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Failed
gpkit.tests.from_paths.TestFiles.test_SPaircraft_py_mosek_conif (from gpkit.tests.from_paths.TestFiles-20200225153223)
Failing for the past 1 build
(Since Failed
)
Error Message
cost contains unsolved variables [Mission.FlightSegment.FlightP.Relax.RC_{min}[4,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[1,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[1,0], Mission.FlightState.Relax.\gamma[4,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[0,0], Mission.FlightState.Atmosphere.Relax.T_s[4,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[2,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[3,0], Mission.FlightState.Atmosphere.Relax.T_s[2,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[3,0], Mission.Aircraft.Fuselage.Relax.n_{pass}[0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[2,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[0,0], Mission.FlightState.Atmosphere.Relax.C_1[3,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[4,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[4,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[2,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[1,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[1,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[4,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[3,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[0,0], Mission.FlightSegment.FlightP.Relax.RC_{min}[0,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[1,0], Mission.FlightState.Relax.R[1,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[0,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[3,0], Mission.FlightState.Relax.\gamma[2,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[1,0], Mission.FlightState.Atmosphere.Relax.T_s[3,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[2,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[1,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[1,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[2,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[0,0], Mission.FlightState.Atmosphere.Relax.C_1[2,0], Mission.FlightState.Atmosphere.Relax.T_s[1,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[4,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[0,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[1,0], Mission.FlightSegment.FlightP.Relax.RC_{min}[1,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[3,0], Mission.FlightState.Relax.\gamma[1,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[2,0], Mission.FlightState.Relax.R[2,0], Mission.FlightSegment.FlightP.Relax.RC_{min}[2,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[0,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[3,0], Mission.FlightSegment.FlightP.Relax.RC_{min}[3,0], Mission.FlightState.Atmosphere.Relax.C_1[4,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[3,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[4,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[2,0], Mission.FlightState.Relax.R[4,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[4,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[0,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[2,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[4,0], Mission.FlightState.Atmosphere.Relax.C_1[0,0], Mission.FlightState.Relax.\gamma[3,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[3,0], Mission.FlightState.Atmosphere.Relax.T_s[0,0], Mission.FlightState.Atmosphere.Relax.C_1[1,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[1,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[4,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[4,0], Mission.FlightState.Relax.R[0,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[2,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[4,0], Mission.FlightState.Relax.\gamma[0,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[3,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[0,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[2,0], Mission.FlightState.Relax.R[3,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[3,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[0,0]]Stacktrace
Traceback (most recent call last):
File "/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/tests/helpers.py", line 64, in test
testfn(name, import_dict, path)(self)
File "/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 "/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 "/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/constraints/prog_factories.py", line 124, in solvefn
result = progsolve(solver, verbosity, **kwargs)
File "/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/constraints/sgp.py", line 169, in localsolve
self.result = gp.generate_result(solver_out, verbosity)
File "/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/constraints/gp.py", line 211, in generate_result
result = self._compile_result(solver_out) # NOTE: SIDE EFFECTS
File "/jenkins/workspace/CE_RM_SPaircraft_PR/mosek/gpkit/gpkit/constraints/gp.py", line 298, in _compile_result
% cost.varkeys.keys())
ValueError: cost contains unsolved variables [Mission.FlightSegment.FlightP.Relax.RC_{min}[4,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[1,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[1,0], Mission.FlightState.Relax.\gamma[4,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[0,0], Mission.FlightState.Atmosphere.Relax.T_s[4,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[2,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[3,0], Mission.FlightState.Atmosphere.Relax.T_s[2,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[3,0], Mission.Aircraft.Fuselage.Relax.n_{pass}[0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[2,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[0,0], Mission.FlightState.Atmosphere.Relax.C_1[3,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[4,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[4,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[2,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[1,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[1,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[4,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[3,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[0,0], Mission.FlightSegment.FlightP.Relax.RC_{min}[0,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[1,0], Mission.FlightState.Relax.R[1,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[0,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[3,0], Mission.FlightState.Relax.\gamma[2,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[1,0], Mission.FlightState.Atmosphere.Relax.T_s[3,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[2,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[1,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[1,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[2,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[0,0], Mission.FlightState.Atmosphere.Relax.C_1[2,0], Mission.FlightState.Atmosphere.Relax.T_s[1,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[4,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[0,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[1,0], Mission.FlightSegment.FlightP.Relax.RC_{min}[1,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[3,0], Mission.FlightState.Relax.\gamma[1,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[2,0], Mission.FlightState.Relax.R[2,0], Mission.FlightSegment.FlightP.Relax.RC_{min}[2,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[0,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{o}}[3,0], Mission.FlightSegment.FlightP.Relax.RC_{min}[3,0], Mission.FlightState.Atmosphere.Relax.C_1[4,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[3,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[4,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[2,0], Mission.FlightState.Relax.R[4,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[4,0], Mission.FlightState.Atmosphere.Relax.R_{atm}[0,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[2,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[4,0], Mission.FlightState.Atmosphere.Relax.C_1[0,0], Mission.FlightState.Relax.\gamma[3,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[3,0], Mission.FlightState.Atmosphere.Relax.T_s[0,0], Mission.FlightState.Atmosphere.Relax.C_1[1,0], Mission.FlightState.Atmosphere.Relax.p_{sl}[1,0], Mission.FlightSegment.FlightP.AircraftP.WingPerformance.Relax.f_{L_{t}}[4,0], Mission.FlightState.Atmosphere.Relax.T_{sl}[4,0], Mission.FlightState.Relax.R[0,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[2,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[4,0], Mission.FlightState.Relax.\gamma[0,0], Mission.FlightSegment.FlightP.AircraftP.Relax.W_{Load_{max}}[3,0], Mission.Aircraft.Engine.EnginePerformance.CombustorPerformance.Relax.M_{4a}[0,0], Mission.FlightSegment.FlightP.AircraftP.Relax.V_{stall}[2,0], Mission.FlightState.Relax.R[3,0], Mission.FlightState.Atmosphere.Relax.L_{atm}[3,0], Mission.FlightState.Atmosphere.Relax.M_{atm}[0,0]]
Standard Output
Beginning signomial solve.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.874 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.654 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.721 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.729 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.762 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.589 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.688 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.776 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.831 seconds.
