#from os import environ as _environ; _environ["scalar_off"] = "off" from scalar.units import FT, IN, ARCDEG, LBF, SEC, OZF, OZM from scalar.units import AsUnit from Aerothon.ACAircraft import ACTailAircraft from Aerothon.ACWingWeight import ACRibWing from Aerothon.DefaultMaterialsLibrary import Basswood, Steel, Balsa, Aluminum, Ultracote, CarbonBar from Adv2020Aircraft.Aircraft_Core_Design.Fuselage import Fuselage from Adv2020Aircraft.Aircraft_Core_Design.Propulsion import Propulsion from Adv2020Aircraft.Aircraft_Core_Design.Wing import Wing import pylab as pyl # # Create the Aircraft from the ACTailAircraft class Aircraft = ACTailAircraft() Aircraft.name = 'AdvAeroCats_2020' # # Assign the already generated parts Aircraft.SetFuselage(Fuselage) Aircraft.SetPropulsion(Propulsion) Aircraft.SetWing(Wing) # # Position the wing on the top of the fuselage Aircraft.WingFuseFrac = 0.3 Aircraft.Wing.i = 0 * ARCDEG # # Aircraft Properties # Total weight is going to change Aircraft.TotalWeight = 54 * LBF # Engine align Aircraft.EngineAlign = 0
#sys.path.append(os.path.join(BAPDir,'Propulsion')) from Propulsion.propulsion_carterSto import Propulsion # propulsion model #sys.path.append(os.path.join(BAPDir,r'Structures\Fuselage')) from Structures.Fuselage.fuselage_carter2 import Fuselage # fuselage model timeStart = time.time() # start clock (to time simulation) #==============================================================================# # AIRCRAFT MODEL #==============================================================================# # Create the Aircraft from the ACTailAircraft class imported above from Aerothon Aircraft = ACTailAircraft() #Aircraft = ACTLenAircraft() Aircraft.name = 'Regular 2019: The Fellowship of the Wing' # Assign parts we imported above (generated outside of this script) to aircraft Aircraft.SetWing(Wing) Aircraft.SetFuselage(Fuselage) Aircraft.SetPropulsion(Propulsion) # Wing alignment Aircraft.WingFuseFrac = 0 # 0.0 @ bottom of fuselage; 1.0 @ top of fuselage Aircraft.Wing.i = 0 * ARCDEG # induced angle of attack, wing incidence #Aircraft.Wing.X[0] = 20*IN # Engine alignment (height) Aircraft.EngineAlign = 0.72 #this doesnt seem to be doing anything # Aircraft Properties
from __future__ import division # let 5/2 = 2.5 rather than 2 from Aerothon.scalar.units import M, FT, IN, ARCDEG, RAD, LBF, SEC, KG, SLUG from Aerothon.scalar.units import AsUnit from Aerothon.ACAircraft import ACTailAircraft from Aerothon.ACWingWeight import ACSolidWing from Aerothon.DefaultMaterialsLibrary import Monokote, PinkFoam, Balsa from Fuselage import Fuselage from Propulsion import Propulsion from Wing import Wing import pylab as pyl # # Create the Aircraft # Aircraft = ACTailAircraft() Aircraft.name = 'Tutorial Aircraft' # # Assign the already generated parts # Aircraft.SetFuselage(Fuselage) Aircraft.SetPropulsion(Propulsion) Aircraft.SetWing(Wing) # # Aircraft Properties # Aircraft.TotalWeight = 28 * LBF Aircraft.TippingAngle = 10 * ARCDEG Aircraft.RotationAngle = 10 * ARCDEG
#sys.path.append(os.path.join(BAPDir,'Propulsion')) from Propulsion.propulsion import Propulsion # propulsion model #sys.path.append(os.path.join(BAPDir,r'Structures\Fuselage')) from Structures.Fuselage.fuselage import Fuselage # fuselage model timeStart = time.time() # start clock (to time simulation) #==============================================================================# # AIRCRAFT MODEL #==============================================================================# # Create the Aircraft from the ACTailAircraft class imported above from Aerothon Aircraft = ACTailAircraft() #Aircraft = ACTLenAircraft() Aircraft.name = 'BAP_AerocatsReg_2017' # Assign parts we imported above (generated outside of this script) to aircraft Aircraft.SetWing(Wing) Aircraft.SetFuselage(Fuselage) Aircraft.SetPropulsion(Propulsion) # Wing alignment Aircraft.WingFuseFrac = 0.44 # 0.0 @ bottom of fuselage; 1.0 @ top of fuselage Aircraft.Wing.i = 0 * ARCDEG # induced angle of attack, wing incidence # Engine alignment (height) Aircraft.EngineAlign = 0.72 # Aircraft Properties EmptyWeight = 17 * LBF # dechellis: estimated airframe weight