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aseredesign/aseredesign.py
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@ -1,353 +1,350 @@
import math import math
import csv import csv
from colorama import just_fix_windows_console from colorama import just_fix_windows_console
just_fix_windows_console() just_fix_windows_console()
from colorama import Fore, Back, Style from colorama import Fore, Back, Style
# #
# HELLO MODIFY THIS! # HELLO MODIFY THIS!
# #
#Hello there! Modify this! #Hello there! Modify this!
#INITIAL SET UP #INITIAL SET UP
Ebasis = 65500.00 Ebasis = 65500.00
mass_limit = 28.000 mass_limit = 28.000
#MODIFY THIS EVERY NEW ITERATION #MODIFY THIS EVERY NEW ITERATION
modAmount = 2 # amount of results you want to iterate through (starts at panel_val_0 and goes to this value minus one) modAmount = 2 # amount of results you want to iterate through (starts at panel_val_0 and goes to this value minus one)
# So the highest x of panel_val_x with one added to it. (modAmount = 1 only runs panel_val_0, modAmount = 3 runs through panel_val_0, 1 and 2) # So the highest x of panel_val_x with one added to it. (modAmount = 1 only runs panel_val_0, modAmount = 3 runs through panel_val_0, 1 and 2)
# 0, 1, 2, 3, 4, 5, 6, 7, 8, 9,10,11,12,13,14,15,16 # 0, 1, 2, 3, 4, 5, 6, 7, 8, 9,10,11,12,13,14,15,16
pThickness_01 = [ 4, 5] # panel 1 and 10 pThickness_01 = [ 4, 5] # panel 1 and 10
pThickness_02 = [ 4, 5] # panel 2 and 9 pThickness_02 = [ 4, 5] # panel 2 and 9
pThickness_03 = [ 4, 5] # panel 3 and 8 pThickness_03 = [ 4, 5] # panel 3 and 8
pThickness_04 = [ 4, 5] # panel 4 and 7 pThickness_04 = [ 4, 5] # panel 4 and 7
pThickness_05 = [ 4, 6] # panel 5 and 6 pThickness_05 = [ 4, 6] # panel 5 and 6
# 0, 1, 2, 3, 4, 5, 6, 7, 8, 9,10,11,12,13,14,15,16 # 0, 1, 2, 3, 4, 5, 6, 7, 8, 9,10,11,12,13,14,15,16
dim1_0 = [25,70] dim1_0 = [25,70]
dim2_0 = [ 2, 2] dim2_0 = [ 2, 2]
dim3_0 = [20,10] dim3_0 = [20,10]
dim4_0 = [15,15] dim4_0 = [15,15]
# BELOW THIS NOTHING NEEDS TO BE MODIFIED # BELOW THIS NOTHING NEEDS TO BE MODIFIED
def GetValueofElement(ElementID, Loadcase, Valuetype, Fileadress): def GetValueofElement(ElementID, Loadcase, Valuetype, Fileadress):
FindTitle = False FindTitle = False
intiated = False intiated = False
with open(Fileadress, newline='') as csvfile: with open(Fileadress, newline='') as csvfile:
reader = csv.reader(csvfile, delimiter=',', quotechar="'") reader = csv.reader(csvfile, delimiter=',', quotechar="'")
for row in reader: for row in reader:
values = row values = row
#print(values) #print(values)
if intiated: if intiated:
if str(values[ElemID_ID]) == str(ElementID) and str(values[Loadcase_ID])==str(Loadcase): if str(values[ElemID_ID]) == str(ElementID) and str(values[Loadcase_ID])==str(Loadcase):
return float(values[Value_ID])*1.5 #Safety Factor here!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!! return float(values[Value_ID])*1.5 #Safety Factor here!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!
