{
  "id": "nasa-saturn-v",
  "title": "Saturn V",
  "maker": "NASA",
  "maker_type": "Space agency",
  "kind": "mission",
  "category": "launchers",
  "page": "https://spacemushroom.com/space-products/nasa-saturn-v/",
  "website": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
  "summary": "Apollo-era NASA launch vehicle; historical engineering sources describe 2219 aluminium propellant tanks in the first stage, 2014-T6 aluminium in the upper stages and 7075-T6 aluminium skins.",
  "application": "The Apollo-era three-stage rocket that sent crews to the Moon. Its stage structures were welded and riveted aluminium alloys chosen for strength at cryogenic temperatures, with honeycomb sandwich panels for insulation and structure.",
  "story": {
    "headline": "Saturn V is the three-stage NASA rocket that sent Apollo crews to the Moon.",
    "intro": [
      "Saturn V was the three-stage rocket NASA used to send crews to the Moon. It stood 363 feet tall and weighed about 6.2 million pounds at liftoff, with 7.6 million pounds of thrust. Thirteen were launched, ten with crews. The first flew in 1967, on the uncrewed Apollo 4.",
      "Its stages were welded and riveted from aluminium alloys, chosen for strength at cryogenic, or extremely low, temperatures. Honeycomb sandwich panels gave insulation and structure. The whole stack was designed with 91 thrust-producing devices: engines, solid motors and small thrusters."
    ],
    "built": [
      {
        "title": "First stage, S-IC",
        "text": "The S-IC is 33 feet across and 138 feet tall, with a kerosene tank below an oxygen tank. Both have 2219 aluminium skins. Five insulated tunnels carry oxygen down through the kerosene tank to the five F-1 engines at the base.",
        "parts": [
          "Fuel tank barrel skin",
          "LOX tank skin",
          "RP-1 fuel tank",
          "LOX suction lines (x5, 17 in) in insulated tunnels",
          "F-1 engines (x5: four gimbaled outer, one fixed centre)"
        ]
      },
      {
        "title": "Second stage, S-II",
        "text": "The S-II is 81.5 feet long and 33 feet across, and most of it is welded 2014-T6 aluminium. The wall shared by its two tanks is a bonded sandwich of aluminium sheets around a fibreglass and phenolic honeycomb core. Foam-filled honeycomb insulates the hydrogen tank.",
        "parts": [
          "Main structure and tanks",
          "Common bulkhead facing sheets",
          "Common bulkhead core",
          "LH2 tank external insulation",
          "J-2 engines (x5: four gimbaled outer, one fixed centre)"
        ]
      },
      {
        "title": "Third stage, S-IVB",
        "text": "The S-IVB tanks are waffle-milled 2014 aluminium alloy. Blocks of sealed fibreglass and polyurethane insulation are bonded into the recesses of the waffle pattern on the hydrogen tank. One J-2 engine burns twice, first to reach Earth orbit and again for the trip to the Moon.",
        "parts": [
          "Propellant tanks",
          "Common bulkhead domes",
          "LH2 tank insulation",
          "J-2 engine (x1, restartable)"
        ]
      },
      {
        "title": "Instrument Unit",
        "text": "The Instrument Unit is a ring 260 inches across and 36 inches tall, weighing about 4,400 pounds. Its structure is aluminium honeycomb sandwich with extruded aluminium channels, in three 120 degree segments. IBM built it, and its launch vehicle digital computer solved the guidance equations.",
        "parts": [
          "IU ring structure",
          "Launch vehicle digital computer (LVDC)",
          "ST-124-M3 inertial platform",
          "Thermal conditioning system (TCS) with sublimator and cold plates"
        ]
      },
      {
        "title": "Launch escape system",
        "text": "A launch escape tower topped the stack. It was a welded titanium tubing truss about 10 feet long, and it carried motors that could pull the command module away in an abort. A boost protective cover of fibreglass and cork shielded the capsule from motor exhaust and ascent heating.",
        "parts": [
          "Launch escape tower",
          "Launch escape motor",
          "Tower jettison motor (TE-M-380)",
          "Boost protective cover"
        ]
      }
    ],
    "materials": [
      {
        "name": "Aluminium alloy 2219",
        "mid": "aluminium-2219",
        "where": "The skins of the first stage's fuel and oxygen tanks."
      },
      {
        "name": "Aluminium alloy 2014-T6",
        "mid": "aluminium-2014-t6",
        "where": "Most of the second stage, including its tanks, and the domes of the third stage's shared bulkhead."
      },
      {
        "name": "Aluminium alloy 7075",
        "mid": "aluminium-7075",
        "where": "Corrugated skin panels of the first stage's thrust structure, intertank and forward skirt, and the shells of the second stage's skirts."
      },
      {
        "name": "16-7 PH stainless steel honeycomb",
        "mid": "stainless-16-7-ph",
        "where": "The heat shield of the first stage's thrust structure, brazed to thin steel face sheets."
      },
      {
        "name": "Fibreglass and polyurethane insulation",
        "mid": "fiberglass-polyurethane-insulation",
        "where": "Sealed blocks bonded into the waffle pattern of the third stage's hydrogen tank."
      },
      {
        "name": "Titanium",
        "mid": "titanium",
        "where": "The first stage's engine fairing bottoms and fins, the launch escape tower and some gas bottles."
