NASA’S SPACE LAUNCH SYSTEM: PAYLOAD OPPORTUNITIES FOR LUNAR EXPLORATION, SCIENCE MISSIONS
October 25, 2019
STEVE CREECH Manager, Spacecraft/ Payload Integration & Evolution NASA’s Space Launch System
0689 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION
322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft.
Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter
Core Stage Core Stage Core Stage
Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines
SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo
> 26 t (57k lbs) > 26 t (57k lbs) 34–37 t (74k–81k lbs) 37–40 t (81k–88k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon
0689 SLS C3 PERFORMANCE
Block 2 Block 1B Block 1
SLS performance is optimized for lunar destinations (C3=-0.99 km2/s2) 0689 BLOCK 1 PAYLOAD ACCOMMODATIONS
SLS Block 1 SLS Block 1 Crew Cargo
CubeSats
Orion 5m Spacecraft Fairing 6U 12U 14 kg 20 kg Integrated ISPE Primary Spacecraft/Payload Payload Element (ISPE)
Payload Adapter
Orion Stage Adapter (OSA)
Interim Cryogenic Propulsion Stage (ICPS)
Booster Booster Booster Booster Launch Vehicle Stage Adapter (LVSA)
Up to 17 places ≤ 12U 3 Stages 229 m available volume Stages (Core) (Core) 0689 BLOCK 1B PAYLOAD ACCOMMODATIONS
SLS Block 1B SLS Block 1B Crew Cargo
Orion Spacecraft Fairing Available diameter x length volume
8.4 m x 19.1 m 621 m3
8.4m x 27.4 m 988 m3 8.4m Fairing
Stages Stages (EUS) (EUS) Co-Manifested Primary Payload Payload Universal Stage Adapter CubeSats (USA) 286 m3, Up to 7 places, ≤12U ≤10 t lbm Payload Adapter (PLA)
CubeSats
Up to 21 places ≤12U
Booster Booster Booster Booster
Stages Stages 6U (Core) 12U (Core) 0689 SLS ENABLES LUNAR, MARTIAN MISSIONS
30’ tall x 27.6’ dia
CubeSats Orion with short-duration 10m fairing w/notional hab module Mars payload
Smallsat access to deep 286 m3 1,320 m3 space, propulsive capabilities 10 t lbm capability >45 t lbm capability
0689 SLS ENABLES SCIENCE MISSIONS
• Europa Clipper and Lander • Dual spacecraft to the Ice Giants • Interstellar probe • Large-aperture space telescopes
Robotic Orion with Large-Aperture Interstellar Probe Payloads to Co-manifested Space Telescopes the outer Science Missions solar system
0689 SLS PROGRESS TOWARD ARTEMIS I: FLIGHT ARTICLES
0689 SLS PROGRESS TOWARD ARTEMIS II & BEYOND
All booster motor segments cast; Five RL-10s complete seven complete
Two RS-25s complete, Payload adapter manufacturing LVSA, OSA, ICPS All Artemis II core stage controllers green run demonstration article panels machined components manufactured 0689 MORE TECHNICAL INFORMATION SLS MISSION PLANNER’S GUIDE
• SLS Mission Planner’s Guide (ESD 30000) • Google or email: NASA-slspayloads@mail.nasa.gov –www.nasa.gov/opportunities for payload opportunities and announcements
0689 www.nasa.gov
@NASA_SLS
NASASLS youtube.com/nasa
@explorenasa
0689 BACKUP
0689 0689 NASA’S SPACE LAUNCH SYSTEM UNIQUE CAPABILITY FOR HUMAN AND ROBOTIC EXPLORATION
• Block 1B: Double the volume of any contemporary heavy lift vehicle VOLUME 8.4 m x 27.4 m Orion with Co- • Only vehicle that can carry the Orion and a fairing with Manifested co-manifested payload to the Moon large-aperture Payloads telescope
*Not to scale
• Block 1B: Can launch 50% more mass than any contemporary launch vehicle MASS • Block 2: Mars-enabling capability of greater than 45 metric tons to Trans Lunar Injection Contemporary SLS SLS Heavy Lift Block 1B Block 2
•Reduce transit times by half or greater DEPARTURE to the outer solar system ENERGY •Enables larger payloads to deep space destinations
