{
  "id": "nasa-apollo-command-service-module",
  "title": "Apollo Command and Service Module",
  "maker": "North American Aviation (Rockwell) for NASA",
  "maker_type": "Commercial",
  "kind": "mission",
  "category": "crew",
  "page": "https://spacemushroom.com/space-products/nasa-apollo-command-service-module/",
  "website": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
  "summary": "The three-person spacecraft that flew the Apollo missions; the ASME landmark record describes an aluminium honeycomb inner cabin inside a stainless steel honeycomb outer shell covered with an ablator.",
  "application": "Apollo CSM carried three astronauts to lunar orbit and back. The command module returned at lunar-return speed, so its stainless steel honeycomb shell and ablative coating are a landmark case of reentry heat shield design.",
  "story": {
    "headline": "The Apollo Command and Service Module was the three-person spacecraft that flew NASA's Apollo missions.",
    "intro": [
      "North American Aviation built the Command and Service Module for NASA. It carried three astronauts to lunar orbit and back. Only the command module, which held the crew, returned to Earth, and each flight ended in a splashdown. The cabin air was pure oxygen at 5 pounds per square inch.",
      "The command module has two walls. Its inner cabin is aluminium honeycomb, a cellular core sandwiched between aluminium sheets. The outer shell is the same idea in stainless steel, covered with an ablative coating. The service module carried the fuel cells, the main propulsion system and tanks of very cold hydrogen and oxygen."
    ],
    "built": [
      {
        "title": "Command module shells",
        "text": "The inner pressure shell around the crew is aluminium honeycomb between aluminium alloy sheets. The outer shell is stainless steel honeycomb between stainless steel sheets, and it carries the heat shield. That is Avcoat 5026-39/HC-G, a low-density glass-filled epoxy-novolac resin held in honeycomb.",
        "parts": [
          "Inner pressure shell (crew compartment)",
          "Outer shell (heat shield structure)",
          "Ablative heat shield material"
        ]
      },
      {
        "title": "Thruster tanks and chambers",
        "text": "The command module had reaction control thrusters for turning the spacecraft. Their fuel and oxidiser tanks were titanium, each with a Teflon bladder to push the propellant out. The thruster chambers combined ablative parts, asbestos and a fibreglass wrap.",
        "parts": [
          "Fuel tanks (2)",
          "Oxidizer tanks (2)",
          "Propellant bladders",
          "Thruster thrust-chamber insulation",
          "Thruster outer wrap"
        ]
      },
      {
        "title": "Service module structure",
        "text": "The service module's frame included solid aluminium alloy radial beams, machined into shape. The outer panels, 1 inch thick, were aluminium honeycomb between two aluminium sheets. The VHF antennas, shaped like scimitars, were stainless steel.",
        "parts": [
          "Radial beams",
          "Sector and RCS exterior panels (1 in thick)",
          "VHF scimitar antennas"
        ]
      },
      {
        "title": "Fuel cells and gas tanks",
        "text": "Three fuel cell power plants supplied the primary electrical power. Spherical tanks held very cold oxygen and hydrogen. The oxygen tanks were made of Inconel and the hydrogen tanks of titanium.",
        "parts": [
          "Cryogenic oxygen tanks",
          "Cryogenic hydrogen tanks"
        ]
      }
    ],
    "materials": [
      {
        "name": "Aluminium honeycomb",
        "mid": "aluminium-honeycomb",
        "where": "The command module's inner pressure shell and the service module's outer panels, between aluminium sheets."
      },
      {
        "name": "Stainless steel",
        "mid": "stainless-steel",
        "where": "The honeycomb and sheets of the command module's outer shell, and the service module's VHF antennas."
      },
      {
        "name": "Avcoat 5026-39/HC-G",
        "mid": "avcoat",
        "where": "The ablative heat shield material, a low-density glass-filled epoxy-novolac held in honeycomb."
      },
      {
        "name": "Titanium",
        "mid": "titanium",
        "where": "The command module's helium, fuel and oxidiser tanks, and the service module's hydrogen tanks."
      },
      {
        "name": "Teflon",
        "mid": "ptfe",
        "where": "Bladders inside the command module's propellant tanks, used to push the propellant out."
      },
      {
        "name": "Asbestos",
        "mid": "asbestos",
        "where": "A layer in the thrust chambers of the command module's thrusters, beside an ablative sleeve and a fibreglass wrap."
      }
    ],
    "connections": "Apollo 7, the first crewed flight, launched on 11 October 1968 on a Saturn IB. Bell Aerosystems of Buffalo, New York, made the command module's propellant tanks. Beech Aircraft of Boulder, Colorado, built the service module's oxygen tanks, and Air Products & Chemical built its hydrogen tanks.",
    "unknown": "The alloys of the face sheets and honeycomb cores are not named, and neither is the window glass. The main engine, fuel cells, parachutes and insulation have no published materials. Published lengths for the service module differ slightly.",
    "facts": [
      {
        "label": "Crew",
        "value": "Three astronauts"
      },
      {
        "label": "First crewed flight",
        "value": "Apollo 7, launched 11 October 1968 on a Saturn IB"
      },
      {
        "label": "Cabin atmosphere",
        "value": "100 percent oxygen at 5 psi"
      },
      {
        "label": "Habitable volume",
        "value": "210 cubic feet"
      }
    ]
  },
  "specifications": [
    {
      "label": "Crew",
      "value": "Three astronauts",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
      "quote": "accommodated three astronauts during the mission"
    },
    {
      "label": "First crewed flight",
      "value": "Apollo 7, launched 11 October 1968 on a Saturn IB",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
      "quote": "Launched October 11, 1968, with a Saturn IB."
    },
    {
      "label": "Cabin atmosphere",
      "value": "100 percent oxygen at 5 psi",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
      "quote": "The atmosphere was 100-percent oxygen, pressurized to 5 pounds per square inch"
    },
    {
      "label": "Habitable volume",
      "value": "210 cubic feet",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
      "quote": "habitable volume of 210 cubic feet"
    },
    {
      "label": "Service module size and mass",
      "value": "24 ft 2 in long, 12 ft 10 in diameter, 55,000 lb loaded",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
      "quote": "At 24 feet 2 inches long, 12 feet 10 inches in diameter and weighing 55,000 lb loaded"
    },
    {
      "label": "Apollo spacecraft stack height",
      "value": "82 ft",
      "source_url": "https://enginehistory.org/Rockets/RPE09.00/RPE09.00.shtml",
      "quote": "Sitting atop the Saturn V launch vehicle (LV) was the 82-foot tall Apollo spacecraft."
    },
    {
      "label": "Service module height and mass (ASME landmark record)",
      "value": "24 ft 9 in tall, 12 ft 10 in diameter, 54,160 lb launch weight",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
      "quote": "Height Diameter Launch weight 24 ft 9 in. 12 ft 10 in. 54,160 lb"
    },
    {
      "label": "Mission duration",
      "value": "8 to 10 days from launch to Earth landing",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
      "quote": "The entire trip, from launch to earth landing, would last between 8 to 10 days."
