# If the user wanted to apply a different constraint, they can just enter the
# degrees of freedom to constrain on the model. This can be done by supplying
# an array such as: [1,2,3,5]. Now let's apply a load. We will make two load
# cases. In the first case, we are going to apply a simple tip load:
load1 = {21:np.array([100.,100.,0.,0.,0.,100.])}
# We can also create a function for a distributed load:
def load2(x):
vx = (1/10)*10*x[2]**2-7*x[2]-2.1
vy = 10*x[2]**2-7*x[2]
pz = 0
mx = 0
my = 0
tz = (10*x[2]**2-7*x[2])/10+3*x[0]**2
return np.array([vx,vy,pz,mx,my,tz])
# Ok now let's add these loads to the model:
model.applyLoads(1,F=load1)
# Notice that when I applied a tip load, I did it using the argument 'F'. When
# we apply a distributed load function, we use the argument 'f' instead.
model.applyLoads(2,f=load2,allElems=True)
# Now with constraints and loads, we can run a static analysis! Let's run the
# first load case.
model.staticAnalysis(1,analysis_name='tip load')
# Let's see what results we get:
model.plotDeformedModel(analysis_name='tip load',figName='Tip Load Analysis',\
numXSects=8,contour='VonMis',contLim=[0,1e5],warpScale=50,displScale=10)
# Now let's try analyzing the distributed load:
model.staticAnalysis(2,analysis_name='distributed load')
# Let's see what results we get for the distributed load:
model.plotDeformedModel(analysis_name='distributed load',\
figName='Distributed Load Analysis',numXSects=8,contour='VonMis',\
contLim=[0,1e5],warpScale=50,displScale=10)
xsect = sbeam1.xsect
model = Model()
model.addAircraftParts([wing1])
model.plotRigidModel(numXSects=10)
# Apply the constraint for the model
model.applyConstraints(0, 'fix')
# CASE 1:
# Apply the case load
tipLoad = np.array([-10000., 100000., -300000., 35000., 60000., 10000.])
F = {40: tipLoad}
model.applyLoads(1, F=F)
# Run the analysis
model.staticAnalysis(1)
model.plotDeformedModel(figName='V8 Case 1',numXSects=10,contLim=[0,293000],\
warpScale=10,displScale=2,contour='sig_33')
# Write the beam displacements and rotations to a file
sbeam1.writeDisplacements(fileName='V8_Case_1.csv')
# CASE 2:
# Apply the case load
def f(x):
vx = -0.1 * (-1.0e3 * x[2]**2 + 6e7 * x[2] + 1.0e6)
vy = (-1.0e3 * x[2]**2 + 6e7 * x[2] + 1.0e6)
pz = 0
tz = .2 * c * (-1.0e3 * x[2]**2 + 6e7 * x[2] + 1.0e6)
xsect = sbeam1.xsect
model = Model()
model.addAircraftParts([wing1])
model.plotRigidModel(numXSects=10)
# Apply the constraint for the model
model.applyConstraints(0,'fix')
# CASE 1:
# Apply the case load
tipLoad = np.array([-10000.,100000.,-300000.,35000.,60000.,10000.])
F = {40:tipLoad}
model.applyLoads(1,F=F)
# Run the analysis
model.staticAnalysis(1)
model.plotDeformedModel(figName='V8 Case 1',numXSects=10,contLim=[0,293000],\
warpScale=10,displScale=2,contour='sig_33')
# Write the beam displacements and rotations to a file
sbeam1.writeDisplacements(fileName = 'V8_Case_1.csv')
# CASE 2:
# Apply the case load
def f(x):
vx = -0.1*(-1.0e3*x[2]**2+6e7*x[2]+1.0e6)
vy = (-1.0e3*x[2]**2+6e7*x[2]+1.0e6)
pz = 0
tz = .2*c*(-1.0e3*x[2]**2+6e7*x[2]+1.0e6)
return np.array([vx,vy,pz,0,0,tz])/1.0e4
