{
  "id": "nasa-sls",
  "title": "Space Launch System (Block 1)",
  "maker": "NASA",
  "maker_type": "Space agency",
  "kind": "mission",
  "category": "launchers",
  "page": "https://spacemushroom.com/space-products/nasa-sls/",
  "website": "https://www.nasa.gov/reference/space-launch-system/",
  "summary": "NASA super heavy-lift launcher for the Artemis missions; NASA sources describe a friction-stir welded aluminium core stage under spray-on foam, steel booster cases and a lightweight aluminium Orion stage adapter.",
  "application": "NASA's heavy-lift rocket for sending Orion and cargo to the Moon. It stacks a large welded aluminium core stage, two reused-case steel solid boosters and a small upper stage.",
  "story": {
    "headline": "The Space Launch System is NASA's super heavy-lift rocket for sending Orion and cargo to the Moon.",
    "intro": [
      "The Space Launch System is NASA's heavy-lift rocket for the Artemis missions. NASA calls it the only rocket that can send the Orion spacecraft and its four astronauts, along with large cargo, directly to the Moon. The Block 1 version stands 322.4 feet tall and weighs 5.74 million pounds when fuelled. It first flew on 16 November 2022.",
      "The core stage is welded aluminium, covered in sprayed foam. The two solid boosters use steel cases that flew before, on space shuttle missions. Reusing shuttle hardware was a goal of the design: the boosters add a fifth segment to the shuttle's four, and the four main engines are RS-25s."
    ],
    "built": [
      {
        "title": "Core stage",
        "text": "The core stage is made of 10 barrel sections, four domes and seven rings. Each barrel has eight aluminium panels, joined by bolts or by friction stir welding, in which a spinning tool stirs the metal together. The intertank, which joins the two propellant tanks, is the only bolted section.",
        "parts": [
          "Core stage barrel sections",
          "Tank domes (gore panels)",
          "Intertank"
        ]
      },
      {
        "title": "Tanks and engine section",
        "text": "The hydrogen tank is 27.6 feet across and 130 feet tall, and it holds 537,000 gallons. The oxygen tank holds 196,000 gallons. Four RS-25 engines sit in the engine section, where a thrust structure carries their push into the stage and a boat tail fairing shields them from launch heat.",
        "parts": [
          "Liquid hydrogen tank",
          "Liquid oxygen tank",
          "RS-25 engines (x4)",
          "Engine thrust structure",
          "Aerodynamic boat tail fairing"
        ]
      },
      {
        "title": "Insulation",
        "text": "A robot sprays flexible polyurethane foam over the outside of the core stage tanks. Cork is used alongside the foam for thermal protection. On the launch vehicle stage adapter, technicians spray the insulation by hand, and it turns orange in sunlight.",
        "parts": [
          "Core stage tank exterior insulation",
          "Core stage thermal protection (additional)",
          "Spray-on insulation"
        ]
      },
      {
        "title": "Solid boosters",
        "text": "Each booster is 177 feet tall and 12 feet across, with five propellant segments in steel cases that flew on space shuttle missions. Together they give 7.2 million pounds of thrust for about 2 minutes 12 seconds, then fall into the Atlantic Ocean. Each nozzle swivels to steer.",
        "parts": [
          "Booster cases",
          "Booster propellant",
          "Five-segment solid rocket motors (x2)",
          "Gimballing ablative nozzle (x2)",
          "Case insulation and liner (asbestos-free)"
        ]
      },
      {
        "title": "Upper elements",
        "text": "The interim upper stage is a modified Delta IV stage with one RL10B-2 engine. The launch vehicle stage adapter is a friction-stir welded shell of two cones and two rings, 27.5 feet tall. The Orion stage adapter is lightweight aluminium, 18 feet across, and holds a diaphragm that keeps hydrogen out of Orion.",
        "parts": [
          "ICPS stage structure (modified Delta Cryogenic Second Stage)",
          "RL10B-2 engine (x1)",
          "Cone and ring sections (two cones, two rings)",
          "Orion stage adapter",
          "Hydrogen barrier diaphragm"
        ]
      }
    ],
    "materials": [
      {
        "name": "Aluminium alloy 2219",
        "mid": "aluminium-2219",
        "where": "A test barrel segment of the liquid hydrogen tank. NASA does not name the alloy of the flight panels."
      },
      {
        "name": "Aluminium",
        "mid": "aluminium",
        "where": "Panels and domes of the core stage, and the lightweight Orion stage adapter. NASA names no alloy for these."
      },
      {
        "name": "Polyurethane foam",
        "mid": "polyurethane-foam-spray-on",
        "where": "Flexible foam sprayed by robot onto the outside of the core stage tanks."
