from Structures import MaterialLib
from AircraftParts import Wing
from FEM import Model
# Define the width of the cross-section
x1 = -0.8990566037735849
x2 = 0.8990566037735849
c = 1.
ctip = c
croot = c
p1 = np.array([0., 0., 0.])
p2 = np.array([0., 0., 20.])
Y_rib = np.linspace(0., 1., 2)
b_s = np.linalg.norm((Y_rib[0], Y_rib[-1]))
matLib = MaterialLib()
matLib.addMat(1, 'AL', 'iso', [71.7e9, .33, 2810], .005)
matLib.addMat(2, 'Weak_mat', 'iso', [100, .33, 10], .005)
matLib.addMat(3, 'AS43501-6*', 'trans_iso',
[142e9, 9.8e9, .34, .42, 6e9, 2000], 0.005)
n_ply = [1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1]
m_ply = [1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1]
# For tension bending coupling
#m_ply = [3,3,3,3,3,3,3,3,3,3,3,3,3,3,3,3]
#th_ply = [0,0,0,0,-30,-30,-30,-30,0,0,0,0,30,30,30,30]
noe_dens = 4
chordVec = np.array([1., 0., 0.])
wing1 = Wing(1,p1,p2,croot,ctip,x1,x2,Y_rib,n_ply,m_ply,matLib,name='box',\