    },
    {
      "label": "Cabin air temperature in flight",
      "value": "70 to 75 F",
      "source_url": "https://enginehistory.org/Rockets/RPE09.00/RPE09.00.shtml",
      "quote": "the cabin was air conditioned to a comfortable 70 - 75 °F"
    },
    {
      "label": "Crew supplies carried",
      "value": "Items for up to 14 days",
      "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
      "quote": "contain all of the items needed by the crew for up to 14 days"
    },
    {
      "label": "Parachute splashdown speed",
      "value": "32 ft/s with three main parachutes, 36 ft/s with two",
      "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf",
      "quote": "Three parachutes - 32 fps Two parachutes - 36 fps"
    },
    {
      "label": "Entry heating and speed",
      "value": "About 24,500 mph at entry, heating up to 5,000 F at the aft heat shield",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml",
      "quote": "The CM, traveling at about 24,500 mph, generated atmospheric heating of up to 5,000°F at the aft heat shield."
    },
    {
      "label": "Production contract scope",
      "value": "49 manned or test spacecraft (command and service modules)",
      "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM27_CSM_Contract_pp257-264.pdf",
      "quote": "The Apollo contract is for development and fabrication of 49 manned or test spacecraft"
    },
    {
      "label": "Prime contract value (3 Feb 1968)",
      "value": "About 2,996,000,000 US dollars",
      "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM27_CSM_Contract_pp257-264.pdf",
      "quote": "Value of the North American Rockwell Space Division contract with NASA's Manned Spacecraft Center on the Apollo program is approximately $2,996,000,000"
    },
    {
      "label": "CM RCS thrust per engine",
      "value": "About 93 lbf",
      "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
      "quote": "Each engine produced about 93 lbT"
    },
    {
      "label": "SPS specific impulse",
      "value": "314 s",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
      "quote": "a 314-sec specific impulse"
    },
    {
      "label": "SPS thrust-vector range",
      "value": "About plus/minus 10 deg (Z) and plus/minus 6 deg (Y)",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
      "quote": "The thrust structure could providing ± 10° inclination about the Z-axis and ± 6° about the Y-axis."
    },
    {
      "label": "Fuel cell redundancy",
      "value": "Three plants normally run; two are sufficient to complete the mission",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
      "quote": "All three power plants normally generated power, but two were sufficient for mission completion"
    },
    {
      "label": "Cryogenic oxygen tank size",
      "value": "26 in diameter, 326 lb each",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
      "quote": "were 26\" in diameter and each held 326 lb"
    },
    {
      "label": "Cryogenic hydrogen tank size",
      "value": "31.75 in diameter, about 29 lb each",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
      "quote": "were 31.75\" in diameter and each held about 29 lb"
    }
  ],
  "features": [
    {
      "text": "Command module is the only part that returned to Earth",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
      "quote": "the CM, the only part to splash down on earth"
    },
    {
      "text": "Service module carried fuel cells, cryogenic tanks and the main propulsion system",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
      "quote": "The SM also contained a major portion of the electrical power subsystem"
    },
    {
      "text": "Fuel cell power plants supplied primary electrical power",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
      "quote": "Three Bacon-type fuel cell power plants"
    }
  ],
  "parts": [
    {
      "assembly": "Command module structure",
      "parts": [
        {
          "part": "Inner pressure shell (crew compartment)",
          "material": "aluminum honeycomb between aluminum alloy sheets",
          "form": "honeycomb sandwich",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The inner pressurized shell was aluminum honeycomb between aluminum alloy sheets.",
          "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
          "profile": null,
          "mid": "aluminium-honeycomb"
        },
        {
          "part": "Outer shell (heat shield structure)",
          "material": "stainless steel honeycomb between stainless steel sheets",
          "form": "honeycomb sandwich",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The outer shell was stainless-steel honeycomb between stainless-steel sheets.",
          "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf",
          "profile": null,
          "mid": "stainless-steel"
        },
        {
          "part": "Ablative heat shield material",
          "material": "Avcoat 5026-39/HC-G",
          "form": "glass-filled epoxy-novolac in honeycomb",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a low-density glass-filled epoxy-novolac system designated Avcoat 5026-39/HC-G",
          "source_url": "https://ntrs.nasa.gov/api/citations/19690013568/downloads/19690013568.pdf",
          "profile": null,
          "mid": "avcoat"
        }
      ]
    },
    {
      "assembly": "Command module reaction control",
      "parts": [
        {
          "part": "Helium tanks (2)",
          "material": "titanium",
          "form": "spherical tanks",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Two spherical titanium helium tanks",
          "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
          "profile": "titanium",
          "mid": "titanium"
        },
        {
          "part": "Fuel tanks (2)",
          "material": "titanium",
          "form": "cylindrical tanks with domed ends",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Two titanium fuel tanks, manufactured by Bell Aerosystems Co. of Buffalo, New York",
          "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
          "profile": "titanium",
          "mid": "titanium"
        },
        {
          "part": "Oxidizer tanks (2)",
          "material": "titanium",
          "form": "cylindrical tanks",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Two titanium oxidizer tanks, manufactured by Bell Aerosystems Co. of Buffalo, New York",
          "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
          "profile": "titanium",
          "mid": "titanium"
        },
        {
          "part": "Propellant bladders",
          "material": "Teflon",
          "form": "bladder",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each tank contained a diffuser tube assembly and a Teflon bladder for positive propellant expulsion.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
          "profile": null,
          "mid": "ptfe"
        },
        {
          "part": "Thruster thrust-chamber insulation",
          "material": "asbestos",
          "form": "layer in thrust chamber assembly",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The thrust chamber assembly consisted of the combustion chamber ablative sleeve, throat insert, ablative body, asbestos, and a fiberglass wrap.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
          "profile": null,
          "mid": "asbestos"
        },
        {
          "part": "Thruster outer wrap",
          "material": "fiberglass",
          "form": "wrap",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The thrust chamber assembly consisted of the combustion chamber ablative sleeve, throat insert, ablative body, asbestos, and a fiberglass wrap.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
          "profile": null,
          "mid": "fiberglass"
        },
        {
          "part": "CM RCS engines (x12, SE-8)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Rocketdyne Division, North American Rockwell",
          "quote": "Twelve ablatively-cooled SE-8 engines, built by North American Rockwell's Rocketdyne Division, of Canoga Park, California",
          "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Roll, pitch and yaw control after service module separation and in some aborts",
          "specs": [
            {
              "label": "Thrust each",
              "value": "About 93 lbf",
              "quote": "Each engine produced about 93 lbT",
              "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml"
            },
            {
              "label": "Propellants",
              "value": "Monomethyl hydrazine fuel, nitrogen tetroxide oxidizer",
              "quote": "fueled by monomethyl hydrazine (MMH) and used nitrogen tetroxide (N2O4) as the oxidizer",
              "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml"
            },
            {
              "label": "Placement",
              "value": "10 engines in the aft compartment, 2 in the forward compartment",
              "quote": "10 engines were in the aft compartment and 2 in the forward compartment",
              "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml"
            },
            {
              "label": "Service life",
              "value": "200 seconds and 3,000 operational cycles per engine",
              "quote": "Each engine's service life was 200 seconds and 3,000 operational cycles.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml"
            }
          ]
        },
        {
          "part": "CM RCS pressurization subsystem",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The pressurization subsystem consisted of a helium supply tank, two dual pressure regulators, two check valves, two pressure relief valves",
          "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml",
          "profile": null,
          "mid": null,
