerofoil_1_thickness_loc"],
input_dict["aerofoil_1_camber"])
cord2 = input_dict["cord_2"]
section2 = avl.Section(cord2)
section2.twist_angle = input_dict["twist_angle_2"]
wing_shift_1 = input_dict["wing_shift_1"]
section2.translation_bias(main_cord1 - cord2 - wing_shift_1, input_dict["span_section_1"], 0)
thickness = input_dict["aerofoil_2_thickness"]
section2.aerofoil = aerofoil.Aerofoil.develop_aerofoil(thickness,
-1 * thickness,
input_dict["aerofoil_2_thickness"],
input_dict["aerofoil_2_thickness_loc"],
input_dict["aerofoil_2_camber"])
cord3 = input_dict["cord_3"]
section3 = avl.Section(cord3)
section3.twist_angle = input_dict["twist_angle_3"]
wing_shift_2 = input_dict["wing_shift_2"]
section3.translation_bias(main_cord1 - cord3 - wing_shift_1 - wing_shift_2, input_dict["span_section_2"], 0)
thickness = input_dict["aerofoil_3_thickness"]
section3.aerofoil = aerofoil.Aerofoil.develop_aerofoil(thickness,
-1 * thickness,
input_dict["aerofoil_3_camber"],
input_dict["aerofoil_3_thickness_loc"],
input_dict["aerofoil_3_camber"])
surface.add_section(section1, section2, section3)
surface.reflect_surface = True
# design tail
tail_surface = avl.Surface("tail")
tail_surface.angle_bias = input_dict["tail_twist"]
tail_surface.define_translation_bias(input_dict["elevator_distance"], 0, 0)
tail_surface.define_mesh(10, 15, 1.0, 1.0)
thickness = input_dict["tail_thickness"]
tail_aerofoil = aerofoil.Aerofoil.develop_aerofoil(0.5*thickness,
-1 * 0.5*thickness,
input_dict["tail_thickness"],
input_dict["tail_thickness_loc"],
input_dict["tail_camber"])
cord1 = input_dict["tail_cord_1"]
tail_section1 = avl.Section(cord1)
tail_section1.aerofoil = tail_aerofoil
cord2 = input_dict["tail_cord_2"]
tail_section2 = avl.Section(cord2)
tail_section2.translation_bias(0, input_dict["boom_width"]*0.5, 0)
tail_section2.aerofoil = tail_aerofoil
cord3 = input_dict["tail_cord_3"]
tail_section3 = avl.Section(cord3)
tail_section3.translation_bias(0, input_dict["boom_width"]*0.5 + input_dict["elevator_span"], 0)
tail_section3.aerofoil = tail_aerofoil
tail_surface.add_section(tail_section1, tail_section2, tail_section3)
tail_surface.reflect_surface = True
control_surface = avl.ControlSurface("elevator", input_dict["elevator_size"], [0, 1, 0], avl.ControlDeflectionType.SYMMETRIC)
tail_surface.add_control_surface(control_surface, 0, 2)
# design verticle_tail
"""
vtail_surface = avl.Surface("verticle_tail")
vtail_surface.define_translation_bias(input_dict["elevator_distance"], 0, 0)
vtail_surface.define_mesh(10, 15, 1.0, 1.0)
cord1 = input_dict["vtail_cord_1"]
vtail_section1 = avl.Section(cord1)
vtail_section1.translation_bias(0, input_dict["boom_width"]*0.5, 0)
vtail_section1.aerofoil = tail_aerofoil
cord2 = input_dict["vtail_cord_2"]
vtail_section2 = avl.Section(cord2)
vtail_section2.translation_bias(0, input_dict["boom_width"]*0.5, input_dict["vtail_height"])
tail_section2.aerofoil = tail_aerofoil
vtail_surface.add_section(vtail_section1, vtail_section2)
vtail_surface.reflect_surface = True
"""
# create a mass file ---------------------------------------------------
# create sustructure from wing
structure_creator = layout.StructureFactory(layout.StructuralModelType.HOLLOWFOAM)
structural_model = structure_creator(surface, wall_thickness = input_dict["wall_thickness"])
structural_clone = structural_model.clone(reflect_y = True)
# create structure for tail
tail_structural_model = structure_creator(tail_surface, wall_thickness = input_dict["tail_wall_thickness"])
tail_structural_model.location = layout.Point(tail_surface.x, tail_surface.y, tail_surface.z)
tail_structural_clone = tail_structural_model.clone(reflect_y = True)
# add some more weights and arrangement
battery = layout.MassObject.from_mass(layout.Cuboid(0.19, 0.035, 0.07), 0.306)
battery.location = layout.Point(input_dict['battery_loc'], -0.05, -0.05)
battery2 = battery.clone(reflect_y = True)
motor = layout.MassObject.from_mass(layout.Cuboid(0.092, 0.042, 0.042), 0.231)
motor.location = layout.Point(-0.092, input_dict["span_section_2"], -0.05)