      }
    ],
    "connections": "Five F-1 engines powered the first stage and five J-2 engines the second. One J-2 drove the third stage, which also flew as the second stage of the Saturn IB. Rocketdyne built both engines. Boeing made the first stage, North American Aviation the second, Douglas Aircraft the third and IBM the Instrument Unit. The Apollo command and service modules rode on top, with the lunar module inside an adapter. The last Saturn V launched Skylab.",
    "unknown": "The published accounts do not say which alloys went into the F-1 and J-2 engines, or what insulated the first-stage tanks. They also leave out the fasteners, the welding filler and most of the Apollo spacecraft's materials, and they name few makers of valves, pumps and batteries.",
    "facts": [
      {
        "label": "Height",
        "value": "363 ft (111 m)"
      },
      {
        "label": "Liftoff thrust",
        "value": "7.6 million lb (34.5 million N)"
      },
      {
        "label": "Payload to Earth orbit",
        "value": "about 118,000 kg (130 tons)"
      },
      {
        "label": "First stage size",
        "value": "33 ft diameter, 138 ft high"
      },
      {
        "label": "Launches",
        "value": "13 Saturn V launches, 10 crewed"
      },
      {
        "label": "Thrust-producing devices",
        "value": "91 (engines, solid motors and thrusters)"
      }
    ]
  },
  "specifications": [
    {
      "label": "Height",
      "value": "363 ft (111 m)",
      "source_url": "https://www.nasa.gov/learning-resources/for-kids-and-students/what-was-the-saturn-v-grades-5-8/",
      "quote": "The Saturn V rocket was 111 meters (363 feet) tall"
    },
    {
      "label": "Liftoff thrust",
      "value": "7.6 million lb (34.5 million N)",
      "source_url": "https://www.nasa.gov/learning-resources/for-kids-and-students/what-was-the-saturn-v-grades-5-8/",
      "quote": "generated 34.5 million newtons (7.6 million pounds) of thrust at launch"
    },
    {
      "label": "Payload to Earth orbit",
      "value": "about 118,000 kg (130 tons)",
      "source_url": "https://www.nasa.gov/learning-resources/for-kids-and-students/what-was-the-saturn-v-grades-5-8/",
      "quote": "launch about 118,000 kilograms (130 tons) into Earth orbit"
    },
    {
      "label": "First launch",
      "value": "1967 (Apollo 4, uncrewed)",
      "source_url": "https://www.nasa.gov/learning-resources/for-kids-and-students/what-was-the-saturn-v-grades-5-8/",
      "quote": "The first Saturn V was launched in 1967"
    },
    {
      "label": "S-IC size",
      "value": "33 ft diameter, 138 ft high",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
      "quote": "The S-IC was 33 ft in diameter and 138 ft high"
    },
    {
      "label": "S-IC empty mass",
      "value": "303,000 lb",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
      "quote": "The S-1C, which weighed 303,000 lb empty"
    },
    {
      "label": "S-IVB dry mass",
      "value": "about 33,142 lb including interstage",
      "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
      "quote": "The stage dry weight, including interstage, was about 33,142 lb."
    },
    {
      "label": "S-IVB LH2 tank size",
      "value": "21.75 ft diameter, 40 ft long",
      "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
      "quote": "each S-IVB LH2 tank was 21.75 feet in diameter and 40 feet long"
    },
    {
      "label": "S-II size and mass",
      "value": "81.5 ft long, 33 ft diameter, about 88,400 lb empty (98,659 lb with interstage), about 1,034,900 lb fuelled",
      "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
      "quote": "The S-II was 81.5 feet long, 33 feet in diameter, weighed about 88,400 lb"
    },
    {
      "label": "S-II burn time",
      "value": "about six minutes",
      "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
      "quote": "The S-II burned for about six minutes."
    },
    {
      "label": "S-IC propellant burned",
      "value": "4,578,000 lb in about 150 s",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
      "quote": "had consumed 4,578,000 lb of propellant in just 150 seconds"
    },
    {
      "label": "Stage 1 liftoff to staging mass",
      "value": "about 6.2 million lb at liftoff, 1.32 million lb at S-IC staging",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
      "quote": "When the Saturn V left the ground, it weighed about 6.2M lbs; after just 150 seconds"
    },
    {
      "label": "S-IVB gross mass at ignition",
      "value": "about 262,300 lb",
      "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
      "quote": "Gross weight at ignition was about 262,300 lb."
    },
    {
      "label": "Instrument Unit size and mass",
      "value": "260 in diameter, 36 in tall, about 4,400 lb; 22 IUs flew",
      "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
      "quote": "The Version 3 IU was 260\" in diameter, 36\" tall and weighed about 4,400 lb."
    },
    {
      "label": "Number of launches",
      "value": "13 Saturn V launches, 10 crewed",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml",
      "quote": "Of the thirteen Saturn V rockets were launched, ten were crewed."
    },
    {
      "label": "Thrust-producing devices",
      "value": "91 (engines, solid motors and thrusters)",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml",
      "quote": "The Saturn V rocket was designed to include 91 thrust-producing devices"
    },
    {
      "label": "J-2 first flight",
      "value": "26 Feb 1966 on Saturn IB AS-201",
      "source_url": "https://enginehistory.org/Rockets/RPE08.22/RPE08.22.shtml",
      "quote": "The J-2 first flew on 26 Feb 1966 as a Saturn 1B second stage, part of AS-201."
    },
    {
      "label": "Launch escape system size",
      "value": "about 8,000 lb, 33 ft long, about 4 ft maximum diameter",
      "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
      "quote": "The 8,000 lb LES was 33 feet long and had a maximum diameter of about 4 feet."
