def on_init(self):
pygame.init()
self._display_surf = pygame.display.set_mode((287,510), pygame.HWSURFACE)
pygame.display.set_caption("Annoying Bird 0.5")
self._running = True
self.ss = spritesheet.spritesheet("Flappy-Graphics.bmp")
self.numbers = self.ss.images_at([(276,647,11,13), (276,665,11,13), (276,699,11,13), (276,717,11,13), (276,751,11,13), (276,769,11,13), (276,803,11,13), (276,821,11,13), (276,855,11,13), (276,873,11,13)], colorkey =(255,255,255))
self.background = self.ss.image_at((0, 0, 287, 510))
self.score = 0
self.numberRect = self.numbers[0].get_rect().move(125, 30)
self.flappy = flappy.flappy(self.ss)
self.tube = tube.tube(self.ss)
self.ground = ground.ground(self.ss)
self.menu = True
self.title = pygame.image.load("Menu.bmp")
pygame.mixer.init()
pygame.mixer.music.load("TOP.ogg")
pygame.mixer.music.set_volume(1.0)
def on_init(self):
pygame.init()
self._display_surf = pygame.display.set_mode((287, 510),
pygame.HWSURFACE)
pygame.display.set_caption("Annoying Bird 0.5")
self._running = True
self.ss = spritesheet.spritesheet("Flappy-Graphics.bmp")
self.numbers = self.ss.images_at(
[(276, 647, 11, 13), (276, 665, 11, 13), (276, 699, 11, 13),
(276, 717, 11, 13), (276, 751, 11, 13), (276, 769, 11, 13),
(276, 803, 11, 13), (276, 821, 11, 13), (276, 855, 11, 13),
(276, 873, 11, 13)],
colorkey=(255, 255, 255))
self.background = self.ss.image_at((0, 0, 287, 510))
self.score = 0
self.numberRect = self.numbers[0].get_rect().move(125, 30)
self.flappy = flappy.flappy(self.ss)
self.tube = tube.tube(self.ss)
self.ground = ground.ground(self.ss)
self.menu = True
self.title = pygame.image.load("Menu.bmp")
pygame.mixer.init()
pygame.mixer.music.load("TOP.ogg")
pygame.mixer.music.set_volume(1.0)
def empty(vehicle):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
This is for a standard Tube and Wing aircraft configuration.
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried[kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages['fuselage'].number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
propulsor_name = vehicle.propulsors.keys()[
0] #obtain the key for the propulsor for assignment purposes
propulsors = vehicle.propulsors[propulsor_name]
num_eng = propulsors.number_of_engines
if propulsor_name == 'turbofan' or propulsor_name == 'Turbofan':
# thrust_sls should be sea level static thrust. Using design thrust results in wrong propulsor
# weight estimation. Engine sizing should return this value.
# for now, using thrust_sls = design_thrust / 0.20, just for optimization evaluations
thrust_sls = propulsors.sealevel_static_thrust
wt_engine_jet = Propulsion.engine_jet(thrust_sls)
wt_propulsion = Propulsion.integrated_propulsion(
wt_engine_jet, num_eng)
propulsors.mass_properties.mass = wt_propulsion
else: #propulsor used is not a turbo_fan; assume mass_properties defined outside model
wt_propulsion = propulsors.mass_properties.mass
if wt_propulsion == 0:
warnings.warn(
"Propulsion mass= 0 ;e there is no Engine Weight being added to the Configuration",
stacklevel=1)
S_gross_w = vehicle.reference_area
#S_gross_w = vehicle.wings['main_wing'].Areas.reference
if not vehicle.wings.has_key('main_wing'):
wt_wing = 0.0
wing_c_r = 0.0
warnings.warn(
"There is no Wing Weight being added to the Configuration",
stacklevel=1)
else:
b = vehicle.wings['main_wing'].spans.projected
lambda_w = vehicle.wings['main_wing'].taper
t_c_w = vehicle.wings['main_wing'].thickness_to_chord
sweep_w = vehicle.wings['main_wing'].sweep
mac_w = vehicle.wings['main_wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['main_wing'].chords.root
wt_wing = wing_main(S_gross_w, b, lambda_w, t_c_w, sweep_w, Nult, TOW,
wt_zf)
vehicle.wings['main_wing'].mass_properties.mass = wt_wing
S_fus = vehicle.fuselages['fuselage'].areas.wetted
diff_p_fus = vehicle.fuselages['fuselage'].differential_pressure
w_fus = vehicle.fuselages['fuselage'].width
h_fus = vehicle.fuselages['fuselage'].heights.maximum
l_fus = vehicle.fuselages['fuselage'].lengths.total
if not vehicle.wings.has_key('horizontal_stabilizer'):
wt_tail_horizontal = 0.0
S_h = 0.0
warnings.warn(
"There is no Horizontal Tail Weight being added to the Configuration",
stacklevel=1)
else:
S_h = vehicle.wings['horizontal_stabilizer'].areas.reference
b_h = vehicle.wings['horizontal_stabilizer'].spans.projected
sweep_h = vehicle.wings['horizontal_stabilizer'].sweep
mac_h = vehicle.wings['horizontal_stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['horizontal_stabilizer'].thickness_to_chord
h_tail_exposed = vehicle.wings[
'horizontal_stabilizer'].areas.exposed / vehicle.wings[
'horizontal_stabilizer'].areas.wetted
l_w2h = vehicle.wings['horizontal_stabilizer'].origin[
0] + vehicle.wings['horizontal_stabilizer'].aerodynamic_center[
0] - vehicle.wings['main_wing'].origin[0] - vehicle.wings[
'main_wing'].aerodynamic_center[
0] #Need to check this is the length of the horizontal tail moment arm
wt_tail_horizontal = tail_horizontal(b_h, sweep_h, Nult, S_h, TOW,
mac_w, mac_h, l_w2h, t_c_h,
h_tail_exposed)
vehicle.wings[
'horizontal_stabilizer'].mass_properties.mass = wt_tail_horizontal
if not vehicle.wings.has_key('vertical_stabilizer'):
output_3 = Data()
output_3.wt_tail_vertical = 0.0
output_3.wt_rudder = 0.0
S_v = 0.0
warnings.warn(