if FindTitle: if FindTitle:
#print(str(values)) #print(str(values))
Header = values Header = values
ElemID_ID = Header.index("Elements") ElemID_ID = Header.index("Elements")
Loadcase_ID = Header.index("Loadcase") Loadcase_ID = Header.index("Loadcase")
Value_ID = Header.index(Valuetype) Value_ID = Header.index(Valuetype)
FindTitle = False FindTitle = False
intiated = True intiated = True
if len(values)==0: if len(values)==0:
FindTitle=True FindTitle=True
return None return None
#CONSTANTS #CONSTANTS
axial = 'Element Stresses (1D):CBAR/CBEAM Axial Stress' axial = 'Element Stresses (1D):CBAR/CBEAM Axial Stress'
# material properties # material properties
sUlt = 530 sUlt = 530
sYield = 490 sYield = 490
density = 2.7 * (10 ** -6) #2.7*10^-9 in t/mm^3 density = 2.7 * (10 ** -6) #2.7*10^-9 in t/mm^3
pWidth_0 = [200,200,200,200,200,200,200,200,200,200,200,200,200,200] pWidth_0 = [200,200,200,200,200,200,200,200,200,200,200,200,200,200]
pLength_0 = [750,750,750,750,750,750,750,750,750,750,750,750,750] pLength_0 = [750,750,750,750,750,750,750,750,750,750,750,750,750]
def GetAvgStressofPanel(panelNo, Loadcase, ValueType): def GetAvgStressofPanel(panelNo, Loadcase, ValueType):
id = panelNo * 3 - 2 id = panelNo * 3 - 2
return (GetValueofElement(id, Loadcase, ValueType, panel) + GetValueofElement(id+1, Loadcase, ValueType, panel) + GetValueofElement(id+2, Loadcase, ValueType, panel))/(3*1.5) return (GetValueofElement(id, Loadcase, ValueType, panel) + GetValueofElement(id+1, Loadcase, ValueType, panel) + GetValueofElement(id+2, Loadcase, ValueType, panel))/(3*1.5)
def GetCombAvgStressofStringer(stringerNo, Loadcase): def GetCombAvgStressofStringer(stringerNo, Loadcase):
id = stringerNo * 3 - 3 + 40 id = stringerNo * 3 - 3 + 40
avgStringerStress = (GetValueofElement(id, Loadcase, axial, stringer) + GetValueofElement(id+1, Loadcase, axial, stringer) + GetValueofElement(id+2, Loadcase, axial, stringer))/(3*1.5) avgStringerStress = (GetValueofElement(id, Loadcase, axial, stringer) + GetValueofElement(id+1, Loadcase, axial, stringer) + GetValueofElement(id+2, Loadcase, axial, stringer))/(3*1.5)
leftPID = stringerNo leftPID = stringerNo
rightPID = stringerNo + 1 rightPID = stringerNo + 1
leftPStress = GetAvgStressofPanel(leftPID, Loadcase, 'XX') leftPStress = GetAvgStressofPanel(leftPID, Loadcase, 'XX')
rightPStress = GetAvgStressofPanel(rightPID, Loadcase, 'XX') rightPStress = GetAvgStressofPanel(rightPID, Loadcase, 'XX')
return((leftPStress * 0.5 * pThickness[stringerNo - 1] * pWidth + rightPStress * 0.5 * pThickness[stringerNo]*pWidth + avgStringerStress * areaStringer) / (areaStringer + 0.5*pThickness[stringerNo-1] * pWidth + 0.5 * pThickness[stringerNo]*pWidth)) return((leftPStress * 0.5 * pThickness[stringerNo - 1] * pWidth + rightPStress * 0.5 * pThickness[stringerNo]*pWidth + avgStringerStress * areaStringer) / (areaStringer + 0.5*pThickness[stringerNo-1] * pWidth + 0.5 * pThickness[stringerNo]*pWidth))
