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Sample Case	PRISM v1.1.7
by: Charlie Taylor	May 05, 2018

PRIOR TO OPTIMIZATION
PRISM System: Sample Case mass = 137.036 lbm type = liquid ====================================== name value minimum maximum Pc 500 350 650 Chamber Pressure (psia) PHe 8000 6000 10000 Helium MEOP (psia) WtPropBurned 100 50 200 Burned Propellant Mass (lbm) eps 10 5 20 Nozzle Area Ratio pcentBell 70 60 90 Nozzle Percent Bell Figure of Merit = 4745.53 = Ideal Delta V, ft/sec (deltaV) ====================================== ======================================

PRIOR TO OPTIMIZATION

PRISM System: Sample Case
                mass =      137.036 lbm
                type = liquid
======================================
      name         value        minimum   maximum
        Pc          500          350          650 Chamber Pressure  (psia)
       PHe         8000         6000        10000 Helium MEOP  (psia)
WtPropBurned          100           50          200 Burned Propellant Mass  (lbm)
       eps           10            5           20 Nozzle Area Ratio
 pcentBell           70           60           90 Nozzle Percent Bell
 Figure of Merit = 4745.53 = Ideal Delta V, ft/sec (deltaV)
======================================
======================================

AFTER OPTIMIZATION
PRISM System: Sample Case mass = 149.988 lbm type = liquid ====================================== name value minimum maximum Pc 543.721 350 650 Chamber Pressure (psia) PHe 10000 6000 10000 Helium MEOP (psia) WtPropBurned 110.761 50 200 Burned Propellant Mass (lbm) eps 12.1906 5 20 Nozzle Area Ratio pcentBell 67.8192 60 90 Nozzle Percent Bell Figure of Merit = 5124.45 = Ideal Delta V, ft/sec (deltaV) ====================================== ======================================

AFTER OPTIMIZATION

PRISM System: Sample Case
                mass =      149.988 lbm
                type = liquid
======================================
      name         value        minimum   maximum
        Pc      543.721          350          650 Chamber Pressure  (psia)
       PHe        10000         6000        10000 Helium MEOP  (psia)
WtPropBurned      110.761           50          200 Burned Propellant Mass  (lbm)
       eps      12.1906            5           20 Nozzle Area Ratio
 pcentBell      67.8192           60           90 Nozzle Percent Bell
 Figure of Merit = 5124.45 = Ideal Delta V, ft/sec (deltaV)
======================================
======================================

Mass Summary
System: Sample Case	149.988	lbm	Total
Name	Mass	Units	Type
INERT
ACS Engines	1.882	lbm	inert
Axial Engine	12.368	lbm	inert
Fuel Tank	5.762	lbm	inert
Helium Tank	10.757	lbm	inert
Oxidizer Tank	6.008	lbm	inert
PRESSURANT
pressurant helium	1.330	lbm	pressurant
PROPELLANT
Monomethyl Hydrazine	40.756	lbm	propellant
Nitrogen Tetroxide	71.124	lbm	propellant

Design Variables (nominal values)
Name	Value	Units	Description
eps	12.1906		Nozzle Area Ratio
Pc	543.721	psia	Chamber Pressure (psia)
pcentBell	67.8192		Nozzle Percent Bell
PHe	10000	psia	Helium MEOP (psia)
WtPropBurned	110.761	lbm	Burned Propellant Mass (lbm)

System Sensitivity

Design Variables (nominal values)
Name	Value	Units	Description
eps	12.1906		Nozzle Area Ratio
Pc	543.721	psia	Chamber Pressure (psia)
pcentBell	67.8192		Nozzle Percent Bell
PHe	10000	psia	Helium MEOP (psia)
WtPropBurned	110.761	lbm	Burned Propellant Mass (lbm)

Result Variables
Name	Value	Units	Description	Constrain	Limit
deltaV	5124.45	ft/sec	Ideal Delta V (ft/sec)		---
Dexit	7.14565	in	Nozzle Diameter (in)		<10
Itot	30140.1	lbf-sec	Total Impulse (lbf-sec)		---
Lstage	65	in	Stage Length (in)		<65
sysMass	149.988	lbm	Total System Mass (lbm)		---

Design Variables (nominal values)
Name	Value	Units	Description
pcentBell	67.8192		Nozzle Percent Bell
PHe	10000	psia	Helium MEOP (psia)
WtPropBurned	110.761	lbm	Burned Propellant Mass (lbm)

