PRISM (PaRametrIc System Model)

PRISM (PaRametrIc System Model)
N2O4/MMH Conical KV	PRISM v1.1.7
by: Prymatt Conehead	May 05, 2018

Mass Summary
System: N2O4/MMH Conical KV	110.316	lbm	Total
Name	Mass	Units	Type
INERT
ACS Engines + Mounts	1.333	lbm	inert
Axial Engine	1.456	lbm	inert
Center Helium Tank	1.433	lbm	inert
Divert Engine	2.962	lbm	inert
Divert Structure	5.288	lbm	inert
Fuel Tank	6.099	lbm	inert
Helium Tank	4.027	lbm	inert
Manifold Block	1.309	lbm	inert
Margin Mass	1.902	lbm	inert
Misc. Wt	2.367	lbm	inert
Oxidizer Tank	6.233	lbm	inert
Payload Mass	21.670	lbm	inert
Tubing	0.291	lbm	inert
PRESSURANT
Helium Pressurant	0.758	lbm	pressurant
PROPELLANT
Monomethyl Hydrazine	19.764	lbm	propellant
Nitrogen Tetroxide	33.423	lbm	propellant

Design Variables (nominal values)
Name	Value	Units	Description
apexTankEllRatio	1.6		Apex Tank Ellipse Ratio
Fdivert	202	lbf	Divert Thrust (lbf)
MR	1.68		Engine Mixture Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentACS	5	%	HLACS Percent of Total Impulse (%)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
PHe	10000	psia	Helium Tank Pressure (psia)
pressTankEllRatio	1.6		Pressure Tank Ellipse Ratio
Wpayload	21.67	lbm	Payload Mass (lbm)
WtProp	48	lbm	Usable Divert Propellant Mass (lbm)

Design Variables (nominal values)
Name	Value	Units	Description
apexTankEllRatio	1.6		Apex Tank Ellipse Ratio
Fdivert	202	lbf	Divert Thrust (lbf)
MR	1.68		Engine Mixture Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentACS	5	%	HLACS Percent of Total Impulse (%)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
PHe	10000	psia	Helium Tank Pressure (psia)
pressTankEllRatio	1.6		Pressure Tank Ellipse Ratio
Wpayload	21.67	lbm	Payload Mass (lbm)
WtProp	48	lbm	Usable Divert Propellant Mass (lbm)

Design Variables (nominal values)
Name	Value	Units	Description
apexTankEllRatio	1.6		Apex Tank Ellipse Ratio
Fdivert	202	lbf	Divert Thrust (lbf)
MR	1.68		Engine Mixture Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentACS	5	%	HLACS Percent of Total Impulse (%)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
PHe	10000	psia	Helium Tank Pressure (psia)
pressTankEllRatio	1.6		Pressure Tank Ellipse Ratio
Wpayload	21.67	lbm	Payload Mass (lbm)
WtProp	48	lbm	Usable Divert Propellant Mass (lbm)

Design Variable Summary

Design Variables (nominal values)
Name	Value	Units	Description
apexTankEllRatio	1.6		Apex Tank Ellipse Ratio
Fdivert	202	lbf	Divert Thrust (lbf)
MR	1.68		Engine Mixture Ratio
Pc	375	psia	Engine Chamber Pressure (psia)
pcentACS	5	%	HLACS Percent of Total Impulse (%)
pcentBell	80	%	Percent Bell Nozzle Contour (%)
PHe	10000	psia	Helium Tank Pressure (psia)
pressTankEllRatio	1.6		Pressure Tank Ellipse Ratio
Wpayload	21.67	lbm	Payload Mass (lbm)
WtProp	48	lbm	Usable Divert Propellant Mass (lbm)

Result Variables
Name	Value	Units	Description	Constrain	Limit
AreaRatioAxial	27.5939		Axial Nozzle Area Ratio		---
AreaRatioDivert	30		Divert Nozzle Area Ratio		---
DACSMass	88.5821	lbm	DACS Mass (lbm)		<81
deltaV	5505.03	ft/sec	Total Vacuum Delta V (ft/sec)		---
deltaV_Axial	3853.03	ft/sec	Axial Vacuum Delta V (ft/sec)		---
deltaV_Divert	1640.5	ft/sec	Divert Vacuum Delta V (ft/sec)		---
deltaV_SI	1677.85	m/sec	Total Vacuum Delta V (m/sec)		---
deltaV_SI_Axial	1174.34	m/sec	Axial Vacuum Delta V (m/sec)		---
deltaV_SI_Divert	500	m/sec	Divert Vacuum Delta V (m/sec)		---
endGameGeesPhi45	4.58894	gees	End Game Gees at phi=45 (gees)		---
htBlock	2.72352	in	Height of IVA Block (in)		---
Isp	291.652	sec	Divert Engine Specific Impulse (sec)		---
IspAxial	290.784	sec	Axial Engine Specific Impulse (sec)		---
Itot	13999.3	lbf-sec	Total Impulse (lbf-sec)		---
lcylOvDfuel	3.37648		Lcyl/Diam Fuel Tank		---
lcylOvDox	3.37648		Lcyl/Diam Ox Tank		---
LenEngineGoal	6.15614	in	Divert Nozzle + Chamber Length (in)		---
Lpackage	20.167	in	Total KV Length (in)		---
Ptank	1000	psia	Propellant Tank Pressure (psia)		---
sysMass	110.252	lbm	Propulsion System Mass (lbm)		---
tBurnAxial	26.4168	sec	Total Axial Engine Burn Time (sec)		---

