SPACE LAUNCH SYSTEM

National Aeronautics and Space Administration

www.nasa.gov/sls

5 . . . 4 . . . 3 . . . 2 . . . 1 . . .

MISSION CAPABILITIES FOR EXPLORATION

Stephen D. CreechSpace Launch System Program

https://ntrs.nasa.gov/search.jsp?R=20150021457 2019-12-27T00:54:36+00:00Z

www.nasa.gov/sls

130 t

RS-25 Engines

105 t

Core StageCore Stage

70 t

SLS Block 2 CargoSLS Block 1B Crew SLS Block 1B Cargo

Interstage

Advanced

Boosters

Solid

Rocket

Boosters

Exploration

Upper Stage

105 t

SLS Block 1

Orion

Launch

Abort

System

Launch Vehicle

Stage Adapter

Interim Cryogenic

Propulsion Stage

Exploration

Upper Stage

Cargo FairingCargo Fairing

Interstage

Universal

Stage Adapter

Solid

Rocket

Boosters

Core Stage

www.nasa.gov/sls8747_CDR_Town_Hall.2

SLS Evolution Overview

www.nasa.gov/sls

THE SPACE LAUNCH SYSTEM’S PATH TO THE PAD

8414

2011 2012 2013 2014 2015 2016 2017 2018

ConceptStudies

Design & DevelopmentFinal Design& Fabrication

System Assembly, Integration and Test, Launch Checkout

✔ ✔✔ ✔Mission

Concept Review

Critical

Design ReviewPreliminary

Design Review

Design

Certification

Review

Launch

AvailabilitySystem

Requirements

Review/System

Definition Review

Key

Decision

Point-C

Booster

Development

Test

Booster

Assembly

at KSC

Booster

Qualification

Tests

RS-25

Flight

Testing

Begins

Core

Stage

Assembly

Complete

Core Stage

Production

Begins

Production

of Adapter

for Orion

Flight Test

SLS

Launch

Readiness

SLS

Design

Chosen

RS-25

Development

Testing

Begins

Engines

Delivered

to

Inventory

Manufacturing

Tooling

Installation

Core

Stage

Structural

Testing

Boosters

Fabrication

Complete

With design and development work

mostly complete, the SLS Program is

now building and testing components

of the world’s most powerful rocket to

be ready for launch in 2018. Each of

these steps advance NASA on the

Journey to Mars.

Core

Stage

Test-Firing

✔

Integrated

Upper

Stage

Structural

Testing

Upper

Stage

Production

Begins

www.nasa.gov/sls

• SLS initial

configuration offers

Block 1 to LEO.

• Future

configurations offer

Block 1B and

Block 2 to LEO.

• Mass capability

benefits mean

larger payloads to

any destination.

Medium/Intermediate Heavy Super Heavy

100’

200’

300’

Retired

Retired

ULA

Atlas V 551

SpaceX

Falcon 9

ULA

Delta IV H

NASA

Space Shuttle

NASA

Block 1

NASA

Block 2

NASA

Saturn V

0

20

40

60

80

100

120

140

160

Pa

ylo

ad

Ma

ss

(m

T)

Mass (mT)

SLS Mass Lift Capability

8736_National_Space_Symposium_4

www.nasa.gov/sls

SLS Block 1B & Mission Element Concepts Under Study

5

Mission concepts

with Universal Stage Adaptor

Co

re S

tag

e / B

oo

ster

sE

xplo

rati

on

Up

per

Sta

ge

Mis

sio

n E

lem

ents

Mission concepts

with 8m and 10m fairings

total mission volume = ~

Orion with short-

duration hab module

30’ tall x 27.6’ dia

400m3

5m fairing w/robotic

lunar lander & short-

duration hab module

600m3

Science

Missions

400m3

ARM Mission

400m3

8m fairing with large

aperture telescope

1200m3

10m fairing w/notional

Mars payload

1800m3

www.nasa.gov/sls

0.00

10.00

20.00

30.00

40.00

50.00

60.00

70.00

-10 0 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150

NetPayload

SystemM

ass(m

t)

Characteris cEnergy,C3(km2/s2)

SLSBlock1-Orion+iCPS

SLSBlock1-5.0mFairing+iCPS

SLSBlock1B-8.4mFairing+EUS

SLSBlock2B-8.4mFairing+EUS+AdvancedBoosters(min-max)

Exis ngLaunchVehicles

EuropaClassMission

SLS Characteristic Energy

Jupiter

Mars

Saturn via JGA Saturn/

UranusDirect

EM-1

Europa

Lunar

www.nasa.gov/sls

Europa Trajectory Comparison

Launch(6/5/22)

JOI (5/23/24)

DSM(7/10/22)

VGA(5/14/22)

EGA-2(10/24/25)

EGA-1(10/24/23)

Jupiter’sOrbit

JOI (4/4/28)

Launch(11/21/21)

Atlas V 551: VEEGA SLS: Direct

REDUCES TRANSIT TIME TO EUROPA BY HALF

8736_National_Space_Symposium_7

www.nasa.gov/sls

Secondary Payload Capability

• Block 1 vehicle offers at least thirteen 6U

payload locations

• 6U volume/mass is the current standard (14

kg payload mass)

• Payloads will be “off” from roll-out through

Orion separation and payload deployment

• Payload Deployment System Sequencer;

payload deployment will begin with pre-

loaded sequence following MPCV

separation and ICPS disposal burn

• Payload requirements captured in Interface

Definition and Requirements Document

• Block 1B and 2 vehicles offer up to six

larger, ESPA-class secondary payload (

>180 kg ) accommodations

8736_National_Space_Symposium_8

ESPA Ring

Secondary Payloads

www.nasa.gov/sls

www.nasa.gov/sls

Game-changing Vehicle For Exploration

Human

Missions

to Mars

Europa Exploration

Ultra-Large Space Telescopes

Mars

Sample

Return

Enceladus Geyser Sample Return

Interstellar Probe

Asteroid

Redirect Mission

NASA’s Space Launch SystemSpace Stations

www.nasa.gov/sls

Summary

• SLS provides capability for human exploration missions.

– Block 1 configuration enables initial flight tests.

– Evolved configurations enable missions including humans to Mars.

• SLS offers unrivaled benefits for a variety of missions.

– Block 1 provides greater mass lift than any contemporary launch

vehicle; Block 2 offers greater lift than any launch vehicle, ever.

– With 8.4m and 10m fairings, SLS will over greater volume lift

capability than any other vehicle.

– Initial ICPS configuration and future evolution will offer

highest-ever C3.

– Updated Mission Planner’s Guide provides capabilities information.

• SLS is currently on schedule for first launch.

– Critical design review completed in July 2015;

SLS is now in implementation.

– Manufacture and testing are currently underway.

– Hardware now exists representing all SLS elements.

8736_National_Space_Sym

posium_11