def GetAlpha(x):
if(0.4 <= x <= 1.095): def GetSigCrip(stringerNo, Loadcase): ## unfinished, need to understand x claulcation still a bit
alpha = 1.4 - 0.628 * x x = (dim1/dim2)*math.sqrt(sYield/(3.60*Ebasis))
elif(1.095 < x <= 1.633):
alpha = 0.78/x if(0.4 <= x <= 1.095):
elif(x > 1.633): alpha = 1.4 - 0.628 * x
alpha = 0.69/(x**0.75) elif(1.095 < x <= 1.633):
else: alpha = 0.78/x
alpha = 0 elif(x > 1.633):
return(alpha) alpha = 0.69/(x**0.75)
else:
def GetSigCrip(stringerNo, Loadcase): ## unfinished, need to understand x claulcation still a bit alpha = 1
#use b1 and b2 for calc
#E_c = Ebasis
#no alpha = 1 it is none -> what do then? -> ignore that element in averaging sigCrip12 = alpha * sYield
#averaging only with elements that cripple
#if nothing cripples, use yield strength x = (dim4/dim2)*math.sqrt(sYield/(3.60*Ebasis))
b1 = dim1 - dim2
b2 = dim3 - dim2 if(0.4 <= x <= 1.095):
alpha = 1.4 - 0.628 * x
x1 = (b1/dim2)*math.sqrt(sYield/(3.60*Ebasis)) elif(1.095 < x <= 1.633):
alpha = 0.78/x
alpha1 = GetAlpha(x1) elif(x > 1.633):
alpha = 0.69/(x**0.75)
#print("x12: " + str(x)) else:
sigCrip1 = alpha1 * sYield alpha = 1
x2 = (b2/dim2)*math.sqrt(sYield/(3.60*Ebasis))
sigCrip24 = alpha * sYield
alpha2 = GetAlpha(x2)
x = (dim3/dim2)*math.sqrt(sYield/(3.60*Ebasis))
sigCrip2 = alpha2 * sYield
if(0.4 <= x <= 1.095):
if(alpha1 != 0 and alpha2 != 0): alpha = 1.4 - 0.628 * x
sigCripAVG = (sigCrip1 * b1 * dim2 + sigCrip2 * b2 * dim2 * 2)/(b1 * dim2 + b2 * dim2 * 2) elif(1.095 < x <= 1.633):
elif(alpha1 != 0): alpha = 0.78/x
sigCripAVG = (sigCrip1 * b1 * dim2)/(b1 * dim2) elif(x > 1.633):
elif(alpha2 != 0): alpha = 0.69/(x**0.75)
sigCripAVG = (sigCrip2 * b2 * dim2)/(b2 * dim2) else:
else: alpha = 1
sigCripAVG = sYield
sigCrip23 = alpha * sYield
# average only over what can buckle!!! F/A, A = sumOf(bi*ti) # i know this is inefficient and shittily as hell!! its quick and dirty tho
return min(sigCripAVG, sYield) # TODO: FIX!!
sigCripAVG = (sigCrip12 * dim1 * dim2 + sigCrip23 * dim2 * dim3 + sigCrip24 * dim2 * dim4)/(dim1 * dim2 + dim2 * dim3 + dim2 * dim4)
def kBiax(panelNo,Loadcase): if(sigCripAVG < sYield):
beta = GetAvgStressofPanel(panelNo, Loadcase, 'YY')/GetAvgStressofPanel(panelNo, Loadcase, 'XX') return sigCripAVG
kSigX = 100000000 else:
for m in range(1, 10): return sYield
for n in range(1, 100):
kTemp = (m*m+n*n*alpha*alpha)*(m*m+n*n*alpha*alpha)/(alpha*alpha*(m*m+beta*n*n*alpha*alpha))
if(0 < kTemp < kSigX): def kBiax(panelNo,Loadcase):
kSigX = kTemp beta = GetAvgStressofPanel(panelNo, Loadcase, 'YY')/GetAvgStressofPanel(panelNo, Loadcase, 'XX')
return(kSigX) kSigX = 100000000
for m in range(1, 10):
for n in range(1, 100):
def RF_panel(panelNo, Loadcase): kTemp = (m*m+n*n*alpha*alpha)*(m*m+n*n*alpha*alpha)/(alpha*alpha*(m*m+beta*n*n*alpha*alpha))
sE = ((pThickness[panelNo-1]/pWidth)**2) * Ebasis * math.pi * math.pi / (12*(1-(0.34*0.34))) if(0 < kTemp < kSigX):
