def test_ForceDensity2(self):
"""
Calculates ForceDensity from AreaDensity and Thickness
"""
Mat = ACMaterial()
Mat.AreaDensity = LBM/IN**2
Mat.Thickness = IN
ForceDensity = (LBM*g/IN**3).asNumber(LBF/IN**3)
self.assertAlmostEqual(Mat.ForceDensity.asNumber(LBF/IN**3), ForceDensity, 5,
"Filed to calculate ForceDensity from AreaDensity and Thickness")
###############################################################################
# Fuselage Materials
###############################################################################
# Bulkhead Truss
# 1/8 inch thick with 75% material cut out
cutout = 0.9
ACTrussBH = ACMaterial()
ACTrussBH.Thickness = 0.25 * IN
ACTrussBH.ForceDensity = Balsa.ForceDensity * (1 - cutout)
# Composite Plate (Composite Plate + monokote)
# 1/4 inch thick Divinicel Foam with 2 ply of Composite
ACNoseComp = ACMaterial()
ACNoseComp.AreaDensity = DivinicelFD * 0.25 * IN / g + 2 * ZylonCompAD
# Section Truss (truss structure + monokote)
# 1/8 inch thick with 80% material cut out
cutout = 0.8
ACTrussSkin = ACMaterial()
ACTrussSkin.AreaDensity = Balsa.ForceDensity * (
1 - cutout) * 0.25 * IN / g + Monokote.AreaDensity
# Bulkhead plywood
# 1/8 inch thick with 75% material cut out
cutout = 0.75
ACPlyBH = ACMaterial()
ACPlyBH.Thickness = 0.125 * IN
ACPlyBH.ForceDensity = ACPly.ForceDensity * (1 - cutout)
ACPly = AircraftPly.copy()
Basswood = Basswood.copy()
Monokote = Monokote.copy()
# Bulkhead plywood
# 1/8 inch thick with 75% material cut out
cutout = 0.75
ACPlyBH = ACMaterial()
ACPlyBH.Thickness = 0.125 * IN
ACPlyBH.ForceDensity = ACPly.ForceDensity * (1 - cutout)
# Section plywood (truss structure + monokote)
# 1/8 inch thick with 80% material cut out
cutout = 0.8
ACPlySkin = ACMaterial()
ACPlySkin.AreaDensity = ACPly.ForceDensity * (
1 - cutout) * 0.125 * IN / g + Monokote.AreaDensity
# Stringer material from basswood (w=0.25 in , t=0.25 in)
w = 0.25 * IN
t = 0.25 * IN
BassStringer = ACMaterial()
BassStringer.LinearForceDensity = Basswood.ForceDensity * w * t
Fuselage = ACFuselage()
#
# Create the sections of the fuselage
#
Fuselage.AddSection('Nose', 6 * IN, 1)
Fuselage.AddSection('PyldBay', 11 * IN, 1)
Fuselage.AddSection('TailTaper')