def GetFlow(self):
'''
Calculating inlet flow (coefficients of the FFT x(t)=A0+sum(2*Ck*exp(j*k*2*pi*f*t)))
Timestep and period from SimulationContext are necessary.
'''
try:
timestep = self.SimulationContext.Context['timestep']
except KeyError:
print "Error, Please set timestep in Simulation Context XML File"
raise
try:
period = self.SimulationContext.Context['period']
except KeyError:
print "Error, Please set period in Simulation Context XML File"
raise
t = arange(0.0,period+timestep,timestep).reshape((1,ceil(period/timestep+1.0)))
Cc = self.f_coeff*1.0/2.0*1e-6
Flow = zeros((1, ceil(period/timestep+1.0)))
for freq in arange(0,ceil(period/timestep+1.0)):
Flow[0, freq] = self.A0_v
for k in arange(0,self.f_coeff.shape[0]):
Flow[0, freq] = Flow[0, freq]+real(2.0*complex(Cc[k,0],Cc[k,1])*exp(1j*(k+1)*2.0*pi*t[0,freq]/period))
self.Flow = Flow
return Flow
def find_distn(lgbinwidth, numlgbins, transient, N, M_t, M_i):
totspkhist = zeros((numlgbins, 1))
skiptime = transient * ms
skipbin = int(ceil(skiptime / lgbinwidth))
for i in xrange(numlgbins):
step_start = (i) * lgbinwidth #30*ms #
step_end = (i + 1) * lgbinwidth #30*ms #
for j in xrange(N):
#spks=where(logical_and(M[j]>step_start, M[j]<step_end))
#totspkhist[i]+=len(M[j][spks])
totspkhist[i] += len(M_i[logical_and(M_t > step_start,
M_t < step_end)])
#totspkhist_1D=reshape(totspkhist,len(totspkhist))
###smooth plot first so thresholds work better
#b,a=butter(3,0.4,'low')
#totspkhist_smooth=filtfilt(b,a,totspkhist_1D)
totspkhist_smooth = reshape(
totspkhist, len(totspkhist)
) #here we took out the actual smoothing and left it as raw distn.
#create distn based on hist, but skip first skiptime to cut out transient excessive spiking
if max(totspkhist_smooth[skipbin:]) > 0:
totspkdist_smooth = totspkhist_smooth / max(
totspkhist_smooth[skipbin:])
else:
totspkdist_smooth = totspkhist_smooth
totspkhist_list = [val for subl in totspkhist for val in subl]
return [totspkhist, totspkdist_smooth, totspkhist_list]
def plot_KLDiv_with_logscale(series):
length = len(series)
fig = plt.figure()
ax = fig.gca()
ax.set_xticks(np.arange(0, float(len(series))), 1)
ymin = min(series)
ymax = max(series)
ymin = floor(ymin * 10) / 10
ymax = ceil(ymax * 10) / 10
ax.set_yticks(np.arange(ymin, ymax, 0.1))
plt.axis([0, length - 1, ymin, ymax])
fontProperties = {'family': 'sans-serif', 'sans-serif': ['Helvetica'],
'weight': 'normal', 'size': 20}
rc('text', usetex=True)
rc('font', **fontProperties)
# ax.set_xticklabels([r'$\frac{%d}{%d}$' % (i+1, length-i) for i in range(length)], fontProperties)
plt.grid()
a = plt.axes() # plt.axis([0, length-1, ymin, ymax])
plt.yscale('log')
c = CVALUE[COLORS[0]]
m = MARKERS[0]
plt.plot(list(range(len(series))), series, '-', marker=m, color=c, linewidth=2.5,
markersize=12, fillstyle='full', label='Label')
c = CVALUE[COLORS[1]]
m = MARKERS[1]
plt.plot(list(range(len(series))), series, '-', marker=m, color=c, linewidth=2.5,
markersize=12, fillstyle='full', label='Label')
plt.legend(loc="best")
plt.ylabel(r'$F_1$')
plt.xlabel(r'$k$')
def plot_fscores(labels, series):
length = max(list(map(len, series)))
fig = plt.figure()
ax = fig.gca()
ax.set_xticks(np.arange(0, float(len(series))), 1)
ymin = min(list(map(min, series)))
ymax = max(list(map(max, series)))
ymin = floor(ymin * 10) / 10
ymax = ceil(ymax * 10) / 10
ax.set_yticks(np.arange(ymin, ymax, 0.1))
plt.axis([0, length - 1, ymin, ymax])
fontProperties = {'family': 'sans-serif', 'sans-serif': ['Helvetica'],
'weight': 'normal', 'size': 20}
rc('text', usetex=True)
rc('font', **fontProperties)
ax.set_xticklabels(
[r'$\frac{%d}{%d}$' % (i + 1, length - i) for i in range(length)],
fontProperties)
plt.grid()
for i, [l, s] in enumerate(zip(labels, series)):
c = CVALUE[COLORS[i]]
plt.plot(list(range(len(s))), s, '-', marker=MARKERS[i], color=c,
linewidth=2.5, markersize=12, fillstyle='full', label=l)
plt.legend(loc="best")
plt.ylabel(r'$F_1$')
plt.xlabel(r'$k$')
def calcPhonemeDurations(self):
'''
rule-based assignment of durations using Initial-Middle-final rules
all consonant durations set to CONSONANT_DURATION
'''
cofficinetTempo = 1
if self.phonemes is None:
self.expandToPhonemes()
if self.getNumPhonemes() == 0:
sys.exit("syllable with no phonemes!")
return
#copy to local var
consonant_duration = ParametersAlgo.CONSONANT_DURATION
# Workaraound: reduce consonant durationInMinUnit for syllables with very short note value.
while (self.getNumPhonemes() - 1) * consonant_duration >= self.durationInNumFrames:
logger.warning("Syllable {} has very short durationInMinUnit: {} . reducing the fixed durationInMinUnit of consonants".format(self.text, self.durationInMinUnit) )
consonant_duration /=2
#################
## assign durations
#############
initPhoneme = self.phonemes[0]
finalPhoneme = self.phonemes[-1]
#
if not initPhoneme.isVowel(): # initial is consonant
initPhoneme.durationInNumFrames = consonant_duration
if not finalPhoneme.isVowel(): # final is consonant
finalPhoneme.durationInNumFrames = consonant_duration
# assign middle
for currPhoneme in self.phonemes[1:-1]:
currPhoneme.durationInNumFrames = (self.durationInNumFrames - 2 * consonant_duration) / len(self.phonemes[1:-1])
else: # final is vowel
dur = (self.durationInNumFrames - float(consonant_duration) ) / len(self.phonemes[1:])
ceilDur = int(ceil(dur))
# assign middle
for currPhoneme in self.phonemes[1:-1]:
currPhoneme.durationInNumFrames = ceilDur
finalPhoneme.durationInNumFrames = self.durationInNumFrames - (len(self.phonemes[1:-1]) * ceilDur)
else: # initial is vowel
if not finalPhoneme.isVowel():
finalPhoneme.durationInNumFrames = consonant_duration
# assign middle
for currPhoneme in self.phonemes[:-1]:
currPhoneme.durationInNumFrames = (self.durationInNumFrames - consonant_duration) / len(self.phonemes[:-1])
else: # final is vowel
# assign middle
for currPhoneme in self.phonemes:
currPhoneme.durationInNumFrames = self.durationInNumFrames / len(self.phonemes)
def get_mean(self, frac=1):
# frac between 0 and 1. 0 means take last element, 1 means take all, 5 means take half
if frac <= 0:
return list(self.samples)[-1]
if frac >= 1:
return np.mean(list(self.samples), 0)
#else
nr = int(max(1, ceil(len(self.samples) / frac)))
return np.mean(list(self.samples)[-nr:], 0)
def get_selbins(grids, inds, c_pts, bbox):
return np.minimum( grids,
np.maximum( 1,
ceil(
(c_pts[inds,:] -
np.tile(np.matrix([bbox[0], bbox[1]]),(len(inds),1)))/
np.tile(np.matrix([(bbox[2]-1)/grids, (bbox[3]-1)/grids]),(len(inds),1))
)
)
);
def get_mean(self,frac=1):
# frac between 0 and 1. 0 means take last element, 1 means take all, 5 means take half
if frac<=0:
return list(self.samples)[-1]
if frac>=1:
return np.mean(list(self.samples),0)
#else
nr = int(max(1,ceil(len(self.samples)/frac)))
return np.mean(list(self.samples)[-nr:],0)
def calcPhonemeDurations(self):
'''
rule-based assignment of durations using Initial-Middle-final rules
all consonant durations set to CONSONANT_DURATION
'''
cofficinetTempo = 1
if self.phonemes is None:
self.expandToPhonemes()
if self.getNumPhonemes() == 0:
sys.exit("syllable with no phonemes!")
