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gpkit.tests.from_paths.TestFiles.test_model_jho_py_mosek_cli (from gpkit.tests.from_paths.TestFiles-20200714225616)

Failing for the past 1 build (Since Failed #446 )
Took 1.2 sec.

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     Mission.Aircraft.Fuselage.FuelTank.W >= f·W_{fuel-tot}     \mathcal{V}/Mission.Aircraft.Fuselage.FuelTank.m_{fac} >= W_{fuel-tot}/\rho_{fuel}     FuselageSkin     m >= S_{wet}·\rho_{kevlar}·Mission.Aircraft.Fuselage.FuselageSkin.t     Mission.Aircraft.Fuselage.FuselageSkin.W >= m·Mission.Aircraft.Fuselage.FuselageSkin.g     Mission.Aircraft.Fuselage.FuselageSkin.t >= t_{min}     Mission.Aircraft.Fuselage.FuselageSkin.I <= π·R³·Mission.Aircraft.Fuselage.FuselageSkin.t     I_G >= m·(4·R² + 4·R·Mission.Aircraft.Fuselage.FuselageSkin.t + Mission.Aircraft.Fuselage.FuselageSkin.t²)     l_{body} = l_{body}     Mission.Aircraft.Fuselage.FuselageSkin.E = Mission.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}    Mission.Aircraft.Fuselage.l <= 3·R·(k_{body}·k_{nose}·k_{bulk})^0.3333333333333333    Mission.Aircraft.Fuselage.S >= π·R²    \mathcal{V}_{body} >= \mathcal{V}    Mission.Aircraft.Fuselage.W/Mission.Aircraft.Fuselage.m_{fac} >= Mission.Aircraft.Fuselage.FuelTank.W + Mission.Aircraft.Fuselage.FuselageSkin.W    Wing    Mission.Aircraft.Wing.W/Mission.Aircraft.Wing.mfac >= Mission.Aircraft.Wing.WingSkin.W + Mission.Aircraft.Wing.CapSpar.W + Mission.Aircraft.Wing.WingCore.W     Planform     Mission.Aircraft.Wing.Planform.b² = Mission.Aircraft.Wing.Planform.S·Mission.Aircraft.Wing.Planform.AR     cave[:] = cbave[:]·Mission.Aircraft.Wing.Planform.S/Mission.Aircraft.Wing.Planform.b     Mission.Aircraft.Wing.Planform.croot = Mission.Aircraft.Wing.Planform.S/Mission.Aircraft.Wing.Planform.b·cbar[0]     Mission.Aircraft.Wing.Planform.cmac = Mission.Aircraft.Wing.Planform.croot·Mission.Aircraft.Wing.Planform.cbarmac    WingSkin     Mission.Aircraft.Wing.WingSkin.W >= CFRPFabric.rho·Mission.Aircraft.Wing.Planform.S·2·Mission.Aircraft.Wing.WingSkin.t·g     Mission.Aircraft.Wing.WingSkin.t >= tmin     CFRPFabric.tau >= 1/Mission.Aircraft.Wing.WingSkin.Jtbar/Mission.Aircraft.Wing.Planform.croot²/Mission.Aircraft.Wing.WingSkin.t·Mission.Aircraft.Wing.WingSkin.Cmw·Mission.Aircraft.Wing.Planform.S·Mission.Aircraft.Wing.WingSkin.rhosl·Mission.Aircraft.Wing.WingSkin.Vne²     CapSpar     I[:]/Mission.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[:])·Mission.Aircraft.Wing.Planform.b/2·deta[:]     Mission.Aircraft.Wing.CapSpar.W >= 2·dm[:].sum()·g     w[:] <= wlim·cave[:]     cave[:]·Mission.Aircraft.Wing.Planform.tau >= hin[:] + 2·t[:]     Sy[:]·(hin[:]/2 + t[:]) <= I[:]     tshear[:] >= tmin     WingCore     Mission.Aircraft.Wing.WingCore.W >= 2·(g·FoamHD.rho·Mission.Aircraft.Wing.WingCore.Abar·cave[:]²·Mission.Aircraft.Wing.Planform.b/2·deta[:]).sum()    mw·(1 + 2/Mission.Aircraft.Wing.Planform.AR) >= 6.28    DF70    W_{DF70} <= Mission.Aircraft.DF70.W/Mission.Aircraft.DF70.m_{fac}    P_{sl-max} = P_{sl-max}    Empennage    HorizontalTail     Mission.Aircraft.Empennage.HorizontalTail.W/Mission.Aircraft.Empennage.HorizontalTail.mfac >= Mission.Aircraft.Empennage.HorizontalTail.WingSkin.W + Mission.Aircraft.Empennage.HorizontalTail.WingCore.W      Planform      Mission.Aircraft.Empennage.HorizontalTail.Planform.b² = Mission.Aircraft.Empennage.HorizontalTail.Planform.S·Mission.Aircraft.Empennage.HorizontalTail.Planform.AR      cave[:] = cbave[:]·Mission.Aircraft.Empennage.HorizontalTail.Planform.S/Mission.Aircraft.Empennage.HorizontalTail.Planform.b      Mission.Aircraft.Empennage.HorizontalTail.Planform.croot = Mission.Aircraft.Empennage.HorizontalTail.Planform.S/Mission.Aircraft.Empennage.HorizontalTail.Planform.b·cbar[0]      Mission.Aircraft.Empennage.HorizontalTail.Planform.cmac = Mission.Aircraft.Empennage.HorizontalTail.Planform.croot·Mission.Aircraft.Empennage.HorizontalTail.Planform.cbarmac     WingSkin      Mission.Aircraft.Empennage.HorizontalTail.WingSkin.W >= CFRPFabric.rho·Mission.Aircraft.Empennage.HorizontalTail.Planform.S·2·Mission.Aircraft.Empennage.HorizontalTail.WingSkin.t·g      Mission.Aircraft.Empennage.HorizontalTail.WingSkin.t >= tmin      CFRPFabric.tau >= 1/Mission.Aircraft.Empennage.HorizontalTail.WingSkin.Jtbar/Mission.Aircraft.Empennage.HorizontalTail.Planform.croot²/Mission.Aircraft.Empennage.HorizontalTail.WingSkin.t·Mission.Aircraft.Empennage.HorizontalTail.WingSkin.Cmw·Mission.Aircraft.Empennage.HorizontalTail.Planform.S·Mission.Aircraft.Empennage.HorizontalTail.WingSkin.rhosl·Mission.Aircraft.Empennage.HorizontalTail.WingSkin.Vne²      WingCore      Mission.Aircraft.Empennage.HorizontalTail.WingCore.W >= 2·(g·FoamHD.rho·Mission.Aircraft.Empennage.HorizontalTail.WingCore.Abar·cave[:]²·Mission.Aircraft.Empennage.HorizontalTail.Planform.b/2·deta[:]).sum()     mh·(1 + 2/Mission.Aircraft.Empennage.HorizontalTail.Planform.AR) <= 6.28     VerticalTail     Mission.Aircraft.Empennage.VerticalTail.W/Mission.Aircraft.Empennage.VerticalTail.mfac >= Mission.Aircraft.Empennage.VerticalTail.WingSkin.W + Mission.Aircraft.Empennage.VerticalTail.WingCore.W      Planform      Mission.Aircraft.Empennage.VerticalTail.Planform.b² = Mission.Aircraft.Empennage.VerticalTail.Planform.S·Mission.Aircraft.Empennage.VerticalTail.Planform.AR      cave[:] = cbave[:]·Mission.Aircraft.Empennage.VerticalTail.Planform.S/Mission.Aircraft.Empennage.VerticalTail.Planform.b      Mission.Aircraft.Empennage.VerticalTail.Planform.croot = Mission.Aircraft.Empennage.VerticalTail.Planform.S/Mission.Aircraft.Empennage.VerticalTail.Planform.b·cbar[0]      Mission.Aircraft.Empennage.VerticalTail.Planform.cmac = Mission.Aircraft.Empennage.VerticalTail.Planform.croot·Mission.Aircraft.Empennage.VerticalTail.Planform.cbarmac     WingSkin      Mission.Aircraft.Empennage.VerticalTail.WingSkin.W >= CFRPFabric.rho·Mission.Aircraft.Empennage.VerticalTail.Planform.S·2·Mission.Aircraft.Empennage.VerticalTail.WingSkin.t·g      Mission.Aircraft.Empennage.VerticalTail.WingSkin.t >= tmin      CFRPFabric.tau >= 1/Mission.Aircraft.Empennage.VerticalTail.WingSkin.Jtbar/Mission.Aircraft.Empennage.VerticalTail.Planform.croot²/Mission.Aircraft.Empennage.VerticalTail.WingSkin.t·Mission.Aircraft.Empennage.VerticalTail.WingSkin.Cmw·Mission.Aircraft.Empennage.VerticalTail.Planform.S·Mission.Aircraft.Empennage.VerticalTail.WingSkin.rhosl·Mission.Aircraft.Empennage.VerticalTail.WingSkin.Vne²      WingCore      Mission.Aircraft.Empennage.VerticalTail.WingCore.W >= 2·(g·FoamHD.rho·Mission.Aircraft.Empennage.VerticalTail.WingCore.Abar·cave[:]²·Mission.Aircraft.Empennage.VerticalTail.Planform.b/2·deta[:]).sum()     TailBoom     I[:] <= π·t[:]·d[:]³/8     Sy[:] <= 2·I[:]/d[:]     dm[:] >= π·CFRPFabric.rho·d[:]·Mission.Aircraft.Empennage.TailBoom.deta·t[:]·kfac·Mission.Aircraft.Empennage.TailBoom.l     Mission.Aircraft.Empennage.TailBoom.W/Mission.Aircraft.Empennage.TailBoom.mfac >= g·dm[:].sum()     t[:] >= tmin     Mission.Aircraft.Empennage.TailBoom.S = Mission.Aircraft.Empennage.TailBoom.l·π·d[0]     Mission.Aircraft.Empennage.TailBoom.b = 2·Mission.Aircraft.Empennage.TailBoom.l    Mission.Aircraft.Empennage.W/Mission.Aircraft.Empennage.mfac >= Mission.Aircraft.Empennage.HorizontalTail.W + Mission.Aircraft.Empennage.VerticalTail.W + Mission.Aircraft.Empennage.TailBoom.W    Mission.Aircraft.Empennage.TailBoom.l >= lh    Mission.Aircraft.Empennage.TailBoom.l >= lv    Pylon    Mission.Aircraft.Pylon.S >= 2·Mission.Aircraft.Pylon.l·Mission.Aircraft.Pylon.h   W_{zfw} >= Mission.Aircraft.Fuselage.W + Mission.Aircraft.Wing.W + Mission.Aircraft.DF70.W + Mission.Aircraft.Empennage.W + Mission.Aircraft.Pylon.W + W_{pay} + W_{avn}   Vh <= Mission.Aircraft.Empennage.HorizontalTail.Planform.S·lh/Mission.Aircraft.Wing.Planform.S²·Mission.Aircraft.Wing.Planform.b   Vv = Mission.Aircraft.Empennage.VerticalTail.Planform.S·lv/Mission.Aircraft.Wing.Planform.S/Mission.Aircraft.Wing.Planform.b   Mission.Aircraft.Wing.Planform.CLmax/mw <= Mission.Aircraft.Empennage.HorizontalTail.Planform.CLmax/mh   w_{antenna} <= Mission.Aircraft.Empennage.VerticalTail.Planform.croot·Mission.Aircraft.Empennage.VerticalTail.Planform.lam   