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.