def execute(self):
wing = Wing(flap_type='single_slot',
configuration='landing',
slats=True,
k_aero=self.k_aero,
sweep=self.sweep,
flap_span=[0.2, 0.4],
taper_ratio=self.taper_ratio)
self.aircraft = Aircraft(wing=wing,
stores=[Payload('Crew', weight=200),
Payload('Cannon', weight=270),
Payload('Ammunition Feed System', weight=405),
Payload('Ammunition', weight=550),
Payload('Casings', weight=198),
Payload('AMRAAMs', weight=332, quantity=4, cd_r=0.005, expendable=True),
Payload('AIM-9Xs', weight=188, quantity=2, cd_r=0.002, expendable=True)],
drag_chute=None)#{'diameter': 15.6, 'cd': 1.4})
mission = Mission(segments=[Segment('warmup',
altitude=self.airfield_altitude,
speed=0,
time=60),
Segment('takeoff',
altitude=self.airfield_altitude,
speed=150,
field_length=self.tofl,
temperature=100),
Segment('climb',
altitude=self.airfield_altitude,
speed=500),
Segment('cruise',
altitude=self.cruise_altitude,
speed=self.cruise_speed,
range=self.cruise_range,
release=[()]),
Segment('descend',
altitude=self.dash_altitude,
speed=1000),
Segment('dash',
altitude=self.dash_altitude,
speed=self.dash_speed,
range=self.dash_range),
Segment('climb',
altitude=self.cruise_altitude,
speed=1000),
Segment('cruise',
altitude=self.cruise_altitude,
speed=1050,
range=self.cruise_range),
Segment('descend',
altitude=self.airfield_altitude,
speed=1000),
Segment('land',
altitude=self.airfield_altitude,
speed=self.landing_speed,
field_length=self.ldgfl)])
self.aircraft._synthesize(mission)
self.aircraft._size(mission)
self.togw = self.aircraft.w_to
self.wing_area = self.aircraft.wing.area
self.thrust = self.aircraft.engine.max_thrust * self.aircraft.num_engines
cost = Cost(aircraft=aircraft,
stealth=self.stealth,
avionics_complexity=self.avionics_complexity,
materials_complexity=self.materials_complexity,
avionics_weight=self.avionics_weight_fraction,
quantity=self.quantity,
year=self.cost_year)
self.acq_cost = cost.estimate_acquisition() / 1e6
class Fighter(Component):
k_aero = Float(0.5, iotype='in', low=0, high=1, desc="K-Factor for aerodynamic efficiency, higher is better")
taper_ratio = Float(0.2, iotype='in', low=0, high=1, desc="The wing tip chord divided by the wing root chord")
sweep = Float(30, iotype='in', low=0, high=55, units='deg', desc="Angle between wing's quarter-chord line and a line perpendicular to the free-stream")
tofl = Float(1500, iotype='in', low=0, units='ft', desc="Takeoff Field Length")
airfield_altitude = Float(0, iotype='in', low=0, units='ft', desc="Altitude at which the airfield is at")
cruise_altitude = Float(30000, iotype='in', low=1000, units='ft', desc="Altitude at which the aircraft is will cruise")
cruise_speed = Float(700, iotype='in', low=0, units='knot', desc="Speed at which the aircraft will cruise")
cruise_range = Float(150, iotype='in', low=0, units='nmi', desc="Distance the aircraft will cover in each cruise segment")
dash_altitude = Float(30000, iotype='in', low=1000, units='ft', desc="Altitude at which the aircraft is will perform the dash segment")
dash_speed = Float(1492, iotype='in', low=0, units='knot', desc="Speed at which the aircraft will dash")
dash_range = Float(100, iotype='in', low=0, units='nmi', desc="Distance the aircraft will cover in each dash segment")
ldgfl = Float(1500, iotype='in', low=0, units='ft', desc="Landing Field Length")
landing_speed = Float(150, iotype='in', low=0, units='knot', desc="Speed the aircraft will fly when touching down")
togw = Float(iotype='out', units='lbm', desc="Take-off Gross Weight")
wing_area = Float(iotype='out', units='ft**2', desc="Wing Area")
thrust = Float(iotype='out', units='lbf', desc="Maximum Thrust produced by the engines")
quantity = Int(iotype='in', low=0, desc="Number of aircraft to manufacture")
stealth = Float(iotype='in', low=0, high=1, desc="Degree of stealthiness required")
materials_complexity = Float(iotype='in', low=0, high=1, desc="Degree of difficulty with working with selected materials")
avionics_weight_fraction = Float(iotype='in', low=0, high=1, desc="Amount of avionics from a nominal amount")
avionics_complexity = Float(iotype='in', low=0, high=1, desc="Degree of complexity of the avionics in the aircraft")
cost_year = Int(iotype='in', low=1999, desc="Year dollars for which to calculate the cost of the aircraft")
acq_cost = Float(iotype='out', units='MUSD', desc="Estimated acquisition cost (fly away cost) for the program")
def execute(self):
wing = Wing(flap_type='single_slot',
configuration='landing',
slats=True,
k_aero=self.k_aero,
sweep=self.sweep,
flap_span=[0.2, 0.4],
taper_ratio=self.taper_ratio)
self.aircraft = Aircraft(wing=wing,
stores=[Payload('Crew', weight=200),
Payload('Cannon', weight=270),
Payload('Ammunition Feed System', weight=405),
Payload('Ammunition', weight=550),
Payload('Casings', weight=198),
Payload('AMRAAMs', weight=332, quantity=4, cd_r=0.005, expendable=True),
Payload('AIM-9Xs', weight=188, quantity=2, cd_r=0.002, expendable=True)],
drag_chute=None)#{'diameter': 15.6, 'cd': 1.4})
mission = Mission(segments=[Segment('warmup',
altitude=self.airfield_altitude,
speed=0,
time=60),
Segment('takeoff',
altitude=self.airfield_altitude,
speed=150,
field_length=self.tofl,
temperature=100),
Segment('climb',
altitude=self.airfield_altitude,
speed=500),
Segment('cruise',
altitude=self.cruise_altitude,
speed=self.cruise_speed,
range=self.cruise_range,
release=[()]),
Segment('descend',
altitude=self.dash_altitude,
speed=1000),
Segment('dash',
altitude=self.dash_altitude,
speed=self.dash_speed,
range=self.dash_range),
Segment('climb',
altitude=self.cruise_altitude,
speed=1000),
Segment('cruise',
altitude=self.cruise_altitude,
speed=1050,
range=self.cruise_range),
Segment('descend',
altitude=self.airfield_altitude,
speed=1000),
Segment('land',
altitude=self.airfield_altitude,
speed=self.landing_speed,
field_length=self.ldgfl)])
self.aircraft._synthesize(mission)
self.aircraft._size(mission)
self.togw = self.aircraft.w_to
self.wing_area = self.aircraft.wing.area
self.thrust = self.aircraft.engine.max_thrust * self.aircraft.num_engines
cost = Cost(aircraft=aircraft,
stealth=self.stealth,
avionics_complexity=self.avionics_complexity,
materials_complexity=self.materials_complexity,
avionics_weight=self.avionics_weight_fraction,
quantity=self.quantity,
year=self.cost_year)
self.acq_cost = cost.estimate_acquisition() / 1e6