Post on 30-May-2018
transcript
8/14/2019 NASA Ares I & V Overview - 2009
1/22
Ares I Overview
Phil Sum rallAdvanced Planning M anag
Ares ProjectsNASA MSFC
Masters Forum'ay 14, 2009
8/14/2019 NASA Ares I & V Overview - 2009
2/22
Crew
LunariLander Orion
S-IVB(One J-2 engine)108.9 mT( 2 4 0 .O K Ib m )L O X / L H 2
S- I I(Five J-2 engines)453.6 mT(1,000.OK Ibm)L O X / L H 2
SAC(Five F-1)1 ,769.0 m T
(3,900.OK Ibm)L O X / R P - 1
Upper Stage(One J-2X)e137.1 mT(302.2K Ibm)
L O X / L H 2
F One 5 -Segm entReusab le Solid
r Rocket Booster0(RSRB)
wo 4-Segmentreusable SolidIocket Booster: Z S R B ' s )
ill
122 m
(400 ft) 1
Bui ld ing o n a F oun da t ion o f P r oven T echn o lo g ie s- Launch V ehicle C om parisons - i
91 m300 ft)
Ptas
Z
2N 61 m
t,V (200 ft)
0
mT - metric tonsTLI - Trans-Lunar Injection
LEO - Low E arth Orbit.A.,a v
ltair"- A
rth Departurea g e ( E D S ) ( 1 J - 2 X )3 . 0 m T ( 5 5 7 . 7 K I b m ),X/LH2
Core Stage(Six RS-68 Engines)1 , 5 8 7 .3 m T( 3 , 4 9 9 . 5 K Ib m )L O X / L H 2
Two 5.5-SegmentReusable SolidRocket Booster(RSRB's)
c aLN
O30 m
(100 ft)
Saturn V Space Shuttle Ares I Ares V1 9 6 7 - 1 9 7 2 1981-Presen t F i r s t F f i ^ h t 2 0 1 5 F i r s t F l i g h t 2 0 1 8
Height: 1 10 .9 m (364 .0 ft) Height: 56.1 m (1 84 .2 ft) Height: 99 .1 m (325.0 ft) Height: 116.2 m (381.1 ft)G ross L ifto ff M ass : G ross L ifto ff M ass: G ross L ifto ff M ass : Gross Liftoff Mass :
2.948 .4 m T (6,500K Ibm ) 2,041.1 m T (4,500.OK Ibm )927.1 mT (2,044.OK Ibm) 3,704.5 mT (8,167.1K Ibm)Payload Capability: Payload Capability: Payload Capability: Payload Capability:
44.9 mT (99.OK Ibm) to TLI 25.0 mT (55.1 K Ibm) 25.5 mT (56.2K Ibm) 71.1 m T (156.7K Ibm) to TLI (with Ares 1)118.8 mT (262.OK Ibm ) to LEO to Low E arth Orbit (LEO) to LEO 62.8 mT (138.5K Ibm) to TLI
N a t i o n a l A e r o n a u t i c s a n d S p a c e A d m i n i s tr a t i o n ' 1 8 7 .7 m T ( 4 1 3 . 8 K I b m ) t o L E O 7 2 1 . 2
8/14/2019 NASA Ares I & V Overview - 2009
3/22
Fi r s t S tage(5-Segment SRB)
Ares 1
2 5 . 5 m T ( 5 6 .2 k I b m ) t o L E O
ffT
0
ST
T
e
Boeing Delta IV
i Employing Common Hardware to ReduceOperations Costs s ^
Note:Vehides Not To Scale
Upper Stage DerivedVehicle Systems
J -2X Upper S tage Enginet=
-s
' m o o 17 1I^
U.S. Air Force (USAF)RS-68B Engine
f rom Del ta IV RS -68
:r
low
0
i
E l e m e n t s fr o mSRB
Ares V
71.1 m T (156.7k Ibm ) to TL (with Ares 'I)63.0 m T (138 .5k Ibm ) to Direct TLI
187.7 mT (413.8k Ibm) to LEO
National Aeronautics and Space A dm inistration 721 .3
8/14/2019 NASA Ares I & V Overview - 2009
4/22
i
Ares I Elements s ^
Stack Integration 927.1 mT (2,044.OK Ibm)
gross liftoff mass (GLOM) 99.1 m (325.0 ft) in length NASA-led
Encapsulated Service Instrument unitModule (ESM) Panels . Primary Ares I control
_ v ion ics sys t em NASA Design
Boeing Production 0.8B
4 0rion CEV
Interstage
