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',\
noe=noe_dens,chordVec=chordVec,ref_ax='origin')#,th_ply=th_ply)
sbeam1 = wing1.wingSects[0].SuperBeams[0]
x1 = np.array([-0.8990566037735849 * 2, 0., 0.])
x2 = np.array([0.8990566037735849 * 2, 0., 0.])
x3 = np.array([0.8990566037735849 * 2, 20., 0.])
x4 = np.array([-0.8990566037735849 * 2, 20., 0.])
nspan = 8 * 5
nchord = 2 * 5
#wing1.addLiftingSurface(1,x1,x2,x3,x4,nspan,nchord)
# Make a FEM model
model = Model()
model.addAircraftParts([wing1])
Y_rib = np.linspace(0., 20., 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)
n_ply = [1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1]
m_i = [1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1, 1]
wing1 = Wing(b_s,
croot,
ctip,
x1,
x2,
Y_rib,
n_ply,
m_i,
matLib,
name='box',
noe_per_unit_length=5)
sbeam1 = wing1.wingSects[0].SuperBeams[0]
#wing1.plotRigidWing()
# Apply the constraint for the model
wing1.addConstraint(0, 'fix')
# CASE 4:
# Apply the case load
tipLoad = np.array([-10000., 100000., -300000., 35000., 60000., 10000.])
F = {100: tipLoad}
