Failed
gpkit.tests.from_paths.TestFiles.test_model_jho_py_mosek_conif (from gpkit.tests.from_paths.TestFiles-20200714225616)
Failing for the past 1 build
(Since Failed
)
Error Message
Invalid ConstraintSet element '[<gpkit.Climb object containing 2 top-level constraint(s) and 933 variable(s)>, <gpkit.Cruise object containing 2 top-level constraint(s) and 364 variable(s)>, <gpkit.Loiter object containing 2 top-level constraint(s) and 612 variable(s)>, <gpkit.Cruise object containing 2 top-level constraint(s) and 364 variable(s)>]' <class 'list'> was between Aircraft ======== Cost ---- 1 Constraints ----------- Fuselage FuelTank Mission1.Aircraft.Fuselage.FuelTank.W >= f·W_{fuel-tot} \mathcal{V}/Mission1.Aircraft.Fuselage.FuelTank.m_{fac} >= W_{fuel-tot}/\rho_{fuel} FuselageSkin m >= S_{wet}·\rho_{kevlar}·Mission1.Aircraft.Fuselage.FuselageSkin.t Mission1.Aircraft.Fuselage.FuselageSkin.W >= m·Mission1.Aircraft.Fuselage.FuselageSkin.g Mission1.Aircraft.Fuselage.FuselageSkin.t >= t_{min} Mission1.Aircraft.Fuselage.FuselageSkin.I <= π·R³·Mission1.Aircraft.Fuselage.FuselageSkin.t I_G >= m·(4·R² + 4·R·Mission1.Aircraft.Fuselage.FuselageSkin.t + Mission1.Aircraft.Fuselage.FuselageSkin.t²) l_{body} = l_{body} Mission1.Aircraft.Fuselage.FuselageSkin.E = Mission1.Aircraft.Fuselage.FuselageSkin.E k_{body} = l_{body}/R S_{wet} >= S_{body} + S_{nose} + S_{bulk} S_{body} >= 2π·R·l_{body} S_{nose}^1.6 >= (2π·R²)^1.6·(0.333 + 0.667·k_{nose}^1.6) S_{bulk} >= R²·(0.0123·k_{bulk}² + 1.52·k_{bulk} + 0.502) \mathcal{V}_{body} <= π·R²·l_{body} Mission1.Aircraft.Fuselage.l <= 3·R·(k_{body}·k_{nose}·k_{bulk})^0.3333333333333333 Mission1.Aircraft.Fuselage.S >= π·R² \mathcal{V}_{body} >= \mathcal{V} Mission1.Aircraft.Fuselage.W/Mission1.Aircraft.Fuselage.m_{fac} >= Mission1.Aircraft.Fuselage.FuelTank.W + Mission1.Aircraft.Fuselage.FuselageSkin.W Wing Mission1.Aircraft.Wing.W/Mission1.Aircraft.Wing.mfac >= Mission1.Aircraft.Wing.WingSkin.W + Mission1.Aircraft.Wing.CapSpar.W + Mission1.Aircraft.Wing.WingCore.W Planform Mission1.Aircraft.Wing.Planform.b² = Mission1.Aircraft.Wing.Planform.S·Mission1.Aircraft.Wing.Planform.AR cave[:] = cbave[:]·Mission1.Aircraft.Wing.Planform.S/Mission1.Aircraft.Wing.Planform.b Mission1.Aircraft.Wing.Planform.croot = Mission1.Aircraft.Wing.Planform.S/Mission1.Aircraft.Wing.Planform.b·cbar[0] Mission1.Aircraft.Wing.Planform.cmac = Mission1.Aircraft.Wing.Planform.croot·Mission1.Aircraft.Wing.Planform.cbarmac WingSkin Mission1.Aircraft.Wing.WingSkin.W >= CFRPFabric.rho·Mission1.Aircraft.Wing.Planform.S·2·Mission1.Aircraft.Wing.WingSkin.t·g Mission1.Aircraft.Wing.WingSkin.t >= tmin CFRPFabric.tau >= 1/Mission1.Aircraft.Wing.WingSkin.Jtbar/Mission1.Aircraft.Wing.Planform.croot²/Mission1.Aircraft.Wing.WingSkin.t·Mission1.Aircraft.Wing.WingSkin.Cmw·Mission1.Aircraft.Wing.Planform.S·Mission1.Aircraft.Wing.WingSkin.rhosl·Mission1.Aircraft.Wing.WingSkin.Vne² CapSpar I[:]/Mission1.Aircraft.Wing.CapSpar.mfac <= 2·w[:]·t[:]·(hin[:]/2)² dm[:] >= (CFRPUD.rho·2·w[:]·t[:] + 2·tshear[:]·CFRPFabric.rho·(hin[:] + 2·t[:]) + FoamHD.rho·w[:]·hin[:])·Mission1.Aircraft.Wing.Planform.b/2·deta[:] Mission1.Aircraft.Wing.CapSpar.W >= 2·dm[:].sum()·g