Mission.Aircraft.Empennage.VerticalTail.Planform.b >= l_{antenna}   Mission.Aircraft.Empennage.TailBoom.l >= lh + Mission.Aircraft.Empennage.HorizontalTail.Planform.croot   \mathcal{V}_{pay} <= (π/1.5)·k_{nose}·R³   \mathcal{V}_{body} >= \mathcal{V} + \mathcal{V}_{avn}   Mission.Aircraft.DF70.h <= 2·R and AircraftLoading ===============  Cost ----  1  Constraints -----------   TailBoomBending    dx[:] = Mission.Aircraft.Empennage.TailBoom.deta    qne[:]·Mission.Aircraft.Empennage.HorizontalTail.Planform.S <= Mission.AircraftLoading.TailBoomBending.F    \bar{EI}[:] <= CFRPFabric.E·I[:]/Mission.AircraftLoading.TailBoomBending.F/l²/2    Mr[:] >= \bar{M}[:-1]·Mission.AircraftLoading.TailBoomBending.F·l    Mr[:]/Sy[:] <= CFRPFabric.sigma    Mission.AircraftLoading.TailBoomBending.th = \theta[1]    Mission.AircraftLoading.TailBoomBending.kappa >= \bar{\delta}[1]·Mission.Aircraft.Empennage.HorizontalTail.Planform.CLmax·Mission.AircraftLoading.TailBoomBending.Nsafety     Beam     \bar{M}[:-1] >= \bar{M}[1:] + 0.5·dx[:]·(\bar{S}[:-1] + \bar{S}[1:])     \bar{M}[1] >= Mission.AircraftLoading.TailBoomBending.Beam.\bar{M}_{tip}     \theta[0] >= Mission.AircraftLoading.TailBoomBending.Beam.\theta_{root}     \theta[1:] >= \theta[:-1] + 0.5·dx[:]·(\bar{M}[1:] + \bar{M}[:-1])/\bar{EI}[:]     \bar{\delta}[0] >= Mission.AircraftLoading.TailBoomBending.Beam.\bar{\delta}_{root}     \bar{\delta}[1:] >= \bar{\delta}[:-1] + 0.5·dx[:]·(\theta[1:] + \theta[:-1])    TailBoomBending1    dx[:] = Mission.Aircraft.Empennage.TailBoom.deta    qne[:]·Mission.Aircraft.Empennage.VerticalTail.Planform.S <= Mission.AircraftLoading.TailBoomBending1.F    \bar{EI}[:] <= CFRPFabric.E·I[:]/Mission.AircraftLoading.TailBoomBending1.F/l²/2    Mr[:] >= \bar{M}[:-1]·Mission.AircraftLoading.TailBoomBending1.F·l    Mr[:]/Sy[:] <= CFRPFabric.sigma    Mission.AircraftLoading.TailBoomBending1.th = \theta[1]    Mission.AircraftLoading.TailBoomBending1.kappa >= \bar{\delta}[1]·Mission.Aircraft.Empennage.VerticalTail.Planform.CLmax·Mission.AircraftLoading.TailBoomBending1.Nsafety     Beam     \bar{M}[:-1] >= \bar{M}[1:] + 0.5·dx[:]·(\bar{S}[:-1] + \bar{S}[1:])     \bar{M}[1] >= Mission.AircraftLoading.TailBoomBending1.Beam.\bar{M}_{tip}     \theta[0] >= Mission.AircraftLoading.TailBoomBending1.Beam.\theta_{root}     \theta[1:] >= \theta[:-1] + 0.5·dx[:]·(\bar{M}[1:] + \bar{M}[:-1])/\bar{EI}[:]     \bar{\delta}[0] >= Mission.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 = Mission.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    Mission.AircraftLoading.SparLoading.kappa >= w[11]/(b/2)    FuselageLoading    FuselageSkinL     M_h >= Mission.AircraftLoading.FuselageLoading.FuselageSkinL.N_{max}·W_{cent}/4·l_{body}     Mission.AircraftLoading.FuselageLoading.FuselageSkinL.\sigma_{Kevlar} >= M_h·R/Mission.Aircraft.Fuselage.FuselageSkin.I     Mission.AircraftLoading.FuselageLoading.FuselageSkinL.q >= W_{cent}·Mission.AircraftLoading.FuselageLoading.FuselageSkinL.N_{max}/l_{body}     \kappa·l_{body}/2 >= Mission.AircraftLoading.FuselageLoading.FuselageSkinL.q·(l_{body}/2)⁴/(8·Mission.Aircraft.Fuselage.FuselageSkin.E·Mission.Aircraft.Fuselage.FuselageSkin.I)     FuselageLanding     Mission.AircraftLoading.FuselageLoading.FuselageLanding.F >= W_{cent}·Mission.AircraftLoading.FuselageLoading.FuselageLanding.N_{max}     a >= Mission.AircraftLoading.FuselageLoading.FuselageLanding.F/m     \dot{\omega} >= a/(l_{body}/2)     M_G >= I_G·\dot{\omega}     Mission.AircraftLoading.FuselageLoading.FuselageLanding.\sigma_{Kevlar} >= M_G·R/Mission.Aircraft.Fuselage.FuselageSkin.I    TailBoomFlexibility    Fne >= 1 + mh·Mission.AircraftLoading.TailBoomBending.th    sph1·mw·Fne/mh/Vh + deda <= 1    sph2 <= Vh·CLhmin/Mission.Aircraft.Wing.Planform.CLmax    deda >= mw·Mission.Aircraft.Wing.Planform.S/b/4/π/lh    sph1 + sph2 >= SMcorr + CM/Mission.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
    Mission.Aircraft.Fuselage.FuelTank.W >= f·W_{fuel-tot}
    \mathcal{V}/Mission.Aircraft.Fuselage.FuelTank.m_{fac} >= W_{fuel-tot}/\rho_{fuel}

