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Failed
gpkit.tests.from_paths.TestFiles.test_SPaircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20200225153317)
Failing for the past 1 build
(Since Failed
)
Error Message
Geometric Program is not fully bounded: Mission1.Aircraft.Engine.EngineConstants.Relax1.R has no lower bound Mission1.Aircraft.Engine.EngineConstants.Relax1.g has no lower bound
Stacktrace
Traceback (most recent call last):
File "/Users/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/tests/helpers.py", line 64, in test
testfn(name, import_dict, path)(self)
File "/Users/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/tests/from_paths.py", line 51, in <lambda>
lambda self: getattr(self, name)())) # pylint:disable=undefined-variable
File "/Users/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/tests/from_paths.py", line 40, in test_fn
mod.test()
File "SPaircraft.py", line 89, in test
sol = optimize_aircraft(m, substitutions, fixedBPR, pRatOpt, mutategparg)
File "SPaircraft.py", line 65, in optimize_aircraft
sol = m_relax.localsolve(verbosity=2, iteration_limit=200, reltol=0.01, mutategp=mutategparg)#, x0 = x0)
File "/Users/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/constraints/prog_factories.py", line 124, in solvefn
result = progsolve(solver, verbosity, **kwargs)
File "/Users/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/constraints/sgp.py", line 149, in localsolve
feas_constrs, None)
File "/Users/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/constraints/gp.py", line 116, in __init__
+ boundstrs)
ValueError: Geometric Program is not fully bounded:
Mission1.Aircraft.Engine.EngineConstants.Relax1.R has no lower bound
Mission1.Aircraft.Engine.EngineConstants.Relax1.g has no lower bound
Standard Output
Beginning signomial solve.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.539 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.252 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.272 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.263 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.258 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.23 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.273 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.275 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.322 seconds.
Solving took 9 GP solves and 12.3 seconds.
Checking for relaxed constants...
GP iteration 0 has relaxed constants
Cost
----
2.72e+110
Free Variables
--------------
| Mission.Aircraft.Engine.Turbine.Relax
C_{p_{t2}} : 2.246 Cp Value for Combustion Products in LP Turbine
| Mission.Aircraft.Fuselage.Relax
l_{nose} : 1.067 Nose length
n_{pass} : [ 2.86 ] Number of passengers
| Mission.Aircraft.Relax
f_{L_{total/wing}} : 1.683 Total lift as a percentage of wing lift
| Mission.Aircraft.Wing.WingNoStruct.Relax
\tan(\Lambda) : 1.109 Tangent of quarter-chord sweep angle
| Mission.FlightState.Atmosphere.Relax
L_{atm} : [ 1.78 1 1 1 1 ] Temperature lapse rate
T_{sl} : [ 1 1 1.27 1 1 ] Temperature at sea level
| Mission.Relax
R_{req} : 2.352 Required Cruise Range
GP iteration 1 has relaxed constants
Cost
----
1.472e+75
Free Variables
--------------
| Mission.Aircraft.Engine.Combustor.Relax
hold_{4a} : 1.117 1+(gamma-1)/2 * M_4a**2
| Mission.Aircraft.Fuselage.Relax
n_{pass} : [ 1.04 ] Number of passengers
| Mission.Aircraft.LandingGear.Relax
h_{hold} : 1.007 Hold height
Solution check warning: Primal solution computed cost did not match solver-returned cost: 1.998972324382873e+72 vs 1.99908047491e+72
WEIGHT DIFFERENCES
Total Fuel Weight Percent Diff: [-92.97033935]
Total Aircraft Weight Percent Diff: [-21.17214269]
Engine Weight Percent Diff: -58.76555047012018
Fuselage Weight Percent Diff: 2.3096728084332754
Payload Weight Percent Diff: [-0.04003555]
VT Weight Percent Diff: -8.68091963167528
HT Weight Percent Diff: -93.22548823252279
Wing Weight Percent Diff: 8.05615841282999
WING DIFFERENCES
Wing Span Percent Diff: -0.029994309491006375
Wing Area Percent Diff: 33.877703222109
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: 41.32273730746586
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -11.04613420758646
VT Area Percent Diff: -60.40801894574819
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-19.04555051]
L/D Percent Diff: [24.03457236]
Nacelle Cd Percent Diff: [-94.59139722]
HT Cd Percent Diff: [-80.83177273] dimensionless
Fuselage Cd Percent Diff: [108.78752887]
VT Cd Percent Diff: [-58.32239675] dimensionless
Wing Cd percent Diff: [-14.78360717]
Induced Drag Cd Percent Diff: [0.72572723]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [-90.67468512]
FUSELAGE DIFFERENCES
Weight of HB material: -39.327543722714886
Weight of VB material: 90.50191622839411
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
[0.69501812]
Beginning signomial solve.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.343 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.238 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.314 seconds.
Beginning signomial solve.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.23 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.245 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.237 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.23 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.251 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.219 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.213 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.211 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.216 seconds.