w[:] <= wlim·cave[:] cave[:]·Mission1.Aircraft.Wing.Planform.tau >= hin[:] + 2·t[:] Sy[:]·(hin[:]/2 + t[:]) <= I[:] tshear[:] >= tmin WingCore Mission1.Aircraft.Wing.WingCore.W >= 2·(g·FoamHD.rho·Mission1.Aircraft.Wing.WingCore.Abar·cave[:]²·Mission1.Aircraft.Wing.Planform.b/2·deta[:]).sum() mw·(1 + 2/Mission1.Aircraft.Wing.Planform.AR) >= 6.28 DF70 W_{DF70} <= Mission1.Aircraft.DF70.W/Mission1.Aircraft.DF70.m_{fac} P_{sl-max} = P_{sl-max} Empennage HorizontalTail Mission1.Aircraft.Empennage.HorizontalTail.W/Mission1.Aircraft.Empennage.HorizontalTail.mfac >= Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.W + Mission1.Aircraft.Empennage.HorizontalTail.WingCore.W Planform Mission1.Aircraft.Empennage.HorizontalTail.Planform.b² = Mission1.Aircraft.Empennage.HorizontalTail.Planform.S·Mission1.Aircraft.Empennage.HorizontalTail.Planform.AR cave[:] = cbave[:]·Mission1.Aircraft.Empennage.HorizontalTail.Planform.S/Mission1.Aircraft.Empennage.HorizontalTail.Planform.b Mission1.Aircraft.Empennage.HorizontalTail.Planform.croot = Mission1.Aircraft.Empennage.HorizontalTail.Planform.S/Mission1.Aircraft.Empennage.HorizontalTail.Planform.b·cbar[0] Mission1.Aircraft.Empennage.HorizontalTail.Planform.cmac = Mission1.Aircraft.Empennage.HorizontalTail.Planform.croot·Mission1.Aircraft.Empennage.HorizontalTail.Planform.cbarmac WingSkin Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.W >= CFRPFabric.rho·Mission1.Aircraft.Empennage.HorizontalTail.Planform.S·2·Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.t·g Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.t >= tmin CFRPFabric.tau >= 1/Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.Jtbar/Mission1.Aircraft.Empennage.HorizontalTail.Planform.croot²/Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.t·Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.Cmw·Mission1.Aircraft.Empennage.HorizontalTail.Planform.S·Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.rhosl·Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.Vne² WingCore Mission1.Aircraft.Empennage.HorizontalTail.WingCore.W >= 2·(g·FoamHD.rho·Mission1.Aircraft.Empennage.HorizontalTail.WingCore.Abar·cave[:]²·Mission1.Aircraft.Empennage.HorizontalTail.Planform.b/2·deta[:]).sum() mh·(1 + 2/Mission1.Aircraft.Empennage.HorizontalTail.Planform.AR) <= 6.28 VerticalTail Mission1.Aircraft.Empennage.VerticalTail.W/Mission1.Aircraft.Empennage.VerticalTail.mfac >= Mission1.Aircraft.Empennage.VerticalTail.WingSkin.W + Mission1.Aircraft.Empennage.VerticalTail.WingCore.W Planform Mission1.Aircraft.Empennage.VerticalTail.Planform.b² = Mission1.Aircraft.Empennage.VerticalTail.Planform.S·Mission1.Aircraft.Empennage.VerticalTail.Planform.AR cave[:] = cbave[:]·Mission1.Aircraft.Empennage.VerticalTail.Planform.S/Mission1.Aircraft.Empennage.VerticalTail.Planform.b Mission1.Aircraft.Empennage.VerticalTail.Planform.croot = Mission1.Aircraft.Empennage.VerticalTail.Planform.S/Mission1.Aircraft.Empennage.VerticalTail.Planform.b·cbar[0] Mission1.Aircraft.Empennage.VerticalTail.Planform.cmac = Mission1.Aircraft.Empennage.VerticalTail.Planform.croot·Mission1.Aircraft.Empennage.VerticalTail.Planform.cbarmac WingSkin Mission1.Aircraft.Empennage.VerticalTail.WingSkin.W >= CFRPFabric.rho·Mission1.Aircraft.Empennage.VerticalTail.Planform.S·2·Mission1.Aircraft.Empennage.VerticalTail.WingSkin.t·g Mission1.Aircraft.Empennage.VerticalTail.WingSkin.t >= tmin CFRPFabric.tau >= 1/Mission1.Aircraft.Empennage.VerticalTail.WingSkin.Jtbar/Mission1.Aircraft.Empennage.VerticalTail.Planform.croot²/Mission1.Aircraft.Empennage.VerticalTail.WingSkin.t·Mission1.Aircraft.Empennage.VerticalTail.WingSkin.Cmw·Mission1.Aircraft.Empennage.VerticalTail.Planform.S·Mission1.Aircraft.Empennage.VerticalTail.WingSkin.rhosl·Mission1.Aircraft.Empennage.VerticalTail.WingSkin.Vne² WingCore Mission1.Aircraft.Empennage.VerticalTail.WingCore.W >= 2·(g·FoamHD.rho·Mission1.Aircraft.Empennage.VerticalTail.WingCore.Abar·cave[:]²·Mission1.Aircraft.Empennage.VerticalTail.Planform.b/2·deta[:]).sum() TailBoom I[:] <= π·t[:]·d[:]³/8 Sy[:] <= 2·I[:]/d[:] dm[:] >= π·CFRPFabric.rho·d[:]·Mission1.Aircraft.Empennage.TailBoom.deta·t[:]·kfac·Mission1.Aircraft.Empennage.TailBoom.l Mission1.Aircraft.Empennage.TailBoom.W/Mission1.Aircraft.Empennage.TailBoom.mfac >= g·dm[:].sum() t[:] >= tmin Mission1.Aircraft.Empennage.TailBoom.S = Mission1.Aircraft.Empennage.TailBoom.l·π·d[0] Mission1.Aircraft.Empennage.TailBoom.b = 2·Mission1.Aircraft.Empennage.TailBoom.l Mission1.Aircraft.Empennage.W/Mission1.Aircraft.Empennage.mfac >= Mission1.Aircraft.Empennage.HorizontalTail.W + Mission1.Aircraft.Empennage.VerticalTail.W + Mission1.Aircraft.Empennage.TailBoom.W Mission1.Aircraft.Empennage.TailBoom.l >= lh Mission1.Aircraft.Empennage.TailBoom.l >= lv Pylon Mission1.Aircraft.Pylon.S >= 2·Mission1.Aircraft.Pylon.l·Mission1.Aircraft.Pylon.h W_{zfw} >= Mission1.Aircraft.Fuselage.W + Mission1.Aircraft.Wing.W + Mission1.Aircraft.DF70.W + Mission1.Aircraft.Empennage.W + Mission1.Aircraft.Pylon.W + W_{pay} + W_{avn} Vh <= Mission1.Aircraft.Empennage.HorizontalTail.Planform.S·lh/Mission1.Aircraft.Wing.Planform.S²·Mission1.Aircraft.Wing.Planform.b Vv = Mission1.Aircraft.Empennage.VerticalTail.Planform.S·lv/Mission1.Aircraft.Wing.Planform.S/Mission1.Aircraft.Wing.Planform.b Mission1.Aircraft.Wing.Planform.CLmax/mw <= Mission1.Aircraft.Empennage.HorizontalTail.Planform.CLmax/mh w_{antenna} <= Mission1.Aircraft.Empennage.VerticalTail.Planform.croot·Mission1.Aircraft.Empennage.VerticalTail.Planform.lam Mission1.Aircraft.Empennage.VerticalTail.Planform.b >= l_{antenna} Mission1.Aircraft.Empennage.TailBoom.l >= lh + Mission1.Aircraft.Empennage.HorizontalTail.Planform.croot \mathcal{V}_{pay} <= (π/1.5)·k_{nose}·R³ \mathcal{V}_{body} >= \mathcal{V} + \mathcal{V}_{avn} Mission1.Aircraft.DF70.h <= 2·R and AircraftLoading =============== Cost ---- 1 Constraints ----------- TailBoomBending dx[:] = Mission1.Aircraft.Empennage.TailBoom.deta qne[:]·Mission1.Aircraft.Empennage.HorizontalTail.Planform.S <= Mission1.AircraftLoading.TailBoomBending.F \bar{EI}[:] <= CFRPFabric.E·I[:]/Mission1.AircraftLoading.TailBoomBending.F/l²/2 Mr[:] >= \bar{M}[:-1]·Mission1.AircraftLoading.TailBoomBending.F·l Mr[:]/Sy[:] <= CFRPFabric.sigma Mission1.AircraftLoading.TailBoomBending.th = \theta[1] Mission1.AircraftLoading.TailBoomBending.kappa >= \bar{\delta}[1]·Mission1.Aircraft.Empennage.HorizontalTail.Planform.CLmax·Mission1.AircraftLoading.TailBoomBending.Nsafety Beam \bar{M}[:-1] >= \bar{M}[1:] + 0.5·dx[:]·(\bar{S}[:-1] + \bar{S}[1:]) \bar{M}[1] >= Mission1.AircraftLoading.TailBoomBending.Beam.