import sys
import os
# Append the root to the system path
sys.path.append(os.path.abspath('..'))
# IMPORT AEROCOMBAT CLASSES
# =========================
from AeroComBAT.Structures import MaterialLib, Laminate
from AeroComBAT.Utilities import RotationHelper
from AeroComBAT.tabulate import tabulate
import numpy as np
# MATERIAL lIBRARY VALIDATION
# ===========================
# Generate Empty Material Library
matlib = MaterialLib()
# Add a graphite orthotropic material
matlib.addMat(1, 'Graphite-Polymer Composite ortho', 'ortho', \
[155.0e9, 12.1e9, 12.1e9, .458, .248, .248, 3.2e9, 4.4e9,\
4.4e9, 1.7e3], .15e-3)
# Add a graphite transversely isotropic material
matlib.addMat(2, 'Graphite-Polymer Composite', 'trans_iso', \
[155.0e9, 12.1e9, .458, .248, 4.4e9, 1.7e3], .15e-3)
# Add a glass transversely isotropic material
matlib.addMat(3, 'Glass-Polymer Composite', 'trans_iso', \
[50.0e9, 15.2e9, .428, .254, 4.7e9, 1.2e3], .15e-3)
# Add a T300 transversely isotropic material
matlib.addMat(4, 'T300/5208', 'trans_iso', \
[181.0e9, 10.3e9, .458, .28, 7.17e9, 1.8e3], .15e-3)
# Add a aluminum isotropic material
matlib.addMat(5, 'AL-2050', 'iso', [75.8, 0.33, 2.7e3], .15e-3)
# IMPORT NUMPY PACKAGES # ===================== import numpy as np import matplotlib.pyplot as plt # IMPORT AEROCOMBAT CLASSES # ========================= from AeroComBAT.Structures import MaterialLib from AeroComBAT.AircraftParts import Wing from AeroComBAT.FEM import Model # ADD MATERIALS TO THE MATERIAL LIBRARY # ===================================== # Create a material library object matLib = MaterialLib() # Add an aluminum material (SI) matLib.addMat(1,'AL','iso',[68.9e9,.33,2700*2],.00025) # Add an soft material material (SI) matLib.addMat(2,'Weak_mat','iso',[100,.33,10],.00025) # Add material property from Hodges 1999 Asymptotically correct anisotropic # beam theory (SI) matLib.addMat(3,'AS43501-6*','trans_iso',[142e9,9.8e9,.34,.42,6e9,20000],0.0005) # CREATE THE WING # =============== # Define the chord length of the model c = .076 # Define the chord length (this will be the hight of the box beam) ctip = 0.0076+.001 # Since the wing isn't tapered
import os
sys.path.append(os.path.abspath('..'))
# IMPORT AEROCOMBAT CLASSES
# =========================
from AeroComBAT.Structures import Node, MaterialLib, CQUADX
from AeroComBAT.Aerodynamics import Airfoil
# IMPORT NUMPY MODULES
# ====================
import numpy as np
import matplotlib.pyplot as plt
# Material Info
mat_lib = MaterialLib()
# Add an aluminum isotropic material
mat_lib.addMat(1, 'AL-2050', 'iso', [75.8, 0.33, 2.7e3], .15e-3)
# CQUADX 2D ELEMENT CREATION
# ==========================
# Create a node 1 object
n1 = Node(1, [0., 0., 0.])
# Create a node 2 object
n2 = Node(2, [2., 0., 0.])
# Create a node 3 object
n3 = Node(3, [2., 3., 0.])
# Create a node 4 object
n4 = Node(4, [0., 5., 0.])
# Create a CQUADX element
elem1 = CQUADX(1, [n1, n2, n3, n4], 1, mat_lib)