0689 SLS BLOCK 1 CONFIGURATION
Launch Abort System (LAS) P Utah, Alabama, Florida P Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle P RL10 Engine Lockheed Martin, P 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Booster (2) Florida Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) P Utah, KSC Boeing/United Launch Alliance, California, Alabama
Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama P
Core Stage & Avionics Boeing Louisiana, Alabama
RS-25 Engine (4) PAerojet Rocketdyne = In Progress California, Mississippi P = Completed
0689 UNMATCHED VOLUME FOR PAYLOADS
0689 0689 ARTEMIS I FULL SYSTEMS CHECKOUT PRIOR TO CREWED MISSIONS
0689 SLS MASS TO DESTINATIONS
SLS Block 1B : 8.4m x 19.1m Fairing SLS Block 2 : 8.4m x 19.1m Fairing SLS Block 1: 5m x 19.1m Fairing SLS Block 1 : Crew SLS Block 1B : Crew SLS Block 2 : Crew
0689 SLS MASS TO DESTINATIONS
Note: assumes SLS B1B EUS with addition of a 3rd and/or 4th stage
0689 REMAINING STEPS TO FINAL INTEGRATION
BOOSTERS: Deliver forward & aft assemblies, ship motor segments; crews maneuvering pathfinders in RPSF
CORE STAGE: Engine installation, shipping to SSC, Green Run test campaign, shipping to KSC
LAUNCH VEHICLE STAGE ADAPTER: Install DFI, quick disconnects & cable runs; final checkout; shipping
SYSTEMS ENGINEERING & INTEGRATION: DCR, flight software delivery, Software Integration Lab (SIL) certification, CoFR, training
0689 SLS BLOCK 1B CONFIGURATION
Launch Abort System Crew Module Service Module Encapsulated Service Module Panels Spacecraft Adapter Orion Multi-Purpose HAB/Cargo Crew Vehicle Payload Attach Fitting (PAF) Lockheed Martin Exploration Upper Stage Boeing 5 Segment Solid Rocket Booster (2) RL10 Engine (4) Universal Stage Adapter Northrop Grumman Aerojet Rocketdyne Dynetics
Interstage Boeing
Core Stage & Avionics Boeing
RS-25 Engine (4) Aerojet Rocketdyne
0689 THIRD FLIGHT AND BEYOND
Five RL-10s complete Booster processing Payload adapter manufacturing demonstration article
Tooling for USA
RS-25 HIP-bonded main combustion chamber EUS weld confidence articles Additively manufactured pogo accumulator 0689 SLS CAN ENABLE BREAKTHROUGH SCIENCE MISSIONS
• SLS is America’s heavy-lift vehicle for strategic human exploration and scientific missions • Manufacturing is complete for the first flight; SLS is nearing the integration phase • SLS has a flexible architecture and an evolvable upgrade path • Discussions with the science community are ongoing to determine how SLS can enable breakthrough science missions, such as sending a probe to interstellar space
0689 0689 SLS LIFT CAPABILITIES FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION
Payload to LEO 95 t (209k lbs) 95 t (209k lbs) 105 t (231k lbs) 105 t (231k lbs) 130 t (287k lbs) 130 t (287k lbs)
Payload to TLI/Moon > 26 t (57k lbs) > 26 t (57k lbs) 34–37 t (74k–81k lbs) 37–40 t (81k–88k lbs) > 45 t (99k lbs) > 45 t (99k lbs)
Payload Volume N/A** 9,030 ft3 (256m3) 10,100 ft3 (286m3)** 18,970 ft3 (537 m3) 10,100 ft3 (286m3)** 34,910 ft3 (988 m3)
Low Earth Orbit (LEO) represents a typical 200 km circular orbit at 28.5 degrees inclination
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.
** Not including Orion/Service Module volume SLS Block 1 SLS Block 1 SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo Crew Cargo Maximum Thrust 8.8M lbs 8.8M lbs 8.8M lbs 8.8M lbs 11.9M lbs 11.9M lbs
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