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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