Design Variable Summary

Design Variables (nominal values)
Name	Value	Units	Description
eps	12.1906		Nozzle Area Ratio
Pc	543.721	psia	Chamber Pressure (psia)
pcentBell	67.8192		Nozzle Percent Bell
PHe	10000	psia	Helium MEOP (psia)
WtPropBurned	110.761	lbm	Burned Propellant Mass (lbm)

Result Variables
Name	Value	Units	Description	Constrain	Limit
deltaV	5124.45	ft/sec	Ideal Delta V (ft/sec)		---
Dexit	7.14565	in	Nozzle Diameter (in)		<10
Itot	30140.1	lbf-sec	Total Impulse (lbf-sec)		---
Lstage	65	in	Stage Length (in)		<65
sysMass	149.988	lbm	Total System Mass (lbm)		---

Bipropellant Engine: ACS Engines

mass = 1.882 lbm type = inert

Propellants : N2O4 / MMH

NASA CEA Code for ODE performance

Physical Weight Model

Injector Material is SS

Nozzle Material is Cb103

Bell Nozzle with Percent Bell = 80

Mass is for 4 engines total

==== INPUT ====
Name	Value	Units
Fvac	= 40	lbf
Pc	= 543.7	psia
eps	= 10
%Bell	= 80.00	%
mr	= 1
CR	= 2.5
xlnOverLcham	= 0.9
LoverDt	= 2
LchamMin	= 1.000	in
cxwInj	= 1
cxwValves	= 0.33
cxw	= 1
etaERE	= 0.94

==== OUTPUT ====
Name	Value	Units
Isp	= 259.609	sec
Cstar	= 5055.6	ft/sec
etaBL	= 0.985876
etaDiv	= 0.987664
etaKin	= 1
etaNoz	= 0.973714
effIsp	= 0.915291
IspODE	= 283.635	sec
CstarODE	= 5378.3	ft/sec
Tc	= 4250.3	degR
PcFace	= 569.844	psia
Pexit	= 5.63542	psia
wdotTot	= 0.154078	lbm/sec
wdotOx	= 0.0770391	lbm/sec
wdotFl	= 0.0770391	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 1.47936	cuin/sec
volDotFl	= 2.44068	cuin/sec
DFlow	= 0.322	in
At	= 0.044528	sqin
Dt	= 0.238	in
Dcham	= 0.376	in
Dexit	= 0.753	in
Lcham	= 1.000	in
xlc	= 0.100	in
xln	= 0.900	in
Lnoz	= 0.769	in
Lengine	= 2.145	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 0.014	lbm
WtChamber	= 0.007	lbm
WtInj	= 0.014	lbm
WtAcoustic	= 0.084	lbm
WtValves(2)	= 0.332	lbm
WtMisc	= 0.020	lbm
wt/Engine	= 0.471	lbm
F/W	= 84.998	lbf/lbm

Solenoid Valve: biprop valves

mass = 0.332 lbm type = inert

Based on Solenoid Valve Experience

Mass is for 2 valves total

==== INPUT ====
Name	Value	Units
cuInchPerSec	= 2.44068	cuin/sec
cxw	= 0.330

==== OUTPUT ====
Name	Value	Units
basemass	= 0.502	lbm

Bipropellant Engine: Axial Engine

mass = 12.368 lbm type = inert

Propellants : N2O4 / MMH

NASA CEA Code for ODE performance

Physical Weight Model

Injector Material is SS

Nozzle Material is Cb103

Bell Nozzle with Percent Bell = 67.8192

==== INPUT ====
Name	Value	Units
Fvac	= 3000	lbf
Pc	= 543.7	psia
eps	= 12.1906
%Bell	= 67.82	%
mr	= 1.8
CR	= 2.5
xlnOverLcham	= 0.9
LoverDt	= 2
LchamMin	= 2.000	in
cxwInj	= 1
cxwValves	= 0.33
cxw	= 1
etaERE	= 0.955