return
#copy to local var
consonant_duration = ParametersAlgo.CONSONANT_DURATION
# Workaraound: reduce consonant durationInMinUnit for syllables with very short note value.
while (self.getNumPhonemes() - 1) * consonant_duration >= self.durationInNumFrames:
logger.warn("Syllable {} has very short durationInMinUnit: {} . reducing the fixed durationInMinUnit of consonants".format(self.text, self.durationInMinUnit) )
consonant_duration /=2
#################
## assign durations
#############
initPhoneme = self.phonemes[0]
finalPhoneme = self.phonemes[-1]
#
if not initPhoneme.isVowel(): # initial is consonant
initPhoneme.durationInNumFrames = consonant_duration
if not finalPhoneme.isVowel(): # final is consonant
finalPhoneme.durationInNumFrames = consonant_duration
for currPhoneme in self.phonemes[1:-1]:
currPhoneme.durationInNumFrames = (self.durationInNumFrames - 2 * consonant_duration) / len(self.phonemes[1:-1])
else: # final is vowel
dur = (self.durationInNumFrames - float(consonant_duration) ) / len(self.phonemes[1:])
ceilDur = int(ceil(dur))
for currPhoneme in self.phonemes[1:-1]:
currPhoneme.durationInNumFrames = ceilDur
finalPhoneme.durationInNumFrames = self.durationInNumFrames - (len(self.phonemes[1:-1]) * ceilDur)
else: # initial is vowel
if not finalPhoneme.isVowel():
finalPhoneme.durationInNumFrames = consonant_duration
for currPhoneme in self.phonemes[:-1]:
currPhoneme.durationInNumFrames = (self.durationInNumFrames - consonant_duration) / len(self.phonemes[:-1])
else: # final is vowel
for currPhoneme in self.phonemes:
currPhoneme.durationInNumFrames = self.durationInNumFrames / len(self.phonemes)
def generate_poisson_tex(params):
seed = params.seed
# TODO: select seed
length = params.length
cell_size = params.cell_size
sigma = params.smoothing_sigma
intensity = params.intensity
buffer_len = int(ceil(length / cell_size))
cell_size = (1.0 * length) / buffer_len
buffer = zeros(shape=(buffer_len,))
def generate_inverted_colors_sequence(length):
colors = zeros(shape=(length,))
for i in range(length):
colors[i] = i % 2
return colors
def generate_random_colors_sequence(length):
return numpy.random.rand(length)
events = generate_poisson_events(intensity, length)
colors = generate_random_colors_sequence(len(events))
current_event = 0
for i in xrange(buffer_len):
current_time = i * cell_size
if current_event < len(events) - 1 and current_time > events[current_event]: # XXX
current_event += 1
buffer[i] = colors[current_event]
tail = 4 * sigma
gaussian_filter_len = int(ceil(tail / cell_size))
xcoord = linspace(-tail, tail, gaussian_filter_len)
gaussian_filter = numpy.exp(-xcoord ** 2 / (2 * sigma ** 2))
gaussian_filter = gaussian_filter / gaussian_filter.sum()
buffer = loop_convolve(buffer, gaussian_filter)
return Texture(buffer=buffer, cell_size=cell_size)
def middleEdge(v,w,sigma = 5):
n = len(v)
m = len(w)
m_mid = int(ceil(m/2))
s = [-sigma*i for i in range(n)]
for j in range(1,m_mid+1):
s_back = s
s = [0 for i in range(n) ]
for i in range(1,n):
sg = s_back[i-1] + blosum62[(v[i-1],w[j-1])]
sd = s[i-1] - sigma
sr = s_back[i] - sigma
s[i] = max(sg,sd,sr)
sm = -65535
smi = 0
for i in range(n):
if s[i]>sm:
sm = s[i]
smi = i
x = (smi,j)
s_back = s
for i in range(1,n):
sg = s_back[i-1] + blosum62[(v[i-1],w[j-1])]
sd = s[i-1] - sigma
sr = s_back[i] - sigma
s[i] = max(sg,sd,sr)
sd = s_back[smi+1]
sr = s[smi]
sg = s[smi+1]
s_max = max(sd,sg,sr)
if s_max == sd:
y = (smi+1,j)
elif s_max == sr:
y = (smi,j+1)
else:
y= (smi+1,j+1)
return x,y
def Solve(self):
'''
This method builds System Matrix and gets Solution
'''
if self.SimulationContext.Id != self.NetworkMesh.Id:
raise self.SimulationContext.XMLIdError()
try:
self.TimeStep = self.SimulationContext.Context['timestep']
self.SquareTimeStep = self.TimeStep*self.TimeStep
except KeyError:
print "Error, Please set timestep in Simulation Context XML File"
raise
try:
self.Period = self.SimulationContext.Context['period']
self.TimeStepFreq = int(self.Period/self.TimeStep)
except KeyError:
print "Error, Please set period in Simulation Context XML File"
raise
try:
self.Cycles = self.SimulationContext.Context['cycles']
self.NumberOfIncrements = (self.Cycles*self.TimeStepFreq)
except KeyError:
print "Error, Please set cycles number in Simulation Context XML File"
raise
history = []
assembler = Assembler()
assembler.SetNetworkMesh(self.NetworkMesh)
assembler.SetBoundaryConditions(self.BoundaryConditions)
info = {'dofmap':assembler.DofMap,'solution':None,'incrementNumber':self.IncrementNumber,'history':history}
self.Evaluator.SetInfo(info)
self.PrescribedPressures = assembler.AssembleBoundaryConditions(self.SimulationContext)
self.LinearZeroOrderGlobalMatrix, self.LinearFirstOrderGlobalMatrix, self.LinearSecondOrderGlobalMatrix = \
assembler.AssembleInit(self.SimulationContext, self.Evaluator)
self.ZeroOrderGlobalMatrix = assembler.ZeroOrderGlobalMatrix
self.FirstOrderGlobalMatrix = assembler.FirstOrderGlobalMatrix
self.SecondOrderGlobalMatrix = assembler.SecondOrderGlobalMatrix
NumberOfGlobalDofs = assembler.GetNumberOfGlobalDofs() # number of dofs
self.UnknownPressures = arange(0,NumberOfGlobalDofs).reshape(NumberOfGlobalDofs,1) # unknown pressures
self.UnknownPressures = delete(self.UnknownPressures, s_[self.PrescribedPressures[:,0]], axis=0)
PressuresMatrix = zeros((NumberOfGlobalDofs, self.NumberOfIncrements))
self.p = zeros((NumberOfGlobalDofs,1))
self.pt = zeros((NumberOfGlobalDofs,1))
self.ptt = zeros((NumberOfGlobalDofs,1))
self.dp = zeros((NumberOfGlobalDofs,1))
self.ddp = zeros((NumberOfGlobalDofs,1))
self.dpt = zeros((NumberOfGlobalDofs,1))
self.ddpt = zeros((NumberOfGlobalDofs,1))
self.fe = zeros((NumberOfGlobalDofs,1))
self.fet = zeros((NumberOfGlobalDofs,1))
self.dfe = zeros((NumberOfGlobalDofs,1))
self.dfet = zeros((NumberOfGlobalDofs,1))
self.fi = zeros((NumberOfGlobalDofs,1))
self.fit = zeros((NumberOfGlobalDofs,1))
self.sumv = zeros((NumberOfGlobalDofs,1))
sumvbk = zeros((NumberOfGlobalDofs,1))
nonLinear = False
for el in self.NetworkMesh.Elements:
if el.IsNonLinear() == True:
nonLinear = True
break
while self.IncrementNumber<=self.NumberOfIncrements:
icc = (self.IncrementNumber%self.TimeStepFreq)
if icc == 0:
icc = self.TimeStepFreq
#for flow in self.BoundaryConditions.elementFlow:
for el in self.BoundaryConditions.elementFlow:
if self.steady == True:
self.Flow = assembler.BoundaryConditions.GetSteadyFlow(el, self.TimeStep,icc*self.TimeStep)
else:
self.Flow = assembler.BoundaryConditions.GetTimeFlow(el, icc*self.TimeStep)
self.fe[assembler.FlowDof[el.Id]]= self.Flow
CoeffRelax = 0.9
nltol = self.nltol
self.pi = None
pI = None
sumvbk[:,:] = self.sumv[:,:]
counter = 0
while True:
#Build the algebric equation system for the increment
SystemMatrix = (2.0/self.TimeStep)*self.SecondOrderGlobalMatrix + self.FirstOrderGlobalMatrix + (self.TimeStep/2.0)*self.ZeroOrderGlobalMatrix #system matrix
RightVector = self.fe + (2.0/self.TimeStep)*dot(self.SecondOrderGlobalMatrix,(self.pt)) + dot(self.SecondOrderGlobalMatrix,(self.dpt)) - dot(self.ZeroOrderGlobalMatrix,(self.sumv))-(self.TimeStep/2.0)*dot(self.ZeroOrderGlobalMatrix,(self.pt)) # right hand side vector
#The reduced (partioned) system of equations is generated.
