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gas.py
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gas.py
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"""Jungle Hawk Owl"""
import numpy as np
from gpkitmodels.GP.aircraft.engine.gas_engine import Engine
from gpkitmodels.GP.aircraft.wing.wing import Wing as WingGP
from gpkitmodels.SP.aircraft.wing.wing import Wing as WingSP
from gpkitmodels.GP.aircraft.fuselage.elliptical_fuselage import Fuselage
from gpkitmodels.GP.aircraft.tail.empennage import Empennage
from gpkitmodels.GP.aircraft.tail.tail_boom import TailBoomState
from gpkitmodels.SP.aircraft.tail.tail_boom_flex import TailBoomFlexibility
from gpkitmodels.tools.summing_constraintset import summing_vars
from gpkit import Model, Variable, Vectorize, units
from flight_segment import FlightSegment
from loiter import Loiter
# pylint: disable=invalid-name
class Aircraft(Model):
"the JHO vehicle"
def setup(self, sp=False):
self.sp = sp
self.fuselage = Fuselage()
if sp:
self.wing = WingSP()
else:
self.wing = WingGP()
self.engine = Engine()
self.emp = Empennage()
components = [self.fuselage, self.wing, self.engine, self.emp]
self.smeared_loads = [self.fuselage, self.engine]
Wzfw = Variable("W_{zfw}", "lbf", "zero fuel weight")
Wpay = Variable("W_{pay}", 10, "lbf", "payload weight")
Wavn = Variable("W_{avn}", 8, "lbf", "avionics weight")
Wwing = Variable("W_{wing}", "lbf", "wing weight for loading")
etaprop = Variable("\\eta_{prop}", 0.8, "-", "propulsive efficiency")
self.emp.substitutions[self.emp.vtail.Vv] = 0.04
self.emp.substitutions[self.emp.vtail.planform.tau] = 0.08
self.emp.substitutions[self.emp.htail.planform.tau] = 0.08
self.wing.substitutions[self.wing.planform.tau] = 0.115
if not sp:
self.emp.substitutions[self.emp.htail.Vh] = 0.45
self.emp.substitutions[self.emp.htail.planform.AR] = 5.0
self.emp.substitutions[self.emp.htail.mh] = 0.1
constraints = [
Wzfw >= sum(summing_vars(components, "W")) + Wpay + Wavn,
Wwing >= sum(summing_vars([self.wing], "W")),
self.emp.htail.Vh <= (
self.emp.htail.planform.S
* self.emp.htail.lh/self.wing.planform.S**2
* self.wing.planform.b),
self.emp.vtail.Vv <= (
self.emp.vtail.planform.S
* self.emp.vtail.lv/self.wing.planform.S
/ self.wing.planform.b),
self.wing.planform.tau*self.wing.planform.croot >= self.emp.tailboom.d0
]
return components, constraints
def flight_model(self, state):
return AircraftPerf(self, state)
class AircraftPerf(Model):
"performance model for aircraft"
def setup(self, static, state):
self.wing = static.wing.flight_model(static.wing, state)
self.fuselage = static.fuselage.flight_model(static.fuselage, state)
self.engine = static.engine.flight_model(state)
self.htail = static.emp.htail.flight_model(static.emp.htail, state)
self.vtail = static.emp.vtail.flight_model(static.emp.vtail, state)
self.tailboom = static.emp.tailboom.flight_model(static.emp.tailboom,
state)
self.dynamicmodels = [self.wing, self.fuselage, self.engine,
self.htail, self.vtail, self.tailboom]
areadragmodel = [self.fuselage, self.htail, self.vtail, self.tailboom]
areadragcomps = [static.fuselage, static.emp.htail,
static.emp.vtail,
static.emp.tailboom]
Wend = Variable("W_{end}", "lbf", "vector-end weight")
Wstart = Variable("W_{start}", "lbf", "vector-begin weight")
CD = Variable("C_D", "-", "drag coefficient")
CDA = Variable("CDA", "-", "area drag coefficient")
mfac = Variable("m_{fac}", 1.0, "-", "drag margin factor")
dvars = []
for dc, dm in zip(areadragcomps, areadragmodel):
if "Cf" in dm.varkeys:
