Calfee, Chris

Smith, David Alan

NASA Technical Reports Server

www.nasa.gov
SLS Mission Planners Guide (MPG) 
Overview
David Alan Smith
Advanced Development Office (XP70)
24 February 2014
1
https://ntrs.nasa.gov/search.jsp?R=20140008794 2019-08-31T20:22:19+00:00Z
• Objective
– Provide a summary overview of draft SLS Mission Planners Guide (MPG)
• Outline
– Section 1‐2: Purpose and Scope
– Section 3: SLS Configuration Overview 
– Section 4: SLS Mission Design
– Section 5: Environments 
– Section 6: Launch Vehicle Interfaces
– Section 7: KSC Payload Launch Facilities
• Approach
– “Inner Loop” (SLS Program) uses its Design Analysis Cycle (DAC) to develop 
Exploration Mission 1 (EM‐1) for first flight in 2017
– “Outer Loop” (SLS Evolvability) uses SLS DAC data to establish potential performance 
of SLS Block upgrades
– Outer Loop analysis based on Inner Loop data provides the basis for the current 
version of this MPG Overview
2
Introduction
1: PURPOSE 
2: SCOPE
SLS Mission Planners Guide Section 1‐2
3
• Serves as a information resource between NASA, industry, and the 
scientific community for understanding potential range of SLS 
mission capture
• Promotes two‐way dialogue between developers and users to most 
efficiently evolve SLS mission/payload capabilities 
• Those requiring additional mission planning information contact Mr. 
Steve Creech, SLS Assistant Program Manager, Strategy and 
Partnerships (steve.creech@nasa.gov)
4
Mission Planners Guide
SLS CONFIGURATION OVERVIEW 
SLS Mission Planners Guide Section 3
5
SLS Performance and Mission Capture Benefits 
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130t  
Blk 2 
70t  
Blk 1 
SLS 
0"
5"
10"
15"
20"
25"
30"
'10" 0" 10" 20" 30" 40" 50" 60" 70" 80" 90" 100" 110" 120" 130" 140" 150" 160" 170" 180"
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"Block"1"SLS"with"DCSS"
"Delta"IV'H"
"Atlas"V"551"
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• Asteroid Redirect 
Mission 
• Mars Sample Return 
• Jupiter Europa Orbiter 
• Saturn/Titan Sample 
Return 
• Ice Giant Explora on 
• Outer Planet Sample 
Return 
• Large Telescopes 
• In‐Space Infrastructure 
Larger Interplanetary Science Payloads  
• 3 to 4 mes the mass to des na on over ELVs 
• Single launch of larger payload reduces payload complexity 
Launch 
(6/5/22) 
JOI   
   (5/23/24) 
DSM 
   (7/10/22) 
VGA 
          (5/14/22) 
EGA-2 
 (10/24/5) 
EGA-1 
  (10/24/23) 
Jupiter s 
Orbit   
JOI   
   (4/4/28) 
Launch 
(11/21/21) 
Atlas 551, 6.4 years 
Shorter Transit Times to Des na on 
SLS Blk 1, 1.9 years 
C3=15 km2/s2 C3=82 km2/s2 
2 Earth Flybys 
0 Earth Flybys 
• Europa Clipper flight me reduced 70% over Atlas 551  
• Longer launch window provides more mission margin 
• Significantly reduced cost for each year of transit reduced 
Increased Mass/Volume Payload to Orbit 
Enhanced Reliability and Safety 
5m 
ELV/SLS 
8.4m 
SLS 
10m 
SLS 
• Up to 5 mes greater mass to orbit capability (SLS 
Block 1) over Delta, Atlas and Falcon 
• Increases payload mass margins and 
offers greater propellant loads 
• Addi onal volume simplifies orbital opera ons (less 
orbital assembly for large spacecra ) 
• Significantly less 
me in Earth Orbit 
reduces propellant  