   FuselageSkin
    m >= S_{wet}·\rho_{kevlar}·Mission.Aircraft.Fuselage.FuselageSkin.t
    Mission.Aircraft.Fuselage.FuselageSkin.W >= m·Mission.Aircraft.Fuselage.FuselageSkin.g
    Mission.Aircraft.Fuselage.FuselageSkin.t >= t_{min}
    Mission.Aircraft.Fuselage.FuselageSkin.I <= π·R³·Mission.Aircraft.Fuselage.FuselageSkin.t
    I_G >= m·(4·R² + 4·R·Mission.Aircraft.Fuselage.FuselageSkin.t + Mission.Aircraft.Fuselage.FuselageSkin.t²)
    l_{body} = l_{body}
    Mission.Aircraft.Fuselage.FuselageSkin.E = Mission.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}
   Mission.Aircraft.Fuselage.l <= 3·R·(k_{body}·k_{nose}·k_{bulk})^0.3333333333333333
   Mission.Aircraft.Fuselage.S >= π·R²
   \mathcal{V}_{body} >= \mathcal{V}
   Mission.Aircraft.Fuselage.W/Mission.Aircraft.Fuselage.m_{fac} >= Mission.Aircraft.Fuselage.FuelTank.W + Mission.Aircraft.Fuselage.FuselageSkin.W