dvars.append(dm["Cf"]*dc["S"]/static.wing["S"])
if "Cd" in dm.varkeys:
dvars.append(dm["Cd"]*dc["S"]/static.wing["S"])
if "C_d" in dm.varkeys:
dvars.append(dm["C_d"]*dc["S"]/static.wing["S"])
constraints = [Wend == Wend,
Wstart == Wstart,
CDA/mfac >= sum(dvars),
CD >= CDA + self.wing.Cd]
return self.dynamicmodels, constraints
class Cruise(Model):
"make a cruise flight segment"
def setup(self, aircraft, N, altitude=15000, latitude=45, percent=90,
day=355, R=200):
fs = FlightSegment(aircraft, N, altitude, latitude, percent, day)
R = Variable("R", R, "nautical_miles", "Range to station")
constraints = [R/N <= fs["V"]*fs.be["t"]]
return fs, constraints
class Climb(Model):
"make a climb flight segment"
def setup(self, aircraft, N, altitude=15000, latitude=45, percent=90,
day=355, dh=15000):
fs = FlightSegment(aircraft, N, altitude, latitude, percent, day)
with Vectorize(N):
hdot = Variable("\\dot{h}", "ft/min", "Climb rate")
deltah = Variable("\\Delta_h", dh, "ft", "altitude difference")
hdotmin = Variable("\\dot{h}_{min}", 100, "ft/min",
"minimum climb rate")
constraints = [
hdot*fs.be["t"] >= deltah/N,
hdot >= hdotmin,
fs.slf["T"] >= (0.5*fs["\\rho"]*fs["V"]**2*fs["C_D"]
* fs.aircraft.wing["S"] + fs["W_{start}"]*hdot
/ fs["V"]),
]
return fs, constraints
class Mission(Model):
"creates flight profile"
def setup(self, latitude=38, percent=90, sp=False):
mtow = Variable("MTOW", "lbf", "max-take off weight")
Wcent = Variable("W_{cent}", "lbf", "center aircraft weight")
Wfueltot = Variable("W_{fuel-tot}", "lbf", "total aircraft fuel weight")
LS = Variable("(W/S)", "lbf/ft**2", "wing loading")
JHO = Aircraft(sp=sp)
climb1 = Climb(JHO, 10, latitude=latitude, percent=percent,
altitude=np.linspace(0, 15000, 11)[1:])
# cruise1 = Cruise(JHO, 1, R=200, latitude=latitude, percent=percent)
loiter1 = Loiter(JHO, 5, latitude=latitude, percent=percent)
# cruise2 = Cruise(JHO, 1, latitude=latitude, percent=percent)
# mission = [climb1, cruise1, loiter1, cruise2]
mission = [climb1, loiter1]
hbend = JHO.emp.tailboom.tailLoad(JHO.emp.tailboom, JHO.emp.htail,
loiter1.fs.fs)
vbend = JHO.emp.tailboom.tailLoad(JHO.emp.tailboom, JHO.emp.vtail,
loiter1.fs.fs)
loading = [JHO.wing.spar.loading(JHO.wing, loiter1.fs.fs),
JHO.wing.spar.gustloading(JHO.wing, loiter1.fs.fs),
hbend, vbend]
if sp:
loading.append(TailBoomFlexibility(JHO.emp.htail,
hbend, JHO.wing))
constraints = [
mtow >= climb1["W_{start}"][0],
Wfueltot >= sum(fs["W_{fuel-fs}"] for fs in mission),
mission[-1]["W_{end}"][-1] >= JHO["W_{zfw}"],
Wcent >= Wfueltot + JHO["W_{pay}"] + JHO["W_{avn}"] + sum(summing_vars(JHO.smeared_loads, "W")),
LS == mtow/JHO.wing["S"],
JHO.fuselage.Vol >= Wfueltot/JHO.fuselage.rhofuel,
Wcent == loading[0]["W"],
Wcent == loading[1]["W"],
loiter1["V"][0] == loading[1].v,
JHO["W_{wing}"] == loading[1].Ww,
loiter1.fs.aircraftPerf.wing.CL[0] == loading[1].cl
]
for i, fs in enumerate(mission[1:]):
constraints.extend([
mission[i]["W_{end}"][-1] == fs["W_{start}"][0]
])
loading[0].substitutions[loading[0].Nmax] = 5
loading[1].substitutions[loading[0].Nmax] = 2
return JHO, mission, loading, constraints
def test():
" test for integrated testing "
model = Mission()
model.substitutions.update({"t_Mission/Loiter": 6})
model.cost = model["MTOW"]
model.solve("mosek")
model = Mission(sp=True)
model.substitutions.update({"t_Mission/Loiter": 6})
model.cost = model["MTOW"]
model.localsolve("mosek")
if __name__ == "__main__":
M = Mission()
M.substitutions.update({"t_Mission/Loiter": 6})
M.cost = M["MTOW"]
sol = M.solve("mosek")