      },
      {
        "name": "Cork",
        "mid": "cork",
        "where": "Extra thermal protection on parts of the vehicle, alongside the foam."
      },
      {
        "name": "Steel",
        "mid": "steel-grade-unstated",
        "where": "The booster cases, reused from space shuttle flights. NASA does not give the grade."
      }
    ],
    "connections": "Four RS-25 engines, made by Aerojet Rocketdyne, power the core stage, and one RL10B-2 powers the upper stage. For the first four missions, 14 of the RS-25s are shuttle engines that have already flown. Boeing is prime contractor for the core stage and Northrop Grumman leads the boosters. United Launch Alliance makes the upper stage, a modified Delta IV stage.",
    "unknown": "NASA names the main metals but publishes no part-by-part list. It does not give the alloy of the flight tank panels or the grade of the booster steel. The booster insulation and nozzle materials, the metals inside the RS-25 and RL10 engines, and the material of the launch vehicle stage adapter are not given either.",
    "facts": [
      {
        "label": "Height",
        "value": "322.4 ft (98.3 m)"
      },
      {
        "label": "Fuelled mass",
        "value": "5.74 million lb (2,603 t)"
      },
      {
        "label": "Maximum thrust",
        "value": "8.8 million lb (39,144 kN)"
      },
      {
        "label": "Core stage size",
        "value": "about 212 ft (64.6 m) tall, 27.6 ft (8.4 m) in diameter"
      },
      {
        "label": "Booster burn time",
        "value": "about 2 min 12 s"
      },
      {
        "label": "First launch",
        "value": "16 November 2022 (Artemis I), Launch Complex 39B"
      }
    ]
  },
  "specifications": [
    {
      "label": "Height",
      "value": "322.4 ft (98.3 m)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "Height: 322.4 ft. (98.3 m)"
    },
    {
      "label": "Mass fueled",
      "value": "5.74 million lb (2,603 t)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "Weight: 5.74 million lbs. (2,603 t) fueled"
    },
    {
      "label": "Maximum thrust",
      "value": "8.8 million lb (39,144 kN)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "Maximum thrust: 8.8 million lbs. (39,144 kN)"
    },
    {
      "label": "Core stage diameter",
      "value": "27.6 ft (8.4 m)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "The liquid hydrogen fuel tank is 27.6 ft. (8.4 m) in diameter"
    },
    {
      "label": "Booster length",
      "value": "177 ft",
      "source_url": "https://www.nasa.gov/reference/space-launch-system-solid-rocket-booster/",
      "quote": "Length: 177 feet"
    },
    {
      "label": "Booster thrust",
      "value": "3.6 million lb each (maximum)",
      "source_url": "https://www.nasa.gov/reference/space-launch-system-solid-rocket-booster/",
      "quote": "Thrust: 3.6 million pounds each"
    },
    {
      "label": "First launch",
      "value": "16 November 2022 (Artemis I), Launch Complex 39B",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/",
      "quote": "On Nov. 16, 2022, SLS took to the sky from Launch Complex 39B"
    },
    {
      "label": "Core stage size",
      "value": "about 212 ft (64.6 m) tall, 27.6 ft (8.4 m) in diameter",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "It measures approximately 212 ft. (64.6 m) tall and 27.6 ft. (8.4 m) in diameter"
    },
    {
      "label": "Core stage fuelled mass, excluding engines",
      "value": "2.4 million lb (1,088 t)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "Its fully fueled weight, excluding engines, is 2.4 million lbs. (1,088 t)."
    },
    {
      "label": "Core stage construction",
      "value": "10 barrel sections, 4 dome sections, 7 rings",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "The core stage is made up of 10 major barrel sections, four dome sections, and seven rings."
    },
    {
      "label": "Liquid oxygen tank capacity",
      "value": "196,000 gal (741,941 L)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "The liquid oxygen tank has a capacity of 196,000 gal. (741,941 L)."
    },
    {
      "label": "Core stage burn time",
      "value": "roughly 480 s",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "The core stage is designed to operate for the entire roughly 480-second launch from ground to Earth orbit"
    },
    {
      "label": "RS-25 size",
      "value": "about 14 ft (4.3 m) tall, 8 ft (2.4 m) diameter",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "Each RS-25 is roughly 14 ft. (4.3 m) tall, 8 ft. (2.4 m) in diameter"
    },
    {
      "label": "RS-25 thrust, four engines",
      "value": "about 2 million lbf for the eight-minute climb",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/",
      "quote": "The four engines provide about 2 million lbs. of thrust for the eight-minute climb to Earth orbit."