==== OUTPUT ====
Name	Value	Units
Isp	= 286.439	sec
Cstar	= 5494.7	ft/sec
etaBL	= 0.990149
etaDiv	= 0.977201
etaKin	= 0.983097
etaNoz	= 0.95122
effIsp	= 0.908415
IspODE	= 315.318	sec
CstarODE	= 5753.6	ft/sec
Tc	= 5821.8	degR
PcFace	= 569.844	psia
Pexit	= 5.00075	psia
wdotTot	= 10.4734	lbm/sec
wdotOx	= 6.73292	lbm/sec
wdotFl	= 3.74051	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 129.291	cuin/sec
volDotFl	= 118.503	cuin/sec
DFlow	= 2.342	in
At	= 3.28964	sqin
Dt	= 2.047	in
Dcham	= 3.236	in
Dexit	= 7.146	in
Lcham	= 4.093	in
xlc	= 0.409	in
xln	= 3.684	in
Lnoz	= 6.453	in
Lengine	= 13.782	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.071	in
thkNoz	= 0.030	in
WtNoz	= 1.474	lbm
WtChamber	= 0.787	lbm
WtInj	= 4.179	lbm
WtAcoustic	= 2.990	lbm
WtValves(2)	= 1.867	lbm
WtMisc	= 1.070	lbm
F/W	= 242.560	lbf/lbm

Solenoid Valve: biprop valves

mass = 1.867 lbm type = inert

Based on Solenoid Valve Experience

Mass is for 2 valves total

==== INPUT ====
Name	Value	Units
cuInchPerSec	= 129.291	cuin/sec
cxw	= 0.330

==== OUTPUT ====
Name	Value	Units
basemass	= 2.828	lbm

Cylindrical/Spherical/Elliptical Tank: Fuel Tank

mass = 5.762 lbm type = inert

Composite Tank Algorithm

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 1332.95	cuin
vfreeTotal	= 1332.95	cuin
ell	= 1.6
rcyltd	= 1.3641
ptank	= 856.838	psia
sf	= 1.5
cxw	= 1.5
ithcyl	= 1
kacqui	= 6	capillary device
inpex	= 1
expefi	= 0.99
tblad	= 0.000	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.098	lbm/cuin
tliner	= 0.030	in
rholiner	= 0.098	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 4.951	in
dinsid	= 9.901	in
OR	= 5.000	in
OD	= 10.000	in
OH	= 19.794	in
hinsid	= 19.694	in
SAinsid	= 654.772	sqin
cyl	= 13.506	in
wacqui	= 1.101	lbm
vacqui	= 11.2379	cuin
dpacq	= 0	psig
pullag	= 856.838	psia
vresid	= 13.3295	cuin
vtank	= 1357.52	cuin
tming	= 0.008	in
thkcyl	= 0.019	in
thkend	= 0.020	in
thkBladOut	= 0.000	in
wliner	= 2.025	lbm
wtank(+liner)	= 2.740	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 201864	lbf-in/lbm
Pburst(est.)	= 1285.3	psia
PburstVoverW	= 302796	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Helium Tank

mass = 10.757 lbm type = inert

Composite Tank Algorithm

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 443.102	cuin
vfreeTotal	= 443.102	cuin
ell	= 1.6
rcyltd	= 0.334369
ptank	= 10000	psia
sf	= 2
cxw	= 1.3746
ithcyl	= 1
kacqui	= 0	no acq. device
inpex	= 0
expefi	= 0.99
tblad	= 0.030	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.28	lbm/cuin
tliner	= 0.065	in
rholiner	= 0.101	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 4.563	in
dinsid	= 9.126	in
OR	= 5.000	in
OD	= 10.000	in
OH	= 9.763	in
hinsid	= 8.755	in
SAinsid	= 286.859	sqin
cyl	= 3.052	in
wacqui	= 0.000	lbm
vacqui	= 0	cuin
dpacq	= 0	psig
pullag	= 10000	psia
vresid	= 5.25187	cuin
vtank	= 448.354	cuin
tming	= 0.008	in
thkcyl	= 0.342	in
thkend	= 0.409	in
thkBladOut	= 0.030	in
wliner	= 2.085	lbm
wtank(+liner)	= 7.826	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 416800	lbf-in/lbm
Pburst(est.)	= 20000.0	psia
PburstVoverW	= 833601	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Oxidizer Tank

mass = 6.008 lbm type = inert

Composite Tank Algorithm

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 1417.88	cuin
vfreeTotal	= 1417.88	cuin
ell	= 1.6
rcyltd	= 1.47687
ptank	= 856.838	psia
sf	= 1.5
cxw	= 1.5
ithcyl	= 1
kacqui	= 6	capillary device
inpex	= 1
expefi	= 0.99
tblad	= 0.000	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.098	lbm/cuin
tliner	= 0.030	in
rholiner	= 0.098	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 4.951	in
dinsid	= 9.901	in
OR	= 5.000	in
OD	= 10.000	in
OH	= 20.911	in
hinsid	= 20.811	in
SAinsid	= 689.502	sqin
cyl	= 14.623	in
wacqui	= 1.119	lbm
vacqui	= 11.4234	cuin
dpacq	= 0	psig
pullag	= 856.838	psia
vresid	= 14.1788	cuin
vtank	= 1443.49	cuin
tming	= 0.008	in
thkcyl	= 0.019	in
thkend	= 0.020	in
thkBladOut	= 0.000	in
wliner	= 2.127	lbm
wtank(+liner)	= 2.886	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 205860	lbf-in/lbm
Pburst(est.)	= 1285.3	psia
PburstVoverW	= 308790	lbf-in/lbm