    }
  ],
  "features": [
    {
      "text": "First stage burns five F-1 engines on RP-1 and LOX",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
      "quote": "five F-1 rocket engines that burned a combination of RP-1 and LOX"
    },
    {
      "text": "Second stage uses five J-2 engines",
      "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
      "quote": "five single-start J-2 rocket engines"
    }
  ],
  "parts": [
    {
      "assembly": "S-IC first stage",
      "parts": [
        {
          "part": "Fuel tank barrel skin",
          "material": "2219-T87 aluminium alloy",
          "form": "skin ranging 0.193 in to 0.170 in thick",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "2219-T87 aluminum alloy skin",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": "aluminium-2219-t87"
        },
        {
          "part": "LOX tank skin",
          "material": "2219 aluminium alloy (temper printed as Y87 in source)",
          "form": "skin 0.254 in to 0.190 in in 8 steps",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Its skin was also of 2219-Y87 aluminum allow",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": "aluminium-2219"
        },
        {
          "part": "Thrust structure skin panels",
          "material": "7075-T6 aluminium alloy",
          "form": "corrugated panels with aluminium rings",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Corrugated 7075-T6 aluminum alloy skin panels stiffened with intermediate aluminum alloy rings",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": "aluminium-7075",
          "mid": "aluminium-7075"
        },
        {
          "part": "Thrust structure heat shield",
          "material": "16-7 PH stainless steel honeycomb",
          "form": "1.0 in honeycomb brazed to 0.010 in steel face sheets",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "1.0” thick 16-7 PH stainless steel honeycomb brazed to 0.010” steel face sheets",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": "stainless-16-7-ph"
        },
        {
          "part": "Intertank",
          "material": "7075-T6 aluminium alloy",
          "form": "corrugated skin panels and five ring frames",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "intertank structure composed of corrugated 7075-T6 aluminum alloy skin panels and five ring frames",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": "aluminium-7075",
          "mid": "aluminium-7075"
        },
        {
          "part": "Forward skirt",
          "material": "7075-T6 aluminium alloy",
          "form": "corrugated skin panels, ring frames and stringers",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "constructed of corrugated 7075-T6 aluminum alloy skin panels stiffened by ring frames and stringers",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": "aluminium-7075",
          "mid": "aluminium-7075"
        }
      ]
    },
    {
      "assembly": "S-II second stage",
      "parts": [
        {
          "part": "Main structure and tanks",
          "material": "2014-T6 aluminium alloy",
          "form": "welded",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Most of the S-II was made of 2014 T6 aluminum alloy",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": "aluminium-2014-t6"
        },
        {
          "part": "Thrust structure shell",
          "material": "7075 aluminium alloy",
          "form": "conical shell",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The shell structure was of 7075 aluminum alloy",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": "aluminium-7075",
          "mid": "aluminium-7075"
        },
        {
          "part": "Thrust structure heat shield",
          "material": "fiberglass honeycomb",
          "form": "honeycomb",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A fiberglass honeycomb heat shield",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": "fiberglass-honeycomb"
        },
        {
          "part": "Common bulkhead facing sheets",
          "material": "2014 aluminium alloy",
          "form": "adhesive-bonded sandwich",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "an adhesive-bonded sandwich with facing sheets of 2014 aluminum alloy",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": "aluminium-2014"
        },
        {
          "part": "Common bulkhead core",
          "material": "fiberglass/phenolic honeycomb",
          "form": "honeycomb core",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "fiberglass/phenolic honeycomb core",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": "fiberglass-phenolic-honeycomb"
        }
      ]
    },
    {
      "assembly": "S-IVB third stage",
      "parts": [
        {
          "part": "Propellant tanks",
          "material": "2014 aluminium alloy",
          "form": "waffle-milled",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "DAC had chosen 2014 aluminum alloy for propellant tanks",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": "aluminium-2014"
        },
        {
          "part": "Common bulkhead domes",
          "material": "2014-T6 aluminium alloy",
          "form": "two hemispherical domes",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "two parallel hemispherical 2014-T6 aluminum alloy domes",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": "aluminium-2014-t6"
        },
        {
          "part": "Common bulkhead core",
          "material": "fiberglass-phenolic honeycomb",
          "form": "bonded between domes",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "separated by a fiberglass-phenolic honeycomb core",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": "fiberglass-phenolic-honeycomb"
        },
        {
          "part": "LH2 tank insulation",
          "material": "fiberglass polyurethane insulation blocks",
          "form": "bonded into waffle recesses",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Sealed fiberglass polyurethane insulation blocks",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": "fiberglass-polyurethane-insulation"
        }
      ]
    },
    {
      "assembly": "Instrument Unit",
      "parts": [
        {
          "part": "IU ring structure",
          "material": "aluminium alloy honeycomb sandwich",
          "form": "three 120 degree segments",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "aluminum alloy honeycomb sandwich material with extruded aluminum channels",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": "aluminium-honeycomb-hexweb",
          "mid": "aluminium-honeycomb-hexweb"
        }
      ]
    },
    {
      "assembly": "S-IC first stage (Boeing)",
      "parts": [
        {
          "part": "F-1 engines (x5: four gimbaled outer, one fixed centre)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "At the S-IC’s base were five F-1 rocket engines that burned a combination of RP-1 and LOX.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Main propulsion, RP-1 and liquid oxygen",
          "specs": [
            {
              "label": "Rated thrust (F-1 development target)",
              "value": "1,522,000 lbf",
              "quote": "aiming at a 1,522,000 lbT rating",
              "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml"
            },
            {
              "label": "Chamber pressure",
              "value": "1,125 psia",
              "quote": "it operated at an unprecedented 1,125 psia chamber pressure",
              "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml"
