def test_structural_solver():
# Material definition
name = "Aluminiun"
density = 0.0975
young_modulus = 1e7
shear_modulus = 3770000
poisson_ratio = 0.33
yield_strength = 350e6
ultimate_strength = 420e6
mat_aluminiun = basic_objects.Material(name, young_modulus, shear_modulus,
poisson_ratio, density,
yield_strength, ultimate_strength)
# Section definition
area = 1
m_inertia_y = 0.08333333
m_inertia_z = 0.08333333
polar_moment = 0.1408333
rotation = 0
section = basic_objects.Section(area, rotation, m_inertia_y, m_inertia_z,
polar_moment)
# Structure points definition
structure_points = np.array([[0, 0, 0], [10, 0, 0], [20, 0, 0]])
# Structure beams definition
beam_0 = basic_objects.Beam(structure_points, 0, 1, section, mat_aluminiun,
5)
beam_1 = basic_objects.Beam(structure_points, 1, 2, section, mat_aluminiun,
5)
beams = [beam_0, beam_1]
# Structure definition
structure = basic_objects.Structure(structure_points, beams)
# Element Length
element_length = 2
# Loads definition
force = basic_objects.Load(0, np.array([0, 100, 0, 0, 0, 0]))
loads = [force]
# Constraints definition
constraint_1 = basic_objects.Constraint(1, [0, 0, 0, 0, 0, 0])
constraint_2 = basic_objects.Constraint(2, [0, 0, 0, None, None, None])
constraints = [constraint_1]
print("# Testing structural_solver")
start = time.time()
deformed_grid, deformations, force_vector = finite_element_method.structural_solver(
structure, loads, constraints, element_length)
end = time.time()
print(f"- Test completed in {end - start}")
def test_plot_structure():
name = "Steel"
density = 8000
young_modulus = 200e9
shear_modulus = 80e9
poisson_ratio = 0.25
yield_strength = 350e6
ultimate_strength = 420e6
mat_steel = basic_objects.Material(name, young_modulus, shear_modulus, poisson_ratio, density, yield_strength, ultimate_strength)
area = 2e-2
m_inertia_y = 10e-5
m_inertia_z = 20e-5
polar_moment = 5e-5
rotation = pi / 6
section = basic_objects.Section(area, rotation, m_inertia_y, m_inertia_z, polar_moment)
structure_points = np.array([[0, 0, 0],
[2, 0, 0],
[5, 0, 0],
[5, 0, 1],
[2, -5, 0.4],
[2, 5, 0.4],
[5, -2, 1],
[5, 2, 1]])
fuselage_frontal = basic_objects.Beam(structure_points, 0, 1, section, mat_steel, 5)
fuselage_posterior = basic_objects.Beam(structure_points, 1, 2, section, mat_steel, 5)
wing_left = basic_objects.Beam(structure_points, 1, 4, section, mat_steel, 5)
wing_right = basic_objects.Beam(structure_points, 1, 5, section, mat_steel, 5)
tail_vertical = basic_objects.Beam(structure_points, 2, 3, section, mat_steel, 5)
tail_horizontal_left = basic_objects.Beam(structure_points, 3, 6, section, mat_steel, 5)
tail_horizontal_right = basic_objects.Beam(structure_points, 3, 7, section, mat_steel, 5)
beams = [fuselage_frontal,
fuselage_posterior,
wing_left,
wing_right,
tail_vertical,
tail_horizontal_left,
tail_horizontal_right]
constraint = basic_objects.Constraint(1, [0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0])
constraints = [[constraint]]
lift_left_wing = basic_objects.Load(4, np.array([0, 10000, 0, 0, 100, 0]))
lift_right_wing = basic_objects.Load(5, np.array([0, 10000, 0, 0, 100, 0]))
loads = [lift_left_wing, lift_right_wing]
aircraft_structure = basic_objects.Structure(structure_points, beams)
visualization.plot_structure(aircraft_structure)
def test_create_global_FEM_matrices():
# Material definition
name = "Aluminiun"
density = 0.0975
young_modulus = 1e7
shear_modulus = 3770000
poisson_ratio = 0.33
yield_strength = 350e6
ultimate_strength = 420e6
mat_aluminiun = basic_objects.Material(name, young_modulus, shear_modulus,
poisson_ratio, density,
yield_strength, ultimate_strength)
# Section definition
area = 1
m_inertia_y = 0.08333333
m_inertia_z = 0.08333333
polar_moment = 0.1408333
rotation = 0
section = basic_objects.Section(area, rotation, m_inertia_y, m_inertia_z,
polar_moment)
# Structure points definition
structure_points = np.array([[0, 0, 0], [10, 0, 0], [20, 0, 0]])
# Structure beams definition
beam_0 = basic_objects.Beam(structure_points, 0, 1, section, mat_aluminiun,
5)
beam_1 = basic_objects.Beam(structure_points, 1, 2, section, mat_aluminiun,
5)
beams = [beam_0, beam_1]
# Structure definition
structure = basic_objects.Structure(structure_points, beams)
# Element Length
element_length = 2
nodes, fem_elements = finite_element_method.generate_FEM_mesh(
structure, element_length)
# Loads definition
force = basic_objects.Load(1, np.array([0, 100, 0, 0, 0, 0]))
loads = [force]
print("# Testing create_global_FEM_matrices")
start = time.time()
K_global, F_global = finite_element_method.create_global_FEM_matrices(
nodes, fem_elements, loads)
end = time.time()
print(f"- Test completed in {end - start}")
right_wing_2 = basic_objects.Beam(structure_points, 8, 9, rectangular_section,
mat_aluminium7075, 1)
right_wing_3 = basic_objects.Beam(structure_points, 9, 10, rectangular_section,
mat_aluminium7075, 1)
right_wing_4 = basic_objects.Beam(structure_points, 10, 11,
rectangular_section, mat_aluminium7075, 1)
right_wing_5 = basic_objects.Beam(structure_points, 11, 12,
rectangular_section, mat_aluminium7075, 1)
structure_beams = [
left_wing_0, left_wing_1, left_wing_2, left_wing_3, left_wing_4,
left_wing_5, right_wing_0, right_wing_1, right_wing_2, right_wing_3,
right_wing_4, right_wing_5
]
wing_structure = basic_objects.Structure(structure_points, structure_beams)
# visualization.plot_structure(wing_structure)
# visualization.plot_aircraft(xx, yy, zz, wing_structure)
# Constrains
constrain = basic_objects.Constraint(6, [0, 0, 0, 0, 0, 0])
constraints = [constrain]
orig_xx, orig_yy, orig_zz = xx, yy, zz
for i in range(50):
# Aerodynamic Loads Calculation
panel_matrix = mesh.generate_panel_matrix(xx, yy, zz, wing.wing_span)