  Wing
   Mission.Aircraft.Wing.W/Mission.Aircraft.Wing.mfac >= Mission.Aircraft.Wing.WingSkin.W + Mission.Aircraft.Wing.CapSpar.W + Mission.Aircraft.Wing.WingCore.W

   Planform
    Mission.Aircraft.Wing.Planform.b² = Mission.Aircraft.Wing.Planform.S·Mission.Aircraft.Wing.Planform.AR
    cave[:] = cbave[:]·Mission.Aircraft.Wing.Planform.S/Mission.Aircraft.Wing.Planform.b
    Mission.Aircraft.Wing.Planform.croot = Mission.Aircraft.Wing.Planform.S/Mission.Aircraft.Wing.Planform.b·cbar[0]
    Mission.Aircraft.Wing.Planform.cmac = Mission.Aircraft.Wing.Planform.croot·Mission.Aircraft.Wing.Planform.cbarmac
   WingSkin
    Mission.Aircraft.Wing.WingSkin.W >= CFRPFabric.rho·Mission.Aircraft.Wing.Planform.S·2·Mission.Aircraft.Wing.WingSkin.t·g
    Mission.Aircraft.Wing.WingSkin.t >= tmin
    CFRPFabric.tau >= 1/Mission.Aircraft.Wing.WingSkin.Jtbar/Mission.Aircraft.Wing.Planform.croot²/Mission.Aircraft.Wing.WingSkin.t·Mission.Aircraft.Wing.WingSkin.Cmw·Mission.Aircraft.Wing.Planform.S·Mission.Aircraft.Wing.WingSkin.rhosl·Mission.Aircraft.Wing.WingSkin.Vne²

   CapSpar
    I[:]/Mission.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[:])·Mission.Aircraft.Wing.Planform.b/2·deta[:]
    Mission.Aircraft.Wing.CapSpar.W >= 2·dm[:].sum()·g
    w[:] <= wlim·cave[:]
    cave[:]·Mission.Aircraft.Wing.Planform.tau >= hin[:] + 2·t[:]
    Sy[:]·(hin[:]/2 + t[:]) <= I[:]
    tshear[:] >= tmin

   WingCore
    Mission.Aircraft.Wing.WingCore.W >= 2·(g·FoamHD.rho·Mission.Aircraft.Wing.WingCore.Abar·cave[:]²·Mission.Aircraft.Wing.Planform.b/2·deta[:]).sum()
   mw·(1 + 2/Mission.Aircraft.Wing.Planform.AR) >= 6.28

  DF70
   W_{DF70} <= Mission.Aircraft.DF70.W/Mission.Aircraft.DF70.m_{fac}
   P_{sl-max} = P_{sl-max}

  Empennage
   HorizontalTail
    Mission.Aircraft.Empennage.HorizontalTail.W/Mission.Aircraft.Empennage.HorizontalTail.mfac >= Mission.Aircraft.Empennage.HorizontalTail.WingSkin.W + Mission.Aircraft.Empennage.HorizontalTail.WingCore.W