            }
          ]
        },
        {
          "part": "RP-1 fuel tank",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The fuel tank contained 209,000 gal (1,400,000 lb) of RP-1.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Holds kerosene fuel for the five F-1 engines"
        },
        {
          "part": "Liquid oxygen (LOX) tank",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Above the fuel tank, the LOX tank’s volume was 334,500 gal (3,178,000 lb).",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Holds oxidizer, sits above the fuel tank"
        },
        {
          "part": "Fuel suction lines (x10)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "At its base, 10 fuel suction lines fed the engines in groups of 2.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Carry RP-1 from the tank bottom to the engines, two per engine"
        },
        {
          "part": "LOX suction lines (x5, 17 in) in insulated tunnels",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Within the tank were five insulated LOX tunnels that housed LOX suction lines connecting the LOX tank to the engines.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Carry LOX through the fuel tank to the engines"
        },
        {
          "part": "LOX and fuel prevalves",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "normally-open pneumatically-controlled prevalves that were emergency backups to the engine’s main LOX valves",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Normally-open emergency backups to the engine main valves; outboard LOX prevalve cavities also served as pogo absorbers"
        },
        {
          "part": "High-pressure helium bottles (x4, 31 cubic ft each)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "four 31 ft³ high-pressure helium bottles, the contents of which provided pressurization for the propellant tanks",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Pressurize the propellant tanks; mounted inside the LOX tank"
        },
        {
          "part": "Thrust structure hold-down posts (x4) and engine thrust posts (x4)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a lower thrust ring assembly, center engine support, four holddown posts, four engine thrust posts",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Take the engine thrust and the hold-down loads"
        },
        {
          "part": "Outboard engine fairings and stabilization fins",
          "material": "titanium (fairing bottoms and fins); aluminium alloy (fairing tops); grades not stated",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The fairing bottoms and fins were constructed of titanium; the fairing tops of aluminum alloy.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": "titanium",
          "mid": "titanium",
          "function": "Shield each outboard F-1 from airloads and add stability"
        },
        {
          "part": "Thrust vector control servoactuators (outboard engines)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Hydraulic Research and Manufacturing Co.; Moog, Inc.",
          "quote": "some S-IC stages flew with Hydraulic Research servoactuators while others flew with ones from Moog",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Gimbal the four outer F-1 engines",
          "specs": [
            {
              "label": "Servoactuator size",
              "value": "300 lb, 5 ft long, 11 in stroke",
              "quote": "Weighing 300 lb and 5 ft long, they had a stroke of 11\" and could articulate the running F-1 engine",
              "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml"
            }
          ]
        },
        {
          "part": "Fluid power system (x5, one per engine)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "High-pressure RP-1 tapped off the fuel pump outlet replaced rotary pumps and traditional hydraulic fluid for this application.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Uses RP-1 tapped from the fuel pump outlet instead of a separate hydraulic fluid"
        },
        {
          "part": "Flight batteries (x2, 28 VDC)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Electrical power for S-IC control and measurement came from two independent 28 VDC batteries.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Power stage controls and instrumentation",
          "specs": [
            {
              "label": "Battery capacity",
              "value": "No. 1: 10.67 Ah; No. 2: 20.83 Ah",
              "quote": "The No. 1 10.67 aH main power battery energized the stage controls while the No. 2 20.83 aH battery powered stage instrumentation.",
              "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml"
            }
          ]
        },
        {
          "part": "Electrical distributors (main power, sequence and control, propulsion, timer, thrust OK, measuring, measuring power)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A collection of distributors subdivided the electrical functions and served as junction boxes.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Junction boxes and switching for stage electrical functions"
        },
        {
          "part": "Telemetry links F1, F2, F3 (FM), S1, S2 (vibration) and P1 (PCM)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Links F1, F2 and F3 were identical systems that transmitted narrow-band frequency-modulated data",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Send stage data to the ground"
        },
        {
          "part": "Retro rockets (provision for x8, Thiokol TE-M-424-6)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Thiokol",
          "quote": "The Thiokol TE-M-424-6 solid-propellant retro rocket motors each produced about 88,600 lbT for 0.667 sec",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Solid motors that push the spent stage away at separation",
          "specs": [
            {
              "label": "Retro motor mass",
              "value": "506 lb each, 208 lb propellant",
              "quote": "weighed 506 lb, which included a 208 lb propellant load",
              "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml"
            }
          ]
        },
        {
          "part": "Range safety system (two independent channels)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Two independent identical range safety systems were composed of electronic and ordnance components.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Lets ground controllers shut down engines and open the tanks"
        },
        {
          "part": "Control pressure nitrogen bottle (2,200 cubic in)",
          "material": "titanium alloy (grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A 2,200 in³ titanium alloy spherical storage bottle mounted within the thrust structure",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": "titanium",
          "mid": "titanium",
          "function": "Stores gaseous nitrogen to actuate propellant valves and purge F-1 subsystems"
        }
      ]
    },
    {
      "assembly": "S-II second stage (North American Aviation)",
      "parts": [
        {
          "part": "J-2 engines (x5: four gimbaled outer, one fixed centre)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The S-II propulsion system consisted of five single-start J-2 rocket engines.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Main propulsion, liquid hydrogen and liquid oxygen",
          "specs": [
            {