"There is no Vertical Tail Weight being added to the Configuration",
stacklevel=1)
else:
S_v = vehicle.wings['vertical_stabilizer'].areas.reference
b_v = vehicle.wings['vertical_stabilizer'].spans.projected
t_c_v = vehicle.wings['vertical_stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['vertical_stabilizer'].sweep
t_tail = vehicle.wings['vertical_stabilizer'].t_tail
output_3 = tail_vertical(S_v, Nult, b_v, TOW, t_c_v, sweep_v,
S_gross_w, t_tail)
vehicle.wings[
'vertical_stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
# Calculating Empty Weight of Aircraft
wt_landing_gear = landing_gear(TOW)
wt_fuselage = tube(S_fus, diff_p_fus, w_fus, h_fus, l_fus, Nlim, wt_zf,
wt_wing, wt_propulsion, wing_c_r)
output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.fuselages['fuselage'].mass_properties.mass = wt_fuselage
# packup outputs
output = payload(TOW, wt_empty, num_pax, wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
output.systems = output_2.wt_systems
output.systems_breakdown = Data()
output.systems_breakdown.control_systems = output_2.wt_flt_ctrl
output.systems_breakdown.apu = output_2.wt_apu
output.systems_breakdown.hydraulics = output_2.wt_hyd_pnu
output.systems_breakdown.instruments = output_2.wt_instruments
output.systems_breakdown.avionics = output_2.wt_avionics
output.systems_breakdown.optionals = output_2.wt_opitems
output.systems_breakdown.electrical = output_2.wt_elec
output.systems_breakdown.air_conditioner = output_2.wt_ac
output.systems_breakdown.furnish = output_2.wt_furnish
#define weights components
try:
landing_gear_component = vehicle.landing_gear #landing gear previously defined
except AttributeError: # landing gear not defined
landing_gear_component = SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.landing_gear = landing_gear_component
control_systems = SUAVE.Components.Physical_Component()
electrical_systems = SUAVE.Components.Physical_Component()
passengers = SUAVE.Components.Physical_Component()
furnishings = SUAVE.Components.Physical_Component()
air_conditioner = SUAVE.Components.Physical_Component()
fuel = SUAVE.Components.Physical_Component()
apu = SUAVE.Components.Physical_Component()
hydraulics = SUAVE.Components.Physical_Component()
optionals = SUAVE.Components.Physical_Component()
rudder = SUAVE.Components.Physical_Component()
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
#assign output weights to objects
landing_gear_component.mass_properties.mass = output.landing_gear
control_systems.mass_properties.mass = output.systems_breakdown.control_systems
electrical_systems.mass_properties.mass = output.systems_breakdown.electrical
passengers.mass_properties.mass = output.pax + output.bag
furnishings.mass_properties.mass = output.systems_breakdown.furnish
avionics.mass_properties.mass = output.systems_breakdown.avionics \
+ output.systems_breakdown.instruments
air_conditioner.mass_properties.mass = output.systems_breakdown.air_conditioner
fuel.mass_properties.mass = output.fuel
apu.mass_properties.mass = output.systems_breakdown.apu
hydraulics.mass_properties.mass = output.systems_breakdown.hydraulics
optionals.mass_properties.mass = output.systems_breakdown.optionals
rudder.mass_properties.mass = output.rudder
#assign components to vehicle
vehicle.control_systems = control_systems
vehicle.electrical_systems = electrical_systems
vehicle.avionics = avionics
vehicle.furnishings = furnishings
vehicle.passenger_weights = passengers
vehicle.air_conditioner = air_conditioner
vehicle.fuel = fuel
vehicle.apu = apu
vehicle.hydraulics = hydraulics
vehicle.optionals = optionals
vehicle.landing_gear = landing_gear_component
vehicle.wings['vertical_stabilizer'].rudder = rudder
return output
]
ds_list = ds_list_sine #[ds_list_mhd[0], ds_list_hydro[0]]
renorm = {'density': 1, 'pressure': 0.6, 'TotalEnergy': 0.9}
if 0:
ds0 = ds_list[0]
ds1 = ds_list[1]
for ds in ds_list:
ray_set[ds] = ds.ortho_ray(axis, coord)
ray_mhd = ray_set[ds0]
ray_hydro = ray_set[ds1]
simname = "both_ics"
simname = 't05_sine'
#x=tube.tube(ds_list, delta=True, fields=fields, renorm=renorm,filename = simname+".png",legend=True)
#y=tube.tube(ds_list_mhd, delta=true, fields=fields, renorm=renorm,filename = "mhd"+".png")
y = tube.tube(ds_list_sine,
delta=True,
fields=fields,
renorm=renorm,
filename="sine" + ".png")
#y=tube.tube(ds_list_hydro,delta=True, fields=fields, renorm=renorm,filename = "hydro"+".png")
if 0:
for i, field in enumerate(fields):
for n_ds, ds in enumerate(ds_list):
counter += 1
this_ray = ray_set[ds]
this_x = this_ray['xyz'[axis]]
this_y = this_ray[field]
stat(this_y)
#needs: ensure list
def empty(vehicle):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
This is for a standard Tube and Wing aircraft configuration.
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried[kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages['fuselage'].number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
V_descent = 80.
d_fus = vehicle.fuselages['fuselage'].effective_diameter
propulsor_name = vehicle.propulsors.keys()[0] # obtain the key for the propulsor for assignment purposes
propulsors = vehicle.propulsors[propulsor_name]
num_eng = propulsors.number_of_engines
if propulsor_name == 'turbofan' or propulsor_name == 'Turbofan':