          "function": "Regulates helium to the propellant tanks through dual regulators, check valves and relief valves",
          "specs": [
            {
              "label": "Squib valves",
              "value": "16 squib valves reconfigure helium and propellant flow for dump, purge and abort",
              "quote": "The distribution lines contained 16 squib valves that permitted the helium and propellant distribution configuration to be changed for various functions.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml"
            }
          ]
        }
      ]
    },
    {
      "assembly": "Service module",
      "parts": [
        {
          "part": "Radial beams",
          "material": "solid aluminum alloy",
          "form": "machined, chemically milled",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The solid aluminum alloy radial beams were machined",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": "aluminium",
          "mid": "aluminium"
        },
        {
          "part": "Sector and RCS exterior panels (1 in thick)",
          "material": "aluminum honeycomb core with aluminum face sheets",
          "form": "honeycomb sandwich",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "made of aluminum honeycomb core between two aluminum face sheets",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": "aluminium-honeycomb"
        },
        {
          "part": "Cryogenic oxygen tanks",
          "material": "Inconel (alloy not stated)",
          "form": "spheres",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Inconel oxygen tanks, built by Beech Aircraft of Boulder, Colorado",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": "inconel"
        },
        {
          "part": "Cryogenic hydrogen tanks",
          "material": "titanium",
          "form": "spheres",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The titanium hydrogen tanks, built by Air Products & Chemical Co.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": "titanium",
          "mid": "titanium"
        },
        {
          "part": "VHF scimitar antennas",
          "material": "stainless steel",
          "form": "thin blade antennas",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Made of stainless steel they were about 13.5",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": "stainless-steel"
        }
      ]
    },
    {
      "assembly": "Launch escape system",
      "parts": [
        {
          "part": "Launch escape motor (solid rocket)",
          "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",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Lifts the command module away from a failing launch vehicle on the pad or in first-stage flight",
          "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"
            },
            {
              "label": "Mass",
              "value": "4,794 lb, of which 3,162 lb is propellant",
              "quote": "weighed 4,794 lb (3,162 of which was propellant",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            },
            {
              "label": "Impulse role",
              "value": "Carries the 13,000 lb command module about a mile from the launch vehicle",
              "quote": "This was enough impulse to carry the 13,000 lb CM about a mile from the LV.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            }
          ]
        },
        {
          "part": "Pitch control motor (solid rocket)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Lockheed Propulsion Co.",
          "quote": "The pitch control motor pushed the LES and CM toward the Atlantic Ocean and away from the LV during a low-altitude abort.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Steers the escape path away from the launch vehicle toward the ocean in a low-altitude abort",
          "specs": [
            {
              "label": "Thrust",
              "value": "2,420 lbf for 0.62 s",
              "quote": "produced 2,420 lbT for 0.62 sec",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            },
            {
              "label": "Builder",
              "value": "Lockheed Propulsion Co., Redlands, California",
              "quote": "Built by the Lockheed Propulsion Co. of Redlands, California",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            }
          ]
        },
        {
          "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 tower and boost cover clear of the command module after a normal launch",
          "specs": [
            {
              "label": "Thrust",
              "value": "31,500 lbf for 1.1 s",
              "quote": "produced 31,500 lbT for 1.1 sec",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            },
            {
              "label": "Nozzles",
              "value": "Two fixed nozzles pointing downward and outward",
              "quote": "The motor had two fixed nozzles, located 180° apart, that projected downward and outward",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            },
            {
              "label": "Builder",
              "value": "Thiokol Chemical Corp., Elkton, Maryland",
              "quote": "Built by the Thiokol Chemical Corp. of Elkton, Maryland",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            }
          ]
        },
        {
          "part": "Launch escape tower (welded titanium truss)",
          "material": "Titanium tubing (alloy not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The launch escape tower was a welded titanium tubing truss structure",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": "titanium",
          "mid": "titanium",
          "function": "Truss that carries the escape motors above the command module on four legs",
          "specs": [
            {
              "label": "Size and mass",
              "value": "About 10 ft long, 3 ft square at top, 4 ft square at base, about 500 lb",
              "quote": "about 10 feet long, 3 feet square at the top and 4 feet square at its base, and weighed about 500 lb",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            },
            {
              "label": "Separation hardware",
              "value": "Four legs fastened with studs and frangible explosive nuts",
              "quote": "fastened with studs and frangible explosive nuts",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            }
          ]
        },
        {
          "part": "Launch escape tower rubber insulation",
          "material": "Buna-N rubber",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "were covered with Buna -N rubber insulation, which protected it from the rocket motor exhaust",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": "buna-n-rubber",
          "function": "Protects the tower tubing from the rocket motor exhaust"
        },
        {
          "part": "Boost protective cover",
          "material": "Impregnated fiberglass, honeycomb-cored laminated fiberglass and cork layers",
          "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-honeycomb",
          "function": "Fiberglass-and-cork shroud that shields the command module from launch heating and motor exhaust",
          "specs": [
            {
              "label": "Size and mass (enginehistory.org)",
              "value": "11 ft tall, 13 ft diameter, about 100 lb",
              "quote": "It was 11 feet tall, 13 feet in diameter, and weighed about 100 lb.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            },
            {
              "label": "Mass (Apollo News Reference)",
              "value": "About 700 lb",
              "quote": "The boost protective cover weighs about 700 pounds",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            }
          ]
        },
        {
          "part": "Canards (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The canards were two metallic clamshell aerodynamic control surfaces",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Two clamshell control surfaces that turn the command module heat-shield-first during an abort",
          "specs": [
            {
              "label": "Deployment",
              "value": "Open 11 s after abort initiation by a gas-powered actuator and lock",
              "quote": "They deployed and via a gas-powered actuator to fixed positions 11 seconds after abort initiation",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            }
          ]
        },
        {
          "part": "Q-ball instrument package and Inconel nose cone",
          "material": "Inconel (alloy not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Inconel nose cone was 13.37\" long",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": "inconel",
          "function": "Q-ball senses angle of attack and dynamic pressure for abort decisions; the cone caps the escape system",
          "specs": [
            {
              "label": "Q-ball sensing",
              "value": "Eight static ports feed differential pressure transducers",
              "quote": "The Q-ball had eight static ports that were connected to differential pressure transducers and electronic modules.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
            }
          ]
        },
        {
          "part": "Ballast compartment (lead and depleted uranium weights)",
          "material": "Lead and depleted uranium weights",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a tapered ballast compartment contained lead and depleted uranium weights",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": "lead-depleted-uranium-ballast",
          "function": "Tapered compartment that keeps the escape system stable at all speeds and modes"
        }
      ]
    },
    {
      "assembly": "Command module structure and interior",
      "parts": [
        {