#print(sE) kSigX = kTemp
rfBiax = (kBiax(panelNo, Loadcase)*sE)/abs(1.5*GetAvgStressofPanel(panelNo, Loadcase, 'XX')) return(kSigX)
rfShear = (kShear*sE)/abs(1.5*GetAvgStressofPanel(panelNo, Loadcase, 'XY'))
result = 1 / ( (1 / rfBiax) + (1 / (rfShear*rfShear)))
#print(rfBiax) def RF_panel(panelNo, Loadcase):
#print(rfShear) sE = ((pThickness[panelNo-1]/pWidth)**2) * Ebasis * math.pi * math.pi / (12*(1-(0.34*0.34)))
return(result) #print(sE)
rfBiax = (kBiax(panelNo, Loadcase)*sE)/abs(1.5*GetAvgStressofPanel(panelNo, Loadcase, 'XX'))
rfShear = (kShear*sE)/abs(1.5*GetAvgStressofPanel(panelNo, Loadcase, 'XY'))
def GetLambda(i): # checked and correct result = 1 / ( (1 / rfBiax) + (1 / (rfShear*rfShear)))
I_comb = GetIcomb(i) #print(rfBiax)
r_gyr = math.sqrt(I_comb/(areaStringer + 0.5 * pThickness[i] * pWidth + 0.5 * pThickness[i+1] * pWidth)) #print(rfShear)
c = 1 return(result)
sLambda = c*pLength/r_gyr
return(sLambda)
def GetLambda(stringerNo):
I_comb = GetIcomb(i)
def GetSigCRIT(stringerNo, Loadcase): r_gyr = math.sqrt(I_comb/(areaStringer + 0.5 * pThickness[i] * pWidth + 0.5 * pThickness[i+1] * pWidth))
sLambda_crit = math.sqrt((2*math.pi*math.pi*Ebasis)/GetSigCrip(stringerNo,Loadcase)) c = 1
# Lambda_crit correct return(1*pLength/r_gyr)
hSigCrip = GetSigCrip(stringerNo, Loadcase)
# SigCrip correct!!
hLambda = GetLambda(stringerNo-1) def GetSigCRIT(stringerNo, Loadcase):
#print("Lmabda: " + str(hLambda)) sLambda_crit = math.sqrt((2*math.pi*math.pi*Ebasis)/GetSigCrip(i,0))
# ISSUE HERE - Lambda off from results if(GetLambda(stringerNo)<sLambda_crit):
# no double checking now return(GetSigCrip(stringerNo, Loadcase) - ((1/Ebasis)*((GetSigCrip(stringerNo, Loadcase)/(2*math.pi))**2)*(GetLambda(stringerNo)**2)))
else:
if(hLambda<sLambda_crit): return((math.pi**2)*Ebasis / (GetLambda(stringerNo) ** 2))
return(hSigCrip - ((1/Ebasis)*((hSigCrip/(2*math.pi))**2)*(hLambda**2)))
else:
return((math.pi**2)*Ebasis / (hLambda ** 2)) def GetRFstringer(stringerNo, Loadcase):
return(abs(GetSigCRIT(stringerNo, Loadcase)/(1.5*GetCombAvgStressofStringer(stringerNo, Loadcase))))
def GetRFstringer(stringerNo, Loadcase): def GetCrosssectionValues(i):
return(abs(GetSigCRIT(stringerNo, Loadcase)/(1.5*GetCombAvgStressofStringer(stringerNo, Loadcase)))) I_comb = GetIcomb(i)
r_gyr = math.sqrt(I_comb/(areaStringer + 0.5 * pThickness[i] * pWidth + 0.5 * pThickness[i+1] * pWidth))
def GetCrosssectionValues(i): c = 1
I_comb = GetIcomb(i) sLambda = c*pLength/r_gyr
r_gyr = math.sqrt(I_comb/(areaStringer + 0.5 * pThickness[i] * pWidth + 0.5 * pThickness[i+1] * pWidth)) sLambda_crit = math.sqrt((2*math.pi*math.pi*Ebasis)/GetSigCrip(i, 0)) # IMPORTANT THIS IS ONLY FOR S crip above 490
c = 1 return(str(I_comb) + "," + str(r_gyr) + "," + str(sLambda) + "," + str(sLambda_crit))
sLambda = c*pLength/r_gyr
sLambda_crit = math.sqrt((2*math.pi*math.pi*Ebasis)/GetSigCrip(i, 0)) # IMPORTANT THIS IS ONLY FOR S crip above 490
