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.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()
VTail2.WingWeight.AddSpar("TrailingEdge2", 1 / 16 * IN, 13 / 8 * IN,
(0.25, 1), 1.0, False)
VTail2.WingWeight.TrailingEdge2.SparMat = Balsa.copy(
) #.LinearForceDensity = .008*LBF/(1*IN)
VTail2.WingWeight.TrailingEdge2.Position = (0.915, -0.2)
VTail2.WingWeight.TrailingEdge2.ScaleToWing = [False, False]
VTail2.WingWeight.TrailingEdge2.WeightGroup = "VTail2"
###############################################################################
#
# Landing Gear
#
###############################################################################
Aluminum = Aluminum.copy()
Steel = Steel.copy()
MainGear = Aircraft.MainGear
MainGear.Theta = 89.9 * ARCDEG
#MainGear.GearHeight = 3 * IN
MainGear.StrutL = 4 * IN
MainGear.StrutW = 0.2 * IN
MainGear.StrutH = 0.1 * IN
MainGear.WheelDiam = 4 * IN
MainGear.X[1] = 2.0 * IN
MainGear.Strut.Weight = 0.1 * LBF #math.pi*(0.125/2*IN)**2*12*IN*Aluminum.ForceDensity #1/8 inch diameter steel, l=12in
MainGear.Strut.WeightGroup = "LandingGear"
MainGear.Wheel.Weight = 0.1 * LBF
MainGear.Wheel.WeightGroup = "LandingGear"
NoseGear = Aircraft.NoseGear
NoseGear.StrutW = 0.1 * IN