\bar{M}_{tip} \theta[0] >= Mission1.AircraftLoading.TailBoomBending.Beam.\theta_{root} \theta[1:] >= \theta[:-1] + 0.5·dx[:]·(\bar{M}[1:] + \bar{M}[:-1])/\bar{EI}[:] \bar{\delta}[0] >= Mission1.AircraftLoading.TailBoomBending.Beam.\bar{\delta}_{root} \bar{\delta}[1:] >= \bar{\delta}[:-1] + 0.5·dx[:]·(\theta[1:] + \theta[:-1]) TailBoomBending1 dx[:] = Mission1.Aircraft.Empennage.TailBoom.deta qne[:]·Mission1.Aircraft.Empennage.VerticalTail.Planform.S <= Mission1.AircraftLoading.TailBoomBending1.F \bar{EI}[:] <= CFRPFabric.E·I[:]/Mission1.AircraftLoading.TailBoomBending1.F/l²/2 Mr[:] >= \bar{M}[:-1]·Mission1.AircraftLoading.TailBoomBending1.F·l Mr[:]/Sy[:] <= CFRPFabric.sigma Mission1.AircraftLoading.TailBoomBending1.th = \theta[1] Mission1.AircraftLoading.TailBoomBending1.kappa >= \bar{\delta}[1]·Mission1.Aircraft.Empennage.VerticalTail.Planform.CLmax·Mission1.AircraftLoading.TailBoomBending1.Nsafety Beam \bar{M}[:-1] >= \bar{M}[1:] + 0.5·dx[:]·(\bar{S}[:-1] + \bar{S}[1:]) \bar{M}[1] >= Mission1.AircraftLoading.TailBoomBending1.Beam.\bar{M}_{tip} \theta[0] >= Mission1.AircraftLoading.TailBoomBending1.Beam.\theta_{root} \theta[1:] >= \theta[:-1] + 0.5·dx[:]·(\bar{M}[1:] + \bar{M}[:-1])/\bar{EI}[:] \bar{\delta}[0] >= Mission1.AircraftLoading.TailBoomBending1.Beam.\bar{\delta}_{root} \bar{\delta}[1:] >= \bar{\delta}[:-1] + 0.5·dx[:]·(\theta[1:] + \theta[:-1]) SparLoading S[:-1] >= S[1:] + 0.5·deta[:]·b/2·(q[:-1] + q[1:]) M[:-1] >= M[1:] + 0.5·deta[:]·b/2·(S[:-1] + S[1:]) N = Mission1.AircraftLoading.SparLoading.Nsafety·Nmax q[:] >= N·W/b·cbar[:] S[11] >= Stip M[11] >= Mtip th[0] >= throot th[1:] >= th[:-1] + 0.5·deta[:]·b/2·(M[1:] + M[:-1])/CFRPUD.E/I[:] w[0] >= wroot w[1:] >= w[:-1] + 0.5·deta[:]·b/2·(th[1:] + th[:-1]) M[:-1]/Sy[:] <= CFRPUD.sigma Mission1.AircraftLoading.SparLoading.kappa >= w[11]/(b/2) FuselageLoading FuselageSkinL M_h >= Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.N_{max}·W_{cent}/4·l_{body} Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.\sigma_{Kevlar} >= M_h·R/Mission1.Aircraft.Fuselage.FuselageSkin.I Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.q >= W_{cent}·Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.N_{max}/l_{body} \kappa·l_{body}/2 >= Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.q·(l_{body}/2)⁴/(8·Mission1.Aircraft.Fuselage.FuselageSkin.E·Mission1.Aircraft.Fuselage.FuselageSkin.I) FuselageLanding Mission1.AircraftLoading.FuselageLoading.FuselageLanding.F >= W_{cent}·Mission1.AircraftLoading.FuselageLoading.FuselageLanding.N_{max} a >= Mission1.AircraftLoading.FuselageLoading.FuselageLanding.F/m \dot{\omega} >= a/(l_{body}/2) M_G >= I_G·\dot{\omega} Mission1.AircraftLoading.FuselageLoading.FuselageLanding.\sigma_{Kevlar} >= M_G·R/Mission1.Aircraft.Fuselage.FuselageSkin.I TailBoomFlexibility Fne >= 1 + mh·Mission1.AircraftLoading.TailBoomBending.th sph1·mw·Fne/mh/Vh + deda <= 1 sph2 <= Vh·CLhmin/Mission1.Aircraft.Wing.Planform.CLmax deda >= mw·Mission1.Aircraft.Wing.Planform.S/b/4/π/lh sph1 + sph2 >= SMcorr + CM/Mission1.Aircraft.Wing.Planform.CLmax.