              "label": "Vacuum thrust per engine (nominal)",
              "value": "228,000 lbf; 1,140,000 lbf total",
              "quote": "developed a nominal vacuum thrust of 228,000 lb each for a total of 1,140,000 lb",
              "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
            }
          ]
        },
        {
          "part": "S-II forward skirt, aft skirt and S-IC/S-II interstage",
          "material": "7075 aluminium alloy",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each unit was a cylindrical shell of semi-monocoque construction, built of 7075 aluminum alloy",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": "aluminium-7075",
          "mid": "aluminium-7075",
          "function": "Cylindrical load-bearing shells of the stage"
        },
        {
          "part": "Thrust structure longerons and centre engine support beam",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Four pairs of thrust longerons (two at each outboard engine location) and a center engine support beam cruciform assembly",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Accept and spread the engine thrust loads"
        },
        {
          "part": "LH2 tank external insulation",
          "material": "foam-filled honeycomb (foam and honeycomb materials not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The insulation material was a foam-filled honeycomb about 1.6\" thick on the LH2 tank sidewalls",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": "foam-filled-honeycomb-insulation",
          "function": "Prevents condensation and limits heat rise; purged with helium"
        },
        {
          "part": "Engine hydraulic control systems and servoactuators (x2 per outboard engine)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each outboard engine had a separate, independent, closed-loop, hydraulic control system that included two servoactuators mounted perpendicular to each other.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Gimbal each outer J-2 about pitch and yaw",
          "specs": [
            {
              "label": "Gimbal range",
              "value": "plus or minus 7 degrees at 8 degrees per second",
              "quote": "The servoactuators were capable of deflecting the engine ± 7° in the pitch and yaw planes, at the rate of 8° per second.",
              "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
            }
          ]
        },
        {
          "part": "Propellant prevalves (x5 per tank)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each propellant tank had five prevalves that provided open/close control of propellant flow through separate feedlines to each engine.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Open/close control of propellant flow to each engine"
        },
        {
          "part": "LH2 feed ducts (x5, 8 in vacuum-jacketed)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The LH2 feed system included five 8\" vacuum-jacketed feed ducts and five normally open prevalves.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Carry liquid hydrogen to the engines"
        },
        {
          "part": "LOX feed ducts (x5, 8 in; four vacuum-jacketed)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The LOX feed system included four 8\", vacuum jacketed feed ducts, one uninsulated feed duct, and five normally open prevalves.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Carry liquid oxygen to the engines"
        },
        {
          "part": "Helium receiver and storage spheres",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The stage onboard pneumatic control system was supplied from the helium receiver.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Supply onboard pneumatic control and valve actuation"
        },
        {
          "part": "Flight batteries (x4 zinc-silver oxide)",
          "material": "zinc-silver oxide batteries",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "In flight the electrical power system busses were energized by four zinc-silver oxide batteries.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": "silver-zinc-battery",
          "function": "Energize the stage electrical busses in flight"
        },
        {
          "part": "Ullage rocket motors (RS-U-601, up to x8, usually x4)",
          "material": "4130 steel case; phenolic exit cone with metal shell",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Rocketdyne (original); Hercules, Inc. (later)",
          "quote": "The RS-U-601 ullage motors were originally built by Rocketdyne in MacGregor, Texas, later by Hercules, Inc.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": "steel-4130",
          "mid": "steel-4130",
          "function": "Settle propellants before J-2 ignition",
          "specs": [
            {
              "label": "Ullage motor thrust",
              "value": "22,700 lbf for 3.7 s",
              "quote": "developed 22,700 lbT for 3.7 seconds",
              "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
            },
            {
              "label": "Case material",
              "value": "4130 steel",
              "quote": "Each 488 lb ullage motor had a 4130 steel case, phenolic exit cone with metal shell",
              "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
            }
          ]
        },
        {
          "part": "Retrorockets (x4, Thiokol Elkton TE-M-29-4)",
          "material": "4130 steel case",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Thiokol (Elkton)",
          "quote": "four Thiokol Elkton TE-M-29-4 retrorockets comprised the system",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": "steel-4130",
          "mid": "steel-4130",
          "function": "Slow the S-II after separation from the S-IVB",
          "specs": [
            {
              "label": "Retrorocket thrust",
              "value": "34,800 lbf for 1.52 s",
              "quote": "34,800 lbT during its 1.52 sec burn time",
              "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
            },
            {
              "label": "Case material",
              "value": "4130 steel",
              "quote": "consisted of a 4130 steel case",
              "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
            }
          ]
        },
        {
          "part": "Stage separation ordnance (EBW firing units and linear shaped charge)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "S-IC/S-II stage separation employed a dual plane technique with the structure between the two stages being severed at two different planes.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Cuts the structure at two planes for S-IC/S-II separation"
        },
        {
          "part": "Propellant dispersion (flight termination) system",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The LH2 tank linear shaped charge when detonated cut a 30-foot vertical opening in the tank.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Opens the tanks with shaped charges if the flight must be ended"
        }
      ]
    },
    {
      "assembly": "S-IVB third stage (Douglas Aircraft)",
      "parts": [
        {
          "part": "J-2 engine (x1, restartable)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The S-IVBs single J-2 engine boosted the Apollo spacecraft into a circular earth orbit on the first burn",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Boosts the stack into orbit, then restarts for the trans-lunar burn"