motor2 = motor.clone(reflect_y = True)
# motor controller
motor_controller = layout.MassObject.from_mass(layout.Cuboid(0.08, 0.017, 0.031), 0.08)
motor_controller.location = layout.Point(main_cord1, -0.05, -0.05)
# add landing gear
landing_gear = layout.MassObject.from_mass(layout.Cuboid(0.105 + 0.238, 0.05, 0.065), 0.274)
landing_gear.location = layout.Point(0.8*main_cord1, input_dict["span_section_2"], -0.05)
landing_gear2 = landing_gear.clone(reflect_y = True)
# add two hollow booms
boom1 = layout.MassObject.from_mass(layout.HollowCylinder(0.012, 0.9, 0.005), 0.02727)
boom1.location = layout.Point(0.25*main_cord1, -0.05, -0.05)
boom1_ref = boom1.clone(reflect_y = True)
boom2 = layout.MassObject(layout.HollowCylinder(0.012, 0.9, 0.005), 0.02727)
boom2.location = layout.Point(0.6*main_cord1, -0.05, -0.05)
boom2_ref = boom2.clone(reflect_y = True)
# add horizontal booms
horizontal_boom1 = layout.MassObject.from_mass(layout.Cuboid( input_dict["elevator_distance"] + 0.5, 0.012, 0.012), 0.03636)
horizontal_boom1.location = layout.Point(-0.5, 0.1, 0)
horizontal_boom2 = horizontal_boom1.clone(reflect_y = True)
# wing box
box = layout.MassObject.from_mass(layout.Cuboid( 0.47, 0.1, 0.05), 0.284)
box.location = layout.Point(0, input_dict["span_section_2"], 0)
box2 = box.clone(reflect_y = True)
# fuselage box top
length = input_dict['fuselage_length']
fuselage = layout.MassObject.from_mass(layout.Cuboid(length, 0.3, 0.09), length * 0.38727)
fuselage.location = layout.Point(0.4 - length, -0.3*0.5, -0.09)
fuselage_bottom = layout.MassObject.from_mass(layout.Cuboid(length, 0.3, 0.09), length * 0.54)
fuselage_bottom.location = layout.Point(0.4 - length, -0.3*0.5, -0.3)
from_bulk_head = layout.MassObject.from_mass(layout.Cuboid(0.06, 0.24, 0.3), 0.161)
from_bulk_head.location = layout.Point(0.4 - length, -0.3*0.5, -0.3)
nose_cone = layout.MassObject.from_mass(layout.Cuboid(0.3, 0.3, 0.3), 0.221)
nose_cone.location = layout.Point(0.4 - length, -0.3*0.5, -0.3)
# ribs
rib_center = layout.MassObject.from_mass(layout.Cuboid(input_dict["cord_1"], 0.06, input_dict["aerofoil_2_thickness"]), 0.02)
rib_center.location = layout.Point(0, 0, 0)
rib_outer = layout.MassObject.from_mass(layout.Cuboid(input_dict["cord_2"], 0.03, input_dict["aerofoil_3_thickness"]), 0.01)
rib_outer.location = layout.Point(0, input_dict["span_section_2"], 0)
rib_outer_mirror = rib_outer.clone(reflect_y = True)
arrangement = layout.Arrangement("plane arrangement", battery,
battery2,
motor, motor2,
landing_gear, landing_gear2,
boom1, boom1_ref,
boom2, boom2_ref,
box, box2,
fuselage, fuselage_bottom,
horizontal_boom1, horizontal_boom2,
rib_center, rib_outer, rib_outer_mirror,
from_bulk_head,
structural_model,
structural_clone,
nose_cone,
tail_structural_model,
tail_structural_clone)
# create case file -----------------------------------------------------
case = avl.TrimCase(surface.area, velocity = input_dict['velocity'],
mass = arrangement.total_mass)
plane = avl.Plane(name, surface, tail_surface)
return plane, case, arrangement
def create(self, input_dict, name="UAV"):
surface = avl.Surface("main_wing")
surface.define_mesh(20, 30, 1.0, 1.0)
cord1 = input_dict["cord_1"]
section1 = avl.Section(cord1)
thickness = input_dict["aerofoil_1_thickness"]
section1.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
thickness, -1 * thickness, input_dict["aerofoil_1_thickness"],
input_dict["aerofoil_1_thickness_loc"],
input_dict["aerofoil_1_camber"])
cord2 = input_dict["cord_2"]
section2 = avl.Section(cord2)
section2.twist_angle = input_dict["twist_angle_2"]
wing_shift_1 = input_dict["wing_shift_1"]
section2.translation_bias(cord1 - cord2 - wing_shift_1,
input_dict["span_section_1"], 0)
thickness = input_dict["aerofoil_2_thickness"]
section2.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
thickness, -1 * thickness, input_dict["aerofoil_2_thickness"],
input_dict["aerofoil_2_thickness_loc"],
input_dict["aerofoil_2_camber"])
cord3 = input_dict["cord_3"]
section3 = avl.Section(cord3)
section3.twist_angle = input_dict["twist_angle_3"]