Stacktrace
Traceback (most recent call last): File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/constraints/set.py", line 86, in __init__ self._update(subconstraint) File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/constraints/set.py", line 114, in _update self.substitutions.update(constraint.substitutions) File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/keydict.py", line 157, in update self[k] = v File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/keydict.py", line 220, in __setitem__ goodvals = ~np.isnan(value) TypeError: ufunc 'isnan' not supported for the input types, and the inputs could not be safely coerced to any supported types according to the casting rule ''safe'' The above exception was the direct cause of the following exception: Traceback (most recent call last): File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/tests/helpers.py", line 59, in test testfn(name, import_dict, path)(self) File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/tests/from_paths.py", line 48, in <lambda> lambda self: getattr(self, name)())) # pylint:disable=undefined-variable File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/tests/from_paths.py", line 37, in test_fn mod.test() File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/jho/model/jho.py", line 366, in test model = Mission() File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/constraints/model.py", line 71, in __init__ CostedConstraintSet.__init__(self, cost, constraints, substitutions) File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/constraints/costed.py", line 25, in __init__ ConstraintSet.__init__(self, constraints, subs) File "/Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/gpkit/constraints/set.py", line 88, in __init__ raise badelement(self, i, constraint) from e ValueError: Invalid ConstraintSet element '[<gpkit.Climb object containing 2 top-level constraint(s) and 933 variable(s)>, <gpkit.Cruise object containing 2 top-level constraint(s) and 364 variable(s)>, <gpkit.Loiter object containing 2 top-level constraint(s) and 612 variable(s)>, <gpkit.Cruise object containing 2 top-level constraint(s) and 364 variable(s)>]' <class 'list'> was between Aircraft ======== Cost ---- 1 Constraints ----------- Fuselage FuelTank Mission1.Aircraft.Fuselage.FuelTank.W >= f·W_{fuel-tot} \mathcal{V}/Mission1.Aircraft.Fuselage.FuelTank.m_{fac} >= W_{fuel-tot}/\rho_{fuel} FuselageSkin m >= S_{wet}·\rho_{kevlar}·Mission1.Aircraft.Fuselage.FuselageSkin.t Mission1.Aircraft.Fuselage.FuselageSkin.W >= m·Mission1.Aircraft.Fuselage.FuselageSkin.g Mission1.Aircraft.Fuselage.FuselageSkin.t >= t_{min} Mission1.Aircraft.Fuselage.FuselageSkin.I <= π·R³·Mission1.Aircraft.Fuselage.FuselageSkin.t I_G >= m·(4·R² + 4·R·Mission1.Aircraft.Fuselage.FuselageSkin.t + Mission1.Aircraft.Fuselage.FuselageSkin.t²) l_{body} = l_{body} Mission1.Aircraft.Fuselage.FuselageSkin.E = Mission1.Aircraft.Fuselage.FuselageSkin.E k_{body} = l_{body}/R S_{wet} >= S_{body} + S_{nose} + S_{bulk} S_{body} >= 2π·R·l_{body} S_{nose}^1.6 >= (2π·R²)^1.6·(0.333 + 0.667·k_{nose}^1.6) S_{bulk} >= R²·(0.0123·k_{bulk}² + 1.52·k_{bulk} + 0.502) \mathcal{V}_{body} <= π·R²·l_{body} Mission1.Aircraft.Fuselage.l <= 3·R·(k_{body}·k_{nose}·k_{bulk})^0.3333333333333333 Mission1.Aircraft.Fuselage.S >= π·R² \mathcal{V}_{body} >= \mathcal{V} Mission1.Aircraft.Fuselage.W/Mission1.Aircraft.Fuselage.m_{fac} >= Mission1.Aircraft.Fuselage.FuelTank.W + Mission1.Aircraft.Fuselage.FuselageSkin.W Wing Mission1.Aircraft.Wing.W/Mission1.Aircraft.Wing.mfac >= Mission1.Aircraft.Wing.WingSkin.W + Mission1.Aircraft.Wing.CapSpar.W + Mission1.Aircraft.Wing.WingCore.W Planform Mission1.Aircraft.Wing.Planform.b² = Mission1.Aircraft.Wing.Planform.S·Mission1.Aircraft.Wing.Planform.AR cave[:] = cbave[:]·Mission1.Aircraft.Wing.Planform.S/Mission1.Aircraft.Wing.Planform.b