PRISM (PaRametrIc System Model)

PRISM (PaRametrIc System Model)
N2O4/MMH He, Piston Ascent Phase	PRISM v1.1.7
by: Wally Seal	May 05, 2018

Design Variables (nominal values)
Name	Value	Units	Description
eps	9		Nozzle Area Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
pcentWpACS	10	%	HLACS Percent of Propellant (%)
PHe	10000	psia	Helium Tank Pressure (psia)
ThrustVac	300	lbf	Engine Vacuum Thrust (lbf)
Wpayload	33.0693	lbm	Payload Mass (lbm)
WtProp	20	lbm	Usable Divert+ACS Propellant Mass (lbm)

Design Variables (nominal values)
Name	Value	Units	Description
eps	9		Nozzle Area Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
pcentWpACS	10	%	HLACS Percent of Propellant (%)
PHe	10000	psia	Helium Tank Pressure (psia)
ThrustVac	300	lbf	Engine Vacuum Thrust (lbf)
Wpayload	33.0693	lbm	Payload Mass (lbm)
WtProp	20	lbm	Usable Divert+ACS Propellant Mass (lbm)

Design Variables (nominal values)
Name	Value	Units	Description
eps	9		Nozzle Area Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
pcentWpACS	10	%	HLACS Percent of Propellant (%)
PHe	10000	psia	Helium Tank Pressure (psia)
ThrustVac	300	lbf	Engine Vacuum Thrust (lbf)
Wpayload	33.0693	lbm	Payload Mass (lbm)
WtProp	20	lbm	Usable Divert+ACS Propellant Mass (lbm)

Mass Summary
System: N2O4/MMH He, Piston Ascent Phase	67.570	lbm	Total
Name	Mass	Units	Type
INERT
Divert Engine	3.199	lbm	inert
Divert Structure	0.457	lbm	inert
Fuel Tank	3.813	lbm	inert
Helium Tank	1.848	lbm	inert
Manifold Block	0.713	lbm	inert
Oxidizer Tank	3.813	lbm	inert
Payload Mass	33.069	lbm	inert
PRESSURANT
Helium Pressurant	0.250	lbm	pressurant
PROPELLANT
Monomethyl Hydrazine	7.947	lbm	propellant
Nitrogen Tetroxide	12.461	lbm	propellant

Design Variables (nominal values)
Name	Value	Units	Description
eps	9		Nozzle Area Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
pcentWpACS	10	%	HLACS Percent of Propellant (%)
PHe	10000	psia	Helium Tank Pressure (psia)
ThrustVac	300	lbf	Engine Vacuum Thrust (lbf)
Wpayload	33.0693	lbm	Payload Mass (lbm)

Design Variable Summary

Design Variables (nominal values)
Name	Value	Units	Description
eps	9		Nozzle Area Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
pcentWpACS	10	%	HLACS Percent of Propellant (%)
PHe	10000	psia	Helium Tank Pressure (psia)
ThrustVac	300	lbf	Engine Vacuum Thrust (lbf)
Wpayload	33.0693	lbm	Payload Mass (lbm)
WtProp	20	lbm	Usable Divert+ACS Propellant Mass (lbm)

Result Variables
Name	Value	Units	Description	Constrain	Limit
AreaRatio	9		Divert Nozzle Area Ratio		---
DACSMass	34.5008	lbm	DACS Mass (lbm)		---
FdivertSL	237.146	lbf	Sea Level Divert Thrust (lbf)		---
FdivertVac	300	lbf	Vacuum Divert Thrust (lbf)		---
IDpiston	3.09759 * ----->	in	ID of Piston Tanks (in) (IDpiston varies to make nestError = 0 in)		>0.99, <3.96
Isp	268.983	sec	Engine Specific Impulse (sec)		---
IspSL	212.627	sec	Sea Level Isp (sec)		---
Itot	4841.7	lbf-sec	Total Impulse (lbf-sec)		---
ItotSL	3827.29	lbf-sec	Sea Level Total Impulse (lbf-sec)		---
Lpackage	19.1534	in	Total KV Length (in)		---
MR	1.64982		Equal Volume Mixture Ratio		---
nestError	1.3002e-07	in	Helium Tank Nesting Quality (in)		=0
OxTankOD	3.17016	in	Ox Tank Diameter (in)		---
Ptank	969.423	psia	Propellant Tank Pressure (psia)		---
rhoBulk	0.0418202	lbm/cuin	Propellant Bulk Density (lbm/cuin)		---
sysMass	67.5701	lbm	Propulsion System Mass (lbm)		---
Vhelium	83.455	cuin	Total Helium Volume (cuin)		---

