Table Of Content,
. ... .. ., . ,!,.,’ ’
.11.,
Pet lorin ail Evnluatioii 01 llte Po1ciili:il Apptic~~ti~oiili sn
Specilic Nuclear Tttertiial Rocket (NIR)O c?sigi\t o Past airil
Ciirrenl (First Lunar Oirlposl) Missioii Ptolilr(s) lor I’ilc~lctl
and Cargo l.iitiar Missioiis, nttd lo Asspss 111A~p plicatiilily 01
NP-TIM-92 347 NIP: System Co,In,c,e!p ts. I.
Mission Statement T
Surlace wllh cot~slrlpinllonfo r evolvnlilllly IO
Mars
-Lutiar IoC 200&21)05
ic
Functional Rcqts System Reqts
1. O Prelaunch Proc Lunar Ditecl Lunor Orbit Rdndezvous
2.0 I.aunc1i Ops - NLS & Saturn V derived 661 6 135 I launch syslem
launch systems Only 2 IiLLV Flts per mlsslon
2nd HLLV FII wllhln 3 days
3.0 Transfer lo Lunor
Surlace 4 Uey lrensll 3 Day 1 ratisit
Cargo Mlsslon- 33 I LO1 Ops Altltude = 300 km
Manned Mlsslon-5 I Post 1LI DlSpoSfIl AV = 30 mls
LO1 Ops Alllloiln = 2OU krii Po51 LO1 Dlspo9nl AV = flG0 nim
Posl TLI Dlsposal AV = 30 m/t Dellver a1 least 5 Ic argo 6
Posl LO1 Dlsposal AV = 860 mrs crew ot 4 on piloled mission
4.0 Surface Ops __ Stirlace Slay = 45 Days Surlace Slay = 180 Days
5.0 Earth Return - NTR reuse altitude = 500 km NTR reuse altilude = 500 km
Return 200 kg to earth Return 500 kg lo earth
Post TEI dlsposal AV = 194 mh1 Post TEI disposal AV = 194 m/r
T
-
Mlsslon Case I NTR Performs TLI
\c /
-
Mlsslon Case II NTR Perlorms TLI 6 LO1
Mlsslon Case IV - NtR Pettorms TLI, La,T EI, a, EOC
r I
1
NTP: System Concepts 348
LD Space Operations Overview vA7
11 ,\t;wxAwI;t ,;
.NTR Performs TLI, LO1 AV = 907 111lS
-Lonaest shale burn time 30 min & NTR
I
045 ~ aLyun ir Surface Stay Scparation
.1 HLLV Launch
-1601 Capabilily
AV = 3131 mls
LOR Space Based Operations Overview &7
'i, p/////;,,
'/';It
AV
NP-TlM-92 340
*
System Design Considerations
.;mr
I1 r$ ;/6 II I,', I
T
-
Expendable vs. Reusable
Operelions Complexity loo High ror Reurabllity
Pertomrance Maxhnlralbii Achieved WHh ExpPttdahlr MIsskm
sSl.ety Concerns Lessened With Expendable Missbi
-
Shielding Cansiderations - Malerid end ConstNcHan Considerations
KAVAU isk 9leld A)urnhnm L H I1~ec 9n~~q0w11 w mt~trio~t
Modllkd Disk ShleM Opllrnlzer Deslgn and Use 01 PIopeitanl FIIghl Use By 2005
Pmpellanl and Tankage IsogtM Construction f l s l n gF or Slriccli#ral
Lander Propellaiil and SINclure Conslttctalions
- -
Lnimch Vchlcin Consldernllons E~tgirieC ortfigurollon
Lunar Ulrecl Mission single vs ClUSIef
Smallest iscsich VeMek Necessary to 25kQSmVSrrt(
Cornptcle FLO Mission
Lunar Orbil Rendezvous
Comptele Reasonable Lunar Archilecture
Using Medium Sired Launch Vehlclc
-
Thermal Proieclion Considerations
Active Reldgerallon Too Heavy For Bcnellt b Abort WSshI f
Failed MLI 6 SOFl
-
Lander Conslderetions
Lunar Dlrect Mlsslon
2 Slage CryoStoraMe Removes Long Tern
Hydropen SIwage on OrbH
Lunar OrbH Rendezvous
1 112 Stage CryoXryo Oul-perlonns 2 Stage
Lander Conslslenlly in Past STV Studks
NTP: System Concepts 350 NP-IIM-92
a~ Orbit Rendezvous ConflguLauo-ns
Ih e chart below shows tho top sown caiitlidales ril Ihe I.uoilr Orbit llendczvous c:ciliiiflliratlriils WC
st;irtetl willi niqhlnt?.ri liossilili* (:niiliguriltluw III tlir:, catnoory. ;III~t \i~r~iigt~i I!I~IIIIII;I~i1:1IIfI s. ~L'SI~II
conslrainls arid operaliurial issues. tliat eiglileen was narrowed to tlin lollowilig SHVL'II Ih i! mssions
tliat utilized a cryogenic liquid oxygen and liqiiid liydrogeri TEI stage were extremely close iii
perlormance lo those missions using NTR lo perlorni the It1 him lherelorn. it was beiiellci;il to sliow
Ilie elirninatiori of an entire technology, IIS~o f a I 0x11 112 s1;ige. arid to show tlint a lunar mission caii
br! supported solely by NTll IHCIIIIOI~I~A~iio llior crilorrn Ilia1 rl~~~i~riacalcfiddi dalcs wn? III*I~IJIIII;IIICC!
