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.TailBulk.WeightGroup = 'Fuselage'
#==============================================================================#
# VISUALIZATION & RESULTS
#==============================================================================#
if __name__ == '__main__':
import pylab as pyl
noseCompWeight = 0.0 * OZF # initialize the weight for the components
noseCompCG = 0.0 * OZF * Fuselage.Nose.CG().copy()
for component in Fuselage.Nose.param.Components: # loop through nose comps
noseCompWeight += component.Weight
noseCompCG += component.Weight * component.CG()
actualNoseWeight = Fuselage.Nose.FrontBulk.Weight + \
Fuselage.Nose.BackBulk.Weight + \
noseCompWeight
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
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()