Upper Stage 137.1 mT (302.2K Ibm) LOX/LH 2 prop 5.5-m (18-ft) diameter Aluminum-Lithium (AI-Li) structures Instrument unit and interstage Reaction Control System (RCS) / roll
co ntrol for f irs t s tag e f l ight Primary Ares I control avionics system NASA Design/ Boeing Production ($1.146)
First Stage Derived from current
Shuttle RSRM/B Five segments/Polybutadiene
Acrylonitrile (PBAN) propellant Recoverable New forward adapter Avionics upgrades ATK Launch Systems
($1.96B)
Upper Stage Engine Saturn J-2 derived engine (J-2X) Expendable Pram and Whi tney Rocketdyne
($1.28B)National Aeronautics and Space A dm inistration 721 .4
8/14/2019 NASA Ares I & V Overview - 2009
5/22
ill
CompositeFrustum
ModernElectronics
j., ew 12-Fin
16orward Segment to
support Ares requirement
Same propellant as Shuttle
/PBAN)-Reformulated for
longer burn time
Same cases and joints as/ huttle, inhibitor geometrychange for better burn control
Tumble Motors'(from Shuttle)
Thrust: 15.8 MN
Burn Duration: 126 sec
Height: 53 m (174 ft)
Diameter: 3 . 7 m ( 1 2 ft )DAC 2 TR 6
National Aeronautics and Space A dm inistration
n ^
Mass: 733 mT (1,616 Ibm)rooster Decelerationlotors (from Shuttle)
Nozzle upgraded tosupport higher
motor performance
7721.5
ki W '
Same Aft Skirt and ThrustControl as Shuttle
8/14/2019 NASA Ares I & V Overview - 2009
6/22
He l ium Pres sur iza t ion Bot tl e s
Ins trum ent Un i t(Mo dern E lec t ron ics )
AI-Li Or thogr id T ank S t ruc tu re
LH 2 Tank
LOX Tank
Co mmonBulkhead
U llage Se t t ling M otors
^ a
f `' r. .
N{
T h r u s t Ve c t o r C o n t ro l
Com pos i t e In te r s tage
Ro l l Co nt ro l Sys tem
F e e d S y s te m s
Propellant Load: 138 mT (304K Ibm)
Total Mass: 156 mT (344K Ibm)Dry Mass: 16.3 mT (36K Ibm)Dry Mass (interstage): 4.1 mT (9K Ibm)
Length: 25.6 m (84 ft)
Diameter: 5.5 m (18 ft)LOX Tank Pressure: 50 psig
L H2 Tank Pressure: 42 psig
National Aeronautics and Space A dm inistration 7721.6
8/14/2019 NASA Ares I & V Overview - 2009
7/22
ThrustConeAvionics
II provide:
itrol (GN&C)
4vionics
Electrical Power: 5,145 Watts
National Aeronautics and Space A dm inistration 721 .7
8/14/2019 NASA Ares I & V Overview - 2009
8/22
s
i J-2X E ngineUsed on Aresl and A res V
Turbomachinery Based on J -2 S
Gas Generator Bas e d on
RS-68 de s i gn
Engine Controller Based directly or
and software arc
Regeneratively CoolE Based o n long h is tc
Mass: 2 . 5 m T ( 5 ,5 11 1Height: 4.7 m (15.4 ft)
Diameter: 3.05 m (10Thrust: 1,308K N (29,
Isp: 448 sec (vac)
Height: 4.7 m (15.4 ft
Diameter: 3.05 m (10
Operation Time: 500
Altitude Start / On-orbit Restart
Flexible Inlet Ducts Based on J -2 & J -2S duc t s
Open-Loop Pneumatic Control S im i la r to J -2
HIP-bonded MCC B a s e d o n R S - 6 8
dem ons t r a t ed t e chno logy
Metallic Nozzle Extension New d es ign
^.- Pratt & W hitneyW I F Awinil i o o n o iw g m s 0 x a n d
Pratt & Whitney Rocketdyn e, Inc.