Simple Equation Mass: ACS Engines + Mounts
mass = 1.333 lbm type = inert
HLACS and LLACS Engines
Calc Wt from Eqn : 1.333

Bipropellant Engine: Axial Engine

mass = 1.456 lbm type = inert

Propellants : N2O4 / MMH

NASA CEA Code for ODE performance

Physical Weight Model

Injector Material is Ti

Nozzle Material is Cb103

Bell Nozzle with Percent Bell = 80

Mass is for 2 engines total

==== INPUT ====
Name	Value	Units
Fvac	= 202	lbf
Pc	= 375.0	psia
eps	= 27.5939
%Bell	= 80.00	%
mr	= 1.68
CR	= 2.5
xlnOverLcham	= 0.9
LoverDt	= 2
LchamMin	= 1.400	in
cxwInj	= 1
cxwValves	= 1
cxw	= 0.9
etaERE	= 0.938069

==== OUTPUT ====
Name	Value	Units
Isp	= 290.784	sec
Cstar	= 5383.4	ft/sec
etaBL	= 0.982094
etaDiv	= 0.991184
etaKin	= 0.974304
etaNoz	= 0.948423
effIsp	= 0.889685
IspODE	= 326.839	sec
CstarODE	= 5738.9	ft/sec
Tc	= 5656.9	degR
PcFace	= 393.017	psia
Pexit	= 1.11437	psia
wdotTot	= 0.694675	lbm/sec
wdotOx	= 0.435468	lbm/sec
wdotFl	= 0.259207	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 8.36218	cuin/sec
volDotFl	= 8.21194	cuin/sec
DFlow	= 0.596	in
At	= 0.30996	sqin
Dt	= 0.628	in
Dcham	= 0.993	in
Dexit	= 3.300	in
Lcham	= 1.400	in
xlc	= 0.140	in
xln	= 1.260	in
Lnoz	= 3.988	in
Lengine	= 6.382	in
rhoInj	= 0.160	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 0.204	lbm
WtChamber	= 0.023	lbm
WtInj	= 0.149	lbm
WtAcoustic	= 0.264	lbm
WtValves(2)	= 0.090	lbm
WtMisc	= 0.069	lbm
wt/Engine	= 0.728	lbm
F/W	= 277.434	lbf/lbm

Cylindrical/Spherical/Elliptical Tank: Center Helium Tank

mass = 1.433 lbm type = inert

Composite Tank Algorithm

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 68.9052	cuin
vfreeTotal	= 68.9052	cuin
ell	= 1.6
rcyltd	= 1.82114
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	= 1.707	in
dinsid	= 3.414	in
OR	= 1.900	in
OD	= 3.800	in
OH	= 8.787	in
hinsid	= 8.352	in
SAinsid	= 94.594	sqin
cyl	= 6.218	in
wacqui	= 0.000	lbm
vacqui	= 0	cuin
dpacq	= 0	psig
pullag	= 10000	psia
vresid	= 1.0424	cuin
vtank	= 69.9476	cuin
tming	= 0.008	in
thkcyl	= 0.128	in
thkend	= 0.153	in
thkBladOut	= 0.030	in
wliner	= 0.353	lbm
wtank(+liner)	= 1.130	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 488199	lbf-in/lbm
Pburst(est.)	= 20000.0	psia
PburstVoverW	= 976399	lbf-in/lbm

Bipropellant Engine: Divert Engine

mass = 2.962 lbm type = inert

Propellants : N2O4 / MMH

NASA CEA Code for ODE performance

Physical Weight Model

Injector Material is Ti

Nozzle Material is Cb103

Bell Nozzle with Percent Bell = 80

Mass is for 4 engines total

==== INPUT ====
Name	Value	Units
Fvac	= 202	lbf
Pc	= 375.0	psia
eps	= 30
%Bell	= 80.00	%
mr	= 1.68
CR	= 2.5
xlnOverLcham	= 0.9
LoverDt	= 2
LchamMin	= 1.400	in
cxwInj	= 1
cxwValves	= 1
cxw	= 0.9
etaERE	= 0.938069