Mission1.Aircraft.Wing.Planform.croot = Mission1.Aircraft.Wing.Planform.S/Mission1.Aircraft.Wing.Planform.b·cbar[0] Mission1.Aircraft.Wing.Planform.cmac = Mission1.Aircraft.Wing.Planform.croot·Mission1.Aircraft.Wing.Planform.cbarmac WingSkin Mission1.Aircraft.Wing.WingSkin.W >= CFRPFabric.rho·Mission1.Aircraft.Wing.Planform.S·2·Mission1.Aircraft.Wing.WingSkin.t·g Mission1.Aircraft.Wing.WingSkin.t >= tmin CFRPFabric.tau >= 1/Mission1.Aircraft.Wing.WingSkin.Jtbar/Mission1.Aircraft.Wing.Planform.croot²/Mission1.Aircraft.Wing.WingSkin.t·Mission1.Aircraft.Wing.WingSkin.Cmw·Mission1.Aircraft.Wing.Planform.S·Mission1.Aircraft.Wing.WingSkin.rhosl·Mission1.Aircraft.Wing.WingSkin.Vne² CapSpar I[:]/Mission1.Aircraft.Wing.CapSpar.mfac <= 2·w[:]·t[:]·(hin[:]/2)² dm[:] >= (CFRPUD.rho·2·w[:]·t[:] + 2·tshear[:]·CFRPFabric.rho·(hin[:] + 2·t[:]) + FoamHD.rho·w[:]·hin[:])·Mission1.Aircraft.Wing.Planform.b/2·deta[:] Mission1.Aircraft.Wing.CapSpar.W >= 2·dm[:].sum()·g w[:] <= wlim·cave[:] cave[:]·Mission1.Aircraft.Wing.Planform.tau >= hin[:] + 2·t[:] Sy[:]·(hin[:]/2 + t[:]) <= I[:] tshear[:] >= tmin WingCore Mission1.Aircraft.Wing.WingCore.W >= 2·(g·FoamHD.rho·Mission1.Aircraft.Wing.WingCore.Abar·cave[:]²·Mission1.Aircraft.Wing.Planform.b/2·deta[:]).sum() mw·(1 + 2/Mission1.Aircraft.Wing.Planform.AR) >= 6.28 DF70 W_{DF70} <= Mission1.Aircraft.DF70.W/Mission1.Aircraft.DF70.m_{fac} P_{sl-max} = P_{sl-max} Empennage HorizontalTail Mission1.Aircraft.Empennage.HorizontalTail.W/Mission1.Aircraft.Empennage.HorizontalTail.mfac >= Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.W + Mission1.Aircraft.Empennage.HorizontalTail.WingCore.W Planform Mission1.Aircraft.Empennage.HorizontalTail.Planform.b² = Mission1.Aircraft.Empennage.HorizontalTail.Planform.S·Mission1.Aircraft.Empennage.HorizontalTail.Planform.AR cave[:] = cbave[:]·Mission1.Aircraft.Empennage.HorizontalTail.Planform.S/Mission1.Aircraft.Empennage.HorizontalTail.Planform.b Mission1.Aircraft.Empennage.HorizontalTail.Planform.croot = Mission1.Aircraft.Empennage.HorizontalTail.Planform.S/Mission1.Aircraft.Empennage.HorizontalTail.Planform.b·cbar[0] Mission1.Aircraft.Empennage.HorizontalTail.Planform.cmac = Mission1.Aircraft.Empennage.HorizontalTail.Planform.croot·Mission1.Aircraft.Empennage.HorizontalTail.Planform.cbarmac WingSkin Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.W >= CFRPFabric.rho·Mission1.Aircraft.Empennage.HorizontalTail.Planform.S·2·Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.t·g Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.t >= tmin CFRPFabric.tau >= 1/Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.Jtbar/Mission1.Aircraft.Empennage.HorizontalTail.Planform.croot²/Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.t·Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.Cmw·Mission1.Aircraft.Empennage.HorizontalTail.Planform.S·Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.rhosl·Mission1.Aircraft.Empennage.HorizontalTail.WingSkin.Vne² WingCore Mission1.Aircraft.Empennage.HorizontalTail.WingCore.W >= 2·(g·FoamHD.rho·Mission1.Aircraft.Empennage.HorizontalTail.WingCore.Abar·cave[:]²·Mission1.Aircraft.Empennage.HorizontalTail.Planform.b/2·deta[:]).sum() mh·(1 + 2/Mission1.Aircraft.Empennage.HorizontalTail.Planform.AR) <= 6.28 VerticalTail Mission1.Aircraft.Empennage.VerticalTail.W/Mission1.Aircraft.Empennage.VerticalTail.mfac >= Mission1.Aircraft.Empennage.VerticalTail.WingSkin.W + Mission1.Aircraft.Empennage.VerticalTail.WingCore.W Planform Mission1.Aircraft.Empennage.VerticalTail.Planform.b² = Mission1.Aircraft.Empennage.VerticalTail.Planform.S·Mission1.Aircraft.Empennage.VerticalTail.Planform.AR cave[:] = cbave[:]·Mission1.Aircraft.Empennage.VerticalTail.Planform.S/Mission1.Aircraft.Empennage.VerticalTail.Planform.b Mission1.Aircraft.Empennage.VerticalTail.Planform.croot = Mission1.Aircraft.Empennage.VerticalTail.Planform.S/Mission1.Aircraft.Empennage.VerticalTail.Planform.b·cbar[0] Mission1.Aircraft.Empennage.VerticalTail.Planform.cmac = Mission1.Aircraft.Empennage.VerticalTail.Planform.croot·Mission1.Aircraft.Empennage.VerticalTail.Planform.cbarmac WingSkin Mission1.Aircraft.Empennage.VerticalTail.WingSkin.W >= CFRPFabric.rho·Mission1.Aircraft.Empennage.VerticalTail.Planform.S·2·Mission1.Aircraft.Empennage.VerticalTail.WingSkin.t·g Mission1.Aircraft.Empennage.VerticalTail.WingSkin.t >= tmin CFRPFabric.tau >= 1/Mission1.Aircraft.Empennage.VerticalTail.WingSkin.Jtbar/Mission1.Aircraft.Empennage.VerticalTail.Planform.croot²/Mission1.Aircraft.Empennage.VerticalTail.WingSkin.t·Mission1.Aircraft.Empennage.VerticalTail.WingSkin.Cmw·Mission1.Aircraft.Empennage.VerticalTail.Planform.S·Mission1.Aircraft.Empennage.VerticalTail.WingSkin.rhosl·Mission1.Aircraft.Empennage.VerticalTail.WingSkin.Vne² WingCore Mission1.Aircraft.Empennage.VerticalTail.WingCore.W >= 2·(g·FoamHD.rho·Mission1.Aircraft.Empennage.VerticalTail.WingCore.Abar·cave[:]²·Mission1.Aircraft.Empennage.VerticalTail.Planform.b/2·deta[:]).sum() TailBoom I[:] <= π·t[:]·d[:]³/8 Sy[:] <= 2·I[:]/d[:] dm[:] >= π·CFRPFabric.rho·d[:]·Mission1.Aircraft.Empennage.TailBoom.deta·t[:]·kfac·Mission1.Aircraft.Empennage.TailBoom.l Mission1.Aircraft.Empennage.TailBoom.W/Mission1.Aircraft.Empennage.TailBoom.mfac >= g·dm[:].sum() t[:] >= tmin Mission1.Aircraft.Empennage.TailBoom.S = Mission1.Aircraft.Empennage.TailBoom.l·π·d[0] Mission1.Aircraft.Empennage.TailBoom.b = 2·Mission1.Aircraft.Empennage.TailBoom.l Mission1.Aircraft.Empennage.W/Mission1.Aircraft.Empennage.mfac >= Mission1.Aircraft.Empennage.HorizontalTail.W + Mission1.Aircraft.Empennage.VerticalTail.W + Mission1.Aircraft.Empennage.TailBoom.W Mission1.Aircraft.Empennage.TailBoom.l >= lh Mission1.Aircraft.Empennage.TailBoom.l >= lv Pylon Mission1.Aircraft.Pylon.S >= 2·Mission1.Aircraft.Pylon.l·Mission1.Aircraft.Pylon.h W_{zfw} >= Mission1.Aircraft.Fuselage.W + Mission1.Aircraft.Wing.W + Mission1.Aircraft.DF70.W + Mission1.Aircraft.Empennage.W + Mission1.Aircraft.Pylon.W + W_{pay} + W_{avn} Vh <= Mission1.Aircraft.Empennage.HorizontalTail.Planform.S·lh/Mission1.Aircraft.Wing.Planform.S²·Mission1.Aircraft.Wing.Planform.b Vv = Mission1.Aircraft.Empennage.VerticalTail.Planform.S·lv/Mission1.Aircraft.Wing.Planform.S/Mission1.Aircraft.Wing.Planform.b Mission1.Aircraft.Wing.Planform.CLmax/mw <= Mission1.Aircraft.Empennage.HorizontalTail.Planform.CLmax/mh w_{antenna} <= Mission1.Aircraft.Empennage.VerticalTail.Planform.croot·Mission1.Aircraft.Empennage.VerticalTail.Planform.lam Mission1.Aircraft.Empennage.VerticalTail.Planform.b >= l_{antenna} Mission1.Aircraft.Empennage.TailBoom.l >= lh + Mission1.Aircraft.Empennage.HorizontalTail.Planform.croot \mathcal{V}_{pay} <= (π/1.5)·k_{nose}·R³ \mathcal{V}_{body} >= \mathcal{V} + \mathcal{V}_{avn} Mission1.Aircraft.DF70.h <= 2·R and AircraftLoading =============== Cost ---- 1 Constraints ----------- TailBoomBending dx[:] = Mission1.Aircraft.Empennage.TailBoom.deta qne[:]·Mission1.Aircraft.Empennage.HorizontalTail.Planform.S <= Mission1.AircraftLoading.TailBoomBending.F \bar{EI}[:] <= CFRPFabric.E·I[:]/Mission1.AircraftLoading.TailBoomBending.F/l²/2 Mr[:] >= \bar{M}[:-1]·Mission1.AircraftLoading.TailBoomBending.F·l Mr[:]/Sy[:] <= CFRPFabric.sigma Mission1.AircraftLoading.TailBoomBending.th = \theta[1] Mission1.AircraftLoading.TailBoomBending.kappa >= \bar{\delta}[1]·Mission1.Aircraft.Empennage.HorizontalTail.Planform.CLmax·Mission1.AircraftLoading.TailBoomBending.Nsafety Beam \bar{M}[:-1] >= \bar{M}[1:] + 0.5·dx[:]·(\bar{S}[:-1] + \bar{S}[1:]) \bar{M}[1] >= Mission1.AircraftLoading.TailBoomBending.Beam.\bar{M}_{tip} \theta[0] >= Mission1.AircraftLoading.TailBoomBending.Beam.\theta_{root} \theta[1:] >= \theta[:-1] + 0.5·dx[:]·(\bar{M}[1:] + \bar{M}[:-1])/\bar{EI}[:] \bar{\delta}[0] >= Mission1.AircraftLoading.TailBoomBending.Beam.