Bipropellant Engine: Divert Engine

mass = 3.199 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

==== INPUT ====
Name	Value	Units
Fvac	= 300	lbf
Pc	= 375.0	psia
eps	= 9
%Bell	= 80.00	%
mr	= 1.64982
CR	= 2
xlnOverLcham	= 0.5
LoverDt	= 0.01
LchamMin	= 1.030	in
cxwInj	= 1
cxwValves	= 1
cxw	= 1.25
etaERE	= 0.916
Pamb	= 14.7	psia

==== OUTPUT ====
Name	Value	Units
Isp	= 268.983	sec
Cstar	= 5253.9	ft/sec
etaBL	= 0.988613
etaDiv	= 0.986865
etaKin	= 0.982692
etaNoz	= 0.958741
effIsp	= 0.878206
IspODE	= 306.287	sec
CstarODE	= 5735.7	ft/sec
Tc	= 5623.1	degR
PcFace	= 401.923	psia
Pexit	= 5.02857	psia
wdotTot	= 1.11531	lbm/sec
wdotOx	= 0.694409	lbm/sec
wdotFl	= 0.420901	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 13.3346	cuin/sec
volDotFl	= 13.3346	cuin/sec
DFlow	= 0.752	in
At	= 0.485671	sqin
Dt	= 0.786	in
Dcham	= 1.112	in
Dexit	= 2.359	in
Lcham	= 1.030	in
xlc	= 0.515	in
xln	= 0.515	in
Lnoz	= 2.348	in
Lengine	= 4.490	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 0.141	lbm
WtChamber	= 0.021	lbm
WtInj	= 0.366	lbm
WtAcoustic	= 0.217	lbm
WtValves(2)	= 2.129	lbm
WtMisc	= 0.110	lbm
F/W	= 93.792	lbf/lbm
IspAmb	= 212.627	sec
Famb	= 237.146	lbf
nozzle condition	= Separated (Psep=5.12724, epsSep=9.82234)

Solenoid Valve: biprop valves

mass = 2.129 lbm type = inert

Based on Solenoid Valve Experience

Mass is for 2 valves total

==== INPUT ====
Name	Value	Units
cuInchPerSec	= 13.3346	cuin/sec
cxw	= 1.000

==== OUTPUT ====
Name	Value	Units
basemass	= 1.065	lbm

Simple Equation Mass: Divert Structure
mass = 0.457 lbm type = inert
Divert Structure
Calc Wt from Eqn : 1.1 * (9.9/10.0) * (2.22419/5.3)

Positive Expulsion Piston Tank: Fuel Tank

mass = 3.813 lbm type = inert

Piston Tank

Metallic Material : Ti

Overwrap Material : grEpox

inputLoverD = 0

Mass is for 2 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 119.559	cuin
vfreeTotal	= 239.119	cuin
Dinside	= 3.098	in
ptank	= 969.423	psia
dPpiston	= 10	psig
sf	= 1.5
thkMetal_minG	= 0.010	in
cxw	= 1
inpex	= 0
expefi	= 0.99

==== OUTPUT ====
Name	Value	Units
radius	= 1.549	in
LoverD	= 5.1218
OD	= 3.170	in
thkPiston	= 0.077	in
thkOv	= 0.023	in
thkMetal	= 0.013	in
rhoMetal	= 0.16	lbm/cuin
rhoOv	= 0.0637	lbm/cuin
designStress	= 393000	psi
Lpiston	= 1.394	in
Lhead	= 0.447	in
Lwet	= 15.865	in
Ltotal	= 18.153	in
vresid	= 1.19559	cuin
vtank	= 120.755	cuin
WmetalShell	= 0.379	lbm
Woverwrap	= 0.262	lbm
Whead	= 0.431	lbm
Wpiston	= 0.402	lbm
Wtotal	= 1.906	lbm
pullag	= 979	psia
Pburst	= 1469	psia
PVoverW	= 61405	lbf-in/lbm
SF*PVoverW	= 92108	lbf-in/lbm
PburstVoverW	= 93058	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Helium Tank

