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121 | from prism import *
from math import *
# create system object (make sure author is correct... it's used for report)
S = SysModel(name="Mass Fraction Study", type="analysis",
author="C Taylor", programName='Delta V Study')
# set design constants from common Constants values
gc = 32.174 # gravitational conversion factor
# deltaV - assumes linear expenditure of RCS propellant during mission
# add design variables to the system (these variables may be used to
# optimize the system or to create plots)
# design vars have:
# name, value, minVal, maxVal, step, units, description
S.addDesVars(
["Isp",300.0, 250.0, 350.0, 2.0, 'sec', 'Engine Specific Impulse'],
["pcentACS",5.,0.,10.,1.,'','% ACS Propellant of Total'],
["Wpayload", 100., 50., 150., 10., 'lbm', 'Payload Mass'],
["massFraction",0.5,0.3,0.9,0.02, "", "Stage Propellant Mass Fraction"],
["WtPropAxial",200.,100.,500.,25., "lbm", "Burned Axial Propellant"],
)
# now add any Result Variables That might be plotted
# result variables have:
# name, units, description
S.addResultVars(
["sysMass", "lbm", "Total System Mass"],
["GLOW", 'lbm', 'Gross Liftoff Mass','<',600.0],
["deltaV", 'ft/sec', 'Delta V','>',4500.0],
["Itot", 'lbf-sec', 'Total Impulse'],
)
# use base mass object to model system mass items (MassItem)
# (most simple of all mass items)
Fl = MassItem(name="Propellant", type="propellant", mass_lbm=170.0)
Payload = MassItem(name="Payload Weight", type="inert", mass_lbm=100.0)
PropulsionSys = MassItem(name="Propulsion system", type="inert", mass_lbm=0.0)
#===== after they have been created, add the Mass Items to the system object ====
S.addMassItem( [Payload, PropulsionSys, Fl] )
# the following control routine ties together the system components
# with the system design variables
def myControlRoutine(S):
# get current values of design variables
Isp,pcentACS,Wpayload,massFraction,WtPropAxial = \
S("Isp","pcentACS","Wpayload","massFraction","WtPropAxial")
Payload.mass_lbm = Wpayload
fracACS = pcentACS / 100.0
WtPropTotal = WtPropAxial * (1.0 + fracACS)
WpRCS = fracACS * WtPropTotal
WtPropAxial = WtPropTotal - WpRCS
GLOW = Payload.mass_lbm + WtPropTotal/massFraction
PropulsionSys.mass_lbm = GLOW - WtPropTotal - Payload.mass_lbm
Fl.mass_lbm = WtPropTotal
S.reCalc() # recalulates all of the mass items in system
S["sysMass"] = S.mass_lbm
# treat RCS propellant as inert flow for axial engine Isp (i.e. linear over mission)
fracIsp = WtPropAxial / (WtPropAxial + WpRCS)
Winit = S.mass_lbm
Wfinal = S.mass_lbm - WtPropTotal
deltaV = gc * Isp* fracIsp * log( Winit / Wfinal)
S["deltaV"] = deltaV
S["GLOW"] = GLOW
S["Itot"] = WtPropAxial * Isp
# need to tell system the name of the control routine
S.setControlRoutine(myControlRoutine)
S.reCalcItems()
S.saveShortSummary()
make2DPlot(S, sysParam="deltaV", desVar="Isp")
makeSensitivityPlot(S,figureOfMerit="deltaV", desVars=["Isp","pcentACS","Wpayload","WtPropAxial","massFraction"], omitViolPts=0)
make2DParametricPlot(S, sysParam="deltaV", desVar="Isp",
paramVar=["massFraction", 0.1,0.3,0.5,0.7,0.9] ,makeHTML=1, dpi=70,
ptData=None, ptLegend='', logX=0, logY=0)
make2DParametricPlot(S, sysParam="deltaV", desVar="WtPropAxial",
paramVar=["massFraction", 0.1,0.3,0.5,0.7,0.9] ,makeHTML=1, dpi=70,
ptData=None, ptLegend='', logX=0, logY=0)
makeContourPlot(S, sysParam="deltaV", desVars=["Wpayload","massFraction"],
interval = 0.0, maxNumCurves=50, nomNumCurves=12, makeHTML=1,
dpi=70, colorMap="summer")
makeCarpetPlot(S, sysParam="deltaV",
desVarL=[["Isp",250.,300.,350.],["massFraction", 0.1,0.3,0.5,0.7,0.9]],
xResultVar="Itot",
makeHTML=1, dpi=70, linewidth=2, smallLegend=1,
ptData=None, ptLegend='', logX=0, logY=0, titleStr='', yLabelStr='',
haLabel='center', vaLabel='center')
# now save summary of system
S.saveFullSummary()
# Be sure to wrap-up any files
S.close()
|