    Planform
     Mission.Aircraft.Empennage.HorizontalTail.Planform.b² = Mission.Aircraft.Empennage.HorizontalTail.Planform.S·Mission.Aircraft.Empennage.HorizontalTail.Planform.AR
     cave[:] = cbave[:]·Mission.Aircraft.Empennage.HorizontalTail.Planform.S/Mission.Aircraft.Empennage.HorizontalTail.Planform.b
     Mission.Aircraft.Empennage.HorizontalTail.Planform.croot = Mission.Aircraft.Empennage.HorizontalTail.Planform.S/Mission.Aircraft.Empennage.HorizontalTail.Planform.b·cbar[0]
     Mission.Aircraft.Empennage.HorizontalTail.Planform.cmac = Mission.Aircraft.Empennage.HorizontalTail.Planform.croot·Mission.Aircraft.Empennage.HorizontalTail.Planform.cbarmac
    WingSkin
     Mission.Aircraft.Empennage.HorizontalTail.WingSkin.W >= CFRPFabric.rho·Mission.Aircraft.Empennage.HorizontalTail.Planform.S·2·Mission.Aircraft.Empennage.HorizontalTail.WingSkin.t·g
     Mission.Aircraft.Empennage.HorizontalTail.WingSkin.t >= tmin
     CFRPFabric.tau >= 1/Mission.Aircraft.Empennage.HorizontalTail.WingSkin.Jtbar/Mission.Aircraft.Empennage.HorizontalTail.Planform.croot²/Mission.Aircraft.Empennage.HorizontalTail.WingSkin.t·Mission.Aircraft.Empennage.HorizontalTail.WingSkin.Cmw·Mission.Aircraft.Empennage.HorizontalTail.Planform.S·Mission.Aircraft.Empennage.HorizontalTail.WingSkin.rhosl·Mission.Aircraft.Empennage.HorizontalTail.WingSkin.Vne²

    WingCore
     Mission.Aircraft.Empennage.HorizontalTail.WingCore.W >= 2·(g·FoamHD.rho·Mission.Aircraft.Empennage.HorizontalTail.WingCore.Abar·cave[:]²·Mission.Aircraft.Empennage.HorizontalTail.Planform.b/2·deta[:]).sum()
    mh·(1 + 2/Mission.Aircraft.Empennage.HorizontalTail.Planform.AR) <= 6.28

   VerticalTail
    Mission.Aircraft.Empennage.VerticalTail.W/Mission.Aircraft.Empennage.VerticalTail.mfac >= Mission.Aircraft.Empennage.VerticalTail.WingSkin.W + Mission.Aircraft.Empennage.VerticalTail.WingCore.W

    Planform
     Mission.Aircraft.Empennage.VerticalTail.Planform.b² = Mission.Aircraft.Empennage.VerticalTail.Planform.S·Mission.Aircraft.Empennage.VerticalTail.Planform.AR
     cave[:] = cbave[:]·Mission.Aircraft.Empennage.VerticalTail.Planform.S/Mission.Aircraft.Empennage.VerticalTail.Planform.b
     Mission.Aircraft.Empennage.VerticalTail.Planform.croot = Mission.Aircraft.Empennage.VerticalTail.Planform.S/Mission.Aircraft.Empennage.VerticalTail.Planform.b·cbar[0]
     Mission.Aircraft.Empennage.VerticalTail.Planform.cmac = Mission.Aircraft.Empennage.VerticalTail.Planform.croot·Mission.Aircraft.Empennage.VerticalTail.Planform.cbarmac
    WingSkin
     Mission.Aircraft.Empennage.VerticalTail.WingSkin.W >= CFRPFabric.rho·Mission.Aircraft.Empennage.VerticalTail.Planform.S·2·Mission.Aircraft.Empennage.VerticalTail.WingSkin.t·g
     Mission.Aircraft.Empennage.VerticalTail.WingSkin.t >= tmin
     CFRPFabric.tau >= 1/Mission.Aircraft.Empennage.VerticalTail.WingSkin.Jtbar/Mission.Aircraft.Empennage.VerticalTail.Planform.croot²/Mission.Aircraft.Empennage.VerticalTail.WingSkin.t·Mission.Aircraft.Empennage.VerticalTail.WingSkin.Cmw·Mission.Aircraft.Empennage.VerticalTail.Planform.S·Mission.Aircraft.Empennage.VerticalTail.WingSkin.rhosl·Mission.Aircraft.Empennage.VerticalTail.WingSkin.Vne²