at least 5.00 lonnes lo the lunar siirlace ofi a pilolerl rrrissinn Also eliminated in the eailler ~II~SuRl S
the study were two HI.1.V candidales We started with lour lII.1V candidates: 661. 10.51. 137t. arid 1351
Iniinch capacities. We narrowed that lield to Iwo candidates based wi pas1 STV analysis showlng tlic
1321 arid 1351 veliiclns virtually even on pcrtornmricc 01 the llrr~e1 11;it were lefl. Gl;t. 11151. 1351, we
nliiiiiiialRtl the 1051 becairse 01 study coii~ploxity arid lo (Iiiiw!~~tral1n1i :iI NII t cnii hn LII~IIIPoCn I1 11~
two extreme launch veliicles and. tlicrclore. everything iri ~)~Iw+!PII
Three 01 Ihe configuralions sl~owiib elow starled with a clustor of lhree 25Klbl NTR nriqt!lpq. brit with
huther analysis their perlormance was greatly enhanced by gning to a siiiyle erigirle configuralion
Also. two of the conltgriralions are two stage NlR conllqiir:~tions Tlin list NTFl stngo perlorms tlie
TLI burn and is then staged 011 to perlorin a lunar assist tl~.;l~r~s;ibl urn into IICIIO~~IIIsIpIa~c e lhl?
qecond NIR staQe lhon pcrlormr; tlie res1 nl Ilie riiis5ioll :ifid IV illso disposed 01 nflcr Ihc 1FI tiririi
*
Lunar Orbit Rendezvous Configurations
661 HCLV 1351 HLLV
Slack Mssa 254.15 253.25 128.56 265.45 267.83 131.73 281.60
Perlommm
Plloted 28.55 19.55 7 21 38 68 19 35 5.88 38.53
cueo 47.55 39.62 25.66 G1.52 44 93 23.69 60.39
J1197lu13 I1 In
NP-TIM-92 35 1 NTP: Svrtem Concepts
Lunar Orbit Rendezvous Configurations
11 I %' ,'# YNi /I I; p
NTR Performs TLI and Dlsposed LZT
NTR Performs TLI and Reused
11IU TIIU
LOI/TEI Slag@ isp pore ne"-
f I I
c&nent I 1 )
2 83
Lti2 1
V a 7
Lunar Orbit Rendezvous Configurations
- // ' ~IflMXd!/// k,?
NTR Performs TLI, LOI, TEI and Disposed 661 HLLV lb 1351 HLLV T
NTR Stage
Component
Slruclure
Tankage
Subsystems
Engine Slruclure
Englne 6.83
22.W m Shield
Conllngency (15%)
Total Ury 14.61 27.50
Propellotit 6373 123.09
.To tal Wet 78.34 150.59
~. -. - -. -J
352
NIP: System Concepts
Y-47
Lunar Orbit Rendezvous Configurations
NTR Performs TLI, LOI, TEI and EOC - 1351 HLLV /I r $dl, Y#~ll/t#?
