# -> AddSection('NAME',sectionLength,alignment(-1=bot, 0=center, 1=top, None=@CG)
Fuselage.AddSection('Nose', 9.63 * IN, 1)
Fuselage.AddSection('PayBay', 9 * IN, 1)
Fuselage.AddSection('Pay2Tail', 25.48 * IN, 0)
Fuselage.AddSection('Tail', 22.53 * IN, 0)
BaseWeight = 24 * OZF # Weight in OZF that is multiplied in the force densities
# SECTION 1: Nose section only -------------------------------------------------#
#### SHIFT ALL X POSITIONS BY 7.03125in (Dist from payload CG to front of fuse)
# SPH 12/1/2015: from 151130 CAD target weight @ 15.5oz CG @ 1.14125in
# in SolidWorks relative to payload CG (5.89,0,-0.12)
# front bulkhead definition
Fuselage.Nose.FrontBulk.Width = 2.0 * IN
Fuselage.Nose.FrontBulk.Height = 2.0 * IN
Fuselage.Nose.FrontBulk.Material = AircraftPly.copy()
Fuselage.Nose.FrontBulk.Material.AreaForceDensity = (0.01 * BaseWeight) / (
2.0 * IN * 2.0 * IN)
Fuselage.Nose.FrontBulk.WeightGroup = 'Fuselage'
# rear bulkhead definition
Fuselage.Nose.BackBulk.Width = 10.55 * IN
Fuselage.Nose.BackBulk.Height = 11.5 * IN
Fuselage.Nose.BackBulk.Material = AircraftPly.copy()
Fuselage.Nose.BackBulk.Material.AreaForceDensity = (0.03 * BaseWeight) / (
10.55 * IN * 11.5 * IN)
Fuselage.Nose.BackBulk.WeightGroup = 'Fuselage'
# miscellaneous
Fuselage.Nose.SkinMat = Ultracote.copy()
Fuselage.Nose.StringerMat = Basswood.copy()
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import IN, LBF, SLUG, FT from Aerothon.ACBase import g from Aerothon.ACMaterial import ACMaterial from Aerothon.DefaultMaterialsLibrary import Steel, AircraftPly, Basswood, Monokote, Balsa # # Materials Set-up # Steel = Steel.copy() ACPly = AircraftPly.copy() Basswood = Basswood.copy() Monokote = Monokote.copy() Balsa = Balsa.copy() DivinicelFD = 0.00137 * LBF / IN**3 Fibre2Resin = 3 / 2 EpoxDens = 0.017316 * LBF / IN**3 XylonDens = 0.056 * LBF / IN**3 CompDens = 0.0404 * LBF / IN**3 ZylonCompFD = CompDens PlyThickness = 1 / 100 * IN / g ZylonCompAD = CompDens * PlyThickness ############################################################################### # Fuselage Materials ############################################################################### # Bulkhead Truss # 1/8 inch thick with 75% material cut out cutout = 0.9