# thrust_sls should be sea level static thrust. Using design thrust results in wrong propulsor
# weight estimation. Engine sizing should return this value.
# for now, using thrust_sls = design_thrust / 0.20, just for optimization evaluations
thrust_sls = propulsors.sealevel_static_thrust
wt_engine_jet = Propulsion.engine_jet(thrust_sls)
# print wt_engine_jet
# print "Test2"
wt_propulsion = Propulsion.integrated_propulsion(wt_engine_jet, num_eng)
propulsors.mass_properties.mass = wt_propulsion
# print wt_propulsion
d_eng = propulsors.nacelle_diameter
else: # propulsor used is not a turbo_fan; assume mass_properties defined outside model
wt_propulsion = propulsors.mass_properties.mass
if wt_propulsion == 0:
warnings.warn("Propulsion mass= 0 ;e there is no Engine Weight being added to the Configuration",
stacklevel=1)
S_gross_w = vehicle.reference_area
# S_gross_w = vehicle.wings['main_wing'].Areas.reference
if not vehicle.wings.has_key('main_wing'):
wt_wing = 0.0
wing_c_r = 0.0
warnings.warn("There is no Wing Weight being added to the Configuration", stacklevel=1)
else:
b = vehicle.wings['main_wing'].spans.projected
lambda_w = vehicle.wings['main_wing'].taper
t_c_w = vehicle.wings['main_wing'].thickness_to_chord
sweep_w = vehicle.wings['main_wing'].sweep
mac_w = vehicle.wings['main_wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['main_wing'].chords.root
# print 'c_root =',wing_c_r
wt_wing = wing_main(S_gross_w, b, lambda_w, t_c_w, sweep_w, Nult, TOW, wt_zf)
vehicle.wings['main_wing'].mass_properties.mass = wt_wing
S_fus = vehicle.fuselages['fuselage'].areas.wetted
diff_p_fus = vehicle.fuselages['fuselage'].differential_pressure
w_fus = vehicle.fuselages['fuselage'].width
h_fus = vehicle.fuselages['fuselage'].heights.maximum
l_fus = vehicle.fuselages['fuselage'].lengths.total
if not vehicle.wings.has_key('horizontal_stabilizer'):
wt_tail_horizontal = 0.0
S_h = 0.0
warnings.warn("There is no Horizontal Tail Weight being added to the Configuration", stacklevel=1)
else:
S_h = vehicle.wings['horizontal_stabilizer'].areas.reference
b_h = vehicle.wings['horizontal_stabilizer'].spans.projected
A_h = vehicle.wings['horizontal_stabilizer'].aspect_ratio
sweep_h = vehicle.wings['horizontal_stabilizer'].sweep
mac_h = vehicle.wings['horizontal_stabilizer'].chords.mean_aerodynamic
c_r_h = vehicle.wings['horizontal_stabilizer'].chords.root
t_c_h = vehicle.wings['horizontal_stabilizer'].thickness_to_chord
# print 'c_r_h =',c_r_h
taper_h = vehicle.wings['horizontal_stabilizer'].taper
h_tail_exposed = vehicle.wings['horizontal_stabilizer'].areas.exposed / vehicle.wings[
'horizontal_stabilizer'].areas.wetted
l_w2h = vehicle.wings['horizontal_stabilizer'].origin[0] + \
vehicle.wings['horizontal_stabilizer'].aerodynamic_center[0] - vehicle.wings['main_wing'].origin[0] - \
vehicle.wings['main_wing'].aerodynamic_center[
0] # Need to check this is the length of the horizontal tail moment arm
# wt_tail_horizontal = tail_horizontal(b_h, sweep_h, Nult, S_h, TOW, mac_w, mac_h, l_w2h, t_c_h, h_tail_exposed)
Sel = 0.15 * S_h
wt_tail_horizontal = hor_tail(c_r_h, taper_h, l_w2h, Sel, S_h, A_h, b_h, sweep_h, TOW, Nult)
vehicle.wings['horizontal_stabilizer'].mass_properties.mass = wt_tail_horizontal
if not vehicle.wings.has_key('vertical_stabilizer'):
output_3 = Data()
output_3.wt_tail_vertical = 0.0
output_3.wt_rudder = 0.0
S_v = 0.0
warnings.warn("There is no Vertical Tail Weight being added to the Configuration", stacklevel=1)
else:
S_v = vehicle.wings['vertical_stabilizer'].areas.reference
b_v = vehicle.wings['vertical_stabilizer'].spans.projected
A_v = vehicle.wings['vertical_stabilizer'].aspect_ratio
t_c_v = vehicle.wings['vertical_stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['vertical_stabilizer'].sweep
taper_v = vehicle.wings['vertical_stabilizer'].taper
c_r_v = vehicle.wings['vertical_stabilizer'].chords.root
mac_v = vehicle.wings['vertical_stabilizer'].chords.mean_aerodynamic
t_tail = vehicle.wings['vertical_stabilizer'].t_tail
output_3 = tail_vertical(S_v, Nult, b_v, TOW, t_c_v, sweep_v, S_gross_w, t_tail)
wt_tail_vertical = vert_tail(S_v, b_v, c_r_v, taper_v, t_c_v, A_v, sweep_v, l_w2h, TOW)
vehicle.wings['vertical_stabilizer'].mass_properties.mass = wt_tail_vertical
# print 'b_v =',b_v
# print 'c_r_v =',c_r_v
# print 'c_t_v =',c_r_v*taper_v
# vehicle.wings['vertical_stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
# Calculating Empty Weight of Aircraft
wt_landing_gear, gear, h_gear = landing_gear(TOW, d_eng, h_fus, V_descent)
# print 'h_gear =', h_gear
l_nose = vehicle.fuselages['fuselage'].lengths.nose
l_center = vehicle.fuselages['fuselage'].lengths.cabin
l_tail = vehicle.fuselages['fuselage'].lengths.tail
S_cstot = 0.22 * mac_w * 0.6 * b * 1.5 + 0.3 * mac_v * 0.9 * b_v + 0.2 * mac_h * 0.9 * b_h # 1.5 factor is because of assumed spoilers on wings
Iy_SI = 1230140.7646609414 # kgm^2
Vmax = 240 # m/s
wt_fuselage = tube(S_fus, diff_p_fus, w_fus, h_fus, l_nose, l_center, l_tail, l_fus, Nlim, wt_zf, wt_wing,
wt_propulsion, wing_c_r, TOW, h_gear)
# output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
OEW = 109000 # kg #FIXME
V_fuel = 69000 / 820 # m^3 #FIXME
wt_engine_jet = 9000 # kg
output_sys = classIIsys(num_eng, wt_engine_jet, V_fuel, Iy_SI, S_cstot, l_fus, OEW, TOW, Vmax, b)
l_eng = 7 # m
output_prop = propgroup(num_eng, wt_engine_jet, d_eng, l_eng, output_sys.w_fuelsys, output_sys.w_starter, Nult,
Vmax)
wt_propulsion = output_prop.w_propulsion
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_sys.w_system +
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.fuselages['fuselage'].mass_properties.mass = wt_fuselage
# packup outputs
output = payload(TOW, wt_empty, num_pax, wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
output.systems = output_sys.w_system
output.systems_breakdown = Data()
output.systems_breakdown.control_systems = output_sys.w_flightcontrol
output.systems_breakdown.apu = output_sys.w_apu
output.systems_breakdown.hydraulics = output_sys.w_hydraullics