    },
    {
      "label": "Booster size and mass",
      "value": "177 ft tall, 12 ft diameter, 1.6 million lb loaded",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "12 ft. (3.7 m) in diameter, and weighs 1.6 million lbs. (726 t) when filled with solid propellant"
    },
    {
      "label": "Booster thrust, pair",
      "value": "7.2 million lbf (32,027 kN)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "The five-segment SLS solid rocket boosters generate 7.2 million lbs. (32,027 kN) of thrust"
    },
    {
      "label": "Booster burn time",
      "value": "about 2 min 12 s",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "The boosters operate for about 2 minutes 12 seconds and are then jettisoned into the Atlantic Ocean."
    },
    {
      "label": "Launch vehicle stage adapter height",
      "value": "27.5 ft (8.4 m)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "The adapter is 27.5 ft. (8.4 m) tall."
    },
    {
      "label": "Orion stage adapter size",
      "value": "18 ft (5.5 m) diameter, 5 ft (1.5 m) tall",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "The Orion stage adapter is 18 ft. (5.5 m) in diameter, 5 ft. (1.5 m) tall, and is made of lightweight aluminum."
    },
    {
      "label": "Exploration Upper Stage thrust",
      "value": "about 97,000 lbf from four RL10C-3 engines",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/",
      "quote": "This 97,000 lbs. of thrust will allow more than 38 t (84,000 lbs.) for Block 1B crew"
    },
    {
      "label": "Block 2 liftoff thrust",
      "value": "9.4 million lb (Block 1: 8.8 million lb)",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/",
      "quote": "will provide 9.4 million lbs. of launch thrust, compared to the Block 1’s 8.8 million lbs."
    }
  ],
  "features": [
    {
      "text": "Core stage tanks are built from friction-stir welded aluminium",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
      "quote": "Those panels are friction-stir welded or bolted vertically and horizontally"
    },
    {
      "text": "Two five-segment solid boosters repurpose shuttle steel cases",
      "source_url": "https://www.nasa.gov/reference/space-launch-system-solid-rocket-booster/",
      "quote": "All booster components use steel cases repurposed from cases used on prior space shuttle flights"
    }
  ],
  "parts": [
    {
      "assembly": "Core stage structure",
      "parts": [
        {
          "part": "Liquid hydrogen tank barrel segment (test article)",
          "material": "Al 2219 aluminium alloy",
          "form": "welded barrel segment",
          "finish": null,
          "standard": null,
          "hardware_ref": "Core stage",
          "quote": "made of Al 2219, an aerospace aluminum alloy",
          "source_url": "https://www.nasa.gov/centers-and-facilities/marshall/first-liquid-hydrogen-tank-barrel-segment-for-the-sls-core-stage-completed-at-michoud/",
          "profile": null,
          "mid": "aluminium-2219"
        },
        {
          "part": "Core stage barrel sections",
          "material": "aluminium (alloy not stated in this source)",
          "form": "eight friction-stir welded or bolted panels per barrel",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each cylindrical barrel section consists of eight aluminum panels",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": "aluminium",
          "mid": "aluminium"
        },
        {
          "part": "Engine section",
          "material": "aluminium (alloy not stated)",
          "form": "welded isogrid panels",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "welded aluminum isogrid panels",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": "aluminium",
          "mid": "aluminium"
        },
        {
          "part": "Liquid oxygen tank",
          "material": "aluminium (alloy not stated)",
          "form": "isogrid barrel panels and two domes",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "sections of isogrid aluminum panels and two domes",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": "aluminium",
          "mid": "aluminium"
        },
        {
          "part": "Forward skirt",
          "material": "aluminium (alloy not stated)",
          "form": "isogrid structure",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The aluminum isogrid structure",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": "aluminium",
          "mid": "aluminium"
        },
        {
          "part": "Tank domes (gore panels)",
          "material": "aluminium alloy (not named)",
          "form": "preformed gores welded into domes",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Gores are preformed aluminum alloy dome segments",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": "aluminium",
          "mid": "aluminium"
        }
      ]
    },
    {
      "assembly": "Thermal protection",
      "parts": [
        {
          "part": "Core stage tank exterior insulation",
          "material": "flexible polyurethane foam",
          "form": "robotically sprayed",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "flexible polyurethane foam",
          "source_url": "https://www.nasa.gov/directorates/esdmd/common-exploration-systems-development-division/space-launch-system/nasas-artemis-iii-core-stage-receives-thermal-protection-coating/",
          "profile": null,
          "mid": "polyurethane-foam-spray-on"
        },
        {
          "part": "Core stage thermal protection (additional)",
          "material": "cork (alongside spray-on foam)",
          "form": "applied to parts of the vehicle",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "materials such as cork, provides thermal protection for every",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": "cork"
        }
      ]
    },
    {
      "assembly": "Solid rocket boosters",
      "parts": [
        {
          "part": "Booster cases",
          "material": "steel (grade not stated)",
          "form": "reused shuttle-era cases",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "All booster components use steel cases repurposed from cases used on prior space shuttle flights",
