## print 'Pay2Tail Wgt w/bulk:', AsUnit(Fuselage.Pay2Tail.Weight,'ozf')
## print 'Pay2Tail CG w/bulk:', AsUnit(Fuselage.Pay2Tail.CG(),'in')
## print 'shiggins weight @', AsUnit(actualTranWeight,'ozf'), ' CG @ ', AsUnit(tranCG,'in')
## print
tailCompWeight = 0.0*OZF # initialize the weight for the components
tailCompCG = 0.0*OZF*Fuselage.Tail.CG().copy()
for component in Fuselage.Tail.param.Components: # loop through nose comps
tailCompWeight += component.Weight
tailCompCG += component.Weight*component.CG()
actualTailWeight = Fuselage.Tail.FrontBulk.Weight + \
Fuselage.Tail.BackBulk.Weight + \
tailCompWeight
tailCG = (1/actualTailWeight)*\
(tailCompCG + \
(Fuselage.Tail.FrontBulk.Weight*Fuselage.Tail.FrontBulk.CG())+\
(Fuselage.Tail.BackBulk.Weight*Fuselage.Tail.BackBulk.CG()))
## print 'Tail Weight w/bulk:', AsUnit(Fuselage.Tail.Weight,'ozf')
## print 'Tail CG w/bulk:', AsUnit(Fuselage.Tail.CG(),'in')
## print 'shiggins weight @', AsUnit(actualTailWeight,'ozf'), ' CG @ ', AsUnit(tailCG,'in')
## print
print 'Fuselage Wgt w/bulk:', AsUnit(Fuselage.Weight,'lbf')
print 'Fuselage CG w/bulk:', AsUnit(Fuselage.CG(),'in')
print
print 'Fuselage MOI :', AsUnit(Fuselage.MOI(),'slug*ft**2')
print 'Fuselage Desired CG :', AsUnit(Fuselage.AircraftCG(),'in')
print
Fuselage.Draw()
pyl.show()
#
# Define the payload shape
#
Fuselage.Payload.Width = 4*IN
Fuselage.Payload.Length = 10*IN
Fuselage.Payload.Face = 'Bottom'
Fuselage.Payload.Material = Steel.copy()
Fuselage.Payload.Weight = 1*LBF
#
# Determine which bulkhead should be set by the horizontal tail
#
Fuselage.TailBulk = Fuselage.Tail.BackBulk
Fuselage.TailBulk.WeightGroup = 'Fuselage'
if __name__ == '__main__':
import pylab as pyl
print 'Nose Weight :', AsUnit( Fuselage.Nose.Weight, 'lbf' )
print 'PyldBay Weight :', AsUnit( Fuselage.PyldBay.Weight, 'ozf' )
print 'TailTaper Weight :', AsUnit( Fuselage.Tail.Weight, 'lbf' )
print 'Fuselage Weight :', AsUnit( Fuselage.Weight, 'lbf' )
print 'Fuselage MOI :', AsUnit( Fuselage.MOI(), 'slug*ft**2' )
print 'Fuselage CG :', AsUnit( Fuselage.CG(), 'in' )
print 'Fuselage Desired CG:', AsUnit( Fuselage.AircraftCG(), 'in' )
Fuselage.Draw()
pyl.show()
#
# Define which section contains the CG of the aircraft
#
Fuselage.XcgSection = Fuselage.PyldBay
Fuselage.XcgSecFrac = 0.3
#
# Determine which bulkhead should be set by the horizontal tail
#
Fuselage.TailBulk = Fuselage.TailTaper.BackBulk
if __name__ == '__main__':
import pylab as pyl
Fuselage.Nose.Weight + Fuselage.Nose.FrontBulk.Weight + Fuselage.Nose.BackBulk.Weight
print 'Composite Section:', Fuselage.Nose.Weight + Fuselage.Nose.FrontBulk.Weight + Fuselage.Nose.BackBulk.Weight
print 'Nose Length :', Fuselage.Nose.Length
print 'PyldBay Weight :', Fuselage.PyldBay.Weight
print 'PyldBay Length :', Fuselage.PyldBay.Length
print 'TailTaper Weight :', Fuselage.TailTaper.Weight
print 'TailTaper Length :', Fuselage.TailTaper.Length
print 'Fuselage Weight :', Fuselage.Weight
print 'Fuselage MOI :', AsUnit(Fuselage.MOI(), "slug*ft**2")
print 'Fuselage CG :', AsUnit(Fuselage.CG(), "in")
print 'Fuselage Desired CG:', AsUnit(Fuselage.AircraftCG(), "in")
Fuselage.Draw()
pyl.show()