NASA Ares I & V Overview - 2009

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


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


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


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


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


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


7/22

ThrustConeAvionics

II provide:

itrol (GN&C)

4vionics

Electrical Power: 5,145 Watts



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



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


10/22

A re s VOverv iew

Phil SumrallAdvanced Planning Manager

A res Pro jec tsNASA MSFC

Masters ForumMay 14 , 200 9


11/22


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



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


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


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


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



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



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


19/22 ational Aeronautics and Space Adm inistration 721 19

i l l


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


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



22/22

i

www.nasa.gov/ares

Date post:	30-May-2018
Category:	Documents
Upload:	orion2015
View:	214 times
Download:	0 times

NASA Ares I & V Overview - 2009

Documents