T
NTR Stage -
010.0m -._- __
Ltl2 lank __ Component -I
Structure 2.91
Tonkage 9.70
Rendezvous LL DO& Subsystems 3.45
Sep. Plane Englne Structure 0 96
Englne 6.83
Sliield 4.50
Conllngency (15%) 4.25
olOOm
.-
LH2 Tank
Tolnl Dry 32.60
PtopnIIoiii 160.08
Tolol Wet 192.68
- - I
P-
(1) 75k Engine
Lunar Orbit Rendezvous Configurations
dk7
- /i .c~/xwrwi/
2 Stage NTR Performs TLI, LOI, TEI and Dispose 661 HLLV
0
05801~1
LH2 lank
NTR Stage 1 & 2
11.30 in 2.59
Inilkage 4.50
Subsystems 1.69
Ll12TankyJJm Engine Structure 0.76
Englne 14.91
(I) 25k Engine Shleld 1.50
Conllngency (15%)
llendezvous LL Dock
Sep Plane
OlOOfll Tolal Dry 29.84
.- Propellant 54.42
Total Wet 84.26
-__.
(3) 25k Engines' L60nt
NP-TIM-92 353
06 IO nl
I I17 Iniik
1.79
6.60
a.73
0.8 I
Engine 14.91
ander/Staqe Adapter Shield 1.50
(I) 75h I ngino - Conllngency (15%) 4.25
-
Tolal Dry 32.59
Propellanl 114.55
I I12 Tmk 147 14
- __ 1
. -nor11
(3) 25k Engines
*
Preliminary LD NTRTTLI Confiq,wations
JI~.@h:!62A8111h ,I I
NTF': System Concepts -92
4 7
NTR Reuse Examined in Study
w
fl.@l:$~m~lll
T
.Developed vehicle mass properties, payload capabllilles, space operatlons
-2 cases conslder reuse lor NTn only
I -2 cases consider mace based fully reusable vehicles
LOR Ulubn LD Mldon LOR Mlsalon LOR Mlrslon
TLI. EOC burn TLI. EOC burn TLI. LOI, TEl. EOC burns TU. LO1 TEl. EOC burn
Cluslor 01 125Llbl englnea Slnple 75kbl enplno
I
nsirse demenls: Reuse elements:
~ renngln es NTR englnm
Reuse olemenls: Reuse dements: m e r Lander
NTR mghea NTR englnes Crew Cabs Crew Cabs
I Notes: AausaMe Hardwaree lemenls deslaned tor 5 tnlsslon
NTR returns lo 500 km clrcular orblt between !nInl~n~
.Identified inlraslruclure needs (assumed exlsling)'
-STS for crew deilverylrelrleval
-SSF for refurb
-Capablllty for on-orbit reluollng or lank exchange
'InlraIINUdUre costs (elemenls b assoclaled operollons) were no1 Included In cos1 analysls
LH920819 REUSE OR0 RIILFS7
Reuse Cost Analysis
Lunar Orbit Rendezvous T
-1
r.rn- 1.00- Expendable N Lunar Direct .-
v) Expendable NTR
Reusable NTR
-3
- Reuse Reduces
Vehicle Recurring
Cost approximately
NTn Perlorins 1LI burn 50%
Ratlo (Plloled Flights: CI ------I
1O:l 5:1 1.1 1'5 1.10
nallo (Plloled.Fllgh!srCargo Only Flighls)
~
- Lunar Orbll Rende_z- vous
1
. 1.07 .unar Direct
I
ileus0 Iiwooses
Vehicle DDT&E
approximately 10%
NP-TIM-92
*
NTR/Cryo Reusable System Comparison
C %’,i‘cc XtiYt11,, i
T
Reusable Rendezvous & Docked
NTRlCryo LTS
Space Based 91
Study Derlved
\A
1
Rendezvous 6 Docked
LTS (2 135 I HLLVs)
Mars Evolution Key to Affordability dJ7
\l,@mmI; P o
T
Total Cost Breakeven Analysis 7
12
’: I
L’A.’, / i II r-- ---I- I
40% line represents shared
englne development program
61,4@$’;‘
I I I
0 .‘ 100 200 300 400
Total Mass Delivered (1)
Lowers Total Cost of Lunar Missions
Example: Splitting the engine developinenl cos1 between the lunar arid Mars
356 NP-TIM42
NTP: System Concepts
