Stough, Robert

NASA Technical Reports Server

Robert Stough
SLS Spacecraft/Payload 
Integration & Evolution
20 July 2018
SPACE LAUNCH SYSTEM
0497
Secondary Payload Accommodations 
in Block 1 and Beyond
https://ntrs.nasa.gov/search.jsp?R=20180006347 2019-08-31T18:39:53+00:00Z
VOLUME
• Three times more volume than any contemporary 
heavy lift vehicle
• Only vehicle that can carry the Orion and a 
co-manifested payload to the Moon
SLS ENABLES HUMAN AND 
ROBOTIC EXPLORATION
Orion 
with 
Science
Missions
8m fairing 
with large 
aperture 
telescope
• Enables larger payloads to deep space destinations
• Reduce transit times by half or more to the outer solar system
• Game-changing benefits for extremely high-energy missions
DESTINATIONS
• Block 1: Can launch more mass than any 
contemporary launch vehicle
• Block 2: Mars-enabling capability of greater than 
45 metric tons to Trans Lunar Injection
MASS
Contemporary 
Heavy Lift
SLS Block 1 
Exploration 
Class
SLS Block 2 
Exploration 
Class
0497
SLS EVOLVABILITY
0497
Foundation for 
a generation 
of deep space 
exploration
** Not including Orion/Service
Module volume
Trans-Lunar Injection 
(TLI) is a propulsive maneuver 
used to set a spacecraft on a 
trajectory that will cause it to 
arrive at the Moon. A spacecraft 
performs TLI to begin a lunar 
transfer from a low circular 
parking orbit around Earth. 
The numbers depicted here 
indicate the mass capability at 
the Trans-Lunar Injection point.
Universal 
Stage Adapter
Universal 
Stage Adapter
Height 365 ft327 ft364 ft322 ft
Launch Abort 
System
RS-25 Engines
Core StageCore Stage
SLS Block 2 Cargo
Interstage
Evolved
Boosters
Solid
Rocket
Boosters
Exploration 
Upper Stage
SLS Block 1
Orion
Launch Vehicle
Stage Adapter
Interim Cryogenic
Propulsion Stage
Exploration 
Upper Stage
Cargo Fairing
Interstage
Solid
Rocket
Boosters
Core Stage
SLS Block 1B Crew SLS Block 1B Cargo
Core Stage
Interstage
Evolved
Boosters
Exploration 
Upper Stage
Cargo Fairing
SLS Block 2 Crew
364 ft
Orion Orion
Launch Abort 
System
Launch Abort 
System
Maximum Thrust
Payload Volume
Payload to TLI/Moon
31,950 ft3 (905 m3)18,970 ft3 (537 m3)10,100 ft3 (286m3)**N/A**
>  45 t (99k lbs) 37–40 t (81k–88k lbs)34–37 t (74k–81k lbs)> 26 t (57k lbs)
10,100 ft3 (286m3)**
>  45 t (99k lbs) 
11.9M lbs8.8M lbs8.8M lbs8.8M lbs 11.9M lbs
SLS Block 1
Elements
(Crew Configuration)
Stages 
(Core)
B
oo
st
er
B
oo
st
er
Stages 
(Core)
B
oo
st
er
B
oo
st
er
Orion
Spacecraft
5m 
Payload Fairing 
(PLF)
Primary 
Payload 
(PPL)
SLS Block 1
Elements
(Cargo Configuration)
Secondary Payload (SPL) 
Up to 17 places ≤12U
Launch Vehicle Stage Adapter 
(LVSA)
Interim Cryogenic Propulsion Stage 
(ICPS)
Integrated 
Spacecraft/Payload 
Element 
(ISPE)
ISPE
Orion Stage Adapter (OSA)
Payload 
Adapter 
(PLA)
SLS BLOCK 1 PAYLOAD ACCOMODATIONS
6U
14kg
12U
25kg
PROGRESS TOWARD EM-1
0497
SLS BLOCK 1B/2 PAYLOAD ACCOMODATIONS
Stages 
(EUS)
Stages 
(Core)
B
oo
st
er
B
oo
st
er
Stages 
(Core)
B
oo
st
er
B
oo
st
er
Universal 
Stage 
Adapter 
(USA)
Co-Manifested 
Payload
(CPL)
Primary 
Payload 
(PPL)
Stages 
(EUS)
Secondary Payloads (SPL)
Up to 7 places, ≤27U
Payload Adapter 
(PLA)
ISPE 8.4m 
Payload Fairing 
(PLF)
SLS Block 1B
Elements
(Crew Configuration)
SLS Block 1B
Elements
(Cargo Configuration)
Orion
Spacecraft
Secondary Payload (SPL) 
Up to 21 places ≤27U
6U
12U
27U
PROGRESS TOWARD FUTURE FLIGHTS
Rendered image of USA 0458
0458
0497
SAMPLE DEPLOYMENT LOCATIONS
0496


Space Launch System: Secondary Payload Accommodations in Block 1 and Beyond

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