return(str(I_comb) + "," + str(r_gyr) + "," + str(sLambda) + "," + str(sLambda_crit)) def GetIcomb(i):
wing_1_w = pWidth/2
wing_2_w = pWidth/2
def GetIcomb(i):
wing_1_w = pWidth/2 wing_1_t = pThickness[i]
wing_2_w = pWidth/2 wing_2_t = pThickness[i+1]
wing_1_t = pThickness[i]
wing_2_t = pThickness[i+1] z1 = -dim1/2
z3 = -(dim1-(dim2/2))
z4 = -dim2/2
z1 = -dim1/2
z3 = -(dim1-(dim2/2)) y1 = ((dim3/2)-(dim2/2))
z4 = -dim2/2 y3 = 0
y4 = dim3+(dim4/2)
y1 = ((dim3/2)-(dim2/2))
y3 = 0 zw_1 = wing_1_t/2
y4 = dim3+(dim4/2) zw_2 = wing_2_t/2
zw_1 = wing_1_t/2 yw_1 = 50
zw_2 = wing_2_t/2 yw_2 = -50
yw_1 = 50
yw_2 = -50 a1 = dim1*dim2
a3 = dim2*(dim3-dim2-dim2)
a4 = dim4*dim2
a1 = dim1*dim2
a3 = dim2*(dim3-dim2-dim2) aw_1 = wing_1_w * wing_1_t
a4 = dim4*dim2 aw_2 = wing_2_t * wing_2_w
aw_1 = wing_1_w * wing_1_t Iyy1 = (dim2*(dim1**3))/12
aw_2 = wing_2_t * wing_2_w Izz1 = (dim1*(dim2**3))/12
Iyy1 = (dim2*(dim1**3))/12 Iyy3 = ((dim3-dim2-dim2)*(dim2**3))/12
Izz1 = (dim1*(dim2**3))/12 Izz3 = (((dim3-dim2-dim2)**3)*(dim2))/12
Iyy3 = ((dim3-dim2-dim2)*(dim2**3))/12 Iyy4 = (dim4*(dim2**3))/12
Izz3 = (((dim3-dim2-dim2)**3)*(dim2))/12 Izz4 = (dim2*(dim4**3))/12
Iyy4 = (dim4*(dim2**3))/12 Iw_1_yy = (wing_1_w*(wing_1_t**3))/12
Izz4 = (dim2*(dim4**3))/12 Iw_1_zz = (wing_1_t*(wing_1_w**3))/12
Iw_1_yy = (wing_1_w*(wing_1_t**3))/12 Iw_2_yy = (wing_2_w*(wing_2_t**3))/12
Iw_1_zz = (wing_1_t*(wing_1_w**3))/12 Iw_2_zz = (wing_2_t*(wing_2_w**3))/12
Iw_2_yy = (wing_2_w*(wing_2_t**3))/12
Iw_2_zz = (wing_2_t*(wing_2_w**3))/12 z_c = (z1*a1+z1*a1+z3*a3+z4*a4+z4*a4+zw_1*aw_1+zw_1*aw_2)/(a1+a1+a3+a4+a4+aw_1+aw_2)
y_c = (-y1*a1+y1*a1+y3*a3+(-y4*a4)+y4*a4+yw_1*aw_1+yw_2*aw_2)/(a1+a1+a3+a4+a4+aw_1+aw_2)
z_c = (z1*a1+z1*a1+z3*a3+z4*a4+z4*a4+zw_1*aw_1+zw_1*aw_2)/(a1+a1+a3+a4+a4+aw_1+aw_2) Iyy = (Iyy1+((z1-z_c)**2)*a1)+(Iyy1+((z1-z_c)**2)*a1)+(Iyy3+((z3-z_c)**2)*a3)+(Iyy4+((z4-z_c)**2)*a4)+(Iyy4+((z4-z_c)**2)*a4)+(Iw_1_yy+((zw_1-z_c)**2)*aw_1)+(Iw_2_yy+((zw_2-z_c)**2)*aw_2)
y_c = (-y1*a1+y1*a1+y3*a3+(-y4*a4)+y4*a4+yw_1*aw_1+yw_2*aw_2)/(a1+a1+a3+a4+a4+aw_1+aw_2) Izz = (Izz1+((y1-y_c)**2)*a1)+(Izz1+((-y1-y_c)**2)*a1)+(Izz3+((y3-y_c)**2)*a3)+(Izz4+((y4-y_c)**2)*a4)+(Izz4+((-y4-y_c)**2)*a4)+(Iw_1_zz+((yw_1-y_c)**2)*aw_1)+(Iw_2_zz+((yw_2-y_c)**2)*aw_2)
Iyy = (Iyy1+((z1-z_c)**2)*a1)+(Iyy1+((z1-z_c)**2)*a1)+(Iyy3+((z3-z_c)**2)*a3)+(Iyy4+((z4-z_c)**2)*a4)+(Iyy4+((z4-z_c)**2)*a4)+(Iw_1_yy+((zw_1-z_c)**2)*aw_1)+(Iw_2_yy+((zw_2-z_c)**2)*aw_2)
Izz = (Izz1+((y1-y_c)**2)*a1)+(Izz1+((-y1-y_c)**2)*a1)+(Izz3+((y3-y_c)**2)*a3)+(Izz4+((y4-y_c)**2)*a4)+(Izz4+((-y4-y_c)**2)*a4)+(Iw_1_zz+((yw_1-y_c)**2)*aw_1)+(Iw_2_zz+((yw_2-y_c)**2)*aw_2) if(Iyy > Izz):
return(Izz)
else:
if(Iyy > Izz): return(Iyy)
return(Izz)
else:
return(Iyy)
for u in range(modAmount):
isWithinRF = 1
for u in range(modAmount): panel = 'panel_val_' + str(u) +'.csv'
isWithinRF = 1 stringer = 'stringer_val_' + str(u) + '.csv'
panel = 'panel_val_' + str(u) +'.csv' # dimensions