boil‐off 
• Eliminates Earth 
flyby nuclear safety 
concern 
• Accommodates a range of 
exis ng (5m) and new 
(8.4m‐10m) fairings 
• Up to 6 mes greater 
payload volume over 
current launch vehicles 
SLS Block 1 Configuration: 70t Crew Mission
Launch Abort System 
Launch Vehicle/ 
Stage Adapter 
Core Stage 
RS-25 
Engines (4) 
Service Module 
MPCV/Stage Adapter 
Solid 
Rocket  
Boosters 
(2) 
Interim Cryogenic  
Propulsion Stage 
Encapsulated Service Module Panels 
Crew Module 
Orion Multi-
Purpose 
Crew Vehicle 
(MPCV) 
Spacecraft Adapter 
SLS 10003 70t DAC2 
• Focus of Exploration Mission‐1 (EM‐1) Flight in 2017
– Core Stage (tankage and engines derived from Shuttle)
– Uses existing Upper Stage (derived from Delta‐IV)
– Uses 5 segment RSRMs (derived from Shuttle)
– Uses existing 5m diameter fairings (cargo)
7
Block 1 Payload Overview
SLS DAC3 PoD Configuration
Launch Vehicle Stage 
Adapter (LVSA)
MPCV Stage Adapter (MSA)
Spacecraft Adapter (SA)
Tri-Sector 
Fairing Deployment
Injected Payload
Same part as below/left
Shown twice for clarity
Same part as above/right
Shown twice for clarity
MPCV Stage Adapter
Crew Module
European Service Module
Encapsulated Service 
Module Panels 
Same part as above/right
Shown twice for clarity
Interim Cryogenic 
Propulsion Stage (ICPS)
Crew Module
Launch Abort 
System (LAS)
SLS Block 1
8
9SLS Block 1 (70t to LEO) Development
SLS Post Block 1 Configuration: 105/130t Cargo
Payload Fairing 
Interstage 
Core Stage 
Advanced Boosters (2)  
Upper Stage 
Cargo Payload Adapter 
RS-25 
Engines 
SLS 2100X 130t DAC2 Cargo 
• Ultimate evolutionary goal post SLS Block 1 EM‐1 and EM‐2 flights
– Minimal changes to Block 1 Core Stage
– New Upper Stage
– New Boosters
– Existing and new Fairings
10
SLS Evolvability Point of Departure Concepts
11
Block 1 
(70t LEO Class)
Block 1B 
(105t LEO Class)
Block 2B
(130t LEO Class)
Vehicle ID
Core
Booster
Upper Stage
Payload
10003 10500 28000 27500 27000 25000A/26000A/26001A
8.4m Common Core 8.4m Common Core 8.4m Common Core
5 Segment Shuttle 
Booster
5 Segment Shuttle 
Booster
Advanced Booster
ICPS Common US Common US
Orion 5m Payload Orion 5m Payload 8.4m Payload 10m Payload
SLS Configuration
Interim 
Cryogenic 
Propulsion 
Stage (ICPS)
Upper Stage 
(US)
Note: Dimensions for reference only
Revision: 2‐21‐14
Under 
Development
17.8’ 
100’ 
200’ 
300’ 
400’ 
210.8’ 
57.7’ 
370.5’67’ 
102’ 
Upper Stage  
≤ 62.7’ 
≤ 62.7’ 
27.3’ 
≥ 62.7’ 
Core Stage  
4.1: MISSION TRAJECTORIES 
4.2: MISSION PERFORMANCE
SLS Mission Planners Guide Section 4
12
2 
NASA’s Capabilities Driven Framework
13
14
SLS Evolvability Mission Cases
Core Burnout/US Separa on 
Fairing Je son 
Booster Je son 
Li off Booster Splashdown 
US MECO/Orbital 
Inser on 
Ellip cal Loiter 
LEO 
Loiter 
SLS Evolvability Mission Cases 
SLS 
Earth Escape 
LEO Ellip cal or Circular Injec on 
(e.g., Asteroids, Mars, Outer Planets, ESL1/L2) 
Earth Orbit 
LEO Circulariza on/Injec on 
(e.g., LEO Aggrega on, LEO 
Parking, HEO) 
Lunar Vicinity 
LEO Circulariza on/Lunar Injec on/
Lunar Braking 
(e.g., LLO, DRO, EML1/L2) 
US Disposal 
Lunar Orbit Inser on 
(LLO Op on) 
Mid Course Correc on 
(LLO Op on) 
Trans Outer Planet Injec on 
US Disposal 
Trans Lunar 
Injec on 