Solving took 9 GP solves and 16.6 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
WEIGHT DIFFERENCES
Total Fuel Weight Percent Diff: [-92.97033271]
Total Aircraft Weight Percent Diff: [-21.17221082]
Engine Weight Percent Diff: -58.76584293252697
Fuselage Weight Percent Diff: 2.309749092316034
Payload Weight Percent Diff: [-0.04003532]
VT Weight Percent Diff: -8.679987604319367
HT Weight Percent Diff: -93.22524498208898
Wing Weight Percent Diff: 8.055766604084313
WING DIFFERENCES
Wing Span Percent Diff: -0.030001313889823626
Wing Area Percent Diff: 33.879051491093065
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: 41.32510317579446
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -11.046130124016372
VT Area Percent Diff: -60.40801531089365
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-19.04693899]
L/D Percent Diff: [24.03451078]
Nacelle Cd Percent Diff: [-94.59140455]
HT Cd Percent Diff: [-80.83157286] dimensionless
Fuselage Cd Percent Diff: [108.78752887]
VT Cd Percent Diff: [-58.32278887] dimensionless
Wing Cd percent Diff: [-14.7849324]
Induced Drag Cd Percent Diff: [0.72317396]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [-90.67467132]
FUSELAGE DIFFERENCES
Weight of HB material: -39.32362159909212
Weight of VB material: 90.53371692152301
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
[0.69501931]
Beginning signomial solve.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.955 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.642 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.808 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.718 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.827 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.578 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.665 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.788 seconds.
Using solver 'mosek'
Solving for 1749 variables.
Solving took 0.934 seconds.
Solution check warning: Primal solution computed cost did not match solver-returned cost: 1.856341347444126e+72 vs 1.85638716626e+72
Solving took 9 GP solves and 18 seconds.
Checking for relaxed constants...
GP iteration 0 has relaxed constants
Cost
----
2.72e+110
Free Variables
--------------
| Mission1.Aircraft.Engine.Turbine.Relax1
C_{p_{t2}} : 2.246 Cp Value for Combustion Products in LP Turbine
| Mission1.Aircraft.Fuselage.Relax1
l_{nose} : 1.067 Nose length
n_{pass} : [ 2.86 ] Number of passengers
| Mission1.Aircraft.Relax1
f_{L_{total/wing}} : 1.683 Total lift as a percentage of wing lift
| Mission1.Aircraft.Wing.WingNoStruct.Relax1
\tan(\Lambda) : 1.109 Tangent of quarter-chord sweep angle
| Mission1.FlightState.Atmosphere.Relax1
L_{atm} : [ 1.78 1 1 1 1 ] Temperature lapse rate
T_{sl} : [ 1 1 1.27 1 1 ] Temperature at sea level
| Mission1.Relax1
R_{req} : 2.352 Required Cruise Range
GP iteration 1 has relaxed constants
Cost
----
1.472e+75
Free Variables
--------------
| Mission1.Aircraft.Engine.Combustor.Relax1
hold_{4a} : 1.117 1+(gamma-1)/2 * M_4a**2
| Mission1.Aircraft.Fuselage.Relax1
n_{pass} : [ 1.04 ] Number of passengers
| Mission1.Aircraft.LandingGear.Relax1
h_{hold} : 1.007 Hold height
Solution check warning: sum of nu^T * A did not vanish
Solution check warning: Primal solution computed cost did not match solver-returned cost: 1.9301585735000924e+72 vs 1.93022155763e+72
Solution check warning: Primal solution computed cost did not match solver-returned cost: 1.856341347444126e+72 vs 1.85638716626e+72
WEIGHT DIFFERENCES
Total Fuel Weight Percent Diff: [-92.97034179]
Total Aircraft Weight Percent Diff: [-21.17215264]
Engine Weight Percent Diff: -58.76551060641039
Fuselage Weight Percent Diff: 2.3096805100875586
Payload Weight Percent Diff: [-0.04003555]
VT Weight Percent Diff: -8.680893291780798
HT Weight Percent Diff: -93.22545106761258
Wing Weight Percent Diff: 8.056036659405914
WING DIFFERENCES
Wing Span Percent Diff: -0.02999449313859564
Wing Area Percent Diff: 33.87816551325714
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: 41.323548078592225
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -11.046133851503638
VT Area Percent Diff: -60.408018628651
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-19.04567833]
L/D Percent Diff: [24.03454583]
Nacelle Cd Percent Diff: [-94.591398]
HT Cd Percent Diff: [-80.83173245] dimensionless
Fuselage Cd Percent Diff: [108.78752887]
VT Cd Percent Diff: [-58.32254876] dimensionless
Wing Cd percent Diff: [-14.78376556]
Induced Drag Cd Percent Diff: [0.72569956]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [-90.67469378]
FUSELAGE DIFFERENCES
Weight of HB material: -39.327003339303786
Weight of VB material: 90.50381911990638
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
[0.69501821]
Beginning signomial solve.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.405 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.393 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.346 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.304 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.291 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.301 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.311 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.33 seconds.
Using solver 'mosek_conif'
Solving for 1749 variables.
Solving took 0.303 seconds.