          "part": "Forward heat shield with release mechanism",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "At about 25,000 feet during entry, the forward heat shield is jettisoned to expose the earth landing equipment",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": null,
          "function": "Covers the apex and earth landing equipment; jettisoned during entry to free the parachutes",
          "specs": [
            {
              "label": "Separation parachute",
              "value": "A small parachute mortar-deployed from the heat shield pulls it out of the command module wake",
              "quote": "This parachute exerts a force to extract the jettisoned heat shield",
              "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf"
            },
            {
              "label": "Tower attachment",
              "value": "Four recessed fittings take the launch escape tower legs",
              "quote": "The forward heat shield contains four recessed fittings into which the legs of the launch escape tower are attached.",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Jettison altitude (Earth Landing System report)",
              "value": "Nominal 24,000 ft",
              "quote": "begins with the jettisoning of the forward heat shield at a nominal altitude of 24 000 feet",
              "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf"
            }
          ]
        },
        {
          "part": "Aft heat shield",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Aeronca Manufacturing Co. (panels); Avco Corp. (ablative coating)",
          "quote": "The command module enters the atmosphere with its base down; this is covered by the aft heat shield which is the thickest portion.",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": null,
          "function": "Thickest part of the heat shield; faces forward through entry and carries the highest heating",
          "specs": [
            {
              "label": "Thickness",
              "value": "2 in at the aft portion; the crew compartment and forward portions are thinner",
              "quote": "The heat shield varies in thickness: the aft portion is 2 inches and the crew compartment and forward",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Total heat shield mass",
              "value": "About 3,000 lb",
              "quote": "Total weight of the shield is about 3,000 pounds.",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Panel maker",
              "value": "Heat shield panels by Aeronca Manufacturing Co., Middletown, Ohio",
              "quote": "The heat shield panels are produced by Aeronca Manufacturing Co., Middletown, Ohio",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Ablative coating maker",
              "value": "Ablative coating developed and applied by Avco Corp., Lowell, Massachusetts",
              "quote": "the ablative coating was developed and applied by Avco Corp., Lowell, Mass.",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            }
          ]
        },
        {
          "part": "Crushable ribs (x4)",
          "material": "Bonded laminations of corrugated aluminum",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The ribs are made of bonded laminations of corrugated aluminum which absorb energy by collapsing upon themselves at impact.",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": "aluminium",
          "mid": "aluminium",
          "function": "External impact-attenuation ribs in the aft compartment that hit the water first",
          "specs": [
            {
              "label": "Size",
              "value": "Four ribs, each about 4 in thick and a foot long",
              "quote": "four crushable ribs (each about 4 inches thick and a foot in length) installed in the aft compartment",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            }
          ]
        },
        {
          "part": "Crew couch frames (x3)",
          "material": "Steel framing and tubing (grade not stated), covered with fireproof fiberglass cloth",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The couches were made of steel framing and tubing and covered with a heavy, fireproof fiberglass cloth.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.00/RPE09.00.shtml",
          "profile": null,
          "mid": "steel-grade-unstated",
          "function": "Support the three crew; can be adjusted so the crew can stand and move around"
        },
        {
          "part": "Couch shock-attenuating struts (x8)",
          "material": "Steel wire rings between an inner and outer piston (grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The internal portion of the system consists of eight struts which connect the crew couches to the CM",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": "steel-grade-unstated",
          "function": "Connect the couches to the structure and absorb landing impact",
          "specs": [
            {
              "label": "Energy-absorbing medium (Apollo News Reference)",
              "value": "Steel wire rings deformed between an inner and an outer piston",
              "quote": "steel wire rings between an inner and an outer piston",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Energy-absorbing medium (enginehistory.org)",
              "value": "Eight crushable honeycomb shock struts",
              "quote": "They rested on eight crushable honeycomb shock struts that absorbed landing impact.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.00/RPE09.00.shtml"
            }
          ]
        },
        {
          "part": "Side (unified crew) hatch",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The side hatch is a single integrated assembly which opens outward",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": null,
          "function": "Single outward-opening hatch for entering and leaving the module",
          "specs": [
            {
              "label": "Mass",
              "value": "About 225 lb",
              "quote": "The hatch weighs about 225 pounds",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Latches",
              "value": "Twelve latches around the periphery of the hatch",
              "quote": "opens or closes the 12 latches around the periphery of the hatch",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Counterbalance",
              "value": "Assembly of two nitrogen bottles and a piston",
              "quote": "This consists of two nitrogen bottles and a piston assembly.",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            }
          ]
        },
        {
          "part": "Forward (docking) hatch",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "ablative hatch mounted at the top of the docking tunnel.",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": null,
          "function": "Pressure-and-ablative hatch at the top of the docking tunnel used for transfer to the lunar module",
          "specs": [
            {
              "label": "Latching",
              "value": "Six-point latching with a pump handle",
              "quote": "The forward hatch has a six-point latching",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Mass",
              "value": "About 80 lb",
              "quote": "weighs about 80 pounds",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            }
          ]
        },
        {
          "part": "Window outer panes (x5 windows)",
          "material": "Amorphous fused silica glass (printed as 'silicon' in the source)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The outer windows are made of amorphous-fused silicon",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": "fused-silica-glass",
          "function": "Single outer pane of each window",
          "specs": [
            {
              "label": "Window set",
              "value": "Five windows: two side, two rendezvous and a hatch window",
              "quote": "The CM has five windows:",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Hatch window position",
              "value": "Over the center couch",
              "quote": "The hatch window is over the center couch.",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            },
            {
              "label": "Outer glass temperature limits",
              "value": "Softening 2800 F, melting 3110 F",
              "quote": "The outer window glass has a softening temperature of 2800°F and a melting point of 3110°F.",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            }
          ]
        },
        {
          "part": "Window inner panes (x5 windows)",
          "material": "Tempered silica glass",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The inner windows are made of tempered silica glass",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": "tempered-silica-glass",
          "function": "Double inner panes of each window",
          "specs": [
            {
              "label": "Inner glass softening temperature",
              "value": "2000 F",
              "quote": "The inner window glass has a softening temperature of 2000°F.",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            }
          ]
        },
        {
          "part": "Lower equipment bay (navigation station)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "It is the navigation station and contains most of the guidance and navigation electronics",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": null,
          "function": "Largest equipment bay; holds guidance electronics, optics, computer and batteries",
          "specs": [
            {
              "label": "Contents",
              "value": "Most guidance and navigation electronics, sextant, telescope and computer",
              "quote": "contains most of the guidance and navigation electronics, as well as the sextant and telescope, the computer, and a computer keyboard",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