US MECO/Orbital 
Inser on 
Core Splashdown 
Revision: 2‐21‐14 
Ascent  
Common to all Cases 
US Disposal 
(LLO Op on) 
• SLS launch to spacecraft separation 
– Block 1 ICPS is strictly an in‐space stage, and can perform 3 engine starts
– Block 1B US is ascent as well as in‐space burns, and can perform ≥3 engine starts
• Ascent communications and tracking use standard KSC range 
services
• Command and telemetry through TDRS S‐band 
• Core Stage must burn out with a ballistic trajectory and avoid 
landmasses on impact
• Fairing separation jettisoned when the free molecular heating rate 
drops below 0.1 BTU/ft2 sec
15
Ascent Profiles
16
Ascent Profiles
Block 1 (ICPS) 
Nominal Ascent Profile
US Ascent Burn 
1st of 5 starts 20 sec a er 
separa on 
Core Burnout/US 
Separa on 
Time of burnout ~ 492 sec 
Fairing Je son 
Je son @ 3‐sigma <0.1 BTU/ 2‐sec 
Booster Je son 
Time of je son = 136.24 sec  
Li off Booster Splashdown Core Splashdown 
US Injec on 
2nd  of 5 starts 
Op miza on/LOI 
3rd  of 5 starts 
Payload Separa on/ 
US Disposal 
RCS disposal 
Course Correc on 
As Needed 
Block 1B/2B (US) 
Nominal Ascent Profile
• SLS Mission Performance Groundrule
– Performance data has appropriate margins built in for mass growth allowance, flight 
performance reserve, and program managers reserve
• LEO or LEO Net Payload is defined as encompassing the spacecraft or cargo 
element mass delivered on‐orbit
– Does not include an upper stage or adapter mass
• Payload System Mass is defined as encompassing the mass of both the 
spacecraft/cargo and any associated vehicle adapter(s) required
– SLS Performance is given in terms of Net Payload System Mass
Key Mission Performance Definitions
17
Earth Escape Performance
18
ENVIRONMENTS
SLS Mission Planners Guide Section 5
19
• Current payload acceleration estimates: 
• Vehicle dynamic coupled loads analysis can be performed to 
generate more specific environments once payload and adapter 
concepts are more mature 
20
Payload Loads Environment
80 
90 
100 
110 
120 
130 
140 
10 100 1000 10000 
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Frequency, Hz 
Based on SLS Block 1 Externalwith ELV Noise Reduc on 
Goal, 40‐50% Fill Factor (OASPL 137.2 dB) 
SLS Goal
Payload Acoustic Environment
21
• Sources of shock environment at the payload/launch vehicle interface
– Booster separation
– Core stage/upper stage separation
– Fairing separation
– Payload/adapter separation
• Similar to ELVs, shock levels due to booster and core stage/upper stage separation 
are highly attenuated through the vehicle structure before reaching the 
payload/vehicle interface
• Shock levels due to fairing and payload/adapter separation are characteristically 
the primary drivers due to proximity with payload/adapter levels being the higher
• SLS cargo vehicles as a goal will utilize existing ELV fairings and payload adapters
• Shock levels for ELV fairing and payload/adapter separation events are readily 
available in ELV Payload Planners Guides
22
Shock Environment
• Payloads will be protected from aerodynamic heating through the 
application of external TPS and attenuation of heating by the 
fairing walls and internal acoustic protection system
