PRISM (PaRametrIc System Model)

PRISM (PaRametrIc System Model)
N2O4/M20 Ascent Phase	PRISM v1.1.7
by: I.M. Pacter	May 05, 2018

Design Variables (nominal values)
Name	Value	Units	Description
eps	9		Nozzle Area Ratio
MR	1		Engine Mixture 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
MR	1		Engine Mixture 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
MR	1		Engine Mixture 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/M20 Ascent Phase	67.196	lbm	Total
Name	Mass	Units	Type
INERT
Divert Engine	3.414	lbm	inert
Divert Structure	0.799	lbm	inert
Fuel Tank	3.662	lbm	inert
Helium Tank	2.032	lbm	inert
Manifold Block	0.704	lbm	inert
Oxidizer Tank	2.859	lbm	inert
Payload Mass	33.069	lbm	inert
PRESSURANT
Helium Pressurant	0.249	lbm	pressurant
PROPELLANT
M20	10.204	lbm	propellant
Nitrogen Tetroxide	10.204	lbm	propellant

Design Variables (nominal values)
Name	Value	Units	Description
eps	9		Nozzle Area Ratio
MR	1		Engine Mixture 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
MR	1		Engine Mixture 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	34.1266	lbm	DACS Mass (lbm)		---
FdivertSL	238.016	lbf	Sea Level Divert Thrust (lbf)		---
FdivertVac	300	lbf	Vacuum Divert Thrust (lbf)		---
Isp	273.717	sec	Engine Specific Impulse (sec)		---
IspSL	217.164	sec	Sea Level Isp (sec)		---
Itot	4926.91	lbf-sec	Total Impulse (lbf-sec)		---
ItotSL	3908.95	lbf-sec	Sea Level Total Impulse (lbf-sec)		---
LcylOx	0	in	Cylinder Length of Ox Tank (in)		---
Lpackage	15.1743	in	Total KV Length (in)		---
OxTankOD	9.39447	in	Ox Tank Diameter (in)		>9.8
Ptank	969.423	psia	Propellant Tank Pressure (psia)		---
rhoBulk	0.0421135	lbm/cuin	Propellant Bulk Density (lbm/cuin)		---
sysMass	67.1959	lbm	Propulsion System Mass (lbm)		---
Vhelium	82.869	cuin	Total Helium Volume (cuin)		---

Bipropellant Engine: Divert Engine

mass = 3.414 lbm type = inert

Propellants : N2O4 / M20

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
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	= 273.717	sec
Cstar	= 5298.8	ft/sec
etaBL	= 0.988613
etaDiv	= 0.986865
etaKin	= 1
etaNoz	= 0.975627
effIsp	= 0.893675
IspODE	= 306.283	sec
CstarODE	= 5784.7	ft/sec
Tc	= 5221.5	degR
PcFace	= 401.923	psia
Pexit	= 4.69292	psia
wdotTot	= 1.09602	lbm/sec
wdotOx	= 0.54801	lbm/sec
wdotFl	= 0.54801	lbm/sec
rhoFl	= 0.0354	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 10.5233	cuin/sec
volDotFl	= 15.5021	cuin/sec
DFlow	= 0.811	in
At	= 0.481349	sqin
Dt	= 0.783	in
Dcham	= 1.107	in
Dexit	= 2.349	in
Lcham	= 1.030	in
xlc	= 0.515	in
xln	= 0.515	in
Lnoz	= 2.337	in
Lengine	= 4.474	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 0.140	lbm
WtChamber	= 0.021	lbm
WtInj	= 0.361	lbm
WtAcoustic	= 0.216	lbm
WtValves(2)	= 2.331	lbm
WtMisc	= 0.128	lbm
F/W	= 87.865	lbf/lbm
IspAmb	= 217.164	sec
Famb	= 238.016	lbf
nozzle condition	= Separated (Psep=5.12724, epsSep=9.23668)

Solenoid Valve: biprop valves

mass = 2.331 lbm type = inert

Based on Solenoid Valve Experience

Mass is for 2 valves total

==== INPUT ====
Name	Value	Units
cuInchPerSec	= 15.5021	cuin/sec
cxw	= 1.000

==== OUTPUT ====
Name	Value	Units
basemass	= 1.166	lbm

Simple Equation Mass: Divert Structure
mass = 0.799 lbm type = inert
Divert Structure
Calc Wt from Eqn : 1.1 * (9.9/10.0) * (3.88936/5.3)

Cylindrical/Spherical/Elliptical Tank: Fuel Tank

mass = 3.662 lbm type = inert

Metal Tank Algorithm

Structural Material : grEpox

Bladder Thickness is input at 0.030 in

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 282.88	cuin
vfreeTotal	= 282.88	cuin
ell	= 2
rcyltd	= 0.0821574
ptank	= 969.423	psia
sf	= 1.5
cxw	= 2.18865
ithcyl	= 1
kacqui	= 1	transverse collapsing Alum. bladder
inpex	= 1
expefi	= 0.98
tblad	= 0.030	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.1	lbm/cuin
tliner	= 0.030	in
rholiner	= 0.1	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 4.872	in
dinsid	= 9.744	in
OR	= 4.950	in
OD	= 9.900	in
OH	= 5.828	in
hinsid	= 5.673	in
SAinsid	= 230.343	sqin
cyl	= 0.801	in
wacqui	= 0.655	lbm
vacqui	= 6.55143	cuin
dpacq	= 58.1937	psig
pullag	= 1027.62	psia
vresid	= 5.6576	cuin
vtank	= 301.895	cuin
tming	= 0.008	in
thkcyl	= 0.018	in
thkend	= 0.018	in
thkBladOut	= 0.030	in
wliner	= 0.691	lbm
wtank(+liner)	= 1.018	lbm
rho	= 0.0637	lbm/cuin
sy	= 393000	psi
e	= 3.5e+07	psi
PmeopVoverW	= 79919.2	lbf-in/lbm
Pburst(est.)	= 1454.1	psia
PburstVoverW	= 119879	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Helium Tank