RightVector[:,:] = RightVector[:,:] - dot(SystemMatrix[:,self.PrescribedPressures[:,0]],self.PrescribedPressures[:,1:])
SystemMatrix = SystemMatrix[:,s_[self.UnknownPressures[:,0]]]
if SystemMatrix.shape[0]> 0.0:
SystemMatrix = SystemMatrix[s_[self.UnknownPressures[:,0]],:]
RightVector = RightVector[s_[self.UnknownPressures[:,0]],:]
#Unknown nodal point values are solved from this system.
# Prescribed nodal values are inserted in the solution vector.
Solution = solve(SystemMatrix,RightVector) # solutions, unknown pressures
self.p[self.UnknownPressures,0] = Solution[:,:]
self.p[self.PrescribedPressures[:,0],0] = self.PrescribedPressures[:,1]
#Calculating derivatives.
#Calculating internal nodal flow values.
self.dp = dot((2.0/self.TimeStep),(self.p-self.pt)) - self.dpt
self.ddp = dot((4.0/self.SquareTimeStep),(self.p-self.pt)) - dot((4.0/self.TimeStep),self.dpt) -self.ddpt
self.sumv = sumvbk + dot((self.TimeStep/2.0),(self.pt+self.p))
self.fi = dot(self.SecondOrderGlobalMatrix,(self.dp)) + dot(self.FirstOrderGlobalMatrix,(self.p)) + dot(self.ZeroOrderGlobalMatrix,(self.sumv))
if not nonLinear :
break
if self.pi == None:
self.pi = zeros((NumberOfGlobalDofs,1))
self.pi[:,:] = self.pt[:,:]
pI = CoeffRelax * self.p + self.pi * (1.0-CoeffRelax)
self.p[:,:] = pI[:,:]
den = norm(self.pi,Inf)
if den < 1e-12:
den = 1.0
nlerr = norm(self.p-self.pi,Inf) / den
info = {'dofmap':assembler.DofMap,'solution':[self.p, self.pt, self.ptt],'incrementNumber':self.IncrementNumber,'history':history}
self.Evaluator.SetInfo(info)
assembler.Assemble(self.SimulationContext, self.Evaluator, self.LinearZeroOrderGlobalMatrix, self.LinearFirstOrderGlobalMatrix, self.LinearSecondOrderGlobalMatrix)
self.ZeroOrderGlobalMatrix = assembler.ZeroOrderGlobalMatrix
self.FirstOrderGlobalMatrix = assembler.FirstOrderGlobalMatrix
self.SecondOrderGlobalMatrix = assembler.SecondOrderGlobalMatrix
#Dynamic nonlinear relaxing coefficient
if counter == 100:
print "relaxing..."
print nlerr, nltol, CoeffRelax
counter = 0
self.pi[:,:] = None
self.sumv[:,:] = sumvbk[:,:]
CoeffRelax *= 0.6
nltol *= 0.95
if nlerr < nltol:
nltol = self.nltol
counter = 0
break
counter+=1
self.pi[:,:] = self.p[:,:]
self.ptt[:,:] = self.pt[:,:]
self.pt[:,:] = self.p[:,:]
self.dpt[:,:] = self.dp[:,:]
self.ddpt[:,:] = self.ddp[:,:]
self.fet[:,:] = self.fe[:,:]
self.fit[:,:] = self.fi[:,:]
PressuresMatrix[:,(self.IncrementNumber-1)] = self.p[:,0]
history.insert(0,self.IncrementNumber)
history = history[:3]
if self.steady == True:
self.MinimumIncrementNumber = 0.01* self.NumberOfIncrements
if norm(self.fi-self.fe,Inf)<self.convergence and self.IncrementNumber > self.MinimumIncrementNumber:
self.IncrementNumber = self.NumberOfIncrements
else:
pass
if self.IncrementNumber==ceil(0.05*self.NumberOfIncrements):
print "->5%"
if self.IncrementNumber==ceil(0.25*self.NumberOfIncrements):
print "->25%"
if self.IncrementNumber==ceil(0.5*self.NumberOfIncrements):
print "->50%"
if self.IncrementNumber==ceil(0.70*self.NumberOfIncrements):
print "->70%"
if self.IncrementNumber==ceil(0.90*self.NumberOfIncrements):
print "->90%"
if self.IncrementNumber==ceil(0.99*self.NumberOfIncrements):
print "->99%"
self.IncrementNumber = self.IncrementNumber+1
self.EndIncrementTime = self.EndIncrementTime + self.TimeStep # increment
info = {'dofmap':assembler.DofMap,'solution':[self.p, self.pt, self.ptt],'incrementNumber':self.IncrementNumber,'history':history,'allSolution':PressuresMatrix}
self.Evaluator.SetInfo(info)
self.Solutions = PressuresMatrix
return PressuresMatrix
def createAdvDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, dfus, phiLE, dihedral, twist, xMAC25, etakf, strUID, yfus, xRoot, etaEng, tcRoot, tcTip):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
** Introduced a linear twist distribution from *0* at root to *twist* at tip
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param dfus: fuselage diameter [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf, dfus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
# trying to correct the commented statement that uses dfus. will try to use yfus
# length1 = dfus / 2.
length1 = yfus
length2 = (etakf * span / 2. - length1) / cos(sweep_rad) / cos(dihedral_rad)
length3 = span / 2.*(1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
twist = twist - 4.
twistgrad = twist / (span / 2.)
twist1 = twistgrad * length1
twist2 = twistgrad * etakf * (span / 2.)
twist3 = twist
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cKink, 1., cKink, 0., twist2, 0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cTip, 1., cTip, 0., twist3, 0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings, str(id) + '_Pos1', None, str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos2', str(id) + '_Sec1', str(id) + '_Sec2', length1, 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos3', str(id) + '_Sec2', str(id) + '_Sec3', length2, phiLE, dihedral, id)
createPositioning(myPositionings, str(id) + '_Pos4', str(id) + '_Sec3', str(id) + '_Sec4', length3, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
etafus = yfus / (span / 2.)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etafus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', etaFus=etafus, nRibs=nouterRibs, etaEng=etaEng, span=span / 2.)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', length1 / (span / 2.), etakf / cos(dihedral_rad), cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# Estimate ribNum of outer Rib
iRib = int(span * (0.85 - etaEng) / (2 * 0.8)) - 1
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', nRib=iRib)
# calc wing position
tauK = cTip / cKink
etar = dfus / span
# XN25F = calcXN25F(cRoot, span, phiLE, etar, etakf, tauK, taperRatio)
# xRoot.py = calcXRoot(xMAC25, XN25F)
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(valueOf_=str(xRoot)))
myWing.get_transformation().get_rotation().set_y(doubleBaseType(valueOf_=str(4.)))
