PRISM (PaRametrIc System Model)

PRISM (PaRametrIc System Model)
NTO/MMH He, PMD, Cb	PRISM v1.1.7
by: N. Orbit	May 05, 2018

Mass Summary
System: NTO/MMH He, PMD, Cb	822.464	lbm	Total
Name	Mass	Units	Type
INERT
Axial Engine	8.777	lbm	inert
Axial Engine Fuel Line	1.257	lbm	inert
Axial Engine Ox Line	1.292	lbm	inert
Fuel Tank	19.309	lbm	inert
Helium Tank	22.661	lbm	inert
Oxidizer Tank	20.001	lbm	inert
SMX misc.	18.410	lbm	inert
Stage External Shell	19.994	lbm	inert
PRESSURANT
pressurant helium	3.692	lbm	pressurant
PROPELLANT
Monomethyl Hydrazine	257.117	lbm	propellant
Nitrogen Tetroxide	449.954	lbm	propellant

Design Variables (nominal values)
Name	Value	Units	Description
eps	40		Axial Nozzle Area Ratio
Ltanks	34.5	in	Tank Length (in)
MR	1.75		Engine Mixture Ratio
Pc	250	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	10000	psia	Helium Tank Pressure (psia)
WtPropAxial	700	lbm	Usable Propellant (lbm)

Design Variables (nominal values)
Name	Value	Units	Description
eps	40		Axial Nozzle Area Ratio
Ltanks	34.5	in	Tank Length (in)
MR	1.75		Engine Mixture Ratio
Pc	250	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	10000	psia	Helium Tank Pressure (psia)
WtPropAxial	700	lbm	Usable Propellant (lbm)

Design Variable Summary

Design Variables (nominal values)
Name	Value	Units	Description
eps	40		Axial Nozzle Area Ratio
Ltanks	34.5	in	Tank Length (in)
MR	1.75		Engine Mixture Ratio
Pc	250	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	10000	psia	Helium Tank Pressure (psia)
WtPropAxial	700	lbm	Usable Propellant (lbm)

Result Variables
Name	Value	Units	Description	Constrain	Limit
burnTime	393.896	sec	Total Burn Time (sec)		---
DiamPkg	32.9767	in	Packaged Diameter (in)		<33
geesBO	3.79666	gees	Burnout Gees (gees)		---
Isp	303.863	sec	Engine Specific Impulse (sec)		---
Itot	212704	lbf-sec	Total Impulse (lbf-sec)		---
Lengine	10.4252	in	Axial Engine Length (in)		---
LenPkg	36	in	Packaged Length (in)		<36
massFrac	0.859943		Stage Propellant Mass Fraction		---
massFracUsable	0.851343		Usable Propellant Mass Fraction		---
sysMass	822.23	lbm	Total System Mass (lbm)		---
Winert	111.468	lbm	System Inert Mass (lbm)		---
WpropTotal	707.071	lbm	Total Propellant Mass (lbm)		---

Bipropellant Engine: Axial Engine

mass = 8.777 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 2 engines total

==== INPUT ====
Name	Value	Units
Fvac	= 270	lbf
Pc	= 250.0	psia
eps	= 40
%Bell	= 80.00	%
mr	= 1.75
CR	= 2.5
xlnOverLcham	= 0.5
LoverDt	= 2
LchamMin	= 2.000	in
cxwInj	= 1
cxwValves	= 1
cxw	= 1.27
etaERE	= 0.97

==== OUTPUT ====
Name	Value	Units
Isp	= 303.863	sec
Cstar	= 5557.0	ft/sec
etaBL	= 0.979854
etaDiv	= 0.991821
etaKin	= 0.966689
etaNoz	= 0.939467
effIsp	= 0.911283
IspODE	= 333.445	sec
CstarODE	= 5728.9	ft/sec
Tc	= 5667.2	degR
PcFace	= 262.011	psia
Pexit	= 0.467376	psia
wdotTot	= 0.888559	lbm/sec
wdotOx	= 0.565446	lbm/sec
wdotFl	= 0.323112	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 10.8581	cuin/sec
volDotFl	= 10.2365	cuin/sec
DFlow	= 0.679	in
At	= 0.613879	sqin
Dt	= 0.884	in
Dcham	= 1.398	in
Dexit	= 5.591	in
Lcham	= 2.000	in
xlc	= 1.000	in
xln	= 1.000	in
Lnoz	= 7.027	in
Lengine	= 10.425	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 0.567	lbm
WtChamber	= 0.050	lbm
WtInj	= 0.727	lbm
WtAcoustic	= 0.534	lbm
WtValves(2)	= 1.889	lbm
WtMisc	= 0.090	lbm
wt/Engine	= 4.388	lbm
F/W	= 61.526	lbf/lbm