# output.systems_breakdown.instruments = output_sys.wt_instruments
output.systems_breakdown.avionics = output_sys.w_avionics
# output.systems_breakdown.optionals = output_sys.wt_opitems
output.systems_breakdown.electrical = output_sys.w_electrical
output.systems_breakdown.air_conditioner = output_sys.w_env
# output.systems_breakdown.furnish = output_2.wt_furnish
# define weights components
try:
landing_gear_component = vehicle.landing_gear # landing gear previously defined
except AttributeError: # landing gear not defined
landing_gear_component = SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.landing_gear = landing_gear_component
control_systems = SUAVE.Components.Physical_Component()
electrical_systems = SUAVE.Components.Physical_Component()
passengers = SUAVE.Components.Physical_Component()
# furnishings = SUAVE.Components.Physical_Component()
air_conditioner = SUAVE.Components.Physical_Component()
fuel = SUAVE.Components.Physical_Component()
apu = SUAVE.Components.Physical_Component()
hydraulics = SUAVE.Components.Physical_Component()
# optionals = SUAVE.Components.Physical_Component()
rudder = SUAVE.Components.Physical_Component()
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
# assign output weights to objects
landing_gear_component.mass_properties.mass = output.landing_gear
control_systems.mass_properties.mass = output.systems_breakdown.control_systems
electrical_systems.mass_properties.mass = output.systems_breakdown.electrical
passengers.mass_properties.mass = output.pax + output.bag
# furnishings.mass_properties.mass = output.systems_breakdown.furnish
avionics.mass_properties.mass = output.systems_breakdown.avionics # \
# + output.systems_breakdown.instruments
air_conditioner.mass_properties.mass = output.systems_breakdown.air_conditioner
fuel.mass_properties.mass = output.fuel
apu.mass_properties.mass = output.systems_breakdown.apu
hydraulics.mass_properties.mass = output.systems_breakdown.hydraulics
# optionals.mass_properties.mass = output.systems_breakdown.optionals
rudder.mass_properties.mass = output.rudder
# assign components to vehicle
vehicle.control_systems = control_systems
vehicle.electrical_systems = electrical_systems
vehicle.avionics = avionics
# vehicle.furnishings = furnishings
vehicle.passenger_weights = passengers
vehicle.air_conditioner = air_conditioner
vehicle.fuel = fuel
vehicle.apu = apu
vehicle.hydraulics = hydraulics
# vehicle.optionals = optionals
vehicle.landing_gear = landing_gear_component
vehicle.wings['vertical_stabilizer'].rudder = rudder
return output
axis = 0
coord = (0.505, 0.505)
counter = 0
#fields=['density','pressure','TotalEnergy','x-velocity', ]#,'x-velocity']
fields = ['%s_p' % s for s in all_x]
#fields += ['Bx','By','Bz','magnetic_energy']
#fields += ['magnetic_field_x','magnetic_field_y','magnetic_field_z','magnetic_energy']
#fields +=['x-velocity','y-velocity','z-velocity']
#fields += ['Ltension_x',
#fields += ['Badvection_x']
ray_set = {}
sim = 'a03'
frames = [0]
ds_list = [
yt.load("%s/DD%04d/data%04d" % (sims[sim], frame, frame))
for frame in frames
]
g = ds_list[0].index.grids[0]
#print g[fields[0]]
data = g
renorm = {'density': 1, 'pressure': 0.6, 'TotalEnergy': 0.9}
y = tube.tube(ds_list,
return_ray=True,
delta=False,
fields=fields,
renorm=renorm,
filename="Tube_%s%s.png" %
(sim, "_%s" * len(fields) % tuple(fields)),
labels=fields,
plot_args={'marker': '*'})
def empty(vehicle):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
This is for a standard Tube and Wing aircraft configuration.
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried[kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages.Fuselage.number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
if not vehicle.propulsors.has_key('Turbo Fan'):
wt_engine_jet = 0.0
wt_propulsion = 0.0
warnings.warn("There is no Turbo Fan Engine Weight being added to the Configuration", stacklevel=1)
else:
num_eng = vehicle.propulsors['Turbo Fan'].number_of_engines
thrust_sls = vehicle.propulsors['Turbo Fan'].thrust.design
wt_engine_jet = Propulsion.engine_jet(thrust_sls)
wt_propulsion = Propulsion.integrated_propulsion(wt_engine_jet,num_eng)
S_gross_w = vehicle.reference_area
#S_gross_w = vehicle.wings['Main Wing'].Areas.reference
if not vehicle.wings.has_key('Main Wing'):
wt_wing = 0.0
wing_c_r = 0.0
warnings.warn("There is no Wing Weight being added to the Configuration", stacklevel=1)
else:
b = vehicle.wings['Main Wing'].spans.projected
lambda_w = vehicle.wings['Main Wing'].taper
t_c_w = vehicle.wings['Main Wing'].thickness_to_chord
sweep_w = vehicle.wings['Main Wing'].sweep
mac_w = vehicle.wings['Main Wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['Main Wing'].chords.root
wt_wing = wing_main(S_gross_w,b,lambda_w,t_c_w,sweep_w,Nult,TOW,wt_zf)
vehicle.wings['Main Wing'].mass_properties.mass = wt_wing
S_fus = vehicle.fuselages.Fuselage.areas.wetted
diff_p_fus = vehicle.fuselages.Fuselage.differential_pressure
w_fus = vehicle.fuselages.Fuselage.width
h_fus = vehicle.fuselages.Fuselage.heights.maximum
l_fus = vehicle.fuselages.Fuselage.lengths.total
if not vehicle.wings.has_key('Horizontal Stabilizer'):
wt_tail_horizontal = 0.0
S_h = 0.0
warnings.warn("There is no Horizontal Tail Weight being added to the Configuration", stacklevel=1)
else:
S_h = vehicle.wings['Horizontal Stabilizer'].areas.reference
b_h = vehicle.wings['Horizontal Stabilizer'].spans.projected
sweep_h = vehicle.wings['Horizontal Stabilizer'].sweep
mac_h = vehicle.wings['Horizontal Stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['Horizontal Stabilizer'].thickness_to_chord
h_tail_exposed = vehicle.wings['Horizontal Stabilizer'].areas.exposed / vehicle.wings['Horizontal Stabilizer'].areas.wetted
l_w2h = vehicle.wings['Horizontal Stabilizer'].origin[0] + vehicle.wings['Horizontal Stabilizer'].aerodynamic_center[0] - vehicle.wings['Main Wing'].origin[0] - vehicle.wings['Main Wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm
wt_tail_horizontal = tail_horizontal(b_h,sweep_h,Nult,S_h,TOW,mac_w,mac_h,l_w2h,t_c_h, h_tail_exposed)