stringer = 'stringer_val_' + str(u) + '.csv' pThickness = [pThickness_01[u], pThickness_02[u], pThickness_03[u], pThickness_04[u], pThickness_05[u], pThickness_05[u], pThickness_04[u], pThickness_03[u], pThickness_02[u], pThickness_01[u]]
pWidth = pWidth_0[u]
# dimensions pLength = pLength_0[u]
pThickness = [pThickness_01[u], pThickness_02[u], pThickness_03[u], pThickness_04[u], pThickness_05[u], pThickness_05[u], pThickness_04[u], pThickness_03[u], pThickness_02[u], pThickness_01[u]]
pWidth = pWidth_0[u] dim1 = dim1_0[u]
pLength = pLength_0[u] dim2 = dim2_0[u]
dim3 = dim3_0[u]
dim1 = dim1_0[u] dim4 = dim4_0[u]
dim2 = dim2_0[u]
dim3 = dim3_0[u] areaStringer = dim4 * dim2 * 2 + (dim1 - dim2) * dim2 * 2 + dim3 * dim2
dim4 = dim4_0[u]
print("\n\n" + Back.CYAN + "Calculations for iteration " + str(u) + Style.RESET_ALL)
areaStringer = dim4 * dim2 * 2 + (dim1 - dim2) * dim2 * 2 + dim3 * dim2 print("\n Panel Thickness 1 & 10: " + str(pThickness[0]) + "\n Panel Thickness 2 & 9: " + str(pThickness[1]) + "\n Panel Thickness 3 & 8: " + str(pThickness[2]) + "\n Panel Thickness 4 & 7: " + str(pThickness[3]) + "\n Panel Thickness 5 & 6: " + str(pThickness[4]) + "\n Panel Width: " + str(pWidth) + "\n Panel Length: " + str(pLength) + "\n\n Dim 1: " + str(dim1) + "\n Dim2: " + str(dim2) + "\n Dim 3: "+ str(dim3) + "\n Dim 4: "+ str(dim4))
print("\n\n" + Back.CYAN + "Calculations for iteration " + str(u) + Style.RESET_ALL) #print("\n Panel Offset: " + str(pThickness/2) + "\n Stringer Offset: " + str(dim1/2))
print("\n Panel Thickness 1 & 10: " + str(pThickness[0]) + "\n Panel Thickness 2 & 9: " + str(pThickness[1]) + "\n Panel Thickness 3 & 8: " + str(pThickness[2]) + "\n Panel Thickness 4 & 7: " + str(pThickness[3]) + "\n Panel Thickness 5 & 6: " + str(pThickness[4]) + "\n Panel Width: " + str(pWidth) + "\n Panel Length: " + str(pLength) + "\n\n Dim 1: " + str(dim1) + "\n Dim2: " + str(dim2) + "\n Dim 3: "+ str(dim3) + "\n Dim 4: "+ str(dim4))
mass = density*(areaStringer*pLength*9) # + 10*pWidth*pThickness*pLength)
#print("\n Panel Offset: " + str(pThickness/2) + "\n Stringer Offset: " + str(dim1/2)) for i in range(10):
mass = mass + pWidth*pThickness[i]*density*pLength
mass = density*(areaStringer*pLength*9) # + 10*pWidth*pThickness*pLength) if(mass<mass_limit):
for i in range(10): print("\n\n Mass: " + Back.GREEN + str(mass) + Style.RESET_ALL)
mass = mass + pWidth*pThickness[i]*density*pLength else:
if(mass<mass_limit): print("\n\n Mass: " + Back.RED + str(mass) + Style.RESET_ALL)
print("\n\n Mass: " + Back.GREEN + str(mass) + Style.RESET_ALL) isWithinRF = 0
else:
print("\n\n Mass: " + Back.RED + str(mass) + Style.RESET_ALL) # REMEMBER SAFETY FACTOR OF 1.5 ALREADY INCLUDED
isWithinRF = 0 # RF calculator for panels
for c in range(1,4):
# REMEMBER SAFETY FACTOR OF 1.5 ALREADY INCLUDED print("\nPanel RF for loadcase " + str(c))
# RF calculator for panels for i in range(1, 31):
for c in range(1,4): w = sUlt/GetValueofElement(i,c,'vonMises',panel)
