def handleMessage(self):
print "< received", repr(self.data)
try:
self.data = json.loads(self.data)
print self.data
config = 'optimalD8'
substitutions = get_optimalD8_subs()
fixedBPR = False
pRatOpt = True
mutategparg = True
m = Mission(3, 2, config, 1)
m.cost = m['W_{f_{total}}']
for name, value in self.data.items():
try:
key = m.design_parameters[name]
m.substitutions[key] = value
except KeyError as e:
print repr(e)
sol = optimize_aircraft(m, substitutions, fixedBPR, pRatOpt, mutategparg)
LASTSOL[0] = sol
genfiles(m, sol)
self.send({"status": "optimal",
"msg": ("Successfully optimized."
" Optimal heat transfer: %.1f watts "
% sol["variables"][m.Q])})
except Exception as e:
self.send({"status": "unknown", "msg": "The last solution"
" raised an exception; tweak it and send again."})
print type(e), e
def standard_killer_plot():
"""
Generates the standard killer plots from the TASOPT paper
"""
Nclimb = 3
Ncruise = 2
Nmission = 1
subsList = [
get_optimal737_subs(),
get_M072_737_subs(),
get_D8_eng_wing_subs(),
get_D8_no_BLI_subs(),
get_optimalD8_subs(),
get_optimalD8_subs()
]
configList = [
'optimal737', 'M072_737', 'D8_eng_wing', 'D8_no_BLI', 'optimalD8',
'optimalD8'
]
fixedBPRList = [True, True, True, True, True, False]
pRatOptList = [False, False, False, False, False, True]
mutategpargList = [False, False, False, False, False, False]
sol = {}
wf = []
for i in range(0, 6):
m = Mission(Nclimb, Ncruise, configList[i], Nmission)
m.cost = m['W_{f_{total}}'].sum()
substitutions = subsList[i]
substitutions.update({
'R_{req}': 3000. * units('nmi'),
'n_{pass}': 180.
})
sol[i] = optimize_aircraft(m, substitutions, fixedBPRList[i],
pRatOptList[i], mutategpargList[i])
wf.append(sol[i]('W_{f_{total}}'))
wing_sens = [
sol[i]['sensitivities']['constants']['C_{wing}'] for i in range(0, 6)
]
HT_sens = [
sol[i]['sensitivities']['constants']['C_{ht}'] for i in range(0, 6)
]
VT_sens = [
sol[i]['sensitivities']['constants']['C_{VT}'] for i in range(0, 6)
]
fuse_sens = [
sol[i]['sensitivities']['constants']['C_{fuse}'] for i in range(0, 6)
]
engine_sens = [
sol[i]['sensitivities']['constants']['C_{engsys}']
for i in range(0, 6)
]
lg_sens = [
sol[i]['sensitivities']['constants']['C_{lg}'] for i in range(0, 6)
]
Mmin_sens = [
sol[i]['sensitivities']['constants']['M_{min}'] for i in range(0, 6)
]
ytest = [mag(wf[i] / wf[0])[0] for i in range(0, 6)]
xtest = [0, 1, 2, 3, 4, 5]
xlabels = [
'Optimized 737-800 M = 0.8', 'Slow to M = 0.72',
'D8 fuselage, Pi tail', 'Rear podded engines',
'Integrated engines, BLI = D8', 'Optimize engine', '2020 Engines'
]
plt.plot(xtest, ytest, "o--")
plt.plot([0, 1, 2, 3, 4, 5, 6], [1, .88, .81, .82, .67, .66, .63], "o--")
plt.plot([0, 1, 2, 3, 6], [1, .868, .871, .865, .602], "o--")
plt.plot([0, 1, 2, 3, 4, 5, 6], [
1, 41129. / 43843, 38402. / 43843, 37180. / 43843, 32987. / 43843,
32383. / 43843, 29753. / 43843
], "o--")
plt.xticks(np.linspace(0, 6, 7), xlabels, rotation='vertical')
plt.ylim([0, 1.1])
plt.xlim([-.5, 6.5])
plt.grid()
plt.xlabel('Design Step', fontsize=20)
plt.ylabel('$W_{\mathrm{f}}/W_{\mathrm{f}_\mathrm{0}}$', fontsize=20)
plt.title('D8 Morphing Chart')
plt.legend(['SP Model', 'TASOPT', 'NASA', 'Aurora'], loc=3)
plt.savefig('Morphing_Chart_Figs/D8_standard_morphing_chart.pdf',
bbox_inches="tight")
plt.show(), plt.close()
xtest = [0, 1, 2, 3, 4, 5]
plt.plot(xtest, wing_sens, "o--")
plt.xticks(xtest, xlabels, rotation='vertical')
plt.ylim([0, 0.25])
plt.xlim([-.5, 5.5])
plt.grid()
plt.xlabel('Design Step', fontsize=20)
plt.ylabel('Sensitivity to Wing Weight', fontsize=20)
plt.title('Wing Weight Sensitivity Morphing Chart')
plt.savefig(
'Morphing_Chart_Figs/D8_standard_killer_chart_max_opt_eng_wing_sens.pdf',
bbox_inches="tight")
plt.show(), plt.close()