vehicle.wings['Horizontal Stabilizer'].mass_properties.mass = wt_tail_horizontal
if not vehicle.wings.has_key('Vertical Stabilizer'):
output_3 = Data()
output_3.wt_tail_vertical = 0.0
output_3.wt_rudder = 0.0
S_v = 0.0
warnings.warn("There is no Vertical Tail Weight being added to the Configuration", stacklevel=1)
else:
S_v = vehicle.wings['Vertical Stabilizer'].areas.reference
b_v = vehicle.wings['Vertical Stabilizer'].spans.projected
t_c_v = vehicle.wings['Vertical Stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['Vertical Stabilizer'].sweep
t_tail = vehicle.wings['Vertical Stabilizer'].t_tail
output_3 = tail_vertical(S_v,Nult,b_v,TOW,t_c_v,sweep_v,S_gross_w,t_tail)
vehicle.wings['Vertical Stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
# process
# Calculating Empty Weight of Aircraft
wt_landing_gear = landing_gear(TOW)
wt_fuselage = tube(S_fus, diff_p_fus,w_fus,h_fus,l_fus,Nlim,wt_zf,wt_wing,wt_propulsion, wing_c_r)
output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.fuselages.Fuselage.mass_properties.mass = wt_fuselage
# packup outputs
output = payload(TOW, wt_empty, num_pax,wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.systems = output_2.wt_systems
output.wt_furnish = output_2.wt_furnish
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
return output
line_title = f"the {line.capitalize()} Line"
station_list = []
line_names = t.getLines(False)
line_ids = t.getLines(True)
if line != "all":
if line.lower() != "dlr":
print(
"--------------------------------------------NON-DLR------------------------------------"
)
id_num = line_names.index(line.title())
line_id = line_ids[id_num]
station_list = t.getStationsOnLine(line_id)
else:
print(
"--------------------------------------------DLR------------------------------------"
)
station_list = t.getDlrStations()
print(station_list)
else:
station_list = t.getAllStations(False)
station_result = []
for item in station_list:
station_result.append("<tr><td>" + item + "</td></tr>")
return str(page).format(''.join(result), line_title,
''.join(station_result))
if __name__ == "__main__":
t = tube.tube()
cherrypy.quickstart(tube_app(), config="config.txt")
import tube
reload(tube)
sim1 = '/Users/dcollins/Enzo/dave_vs_enzo_COSMOLOGY_UP/run/Cosmology/MHDZeldovichPancake'
sim2 = '/Users/dcollins/Enzo/dave_vs_enzo_COSMOLOGY_UP/run/Cosmology/MHDCTZeldovichPancake'
coord = (0.505, 0.505)
frame_list = [0]
#ds_list = [yt.load("%s/DD%04d/data%04d"%(sim,frame,frame)) for frame in frame_list]
#rays = [ds.ortho_ray(0,coord) for ds in ds_list]
for this_frame in [0, 20]:
frame_list = [this_frame]
ds_list = [
yt.load("%s/DD%04d/data%04d" % (sim1, frame, frame))
for frame in frame_list
]
ds_list += [
yt.load("%s/DD%04d/mhdct%04d" % (sim2, frame, frame))
for frame in frame_list
]
outname = 'with_a_in_pressure_%d.pdf' % frame
fields = ['density', 'pressure', 'By', 'x-velocity']
y = tube.tube(ds_list, fields=fields, filename=outname,
legend=True) #, renorm=renorm,filename = "sine"+".png")
if 0:
print outname
#print rays[0]['magnetic_energy']/rays[2]['magnetic_energy']
print rays[0]['magnetic_energy'] / rays[2]['magnetic_energy']
print "print rays[1]['magnetic_energy']/rays[3]['magnetic_energy']"
x = rays[0]['density'] / rays[2]['density']
print "densty 0", x.min(), x.max()
from pylab import *
import numpy as np
import scikits.audiolab
import tube
import scipy.io.wavfile
#x = arange(0, 1, 0.01)
ret = scikits.audiolab.wavread("/Users/shaoduo/Desktop/dsp_presentation/eg.wav")
#ret = scipy.io.wavfile.read("/Users/shaoduo/Desktop/dsp_presentation/eg.wav")
x = ret[1]
subplot(3, 1, 1)
plot(x)
for i in range(0, len(x)):
x[i] = x[i] / 2**15
y = tube.tube(x, 3.0, 1.0, 150.0, 0.8, 0.8, 0.6)
#y = tube.symclip(x)
#y = tube.expdist(x, 10.0, 0.8)
scikits.audiolab.wavwrite(y, "/Users/shaoduo/Desktop/dsp_presentation/eg-d.wav", fs=44100, enc='pcm16')
#scipy.io.wavfile.write("/Users/shaoduo/Desktop/dsp_presentation/eg-d.wav", 44100, y)
subplot(3, 1, 2)
plot(y)
xy = abs(x) - abs(y)
subplot(3, 1, 3)
plot(xy)
show()
import matplotlib
matplotlib.use('Agg')
import matplotlib.pyplot as plt
import yt
import tube
ds_list = [yt.load("DD%04d/data%04d"%(frame,frame)) for frame in [0,1]]
tube.tube(ds_list, legend = True, delta=False, fields=['density','Metal_Density'],filename = 'tube.pdf',labels=['DD%04d'%n for n in [0,1]])
]
all_ds += ds_list
print(all_ds)
g = ds_list[0].index.grids[0]
data = g
renorm = {'density': 1, 'pressure': 0.6, 'TotalEnergy': 0.9}
#renorm = False
#this_ray = ray_info.get(i,ray_info_default)
print(this_ray)
y = tube.tube(
ds_list,
return_ray=False,
delta=False,
fields=fields,
renorm=renorm,
filename=
outname, # "Tube_%s%s.png"%(sim,"_%s"*len(fields)%tuple(fields)),
#labels=fields,
plot_args={'marker': '*'},
legend=True,
labels=sim_list,
ylim_method='monotonic',
yscale={'density': 'linear'},
**this_ray)
#y=tube.tube(all_ds, return_ray=False, delta=False, fields=fields, renorm=renorm,
# filename = "TUBE_many",# "Tube_%s%s.png"%(sim,"_%s"*len(fields)%tuple(fields)),
# #labels=fields,
# plot_args={'marker':'*'},legend=True, labels=sim_list+sim_list+sim_list)
import tube
reload(tube)
base_dir = '/Users/dcollins/Enzo/enzo-dev/run/MHD/1D/'
bw_ded = '%s/BrioWu-MHD-1D'%base_dir
bw_ct = '%s/BrioWu-MHD-1D-MHDCT'%base_dir
bw_cbremoval = '/Users/dcollins/Enzo/dave_vs_enzo_CenteredBremoval/run/MHD/1D/BrioWu-MHD-1D-MHDCT-CenteredBremoval'
bw_ct_fid = '/Users/dcollins/Enzo/dave_vs_enzo_CenteredBremoval/run/MHD/1D/BrioWu-MHD-1D-MHDCT'
frame = 1
fields=['density','pressure','TotalEnergy','x-velocity', 'By' ]#,'x-velocity']
fields += ['ByF','Bz', 'velocity_y','velocity_z']
BWfields = ['density','x-velocity','By']
fields = BWfields
extra=2
frame=11
#set_name = 'ED%02d_%04d/Extra%02d_%04d'%(extra,frame,extra,frame)
#outname = 'ED%02d_%04d.pdf'%(extra,frame)
outname="BW"+"%04d.pdf"%frame
set_name = 'DD%04d/data%04d'%(frame,frame)
#ds_list = [yt.load("%s/%s"%(sim, set_name)) for sim in [bw_ct_fid,bw_cbremoval]]
bw02 = '/scratch1/dcollins/EnzoProjects/E22_DEF_NonCosmo/bw02_ct'
