Failed
gpkit.tests.from_paths.TestFiles.test_SPaircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20200225153233)
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 0.337 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.272 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.323 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.312 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.302 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.253 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.304 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.325 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.332 seconds. Solving took 9 GP solves and 11.7 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 0.45 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.24 seconds. Using solver 'mosek' Solving for 1749 variables. Solving took 0.324 seconds. Beginning signomial solve. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.245 seconds. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.244 seconds. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.249 seconds. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.225 seconds. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.24 seconds. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.234 seconds. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.22 seconds. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.212 seconds. Using solver 'mosek_conif' Solving for 1749 variables. Solving took 0.229 seconds.