            }
          ]
        },
        {
          "part": "CM-SM tension ties (x3) and compression pads (x6)",
          "material": "Stainless steel straps (grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "three tension ties which extend from the CM's aft heat shield to six compression pads on the top of the SM",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": "stainless-steel",
          "function": "Hold the command module on the service module until separation"
        },
        {
          "part": "Environmental control unit and oxygen surge tank (left-hand equipment bay)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "including the environmental control unit, the oxygen surge tank, and displays and controls.",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf",
          "profile": null,
          "mid": null,
          "function": "Key cabin environmental control hardware, with its displays and controls"
        },
        {
          "part": "Main display console",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The main display console contained the switches and displays that allowed astronauts to control the spacecraft while in their couches.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml",
          "profile": null,
          "mid": null,
          "function": "Switches and displays that let the crew control the spacecraft from their couches"
        },
        {
          "part": "Docking probe assembly",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The primary function of the docking probe assembly is to provide initial vehicle CSM/LM coupling and attenuate impact energy imposed by vehicle contact.",
          "source_url": "https://www.ibiblio.org/apollo/ApolloProjectOnline/Documents/SMA2A-03-BLOCK%20II%20Volume%201%2019691015/aoh-v1-2-13-dock.pdf",
          "profile": null,
          "mid": null,
          "function": "Extendable probe that soft-captures the LM drogue, then retracts to pull the vehicles together"
        },
        {
          "part": "Docking ring with 12 automatic latches",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "the LM tunnel ring will activate the 12 automatic docking ring latches on the CM and effect a pressure seal",
          "source_url": "https://www.ibiblio.org/apollo/ApolloProjectOnline/Documents/SMA2A-03-BLOCK%20II%20Volume%201%2019691015/aoh-v1-2-13-dock.pdf",
          "profile": null,
          "mid": null,
          "function": "Ring on the command module that mates with the lunar module tunnel ring and seals the interface"
        }
      ]
    },
    {
      "assembly": "Service module structure and thermal",
      "parts": [
        {
          "part": "SM center section and six sectors",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The SM consisted of a circular center section surrounded by six pie-shaped sectors.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Center section holds the engine and helium tanks; six sectors hold tanks, fuel cells and equipment"
        },
        {
          "part": "Space radiators: ECS (x2) and EPS (x8, in the forward fairing)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Two large (30 ft²) ECS space radiators radiated CM cabin and equipment heat to the cold of space.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Reject cabin, equipment and fuel cell waste heat through water-glycol tubes",
          "specs": [
            {
              "label": "Tube layout",
              "value": "Five parallel horizontal primary tubes and four vertical secondary tubes",
              "quote": "five parallel horizontal primary tubes and four parallel vertical secondary tubes through which a water-glycol coolant flowed",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml"
            },
            {
              "label": "EPS radiators",
              "value": "Eight radiators alternate with eight aluminum honeycomb panels in the fairing",
              "quote": "Eight electrical power system radiators alternating with eight aluminum honeycomb panels comprised the fairing.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml"
            },
            {
              "label": "Fairing size",
              "value": "0.5 in thick, 22 in high",
              "quote": "a fairing that was 0.5\" thick and 22\" high",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml"
            }
          ]
        }
      ]
    },
    {
      "assembly": "Service propulsion system",
      "parts": [
        {
          "part": "SPS engine AJ10-137",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Aerojet-General Corporation",
          "quote": "The SPS engine, built by the Aerojet General Corporation Space Propulsion Division of Sacramento, California",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Main engine for mid-course corrections, lunar orbit insertion, return to Earth and post-tower abort",
          "specs": [
            {
              "label": "Thrust (NASA SP-4205)",
              "value": "20,500 lbf (91,200 N)",
              "quote": "the service module motor attained 91,200 newtons (20,500 pounds) of thrust",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html"
            },
            {
              "label": "Thrust (enginehistory.org)",
              "value": "20,000 lbf, pressure-fed, 100 psi chamber pressure, 314 s specific impulse",
              "quote": "The resulting 20,000 lbT pressure-fed engine had a low 100 psi chamber pressure and a 314-sec specific impulse",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Propellants",
              "value": "Aerozine 50 fuel and inhibited nitrogen tetroxide oxidizer",
              "quote": "The oxidizer was inhibited nitrogen tetroxide (N2O4), the fuel was Aerozine 50",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Expansion ratio",
              "value": "6:1 at the nozzle extension joint, 62.5:1 at the exit",
              "quote": "The thrust expansion ratio was 6:1 at the nozzle extension joint and 62.5:1 at the nozzle extension exit.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Life and restarts",
              "value": "750 s service life, minimum 36 restarts",
              "quote": "It had a 750-second service life and could be restarted a minimum of 36 times.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Dimensions and mass",
              "value": "159.944 in high, nozzle exit diameter 98.4 in, about 650 lb",
              "quote": "was 159.944\" high; the nozzle extension exit diameter was 98.4\" and the engine weighed about 650 lb.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            }
          ]
        },
        {
          "part": "SPS injector",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The injector was baffled to enhance combustion stability.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Baffled injector that distributes fuel and oxidizer; baffles added to stop combustion instability",
          "specs": [
            {
              "label": "Ring channels",
              "value": "Changed from 22 ring channels to a 15-ring design when baffles were added",
              "quote": "The resulting injector had 22 ring channels, but this was later changed to a 15-ring design when baffles were added",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Joining method",
              "value": "Electron beam welding replaced brazing after brazed joints leaked",
              "quote": "The assembly process was changed to incorporate electron beam welding, which worked well.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            }
          ]
        },
        {
          "part": "SPS ablative thrust chamber",
          "material": "Laid-up ablative material (hand-laid coated glass fiber in ablative epoxy) with aluminum end flanges",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The ablative thrust chamber consisted of laid-up ablative material with an aluminum flange at each end.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
          "profile": null,
          "mid": "glass-epoxy-ablative",
          "function": "Ablative and film-cooled combustion chamber with an aluminum flange at each end"
        },
        {
          "part": "SPS nozzle extension",
          "material": "Columbium (niobium) to the 40:1 area ratio point, titanium beyond",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The final nozzle was made of columbium to the 40:1 area ratio point and titanium to the end.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
          "profile": null,
          "mid": "columbium-niobium",
          "function": "Radiation-cooled bell that raises the expansion ratio to 62.5:1",
          "specs": [
            {
              "label": "Original design",
              "value": "Titanium nozzle extension of 16 welded compound-curved gores",
              "quote": "The original titanium nozzle extension consisted of 16 compound-curved gores welded together.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            }
          ]
        },
        {
          "part": "SPS bipropellant valve assembly (eight ball valves)",
          "material": "Stainless steel valve balls with fiberglass-impregnated Teflon seals",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Eight bipropellant ball valves distributed fuel and oxidizer to the engine injector assembly.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
          "profile": null,
          "mid": "stainless-steel",
          "function": "Series-parallel ball valves that guarantee engine start and shutdown with one actuator failed",
          "specs": [
            {
              "label": "Ball material",
              "value": "Stainless steel after beryllium proved too soft",