def capacity_value(env, prediciton_value, cores_allocation_by_server):
capacity = int(maximum(int(ceil(round((prediciton_value / float(env.reference_value) / cores_allocation_by_server), 2))), int(env.min_instance_num)))
return capacity
def find_bursts(duration, dt, transient, N, M_t, M_i, max_freq):
base = 2 #round lgbinwidth to nearest 2 so will always divide into durations
expnum = 2.0264 * exp(-0.2656 * max_freq + 2.9288) + 5.7907
lgbinwidth = (int(base * round(
(-max_freq + 33) / base))) * ms #23-good for higher freq stuff
#lgbinwidth=(int(base*round((expnum)/base)))/1000 #use exptl based on some fit of choice binwidths
#lgbinwidth=10*ms
numlgbins = int(ceil(duration / lgbinwidth))
#totspkhist=zeros((numlgbins,1))
totspkhist = zeros(numlgbins)
#totspkdist_smooth=zeros((numlgbins,1))
skiptime = transient * ms
skipbin = int(ceil(skiptime / lgbinwidth))
inc_past_thresh = []
dec_past_thresh = []
#Create histogram given the bins calculated
for i in xrange(numlgbins):
step_start = (i) * lgbinwidth
step_end = (i + 1) * lgbinwidth
totspkhist[i] = len(M_i[logical_and(M_t > step_start, M_t < step_end)])
###smooth plot first so thresholds work better
#totspkhist_1D=reshape(totspkhist,len(totspkhist)) #first just reshape so single row not single colm
#b,a=butter(3,0.4,'low')
#totspkhist_smooth=filtfilt(b,a,totspkhist_1D)
#totspkhist_smooth=reshape(totspkhist,len(totspkhist)) #here we took out the actual smoothing and left it as raw distn. here just reshape so single row not single colm
totspkdist_smooth = totspkhist / max(
totspkhist[skipbin:]
) #create distn based on hist, but skip first skiptime to cut out transient excessive spiking
# ####### FOR MOVING THRESHOLD #################
## find points where increases and decreases over some threshold
dist_thresh = []
thresh_plot = []
mul_fac = 0.35
switch = 0 #keeps track of whether inc or dec last
elim_noise = 1 / (max_freq * 2.5 * Hz)
#For line 95, somehow not required in previous version?
#elim_noise_units = 1/(max_freq*Hz*2.5)
thresh_time = 5 / (max_freq) #capture 5 cycles
thresh_ind = int(floor(
(thresh_time / lgbinwidth) /
2)) #the number of indices on each side of the window
#dist_thresh moves with window capturing approx 5 cycles (need special cases for borders) Find where increases and decreases past threshold (as long as a certain distance apart, based on "elim_noise" which is based on avg freq of bursts
dist_thresh.append(
totspkdist_smooth[skipbin:skipbin + thresh_ind].mean(0) +
mul_fac * totspkdist_smooth[skipbin:skipbin + thresh_ind].std(0))
for i in xrange(1, numlgbins):
step_start = (i) * lgbinwidth
step_end = (i + 1) * lgbinwidth
#moving threshold
if i > (skipbin +
thresh_ind) and (i + thresh_ind) < len(totspkdist_smooth):
#print(totspkdist_smooth[i-thresh_ind:i+thresh_ind])
dist_thresh.append(
totspkdist_smooth[i - thresh_ind:i + thresh_ind].mean(0) +
mul_fac *
totspkdist_smooth[i - thresh_ind:i + thresh_ind].std(0))
elif (i + thresh_ind) >= len(totspkdist_smooth):
dist_thresh.append(totspkdist_smooth[-thresh_ind:].mean(0) +
mul_fac *
totspkdist_smooth[-thresh_ind:].std(0))
else:
dist_thresh.append(
totspkdist_smooth[skipbin:skipbin + thresh_ind].mean(0) +
mul_fac *
totspkdist_smooth[skipbin:skipbin + thresh_ind].std(0))
if (totspkdist_smooth[i - 1] <
dist_thresh[i]) and (totspkdist_smooth[i] >= dist_thresh[i]):
#inc_past_thresh.append(step_start-0.5*lgbinwidth)
if (inc_past_thresh): #there has already been at least one inc,
if (
abs(inc_past_thresh[-1] -
(step_start - 0.5 * lgbinwidth)) > elim_noise
) and switch == 0: #must be at least x ms apart (yHz), and it was dec last..
inc_past_thresh.append(
step_start - 0.5 * lgbinwidth
) #take lower point (therefore first) when increasing. Need to -0.5binwidth to adjust for shift between index of bin width and index of bin distn
#print (['incr=%f'%inc_past_thresh[-1]])
thresh_plot.append(dist_thresh[i])
switch = 1
else:
inc_past_thresh.append(
step_start - 0.5 * lgbinwidth
) #take lower point (therefore first) when increasing. Need to -0.5binwidth to adjust for shift between index of bin width and index of bin distn
thresh_plot.append(dist_thresh[i])
switch = 1 #keeps track of that it was inc. last
elif (totspkdist_smooth[i - 1] >=
dist_thresh[i]) and (totspkdist_smooth[i] < dist_thresh[i]):
# dec_past_thresh.append(step_end-0.5*lgbinwidth) #take lower point (therefore second) when decreasing
if (dec_past_thresh): #there has already been at least one dec
if (
abs(dec_past_thresh[-1] -
(step_end - 0.5 * lgbinwidth)) > elim_noise
) and switch == 1: #must be at least x ms apart (y Hz), and it was inc last
dec_past_thresh.append(
step_end - 0.5 * lgbinwidth
) #take lower point (therefore second) when decreasing
#print (['decr=%f'%dec_past_thresh[-1]])
switch = 0
else:
dec_past_thresh.append(
step_end - 0.5 * lgbinwidth
) #take lower point (therefore second) when decreasing
switch = 0 #keeps track of that it was dec last
if totspkdist_smooth[0] < dist_thresh[
0]: #if you are starting below thresh, then pop first inc. otherwise, don't (since will decrease first)
if inc_past_thresh: #if list is not empty
inc_past_thresh.pop(0)
#
#####################################################################
#
######### TO DEFINE A STATIC THRESHOLD AND FIND CROSSING POINTS
# dist_thresh=0.15 #static threshold
# switch=0 #keeps track of whether inc or dec last
# overall_freq=3.6 #0.9
# elim_noise=1/(overall_freq*5)#2.5)
#
#
# for i in xrange(1,numlgbins):
# step_start=(i)*lgbinwidth
# step_end=(i+1)*lgbinwidth
#
# if (totspkdist_smooth[i-1]<dist_thresh) and (totspkdist_smooth[i]>=dist_thresh): #if cross threshold (increasing)
# if (inc_past_thresh): #there has already been at least one inc,
# if (abs(dec_past_thresh[-1]-(step_start-0.5*lgbinwidth))>elim_noise) and switch==0: #must be at least x ms apart (yHz) from the previous dec, and it was dec last..
# inc_past_thresh.append(step_start-0.5*lgbinwidth) #take lower point (therefore first) when increasing. Need to -0.5binwidth to adjust for shift between index of bin width and index of bin distn
# #print (['incr=%f'%inc_past_thresh[-1]]) #-0.5*lgbinwidth
# switch=1
# else:
# inc_past_thresh.append(step_start-0.5*lgbinwidth) #take lower point (therefore first) when increasing. Need to -0.5binwidth to adjust for shift between index of bin width and index of bin distn
# switch=1 #keeps track of that it was inc. last
# elif (totspkdist_smooth[i-1]>=dist_thresh) and (totspkdist_smooth[i]<dist_thresh):
# if (dec_past_thresh): #there has already been at least one dec
# if (abs(inc_past_thresh[-1]-(step_end-0.5*lgbinwidth))>elim_noise) and switch==1: #must be at least x ms apart (y Hz) from the previous incr, and it was inc last
# dec_past_thresh.append(step_end-0.5*lgbinwidth) #take lower point (therefore second) when decreasing
# #print (['decr=%f'%dec_past_thresh[-1]])
# switch=0
# else:
# dec_past_thresh.append(step_end-0.5*lgbinwidth) #take lower point (therefore second) when decreasing
# switch=0 #keeps track of that it was dec last
#
#
# if totspkdist_smooth[0]<dist_thresh: #if you are starting below thresh, then pop first inc. otherwise, don't (since will decrease first)
# if inc_past_thresh: #if list is not empty
# inc_past_thresh.pop(0)
################################################################
###############################################################
######## DEFINE INTER AND INTRA BURSTS ########
#since always start with dec, intraburst=time points from 1st inc:2nd dec, from 2nd inc:3rd dec, etc.