    WingCore
     Mission.Aircraft.Empennage.VerticalTail.WingCore.W >= 2·(g·FoamHD.rho·Mission.Aircraft.Empennage.VerticalTail.WingCore.Abar·cave[:]²·Mission.Aircraft.Empennage.VerticalTail.Planform.b/2·deta[:]).sum()

   TailBoom
    I[:] <= π·t[:]·d[:]³/8
    Sy[:] <= 2·I[:]/d[:]
    dm[:] >= π·CFRPFabric.rho·d[:]·Mission.Aircraft.Empennage.TailBoom.deta·t[:]·kfac·Mission.Aircraft.Empennage.TailBoom.l
    Mission.Aircraft.Empennage.TailBoom.W/Mission.Aircraft.Empennage.TailBoom.mfac >= g·dm[:].sum()
    t[:] >= tmin
    Mission.Aircraft.Empennage.TailBoom.S = Mission.Aircraft.Empennage.TailBoom.l·π·d[0]
    Mission.Aircraft.Empennage.TailBoom.b = 2·Mission.Aircraft.Empennage.TailBoom.l
   Mission.Aircraft.Empennage.W/Mission.Aircraft.Empennage.mfac >= Mission.Aircraft.Empennage.HorizontalTail.W + Mission.Aircraft.Empennage.VerticalTail.W + Mission.Aircraft.Empennage.TailBoom.W
   Mission.Aircraft.Empennage.TailBoom.l >= lh
   Mission.Aircraft.Empennage.TailBoom.l >= lv

  Pylon
   Mission.Aircraft.Pylon.S >= 2·Mission.Aircraft.Pylon.l·Mission.Aircraft.Pylon.h
  W_{zfw} >= Mission.Aircraft.Fuselage.W + Mission.Aircraft.Wing.W + Mission.Aircraft.DF70.W + Mission.Aircraft.Empennage.W + Mission.Aircraft.Pylon.W + W_{pay} + W_{avn}
  Vh <= Mission.Aircraft.Empennage.HorizontalTail.Planform.S·lh/Mission.Aircraft.Wing.Planform.S²·Mission.Aircraft.Wing.Planform.b
  Vv = Mission.Aircraft.Empennage.VerticalTail.Planform.S·lv/Mission.Aircraft.Wing.Planform.S/Mission.Aircraft.Wing.Planform.b
  Mission.Aircraft.Wing.Planform.CLmax/mw <= Mission.Aircraft.Empennage.HorizontalTail.Planform.CLmax/mh
  w_{antenna} <= Mission.Aircraft.Empennage.VerticalTail.Planform.croot·Mission.Aircraft.Empennage.VerticalTail.Planform.lam
  Mission.Aircraft.Empennage.VerticalTail.Planform.b >= l_{antenna}
  Mission.Aircraft.Empennage.TailBoom.l >= lh + Mission.Aircraft.Empennage.HorizontalTail.Planform.croot
  \mathcal{V}_{pay} <= (π/1.5)·k_{nose}·R³
  \mathcal{V}_{body} >= \mathcal{V} + \mathcal{V}_{avn}
  Mission.Aircraft.DF70.h <= 2·R and AircraftLoading
===============

Cost
----
 1

Constraints
-----------
  TailBoomBending
   dx[:] = Mission.Aircraft.Empennage.TailBoom.deta
   qne[:]·Mission.Aircraft.Empennage.HorizontalTail.Planform.S <= Mission.AircraftLoading.TailBoomBending.F
   \bar{EI}[:] <= CFRPFabric.E·I[:]/Mission.AircraftLoading.TailBoomBending.F/l²/2
   Mr[:] >= \bar{M}[:-1]·Mission.AircraftLoading.TailBoomBending.F·l
   Mr[:]/Sy[:] <= CFRPFabric.sigma
   Mission.AircraftLoading.TailBoomBending.th = \theta[1]
   Mission.AircraftLoading.TailBoomBending.kappa >= \bar{\delta}[1]·Mission.Aircraft.Empennage.HorizontalTail.Planform.CLmax·Mission.AircraftLoading.TailBoomBending.Nsafety