              "quote": "Stainless steel was the material choice for the valve balls after beryllium was tried",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Seal material",
              "value": "Fiberglass-impregnated Teflon after plain Teflon cold-flowed",
              "quote": "so a fiberglass-impregnated Teflon seal was substituted",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Nitrogen supply",
              "value": "Two GN2 pressure tanks at 2,500 psig",
              "quote": "Two GN2 pressure tanks, mounted on the bipropellant valve assembly and pressurized to 2,500 ± 50 psig at 68°F",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Actuations",
              "value": "Supply covers up to 43 valve actuations",
              "quote": "supplied pressure to the injector prevalves for up to 43 actuations",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            }
          ]
        },
        {
          "part": "SPS thrust mount and gimbal actuators",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Aerojet-General Corporation",
          "quote": "Dual sealed electromechanical servo actuators articulated the SPS engine for thrust vector control.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Gimbal ring and dual electromechanical servo actuators that steer the engine",
          "specs": [
            {
              "label": "Gimbal range",
              "value": "Plus or minus 10 deg about Z and plus or minus 6 deg about Y",
              "quote": "The thrust structure could providing ± 10° inclination about the Z-axis and ± 6° about the Y-axis.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Actuator maker",
              "value": "Aerojet actuator with magnetic particle clutch diameters more than quadrupled",
              "quote": "The Aerojet actuator broke ground by more than quadrupling the magnetic particle clutch diameters",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            }
          ]
        },
        {
          "part": "SPS helium tanks (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Sargent Industries",
          "quote": "Two 40\" diameter spherical helium tanks, manufactured by Sargent Industries of El Segundo, California",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
          "profile": null,
          "mid": null,
          "function": "Spherical tanks holding the helium that pressurizes the propellant tanks",
          "specs": [
            {
              "label": "Fill pressure",
              "value": "3,600 psia nominal fill",
              "quote": "Each was nominally filled to 3,600 ± 50 psia",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Capacity and mass",
              "value": "19.4 cubic ft and 393 lb each",
              "quote": "19.4 ft³ capacity, a 0.46\" wall thickness, and weighed 393 lb",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            }
          ]
        },
        {
          "part": "SPS propellant tanks (x4: fuel storage and sump, oxidizer storage and sump)",
          "material": "Titanium (alloy not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: General Motors Allison Division",
          "quote": "The propellant subsystem consisted of two titanium fuel tanks (storage and sump) located in Sector 5, two titanium oxidizer tanks",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml",
          "profile": "titanium",
          "mid": "titanium",
          "function": "Hold Aerozine 50 and nitrogen tetroxide for the main engine",
          "specs": [
            {
              "label": "Maker",
              "value": "General Motors Allison Division, Indianapolis",
              "quote": "The four hemispherically-domed cylindrical propellant tanks were all manufactured by General Motors Corp's Allison Division of Indianapolis, Indiana.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Fuel capacity",
              "value": "15,766.46 lb total fuel capacity at 103.4% fill",
              "quote": "Total fuel capacity was 15,766.46 lb at 103.4%",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            },
            {
              "label": "Oxidizer capacity",
              "value": "25,208.41 lb total oxidizer capacity at 103.4% fill",
              "quote": "Total oxidizer capacity was 25,208.41 lb when the tanks were filled to 103.4%",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
            }
          ]
        }
      ]
    },
    {
      "assembly": "Service module reaction control",
      "parts": [
        {
          "part": "SM RCS thrusters (x16, Marquardt R-4D)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: The Marquardt Corporation",
          "quote": "Four Marquardt R-4D reaction control rocket engines were clustered on the quad exterior.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml",
          "profile": null,
          "mid": null,
          "function": "Four quads of four engines for attitude control, translation, ullage and separation",
          "specs": [
            {
              "label": "Thrust each",
              "value": "About 100 lbf nominal",
              "quote": "Each engine provided approximately 100 lbT and used hypergolic propellants.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml"
            },
            {
              "label": "Propellants",
              "value": "Monomethyl hydrazine fuel and nitrogen tetroxide oxidizer",
              "quote": "The fuel was monomethyl hydrazine (MMH) and the oxidizer was nitrogen tetroxide (N2O4).",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml"
            },
            {
              "label": "Life",
              "value": "1,000 s service life and 10,000 operation cycles",
              "quote": "a 1,000 second service life, was capable of 10,000 operation cycle",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml"
            },
            {
              "label": "Size and mass",
              "value": "13.4 in long, 5 lb, 5.6 in nozzle exit",
              "quote": "was 13.4\" long, weighed 5 lb, and had a 5.6\". nozzle exit diameter",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml"
            },
            {
              "label": "Quad layout",
              "value": "Four quads located 90 degrees apart, each with four engines",
              "quote": "The SM RCS consisted of four similar, independent systems (quads) located 90° apart around the service module. Each quad had four rocket engines",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml"
            }
          ]
        },
        {
          "part": "R-4D thrust chamber",
          "material": "Unalloyed molybdenum coated with molybdenum disilicide",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The combustion chamber was constructed of unalloyed molybdenum coated with molybdenum disilicide to prevent oxidation of the base metal.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml",
          "profile": "molybdenum",
          "mid": "molybdenum",
          "function": "Radiation-cooled combustion chamber; the only non-ablative engines on the command and service module"
        },
        {
          "part": "R-4D nozzle extension",
          "material": "Cobalt-base alloy (grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "nozzle extensions were a cobalt-base alloy",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml",
          "profile": null,
          "mid": "cobalt-base-alloy",
          "function": "Radiation-cooled nozzle skirt with integral stiffener rings"
        },
        {
          "part": "SM RCS helium tanks (x4, one per quad)",
          "material": "Titanium (alloy not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Airite Division of Sargent Industries",
          "quote": "A spherical titanium helium tank, manufactured by the Airite Division of Sargent Industries, El Segundo, California",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml",
          "profile": "titanium",
          "mid": "titanium",
          "function": "Spherical titanium tank pressurizing each quad's propellant tanks"
        },
        {
          "part": "SM RCS propellant tanks (two fuel and two oxidizer per quad)",
          "material": "Titanium (alloy not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Bell Aerosystems Company",
          "quote": "The cylindrical titanium fuel and oxidizer tanks had domed ends and were manufactured by Bell Aerosystems Company of Buffalo, New York.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml",
          "profile": "titanium",
          "mid": "titanium",
          "function": "Titanium tanks with Teflon bladders for positive expulsion"
        }
      ]
    },
    {
      "assembly": "Electrical power",
      "parts": [
        {
          "part": "Fuel cell power plants (x3, Bacon-type)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Pratt & Whitney Aircraft",
          "quote": "The fuel cell powerplants, built by Pratt & Whitney Aircraft of Hartford, Connecticut were 44\" high, 22\" in diameter, and weighed about 245 lb.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Primary DC power from hydrogen and oxygen; also supply drinking water",
          "specs": [
            {
              "label": "Cells",
              "value": "31 single cells in series in a metal pressure jacket",
              "quote": "Each power plant consisted of 31 single cells connected in series and enclosed in a metal pressure jacket.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml"
            },
            {
              "label": "Output",
              "value": "400 to 1,420 W each at 31 to 27 VDC",
              "quote": "Each power plant could nominally supply from 400 to 1,420 watts at 31 to 27 VDC",
              "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml"
            }
          ]
        },
        {
          "part": "Fuel cell electrolyte",