• Current estimates of aerodynamic heating are consistent with 
those of other ELV
• Internal heat flux will be no greater than 0.1 BTU/ft2‐sec typical of 
current ELV
• Payload fairing is not jettisoned until the external heat flux drops 
below 0.1 BTU/ft2‐sec
23
Payload Ascent Thermal Environment
• SLS fairings can be vented during the ascent phase by proper 
implementation of vent doors to insure an acceptable 
depressurization rate of the payload compartment
• Specific venting scheme designs will depend on the mission 
trajectory and payload depressurization rate requirement
24
Payload Ascent Venting Environment
• Typical sources of ascent contamination include:  molecular 
outgassing, NVR redistribution, particle redistribution, fairing 
separation, booster separation, core stage separation, and upper 
stage reaction control system
• Except for booster & core stage separation contamination sources, 
environments will be consistent with current industry available 
fairing provisions, cleanliness procedures and deposition 
requirements
• Since the payload is fully encapsulate by the fairing far forward of 
the sources, booster and core stage separation system potential 
debris contamination products will not pose a threat to the 
spacecraft
25
Payload Ascent Contamination Environment
• Other ascent environments under evaluation to be made available 
in the future:
– Radiation and EMC ‐‐‐ TBD
– Vibrations ‐‐‐ TBD
26
Payload Other Ascent Environments
LAUNCH VEHICLE INTERFACES
SLS Mission Planners Guide Section 6
27
• SLS accommodates 5m, 8.m and 10m Diameter Fairings depending 
on mission need
– POD Configurations shown as reference
28
SLS Offers Numerous Fairing Options
Payload Adapter 
Fairing 
SLS Block 
Cargo 
Config
u
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SLS Block 1 
5m 
(10500) 
SLS Block 1B 
5m 
(27500) 
SLS Block 1B 
8.4m 
(27000) 
SLS Block 2B 
10m 
(25000A) 
(26000A) 
(26001A) 
Exis ng 5m Class 
• Outer: 5.1m to 5.4m 
dia by  ≤19.1m long 
• Inner: 4.6m dia PL 
envelope 
• Up to 300 m3 PL 
volume 
Exis ng 5m Adapters SLS CPA 8.4m SLS CPA 10m 
SLS 10m 
• 10m dia x 31.1m 
• 9.1m dia PL envelope 
• 1800 m3 PL volume 
 
 
Revised 2‐21‐14 
Exis ng 5m Class 
• Outer: 5.1m to 5.4m 
dia by ≤19.1m long 
• Inner: 4.6m dia PL 
envelope 
• Up to 300  m3 PL 
volume 
Exis ng 5m Adapters 
SLS 8.4m 
• 8.4m dia x ≥19.1m* 
• 7.5m dia PL envelope 
• 620 m3 PL volume 
* Barrel sec on can be 
added as needed 
 
 
PL 
PL 
PL 
PL 
29
POD 8.4m and 10m Diameter Fairings
Overall Length   = 62.8 ft  (19.1m)
Barrel Section Length  =   24.2 ft  (7.4m)
External Diameter =   27.6 ft (8.4m) 
Internal Diameter =   24.6 ft  (7.5m)
Usable Volume = 21,900 ft3 (620m3)
Overall Length   = 102 ft  (31.1m)
Barrel Section Length  =   56.4 ft  (17.2m)
External Diameter =   33 ft (10.0m)
Internal Diameter = 29.9 ft  (9.1m)
Usable Volume = 63,500 ft3 (1,800m)3
Additional Barrel 
Sections Can be 
Added to the 
8.4m Fairing
KSC PAYLOAD LAUNCH FACILITIES
SLS Mission Planners Guide Section 7
30
National Aeronautics and Space Administration
EM-1 SLS Block 1 Crew Operational Flow
31
VAB
Pad
Launch
CM 
Recovery Safe,
Transportation
Aft Skirt
Ground interface verification
Hazardous Servicing, Crew ingress1
FWD Assy.
