https://ntrs.nasa.gov/search.jsp?R=20100021953 2020-08-03T01:15:56+00:00Z

Constellation Launch Vehicle Elements

Stennis Space Center

I j Composite Shroud

LAS

Crew Exploration Vehicle (CEV)(Crew Module / Service Module)

Spacecraft AdapterInstrument Unit

Forward SkirtY

Upper Stage

J-2X Upper Stage Engine

Interstage

Forward Frustum

w.j

First Stage+^ (5-Segment Reusable Solida Rocket Booster (RSRB))

151n

a

Crew Launch Vehicle

LSAM

EDS StageLOx/LH2One J2S+ EngineAl-Li Tanks/Structures

Interstage

Core StageLOx/LH2Five RS-68 EnginesAl-Li Tanks/Structures

Two 5-Segment RSRBs

Cargo Launch Vehicle

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nnis

If k

J.

Space Center

SurIm

aceMission Crew

(7 -180 Days) Transfer toLLO

Crew Transfer to

Crew Earth -^

Transfer to (4 Days) jSurface I

LSAM Ascent Stage

LLO 100 km - - s Expended – Lunar Surface

............... ............................................-,:, I.,: ''^^ rti....................., ....^ri r•, ............................

tch^EN-T ...................:

LSAM Lunar Exploration1 (c 2018)

Transfer toLLO f

(4 days) - , * ^^ Expended – (Where? – TBD)

^u

LeO 296 km — EDS Qrion ISS Crew/Car o (c 2014) __

(160 nmi) ,/^ '/► 9

rr ' /' `ice ExpendedI

Expended – Ocean

– Ocean

Ares V

Ares I Recovered–Ocean

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.........

EARTH_.......111111 ^^::.I1111I IL -111111111111111111111111...:"

SM Disposal._mk. Mass 4,372 kg—

Delta V 15 m/s RCS

Earth Return– DirectEntry to Service Module

Land (Water) Expended –Ocean

L'-"- Recovered_ _ - _ - Land – Reused

- -:^• 4

Propulsion Test Facility Trades for J-2X Altitude TestingAltitude Test Facility Requirements

Stennis Space Center

120”

♦ A3 Facility Requirements• Start/Run Pressure: 0.16-0.4 psia (100-80

Kft)

• Run Duration: 550 sec

• Gimbal Angle: 5° (square pattern)

• Maximum Thrust Load: 1.0 Mlbf (vertical)

• Provide maximum flexibility for future testconfigurations

− Sea-level testing

− Stage testing

• Utilize existing propulsion testinfrastructure, including cryogenics,barges, high pressure water, highpressure gas, engine assembly andwarehousing facilities, skilled workforce,etc.

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A-3 Altitude Test Facility - rr^^^^ k

Meeting J-2X Project RequirementsStennis Space Center

• Design• Simplicity of “open diffuser” eliminates need for

complex spray condensing chamber, dewatering &exhaust systems

• Design maximizes use of commercially availableindustrial components

• Key design elements based on establishedtraditional rocket diffuser and chemical steamgenerator concepts supported by extensiveoperational data (40+ years)

• Early design risk mitigation thru testing of subscalediffuser and chemical steam generators at SSC

• SSC Location Benefits• Experienced test crews available• Enables workforce flexing across test stands• Enables efficient utilization of SSC’s extensive

propulsion test infrastructure• Collocation of J-2X test facilities with engine

assembly, integration and warehousing facilityreduces log istics costs

A3 g ives NASA at least one new large sealevel & altitude ca pable test stand for thenext 40 years

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A3 Test Stand 3-D Layout ri^^^ o

Test Cell and Thrust Takeout ^f q

Stennis Space Center

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A3 Test Stand 3-D Layout ri^^^ o

Engine Deck and Superstructure ^f q

Stennis Space Center

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A3 Test Stand 3-D Layout ri^^^ o

Structure and Altitude Support Systems ^f q

Stennis Space Center

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Steam Supply

♦ A3 Steam System Schematic Diagram

First Stage EjectorSteam Supply LOX Feed

IPA Feed

Water Feed

Steam

2nd Stage Ejector

"- Typical 3-unit CSG Module Output

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2^^41 Chemical Steam Generators

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Chemical Steam Generators

Stennis Space Center

♦ CSG cans for facility operation risk mitigate testing have been fabricated andtested

Development CSG CanNational Aeronautics and Space Administration

Subscale Diffuser— Stennis Space Center

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Stennis A3 Site LocationStennis Space Center

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A3 Construction SiteStennis Space Center

15

A3 Construction SiteStennis Space Center

16

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