Space Launch System

This article is about the NASA rocket family. For the similarly-named US Air Force project of the 1960s, see Space Launching System. For Turkey's UFS satellite launcher, see Space Launch System (Turkey). For the general topic, see space launcher.

Space Launch System
SLS Block 1 with the Orion spacecraft launching from Pad 39B
FunctionSuper heavy-lift launch vehicle
Manufacturer
Country of originUnited States
Project costUS$26.4 billion
Cost per launchUS$2.5 billion
Cost per yearUS$2.6 billion (FY23)
Size
Height
  • Block 1: 98 m (322 ft)[a]
  • Block 1B/2: 111 m (365 ft)[a]
Diameter8.4 m (27.6 ft)[2]
Mass2,610,000 kg (5,750,000 lb)[3]
Stages2½
Maximum thrust
  • Block 1: 39 MN (8,800,000 lbf)
  • Block 1B: 40 MN (8,900,000 lbf)
  • Block 2: 42 MN (9,500,000 lbf)
Capacity
Payload to LEO
Altitude200 km (120 mi)[4]
Orbital inclination28.5°
Mass
  • Block 1: 95,000 kg (209,000 lb)[5]
  • Block 1B: 105,000 kg (231,000 lb)
  • Block 2: 130,000 kg (290,000 lb)
Payload to TLI
Mass
  • Block 1: >27,000 kg (59,500 lb)
  • Block 1B: 42,000 kg (92,500 lb)[b]
  • Block 2: >46,000 kg (101,400 lb)[b]
Associated rockets
Based on
Comparable
Launch history
StatusActive
Launch sitesKennedy, LC-39B
Total launches1
Success(es)1
First flight16 November 2022, 06:47:44 UTC[6] (1:47:44 am EST)
Carries passengers or cargoOrion
Stage info
Boosters (Block 1/1B)
No. boosters2 × five-segment Solid Rocket Boosters
Height54 m (177 ft)[7]
Diameter3.7 m (12 ft)
Gross mass730,000 kg (1,600,000 lb)[7]
Maximum thrust
  • SL: 14.6 MN (3,280,000 lbf)
  • vac: 16 MN (3,600,000 lbf)[8]
Total thrust
  • SL: 29.2 MN (6,560,000 lbf)
  • vac: 32 MN (7,200,000 lbf)
Specific impulse269 s (2.64 km/s)
Burn time126 seconds
PropellantPBAN, APCP
First stage – Core
Height64.6 m (212 ft)
Diameter8.4 m (28 ft)
Empty mass97,940 kg (215,910 lb)[9]
Gross mass1,085,410 kg (2,392,910 lb)
Propellant mass
  • LH2: 144,000 kg (317,000 lb)
  • LOX: 840,000 kg (1,860,000 lb)[10]
Powered by4 × RS-25
Maximum thrust
  • SL: 7.4 MN (1,672,000 lbf)
  • vac: 9.1 MN (2,049,200 lbf)[11]
Specific impulse
  • SL: 366 s (3.59 km/s)
  • vac: 452 s (4.43 km/s)
Burn time480 seconds
PropellantLH2 / LOX
Second stage (Block 1) – ICPS
Height13.7 m (45 ft)[12]
Diameter
  • 5 m (16 ft) (LH2 tank)
  • 3.2 m (10 ft) (LOX tank)[13]
Empty mass3,490 kg (7,690 lb)[14]
Gross mass32,066 kg (70,693 lb)
Powered by1 × RL10
Maximum thrust110.1 kN (24,800 lbf)
Specific impulse465.5 s (4.565 km/s)[15]
Burn time1,125 seconds
PropellantLH2 / LOX
Second stage (Block 1B/2) – EUS
Height17.3 m (57 ft)[14]
Diameter
  • 8.4 m (28 ft) (LH2 tank)
  • 5.5 m (18 ft) (LOX tank)[16]
Propellant mass129,000 kg (284,000 lb)
Powered by4 × RL10C-3[14]
Maximum thrust433.1 kN (97,360 lbf)
Specific impulse460.1 s (4.512 km/s)[17]
Burn time1,275 seconds
PropellantLH2 / LOX

The Space Launch System (SLS) is an American super heavy-lift expendable launch vehicle used by NASA. As the primary launch vehicle of the Artemis Moon landing program, SLS is designed to launch the crewed Orion spacecraft on a trans-lunar trajectory. The first (and so far only) SLS launch was the uncrewed Artemis I, which took place on 16 November 2022.