mass = 2.032 lbm type = inert

Composite Tank Algorithm

kalmod = 0

Mass is for 4 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 20.7172	cuin
vfreeTotal	= 82.869	cuin
ell	= 1.6
rcyltd	= 0.993134
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	= 1.335	in
dinsid	= 2.670	in
OR	= 1.500	in
OD	= 3.000	in
OH	= 4.689	in
hinsid	= 4.320	in
SAinsid	= 39.306	sqin
cyl	= 2.652	in
wacqui	= 0.000	lbm
vacqui	= 0	cuin
dpacq	= 0	psig
pullag	= 10000	psia
vresid	= 0.35723	cuin
vtank	= 21.0745	cuin
tming	= 0.008	in
thkcyl	= 0.100	in
thkend	= 0.120	in
thkBladOut	= 0.030	in
wliner	= 0.150	lbm
wtank(+liner)	= 0.401	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 414820	lbf-in/lbm
Pburst(est.)	= 20000.0	psia
PburstVoverW	= 829640	lbf-in/lbm

Simple Equation Mass: Manifold Block
mass = 0.704 lbm type = inert
Manifold Block
Calc Wt from Eqn : 2.21427 * 1.99284*2 0.16 / 2.0

Cylindrical/Spherical/Elliptical Tank: Oxidizer Tank

mass = 2.859 lbm type = inert

Metal Tank Algorithm

Structural Material : grEpox

Bladder Thickness is input at 0.030 in

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 192.028	cuin
vfreeTotal	= 192.028	cuin
ell	= 2
rcyltd	= 0
ptank	= 969.423	psia
sf	= 1.5
cxw	= 2.18865
ithcyl	= 1
kacqui	= 1	transverse collapsing Alum. bladder
inpex	= 1
expefi	= 0.98
tblad	= 0.030	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.1	lbm/cuin
tliner	= 0.030	in
rholiner	= 0.1	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 4.620	in
dinsid	= 9.240	in
OR	= 4.697	in
OD	= 9.394	in
OH	= 4.774	in
hinsid	= 4.620	in
SAinsid	= 185.111	sqin
cyl	= 0.000	in
wacqui	= 0.523	lbm
vacqui	= 5.23129	cuin
dpacq	= 59.5025	psig
pullag	= 1028.93	psia
vresid	= 3.84055	cuin
vtank	= 206.555	cuin
tming	= 0.008	in
thkcyl	= 0.017	in
thkend	= 0.017	in
thkBladOut	= 0.030	in
wliner	= 0.555	lbm
wtank(+liner)	= 0.783	lbm
rho	= 0.0637	lbm/cuin
sy	= 393000	psi
e	= 3.5e+07	psi
PmeopVoverW	= 70048.2	lbf-in/lbm
Pburst(est.)	= 1454.1	psia
PburstVoverW	= 105072	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 = 0.249 lbm type = pressurant

Integrated Heat Transfer

==== INPUT ====
Name	Value	Units
VpropTnk	= 474.908	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	= 0.249	lbm
WtGasResid	= 0.053	lbm
WGasNon-Resid	= 0.196	lbm
Vbottle	= 82.869	cuin
wdotGas	= 0.00196078	lbm/sec
compressInit	= 1.31036
PbottleCold	= 9290.86	psia
densInitBot	= 5.18655	lbm/cuft
densFinalBot	= 1.0979	lbm/cuft
densFinalProp	= 0.712723	lbm/cuft
gammaIsen	= 1.62144
gamPolyBottle	= 1.22401
gamPolyTank	= 1.01829
fracIsenBottle	= 0.360467
fracIsenTank	= 0.029429
TfinalPropGas	= 490.6	degR
TfinalGasBot	= 343.2	degR
PfinalGasBot	= 1066.4	psia

Incompressible Liquid: M20

mass = 10.204 lbm type = propellant

M20 Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 530.0	degR
P	= 14.7	psia
Tref	= 530.0	degR
Tnbp	= 687.8	degR
Tcrit	= 1150.6	degR
Pref	= 14.7	psia
Pcrit	= 1943.8	psia
WtMol	= 34.8524
RhoRef	= 0.0353507	lb/cuin
ViscRefFT	= 0.000596928	lb/ft-sec
CondRefFTHR	= 0.255027	BTU/ft-hr-R
CpRef	= 0.72808	BTU/lbm degR
Burned Divert	= 9.000	lbm
Burned RCS	= 1.000	lbm
Residual	= 0.204	lbm

==== OUTPUT ====
Name	Value	Units
D	= 61.086	lbm/cuft
rho	= 0.0353507	lbm/cuin (0.978504 SG)
Cp	= 0.72808	BTU/lbm degR
Visc	= 59.6928	[1.0E5 * lb/ft-sec]
Cond	= 0.255027	BTU/ft-hr-R
SurfTen	= 0.00034216	lbf/in
phase	= LIQUID
Pvap	= 0.274292	psia
Vcuft	= 0.167045	cuft
Volume	= 288.653	cuin

Incompressible Liquid: Nitrogen Tetroxide

mass = 10.204 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	= 9.000	lbm
Burned RCS	= 1.000	lbm
Residual	= 0.204	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	= 0.113395	cuft
Volume	= 195.947	cuin

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