Solenoid Valve: biprop valves

mass = 1.889 lbm type = inert

Based on Solenoid Valve Experience

Mass is for 2 valves total

==== INPUT ====
Name	Value	Units
cuInchPerSec	= 10.8581	cuin/sec
cxw	= 1.000

==== OUTPUT ====
Name	Value	Units
basemass	= 0.945	lbm

Liquid Line: Axial Engine Fuel Line

mass = 1.257 lbm type = inert

fluid : MMH

Structural Material : Ti

Allow Non-Standard wall thickness

Mass is for 2 lines total

==== INPUT ====
Name	Value	Units
wdot	= 0.646225	lbm/sec
velFPS	= 10	ft/sec
len_inches	= 24	in
Kfactors	= 10	vel heads
roughness	= 5e-06	in
thkInp	= 0	in
pLine	= 439.234	psia
sf	= 4
cxw	= 3.5
# Lines	= 2

==== OUTPUT ====
Name	Value	Units
dpLine	= 6.55	psig
ReNum	= 3.994068E+04
thkLine	= 0.030	in
rinsid	= 0.233	in
dinsid	= 0.466	in
doutside	= 0.526	in
volLine	= 4.09461	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi
tming	= 0.030	in
fluid rho	= 0.0315646	lbm/cuin
fluid visc	= 53.04	1.0E5 * lb/ft-sec
wt/Line	= 0.628	lbm

Liquid Line: Axial Engine Ox Line

mass = 1.292 lbm type = inert

fluid : N2O4

Structural Material : Ti

Allow Non-Standard wall thickness

Mass is for 2 lines total

==== INPUT ====
Name	Value	Units
wdot	= 1.13089	lbm/sec
velFPS	= 10	ft/sec
len_inches	= 24	in
Kfactors	= 10	vel heads
roughness	= 5e-06	in
thkInp	= 0	in
pLine	= 439.234	psia
sf	= 4
cxw	= 3.5
# Lines	= 2

==== OUTPUT ====
Name	Value	Units
dpLine	= 10.52	psig
ReNum	= 1.351206E+05
thkLine	= 0.030	in
rinsid	= 0.240	in
dinsid	= 0.480	in
doutside	= 0.540	in
volLine	= 4.34325	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi
tming	= 0.030	in
fluid rho	= 0.0520758	lbm/cuin
fluid visc	= 26.64	1.0E5 * lb/ft-sec
wt/Line	= 0.646	lbm

Cylindrical/Spherical/Elliptical Tank: Fuel Tank

mass = 19.309 lbm type = inert

Composite Tank Algorithm

kalmod = 0

Mass is for 2 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 4198.82	cuin
vfreeTotal	= 8397.65	cuin
ell	= 1.764
rcyltd	= 2.07225
ptank	= 439.234	psia
sf	= 1.5
cxw	= 1.32
ithcyl	= 1
kacqui	= 6	capillary device
inpex	= 1
expefi	= 0.98
tblad	= 0.000	in
tbond	= 0.000	in
ttrspc	= 0.000	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	= 6.536	in
dinsid	= 13.072	in
OR	= 6.579	in
OD	= 13.159	in
OH	= 34.587	in
hinsid	= 34.500	in
SAinsid	= 1503.305	sqin
cyl	= 27.089	in
wacqui	= 1.577	lbm
vacqui	= 16.0902	cuin
dpacq	= 0	psig
pullag	= 439.234	psia
vresid	= 83.9765	cuin
vtank	= 4298.89	cuin
tming	= 0.035	in
thkcyl	= 0.013	in (use tming)
thkend	= 0.014	in (use tming)
thkBladOut	= 0.000	in
wliner	= 4.584	lbm
wtank(+liner)	= 5.737	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 195580	lbf-in/lbm
Pburst(est.)	= 2104.4	psia
PburstVoverW	= 937048	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Helium Tank