Operational Life: 8 starts/ 2,600 sec
National Aeronautics and Space A dm inistration 721 .8
8/14/2019 NASA Ares I & V Overview - 2009
9/22
i l l
D em ons trate and collect key da ta toinform the A res I design:
Vehic le i n t eg r a tion , a s s e m b ly, and K S Claunch opera t ions
S tag ing / sepa ra t ion Rol l and ove ra l l veh ic le con t ro l Ae r o dyna m ics and veh ic le l oa d s
F ir s t s ta g e e n t r y dyna m ics fo r re cov e ry
Performan ce Data:
Ares I-X14.1 MN
Mach 4.7
39,600 m (130K ft)
816 mT (1,799K Ibm)
99.7 m (327 ft)
2.46 g
2 Ares15.8 MNMach 5.84
57,700 m (188K ft)
927 mT (2,044K Ibm)
99.1 m (325 ft)
3.79 g
i r
First Stage Max . Thrust (vacuum :
Max. Speed:
Staging A ltitude:
Liftoff W eight:
L e n g t h :
M ax. Acce leration:7721.9
8/14/2019 NASA Ares I & V Overview - 2009
10/22
A re s VOverv iew
Phil SumrallAdvanced Planning Manager
A res Pro jec tsNASA MSFC
Masters ForumMay 14 , 200 9
8/14/2019 NASA Ares I & V Overview - 2009
11/22
8/14/2019 NASA Ares I & V Overview - 2009
12/22
Same Aft Skirt and Thrust
Vector Control as Shuttle
' ^ 4A
ti - r
y
Same cases and joints
t^ as Shutt le
BoosterDecelerationMotors
Wide Throat
Nozzle
Each Booster:
M a s s : 7 9 1 . 5 t ( 1 ,7 4 4 . 9 k lb m )
Thrust: 16.86 MN (3.79 Mlbf)
Burn Duration: 126 sec
Height: 59 m (193 ft)
Diameter: 3.7 m (12 ft)
12-FinForward Segment
Same propellant as Shuttle(PBA N) Optimized forAres Application
Ares V SRB is ' Nosecone im ilar toSpace
Shut tle and A res lbut opt im ized for
Modern unar m iss ionsElectronics
National Aeronautics and Space A dm inistration 721.12
8/14/2019 NASA Ares I & V Overview - 2009
13/22
LO :
Forward Skirt &Core Stage Avionics
. .Usable Propellant: 1,587.3 mT (3,499.5k Ibm)Dry Mass: 157.6 mT (347.5k Ibm)Burnout Mass: 173.9 mT (383.4k Ibm)
Number of Enaines: 6d RS-68B
Core Stage
RS-68B Engines
A l u m i n u m - L i iC o m p o s it e d ^, ^.1 0 m ( 3 3 f t) o u te r d ia m e t e rDer ived from Shu t tl e Ex te rna l Tank
Engine Thrust Structure
Engine CompartmentNational Aeronautics and Space A dm inistration 721 13
8/14/2019 NASA Ares I & V Overview - 2009
14/22
* Redesigned turbinenozz les to inc reasem a xim u m p o w e rl eve l b y:z 2%
Re des igned t u rb ineseals to s ignif icant lyr e d u c e h e liu m u s a g Efor pre- launch