bw01 = '/scratch1/dcollins/EnzoProjects/E22_DEF_NonCosmo/bw01_ded'
outname = 'E22_wtf.pdf'
ds_list = [yt.load("%s/%s"%(sim, set_name)) for sim in [bw01,bw02]]
y=tube.tube(ds_list, delta=False, fields=fields, renorm=False,filename =outname ,labels=['bw01','bw02'],legend=True)
#OutputTemplate = "/RD%04d/RedshiftOutput%04d"
axis = 1
counter = 0
#fields=['density','TotalEnergy','x-velocity','By','enzo_pressure']
#renorm={'density':1,'pressure':0.6,'TotalEnergy':0.9}
for frame in frames:
ds_list = [
yt.load(sim_1 + OutputTemplate % (frame, frame)) for sim_1 in sim_list
]
y = tube.tube(ds_list,
delta=delta,
fields=fields,
renorm=False,
filename='e12_tube_%s_cons_%04d.pdf' % (note, frame),
legend=True,
labels=labels,
xlim=[0.42, 0.58])
if 0:
fields_derived = ['thermal_energy', 'pressure', 'BoverRho']
y = tube.tube(ds_list,
delta=delta,
fields=fields_derived,
renorm=False,
filename='e12_tube_%s_derived_%04d.pdf' % (note, frame),
legend=True,
labels=labels)
def process(mobile, message):
# extract the first word, and call it "operator"
message_array = message.split()
operator = message_array[0]
data = sessions.retrive_data(mobile)
origin = data[1]
destination = data[2]
req_time = data[3]
req_mes = " ".join(message_array[1:])
if len(re.findall("((?<= at )\d{1,2})(:)((?<=:)\d{1,2}).*", req_mes, re.IGNORECASE)) != 0:
user_time = re.findall("((?<= at )\d{1,2})(:)((?<=:)\d{1,2}).*", req_mes, re.IGNORECASE)[0]
start_time = datetime.datetime.today()
start_time = start_time.replace(hour = int(user_time[0]))
start_time = start_time.replace(minute = int(user_time[2]))
req_time = int((start_time - datetime.datetime(1970,1,1)).total_seconds())
sessions.save_time(number, req_time)
#Is the operator "from"
if operator == "from":
#do we have a stored destination?
if destination != None:
#google using the rest of the message and the stored destination
google_it(mobile, " ".join(message_array[1:]), destination, req_time)
# else:
else:
# save the rest of the message as the origin
origin = " ".join(message_array[1:])
sessions.add_origin(mobile, origin)
# Request the destination
dest_req(mobile)
#ok, how about "to"
elif operator == "to":
process_origin(mobile, " ".join(message_array[1:]), origin, destination, req_time)
#if they have asked to reset:
elif operator == "reset":
sessions.delete(mobile)
send_text.text(mobile, "Reset successful!")
elif operator == "bus":
bus.bus(mobile, " ".join(message_array[1:]))
elif operator == "tube":
tube.tube(mobile, " ".join(message_array[1:]))
#help operator:
elif operator == "help":
send_text.text(mobile, "Hi! Thanks for using traxt. Our service is simple to use:")
time.sleep(3)
send_text.text(mobile, "1) If you want directions, send a text containing either the start or end point, formatted like so: ")
time.sleep(3)
send_text.text(mobile, "To set the destination, send a message starting with \"to\" directly followed by the destination. e.g: \"to London\". You will then be prompted to send your start point, which should be formatted like so: ")
time.sleep(3)
send_text.text(mobile, "To set the start point of your journey, send a message starting with \"from\", directly followed by the start point. e.g: \"from London\". You will then be prompted to send your destination, which should be formatted as shown above.")
time.sleep(3)
send_text.text(mobile, "2) If you would like tube or bus status, text \"tube [underground line]\" or \"bus [bus No.]\" ")
time.sleep(3)
send_text.text(mobile, "By sending \"reset\", your session will be cleared, although it will also be cleared automatically. Thanks for using traxt.")
sessions.delete(mobile)
# so we don't know the operator.
else:
# Do we have a saved origin?
if origin != None:
# then this must be the destination
destination = " ".join(message_array)
# google using the saved origin and the rest of the message
print "Origin is: " +str(origin) +". Type is "+str(type(origin))
print "Destination is: "+str(destination)+". Type is "+str(type(destination))
google_it(mobile, origin, destination, req_time)
# we dont have a saved origin, so this must be it
else:
# save the message as the origin
origin = " ".join(message_array)
if destination != None:
google_it(mobile, origin, destination, req_time)
else:
sessions.add_origin(mobile, origin)
# prompt for the destination
dest_req(mobile)
simlist = ['s11']
axis = 0
coord = (0.505, 0.505)
counter = 0
#fields=['density','pressure','TotalEnergy','x-velocity', ]#,'x-velocity']
#fields =['%s_p'%s for s in all_x]
#fields += ['Bx','By','Bz','magnetic_energy']
#fields += ['magnetic_field_x','magnetic_field_y','magnetic_field_z','magnetic_energy']
#fields +=['x-velocity','y-velocity','z-velocity']
#fields += ['Ltension_x',
#fields += ['Badvection_x']
fields = ['density',
'Metal_Density'] #'Temperature', 'TotalEnergy']# , 'metallicity']
ray_set = {}
frames = [0, 1] #range(0,10)
renorm = {'density': 1, 'pressure': 0.6, 'TotalEnergy': 0.9}
for sim in simlist:
ds_list = []
ds_list += [
yt.load("%s/DD%04d/data%04d" % (sims[sim], frame, frame))
for frame in frames
]
fname = "Tube_%s_dev_%s.pdf" % (sim, "_%s" * len(fields) % tuple(fields))
y = tube.tube(ds_list,
legend=True,
delta=False,
fields=fields,
filename=fname,
labels=[""] * 100) #, xlim = [0.25,0.75])
#, labels=fields, plot_args={'marker':'*'})
def main():
system("cls")
print("Welcome to the JMC Tube & Rail App")
print(
"\n[1]: View Statuses\n[2]: View Stations\n[3]: View Fares\n[4]: View Lines\n[9]: Sync\n[0]: Exit"
)
option = input("Please select an option > ")
if option == "1":
status()
elif option == "2":
station()
elif option == "3":
fares()
elif option == "4":
lines()
elif option == "9":
print("\nSyncing...")
tube_data.update()
rail_data.update()
elif option == "0":
raise SystemExit
else:
print("Thats not an option!")
input("Press enter to continue... ")
main()
if __name__ == "__main__":
tube_data = tube.tube()
rail_data = tube.rail()
main()
def empty_custom_eng(vehicle, propulsor):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
This is for a standard Tube and Wing aircraft configuration.