mass = 22.429 lbm type = inert

Composite Tank Algorithm

kalmod = 0

Mass is for 2 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 614.956	cuin
vfreeTotal	= 1229.91	cuin
ell	= 1.764
rcyltd	= 6.5381
ptank	= 10000	psia
sf	= 2
cxw	= 1.1
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	= 2.428	in
dinsid	= 4.856	in
OR	= 2.705	in
OD	= 5.410	in
OH	= 35.125	in
hinsid	= 34.500	in
SAinsid	= 538.218	sqin
cyl	= 31.747	in
wacqui	= 0.000	lbm
vacqui	= 0	cuin
dpacq	= 0	psig
pullag	= 10000	psia
vresid	= 6.93404	cuin
vtank	= 621.89	cuin
tming	= 0.008	in
thkcyl	= 0.182	in
thkend	= 0.217	in
thkBladOut	= 0.030	in
wliner	= 3.636	lbm
wtank(+liner)	= 10.195	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 554544	lbf-in/lbm
Pburst(est.)	= 20000.0	psia
PburstVoverW	= 1.10909e+06	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Oxidizer Tank

mass = 20.000 lbm type = inert

Composite Tank Algorithm

kalmod = 0

Mass is for 2 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 4453.8	cuin
vfreeTotal	= 8907.59	cuin
ell	= 1.764
rcyltd	= 1.99269
ptank	= 439.234	psia
sf	= 1.5
cxw	= 1.32
ithcyl	= 1
kacqui	= 6	capillary device
inpex	= 1
expefi	= 0.98
tblad	= 0.000	in
tbond	= 0.000	in
ttrspc	= 0.000	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	= 6.739	in
dinsid	= 13.479	in
OR	= 6.783	in
OD	= 13.566	in
OH	= 34.588	in
hinsid	= 34.500	in
SAinsid	= 1552.802	sqin
cyl	= 26.859	in
wacqui	= 1.613	lbm
vacqui	= 16.4552	cuin
dpacq	= 0	psig
pullag	= 439.234	psia
vresid	= 89.0759	cuin
vtank	= 4559.33	cuin
tming	= 0.035	in
thkcyl	= 0.014	in (use tming)
thkend	= 0.014	in (use tming)
thkBladOut	= 0.000	in
wliner	= 4.739	lbm
wtank(+liner)	= 5.963	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 200259	lbf-in/lbm
Pburst(est.)	= 2041.0	psia
PburstVoverW	= 930544	lbf-in/lbm

Miscellaneous Mass Items: SMX misc.

mass = 18.410 lbm type = inert

All items are of type: inert

==== INPUT ====
Name	Value	Units
===SORT ORDER===	= Alphabetical
Axial Engine Insulation	= 1.000	lbm
Axial Install	= 0.450	lbm
Axial Transducer	= 0.140	lbm
Cap, Weld - F&D Valves	= 0.050	lbm
Connector, Mech. Sep.	= 0.100	lbm
Electrical Cable Install	= 2.000	lbm
Electrical Install	= 1.000	lbm
Fuel Tank bracket, spacer, sensor	= 2.000	lbm
Fuel Tank Gas Inlet Assembly	= 1.000	lbm
Fuel Tank Outlet Assembly	= 1.000	lbm
Gas Valves (Reg, F&D, Iso, Relief, P Switch)	= 3.000	lbm
GSA Install	= 0.240	lbm
GSA Mount & Assembly	= 2.000	lbm
Ox Tank bracket, spacer, sensor	= 2.000	lbm
Ox Tank Gas Inlet Assembly	= 1.000	lbm
Ox Tank Outlet Assembly	= 1.000	lbm
PSA Install	= 0.340	lbm
Squib, Electrical Sep.	= 0.090	lbm