==== OUTPUT ====
Name	Value	Units
Isp	= 291.652	sec
Cstar	= 5383.4	ft/sec
etaBL	= 0.981643
etaDiv	= 0.991331
etaKin	= 0.973923
etaNoz	= 0.947758
effIsp	= 0.889061
IspODE	= 328.045	sec
CstarODE	= 5738.9	ft/sec
Tc	= 5656.9	degR
PcFace	= 393.017	psia
Pexit	= 0.997211	psia
wdotTot	= 0.692606	lbm/sec
wdotOx	= 0.434171	lbm/sec
wdotFl	= 0.258435	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 8.33728	cuin/sec
volDotFl	= 8.18749	cuin/sec
DFlow	= 0.595	in
At	= 0.309037	sqin
Dt	= 0.627	in
Dcham	= 0.992	in
Dexit	= 3.436	in
Lcham	= 1.400	in
xlc	= 0.140	in
xln	= 1.260	in
Lnoz	= 4.193	in
Lengine	= 6.584	in
rhoInj	= 0.160	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 0.219	lbm
WtChamber	= 0.023	lbm
WtInj	= 0.148	lbm
WtAcoustic	= 0.263	lbm
WtValves(2)	= 0.090	lbm
WtMisc	= 0.069	lbm
wt/Engine	= 0.740	lbm
F/W	= 272.819	lbf/lbm

Simple Equation Mass: Divert Structure
mass = 5.288 lbm type = inert
Divert Structure
Calc Wt from Eqn : 3.449 * (13.8/9.0)

Conical Tank with Elliptical Domes: Fuel Tank

mass = 6.099 lbm type = inert

Metal Tank Algorithm

Structural Material : Ti

Bladder Thickness is input at 0.030 in

kalmod = 0

Mass is for 2 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 322.762	cuin
vfreeTotal	= 645.523	cuin
ell	= 1.6
RbigOvrRsml	= 1.68182
coneAngleDeg	= 4.31	deg
ptank	= 1000	psia
sf	= 1.5
cxw	= 1.25
ithcyl	= 1
kacqui	= 1	transverse collapsing Alum. bladder
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	= 0.000	in
rholiner	= 0.1	lbm/cuin

==== OUTPUT ====
Name	Value	Units
IRbig	= 2.947	in
IDbig	= 5.893	in
IRsmall	= 1.752	in
IDsmall	= 3.504	in
OR	= 3.007	in
OD	= 6.014	in
OH	= 19.011	in
IHtotal	= 18.891	in
SAinsid	= 304.013	sqin
Hcone	= 15.864	in
wacqui	= 0.875	lbm
vacqui	= 8.7542	cuin
dpacq	= 76.8119	psig
pullag	= 1076.81	psia
vresid	= 5.34394	cuin
Vcone	= 280.369	cuin
vtank	= 336.86	cuin
tming	= 0.030	in
thkcyl	= 0.031	in
thkend	= 0.030	in (use tming)
thkBladOut	= 0.030	in
wtank	= 1.564	lbm
rho	= 0.16	lbm/cuin
sy	= 118663	psi
e	= 1.5e+07	psi
PmeopVoverW	= 110463	lbf-in/lbm
Pburst(est.)	= 1500.0	psia
PburstVoverW	= 165694	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Helium Tank

mass = 4.027 lbm type = inert

Composite Tank Algorithm

kalmod = 0

Mass is for 4 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 45.9368	cuin
vfreeTotal	= 183.747	cuin
ell	= 1.6
rcyltd	= 2.26586
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	= 1.404	in
dinsid	= 2.808	in
OR	= 1.574	in
OD	= 3.149	in
OH	= 8.500	in
hinsid	= 8.119	in
SAinsid	= 75.021	sqin
cyl	= 6.363	in
wacqui	= 0.000	lbm
vacqui	= 0	cuin
dpacq	= 0	psig
pullag	= 10000	psia
vresid	= 0.727713	cuin
vtank	= 46.6645	cuin
tming	= 0.008	in
thkcyl	= 0.105	in
thkend	= 0.126	in
thkBladOut	= 0.030	in
wliner	= 0.279	lbm
wtank(+liner)	= 0.794	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 463570	lbf-in/lbm
Pburst(est.)	= 20000.0	psia
PburstVoverW	= 927140	lbf-in/lbm

Simple Equation Mass: Manifold Block
mass = 1.309 lbm type = inert
Manifold Block
Calc Wt from Eqn : 2.72352 * 2.45117*2 0.16 / 2.0

Simple Equation Mass: Margin Mass
mass = 1.899 lbm type = inert
Margin Mass
Calc Wt from Eqn : 0.058*32.7371