        },
        {
          "part": "Auxiliary propulsion system (APS) modules (x2, 180 degrees apart)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "APS engines were located in two detachable modules spaced 180° apart on the S-IVB aft skirt.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Roll control during burns; three-axis attitude and propellant control in coast",
          "specs": [
            {
              "label": "APS propellants",
              "value": "monomethyl hydrazine fuel, dinitrogen tetroxide oxidizer",
              "quote": "MIL-P-27404 monomethyl hydrazine (MMH) was used as fuel and MIL-P-28539A dinitrogen tetroxide (N204) was used as an oxidizer for APS engines.",
              "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml"
            }
          ]
        },
        {
          "part": "APS attitude control engines (x6, TRW TR-204, 150 lbf)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: TRW",
          "quote": "Each module contained four engines: three TRW TR-204 150-lbT attitude control engines and one Rocketdyne SE-7-1 70-lbT ullage engine.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Pitch, yaw and roll thrusters, three per module"
        },
        {
          "part": "APS ullage engines (x2, Rocketdyne SE-7-1, 70 lbf)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Rocketdyne",
          "quote": "Each module contained four engines: three TRW TR-204 150-lbT attitude control engines and one Rocketdyne SE-7-1 70-lbT ullage engine.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Settle propellants just before the J-2 restart"
        },
        {
          "part": "Solid-propellant ullage motors (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "It was also fitted with two solid-propellant ullage motors that settled its propellants prior to the first burn.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml",
          "profile": null,
          "mid": null,
          "function": "Settle propellants before the first burn"
        },
        {
          "part": "O2/H2 burner",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The O2/H2 burner produced 15 to 35 lbT through the S-IVB center of gravity.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Heats helium to repressurize the tanks and settles propellants before the restart"
        },
        {
          "part": "S-IVB forward skirt, aft skirt, thrust structure and aft interstage",
          "material": "aluminium alloy (grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "These assemblies, except for the propellant tanks, were built-up skin-and-stringer aluminum alloy airframe construction.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": "aluminium",
          "mid": "aluminium",
          "function": "Load-bearing airframe around the tanks and engine"
        },
        {
          "part": "Helium storage spheres on the thrust structure (x8, titanium)",
          "material": "titanium (grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "one of the eight high-pressure titanium helium storage spheres on the S-IVB thrust structure had exploded",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": "titanium",
          "mid": "titanium",
          "function": "Ambient helium for pressurization and valve control"
        },
        {
          "part": "Propellant utilization probes (LH2 34 ft, LOX 13.5 ft)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Attached to the LOX tank interior were slosh baffles, a chilldown pump, a 13.5-foot-long PU probe",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Measure propellant mass for the PU valve"
        },
        {
          "part": "Propellant chilldown pumps (LOX and LH2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Propellants from each tank were recirculated through the feed systems and return bleed lines by chilldown pumps.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Recirculate propellant to chill the lines and engine before each start"
        },
        {
          "part": "J-2 gimbal actuators (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Moog Industries",
          "quote": "DAC contracted with Moog Industries to build actuators to MSFC specifications.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Linear actuators built to MSFC specifications"
        },
        {
          "part": "Flight batteries (x4 zinc/silver-oxide)",
          "material": "zinc/silver-oxide batteries",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "On board power came from four zinc/silver-oxide batteries, two in the forward equipment area and two in the aft equipment area.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": "silver-zinc-battery",
          "function": "Two forward and two aft"
        },
        {
          "part": "Switch selector and stage sequencer",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "provided up to 112 discrete commands to the stage sequencer",
          "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Turns IU digital commands into stage commands"
        }
      ]
    },
    {
      "assembly": "Instrument Unit (IBM)",
      "parts": [
        {
          "part": "Launch vehicle digital computer (LVDC)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: IBM",
          "quote": "A launch vehicle digital computer (LVDC) was used to solve guidance equations and an analog FCC was used to control the flight path.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Solves the guidance equations"
        },
        {
          "part": "Launch vehicle data adapter (LVDA)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: IBM",
          "quote": "Then IBM started having problems with Launch Vehicle Digital Computer (LVDC) and Launch Vehicle Data Adapter (LVDA) logic failures.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Input/output unit for the LVDC"
        },
        {
          "part": "Analog flight control computer (FCC)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "an analog FCC was used to control the flight path",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Controls the flight path from guidance commands"
        },
        {
          "part": "ST-124-M3 inertial platform",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "During prelaunch, the ST-124-M3 platform was held aligned to the local vertical by a set of gas bearing leveling pendulums.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Space-stabilized platform that measures attitude and acceleration"
        },
        {
          "part": "Thermal conditioning system (TCS) with sublimator and cold plates",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The thermal conditioning system (TCS) that maintained a circulating coolant temperature of 59 (± 1)° F.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Keeps equipment coolant at 59 F, rejects heat by subliming water"
        },
        {
          "part": "Flight batteries (28 VDC silver zinc)",
          "material": "silver-zinc batteries",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Primary IU flight power was supplied by 28 (± 2) VDC silver zinc batteries.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": "silver-zinc-battery",
          "function": "Primary IU flight power"
        },
        {
          "part": "C-band radar transponders (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Saturn V IU carried two C-band radar transponders.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Radio tracking of the vehicle trajectory"