Inputs:
propulsor - a propulsor object
mass_properties.mass
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried[kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
#thrust_sls = vehicle.propulsors['Turbo Fan'].thrust.design
S_gross_w = vehicle.reference_area
#S_gross_w = vehicle.wings['Main Wing'].Areas.reference
b = vehicle.wings['Main Wing'].spans.projected
lambda_w = vehicle.wings['Main Wing'].taper
t_c_w = vehicle.wings['Main Wing'].thickness_to_chord
sweep_w = vehicle.wings['Main Wing'].sweep
mac_w = vehicle.wings['Main Wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['Main Wing'].chords.root
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages.Fuselage.number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
#l_w2h = vehicle.wings['Horizontal Stabilizer'].position[0] + vehicle.wings['Horizontal Stabilizer'].aerodynamic_center[0] - vehicle.wings['Main Wing'].position[0] - vehicle.wings['Main Wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm
l_w2h = vehicle.w2h
S_fus = vehicle.fuselages.Fuselage.areas.wetted
diff_p_fus = vehicle.fuselages.Fuselage.differential_pressure
w_fus = vehicle.fuselages.Fuselage.width
h_fus = vehicle.fuselages.Fuselage.heights.maximum
l_fus = vehicle.fuselages.Fuselage.lengths.total
S_h = vehicle.wings['Horizontal Stabilizer'].areas.reference
b_h = vehicle.wings['Horizontal Stabilizer'].spans.projected
sweep_h = vehicle.wings['Horizontal Stabilizer'].sweep
mac_h = vehicle.wings['Horizontal Stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['Horizontal Stabilizer'].thickness_to_chord
h_tail_exposed = vehicle.wings[
'Horizontal Stabilizer'].areas.exposed / vehicle.wings[
'Horizontal Stabilizer'].areas.wetted
S_v = vehicle.wings['Vertical Stabilizer'].areas.reference
b_v = vehicle.wings['Vertical Stabilizer'].spans.projected
t_c_v = vehicle.wings['Vertical Stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['Vertical Stabilizer'].sweep
t_tail = vehicle.wings['Vertical Stabilizer'].t_tail
# process
# Calculating Empty Weight of Aircraft
wt_wing = wing_main(S_gross_w, b, lambda_w, t_c_w, sweep_w, Nult, TOW,
wt_zf)
wt_landing_gear = landing_gear(TOW)
wt_propulsion = propulsor.mass_properties.mass
wt_fuselage = tube(S_fus, diff_p_fus, w_fus, h_fus, l_fus, Nlim, wt_zf,
wt_wing, wt_propulsion, wing_c_r)
output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
wt_tail_horizontal = tail_horizontal(b_h, sweep_h, Nult, S_h, TOW, mac_w,
mac_h, l_w2h, t_c_h, h_tail_exposed)
output_3 = tail_vertical(S_v, Nult, b_v, TOW, t_c_v, sweep_v, S_gross_w,
t_tail)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.wings['Main Wing'].mass_properties.mass = wt_wing
vehicle.wings[
'Horizontal Stabilizer'].mass_properties.mass = wt_tail_horizontal
vehicle.wings[
'Vertical Stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
vehicle.fuselages.Fuselage.mass_properties.mass = wt_fuselage
#vehicle.propulsors['Turbo Fan'].mass_properties.mass = wt_engine_jet
# packup outputs
output = payload(TOW, wt_empty, num_pax, wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.systems = output_2.wt_systems
output.wt_furnish = output_2.wt_furnish
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
return output
#df.loc[:, 'num_bends_quantity'] = (df['num_bends'] / df['quantity']) ** (1/3)
#df.loc[:, 'bend_ratio'] = ((df['num_bends'] * df['bend_radius']) / df['quantity']) ** (1/3)
# train.loc[:, 'inv_diameter'] = train['diameter'].apply(utils.make_inv)
# test.loc[:, 'inv_diameter'] = test['diameter'].apply(utils.make_inv)
return df
print('reading train data')
data = pd.read_csv('../competition_data/train_set.csv', parse_dates=[2, ])
data = data[data['quantity'] != 2500]
#data = data[data['annual_usage'] != 150000]
# tube data
tube_data = pd.read_csv('../competition_data/tube.csv')
tube_data = tube.tube(tube_data)
data = pd.merge(data, tube_data, on='tube_assembly_id')
data = specs.specs(data)
data = bill_of_material.bill_of_material(data)
#data.loc[:, 'diameter'] = (data['diameter'] / data['quantity']) ** (1/3)
#data.loc[:, 'length_quantity'] = (data['length'] / data['quantity']) ** (1/3)
#data.loc[:, 'wall_quantity'] = (data['wall'] / data['quantity']) ** (1/3)
#data.loc[:, 'volume_quantity'] = (data['volume'] / data['quantity'])
feature_importance = {}
if not test:
scores = []
for train, test in train_test(data, unique_split_label='tube_assembly_id'):
#print('train', train.head())
# train.loc[:, 'inv_diameter'] = train['diameter'].apply(utils.make_inv)
# test.loc[:, 'inv_diameter'] = test['diameter'].apply(utils.make_inv)
return df
print('reading train data')
data = pd.read_csv('../competition_data/train_set.csv', parse_dates=[
2,
])
data = data[data['quantity'] != 2500]
#data = data[data['annual_usage'] != 150000]
# tube data
tube_data = pd.read_csv('../competition_data/tube.csv')
tube_data = tube.tube(tube_data)
data = pd.merge(data, tube_data, on='tube_assembly_id')
data = specs.specs(data)
data = bill_of_material.bill_of_material(data)
#data.loc[:, 'diameter'] = (data['diameter'] / data['quantity']) ** (1/3)
#data.loc[:, 'length_quantity'] = (data['length'] / data['quantity']) ** (1/3)
#data.loc[:, 'wall_quantity'] = (data['wall'] / data['quantity']) ** (1/3)
#data.loc[:, 'volume_quantity'] = (data['volume'] / data['quantity'])
feature_importance = {}
if not test:
scores = []
for train, test in train_test(data, unique_split_label='tube_assembly_id'):
#print('train', train.head())
def empty(vehicle):
""" This is for a standard Tube and Wing aircraft configuration.