Miscellaneous Mass Items: Misc. Wt

mass = 2.367 lbm type = inert

All items are of type: inert

==== INPUT ====
Name	Value	Units
===SORT ORDER===	= Alphabetical
Electronics & Harnesses	= 0.438	lbm
He Controls (pyro, reg, etc.)	= 1.659	lbm
Ox and Fuel Burst Disks	= 0.110	lbm
Ox and Fuel Service Valves	= 0.120	lbm
Pressure Transducers	= 0.040	lbm

==== OUTPUT ====
Name	Value	Units
===SORT ORDER===	= Mass
He Controls (pyro, reg, etc.)	= 1.659	lbm
Electronics & Harnesses	= 0.438	lbm
Ox and Fuel Service Valves	= 0.120	lbm
Ox and Fuel Burst Disks	= 0.110	lbm
Pressure Transducers	= 0.040	lbm

Conical Tank with Elliptical Domes: Oxidizer Tank

mass = 6.233 lbm type = inert

Metal Tank Algorithm

Structural Material : Ti

Bladder Thickness is input at 0.030 in

kalmod = 0

Mass is for 2 Tanks total

==== INPUT ====
Name	Value	Units
vfree	= 330.837	cuin
vfreeTotal	= 661.674	cuin
ell	= 1.6
RbigOvrRsml	= 1.68182
coneAngleDeg	= 4.31	deg
ptank	= 1000	psia
sf	= 1.5
cxw	= 1.25
ithcyl	= 1
kacqui	= 1	transverse collapsing Alum. bladder
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	= 0.000	in
rholiner	= 0.1	lbm/cuin

==== OUTPUT ====
Name	Value	Units
IRbig	= 2.971	in
IDbig	= 5.942	in
IRsmall	= 1.766	in
IDsmall	= 3.533	in
OR	= 3.032	in
OD	= 6.063	in
OH	= 19.167	in
IHtotal	= 19.047	in
SAinsid	= 309.027	sqin
Hcone	= 15.996	in
wacqui	= 0.890	lbm
vacqui	= 8.90053	cuin
dpacq	= 76.5581	psig
pullag	= 1076.56	psia
vresid	= 5.49012	cuin
Vcone	= 287.384	cuin
vtank	= 345.227	cuin
tming	= 0.030	in
thkcyl	= 0.031	in
thkend	= 0.030	in (use tming)
thkBladOut	= 0.030	in
wtank	= 1.603	lbm
rho	= 0.16	lbm/cuin
sy	= 118663	psi
e	= 1.5e+07	psi
PmeopVoverW	= 110778	lbf-in/lbm
Pburst(est.)	= 1500.0	psia
PburstVoverW	= 166167	lbf-in/lbm

Simple Equation Mass: Payload Mass
mass = 21.670 lbm type = inert
Payload Mass
Calc Wt from Eqn : 21.67

Simple Equation Mass: Tubing
mass = 0.230 lbm type = inert
Tubing for Ox, Fuel and He
Calc Wt from Eqn : 0.19 * (13.8 + 20.167) / (10.0 + 18.0)

Helium Pressurant: Helium Pressurant

mass = 0.758 lbm type = pressurant

Polytropic Heat Transfer

Heated Helium (Heat Exchanger between source and tank

==== INPUT ====
Name	Value	Units
VpropTnk	= 1346.41	cuin
PHeTnk	= 10000	psia
PpropNom	= 1000	psia
PfinHeOvPnom	= 1
tAction	= 100	sec
TminR	= 510.0	degR
TmaxR	= 550.0	degR
tPolyCorr	= 200	sec
gamPolyCorr	= 1.2
gamLimPolyCorr	= 1.18
THeTnkHX	= 450.0	degR

==== OUTPUT ====
Name	Value	Units
WHeTotal	= 0.758	lbm
WtHeResid	= 0.137	lbm
WHeExpended	= 0.622	lbm
volHeTotal	= 252.653	cuin
wdotHe	= 0.00621686	lbm/sec
compressInit	= 1.31036
PinitCold	= 9290.86	psia
densInitBot	= 5.18647	lbm/cuft
densFinalBot	= 0.93457	lbm/cuft
densFinalProp	= 0.797878	lbm/cuft
gammaPoly	= 1.15
TfinalPropHe	= 450.0	degR
TfinalHeBot	= 381.3	degR
PfinalHeBot	= 1000.0	psia

Incompressible Liquid: Monomethyl Hydrazine

mass = 19.764 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	= 17.910	lbm
Burned RCS	= 1.750	lbm
Residual	= 0.104	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	= 0.36236	cuft
Volume	= 626.158	cuin

Incompressible Liquid: Nitrogen Tetroxide

mass = 33.423 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	= 30.090	lbm
Burned RCS	= 1.750	lbm
Residual	= 1.584	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	= 0.371426	cuft
Volume	= 641.823	cuin

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