\bar{\delta}_{root} \bar{\delta}[1:] >= \bar{\delta}[:-1] + 0.5·dx[:]·(\theta[1:] + \theta[:-1]) TailBoomBending1 dx[:] = Mission1.Aircraft.Empennage.TailBoom.deta qne[:]·Mission1.Aircraft.Empennage.VerticalTail.Planform.S <= Mission1.AircraftLoading.TailBoomBending1.F \bar{EI}[:] <= CFRPFabric.E·I[:]/Mission1.AircraftLoading.TailBoomBending1.F/l²/2 Mr[:] >= \bar{M}[:-1]·Mission1.AircraftLoading.TailBoomBending1.F·l Mr[:]/Sy[:] <= CFRPFabric.sigma Mission1.AircraftLoading.TailBoomBending1.th = \theta[1] Mission1.AircraftLoading.TailBoomBending1.kappa >= \bar{\delta}[1]·Mission1.Aircraft.Empennage.VerticalTail.Planform.CLmax·Mission1.AircraftLoading.TailBoomBending1.Nsafety Beam \bar{M}[:-1] >= \bar{M}[1:] + 0.5·dx[:]·(\bar{S}[:-1] + \bar{S}[1:]) \bar{M}[1] >= Mission1.AircraftLoading.TailBoomBending1.Beam.\bar{M}_{tip} \theta[0] >= Mission1.AircraftLoading.TailBoomBending1.Beam.\theta_{root} \theta[1:] >= \theta[:-1] + 0.5·dx[:]·(\bar{M}[1:] + \bar{M}[:-1])/\bar{EI}[:] \bar{\delta}[0] >= Mission1.AircraftLoading.TailBoomBending1.Beam.\bar{\delta}_{root} \bar{\delta}[1:] >= \bar{\delta}[:-1] + 0.5·dx[:]·(\theta[1:] + \theta[:-1]) SparLoading S[:-1] >= S[1:] + 0.5·deta[:]·b/2·(q[:-1] + q[1:]) M[:-1] >= M[1:] + 0.5·deta[:]·b/2·(S[:-1] + S[1:]) N = Mission1.AircraftLoading.SparLoading.Nsafety·Nmax q[:] >= N·W/b·cbar[:] S[11] >= Stip M[11] >= Mtip th[0] >= throot th[1:] >= th[:-1] + 0.5·deta[:]·b/2·(M[1:] + M[:-1])/CFRPUD.E/I[:] w[0] >= wroot w[1:] >= w[:-1] + 0.5·deta[:]·b/2·(th[1:] + th[:-1]) M[:-1]/Sy[:] <= CFRPUD.sigma Mission1.AircraftLoading.SparLoading.kappa >= w[11]/(b/2) FuselageLoading FuselageSkinL M_h >= Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.N_{max}·W_{cent}/4·l_{body} Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.\sigma_{Kevlar} >= M_h·R/Mission1.Aircraft.Fuselage.FuselageSkin.I Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.q >= W_{cent}·Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.N_{max}/l_{body} \kappa·l_{body}/2 >= Mission1.AircraftLoading.FuselageLoading.FuselageSkinL.q·(l_{body}/2)⁴/(8·Mission1.Aircraft.Fuselage.FuselageSkin.E·Mission1.Aircraft.Fuselage.FuselageSkin.I) FuselageLanding Mission1.AircraftLoading.FuselageLoading.FuselageLanding.F >= W_{cent}·Mission1.AircraftLoading.FuselageLoading.FuselageLanding.N_{max} a >= Mission1.AircraftLoading.FuselageLoading.FuselageLanding.F/m \dot{\omega} >= a/(l_{body}/2) M_G >= I_G·\dot{\omega} Mission1.AircraftLoading.FuselageLoading.FuselageLanding.\sigma_{Kevlar} >= M_G·R/Mission1.Aircraft.Fuselage.FuselageSkin.I TailBoomFlexibility Fne >= 1 + mh·Mission1.AircraftLoading.TailBoomBending.th sph1·mw·Fne/mh/Vh + deda <= 1 sph2 <= Vh·CLhmin/Mission1.Aircraft.Wing.Planform.CLmax deda >= mw·Mission1.Aircraft.Wing.Planform.S/b/4/π/lh sph1 + sph2 >= SMcorr + CM/Mission1.Aircraft.Wing.Planform.CLmax.
Standard Output
Standard Error
<string>:6: UnitStrippedWarning: The unit of the quantity is stripped when downcasting to ndarray. /Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/venv2_gpkit/lib/python3.7/site-packages/gpfit/fit_constraintset.py:46: VisibleDeprecationWarning: Creating an ndarray from ragged nested sequences (which is a list-or-tuple of lists-or-tuples-or ndarrays with different lengths or shapes) is deprecated. If you meant to do this, you must specify 'dtype=object' when creating the ndarray for k in range(fitdata["K"])] /Users/jenkins/workspace/CE_gpkit_PR_research_models/buildnode/macys_VM/optimizer/mosek/venv2_gpkit/lib/python3.7/site-packages/numpy/core/_asarray.py:83: VisibleDeprecationWarning: Creating an ndarray from ragged nested sequences (which is a list-or-tuple of lists-or-tuples-or ndarrays with different lengths or shapes) is deprecated. If you meant to do this, you must specify 'dtype=object' when creating the ndarray return array(a, dtype, copy=False, order=order)