print("\nPanel RF for loadcase " + str(c)) if(w>1):
for i in range(1, 31): print(Back.GREEN + str(w) + Style.RESET_ALL)
w = sUlt/GetValueofElement(i,c,'vonMises',panel) else:
if(w>1): print(Back.RED + str(w) + Style.RESET_ALL)
print(Back.GREEN + str(w) + Style.RESET_ALL) isWithinRF = 0
else:
print(Back.RED + str(w) + Style.RESET_ALL) print(" ")
isWithinRF = 0 # RF calculator for stringers
for c in range(1,4):
print(" ") print("\nStringer RF for loadcase " + str(c))
# RF calculator for stringers for i in range(40,67):
for c in range(1,4): w = abs(sUlt/GetValueofElement(i,c,axial,stringer))
print("\nStringer RF for loadcase " + str(c)) if(w>1):
for i in range(40,67): print(Back.GREEN + str(w) + Style.RESET_ALL)
w = abs(sUlt/GetValueofElement(i,c,axial,stringer)) else:
if(w>1): print(Back.RED + str(w) + Style.RESET_ALL)
print(Back.GREEN + str(w) + Style.RESET_ALL) isWithinRF = 0
else:
print(Back.RED + str(w) + Style.RESET_ALL) # Stability Analysis
isWithinRF = 0 print("\n\nStability Analysis\nPanel buckling")
# Panel buckling
# Stability Analysis # sig_aa,avg calculator
print("\n\nStability Analysis\nPanel buckling") alpha = pLength/pWidth
# Panel buckling kShear = 5.34 + 4/(alpha*alpha)
# sig_aa,avg calculator for c in range(1,4):
alpha = pLength/pWidth print("\nLoadcase " + str(c) + "\nAverage stress for panels 1 to 5 - XX, YY, XY - k_shear, k_biax, RF_panelbuckl")
kShear = 5.34 + 4/(alpha*alpha) for i in range(1,6):
for c in range(1,4): w = RF_panel(i,c)
print("\nLoadcase " + str(c) + "\nAverage stress for panels 1 to 5 - XX, YY, XY - k_shear, k_biax, RF_panelbuckl") if(w>1):
for i in range(1,6): w = Back.GREEN + str(w) + Style.RESET_ALL
w = RF_panel(i,c) else:
if(w>1): w = Back.RED + str(w) + Style.RESET_ALL
w = Back.GREEN + str(w) + Style.RESET_ALL isWithinRF = 0
else:
w = Back.RED + str(w) + Style.RESET_ALL print(str(GetAvgStressofPanel(i, c, 'XX')) + "," + str(GetAvgStressofPanel(i, c, 'YY')) + "," + str(GetAvgStressofPanel(i, c, 'XY')) + "," + str(kShear) + "," + str(kBiax(i, c)) + "," + str(w))
isWithinRF = 0
# Stringer buckling
print(str(GetAvgStressofPanel(i, c, 'XX')) + "," + str(GetAvgStressofPanel(i, c, 'YY')) + "," + str(GetAvgStressofPanel(i, c, 'XY')) + "," + str(kShear) + "," + str(kBiax(i, c)) + "," + str(w)) print("\n\nStringer buckling")
for c in range(1,4):
# Stringer buckling print("\nLoadcase " + str(c) + "\nCombined, average axial stress for stringers 1 to 5")
print("\n\nStringer buckling") for i in range(1,6):
for c in range(1,4): w = GetRFstringer(i,c)
print("\nLoadcase " + str(c) + "\nCombined, average axial stress for stringers 1 to 5") if(w>1):
for i in range(1,6): w = Back.GREEN + str(w) + Style.RESET_ALL
w = GetRFstringer(i,c) else:
if(w>1): w = Back.RED + str(w) + Style.RESET_ALL
w = Back.GREEN + str(w) + Style.RESET_ALL isWithinRF = 0
else:
w = Back.RED + str(w) + Style.RESET_ALL