#interburst=time points from 1st dec:1st inc, from 2nd dec:2nd inc, etc.
intraburst_time_ms_compound_list = []
interburst_time_ms_compound_list = []
intraburst_bins = [] #in seconds
interburst_bins = []
#print(inc_past_thresh)
if len(inc_past_thresh) < len(dec_past_thresh): #if you end on a decrease
for i in xrange(len(inc_past_thresh)):
intraburst_time_ms_compound_list.append(
arange(inc_past_thresh[i] / ms, dec_past_thresh[i + 1] / ms,
1)) #10 is timestep
interburst_time_ms_compound_list.append(
arange((dec_past_thresh[i] + dt) / ms,
(inc_past_thresh[i] - dt) / ms, 1)) #10 is timestep
intraburst_bins.append(inc_past_thresh[i])
intraburst_bins.append(dec_past_thresh[i + 1])
interburst_bins.append(dec_past_thresh[i])
interburst_bins.append(inc_past_thresh[i])
else: #if you end on an increase
for i in xrange(len(inc_past_thresh) - 1):
intraburst_time_ms_compound_list.append(
arange(inc_past_thresh[i] / ms, dec_past_thresh[i + 1] / ms,
1)) #10 is timestep
interburst_time_ms_compound_list.append(
arange((dec_past_thresh[i] + dt) / ms,
(inc_past_thresh[i] - dt) / ms, 1)) #10 is timestep
intraburst_bins.append(inc_past_thresh[i])
intraburst_bins.append(dec_past_thresh[i + 1])
interburst_bins.append(dec_past_thresh[i] + dt)
interburst_bins.append(inc_past_thresh[i] - dt)
if dec_past_thresh and inc_past_thresh: #if neither dec_past_thresh nor inc_past_thresh is empty
interburst_bins.append(dec_past_thresh[-1] +
dt) #will have one more inter than intra
interburst_bins.append(inc_past_thresh[-1] + dt)
interburst_bins = interburst_bins / second
intraburst_bins = intraburst_bins / second
intraburst_time_ms = [
num for elem in intraburst_time_ms_compound_list for num in elem
] #flatten list
interburst_time_ms = [
num for elem in interburst_time_ms_compound_list for num in elem
] #flatten list
num_intraburst_bins = len(
intraburst_bins
) / 2 #/2 since have both start and end points for each bin
num_interburst_bins = len(interburst_bins) / 2
intraburst_bins_ms = [x * 1000 for x in intraburst_bins]
interburst_bins_ms = [x * 1000 for x in interburst_bins]
######################################
#bin_s=[((inc_past_thresh-dec_past_thresh)/2+dec_past_thresh) for inc_past_thresh, dec_past_thresh in zip(inc_past_thresh,dec_past_thresh)]
bin_s = [((x - y) / 2 + y)
for x, y in zip(inc_past_thresh, dec_past_thresh)] / second
binpt_ind = [int(floor(x / lgbinwidth)) for x in bin_s]
########## FIND PEAK TO TROUGH AND SAVE VALUES ###################
########## CATEGORIZE BURSTING BASED ON PEAK TO TROUGH VALUES ###################
########## DISCARD BINPTS IF PEAK TO TROUGH IS TOO SMALL ###################
peaks = []
trough = []
peak_to_trough_diff = []
min_burst_size = 0.2 #defines a burst as 0.2 or larger.
for i in xrange(len(binpt_ind) - 1):
peaks.append(max(totspkdist_smooth[binpt_ind[i]:binpt_ind[i + 1]]))
trough.append(min(totspkdist_smooth[binpt_ind[i]:binpt_ind[i + 1]]))
peak_to_trough_diff = [
max_dist - min_dist for max_dist, min_dist in zip(peaks, trough)
]
#to delete all bins following any <min_burst_size
first_ind_not_burst = next(
(x[0] for x in enumerate(peak_to_trough_diff) if x[1] < 0.2), None)
# if first_ind_not_burst:
# del bin_s[first_ind_not_burst+1:] #needs +1 since bin_s has one additional value (since counts edges)
#to keep track of any bins <0.2 so can ignore in stats later
all_ind_not_burst = [
x[0] for x in enumerate(peak_to_trough_diff) if x[1] < 0.2
] #defines a burst as 0.2 or larger.
bin_ms = [x * 1000 for x in bin_s]
binpt_ind = [int(floor(x / lgbinwidth)) for x in bin_s]
#for moving threshold only
thresh_plot = []
thresh_plot = [dist_thresh[x] for x in binpt_ind]
#for static threshold
#thresh_plot=[dist_thresh]*len(bin_ms)
#
#
# bin_s=[((inc_past_thresh-dec_past_thresh)/2+dec_past_thresh) for inc_past_thresh, dec_past_thresh in zip(inc_past_thresh,dec_past_thresh)]
# bin_ms=[x*1000 for x in bin_s]
# thresh_plot=[]
# binpt_ind=[int(floor(x/lgbinwidth)) for x in bin_s]
# thresh_plot=[dist_thresh[x] for x in binpt_ind]
#
binpts = xrange(int(lgbinwidth * 1000 / 2),
int(numlgbins * lgbinwidth * 1000), int(lgbinwidth * 1000))
totspkhist_list = totspkhist.tolist(
) #[val for subl in totspkhist for val in subl]
#find first index after transient to see if have enough bins to do stats
bin_ind_no_trans = bisect.bisect(bin_ms, transient)
intrabin_ind_no_trans = bisect.bisect(intraburst_bins, transient /
1000) #transient to seconds
if intrabin_ind_no_trans % 2 != 0: #index must be even since format is ind0=start_bin, ind1=end_bin, ind2=start_bin, .... .