mass = 1.848 lbm type = inert

Composite Tank Algorithm

kalmod = 0

Mass is for 2 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 41.7275	cuin
vfreeTotal	= 83.455	cuin
ell	= 1.6
rcyltd	= 1.9942
ptank	= 10000	psia
sf	= 2
cxw	= 1.26807
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	= 0.035	in
rholiner	= 0.101	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 1.409	in
dinsid	= 2.819	in
OR	= 1.580	in
OD	= 3.160	in
OH	= 7.765	in
hinsid	= 7.382	in
SAinsid	= 68.785	sqin
cyl	= 5.621	in
wacqui	= 0.000	lbm
vacqui	= 0	cuin
dpacq	= 0	psig
pullag	= 10000	psia
vresid	= 0.668089	cuin
vtank	= 42.3956	cuin
tming	= 0.008	in
thkcyl	= 0.106	in
thkend	= 0.126	in
thkBladOut	= 0.030	in
wliner	= 0.257	lbm
wtank(+liner)	= 0.729	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 458838	lbf-in/lbm
Pburst(est.)	= 20000.0	psia
PburstVoverW	= 917676	lbf-in/lbm

Simple Equation Mass: Manifold Block
mass = 0.713 lbm type = inert
Manifold Block
Calc Wt from Eqn : 2.22419 * 2.00177*2 0.16 / 2.0

Positive Expulsion Piston Tank: Oxidizer Tank

mass = 3.813 lbm type = inert

Piston Tank

Metallic Material : Ti

Overwrap Material : grEpox

inputLoverD = 0

Mass is for 2 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 119.559	cuin
vfreeTotal	= 239.119	cuin
Dinside	= 3.098	in
ptank	= 969.423	psia
dPpiston	= 10	psig
sf	= 1.5
thkMetal_minG	= 0.010	in
cxw	= 1
inpex	= 0
expefi	= 0.99

==== OUTPUT ====
Name	Value	Units
radius	= 1.549	in
LoverD	= 5.1218
OD	= 3.170	in
thkPiston	= 0.077	in
thkOv	= 0.023	in
thkMetal	= 0.013	in
rhoMetal	= 0.16	lbm/cuin
rhoOv	= 0.0637	lbm/cuin
designStress	= 393000	psi
Lpiston	= 1.394	in
Lhead	= 0.447	in
Lwet	= 15.865	in
Ltotal	= 18.153	in
vresid	= 1.19559	cuin
vtank	= 120.755	cuin
WmetalShell	= 0.379	lbm
Woverwrap	= 0.262	lbm
Whead	= 0.431	lbm
Wpiston	= 0.402	lbm
Wtotal	= 1.906	lbm
pullag	= 979	psia
Pburst	= 1469	psia
PVoverW	= 61405	lbf-in/lbm
SF*PVoverW	= 92108	lbf-in/lbm
PburstVoverW	= 93058	lbf-in/lbm

Simple Equation Mass: Payload Mass
mass = 33.069 lbm type = inert
Payload Mass
Calc Wt from Eqn : 33.0693

Helium Pressurant: Helium Pressurant

mass = 0.250 lbm type = pressurant

Integrated Heat Transfer

==== INPUT ====
Name	Value	Units
VpropTnk	= 478.237	cuin
PGasTnkMEOP	= 10000	psia
PpropNom	= 969.423	psia
PfinGasOvPnom	= 1.1
tAction	= 100	sec
TminR	= 510.0	degR
TmaxR	= 550.0	degR

==== OUTPUT ====
Name	Value	Units
WGasTotal	= 0.250	lbm
WtGasResid	= 0.053	lbm
WGasNon-Resid	= 0.197	lbm
Vbottle	= 83.455	cuin
wdotGas	= 0.0019746	lbm/sec
compressInit	= 1.31036
PbottleCold	= 9290.86	psia
densInitBot	= 5.18655	lbm/cuft
densFinalBot	= 1.098	lbm/cuft
densFinalProp	= 0.712748	lbm/cuft
gammaIsen	= 1.62144
gamPolyBottle	= 1.22407
gamPolyTank	= 1.01831
fracIsenBottle	= 0.360572
fracIsenTank	= 0.0294568
TfinalPropGas	= 490.5	degR
TfinalGasBot	= 343.1	degR
PfinalGasBot	= 1066.4	psia

Incompressible Liquid: Monomethyl Hydrazine

mass = 7.947 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 Divert	= 6.793	lbm
Burned RCS	= 1.000	lbm
Residual	= 0.154	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	= 0.145699	cuft
Volume	= 251.768	cuin

Incompressible Liquid: Nitrogen Tetroxide

mass = 12.461 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 Divert	= 11.207	lbm
Burned RCS	= 1.000	lbm
Residual	= 0.254	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	= 0.138478	cuft
Volume	= 239.29	cuin

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