          "material": "83% potassium hydroxide, 17% water by weight",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each power plant cell contained electrolyte consisting of 83% potassium hydroxide (KOH) and 17% water by weight.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": "potassium-hydroxide-electrolyte",
          "function": "Potassium hydroxide solution in each cell"
        },
        {
          "part": "Silver oxide-zinc batteries in the command module (x5)",
          "material": "Silver oxide-zinc",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Five silver oxide-zinc storage batteries were located in the CM lower equipment bay.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": "silver-zinc-battery",
          "function": "Secondary power; three rechargeable batteries power entry and post-landing"
        }
      ]
    },
    {
      "assembly": "Telecommunications",
      "parts": [
        {
          "part": "Unified S-band, VHF/AM and data equipment",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Collins Radio Co.",
          "quote": "Most of the components of the telecommunications subsystem are produced by the Collins Radio Co., Cedar Rapids, Iowa.",
          "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM18_Telecommunications_Subsystem_pp173-188.pdf",
          "profile": null,
          "mid": null,
          "function": "Voice, data, TV, tracking and ranging links to Earth and the lunar module"
        },
        {
          "part": "S-band high-gain antennas (x4)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Four S-band high-gain antennas, mounted outside the SM aft bulkhead, were used for deep space communications.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml",
          "profile": null,
          "mid": null,
          "function": "Deep-space Earth link, folded inside the adapter at launch",
          "specs": [
            {
              "label": "Stowage",
              "value": "Stowed within the spacecraft-LM adapter until transposition and docking",
              "quote": "The high-gain antenna is stowed within the SLA until the transposition and docking maneuver",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM18_Telecommunications_Subsystem_pp173-188.pdf"
            },
            {
              "label": "Steering",
              "value": "Steered through a gimbal system; principal deep-space antenna",
              "quote": "It can be steered through a gimbal system and is the principal antenna",
              "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM18_Telecommunications_Subsystem_pp173-188.pdf"
            }
          ]
        }
      ]
    },
    {
      "assembly": "Guidance, navigation and control",
      "parts": [
        {
          "part": "Inertial measurement unit (IMU)",
          "material": "Beryllium stable member",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: AC Electronics Division, General Motors",
          "quote": "The IMU, manfactured by AC Electronics Division of General Motors, had a 12.6\" diameter and weighed 42.5 lb.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml",
          "profile": "beryllium",
          "mid": "beryllium",
          "function": "Three-gimbal stable platform with gyros and accelerometers that senses attitude and velocity change",
          "specs": [
            {
              "label": "Stable member",
              "value": "Machined from a solid block of beryllium",
              "quote": "The stable member was machined from a solid block of beryllium",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            }
          ]
        },
        {
          "part": "Navigation base",
          "material": "Anodized aluminum alloy sheet, filled with polyurethane foam",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: AC Electronics Division, General Motors",
          "quote": "weighed 17.4 lb, and was made of riveted and bonded preformed anodized aluminum alloy sheet",
          "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml",
          "profile": "anodized-aluminium",
          "mid": "anodized-aluminium",
          "function": "Rigid mount for the IMU and optics",
          "specs": [
            {
              "label": "Size and maker",
              "value": "27.0 x 22.0 x 4.5 in, made by AC Electronics",
              "quote": "The Navigation Base (AC Electronics) was 27.0\" x 22.0\" x 4.5\"",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            },
            {
              "label": "Filling",
              "value": "Filled with polyurethane foam",
              "quote": "It was filled with polyurethane foam and formed a rigid supporting structure for the IMU and optical equipment.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            }
          ]
        },
        {
          "part": "Optical subsystem (scanning telescope and sextant)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Kollsman Instrument Co.",
          "quote": "It consisted of a navigation base, a scanning telescope, a sextant, and equipment to permit operation with the CMC and IGS.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml",
          "profile": null,
          "mid": null,
          "function": "Star and landmark sightings for navigation",
          "specs": [
            {
              "label": "Maker",
              "value": "Optics produced by Kollsman Instrument Co.",
              "quote": "the optics was produced by Kollsman Instrument Co.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            },
            {
              "label": "Sextant",
              "value": "28x magnification, 1.8 deg field of view, sights two celestial targets at once",
              "quote": "28x magnification, 1.8° field of view instrument that could sight two celestial targets simultaneously",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            },
            {
              "label": "Scanning telescope",
              "value": "1x, 60 deg field of view",
              "quote": "The scanning telescope was a single line-of-sight, refracting 1x magnification instrument with 60° instantaneous field of view.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            }
          ]
        },
        {
          "part": "Command module computer (Block II Apollo Guidance Computer)",
          "material": "Gold-alodined aluminum alloy box",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Raytheon Co. (built); MIT Instrumentation Laboratory (designed)",
          "quote": "was 24\" x 12.5\" x 6\" (0.97 ft³) gold-alodined aluminum alloy box that weighed 70.1 lb",
          "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml",
          "profile": "aluminium",
          "mid": "aluminium",
          "function": "Digital computer for guidance, navigation and engine commands",
          "specs": [
            {
              "label": "Designer and builder",
              "value": "Designed by MIT Instrumentation Laboratory, built by Raytheon",
              "quote": "The CMC, designed by the Massachusetts Institute of Technology (MIT) Instrumentation Laboratory and built by the Raytheon Co.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            },
            {
              "label": "Power",
              "value": "55 W at 28 VDC",
              "quote": "It power consumption was 55 watts at 28 VDC.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            },
            {
              "label": "Memory",
              "value": "36,864 words fixed and 2,048 words erasable",
              "quote": "Both fixed and erasable memory sizes were increased to 36,864 and 2,048 words.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.50/RPE09.50.shtml"
            },
            {
              "label": "Logic",
              "value": "Dual three-input NOR gate integrated circuits in 10-lead flatpacks",
              "quote": "a new IC logic family featuring dual 3-input NOR gates in a single, smaller, 10-lead flatpack",
              "source_url": "https://enginehistory.org/Rockets/RPE09.50/RPE09.50.shtml"
            },
            {
              "label": "Frame",
              "value": "Block II frame changed from aluminum to magnesium alloys, saving 12 lb",
              "quote": "a change from aluminum to magnesium alloys for the Block II computer frame, saving 12 lb",
              "source_url": "https://enginehistory.org/Rockets/RPE09.50/RPE09.50.shtml"
            }
          ]
        },
        {
          "part": "Display and keyboard (DSKY) panels (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The information display that resulted from computations, and the control of the computer by the astronauts was accomplished with two display-keyboard (DSKY) panels.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml",
          "profile": null,
          "mid": null,
          "function": "Crew interface to the computer",
          "specs": [
            {
              "label": "Size and mass",
              "value": "8 x 8 x 7 in, 17.5 lb",
              "quote": "The display keyboard (DSKY) was an 8\" x 8\" x 7\" panel that weighed 17.5 lb.",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            }
          ]
        },
        {
          "part": "Stabilization and control gyro assemblies (x2)",
          "material": "Welded aluminum alloy enclosure",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Honeywell, Inc.",
          "quote": "Gyro Assemblies (Honeywell) – Two gyroscope assemblies, each 6.00\" x 7.00\" by 14.25\" and weighing 22.44 lb",
          "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml",
          "profile": "aluminium",
          "mid": "aluminium",
          "function": "Attitude gyros for the backup stabilization and control subsystem",
          "specs": [
            {
              "label": "Mass",
              "value": "22.44 lb each",