          "source_url": "https://www.nasa.gov/reference/space-launch-system-solid-rocket-booster/",
          "profile": null,
          "mid": "steel-grade-unstated"
        },
        {
          "part": "Booster propellant",
          "material": "PBAN, ammonium perchlorate and aluminium powder",
          "form": "cast propellant segments",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "perchlorate, and aluminum powder",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": "pban-ap-aluminium-propellant"
        }
      ]
    },
    {
      "assembly": "Upper elements",
      "parts": [
        {
          "part": "Orion stage adapter",
          "material": "lightweight aluminium",
          "form": "ring adapter, 18 ft diameter",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "made of lightweight aluminum",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": "aluminium",
          "mid": "aluminium"
        },
        {
          "part": "Launch vehicle stage adapter",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Teledyne Brown Engineering manufactures the launch",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null
        }
      ]
    },
    {
      "assembly": "Core stage (Boeing)",
      "parts": [
        {
          "part": "Liquid hydrogen tank",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The liquid hydrogen fuel tank is 27.6 ft. (8.4 m) in diameter and 130 ft. (39.7 m) tall.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Holds the RS-25 fuel; five barrel sections and two domes",
          "specs": [
            {
              "label": "Capacity",
              "value": "537,000 gal (2 million L) of liquid hydrogen",
              "quote": "The tank has a capacity of 537,000 gal. (2 million L) of liquid hydrogen.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            }
          ]
        },
        {
          "part": "Intertank",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The intertank measures 27.6 ft. (8.4 m) in diameter and 21.8 ft. (6.7 m) tall.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Joins the two propellant tanks and is the forward attach point for the boosters; the only bolted section",
          "specs": [
            {
              "label": "Structure",
              "value": "Contains a thrust structure that carries booster loads",
              "quote": "It contains a thrust structure to carry loads imparted from the solid rocket boosters during ascent.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            }
          ]
        },
        {
          "part": "Engine thrust structure",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "the engine section houses four RS-25 main engines, the engine thrust structure, propellant ducts, various avionics systems",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Carries the RS-25 thrust into the stage; houses the engine ducts and thrust vector control"
        },
        {
          "part": "Aerodynamic boat tail fairing",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "An aerodynamic boat tail fairing at the bottom channels airflow and protects the engines from extreme temperatures during launch.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Channels airflow and shields the engines from extreme launch temperatures"
        },
        {
          "part": "Liquid hydrogen feedlines (x4)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The aft end of the liquid hydrogen tank includes four liquid hydrogen feedlines to the RS-25 engines.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Carry LH2 from the tank aft end to the RS-25 engines"
        },
        {
          "part": "Liquid oxygen downcomer ducts (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "through a pair of “downcomer” ducts that exit the intertank on opposite sides",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Carry LOX from the intertank down to the engine section"
        },
        {
          "part": "Main propulsion system (ducts, valves, pressurization)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "consists of the ducts, valves, and other equipment that supply and control the flow of liquid hydrogen and liquid oxygen propellants",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Supplies and controls propellant, helium and nitrogen flow"
        },
        {
          "part": "Core stage flight computers (forward skirt)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Boeing (core stage lead contractor)",
          "quote": "The core stage forward skirt contains the flight computers for the Block 1 SLS rocket.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Run the Block 1 vehicle in flight; software written at NASA Marshall",
          "specs": [
            {
              "label": "Supplier statement",
              "value": "Boeing is lead contractor for the core stage, including the flight computers",
              "quote": "lead contractor for SLS core stage manufacturing, including the flight computers that control the rocket during flight",
              "source_url": "https://www.nasa.gov/reference/space-launch-system/"
            }
          ]
        },
        {
          "part": "Cabling (562 cables) and sensors (775)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "There are 562 cables in the core stage.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Wiring and instrumentation, 231 cables in the engine section alone",
          "specs": [
            {
              "label": "Sensors with wire routing",
              "value": "775",
              "quote": "There are 775 independent sensors that have wire routing to them.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            }
          ]
        },
        {
          "part": "Rear-facing cameras in the intertank (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "including two rear-facing cameras and interfaces to the liquid hydrogen and liquid oxygen tanks",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Watch the vehicle from the intertank, with the tank interfaces"
        }