intrabin_ind_no_trans += 1
interbin_ind_no_trans = bisect.bisect(interburst_bins, transient / 1000)
if interbin_ind_no_trans % 2 != 0:
interbin_ind_no_trans += 1
return [
bin_s, bin_ms, binpts, totspkhist, totspkdist_smooth, dist_thresh,
totspkhist_list, thresh_plot, binpt_ind, lgbinwidth, numlgbins,
intraburst_bins, interburst_bins, intraburst_bins_ms,
interburst_bins_ms, intraburst_time_ms, interburst_time_ms,
num_intraburst_bins, num_interburst_bins, bin_ind_no_trans,
intrabin_ind_no_trans, interbin_ind_no_trans
]
def Solve(self):
'''
This method builds System Matrix and gets Solution
'''
if self.SimulationContext.Id != self.NetworkMesh.Id:
raise self.SimulationContext.XMLIdError()
try:
self.TimeStep = self.SimulationContext.Context['timestep']
self.SquareTimeStep = self.TimeStep * self.TimeStep
except KeyError:
print "Error, Please set timestep in Simulation Context XML File"
raise
try:
self.Period = self.SimulationContext.Context['period']
self.TimeStepFreq = int(self.Period / self.TimeStep)
except KeyError:
print "Error, Please set period in Simulation Context XML File"
raise
try:
self.Cycles = self.SimulationContext.Context['cycles']
self.NumberOfIncrements = (self.Cycles * self.TimeStepFreq)
except KeyError:
print "Error, Please set cycles number in Simulation Context XML File"
raise
history = []
assembler = Assembler()
assembler.SetNetworkMesh(self.NetworkMesh)
assembler.SetBoundaryConditions(self.BoundaryConditions)
info = {
'dofmap': assembler.DofMap,
'solution': None,
'incrementNumber': self.IncrementNumber,
'history': history
}
self.Evaluator.SetInfo(info)
self.PrescribedPressures = assembler.AssembleBoundaryConditions(
self.SimulationContext)
self.LinearZeroOrderGlobalMatrix, self.LinearFirstOrderGlobalMatrix, self.LinearSecondOrderGlobalMatrix = \
assembler.AssembleInit(self.SimulationContext, self.Evaluator)
self.ZeroOrderGlobalMatrix = assembler.ZeroOrderGlobalMatrix
self.FirstOrderGlobalMatrix = assembler.FirstOrderGlobalMatrix
self.SecondOrderGlobalMatrix = assembler.SecondOrderGlobalMatrix
NumberOfGlobalDofs = assembler.GetNumberOfGlobalDofs(
) # number of dofs
self.UnknownPressures = arange(0, NumberOfGlobalDofs).reshape(
NumberOfGlobalDofs, 1) # unknown pressures
self.UnknownPressures = delete(self.UnknownPressures,
s_[self.PrescribedPressures[:, 0]],
axis=0)
PressuresMatrix = zeros((NumberOfGlobalDofs, self.NumberOfIncrements))
self.p = zeros((NumberOfGlobalDofs, 1))
self.pt = zeros((NumberOfGlobalDofs, 1))
self.ptt = zeros((NumberOfGlobalDofs, 1))
self.dp = zeros((NumberOfGlobalDofs, 1))
self.ddp = zeros((NumberOfGlobalDofs, 1))
self.dpt = zeros((NumberOfGlobalDofs, 1))
self.ddpt = zeros((NumberOfGlobalDofs, 1))
self.fe = zeros((NumberOfGlobalDofs, 1))
self.fet = zeros((NumberOfGlobalDofs, 1))
self.dfe = zeros((NumberOfGlobalDofs, 1))
self.dfet = zeros((NumberOfGlobalDofs, 1))
self.fi = zeros((NumberOfGlobalDofs, 1))
self.fit = zeros((NumberOfGlobalDofs, 1))
self.sumv = zeros((NumberOfGlobalDofs, 1))
sumvbk = zeros((NumberOfGlobalDofs, 1))
nonLinear = False
for el in self.NetworkMesh.Elements:
if el.IsNonLinear() == True:
nonLinear = True
break
while self.IncrementNumber <= self.NumberOfIncrements:
icc = (self.IncrementNumber % self.TimeStepFreq)
if icc == 0:
icc = self.TimeStepFreq
#for flow in self.BoundaryConditions.elementFlow:
for el in self.BoundaryConditions.elementFlow:
if self.steady == True:
self.Flow = assembler.BoundaryConditions.GetSteadyFlow(
el, self.TimeStep, icc * self.TimeStep)
else:
self.Flow = assembler.BoundaryConditions.GetTimeFlow(
el, icc * self.TimeStep)
self.fe[assembler.FlowDof[el.Id]] = self.Flow
CoeffRelax = 0.9
nltol = self.nltol
self.pi = None
pI = None
sumvbk[:, :] = self.sumv[:, :]
counter = 0
while True:
#Build the algebric equation system for the increment
SystemMatrix = (
2.0 / self.TimeStep
) * self.SecondOrderGlobalMatrix + self.FirstOrderGlobalMatrix + (
self.TimeStep /
2.0) * self.ZeroOrderGlobalMatrix #system matrix
RightVector = self.fe + (2.0 / self.TimeStep) * dot(
self.SecondOrderGlobalMatrix, (self.pt)) + dot(
self.SecondOrderGlobalMatrix, (self.dpt)) - dot(
self.ZeroOrderGlobalMatrix,
(self.sumv)) - (self.TimeStep / 2.0) * dot(
self.ZeroOrderGlobalMatrix,
(self.pt)) # right hand side vector
#The reduced (partioned) system of equations is generated.
RightVector[:, :] = RightVector[:, :] - dot(
SystemMatrix[:, self.PrescribedPressures[:, 0]],
self.PrescribedPressures[:, 1:])
SystemMatrix = SystemMatrix[:, s_[self.UnknownPressures[:, 0]]]
if SystemMatrix.shape[0] > 0.0:
SystemMatrix = SystemMatrix[
s_[self.UnknownPressures[:, 0]], :]
RightVector = RightVector[s_[self.UnknownPressures[:, 0]], :]
#Unknown nodal point values are solved from this system.
# Prescribed nodal values are inserted in the solution vector.
Solution = solve(SystemMatrix,
RightVector) # solutions, unknown pressures
self.p[self.UnknownPressures, 0] = Solution[:, :]
self.p[self.PrescribedPressures[:, 0],
0] = self.PrescribedPressures[:, 1]
#Calculating derivatives.
#Calculating internal nodal flow values.
self.dp = dot((2.0 / self.TimeStep),
(self.p - self.pt)) - self.dpt
self.ddp = dot((4.0 / self.SquareTimeStep),
(self.p - self.pt)) - dot(
(4.0 / self.TimeStep), self.dpt) - self.ddpt
self.sumv = sumvbk + dot((self.TimeStep / 2.0),
(self.pt + self.p))
self.fi = dot(self.SecondOrderGlobalMatrix, (self.dp)) + dot(
self.FirstOrderGlobalMatrix,
(self.p)) + dot(self.ZeroOrderGlobalMatrix, (self.sumv))
if not nonLinear:
break
if self.pi == None:
self.pi = zeros((NumberOfGlobalDofs, 1))
self.pi[:, :] = self.pt[:, :]
pI = CoeffRelax * self.p + self.pi * (1.0 - CoeffRelax)
self.p[:, :] = pI[:, :]
den = norm(self.pi, Inf)
if den < 1e-12:
den = 1.0
nlerr = norm(self.p - self.pi, Inf) / den
info = {
'dofmap': assembler.DofMap,
'solution': [self.p, self.pt, self.ptt],
'incrementNumber': self.IncrementNumber,
'history': history
}
self.Evaluator.SetInfo(info)
assembler.Assemble(self.SimulationContext, self.Evaluator,
self.LinearZeroOrderGlobalMatrix,
self.LinearFirstOrderGlobalMatrix,
self.LinearSecondOrderGlobalMatrix)
self.ZeroOrderGlobalMatrix = assembler.ZeroOrderGlobalMatrix
self.FirstOrderGlobalMatrix = assembler.FirstOrderGlobalMatrix
self.SecondOrderGlobalMatrix = assembler.SecondOrderGlobalMatrix
#Dynamic nonlinear relaxing coefficient
if counter == 100:
print "relaxing..."