wing_shift_2 = input_dict["wing_shift_2"]
section3.translation_bias(cord1 - cord3 - wing_shift_1 - wing_shift_2,
input_dict["span_section_2"], 0)
thickness = input_dict["aerofoil_3_thickness"]
section3.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
thickness, -1 * thickness, input_dict["aerofoil_3_camber"],
input_dict["aerofoil_3_thickness_loc"],
input_dict["aerofoil_3_camber"])
control_surface = avl.ControlSurface(
"elevator", input_dict["elevator_size"], [0, 1, 0],
avl.ControlDeflectionType.SYMMETRIC)
surface.add_section(section1, section2, section3)
surface.add_control_surface(control_surface, 1, 2)
surface.reflect_surface = True
# create a mass file ---------------------------------------------------
# create sustructure from wing
"""structure_creator = layout.StructureFactory(layout.StructuralModelType.HOLLOWFOAM)
structural_model = structure_creator(surface, wall_thickness = input_dict["wall_thickness"])
structural_clone = structural_model.clone(reflect_y = True)"""
# add some more weights and arrangement
battery = layout.MassObject.from_mass(layout.Cuboid(0.19, 0.035, 0.07),
0.306)
battery.location = layout.Point(input_dict["battery_x_loc"] * cord1,
-0.035 * 0.5, -0.07 * 0.5)
motor = layout.MassObject.from_mass(layout.Cuboid(0.092, 0.042, 0.042),
0.231 * 2)
motor.location = layout.Point(cord1, -0.042 * 0.5, -0.042 * 0.5)
structure = layout.MassObject.from_mass(
layout.Cuboid(0.01, 0.01, 0.01), 6)
structure.location = layout.Point(cord1 * 0.6, -0.005, -0.005)
arrangement = layout.Arrangement("plane arrangement", battery, motor,
structure)
# create case file -----------------------------------------------------
print('AREA ', surface.area)
print('mass ', arrangement.total_mass)
case = avl.TrimCase(surface.area,
velocity=22,
mass=arrangement.total_mass)
plane = avl.Plane(name, surface)
return plane, case, arrangement
def test_integration(self):
# create a surface file ------------------------------------------------
surface = avl.Surface("UAV")
surface.define_mesh(20, 30, 1.0, 1.0)
cord1 = 0.8
section1 = avl.Section(cord1)
section1.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
0.2, -0.2, 0.2, 0.5, 0)
cord2 = 0.3
section2 = avl.Section(cord2)
section2.translation_bias(cord1 - cord2, 0.3, 0)
section2.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
0.2, -0.2, 0.2, 0.5, 0)
cord3 = 0.05
section3 = avl.Section(cord3)
section3.translation_bias(cord1 - cord3, 0.85, 0)
section3.aerofoil = aerofoil.Aerofoil.develop_aerofoil(
0.2, -0.2, 0.2, 0.5, 0)
control_surface = avl.ControlSurface(
"elevator", 0.3, [0, 1, 0], avl.ControlDeflectionType.SYMMETRIC)
surface.add_section(section1, section2, section3)
surface.add_control_surface(control_surface, 1, 2)
surface.reflect_surface = True
plane = avl.Plane("UAV", surface)
avl_input, aerofoil_files = plane.dump_avl_files(self.test_folder)
# create a mass file ---------------------------------------------------
# create sustructure from wing
structure_creator = layout.StructureFactory(
layout.StructuralModelType.HOLLOWFOAM)
structural_model = structure_creator(surface, wall_thickness=1)
structural_clone = structural_model.clone(reflect_y=True)
# add some more weights and arrangement
battery = layout.MassObject(layout.Cuboid(0.1, 0.1, 0.1), 1)
battery.location = layout.Point(0, -0.05, -0.05)
arrangement = layout.Arrangement("plane arrangement", battery,
structural_model, structural_clone)
# create case file -----------------------------------------------------
case = avl.TrimCase(surface.area * 2,
velocity=22,
mass=arrangement.total_mass)
case.to_file(self.run_file)
layout.create_mass_file(self.mass_file, arrangement, case)
# run through athena
avl_runner = avl.AVLRunner()
avl_runner.setup_analysis(avl_input, self.mass_file, self.run_file,
*aerofoil_files)
results = avl_runner.generate_results(self.results_dir)
self.assertEqual(results.alpha, 6.70371)
self.assertEqual(results.elevator_deflection, 26.68316)
if self.plot:
plot = plt.subplot(111)
surface.plot_xy(plot, "g_")
arrangement.plot_xy(plot, True, "r-")
plt.show()
