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Failed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek_cli (from gpkit.tests.from_paths.TestFiles-20171016201007)
Failing for the past 1 build
(Since Failed
)
Error Message
Command '['mskexpopt', 'c:\\users\\jenkins\\appdata\\local\\temp\\tmpd90aqw\\gpkit_mosek']' returned non-zero exit status 1432
Stacktrace
Traceback (most recent call last):
File "c:\users\jenkins\workspace\gpkit_commons_pr_models\buildnode\windows10x64\optimizer\mosek\gpkit\gpkit\tests\helpers.py", line 62, in test
testfn(name, import_dict, path)(self)
File "c:\users\jenkins\workspace\gpkit_commons_pr_models\buildnode\windows10x64\optimizer\mosek\gpkit\gpkit\tests\from_paths.py", line 50, in <lambda>
lambda self: getattr(self, name)())) # pylint:disable=undefined-variable
File "c:\users\jenkins\workspace\gpkit_commons_pr_models\buildnode\windows10x64\optimizer\mosek\gpkit\gpkit\tests\from_paths.py", line 41, in test_fn
mod.test()
File "SP_aircraft.py", line 520, in test
run_optimal_737('W_{f_{total}}', True, False)
File "SP_aircraft.py", line 374, in run_optimal_737
sol = m_relax.localsolve(verbosity=1, iteration_limit=200, reltol=0.01)
File "c:\users\jenkins\workspace\gpkit_commons_pr_models\buildnode\windows10x64\optimizer\mosek\gpkit\gpkit\constraints\prog_factories.py", line 83, in solvefn
result = solvefn(solver, verbosity, *args, **kwargs)
File "c:\users\jenkins\workspace\gpkit_commons_pr_models\buildnode\windows10x64\optimizer\mosek\gpkit\gpkit\constraints\sgp.py", line 133, in localsolve
result = primal_feas.solve(solver, verbosity=verbosity-1)
File "c:\users\jenkins\workspace\gpkit_commons_pr_models\buildnode\windows10x64\optimizer\mosek\gpkit\gpkit\constraints\gp.py", line 182, in solve
k=self.k, *args, **kwargs)
File "c:\users\jenkins\workspace\gpkit_commons_pr_models\buildnode\windows10x64\optimizer\mosek\gpkit\gpkit\_mosek\cli_expopt.py", line 86, in imize
for logline in check_output(["mskexpopt", filename]).split(b"\n"):
File "c:\anaconda2\Lib\subprocess.py", line 219, in check_output
raise CalledProcessError(retcode, cmd, output=output)
CalledProcessError: Command '['mskexpopt', 'c:\\users\\jenkins\\appdata\\local\\temp\\tmpd90aqw\\gpkit_mosek']' returned non-zero exit status 1432
Standard Output
Beginning signomial solve.
Solving took 7 GP solves and 7.58 seconds.
Warning: Constraint [W_{avg}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)*x_{CG}_Mission/CruiseSegment/CruiseP/Aircra... >= 0.225*W_{ht}_Mission/Aircraft/HorizontalTail*x_{CG_{ht}}_Mission/Aircraft/HorizontalTail/HorizontalT...] is not tight because the left hand side evaluated to 2427085.7796 force_pound * meter but the right hand side evaluated to 2397886.47128 force_pound * meter (Allowable error: 0.1%, Actual error: 1.2%)
Warning: Constraint [0.0417*S_Mission/Aircraft/Wing/WingNoStruct**-1*\tan(\Lambda)_Mission/Aircraft/Wing/WingNoStruct*b_M... >= \Delta x_{AC_{wing}}_Mission/Aircraft/Wing [m]...] is not tight because the left hand side evaluated to 2.21510116702 meter but the right hand side evaluated to 1.96470280719 meter (Allowable error: 0.1%, Actual error: 11%)
Warning: Constraint [F_{6}_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(3, 0) + F_{8}_Mission/Aircraft/En... >= F_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(3, 0) [N]...] is not tight because the left hand side evaluated to 17472.6001504 newton but the right hand side evaluated to 17443.2649252 newton (Allowable error: 0.1%, Actual error: 0.17%)
Warning: Constraint [-C_{p_{fuel}_Mission/Aircraft/Engine/Combustor*T_{t_f}_Mission/Aircraft/Engine/Combustor*f_Mission/A... <= \eta_{B}_Mission/Aircraft/Engine/Combustor*f_Mission/Aircraft/Engine/EnginePerformance/CombustorPerf...] is not tight because the left hand side evaluated to 1242113.83178 joule / kilogram but the right hand side evaluated to 1.48132834762 megajoule / kilogram (Allowable error: 0.1%, Actual error: 9.5%)
Warning: Constraint [-C_{p_{fuel}_Mission/Aircraft/Engine/Combustor*T_{t_f}_Mission/Aircraft/Engine/Combustor*f_Mission/A... <= \eta_{B}_Mission/Aircraft/Engine/Combustor*f_Mission/Aircraft/Engine/EnginePerformance/CombustorPerf...] is not tight because the left hand side evaluated to 642470.874152 joule / kilogram but the right hand side evaluated to 0.643955121233 megajoule / kilogram (Allowable error: 0.1%, Actual error: 0.1%)
Warning: Constraint [W_{lg}_Mission/Aircraft/LandingGear*x_{CG_{lg}}_Mission/Aircraft/LandingGear [N*m]... >= W_{mg}_Mission/Aircraft/LandingGear*x_m_Mission/Aircraft/LandingGear + W_{ng}_Mission/Aircraft/Landi...] is not tight because the left hand side evaluated to 271789.900616 meter * newton but the right hand side evaluated to 263035.031291 meter * newton (Allowable error: 1.0%, Actual error: 3.3%)