   Beam
    \bar{M}[:-1] >= \bar{M}[1:] + 0.5·dx[:]·(\bar{S}[:-1] + \bar{S}[1:])
    \bar{M}[1] >= Mission.AircraftLoading.TailBoomBending.Beam.\bar{M}_{tip}
    \theta[0] >= Mission.AircraftLoading.TailBoomBending.Beam.\theta_{root}
    \theta[1:] >= \theta[:-1] + 0.5·dx[:]·(\bar{M}[1:] + \bar{M}[:-1])/\bar{EI}[:]
    \bar{\delta}[0] >= Mission.AircraftLoading.TailBoomBending.Beam.\bar{\delta}_{root}
    \bar{\delta}[1:] >= \bar{\delta}[:-1] + 0.5·dx[:]·(\theta[1:] + \theta[:-1])

  TailBoomBending1
   dx[:] = Mission.Aircraft.Empennage.TailBoom.deta
   qne[:]·Mission.Aircraft.Empennage.VerticalTail.Planform.S <= Mission.AircraftLoading.TailBoomBending1.F
   \bar{EI}[:] <= CFRPFabric.E·I[:]/Mission.AircraftLoading.TailBoomBending1.F/l²/2
   Mr[:] >= \bar{M}[:-1]·Mission.AircraftLoading.TailBoomBending1.F·l
   Mr[:]/Sy[:] <= CFRPFabric.sigma
   Mission.AircraftLoading.TailBoomBending1.th = \theta[1]
   Mission.AircraftLoading.TailBoomBending1.kappa >= \bar{\delta}[1]·Mission.Aircraft.Empennage.VerticalTail.Planform.CLmax·Mission.AircraftLoading.TailBoomBending1.Nsafety

   Beam
    \bar{M}[:-1] >= \bar{M}[1:] + 0.5·dx[:]·(\bar{S}[:-1] + \bar{S}[1:])
    \bar{M}[1] >= Mission.AircraftLoading.TailBoomBending1.Beam.\bar{M}_{tip}
    \theta[0] >= Mission.AircraftLoading.TailBoomBending1.Beam.\theta_{root}
    \theta[1:] >= \theta[:-1] + 0.5·dx[:]·(\bar{M}[1:] + \bar{M}[:-1])/\bar{EI}[:]
    \bar{\delta}[0] >= Mission.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 = Mission.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
   Mission.AircraftLoading.SparLoading.kappa >= w[11]/(b/2)

  FuselageLoading
   FuselageSkinL
    M_h >= Mission.AircraftLoading.FuselageLoading.FuselageSkinL.N_{max}·W_{cent}/4·l_{body}
    Mission.AircraftLoading.FuselageLoading.FuselageSkinL.\sigma_{Kevlar} >= M_h·R/Mission.Aircraft.Fuselage.FuselageSkin.I
    Mission.AircraftLoading.FuselageLoading.FuselageSkinL.q >= W_{cent}·Mission.AircraftLoading.FuselageLoading.FuselageSkinL.N_{max}/l_{body}
    \kappa·l_{body}/2 >= Mission.AircraftLoading.FuselageLoading.FuselageSkinL.q·(l_{body}/2)⁴/(8·Mission.Aircraft.Fuselage.FuselageSkin.E·Mission.Aircraft.Fuselage.FuselageSkin.I)

   FuselageLanding
    Mission.AircraftLoading.FuselageLoading.FuselageLanding.F >= W_{cent}·Mission.AircraftLoading.FuselageLoading.FuselageLanding.N_{max}
    a >= Mission.AircraftLoading.FuselageLoading.FuselageLanding.F/m
    \dot{\omega} >= a/(l_{body}/2)
    M_G >= I_G·\dot{\omega}
    Mission.AircraftLoading.FuselageLoading.FuselageLanding.\sigma_{Kevlar} >= M_G·R/Mission.Aircraft.Fuselage.FuselageSkin.I

  TailBoomFlexibility
   Fne >= 1 + mh·Mission.AircraftLoading.TailBoomBending.th
   sph1·mw·Fne/mh/Vh + deda <= 1
   sph2 <= Vh·CLhmin/Mission.Aircraft.Wing.Planform.CLmax
   deda >= mw·Mission.Aircraft.Wing.Planform.S/b/4/π/lh
   sph1 + sph2 >= SMcorr + CM/Mission.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)