      ]
    },
    {
      "assembly": "RS-25 engine installation",
      "parts": [
        {
          "part": "RS-25 engines (x4)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Aerojet Rocketdyne (now L3Harris)",
          "quote": "The SLS core stage contains four RS-25 engines, their liquid hydrogen and liquid oxygen propellant supply",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Main engines of the core stage, liquid hydrogen and liquid oxygen",
          "specs": [
            {
              "label": "Maximum vacuum thrust per engine",
              "value": "about 512,300 lbf (2,279 kN) at 109 percent",
              "quote": "Each SLS engine will operate at 109 percent thrust – approximately 512,300 lbs. (2,279 kN) maximum thrust in a vacuum.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            },
            {
              "label": "Mass per engine",
              "value": "about 7,750 lb (3.5 t)",
              "quote": "weighs approximately 7,750 lbs. (3.5 t)",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            },
            {
              "label": "Engines for the first four missions",
              "value": "14 flight-proven shuttle engines and two new engines assembled from shuttle-era parts",
              "quote": "The first four SLS missions will be powered by 14 flight-proven engines and two new engines assembled from shuttle-era engine components.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            }
          ]
        },
        {
          "part": "RS-25 engine controllers (x4, new for SLS)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each engine has an onboard computer that automatically controls start and shutdown",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Onboard computer that runs start, shutdown, throttle, mixture ratio and engine health",
          "specs": [
            {
              "label": "Controller upgrade",
              "value": "New controllers hot-fire tested before Artemis I",
              "quote": "The RS-25s have been upgraded with new controllers that were hot-fire tested prior to the Artemis I flight.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            }
          ]
        },
        {
          "part": "RS-25 nozzle insulation (new for SLS)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "the addition of nozzle insulation to protect them from booster exhaust",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Protects the nozzles from booster exhaust"
        },
        {
          "part": "Engine gimbal hydraulic actuators",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "During ascent, the engines are gimballed through two planes by hydraulic actuators to produce vehicle pitch, yaw, and roll.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Steer each engine through two planes for pitch, yaw and roll"
        },
        {
          "part": "Pogo accumulator assembly (3D printed, new-production engines)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The 3-D printed part tested, called the pogo accumulator, is a beachball-sized piece of hardware",
          "source_url": "https://www.nasa.gov/humans-in-space/nasa-tests-3-d-printed-rocket-part-to-reduce-future-sls-engine-costs/",
          "profile": null,
          "mid": null,
          "function": "Shock absorber that regulates LOX movement to stop pogo vibration",
          "specs": [
            {
              "label": "Effect of 3D printing",
              "value": "more than 100 welds eliminated, about 35 percent cost and 80 percent production time saved",
              "quote": "more than 100 welds were eliminated, reducing costs by nearly 35 percent and production time by more than 80 percent",
              "source_url": "https://www.nasa.gov/humans-in-space/nasa-tests-3-d-printed-rocket-part-to-reduce-future-sls-engine-costs/"
            }
          ]
        }
      ]
    },
    {
      "assembly": "Solid rocket boosters (Northrop Grumman)",
      "parts": [
        {
          "part": "Five-segment solid rocket motors (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Northrop Grumman",
          "quote": "The motor assembly has five segments, each with two case segments filled with rubbery propellant.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Burn about two minutes and give more than 75 percent of liftoff thrust"
        },
        {
          "part": "Motor igniter (forward segment)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The forward segment contains the igniter that fires the length of the hollow motor segments",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Lights the length of the hollow motor so all segments ignite together"
        },
        {
          "part": "Gimballing ablative nozzle (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The aft motor segment is attached to an ablative exhaust nozzle that can be gimballed to steer the rocket.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Steers the vehicle; wider than the shuttle nozzle",
          "specs": [
            {
              "label": "Nozzle size",
              "value": "three inches wider than the shuttle nozzle",
              "quote": "New nozzle design three inches wider than the shuttle nozzle to support increased thrust.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            }
          ]
        },
        {
          "part": "Booster thrust vector control systems (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The thrust vector control system gimbals the exhaust nozzle and steers the vehicle.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Gimbal the nozzle; boosters give 90 percent of steering in the first two minutes"
        },
        {
          "part": "Booster separation motors (x16: 4 nose and 4 aft per booster)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Northrop Grumman",
          "quote": "Northrop Grumman, lead booster contractor, also produces the booster separation motors",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Push the spent boosters away at motor burnout",
          "specs": [