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
Source:
N/A
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried [kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Properties Used:
N/A
"""
# Unpack inputs
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages['fuselage'].number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
propulsor_name = vehicle.propulsors.keys()[0] #obtain the key for the propulsor for assignment purposes
propulsors = vehicle.propulsors[propulsor_name]
num_eng = propulsors.number_of_engines
if propulsor_name=='turbofan' or propulsor_name=='Turbofan':
# thrust_sls should be sea level static thrust. Using design thrust results in wrong propulsor
# weight estimation. Engine sizing should return this value.
# for now, using thrust_sls = design_thrust / 0.20, just for optimization evaluations
thrust_sls = propulsors.sealevel_static_thrust
wt_engine_jet = Propulsion.engine_jet(thrust_sls)
wt_propulsion = Propulsion.integrated_propulsion(wt_engine_jet,num_eng)
propulsors.mass_properties.mass = wt_propulsion
else: #propulsor used is not a turbo_fan; assume mass_properties defined outside model
wt_propulsion = propulsors.mass_properties.mass
if wt_propulsion==0:
warnings.warn("Propulsion mass= 0 ;e there is no Engine Weight being added to the Configuration", stacklevel=1)
S_gross_w = vehicle.reference_area
if not vehicle.wings.has_key('main_wing'):
wt_wing = 0.0
wing_c_r = 0.0
warnings.warn("There is no Wing Weight being added to the Configuration", stacklevel=1)
else:
b = vehicle.wings['main_wing'].spans.projected
lambda_w = vehicle.wings['main_wing'].taper
t_c_w = vehicle.wings['main_wing'].thickness_to_chord
sweep_w = vehicle.wings['main_wing'].sweeps.quarter_chord
mac_w = vehicle.wings['main_wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['main_wing'].chords.root
wt_wing = wing_main.wing_main(S_gross_w,b,lambda_w,t_c_w,sweep_w,Nult,TOW,wt_zf)
vehicle.wings['main_wing'].mass_properties.mass = wt_wing
S_fus = vehicle.fuselages['fuselage'].areas.wetted
diff_p_fus = vehicle.fuselages['fuselage'].differential_pressure
w_fus = vehicle.fuselages['fuselage'].width
h_fus = vehicle.fuselages['fuselage'].heights.maximum
l_fus = vehicle.fuselages['fuselage'].lengths.total
if not vehicle.wings.has_key('horizontal_stabilizer'):
wt_tail_horizontal = 0.0
S_h = 0.0
warnings.warn("There is no Horizontal Tail Weight being added to the Configuration", stacklevel=1)
else:
S_h = vehicle.wings['horizontal_stabilizer'].areas.reference
b_h = vehicle.wings['horizontal_stabilizer'].spans.projected
sweep_h = vehicle.wings['horizontal_stabilizer'].sweeps.quarter_chord
mac_h = vehicle.wings['horizontal_stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['horizontal_stabilizer'].thickness_to_chord
h_tail_exposed = vehicle.wings['horizontal_stabilizer'].areas.exposed / vehicle.wings['horizontal_stabilizer'].areas.wetted
l_w2h = vehicle.wings['horizontal_stabilizer'].origin[0] + vehicle.wings['horizontal_stabilizer'].aerodynamic_center[0] - vehicle.wings['main_wing'].origin[0] - vehicle.wings['main_wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm
wt_tail_horizontal = tail_horizontal(b_h,sweep_h,Nult,S_h,TOW,mac_w,mac_h,l_w2h,t_c_h, h_tail_exposed)
vehicle.wings['horizontal_stabilizer'].mass_properties.mass = wt_tail_horizontal
if not vehicle.wings.has_key('vertical_stabilizer'):
output_3 = Data()
output_3.wt_tail_vertical = 0.0
output_3.wt_rudder = 0.0
S_v = 0.0
warnings.warn("There is no Vertical Tail Weight being added to the Configuration", stacklevel=1)
else:
S_v = vehicle.wings['vertical_stabilizer'].areas.reference
b_v = vehicle.wings['vertical_stabilizer'].spans.projected
t_c_v = vehicle.wings['vertical_stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['vertical_stabilizer'].sweeps.quarter_chord
t_tail = vehicle.wings['vertical_stabilizer'].t_tail
output_3 = tail_vertical(S_v,Nult,b_v,TOW,t_c_v,sweep_v,S_gross_w,t_tail)
vehicle.wings['vertical_stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
# Calculating Empty Weight of Aircraft
wt_landing_gear = landing_gear.landing_gear(TOW)
wt_fuselage = tube(S_fus, diff_p_fus,w_fus,h_fus,l_fus,Nlim,wt_zf,wt_wing,wt_propulsion, wing_c_r)
output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.fuselages['fuselage'].mass_properties.mass = wt_fuselage
# packup outputs
output = payload.payload(TOW, wt_empty, num_pax,wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
output.systems = output_2.wt_systems
output.systems_breakdown = Data()
output.systems_breakdown.control_systems = output_2.wt_flt_ctrl
output.systems_breakdown.apu = output_2.wt_apu
output.systems_breakdown.hydraulics = output_2.wt_hyd_pnu
output.systems_breakdown.instruments = output_2.wt_instruments
output.systems_breakdown.avionics = output_2.wt_avionics
output.systems_breakdown.optionals = output_2.wt_opitems
output.systems_breakdown.electrical = output_2.wt_elec
output.systems_breakdown.air_conditioner = output_2.wt_ac
output.systems_breakdown.furnish = output_2.wt_furnish
#define weights components
try:
landing_gear_component=vehicle.landing_gear #landing gear previously defined
except AttributeError: # landing gear not defined
landing_gear_component=SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.landing_gear=landing_gear_component
control_systems = SUAVE.Components.Physical_Component()
electrical_systems= SUAVE.Components.Physical_Component()
passengers = SUAVE.Components.Physical_Component()
furnishings = SUAVE.Components.Physical_Component()
air_conditioner = SUAVE.Components.Physical_Component()
fuel = SUAVE.Components.Physical_Component()
apu = SUAVE.Components.Physical_Component()
hydraulics = SUAVE.Components.Physical_Component()
optionals = SUAVE.Components.Physical_Component()
rudder = SUAVE.Components.Physical_Component()
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
#assign output weights to objects
landing_gear_component.mass_properties.mass = output.landing_gear
control_systems.mass_properties.mass = output.systems_breakdown.control_systems
electrical_systems.mass_properties.mass = output.systems_breakdown.electrical
passengers.mass_properties.mass = output.pax + output.bag
furnishings.mass_properties.mass = output.systems_breakdown.furnish
avionics.mass_properties.mass = output.systems_breakdown.avionics \
+ output.systems_breakdown.instruments
air_conditioner.mass_properties.mass = output.systems_breakdown.air_conditioner
fuel.mass_properties.mass = output.fuel
apu.mass_properties.mass = output.systems_breakdown.apu
hydraulics.mass_properties.mass = output.systems_breakdown.hydraulics
optionals.mass_properties.mass = output.systems_breakdown.optionals
rudder.mass_properties.mass = output.rudder
#assign components to vehicle
vehicle.control_systems = control_systems
vehicle.electrical_systems = electrical_systems
vehicle.avionics = avionics
vehicle.furnishings = furnishings
vehicle.passenger_weights = passengers
vehicle.air_conditioner = air_conditioner
vehicle.fuel = fuel
vehicle.apu = apu
vehicle.hydraulics = hydraulics
vehicle.optionals = optionals
vehicle.landing_gear = landing_gear_component
vehicle.wings['vertical_stabilizer'].rudder = rudder
return output