Othe r RS-68A up grades om a y b e i n c lu d e d :
Bea r ing m a t e r ia l c hang e N e w G a s G e n e r a t o r ig n i Im pr o ve d O x id i ze r Tu r bc
t em p s e n s o r Imp r o ve d ho t ga s s en so r 2n ds t a g e F u e l Tu r b o P u i
crack m i tiga t ion Cav i t a ti on supp re s s io n
E C U p a r ts u p g r a d e
Hel ium sp in -s t a rt duc t
redes ign , a long w i ths ta r t sequenc em odi fica t ions , to he lpm inim ize p re - ign i t ionfree hydrog en
I H i g he r e l e m e n tden s it y m a in in j ec to rim prov ing spe c i fi cim p u ls e b yz 2%and thrust by :z 4 %
Inc reased du ra t ioncapabi l i ty abla t ive nozzle
* R S - 6 8 A U p g r a d e sNational Aeronautics and Space A dm inistration 721 14
8/14/2019 NASA Ares I & V Overview - 2009
15/22
.--Altair (Lander) Adapter Usable Propellant: 2 5 1 . 9 m T ( 5 5 5 .2 k Ib m )Dry Mass: 2 4 . 2 m T ( 5 3 . 5 k Ib m )B u r n ou t M a s s :2 6 . 6 m T ( 5 8 . 7 k Ib m )Number of Engines: 1E n g in e Ty p e :J -2X
L H 2 Ta n k
Forward S k i r t/
I n s t r u m e n tUni t Avionics EDS J-2X Engine
.v .
Aluminum-LithiumAI-Lipropellant tankspro p Composite dry structure oiter Skirt
10 m (33 ft) outer diameter Derived from Ares I Upper Stage 4-day on-orbit loiter capability prior to Trans-Lunar Injection (TLI) Main ta ins O r ion /A l ta i r /E DS s t ack a t ti tude in Low E ar th O rb i t p rio r to T LI Burn
EDS provide 1.5 kW of power to Altair from launch to TLI
Interstage
rtank
A ft Sk i r t
L O X Ta n k
National Aeronautics and Space A dm inistration 721 15
8/14/2019 NASA Ares I & V Overview - 2009
16/22
ft
Upper Stage Engine Element challenge:Des ign an en g ine . . .b a s ed on a n evo lu ti on o f the Ap o l lo /Sa tu rn e r a J - 2 (G G cyc l e ,230 ,000 Ibf, 424 seconds ISp) . . .
i n c r ea s ed t o 2 94 ,0 00 Ib f ( 1 . 3M New t ons ) th ru s t . . .
i n c r ea s ed t o 4 4 8 s e conds o f spec i fi c im pu l se (h ighes t eve r I s pfor an engine of this class) ...
nearly two years faster than an engine of this class hasb e e n d e v e l o p e d .. .
and m ake i t wo rk for two d i ffe ren t veh ic les wi th two d i ffe ren tm i s s io ns , keep in g a s m uch com m ona l it y a s pos s ib l e .