print nlerr, nltol, CoeffRelax
counter = 0
self.pi[:, :] = None
self.sumv[:, :] = sumvbk[:, :]
CoeffRelax *= 0.6
nltol *= 0.95
if nlerr < nltol:
nltol = self.nltol
counter = 0
break
counter += 1
self.pi[:, :] = self.p[:, :]
self.ptt[:, :] = self.pt[:, :]
self.pt[:, :] = self.p[:, :]
self.dpt[:, :] = self.dp[:, :]
self.ddpt[:, :] = self.ddp[:, :]
self.fet[:, :] = self.fe[:, :]
self.fit[:, :] = self.fi[:, :]
PressuresMatrix[:, (self.IncrementNumber - 1)] = self.p[:, 0]
history.insert(0, self.IncrementNumber)
history = history[:3]
if self.steady == True:
self.MinimumIncrementNumber = 0.01 * self.NumberOfIncrements
if norm(
self.fi - self.fe, Inf
) < self.convergence and self.IncrementNumber > self.MinimumIncrementNumber:
self.IncrementNumber = self.NumberOfIncrements
else:
pass
if self.IncrementNumber == ceil(0.05 * self.NumberOfIncrements):
print "->5%"
if self.IncrementNumber == ceil(0.25 * self.NumberOfIncrements):
print "->25%"
if self.IncrementNumber == ceil(0.5 * self.NumberOfIncrements):
print "->50%"
if self.IncrementNumber == ceil(0.70 * self.NumberOfIncrements):
print "->70%"
if self.IncrementNumber == ceil(0.90 * self.NumberOfIncrements):
print "->90%"
if self.IncrementNumber == ceil(0.99 * self.NumberOfIncrements):
print "->99%"
self.IncrementNumber = self.IncrementNumber + 1
self.EndIncrementTime = self.EndIncrementTime + self.TimeStep # increment
info = {
'dofmap': assembler.DofMap,
'solution': [self.p, self.pt, self.ptt],
'incrementNumber': self.IncrementNumber,
'history': history,
'allSolution': PressuresMatrix
}
self.Evaluator.SetInfo(info)
self.Solutions = PressuresMatrix
return PressuresMatrix
def createRibs(parent, parentUID, typeOfSeg, thickness=0.03, pitch=.8, nRibs=None, etaFus=0.2, etaEng=.3, span=17., fanDiameter=1.9, etaStrut=0.0, phi25 = 0.0):
'''
Used for generation of a ribs definition in the wing
@param parent: ComponentSegment object, ribsDefinition will be added here
@param thickness: thickness of the ribs
@param pitch: pitch of the ribs
@param typeOfSeg: either advDoubleTrapezoid or trapezoid
'''
myUID = parentUID + '_ribs'
ribsList = []
#===============================================================================
# Advanced Double Trapezoid
#===============================================================================
if typeOfSeg.lower() == 'advdoubletrapezoid':
myName = stringBaseType(valueOf_='wing_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material=myMaterial)
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribEnd = stringBaseType(valueOf_=parentUID + '_Spar_RS')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
#=======================================================================
# First set of 4 ribs inside the fuselage
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.0')
etaEnd = doubleBaseType(valueOf_=str(etaFus))
innerRibs = doubleBaseType(valueOf_= 4)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=innerRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_inner'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Second set outside of the fuselage up to the engine
#===============================================================
etaPylon = 1. / 10. * fanDiameter / span
etaStart = doubleBaseType(valueOf_=str(etaFus + pitch / span))
etaEnd = doubleBaseType(valueOf_=str(etaEng - etaPylon))
middleRibs = int(ceil((etaEng - etaPylon - etaFus) * span / pitch)) - 1
if middleRibs < 1:
middleRibs = 1
middleRibs = doubleBaseType(valueOf_=middleRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=middleRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_engine1'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Third set one ribs outside of the pylon
#===============================================================
etaEnd = doubleBaseType(valueOf_= str(etaEng + etaPylon))
pylonRibs = doubleBaseType(valueOf_= str(1))
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=pylonRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_engine2'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Fourth set outside of the engine
#===============================================================
etaStart = doubleBaseType(valueOf_= str(etaEng + etaPylon + pitch / span))
etaEnd = doubleBaseType(valueOf_= '0.95')
ribCrossing = ribCrossingBehaviourType(valueOf_='end')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='wing_Spar_FS'), \
z=doubleBaseType(valueOf_='90.'))
outerRibs = int(ceil((0.95 - etaEng + etaPylon) * span / pitch)) - 1
outerRibs = doubleBaseType(valueOf_= outerRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=outerRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_outer'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Strut Braced Wing
#===============================================================================
if typeOfSeg.lower() == 'strutbracedwing':
myName = stringBaseType(valueOf_='wing_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material=myMaterial)
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribEnd = stringBaseType(valueOf_=parentUID + '_Spar_RS')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
#=======================================================================
# First set of 4 ribs inside the fuselage
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.0')
etaEnd = doubleBaseType(valueOf_=str(etaFus))
innerRibs = doubleBaseType(valueOf_=4)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=innerRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_inner'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Second set outside of the fuselage up to the strut
#===============================================================
etaStart = doubleBaseType(valueOf_=str(etaFus + pitch / span + phi25 * 0.0002))
etaEnd = doubleBaseType(valueOf_=str(etaStrut))
middleRibs = int(ceil((etaStrut - etaFus) * span / pitch)) - 1
middleRibs = doubleBaseType(valueOf_=middleRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=middleRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_strut'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Third set outside of the spar
#===============================================================
etaStart = doubleBaseType(valueOf_=str(etaStrut + pitch / span))
etaEnd = doubleBaseType(valueOf_='0.95')
ribCrossing = ribCrossingBehaviourType(valueOf_='end')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='wing_Spar_FS'), z=doubleBaseType(valueOf_=str('90.')))
outerRibs = int(ceil((0.95 - etaStrut) * span / pitch)) - 1
outerRibs = doubleBaseType(valueOf_=outerRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=outerRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_outer'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Strut (And only the strut not the wing that goes along with it)
#===============================================================================
if typeOfSeg.lower() == 'strut':
myName = stringBaseType(valueOf_='strut_ribs')
# Rib Cross Section
#=======================================================================
#myMaterial = materialDefinitionType(compositeUID=stringUIDBaseType(isLink='True',valueOf_='Comp_Shear'), orthotropyDirection=doubleBaseType(valueOf_='0.'),\
# thicknessScaling=doubleBaseType(valueOf_='0.001'))
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material=myMaterial)
ribReference = stringBaseType(valueOf_='leadingEdge')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
etaStart = doubleBaseType(valueOf_=str(0.))
etaEnd = doubleBaseType(valueOf_=str(1.))
middleRibs = doubleBaseType(valueOf_=5.)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=middleRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Aileron
#===============================================================================
if typeOfSeg.lower() == 'aileron':
myName = stringBaseType(valueOf_='aileron_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material= myMaterial)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.')
etaEnd = doubleBaseType(valueOf_='1.')
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
if nRibs is None:
ribSpacing = doubleBaseType(valueOf_=pitch)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
spacing=ribSpacing, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
else:
nRibs = doubleBaseType(valueOf_=nRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=nRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
if typeOfSeg.lower() == 'trapezoid':
myName = stringBaseType(valueOf_='trapezoid_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material= myMaterial)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.')
etaEnd = doubleBaseType(valueOf_='1.')
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
middleRibs = doubleBaseType(valueOf_=5.)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=middleRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Flap
#===============================================================================
if typeOfSeg.lower() == 'flap' or typeOfSeg.lower() == 'innerflap':
myName = stringBaseType(valueOf_='flap_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material= myMaterial)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.')
etaEnd = doubleBaseType(valueOf_='1.')
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
if nRibs is None:
ribSpacing = doubleBaseType(valueOf_=pitch)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
spacing=ribSpacing, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
else:
nRibs = doubleBaseType(valueOf_=nRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=nRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Spoiler
#===============================================================================
if typeOfSeg.lower() == 'spoiler':
myName = stringBaseType(valueOf_='spoiler_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material= myMaterial)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.')
etaEnd = doubleBaseType(valueOf_='1.')
ribReference = stringBaseType(valueOf_='leadingEdge')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
if nRibs is None:
ribSpacing = doubleBaseType(valueOf_=pitch)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
spacing=ribSpacing, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
else:
nRibs = doubleBaseType(valueOf_=nRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=nRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#=======================================================================
# RibsDefinition
#=======================================================================
myRibsDefinitions = wingRibsDefinitionsType(None, None, None, ribsList)
parent.get_structure().set_ribsDefinitions(myRibsDefinitions)
def createAdvDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, dfus,
phiLE, dihedral, twist, xMAC25, etakf, strUID,
yfus, xRoot, etaEng, tcRoot, tcTip):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
** Introduced a linear twist distribution from *0* at root to *twist* at tip
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param dfus: fuselage diameter [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf, dfus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
# trying to correct the commented statement that uses dfus. will try to use yfus
# length1 = dfus / 2.
length1 = yfus
length2 = (etakf * span / 2. -
length1) / cos(sweep_rad) / cos(dihedral_rad)
length3 = span / 2. * (1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
twist = twist - 4.
twistgrad = twist / (span / 2.)
twist1 = twistgrad * length1
twist2 = twistgrad * etakf * (span / 2.)
twist3 = twist
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA0009', 1, strUID + '_Sec1',
strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA653218', 1, strUID + '_Sec2',
strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cKink, 1., cKink,
0., twist2, 0., 'NACA653218', 1, strUID + '_Sec3',
strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cTip, 1., cTip, 0.,
twist3, 0., 'NACA653218', 1, strUID + '_Sec4',
strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', length1, 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', length2, phiLE, dihedral, id)
createPositioning(myPositionings,
str(id) + '_Pos4',
str(id) + '_Sec3',
str(id) + '_Sec4', length3, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
etafus = yfus / (span / 2.)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etafus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
etaFus=etafus,
nRibs=nouterRibs,
etaEng=etaEng,
span=span / 2.)