plt.plot(xtest, HT_sens, "o--")
plt.xticks(xtest, xlabels, rotation='vertical')
plt.ylim([0, 0.02])
plt.xlim([-.5, 5.5])
plt.grid()
plt.xlabel('Design Step', fontsize=20)
plt.ylabel('Sensitivity to Horizontal Tail Weight', fontsize=20)
plt.title('Horizontal Tail Weight Sensitivity Morphing Chart')
plt.savefig(
'Morphing_Chart_Figs/D8_standard_killer_chart_max_opt_eng_HT_sens.pdf',
bbox_inches="tight")
plt.show(), plt.close()
plt.plot(xtest, VT_sens, "o--")
plt.xticks(xtest, xlabels, rotation='vertical')
plt.ylim([0, 0.15])
plt.xlim([-.5, 5.5])
plt.grid()
plt.xlabel('Design Step', fontsize=20)
plt.ylabel('Sensitivity to Vertical Tail Weight', fontsize=20)
plt.title('Vertical Tail Weight Sensitivity Morphing Chart')
plt.savefig(
'Morphing_Chart_Figs/D8_standard_killer_chart_max_opt_eng_VT_sens.pdf',
bbox_inches="tight")
plt.show(), plt.close()
plt.plot(xtest, fuse_sens, "o--")
plt.xticks(xtest, xlabels, rotation='vertical')
plt.ylim([0, 0.55])
plt.xlim([-.5, 5.5])
plt.grid()
plt.xlabel('Design Step', fontsize=20)
plt.ylabel('Sensitivity to Fuselage Weight', fontsize=20)
plt.title('Fuselage Weight Sensitivity Morphing Chart')
plt.savefig(
'Morphing_Chart_Figs/D8_standard_killer_chart_max_opt_eng_fuse_sens.pdf',
bbox_inches="tight")
plt.show(), plt.close()
plt.plot(xtest, engine_sens, "o--")
plt.xticks(xtest, xlabels, rotation='vertical')
plt.ylim([0, 0.3])
plt.xlim([-.5, 5.5])
plt.grid()
plt.xlabel('Design Step', fontsize=20)
plt.ylabel('Sensitivity to Engine Weight', fontsize=20)
plt.title('Engine Weight Sensitivity Morphing Chart')
plt.savefig(
'Morphing_Chart_Figs/D8_standard_killer_chart_max_opt_eng_engine_sens.pdf',
bbox_inches="tight")
plt.show(), plt.close()
plt.plot(xtest, lg_sens, "o--")
plt.xticks(xtest, xlabels, rotation='vertical')
plt.ylim([0, 0.07])
plt.xlim([-.5, 5.5])
plt.grid()
plt.xlabel('Design Step', fontsize=20)
plt.ylabel('Sensitivity to Landing Gear Weight', fontsize=20)
plt.title('Landing Gear Weight Sensitivity Morphing Chart')
plt.savefig(
'Morphing_Chart_Figs/D8_standard_killer_chart_max_opt_eng_lg_sens.pdf',
bbox_inches="tight")
plt.show(), plt.close()
" raised an exception; tweak it and send again."})
print type(e), e
def send(self, msg):
print "> sent", repr(msg)
self.sendMessage(unicode(json.dumps(msg)))
def handleConnected(self):
print self.address, "connected"
def handleClose(self):
print self.address, "closed"
EXIT[0] = True
if __name__ == "__main__":
objective = 'W_{f_{total}}'
aircraft = 'optimald8'
substitutions = get_optimalD8_subs()
fixedBPR = False
pRatOpt = True
mutategparg = True
LASTSOL[0] = None
sol = optimize_aircraft(objective, aircraft, substitutions, fixedBPR, pRatOpt, mutategparg, x0 = LASTSOL[0])
LASTSOL[0] = sol
genfiles(m, sol)
server = SimpleWebSocketServer('', 8000, SPaircraftServer)
while not EXIT[0]:
server.serveonce()
print "Python server has exited."
Nclimb = 3 # number of climb segments
Ncruise = 2 # number of cruise segments
Nmission = 1 # number of missions
config = 'optimal737' # String describing configuration:
m = Mission(Nclimb, Ncruise, config, Nmission)
# Additional options
fixedBPR = True
pRatOpt = False
mutategparg = False
sol = {}
objectives = [
m['W_{f_{total}}'], m['W_{dry}'], m['b'], m['AR'], m['W_{engine}'],
m['TotalTime'], m['L/D'][Nclimb], m['W_{lg}']
]
for i in range(0, 8):
m.cost = objectives[i].sum()
substitutions = get_optimal737_subs()
substitutions.update({'R_{req}': 3000. * units('nmi'), 'n_{pass}': 180.})
sol[i] = optimize_aircraft(m, substitutions, fixedBPR, pRatOpt,
mutategparg)
basesol = sol[0]
# output the columns of the table
for i in range(0, 8):
print("column %s" % i)
print "\n"
print[sol[i](objectives[j]) / basesol(objectives[j]) for j in range(0, 8)]
print "\n"
print "\n"