Helium Pressurant: pressurant helium

mass = 1.330 lbm type = pressurant

Polytropic Heat Transfer

Heated Helium (Heat Exchanger between source and tank

==== INPUT ====
Name	Value	Units
VpropTnk	= 2750.84	cuin
PHeTnk	= 10000	psia
PpropNom	= 856.838	psia
PfinHeOvPnom	= 1.1
tAction	= 10.0467	sec
TminR	= 500.0	degR
TmaxR	= 550.0	degR
tPolyCorr	= 750	sec
gamPolyCorr	= 1.4
gamLimPolyCorr	= 1
THeTnkHX	= 490.0	degR

==== OUTPUT ====
Name	Value	Units
WHeTotal	= 1.330	lbm
WtHeResid	= 0.322	lbm
WHeExpended	= 1.008	lbm
volHeTotal	= 443.102	cuin
wdotHe	= 0.100312	lbm/sec
compressInit	= 1.31102
PinitCold	= 9113.27	psia
densInitBot	= 5.18647	lbm/cuft
densFinalBot	= 1.25634	lbm/cuft
densFinalProp	= 0.633074	lbm/cuft
gammaPoly	= 1.39598
TfinalPropHe	= 490.0	degR
TfinalHeBot	= 262.7	degR
PfinalHeBot	= 942.5	psia

Incompressible Liquid: Monomethyl Hydrazine

mass = 40.756 lbm type = propellant

MMH Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 550.0	degR
P	= 14.7	psia
Tref	= 530.0	degR
Tnbp	= 650.0	degR
Tcrit	= 1053.0	degR
Pref	= 14.7	psia
Pcrit	= 1195.0	psia
WtMol	= 46.07
RhoRef	= 0.0315646	lb/cuin
ViscRefFT	= 0.0005304	lb/ft-sec
CondRefFTHR	= 0.143294	BTU/ft-hr-R
CpRef	= 0.7	BTU/lbm degR
Burned Axial	= 37.580	lbm
Burned RCS	= 2.769	lbm
Residual	= 0.408	lbm

==== OUTPUT ====
Name	Value	Units
D	= 53.892	lbm/cuft
rho	= 0.0311875	lbm/cuin (0.863267 SG)
Cp	= 0.7	BTU/lbm degR
Visc	= 53.04	[1.0E5 * lb/ft-sec]
Cond	= 0.143294	BTU/ft-hr-R
SurfTen	= 0.000184989	lbf/in
phase	= LIQUID
Pvap	= 1.54936	psia
Vcuft	= 0.75626	cuft
Volume	= 1306.82	cuin

Incompressible Liquid: Nitrogen Tetroxide

mass = 71.124 lbm type = propellant

N2O4 Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 550.0	degR
P	= 30.0	psia
Tref	= 530.0	degR
Tnbp	= 529.8	degR
Tcrit	= 776.5	degR
Pref	= 14.7	psia
Pcrit	= 1440.0	psia
WtMol	= 92.016
RhoRef	= 0.0520758	lb/cuin
ViscRefFT	= 0.0002664	lb/ft-sec
CondRefFTHR	= 0.0759456	BTU/ft-hr-R
CpRef	= 0.378	BTU/lbm degR
Burned Axial	= 67.644	lbm
Burned RCS	= 2.769	lbm
Residual	= 0.711	lbm

==== OUTPUT ====
Name	Value	Units
D	= 88.413	lbm/cuft
rho	= 0.0511652	lbm/cuin (1.41625 SG)
Cp	= 0.378	BTU/lbm degR
Visc	= 26.64	[1.0E5 * lb/ft-sec]
Cond	= 0.0759456	BTU/ft-hr-R
SurfTen	= 0.000137202	lbf/in
phase	= LIQUID
Pvap	= 25.8289	psia
Vcuft	= 0.804445	cuft
Volume	= 1390.08	cuin

(PRISM) PaRametrIc System Model
PRISM v1.1.7
contact: C. Taylor, cet@appliedpython.com