createSpars(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
length1 / (span / 2.),
etakf / cos(dihedral_rad),
cTip=cTip,
cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'advDoubletrapezoid')
createWingFuselageAttachment(
myWing.get_componentSegments().get_componentSegment()[0], strUID,
'advDoubletrapezoid')
# Estimate ribNum of outer Rib
iRib = int(span * (0.85 - etaEng) / (2 * 0.8)) - 1
createTanks(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
nRib=iRib)
# calc wing position
tauK = cTip / cKink
etar = dfus / span
# XN25F = calcXN25F(cRoot, span, phiLE, etar, etakf, tauK, taperRatio)
# xRoot.py = calcXRoot(xMAC25, XN25F)
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(
doubleBaseType(None, None, None, str(xRoot)))
myWing.get_transformation().get_rotation().set_y(
doubleBaseType(None, None, None, str(4.)))
def createRibs(parent,
parentUID,
typeOfSeg,
thickness=0.03,
pitch=.8,
nRibs=None,
etaFus=0.2,
etaEng=.3,
span=17.,
fanDiameter=1.9,
etaStrut=0.0,
phi25=0.0):
'''
Used for generation of a ribs definition in the wing
@param parent: ComponentSegment object, ribsDefinition will be added here
@param thickness: thickness of the ribs
@param pitch: pitch of the ribs
@param typeOfSeg: either advDoubleTrapezoid or trapezoid
'''
myUID = parentUID + '_ribs'
ribsList = []
#===============================================================================
# Advanced Double Trapezoid
#===============================================================================
if typeOfSeg.lower() == 'advdoubletrapezoid':
myName = stringBaseType(None, None, None, 'wing_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium7075'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribEnd = stringBaseType(None, None, None, parentUID + '_Spar_RS')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
#=======================================================================
# First set of 4 ribs inside the fuselage
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.0')
etaEnd = doubleBaseType(None, None, None, str(etaFus))
innerRibs = doubleBaseType(None, None, None, 4)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, innerRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_inner'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Second set outside of the fuselage up to the engine
#===============================================================
etaPylon = 1. / 10. * fanDiameter / span
etaStart = doubleBaseType(None, None, None, str(etaFus + pitch / span))
etaEnd = doubleBaseType(None, None, None, str(etaEng - etaPylon))
middleRibs = int(ceil((etaEng - etaPylon - etaFus) * span / pitch)) - 1
if middleRibs < 1:
middleRibs = 1
middleRibs = doubleBaseType(None, None, None, middleRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, middleRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_engine1'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Third set one ribs outside of the pylon
#===============================================================
etaEnd = doubleBaseType(None, None, None, str(etaEng + etaPylon))
pylonRibs = doubleBaseType(None, None, None, str(1))
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaEnd, etaEnd, ribStart, ribEnd, \
None, pylonRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_engine2'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Fourth set outside of the engine
#===============================================================
etaStart = doubleBaseType(None, None, None,
str(etaEng + etaPylon + pitch / span))
etaEnd = doubleBaseType(None, None, None, '0.95')
ribCrossing = ribCrossingBehaviourType(None, None, None, 'end')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'wing_Spar_FS'), \
doubleBaseType(None, None, None, '90.'))
outerRibs = int(ceil((0.95 - etaEng + etaPylon) * span / pitch)) - 1
outerRibs = doubleBaseType(None, None, None, outerRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, outerRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_outer'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Strut Braced Wing
#===============================================================================
if typeOfSeg.lower() == 'strutbracedwing':
myName = stringBaseType(None, None, None, 'wing_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium7075'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribEnd = stringBaseType(None, None, None, parentUID + '_Spar_RS')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
#=======================================================================
# First set of 4 ribs inside the fuselage
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.0')
etaEnd = doubleBaseType(None, None, None, str(etaFus))
innerRibs = doubleBaseType(None, None, None, 4)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, innerRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_inner'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Second set outside of the fuselage up to the strut
#===============================================================
etaStart = doubleBaseType(None, None, None,
str(etaFus + pitch / span + phi25 * 0.0002))
etaEnd = doubleBaseType(None, None, None, str(etaStrut))
middleRibs = int(ceil((etaStrut - etaFus) * span / pitch)) - 1
middleRibs = doubleBaseType(None, None, None, middleRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, middleRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_strut'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Third set outside of the spar
#===============================================================
etaStart = doubleBaseType(None, None, None,
str(etaStrut + pitch / span))
etaEnd = doubleBaseType(None, None, None, '0.95')
ribCrossing = ribCrossingBehaviourType(None, None, None, 'end')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'wing_Spar_FS'), \
doubleBaseType(None, None, None, '90.'))
outerRibs = int(ceil((0.95 - etaStrut) * span / pitch)) - 1
outerRibs = doubleBaseType(None, None, None, outerRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, outerRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_outer'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Strut (And only the strut not the wing that goes along with it)
#===============================================================================
if typeOfSeg.lower() == 'strut':
myName = stringBaseType(None, None, None, 'strut_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(compositeUID=stringUIDBaseType(isLink='True',valueOf_='Comp_Shear'), orthotropyDirection=doubleBaseType(valueOf_='0.'),\
thicknessScaling=doubleBaseType(valueOf_='0.001'))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
ribReference = stringBaseType(None, None, None, 'leadingEdge')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
etaStart = doubleBaseType(None, None, None, str(0.001))
etaEnd = doubleBaseType(None, None, None, str(0.999))
#middleRibs = int(ceil(span / 0.70)) - 1
middleRibs = doubleBaseType(None, None, None, 5.)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, middleRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Aileron
#===============================================================================
if typeOfSeg.lower() == 'aileron':
myName = stringBaseType(None, None, None, 'aileron_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium2024'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.')
etaEnd = doubleBaseType(None, None, None, '1.')
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
if nRibs is None:
ribSpacing = doubleBaseType(None, None, None, pitch)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
ribSpacing, None, ribCrossing, ribRotation)
else:
nRibs = doubleBaseType(None, None, None, nRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, nRibs, ribCrossing, ribRotation)
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
if typeOfSeg.lower() == 'trapezoid':
myName = stringBaseType(None, None, None, 'trapezoid_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium2024'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.')
etaEnd = doubleBaseType(None, None, None, '1.')
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
etaStart = doubleBaseType(None, None, None, str(0.0))
etaEnd = doubleBaseType(None, None, None, str(0.95))
middleRibs = doubleBaseType(None, None, None, 5.)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, middleRibs, ribCrossing, ribRotation)
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Flap
#===============================================================================
if typeOfSeg.lower() == 'flap' or typeOfSeg.lower() == 'innerflap':
myName = stringBaseType(None, None, None, 'flap_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium2024'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.')
etaEnd = doubleBaseType(None, None, None, '1.')
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
if nRibs is None:
ribSpacing = doubleBaseType(None, None, None, pitch)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
ribSpacing, None, ribCrossing, ribRotation)
else:
nRibs = doubleBaseType(None, None, None, nRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, nRibs, ribCrossing, ribRotation)
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Spoiler
#===============================================================================
if typeOfSeg.lower() == 'spoiler':
myName = stringBaseType(None, None, None, 'spoiler_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium2024'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.')
etaEnd = doubleBaseType(None, None, None, '1.')
ribReference = stringBaseType(None, None, None, 'leadingEdge')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'leadingEdge'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
if nRibs is None:
ribSpacing = doubleBaseType(None, None, None, pitch)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
ribSpacing, None, ribCrossing, ribRotation)
else:
nRibs = doubleBaseType(None, None, None, nRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, nRibs, ribCrossing, ribRotation)
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#=======================================================================
# RibsDefinition
#=======================================================================
myRibsDefinitions = wingRibsDefinitionsType(None, None, None, ribsList)
parent.get_structure().set_ribsDefinitions(myRibsDefinitions)
