Fuselage.Tail.BackBulk.Material = AircraftPly.copy()
Fuselage.Tail.BackBulk.Material.AreaForceDensity = (0.2 * BaseWeight) / (
4.37 * IN * 2.56 * IN)
Fuselage.Tail.BackBulk.WeightGroup = 'Fuselage'
# miscellaneous
Fuselage.Tail.SkinMat = Ultracote.copy()
Fuselage.Tail.WeightGroup = 'Fuselage'
Fuselage.Tail.StringerMat = AircraftPly.copy()
Fuselage.Tail.StringerMat.LinearForceDensity = 0.01 * LBF / IN
Fuselage.Tail.Align = 0 # Top of section relative to previous section
#------------------------------------------------------------------------------#
# Define which section contains the CG of the aircraft (design CG, will be recalculated)
Fuselage.XcgSection = Fuselage.PayBay
Fuselage.XcgSecFrac = 0.694
# Define the payload shape
##Fuselage.Payload.Face = 'Top'
Fuselage.Payload.Axis = (
1, 0, 0
) # dechellis: Axis that payload is added along to hit weight based on density and dimensions
Fuselage.Payload.Width = 7.25 * IN #changed ACFuselage pretty significantly
Fuselage.Payload.Length = 1.625 * IN #changed ACFuselage pretty significantly
Fuselage.Payload.Material = Steel.copy()
Fuselage.Payload.Weight = 0.0 * LBF
Fuselage.Payload.Position = (0.12, 0.5, 0.55
) # changed ACFuselage (ACPayload class)
# Determine which bulkhead should be set by the horizontal tail
Fuselage.TailBulk = Fuselage.Tail.BackBulk
Fuselage.Nose.AddComponent("Battery", 0.114 * LBF,
(0.25 * IN, 1.5 * IN, 1 * IN), "Right",
(0.2, 0.5, 0.5))
Fuselage.Nose.AddComponent("FuelTank", 0.1 * LBF,
(2.5 * IN, 2 * IN, 1.25 * IN), "Back",
(0.75, 0.5, 0.7))
Fuselage.Nose.AddComponent("NoseWheelServo", 0.04 * LBF,
(.5 * IN, 1 * IN, 1 * IN), "Bottom",
(0.6, 0.2, 0.0))
Fuselage.Nose.AddComponent("Receiver", 0.02 * LBF, (.5 * IN, 1 * IN, 1 * IN),
"Left", (0.6, 0.2, 0.5))
#
# Define which section contains the CG of the aircraft
#
Fuselage.XcgSection = Fuselage.PyldBay
Fuselage.XcgSecFrac = 0.5
#
# Determine which bulkhead should be set by the horizontal tail
#
Fuselage.TailBulk = Fuselage.TailTaper.BackBulk
if __name__ == '__main__':
import pylab as pyl
print 'Nose Weight :', Fuselage.Nose.Weight
print 'PyldBay Weight :', Fuselage.PyldBay.Weight
print 'TailTaper Weight :', Fuselage.TailTaper.Weight
print 'Fuselage Weight :', Fuselage.Weight