        },
        {
          "part": "Emergency detection system (EDS)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The EDS sensed developing conditions that could cause vehicle failure and reacted to these emergencies in one of two ways.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Senses developing failures and starts an abort or warns the crew"
        },
        {
          "part": "Command communications system (CCS)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The CCS provided for digital data transmission from ground stations to the LVDC.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.31/RPE08.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Digital uplink from ground stations to the LVDC"
        }
      ]
    },
    {
      "assembly": "Launch escape system (top of the stack)",
      "parts": [
        {
          "part": "Launch escape motor",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Lockheed Propulsion Co.",
          "quote": "The launch escape motor, built by the Lockheed Propulsion Co. of Redlands, California, was 186\" long, 26\" in diameter",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Pulls the command module away from the rocket in an abort",
          "specs": [
            {
              "label": "Thrust",
              "value": "138,300 lbf for 3.3 s at sea level",
              "quote": "produced 138,300 lbT for 3.3 sec at sea level",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            }
          ]
        },
        {
          "part": "Pitch control motor",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Lockheed Propulsion Co.",
          "quote": "Built by the Lockheed Propulsion Co. of Redlands, California, it was 22\" long, 8.75\" in diameter",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Pushes the escape system and capsule toward the ocean in a low-altitude abort"
        },
        {
          "part": "Tower jettison motor (TE-M-380)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Thiokol Chemical Corp.",
          "quote": "The TE-M-380 tower jettison motor was used in all missions to jettison the LES.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Pulls the escape system free of the capsule on a normal flight"
        },
        {
          "part": "Launch escape tower",
          "material": "titanium tubing (grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The launch escape tower was a welded titanium tubing truss structure, about 10 feet long",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": "titanium",
          "mid": "titanium",
          "function": "Truss that carries the motors above the command module"
        },
        {
          "part": "Boost protective cover",
          "material": "impregnated fiberglass, honeycomb-cored laminated fiberglass and cork",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Impregnated fiberglass, honeycomb-cored laminated fiberglass, and cork layers comprised the boost protective cover's structure.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": "fiberglass",
          "function": "Shields the command module from motor exhaust and ascent heating"
        },
        {
          "part": "Q-ball and nose cone",
          "material": "Inconel (nose cone; grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Inconel nose cone was 13.37\" long and 13.3\" in diameter.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": "inconel",
          "function": "Measures dynamic pressure about pitch and yaw to monitor angle of attack"
        }
      ]
    }
  ],
  "materials": [
    {
      "id": "aluminium-2219-t87",
      "name": "2219-T87 aluminium alloy",
      "material_page": null
    },
    {
      "id": "aluminium-2219",
      "name": "2219 aluminium alloy (temper printed as Y87 in source)",
      "material_page": null
    },
    {
      "id": "aluminium-7075",
      "name": "7075 aluminium alloy",
      "material_page": "https://spacemushroom.com/profiles/aluminium-7075/"
    },
    {
      "id": "stainless-16-7-ph",
      "name": "16-7 PH stainless steel honeycomb",
      "material_page": null
    },
    {
      "id": "aluminium-2014-t6",
      "name": "2014-T6 aluminium alloy",
      "material_page": null
    },
    {
      "id": "fiberglass-honeycomb",
      "name": "fiberglass honeycomb",
      "material_page": null
    },
    {
      "id": "aluminium-2014",
      "name": "2014 aluminium alloy",
      "material_page": null
    },
    {
      "id": "fiberglass-phenolic-honeycomb",
      "name": "fiberglass-phenolic honeycomb",
      "material_page": null
    },
    {
      "id": "fiberglass-polyurethane-insulation",
      "name": "fiberglass polyurethane insulation blocks",
      "material_page": null
    },
    {
      "id": "aluminium-honeycomb-hexweb",
      "name": "aluminium alloy honeycomb sandwich",
      "material_page": "https://spacemushroom.com/profiles/aluminium-honeycomb-hexweb/"
    },
    {
      "id": "titanium",
      "name": "titanium tubing (grade not stated)",
      "material_page": "https://spacemushroom.com/profiles/titanium/"
    },
    {
      "id": "foam-filled-honeycomb-insulation",
      "name": "foam-filled honeycomb (foam and honeycomb materials not stated)",
      "material_page": null
    },
    {
      "id": "silver-zinc-battery",
      "name": "silver-zinc batteries",
      "material_page": null
    },
    {
      "id": "steel-4130",
      "name": "4130 steel case",
      "material_page": "https://spacemushroom.com/profiles/steel-4130/"
    },
    {
      "id": "aluminium",
      "name": "aluminium alloy (grade not stated)",
      "material_page": "https://spacemushroom.com/profiles/aluminium/"
    },
    {
      "id": "fiberglass",
      "name": "impregnated fiberglass, honeycomb-cored laminated fiberglass and cork",
      "material_page": null
    },
    {
      "id": "inconel",
      "name": "Inconel (nose cone; grade not stated)",
      "material_page": null
    }
  ],
  "standards": [
    {
      "name": "Alloy-temper designations 2219-T87, 7075-T6, 2014-T6",
      "org": "other",
      "used_for": "Stage structures"
    }
  ],
  "relations": [
    {
      "type": "carries",
      "target": "F-1 engine",
      "target_slug": "nasa-rocketdyne-f-1",
      "note": "S-IC: five engines, RP-1 and LOX",
      "quote": "At the S-IC’s base were five F-1 rocket engines that burned a combination of RP-1 and LOX.",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml"
    },
    {
      "type": "carries",
      "target": "J-2 engine",
      "target_slug": "rocketdyne-j-2",
      "note": "S-II: five single-start engines",
      "quote": "The S-II propulsion system consisted of five single-start J-2 rocket engines.",
      "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
    },
    {
      "type": "carries",
      "target": "J-2 engine",
      "target_slug": "rocketdyne-j-2",
      "note": "S-IVB: one engine",
      "quote": "The S-IVBs single J-2 engine boosted the Apollo spacecraft into a circular earth orbit on the first burn",
      "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml"
    },
    {
      "type": "carries",
      "target": "Apollo Command and Service Module",
      "target_slug": "nasa-apollo-command-service-module",
      "note": "Part of the Apollo spacecraft carried on top of the stack",
      "quote": "Service Module (SM), Command Module (CM) and Launch Escape System (LES)",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "carries",