isWithinRF = 0 print(str(GetCombAvgStressofStringer(i,c)) + "," + str(GetSigCrip(i, c)) + "," + str(w)) # no longer slightly off, RF stringer calc still wrong?
# combined crosssection properties for combined buckling mode
print(str(GetCombAvgStressofStringer(i,c)) + "," + str(GetSigCrip(i, c)) + "," + str(w)) # no longer slightly off, RF stringer calc still wrong? print("\n\nCombined crosssection properties for combined buckling")
for i in range(5):
# combined crosssection properties for combined buckling mode print(GetCrosssectionValues(i))
print("\n\nCombined crosssection properties for combined buckling")
for i in range(5): if(isWithinRF == 1):
print(GetCrosssectionValues(i)) print("\n\n" + Back.GREEN + str(u) + " WORKS!" + Style.RESET_ALL)
else:
if(isWithinRF == 1): print("\n\n" + Back.RED + str(u) + " FAILURE!" + Style.RESET_ALL)
print("\n\n" + Back.GREEN + str(u) + " WORKS!" + Style.RESET_ALL)
else: #print(GetIcomb())
print("\n\n" + Back.RED + str(u) + " FAILURE!" + Style.RESET_ALL)
#print(GetIcomb()) ## OVERVIEW OF TODO:
## OVERVIEW OF TODO:
# - improve some sections of code with TODO # - improve some sections of code with TODO

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aseredesign/readme.md
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# ASE Redesign Calculator # ASE Redesign Calculator
**Important:**
Version was updated --- new release. There might be issues with the RF of the column buckling. I am unsure at this exact moment.
Nothing regarding the procedure has changed.
***
This redesign calculator requires manual input in Hyperworks, but returns the values needed for the final results csv file. This redesign calculator requires manual input in Hyperworks, but returns the values needed for the final results csv file.
It can calculate several results at the same time which I found helpful for comparing and analysing. It can calculate several results at the same time which I found helpful for comparing and analysing.
It has the following limitations: It has the following limitations:
1. All stringers have to have the same dimensions (panel thickness may vary tho) 1. All stringers have to have the same dimensions (panel thickness may vary tho)
2. Dimensions must be inputted into Python as well as Hyperworks 2. Dimensions must be inputted into Python as well as Hyperworks
[Releases here](https://git.zoerdu.net/Sasha/uni/releases)
## Quick rundown ## Quick rundown
1. Modify the dimensions of the stringers and panels in the *.hm* and *aseredesign.py* file 1. Modify the dimensions of the stringers and panels in the *.hm* and *aseredesign.py* file
2. Run the simulation 2. Run the simulation

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readme.md
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# Uni stuff # Uni stuff
[aseredesign](https://git.zoerdu.net/Sasha/uni/src/branch/main/aseredesign) [aseredesign](https://git.zoerdu.net/Sasha/uni/aseredesign)