==== OUTPUT ====
Name	Value	Units
===SORT ORDER===	= Mass
Gas Valves (Reg, F&D, Iso, Relief, P Switch)	= 3.000	lbm
Electrical Cable Install	= 2.000	lbm
Fuel Tank bracket, spacer, sensor	= 2.000	lbm
GSA Mount & Assembly	= 2.000	lbm
Ox Tank bracket, spacer, sensor	= 2.000	lbm
Axial Engine Insulation	= 1.000	lbm
Electrical Install	= 1.000	lbm
Fuel Tank Gas Inlet Assembly	= 1.000	lbm
Fuel Tank Outlet Assembly	= 1.000	lbm
Ox Tank Gas Inlet Assembly	= 1.000	lbm
Ox Tank Outlet Assembly	= 1.000	lbm
Axial Install	= 0.450	lbm
PSA Install	= 0.340	lbm
GSA Install	= 0.240	lbm
Axial Transducer	= 0.140	lbm
Connector, Mech. Sep.	= 0.100	lbm
Squib, Electrical Sep.	= 0.090	lbm
Cap, Weld - F&D Valves	= 0.050	lbm

Shell Structure: Stage External Shell

mass = 19.994 lbm type = inert

Structural Material : grEpox

Flange Material : Al

Total Mass includes two (2) flanges

==== INPUT ====
Name	Value	Units
OD	= 33.000	in
Length	= 36.000	in
thkShell	= 0.080	in
thkFlange	= 0.100	in
widthFlange	= 0.500	in
cxw	= 1.000

==== OUTPUT ====
Name	Value	Units
rho Shell	= 0.0637	lbm/cuin
rho Flange	= 0.1	lbm/cuin

ID	= 32.840	in
flangeID	= 32.000	in
shellVolume	= 297.853	cuin
flangeVolume	= 5.10509	cuin
shellMass	= 18.973	lbm
flangeMass	= 0.511	lbm

Helium Pressurant: pressurant helium

mass = 3.692 lbm type = pressurant

Calibrated Polytropic Heat Transfer

Final Helium Temperatures Calibrated with High Fidelity Analysis

==== INPUT ====
Name	Value	Units
VpropTnk	= 17305.2	cuin
PHeTnk	= 10000	psia
PpropNom	= 439.234	psia
PfinHeOvPnom	= 1.1
tAction	= 393.896	sec
TminR	= 510.0	degR
TmaxR	= 550.0	degR
gammaPolyCalibrated	= 1.18607
THeCalibrated	= 489.3	degR

==== OUTPUT ====
Name	Value	Units
WHeTotal	= 3.692	lbm
WtHeResid	= 0.389	lbm
WHeExpended	= 3.302	lbm
volHeTotal	= 1229.91	cuin
wdotHe	= 0.00838343	lbm/sec
compressInit	= 1.31036
PinitCold	= 9290.86	psia
densInitBot	= 5.18647	lbm/cuft
densFinalBot	= 0.547025	lbm/cuft
densFinalProp	= 0.329739	lbm/cuft
gammaPoly	= 1.18607
TfinalPropHe	= 489.3	degR
TfinalHeBot	= 320.7	degR
PfinalHeBot	= 483.2	psia

Incompressible Liquid: Monomethyl Hydrazine

mass = 257.117 lbm type = propellant

MMH Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 530.0	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	= 254.545	lbm
Residual	= 2.571	lbm

==== OUTPUT ====
Name	Value	Units
D	= 54.544	lbm/cuft
rho	= 0.0315646	lbm/cuin (0.873706 SG)
Cp	= 0.7	BTU/lbm degR
Visc	= 53.04	[1.0E5 * lb/ft-sec]
Cond	= 0.143294	BTU/ft-hr-R
SurfTen	= 0.0001932	lbf/in
phase	= LIQUID
Pvap	= 0.875502	psia
Vcuft	= 4.71396	cuft
Volume	= 8145.72	cuin

Incompressible Liquid: Nitrogen Tetroxide

mass = 449.954 lbm type = propellant

N2O4 Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 530.0	degR
P	= 20.0	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	= 445.455	lbm
Residual	= 4.500	lbm

==== OUTPUT ====
Name	Value	Units
D	= 89.987	lbm/cuft
rho	= 0.0520758	lbm/cuin (1.44145 SG)
Cp	= 0.378	BTU/lbm degR
Visc	= 26.64	[1.0E5 * lb/ft-sec]
Cond	= 0.0759456	BTU/ft-hr-R
SurfTen	= 0.0001433	lbf/in
phase	= LIQUID
Pvap	= 14.7864	psia
Vcuft	= 5.00021	cuft
Volume	= 8640.36	cuin

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