            {
              "label": "Count",
              "value": "four in the nose and four on the aft skirt of each booster, 16 in total",
              "quote": "Each booster has four separation motors in the nose and four on the aft skirt for a total of 16 on the vehicle.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            },
            {
              "label": "Thrust",
              "value": "about 20,000 lbf (89 kN) each",
              "quote": "Each booster separation motor generates about 20,000 lbs. (89 kN) of thrust.",
              "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
            }
          ]
        },
        {
          "part": "Booster forward assembly (nose cap, frustum, booster forward skirt)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The forward skirt assembly includes the nose cap, frustum with four solid fuel booster separation motors, and forward skirt.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Top of the booster; frustum carries four separation motors"
        },
        {
          "part": "Aft skirt assembly",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The aft skirt assembly on each booster consists of the aft skirt, the thrust vector control system",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Carries the whole stack weight on the mobile launcher; holds the TVC system"
        },
        {
          "part": "Booster avionics and flight termination system",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The forward skirt houses booster avionics, the flight termination system, and the core stage attach support posts",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Booster control and safety, housed in the forward skirt"
        },
        {
          "part": "Core-stage attach struts (forward and aft)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The forward attach struts are also located on the forward segment.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Tie each booster to the core stage"
        },
        {
          "part": "Pyrotechnic separation bolts",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "pyrotechnically activated separation bolts on the booster attach struts fire",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Fire on the attach struts at booster separation"
        },
        {
          "part": "Case insulation and liner (asbestos-free)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "New asbestos-free insulation and liner configuration.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Thermal protection of the motor case"
        }
      ]
    },
    {
      "assembly": "Interim Cryogenic Propulsion Stage (United Launch Alliance)",
      "parts": [
        {
          "part": "ICPS stage structure (modified Delta Cryogenic Second Stage)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: United Launch Alliance",
          "quote": "ICPS is a modified Delta Cryogenic Second Stage, a proven upper stage used on ULA’s Delta IV family of launch vehicles",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Interim upper stage that sends Orion to the Moon"
        },
        {
          "part": "RL10B-2 engine (x1)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Aerojet Rocketdyne (now L3Harris)",
          "quote": "feeding a single Aerojet Rocketdyne RL10B-2 engine producing 24,750 lbs. (110 kN) of thrust",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Single liquid hydrogen/liquid oxygen engine of the ICPS"
        },
        {
          "part": "Hydrazine bottles for attitude control (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "adding a second hydrazine bottle for attitude control",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Reaction control; a second bottle was added for SLS"
        },
        {
          "part": "Liquid hydrogen tank (lengthened 18.4 in)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "lengthening the liquid hydrogen tank by 18.4 in. (46.7 cm)",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Stretched compared with the Delta IV stage"
        },
        {
          "part": "Navigation system (new)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a new navigation system, Orion and launch vehicle stage adapter electrical and mechanical interfaces",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Replaces the Delta stage navigation hardware"
        },
        {
          "part": "RL10 in-flight helium injector purge",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "an RL10 in-flight helium injector purge to support engine restart",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Supports engine restart"
        },
        {
          "part": "Liquid hydrogen vent and relief valve (modified)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a modified liquid hydrogen vent and relief valve",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Tank venting and over-pressure relief"
        }
      ]
    },
    {
      "assembly": "Launch vehicle stage adapter (Teledyne Brown Engineering)",
      "parts": [
        {
          "part": "Frangible joint assembly",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A pneumatically actuated frangible joint assembly at the top of the launch vehicle stage adapter separates the ICPS",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Pneumatically actuated joint that releases the ICPS, adapter and Orion from the core stage"
        },
        {
          "part": "Cone and ring sections (two cones, two rings)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Teledyne Brown Engineering",
          "quote": "The adapter consists of two cones and two ring sections.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Friction-stir welded shell"
        },
        {
          "part": "Spray-on insulation",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "technicians manually apply spray-on insulation, which turns orange in sunlight",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Thermal protection applied by hand; turns orange in sunlight"
        },
        {
