def test_emp():
Sw = Variable("S_w", 50, "ft**2", "wing area")
bw = Variable("b_w", 20, "ft", "wing span")
cmac = Variable("cmac", 15, "in", "wing MAC")
emp = Empennage()
fs = FlightState()
emp.substitutions.update({emp.W: 10, emp.tailboom.l: 5,
emp.htail.planform.AR: 4,
emp.vtail.planform.AR: 4,
emp.htail.planform.tau: 0.08,
emp.vtail.planform.tau: 0.08,
emp.vtail.Vv: 0.04,
emp.htail.Vh: 0.4,
emp.htail.mh: 0.01})
htperf = emp.htail.flight_model(emp.htail, fs)
vtperf = emp.vtail.flight_model(emp.vtail, fs)
tbperf = emp.tailboom.flight_model(emp.tailboom, fs)
hbend = emp.tailboom.tailLoad(emp.tailboom, emp.htail, fs)
vbend = emp.tailboom.tailLoad(emp.tailboom, emp.vtail, fs)
m = Model(htperf.Cd + vtperf.Cd + tbperf.Cf,
[emp.vtail.lv == emp.tailboom.l, emp.htail.lh == emp.tailboom.l,
emp.htail.Vh <= emp.htail.planform.S*emp.htail.lh/Sw/cmac,
emp.vtail.Vv <= emp.vtail.planform.S*emp.vtail.lv/Sw/bw,
fs, emp, fs, htperf, vtperf, tbperf, hbend, vbend])
from gpkit import settings
if settings["default_solver"] == "cvxopt":
for l in [hbend, vbend]:
for v in ["\\bar{M}_{tip}", "\\bar{\\delta}_{root}",
"\\theta_{root}"]:
m.substitutions[l[v]] = 1e-3
m.solve(verbosity=0)
def setup(self):
fs = FlightState()
p = Propulsor()
pp = p.flight_model(p,fs)
pp.substitutions[pp.prop.T] = 100
self.cost = 1./pp.motor.etam + p.W/(1000*units('lbf')) + 1./pp.prop.eta
return fs,p,pp
def setup(self):
fs = FlightState()
m = Motor()
mp = MotorPerf(m,fs)
self.mp = mp
mp.substitutions[m.Qmax] = 100
mp.substitutions[mp.Q] = 10
self.cost = 1./mp.etam + m.W/(100.*units('lbf'))
return self.mp, fs, m
def setup(self):
fs = FlightState()
Propulsor.prop_flight_model = BladeElementProp
p = Propulsor()
pp = p.flight_model(p,fs)
pp.substitutions[pp.prop.T] = 100
self.cost = pp.motor.Pelec/(1000*units('W')) + p.W/(1000*units('lbf'))
return fs,p,pp
def test_ellp():
"elliptical fuselage test"
f = Fuselage()
fs = FlightState()
faero = f.flight_model(f, fs)
f.substitutions[f.Vol] = 1.33
m = Model(f.W * faero.Cd, [f, fs, faero])
m.solve()
def setup(self):
fs = FlightState()
m = Motor()
mp = MotorPerf(m,fs)
self.mp = mp
mp.substitutions[m.Qmax] = 10000
mp.substitutions[mp.R] = .033
mp.substitutions[mp.i0] = 4.5
mp.substitutions[mp.Kv] = 29
self.cost = 1./mp.etam
return self.mp, fs
def test_vtail():
Sw = Variable("S_w", 50, "ft**2", "wing area")
bw = Variable("b_w", 20, "ft", "wing span")
vt = VerticalTail()
fs = FlightState()
vt.substitutions.update({vt.W: 5, vt.planform.AR: 3, vt.Vv: 0.04,
vt.lv: 10, vt.planform.tau: 0.08})
perf = vt.flight_model(vt, fs)
m = Model(perf.Cd, [vt.Vv <= vt.planform.S*vt.lv/Sw/bw, vt, fs, perf])
m.solve(verbosity=0)
def test_htail():
Sw = Variable("S_w", 50, "ft**2", "wing area")
cmac = Variable("cmac", 15, "in", "wing MAC")
ht = HorizontalTail()
fs = FlightState()
ht.substitutions.update({ht.W: 5, ht.mh: 0.01, ht.planform.AR: 4,
ht.Vh: 0.5, ht.lh: 10})
perf = ht.flight_model(ht, fs)
m = Model(perf.Cd, [ht.Vh <= ht.planform.S*ht.lh/Sw/cmac, ht, perf])
m.solve(verbosity=0)
def test_emp():
Sw = Variable("S_w", 50, "ft**2", "wing area")
bw = Variable("b_w", 20, "ft", "wing span")
cmac = Variable("cmac", 15, "in", "wing MAC")
emp = Empennage()
fs = FlightState()
emp.substitutions.update({emp.W: 10, emp.tailboom.l: 5,
emp.htail.planform.AR: 4,
emp.vtail.planform.AR: 4,
emp.vtail.Vv: 0.04,
emp.htail.Vh: 0.4,
emp.htail.mh: 0.01})
htperf = emp.htail.flight_model(emp.htail, fs)
vtperf = emp.vtail.flight_model(emp.vtail, fs)
tbperf = emp.tailboom.flight_model(emp.tailboom, fs)
m = Model(htperf.Cd + vtperf.Cd + tbperf.Cf,
[emp.vtail.lv == emp.tailboom.l, emp.htail.lh == emp.tailboom.l,
emp.htail.Vh <= emp.htail.planform.S*emp.htail.lh/Sw/cmac,
emp.vtail.Vv <= emp.vtail.planform.S*emp.vtail.lv/Sw/bw,
emp, fs, htperf, vtperf, tbperf])
m.solve(verbosity=0)