Warning: Constraint [x_m_Mission/Aircraft/LandingGear [m]... >= x_{wing}_Mission/Aircraft/Fuselage [m]...] is not tight because the left hand side evaluated to 18.5759834054 meter but the right hand side evaluated to 16.6120531978 meter (Allowable error: 0.1%, Actual error: 12%)
Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(0, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(0, 0)...] is not tight because the left hand side evaluated to 10.9551767662 but the right hand side evaluated to 4.85819298866 (Allowable error: 0.1%, Actual error: 56%)
Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(1, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(1, 0)...] is not tight because the left hand side evaluated to 10.006927572 but the right hand side evaluated to 4.85820321075 (Allowable error: 0.1%, Actual error: 51%)
Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(2, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(2, 0)...] is not tight because the left hand side evaluated to 8.21525183431 but the right hand side evaluated to 4.85820329283 (Allowable error: 0.1%, Actual error: 41%)
Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/CruiseSegment/CruiseP/AircraftP.1_(... >= x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0) [m]...] is not tight because the left hand side evaluated to 18.622005748 meter but the right hand side evaluated to 18.3758704082 meter (Allowable error: 0.1%, Actual error: 1.3%)
Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/CruiseSegment/CruiseP/AircraftP.1_(... >= x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0) [m]...] is not tight because the left hand side evaluated to 18.622005748 meter but the right hand side evaluated to 18.4513331532 meter (Allowable error: 0.1%, Actual error: 0.92%)
Warning: Constraint [SM_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0) + mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{... <= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0)...] is not tight because the left hand side evaluated to 4.67771676073 but the right hand side evaluated to 4.79404609281 (Allowable error: 0.1%, Actual error: 2.4%)
Warning: Constraint [SM_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0) + mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{... <= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)...] is not tight because the left hand side evaluated to 4.73114395954 but the right hand side evaluated to 4.81373342571 (Allowable error: 0.1%, Actual error: 1.7%)
Warning: Constraint [C_{L_{ht}}_Mission/CruiseSegment/CruiseP/AircraftP.1/HorizontalTailPerformance.1_(0, 0)*C_{L}_Missio... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0)...] is not tight because the left hand side evaluated to 7.60829133351 but the right hand side evaluated to 4.79404609281 (Allowable error: 0.1%, Actual error: 37%)
Warning: Constraint [C_{L_{ht}}_Mission/CruiseSegment/CruiseP/AircraftP.1/HorizontalTailPerformance.1_(1, 0)*C_{L}_Missio... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)...] is not tight because the left hand side evaluated to 7.57971136668 but the right hand side evaluated to 4.81373342571 (Allowable error: 0.1%, Actual error: 36%)
Solves with these variables bounded:
value near lower bound: [CruiseAlt_Mission]
value near upper bound: [TotalTime_Mission, MaxClimbDistance_Mission, \bar{A}_{fuel, max}_Mission/Aircraft/Wing/WingNoStruct, A_{tri}_Mission/Aircraft/Wing/WingNoStruct, ClimbDistance_Mission]
Checking for relaxed constants...
WEIGHT DIFFERENCES
Total Fuel Weight Percent Diff: [-6.97449972]
Total Aircraft Weight Percent Diff: [-4.9503972]
Engine Weight Percent Diff: -8.23490602214
Fuselage Weight Percent Diff: -10.9541900943
Payload Weight Percent Diff: [-0.04003555]
VT Weight Percent Diff: -24.5188556727
HT Weight Percent Diff: -85.1524486758
Wing Weight Percent Diff: 0.426089071376
WING DIFFERENCES
Wing Span Percent Diff: 0.921607110044
Wing Area Percent Diff: -6.86180851951
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: -54.6184377974
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -16.3231659765
VT Area Percent Diff: -29.9969254319
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-0.13104474]
Nacelle Cd Percent Diff: [ 23.80939085]
HT Cd Percent Diff: [-63.50963767] dimensionless
Fuselage Cd Percent Diff: [ 45.32349081]
VT Cd Percent Diff: [ 60.36878528] dimensionless
Induced Drag Cd Percent Diff: [ 1.06334871]
Wing Profile Cd Percent Diff: [-15.69410576]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [ 2.9911493]
FUSELAGE DIFFERENCES
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004841743
Beginning signomial solve.