      "target": "Apollo Lunar Module",
      "target_slug": "grumman-apollo-lunar-module",
      "note": "Housed in the spacecraft/lunar module adapter",
      "quote": "consist of the Lunar Module (LM) housed within a Spacecraft/Lunar Module Adapter (SLA)",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "carries",
      "target": "Skylab space station",
      "target_slug": null,
      "note": "The last Saturn V launch put Skylab in orbit",
      "quote": "the last launched Skylab, which was the first U.S. Space Station",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "heritage_of",
      "target": "Saturn IB",
      "target_slug": null,
      "note": "The S-IVB stage also flew as the second stage of the Saturn IB",
      "quote": "The Saturn S-IVB was the second Saturn IB booster stage and third Saturn V booster stage.",
      "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Boeing",
      "target_slug": null,
      "note": "Built the S-IC first stage at Michoud",
      "quote": "SA-500D/F's stage 1, known as S-IC-D was the first S-IC built by Boeing at NASA's Michoud Assembly Facility",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "supplied_by",
      "target": "North American Aviation",
      "target_slug": null,
      "note": "Built the S-II second stage",
      "quote": "Stage 2, built by North American Aviation and known as S-II-F/D",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Douglas Aircraft",
      "target_slug": null,
      "note": "Built the S-IVB third stage",
      "quote": "Stage 3, built by Douglas Aircraft and known as S-IVB-D",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "supplied_by",
      "target": "IBM (International Business Machines)",
      "target_slug": null,
      "note": "Built the Instrument Unit",
      "quote": "Instrument Unit, built by International Business Machines",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Rocketdyne",
      "target_slug": null,
      "note": "Developed the F-1 engine for the S-IC",
      "quote": "the Air Force told Rocketdyne to go build one. It was to be called the F-1.",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Rocketdyne",
      "target_slug": null,
      "note": "Won the J-2 engine contract",
      "quote": "Rocketdyne won the J-2 engine contract",
      "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Thiokol",
      "target_slug": null,
      "note": "S-IC retro rocket motors",
      "quote": "The Thiokol TE-M-424-6 solid-propellant retro rocket motors each produced about 88,600 lbT for 0.667 sec",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Moog, Inc.",
      "target_slug": null,
      "note": "One of two vendors of S-IC thrust vector control servoactuators",
      "quote": "some S-IC stages flew with Hydraulic Research servoactuators while others flew with ones from Moog",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml"
    },
    {
      "type": "supplied_by",
      "target": "TRW",
      "target_slug": null,
      "note": "S-IVB APS attitude control engines",
      "quote": "Each module contained four engines: three TRW TR-204 150-lbT attitude control engines and one Rocketdyne SE-7-1 70-lbT ullage engine.",
      "source_url": "https://enginehistory.org/Rockets/RPE08.30/RPE08.30.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Lockheed Propulsion Co.",
      "target_slug": null,
      "note": "Launch escape motor",
      "quote": "The launch escape motor, built by the Lockheed Propulsion Co. of Redlands, California, was 186\" long, 26\" in diameter",
      "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Hercules, Inc.",
      "target_slug": null,
      "note": "Later builder of the S-II RS-U-601 ullage motors",
      "quote": "The RS-U-601 ullage motors were originally built by Rocketdyne in MacGregor, Texas, later by Hercules, Inc.",
      "source_url": "https://enginehistory.org/Rockets/RPE08.20/RPE08.20.shtml"
    }
  ],
  "not_published": "Not stated in the sources read: F-1 and J-2 engine alloys, S-IC propellant tank insulation, fasteners, welding filler, Apollo spacecraft and launch escape system materials. The S-IC LOX temper is printed as 2219-Y87 in the source (likely a typo for T87; not changed). Sources are the Rocket Propulsion Evolution history site, which cites period NASA manuals, rather than NTRS originals (the scanned NTRS PDFs checked could not be text-read). More detail: Engine internals are left to the F-1 and J-2 entries (no F-1 or J-2 alloys read). Suppliers of most tank valves, pumps, regulators, the S-II and S-IVB batteries, and the IU computer logic parts are not named in the sources read. Sources are the Rocket Propulsion Evolution history site, which cites the Saturn V News Reference (1968) and the SA-503/SA-507 flight manuals; the NTRS originals were not text-readable. The S-IVB page gives both nine and five ambient helium spheres in different paragraphs, so only the eight-sphere statement is used. The S-II ullage motor count is 'up to eight, usually four'. More detail: Engine internals are left to the F-1 and J-2 entries (no F-1 or J-2 alloys read). Suppliers of most tank valves, pumps, regulators, the S-II and S-IVB batteries, and the IU computer logic parts are not named in the sources read. Sources are the Rocket Propulsion Evolution history site, which cites the Saturn V News Reference (1968) and the SA-503/SA-507 flight manuals; the NTRS originals were not text-readable. The S-IVB page gives both nine and five ambient helium spheres in different paragraphs, so only the eight-sphere statement is used. The S-II ullage motor count is 'up to eight, usually four'.",
  "depth": "partial",
  "photos": [
    {
      "file": "products/context/nasa-saturn-v-1.jpg",
      "alt": "Saturn V with Apollo 11 lifting off, seen from the launch tower looking down",
      "long": "Saturn V with Apollo 11 lifting off, seen from the launch tower looking down",
      "kind": "product",
      "credit": "NASA; restored by Michel Vuijlsteke | https://images.nasa.gov/details/S69-39963 http://grin.hq.nasa.gov/IMAGES/LARGE/GPN-2000-000629.jpg on the Wayback Machine at the Wayback Machine http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000629.html on the Wayback Machine at the Wayback Machine",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:Apollo_11_Launch2.jpg"
    },
    {
      "file": "products/context/nasa-saturn-v-2.jpg",
      "alt": "Apollo 11 Saturn V and mobile launcher on the crawler-transporter during rollout",
      "long": "Apollo 11 Saturn V and mobile launcher on the crawler-transporter during rollout",
      "kind": "product",
      "credit": "NASA/KSC | http://images.ksc.nasa.gov/photos/1969/captions/KSC-69PC-0234.html (image link)",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:Apollo_11_rollout_(KSC-69PC-0234).jpg"
    },
    {
      "file": "products/context/nasa-saturn-v-3.jpg",
      "alt": "Aerial view of the Vehicle Assembly Building with a Saturn V on its crawler heading to the pad",
      "long": "Aerial view of the Vehicle Assembly Building with a Saturn V on its crawler heading to the pad",
      "kind": "product",
      "credit": "NASA/unknown photographer | https://web.archive.org/web/20130302144525/http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000614.html; previously at http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000614.html (direct link)",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:Apollo_Saturn_500F_and_VAB.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"
}