466
4 6 0 Increased Pc Increased Density Injector
4 55 Added No zzle Extension to 92:1 Turbine E xhaust Gas Injection
4 50 Upgraded TIM & GG
r 45 -2 X Inc reased Pc
M 40 . Increased Nozzle 40:1 New TIM
435^ J2
4 3 0 FlightC onri guration
425
420
20 0 20 40 60 80 0 0
Thrust (k)
320
National Aeronautics and Space A dm inistration 721 16
8/14/2019 NASA Ares I & V Overview - 2009
17/22
21.7 m
AL
F
23.2 m
10m-*
116 .2 m
71.3 m
1 0 r
58 .7 m
S R R ( 2 0 1 0 ) Ad di tiona l pe r fo rm anc e cap ab i li ty if nee ded fo r m arg in
o r r equ ir em en t s A llow s fo r com pe t it iv e a cqu is i tion env i ronm en t fo r b oos
Vehicle 51 .0.48 approved in 200 8 6 E n g i n e C o r e , 5 . 5 S e g m e n t P B A N s t e e l c a s e b o o s te r P rov ides a rch itec tu re c losure w i th m arg in
Ap proved m aintaining Vehicle 51 .0.4 7 withcom posite HT PB b ooster as Ares V option
F ina l dec i s io n o n A re s V b o os t e r a t Co n s t e l la t io n L una r
Near Term Plan to Ma intain Booster Options F u n d k e y t e c hn o l o g y a r e a s : c o m p o s i te c a s e s , H T P Bpropel lant character iza t ion C om pet i tive Phase 1 indus t ry s tud ies
NOTE: These are MEA N numbers
National Aeronautics and Space A dm inistration 721 17
8/14/2019 NASA Ares I & V Overview - 2009
18/22
Tank Ba rrel Structural Test
Ares I
Ares I , F i r s t S t age , & Up per S tage PDR scom ple te in '08 N u m e r o u s F i rs t S ta g e d e v e l o p m e n t a n d
s ta t ic m oto r cas t ing & f ir ing t e s t s , w indtunne l , nozz le , m a te r ia l s , pa rachu te d roptes t s comple te
Al l Ares I -X ha rdw are a t K SC fo r`09 launch
C o m p l e te d J - 2 X P D R i n '0 7 , C D R i n '0 8 S S C A - 1 t e s t s t a n d c o n v e r t e d , A - 3 s t a n d
con s t ruc tion under wa y to supp or t J -2X N u m e r o u s h e rit a g e / c o m p o n e n t /
s u b s c a l e /p o w e r p a c k te s t s a n d C F Dc o m p l e te d in s u p p o r t o f J -2 Xt u rb o m a c h in e r y, c o m b u s t io n d e v i c e s , e t c .
J -2X c as t ing /m ach in ing t r ia l s unde rway / long- lead pa r t s p rocured
Ares V Sub sca le m a in in j ec to r te s t s , ana lys i s
c o n d u c t e d o n R S - 6 8 B L C C R e s t a b l is h e s P O D c o n c e p t '0 8 RFP fo r con cep t d e fin it ion i s sued `09
National Aeronautics and Space A dm inistration or more information go to www.nasa.gov/ares 7721.18
8/14/2019 NASA Ares I & V Overview - 2009
19/22 ational Aeronautics and Space Adm inistration 721 19
i l l
8/14/2019 NASA Ares I & V Overview - 2009
20/22
f
i l l
Integ rating techn ical products
and p eop le W ithin A res
W ith other Co ns te l la t ion P rojects
W ith other s take holders
Ensu ring ownership andaccountability
M anag ing workload M anaging com m unication
C on trol ling dis t r ibut ion ofsen s i tive in form at ion
M ana ging in te rna l and ex te rna lcom m u n ica t ions i n the In t e rne t a ge
Balanc ing ne ed to redu ce costswith the n eed to ma intain am otivated, knowledg eable
workforceNational Aeronautics and Space A dm inistration 721 20
F ll U d t di g P g ti
8/14/2019 NASA Ares I & V Overview - 2009
21/22
Ending Shuttle ops, completing ISS,transition to lunar exploration
Infrastructure sustainment facilities
workforce, industrial base Accommodating sciencelexpIoration
Fully Understanding Programmaticand Technical Challenges
U sab le A na logs A po llo , Shu ttle , ISS ? Dual-Launch Architecture ground ops, on-orbit A m u c h la rg e r ro c k e t A r e s V Reduced touch labor, simplified operations International and commercial participation
Sustained operations with a pay-as-you-go budget
s
National Aeronautics and Space A dm inistration 721.21
8/14/2019 NASA Ares I & V Overview - 2009
22/22
i
www.nasa.gov/ares