          "part": "Cameras inside the adapter",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Cameras inside the adapter provide engineers with data on its performance and location in space",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Record adapter performance and its location after separation"
        }
      ]
    },
    {
      "assembly": "Orion stage adapter (NASA Marshall)",
      "parts": [
        {
          "part": "Secondary payload deployment system",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "SLS provided a comprehensive secondary payload deployment system for the CubeSats",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Brackets, harnesses, vibration isolation and an avionics unit that release CubeSats"
        },
        {
          "part": "Hydrogen barrier diaphragm",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The adapter contains a diaphragm that provides a barrier to prevent gases, such as hydrogen, generated during launch from entering Orion.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Keeps gases generated during launch out of Orion"
        }
      ]
    },
    {
      "assembly": "Block 1B upper stage (planned)",
      "parts": [
        {
          "part": "Exploration Upper Stage with four RL10C-3 engines",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Boeing (stage); L3Harris (engines)",
          "quote": "It is powered by four RL10C-3 engines that produce almost four times more thrust than the one RL10B-2 engine that powers the ICPS.",
          "source_url": "https://www.nasa.gov/reference/space-launch-system/",
          "profile": null,
          "mid": null,
          "function": "Planned replacement for the ICPS from Artemis IV"
        },
        {
          "part": "Universal stage adapter (10,000 cubic ft)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a new 10,000-cubic-foot universal stage adapter",
          "source_url": "https://www.nasa.gov/reference/space-launch-system/",
          "profile": null,
          "mid": null,
          "function": "Cargo compartment for Block 1B"
        }
      ]
    },
    {
      "assembly": "Avionics",
      "parts": [
        {
          "part": "Distributed avionics (engines, boosters, ICPS tied to core stage)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The avionics in the engines, boosters, and ICPS are connected to the flight avionics in the core stage.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf",
          "profile": null,
          "mid": null,
          "function": "Core stage computers use data from every element to fly the rocket"
        }
      ]
    }
  ],
  "materials": [
    {
      "id": "aluminium-2219",
      "name": "Al 2219 aluminium alloy",
      "material_page": null
    },
    {
      "id": "aluminium",
      "name": "lightweight aluminium",
      "material_page": "https://spacemushroom.com/profiles/aluminium/"
    },
    {
      "id": "polyurethane-foam-spray-on",
      "name": "flexible polyurethane foam",
      "material_page": null
    },
    {
      "id": "cork",
      "name": "cork (alongside spray-on foam)",
      "material_page": null
    },
    {
      "id": "steel-grade-unstated",
      "name": "steel (grade not stated)",
      "material_page": null
    },
    {
      "id": "pban-ap-aluminium-propellant",
      "name": "PBAN, ammonium perchlorate and aluminium powder",
      "material_page": null
    },
    {
      "id": "aluminium-unstated",
      "name": "material not stated in sources read",
      "material_page": null
    }
  ],
  "standards": [
    {
      "name": "Al 2219 (alloy designation)",
      "org": "other",
      "used_for": "Core stage test barrel segment"
    }
  ],
  "relations": [
    {
      "type": "carries",
      "target": "RS-25 engine",
      "target_slug": "aerojet-rs-25",
      "note": "Core stage: four engines, in every SLS configuration",
      "quote": "Every SLS configuration uses the core stage with four RS-25 engines.",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/"
    },
    {
      "type": "carries",
      "target": "RL10 engine",
      "target_slug": "ula-rl10",
      "note": "ICPS: one RL10B-2 engine (24,750 lbf)",
      "quote": "feeding a single Aerojet Rocketdyne RL10B-2 engine producing 24,750 lbs. (110 kN) of thrust",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "carries",
      "target": "RL10 engine",
      "target_slug": "ula-rl10",
      "note": "Planned Exploration Upper Stage (Block 1B): four RL10C-3 engines",
      "quote": "It is powered by four RL10C-3 engines that produce almost four times more thrust than the one RL10B-2 engine that powers the ICPS.",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/"
    },
    {
      "type": "carries",
      "target": "Orion spacecraft",
      "target_slug": "nasa-orion",
      "note": "SLS is the launcher for Orion",
      "quote": "the only rocket that can send NASA’s Orion spacecraft, four astronauts, and large cargo directly to the Moon",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/"
    },
    {
      "type": "heritage_of",
      "target": "Space Shuttle",
      "target_slug": null,
      "note": "Reuses shuttle components and design heritage",
      "quote": "A key goal of the SLS design was to reuse space shuttle components or design within shuttle heritage experience where possible.",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "built_on",
      "target": "Space Shuttle solid rocket booster",
      "target_slug": null,
      "note": "Booster adds a fifth segment to the four-segment shuttle design",
      "quote": "Based on the space shuttle solid rocket boosters, the SLS boosters are the largest, most powerful solid propellant boosters ever built for flight.",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "built_on",
      "target": "Delta Cryogenic Second Stage (Delta IV)",
      "target_slug": null,
      "note": "ICPS is a modified Delta IV upper stage",
      "quote": "ICPS is a modified Delta Cryogenic Second Stage, a proven upper stage used on ULA’s Delta IV family of launch vehicles",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Boeing",
      "target_slug": null,
