def box_spar():
" test wing models "
Wing.sparModel = BoxSpar
W = Wing()
W.substitutions[W.W] = 50
fs = FlightState()
perf = W.flight_model(W, fs)
loading = [W.spar.loading(W)]
loading[0].substitutions["W"] = 100
loading.append(W.spar.gustloading(W))
loading[1].substitutions["W"] = 100
from gpkit import settings
if settings["default_solver"] == "cvxopt":
for l in loading:
for v in ["\\bar{M}_{tip}", "\\bar{S}_{tip}",
"\\bar{\\delta}_{root}", "\\theta_{root}"]:
l.substitutions[v] = 1e-3
m = Model(perf.Cd, [
loading[1].v == fs.V,
loading[1].cl == perf.CL,
loading[1].Ww == W.W,
loading[1].Ww <= 0.5*fs.rho*fs.V**2*perf.CL*W.planform.S,
W, fs, perf, loading])
m.solve(verbosity=0)
def box_spar():
" test wing models "
Wing.sparModel = BoxSpar
W = Wing()
W.substitutions[W.W] = 50
W.substitutions[W.planform.tau] = 0.115
fs = FlightState()
perf = W.flight_model(W, fs)
loading = [W.spar.loading(W, fs)]
loading[0].substitutions["W"] = 100
loading.append(W.spar.gustloading(W, fs))
loading[1].substitutions["W"] = 100
from gpkit import settings
if settings["default_solver"] == "cvxopt":
for l in loading:
for v in ["Mtip", "Stip", "wroot", "throot"]:
l.substitutions[v] = 1e-2
m = Model(perf.Cd, [
loading[1].v == fs.V, loading[1].cl == perf.CL, loading[1].Ww == W.W,
loading[1].Ww <= fs.qne * perf.CL * W.planform.S, W, fs, perf, loading
])
m.solve(verbosity=0)
def setup(self, N=5):
exec parse_variables(Wing.__doc__)
self.wing = WingGP.setup(self, N=N)
with SignomialsEnabled():
constraints = [mw * (1 + 2 / self.planform["AR"]) >= 2 * np.pi]
return self.wing, constraints
def setup(self, N=5):
self.wing = WingGP.setup(self, N=N)
mw = Variable("m_w", "-", "span wise effectiveness")
with SignomialsEnabled():
constraints = [mw * (1 + 2 / self.planform["AR"]) >= 2 * np.pi]
return self.wing, constraints
def setup(self, N=3):
exec parse_variables(VerticalTail.__doc__)
self.ascs = Wing.setup(self, N)
self.planform.substitutions.update(
{self.planform.tau: 0.08, self.planform.lam: 0.8,
self.planform.AR: 4})
if self.fillModel:
self.foam.substitutions.update({self.foam.Abar: 0.0548,
self.foam.material.rho: 0.024})
return self.ascs
def setup(self, N=3):
exec parse_variables(HorizontalTail.__doc__)
self.ascs = Wing.setup(self, N)
self.planform.substitutions.update({
self.planform.AR: 4,
self.planform.lam: 0.8
})
if self.fillModel:
self.foam.substitutions.update({
self.foam.Abar: 0.0548,
self.foam.material.rho: 0.024
})
return self.ascs, mh * (1 + 2.0 / self.planform["AR"]) <= 2 * np.pi
def setup(self):
Wing.fillModel = None
self.wing = Wing()
W = Variable("W", "lbf", "aircraft weight")
WS = Variable("W/S", "lbf/ft^2", "Aircraft wing loading")
PW = Variable("P/W", "hp/lbf", "Aircraft shaft hp/weight ratio")
Wpay = Variable("W_{pay}", 2 * 195, "lbf", "payload weight")
hbatt = Variable("h_{batt}", 210, "W*hr/kg", "battery specific energy")
etae = Variable("\\eta_{e}", 0.9, "-", "total electrical efficiency")
Wbatt = Variable("W_{batt}", "lbf", "battery weight")
Wwing = Variable("W_{wing}", "lbf", "wing weight")
Pshaftmax = Variable("P_{shaft-max}", "W", "max shaft power")
sp_motor = Variable("sp_{motor}", 7. / 9.81, "kW/N",
'Motor specific power')
Wmotor = Variable("W_{motor}", "lbf", "motor weight")
Wcent = Variable("W_{cent}", "lbf", "aircraft center weight")
fstruct = Variable("f_{struct}", 0.2, "-",
"structural weight fraction")
Wstruct = Variable("W_{struct}", "lbf", "structural weight")
e = Variable("e", 0.8, "-", "span efficiency factor")
CL_max_clean = Variable("CL_{max_{clean}}", 1.6, "-", "Clean CL max")
CL_max_to = Variable("CL_{max_{to}}", 2.0, "-", "Clean CL max")
CL_max_aprch = Variable("CL_{max_{aprch}}", 2.4, "-", "Clean CL max")
fbattmax = Variable("f_{batt,max}", 1.0, "-", "max battery fraction")
loading = self.wing.spar.loading(self.wing)
loading.substitutions.update({
loading.kappa: 0.05,
self.wing.spar.material.sigma: 1.5e9,
loading.Nmax: 6,
self.wing.skin.material.tmin: 0.012 * 4,
self.wing.mfac: 1.4,
self.wing.spar.mfac: 0.8
})
constraints = [
Wcent == loading.W,
WS == W / self.wing.planform.S,
PW == Pshaftmax / W,
TCS([W >= Wbatt + Wpay + self.wing.W + Wmotor + Wstruct]),
Wcent >= Wbatt + Wpay + Wmotor + Wstruct,
Wstruct >= fstruct * W,
Wmotor >= Pshaftmax / sp_motor,
Wbatt / W <= fbattmax,
]
return constraints, self.wing, loading