MPPF
De-Servicing
SLS:
MSA
SLS: 
LVSA
SLS:
ICPS
SLS: 
CS
Turn 
Basin
Turn 
Basin
KSC/GSDO Managed Operations
MPPF
Hazardous Servicing
BFF
Aft skirt & FWD assy build up, 
and Hot Fire
RPSF
Receiving / Inspection
AFT Booster Buildup
SLS: Motor Segments 
& Aft Exit Cones
Connect to KSC locomotive
MPPFOrion:
CM Hazardous Servicing
Orion:
LAS-Motor
Orion: 
SM
O&C  IOZ, Assemble/Test,
Refurbishment
MPCV:
LAS-Ogive
CRF
Motor Processing
National Aeronautics and Space Administration
EM-1 SLS Block 1 Payload Operational Flow
32
VAB
Pad
Launch
Aft Skirt
Ground interface verification
Hazardous Servicing, Crew ingress1
FWD Assy.
SLS:
MSA
SLS: 
LVSA
SLS:
ICPS
SLS: 
CS
Turn 
Basin
Turn 
Basin
KSC/GSDO Managed Operations
MPPF
Hazardous Servicing
BFF
Aft skirt & FWD assy build up, 
and Hot Fire
RPSF
Receiving / Inspection
AFT Booster Buildup
SLS: Motor Segments 
& Aft Exit Cones
Connect to KSC locomotive
TBD:
Payload Fairing
TBD:
Payload
Processing 
Facility PHSF
Payload Fairing Processing, 
Payload Encapsulation
SLF
National Aeronautics and Space Administration 33
KSC/GSDO Facility Overview
Space Station Processing Facility (SSPF)
• High Bay, Intermediate Bay, Air Lock
• Level4/5 Clean Work Area
• Door Dimensions (H x W): 49.5’ x 42’ 
• Cranes: (2) 30 t / (2) 5 t / (1) 15 t
• Hook Height: 50’ / 25’ / 50’
• Ammonia Servicing, Compressed Air, 
GHe, GN2 
Payload Hazardous Servicing Facility (PHSF)
• High Bay, Air Lock
• Level4/5 Clean Work Area
• Door Dimensions (H x W): 75’ x 35’ 
• Cranes: (1) 50 t / (1) 15 t
• Hook Height: 74.5’ / 72.5’
• Compressed Air, GHe, GN2 
• Hypergolic Vent System
• PHE Breathing Air 
Vehicle Assembly Building (VAB)
• (4) High Bays, (4) Low Bay Areas, 
Transfer Aisle
• Cranes: (2) 250 t / (2) 325 t / (1) 175 t
• Hook Height: 462.5’ / 462.5’ / 160.25’
• Compressed Air, GHe, GN2 
• 360° Access to OML of Launch 
Vehicle
Mobile Launcher (ML)
• Service Interfaces for SLS Vehicle 
(Umbilicals, Access Arms)
• Compressed Air
• Environmental Control System
Crawler Transporter (CT)
• Transports ML with Integrated Vehicle 
• Environmental Control System
Launch Complex 39B (LC-39B)
• Human-Rated Space Launch Complex
• Clean Pad Approach
• Compressed Air, GHe, GN2, GO2, LH2, 
LO2
• Environmental Control System
Launch Control Center (LCC)
• “Brain” of LC-39
• Controls Operations Interfaces with 
Launch Vehicle and Spacecraft
SUMMARY AND NEXT STEPS
SLS Mission Planners Guide
34
• SLS Program (Inner Loop) continues to develop the 2017 vehicle
• SLS Evolvability (Outer Loop) continues to assess SLS Program 
results and incorporate those into Block upgrade performance 
studies
• A formal SLS Mission Planners Guide will be available after the next 
synch between Inner and Outer Loop is completed
• This overview also provides insight to better understand needed 
mission enabling technology investments for SLS Block upgrades
– Users are invited to continue the discussion involving potential SLS utilization and 
related performance improvements that can increase SLS mission capture
35
Summary and Next Steps


SLS Mission Planners Guide (MPG) Overview

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