      "note": "Prime contractor for the core stage (and the Exploration Upper Stage)",
      "quote": "Boeing, as the prime contractor for the SLS core stage, is responsible for the design, manufacturing, and testing of the stage.",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Northrop Grumman",
      "target_slug": null,
      "note": "Lead contractor for the solid rocket boosters and separation motors",
      "quote": "Northrop Grumman, lead booster contractor, also produces the booster separation motors",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Aerojet Rocketdyne",
      "target_slug": null,
      "note": "Maker of the RS-25",
      "quote": "The RS-25, manufactured by Aerojet Rocketdyne, is the most efficient rocket engine in its class",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "supplied_by",
      "target": "L3Harris Technologies",
      "target_slug": null,
      "note": "Upgrading an inventory of 16 RS-25 engines to SLS requirements",
      "quote": "is upgrading an inventory of 16 RS-25 engines to SLS performance requirements",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/"
    },
    {
      "type": "supplied_by",
      "target": "Aerojet Rocketdyne",
      "target_slug": null,
      "note": "Makes the ICPS RL10 engine in West Palm Beach, Florida",
      "quote": "Its RL10 engine is manufactured by Aerojet Rocketdyne in its West Palm Beach, Florida facility.",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "supplied_by",
      "target": "L3Harris Technologies",
      "target_slug": null,
      "note": "Named as maker of the ICPS RL10 engine",
      "quote": "The ICPS uses one RL10 engine made by L3Harris.",
      "source_url": "https://www.nasa.gov/reference/space-launch-system/"
    },
    {
      "type": "supplied_by",
      "target": "United Launch Alliance",
      "target_slug": null,
      "note": "Builds the ICPS",
      "quote": "The ICPS is manufactured by ULA.",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Teledyne Brown Engineering",
      "target_slug": null,
      "note": "Builds the launch vehicle stage adapter",
      "quote": "Teledyne Brown Engineering manufactures the launch vehicle stage adapter",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    },
    {
      "type": "supplied_by",
      "target": "NASA Marshall Space Flight Center",
      "target_slug": null,
      "note": "Builds the Orion stage adapter in house",
      "quote": "The Orion stage adapter is manufactured in-house at Marshall.",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2022/03/sls-reference-guide-2022-v2-508-0.pdf"
    }
  ],
  "not_published": "Materials not stated in the sources read: alloy of the barrel, isogrid and skirt panels (only the test barrel segment is named Al 2219), booster steel grade, case insulation and nozzle materials, RS-25 and RL10 engine alloys, ICPS tank alloy, launch vehicle stage adapter material. Block 1B composite booster case is mentioned by NASA but is not flown yet. More detail: Alloys of the tank panels, intertank, engine section, LVSA and OSA beyond those in the current entry are not stated. Case steel grade, insulation and nozzle materials of the boosters, the RS-25 and RL10 internals, ICPS tank alloy, and flight computer, avionics and TVC hardware makers are not named in the NASA pages read. RS-25 and RL10 are cross-linked in the engine entries. The NASA SLS page (updated 24 Mar 2026) still describes the Exploration Upper Stage and Block 1B from Artemis IV; one search result (Wikipedia) reported a Feb 2026 cancellation of the EUS and Block 1B that was not confirmed on a NASA page, so re-check the Block 1B rows before publishing them as current. More detail: Alloys of the tank panels, intertank, engine section, LVSA and OSA beyond those in the current entry are not stated. Case steel grade, insulation and nozzle materials of the boosters, the RS-25 and RL10 internals, ICPS tank alloy, and flight computer, avionics and TVC hardware makers are not named in the NASA pages read. RS-25 and RL10 are cross-linked in the engine entries. The NASA SLS page (updated 24 Mar 2026) still describes the Exploration Upper Stage and Block 1B from Artemis IV; one search result (Wikipedia) reported a Feb 2026 cancellation of the EUS and Block 1B that was not confirmed on a NASA page, so re-check the Block 1B rows before publishing them as current.",
  "depth": "partial",
  "photos": [
    {
      "file": "products/context/nasa-sls-1.jpg",
      "alt": "SLS Block 1 with Orion lifting off from Launch Complex 39B at night on Artemis I",
      "long": "SLS Block 1 with Orion lifting off from Launch Complex 39B at night on Artemis I",
      "kind": "product",
      "credit": "Joel Kowsky | https://www.flickr.com/photos/nasahqphoto/52504616014/in/photostream/",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:Artemis_I_Launch_(NHQ202211160017).jpg"
    },
    {
      "file": "products/context/nasa-sls-2.jpg",
      "alt": "SLS core stage horizontal in the Michoud assembly hall showing its four RS-25 engine nozzles and orange foam insulation",
      "long": "SLS core stage horizontal in the Michoud assembly hall showing its four RS-25 engine nozzles and orange foam insulation",
      "kind": "context",
      "context": "RS-25 nozzles on the core stage",
      "credit": "Jared Lyons | https://images.nasa.gov/details-MAF_20191107_Engine%20Section%20Full_Jnl-3951",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:SLS_Core_Stage_Nov_8_2019.jpg"
    },
    {
      "file": "products/context/nasa-sls-3.jpg",
      "alt": "SLS core stage being lifted in the Vehicle Assembly Building",
      "long": "SLS core stage being lifted in the Vehicle Assembly Building",
      "kind": "product",
      "credit": "NASA/Cory Huston | https://images.nasa.gov/details/KSC-20210612-PH-CSH01_0036",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:Artemis_I_SLS_Core_Stage_Lift_and_Mate.jpg"
    }
  ],
  "context": {
    "size": [],
    "mass": [],
    "orbit": []
  },
  "licence": "Product data CC BY 4.0, cite Space Mushroom. Photos keep their own licences, given per photo.",
  "mcp": "https://spacemushroom.com/mcp"
}