Development of SLS began in 2011 as a replacement for the retiring Space Shuttle as well as the canceled Ares I and Ares V launch vehicles. SLS was built using existing Shuttle technology, including solid rocket boosters and RS-25 engines. The rocket has been criticized for its political motivations, seen as a way to preserve jobs and contracts for aerospace companies involved in the Shuttle program at great expense to NASA. The project has faced significant challenges, including mismanagement, substantial budget overruns, and significant delays. The first Congressionally mandated launch in late 2016 was delayed by nearly six years.

All Space Launch System flights are to be launched from Launch Complex 39B at the Kennedy Space Center in Florida. The first three SLS flights are expected to use the Block 1 configuration, comprising a core stage, extended Space Shuttle boosters developed for Ares I and the Interim Cryogenic Propulsion Stage (ICPS) upper stage. The improved Block 1B configuration, with the powerful and purpose-built Exploration Upper Stage (EUS), is planned to be introduced on the fourth flight; a further improved Block 2 configuration with new solid rocket boosters is planned for the ninth flight. After the launch of Artemis IV, NASA plans to transfer production and launch operations of SLS to Deep Space Transport LLC, a joint venture between Boeing and Northrop Grumman.


Cite error: There are <ref group=lower-alpha> tags or {{efn}} templates on this page, but the references will not show without a {{reflist|group=lower-alpha}} template or {{notelist}} template (see the help page).

  1. ^ Cite error: The named reference SLS_Lift_Capacity was invoked but never defined (see the help page).
  2. ^ NASA (27 October 2021). "Space Launch System Core Stage". nasa.gov. Archived from the original on 15 June 2020. Retrieved 19 November 2022.
  3. ^ "SLS October 2015 Fact Sheet" (PDF). Archived (PDF) from the original on 6 September 2014. Retrieved 19 November 2022.
  4. ^ "2018 draft factsheet of SLS capabilities" (PDF). NASA. 20 August 2018. Archived (PDF) from the original on 30 June 2019. Retrieved 24 August 2022.
  5. ^ "2024 update on SLS status". NASA. Retrieved 16 May 2025.
  6. ^ Cite error: The named reference nasa-blog-20221108 was invoked but never defined (see the help page).
  7. ^ a b Cite error: The named reference SRBSheet was invoked but never defined (see the help page).
  8. ^ Cite error: The named reference SLS Booster Development was invoked but never defined (see the help page).
  9. ^ @NASAGroundSys (2 October 2024). "The results are in… *drumroll* 🥁
    Core stage weighs a total of 215,910 pounds! When full of propellant, core stage will weigh over 2 million pounds.
    Using the Vehicle Assembly Building high bay crane and a secondary crane, Exploration Ground Systems teams lifted the @NASA_SLS core stage for @NASAArtemis II approximately 6 inches from its current mounts. Teams repeated the lift, weighing the core stage twice to ensure an exact weight reading was achieved"     (Tweet). Retrieved 3 October 2024 – via Twitter.
  10. ^ Cite error: The named reference SLSCoreStageFactSheet was invoked but never defined (see the help page).
  11. ^ Cite error: The named reference RS-25 was invoked but never defined (see the help page).
  12. ^ Cite error: The named reference ICPS_ULA_Infographic_2021 was invoked but never defined (see the help page).
  13. ^ "Delta IV Launch Services User's Guide" (PDF). United Launch Alliance. Archived (PDF) from the original on 21 September 2018. Retrieved 13 April 2024.
  14. ^ a b c Cite error: The named reference SLS_Specs_SFI was invoked but never defined (see the help page).
  15. ^ Cite error: The named reference RL10 was invoked but never defined (see the help page).
  16. ^ "1 year down, a galaxy to go". Boeing. Archived from the original on 21 April 2024. Retrieved 13 April 2024.
  17. ^ "RL10 Engine". Aerojet Rocketdyne. Archived from the original on 7 November 2021. Retrieved 18 November 2021.
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