              "quote": "weighing 22.44 lb",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            },
            {
              "label": "Prime contractor",
              "value": "SCS produced by Honeywell, Inc., Minneapolis",
              "quote": "The SCS, produced by Honeywell, Inc., Minneapolis, Minnesota",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            }
          ]
        },
        {
          "part": "Rotation controls (x2), translation control and flight director attitude indicators (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Honeywell, Inc.",
          "quote": "Rotation Controls (Honeywell) – Two identical three-axes rotation controls provided proportional rate command signals",
          "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml",
          "profile": null,
          "mid": null,
          "function": "Honeywell hand controllers and attitude displays of the stabilization and control subsystem",
          "specs": [
            {
              "label": "Attitude indicators",
              "value": "Two FDAIs in 9-lb metal boxes",
              "quote": "Flight Director Attitude Indicator (FDAI) (Honeywell) – Two indicators were each in a 9-lb metal box",
              "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
            }
          ]
        }
      ]
    },
    {
      "assembly": "Earth landing system",
      "parts": [
        {
          "part": "Drogue parachutes (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Two 16.5-foot-diameter conical ribbon drogue parachutes are mortar-deployed",
          "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf",
          "profile": null,
          "mid": null,
          "function": "Stabilize and slow the command module after forward heat shield jettison",
          "specs": [
            {
              "label": "System",
              "value": "Nine parachutes in total, all used in the recovery sequence",
              "quote": "Nine parachutes are installed on the CM all of which function during the recovery sequence.",
              "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf"
            }
          ]
        },
        {
          "part": "Pilot parachutes (x3)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "three 7.2-foot-diameter ringslot pilot parachutes",
          "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf",
          "profile": null,
          "mid": null,
          "function": "Pull the main parachutes out of their packs"
        },
        {
          "part": "Main parachutes (x3)",
          "material": "Lightweight 1.1 oz nylon cloth",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each main parachute then inflates through two reefing stages to a full-open condition.",
          "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf",
          "profile": null,
          "mid": "nylon",
          "function": "Final descent canopies, each opening through two reefing stages",
          "specs": [
            {
              "label": "Nominal diameter",
              "value": "83.5 ft",
              "quote": "Nominal diameter: 83.5 ft",
              "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf"
            },
            {
              "label": "Cloth",
              "value": "A high percentage of the canopy is 1.1 oz nylon cloth",
              "quote": "a high percentage of the main parachute is fabricated from lightweight (1.1 ounce) nylon cloth",
              "source_url": "https://ntrs.nasa.gov/api/citations/19740003586/downloads/19740003586.pdf"
            }
          ]
        },
        {
          "part": "Uprighting flotation bags (x3)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "At splashdown, the crew jettisoned the main parachutes, deployed CM flotation bags to keep it upright",
          "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml",
          "profile": null,
          "mid": null,
          "function": "Inflate after splashdown to right the capsule",
          "specs": [
            {
              "label": "Count and location",
              "value": "Three bags installed under the main parachutes",
              "quote": "Three uprighting flotation bags are installed under the main parachutes.",
              "source_url": "https://www.ibiblio.org/apollo/ApolloProjectOnline/Documents/SMA2A-03-BLOCK%20II%20Volume%201%2019691015/aoh-v1-2-09-seqsys.pdf"
            }
          ]
        },
        {
          "part": "VHF recovery antennas (x2) and flashing beacon",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Deploy the two VHF recovery antennas and the flashing beacon light.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Deployed after main parachute opening to help recovery forces find the capsule"
        }
      ]
    },
    {
      "assembly": "Launch vehicle interface",
      "parts": [
        {
          "part": "Spacecraft-lunar module adapter (SLA)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The SLA served as a smooth aerodynamic enclosure for the lunar module during boost",
          "source_url": "https://enginehistory.org/Rockets/RPE09.00/RPE09.00.shtml",
          "profile": null,
          "mid": null,
          "function": "Aerodynamic enclosure for the LM and link to the launch vehicle; jettisoned after translunar injection"
        },
        {
          "part": "Emergency detection system (EDS)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The emergency detection system (EDS) operated from LV umbilical separation until 100 seconds after liftoff.",
          "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml",
          "profile": null,
          "mid": null,
          "function": "Detects launch vehicle emergencies, displays them and can start an automatic abort"
        }
      ]
    }
  ],
  "materials": [
    {
      "id": "aluminium-honeycomb",
      "name": "aluminum honeycomb core with aluminum face sheets",
      "material_page": null
    },
    {
      "id": "stainless-steel",
      "name": "Stainless steel valve balls with fiberglass-impregnated Teflon seals",
      "material_page": null
    },
    {
      "id": "avcoat",
      "name": "Avcoat 5026-39/HC-G",
      "material_page": null
    },
    {
      "id": "titanium",
      "name": "Titanium (alloy not stated)",
      "material_page": "https://spacemushroom.com/profiles/titanium/"
    },
    {
      "id": "ptfe",
      "name": "Teflon",
      "material_page": null
    },
    {
      "id": "asbestos",
      "name": "asbestos",
      "material_page": null
    },
    {
      "id": "fiberglass",
      "name": "fiberglass",
      "material_page": null
    },
    {
      "id": "aluminium",
      "name": "Welded aluminum alloy enclosure",
      "material_page": "https://spacemushroom.com/profiles/aluminium/"
    },
    {
      "id": "inconel",
      "name": "Inconel (alloy not stated)",
      "material_page": null
    },
    {
      "id": "buna-n-rubber",
      "name": "Buna-N rubber",
      "material_page": null
    },
    {
      "id": "fiberglass-honeycomb",
      "name": "Impregnated fiberglass, honeycomb-cored laminated fiberglass and cork layers",
      "material_page": null
    },
    {
      "id": "lead-depleted-uranium-ballast",
      "name": "Lead and depleted uranium weights",
      "material_page": null
    },
    {
      "id": "steel-grade-unstated",
      "name": "Steel wire rings between an inner and outer piston (grade not stated)",
      "material_page": null
    },
    {
      "id": "fused-silica-glass",
      "name": "Amorphous fused silica glass (printed as 'silicon' in the source)",
      "material_page": null
    },
    {
      "id": "tempered-silica-glass",
      "name": "Tempered silica glass",
      "material_page": null
    },
    {
      "id": "glass-epoxy-ablative",
      "name": "Laid-up ablative material (hand-laid coated glass fiber in ablative epoxy) with aluminum end flanges",
      "material_page": null
    },
    {
      "id": "columbium-niobium",
      "name": "Columbium (niobium) to the 40:1 area ratio point, titanium beyond",
      "material_page": null
    },
    {
      "id": "molybdenum",
      "name": "Unalloyed molybdenum coated with molybdenum disilicide",
      "material_page": "https://spacemushroom.com/profiles/molybdenum/"
    },
    {
      "id": "cobalt-base-alloy",
      "name": "Cobalt-base alloy (grade not stated)",
      "material_page": null
    },
    {
      "id": "potassium-hydroxide-electrolyte",
      "name": "83% potassium hydroxide, 17% water by weight",
      "material_page": null
    },
    {
      "id": "silver-zinc-battery",
      "name": "Silver oxide-zinc",
      "material_page": null
    },
    {
      "id": "beryllium",
      "name": "Beryllium stable member",
      "material_page": "https://spacemushroom.com/profiles/beryllium/"
    },
    {
      "id": "anodized-aluminium",
      "name": "Anodized aluminum alloy sheet, filled with polyurethane foam",
      "material_page": "https://spacemushroom.com/profiles/anodized-aluminium/"
    },
    {
      "id": "nylon",
      "name": "Lightweight 1.1 oz nylon cloth",
      "material_page": null
    }
  ],
  "standards": [],
  "relations": [
    {
      "type": "launched_on",
      "target": "Saturn V",
      "target_slug": "nasa-saturn-v",
      "note": "The 82-foot Apollo spacecraft sat atop the Saturn V launch vehicle",
      "quote": "Sitting atop the Saturn V launch vehicle (LV) was the 82-foot tall Apollo spacecraft.",
      "source_url": "https://enginehistory.org/Rockets/RPE09.00/RPE09.00.shtml"
    },
    {
      "type": "launched_on",
      "target": "Saturn IB",
      "target_slug": null,
      "note": "Apollo 7, the first crewed Apollo flight, launched on a Saturn IB",
      "quote": "Launched October 11, 1968, with a Saturn IB.",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf"
    },
    {
      "type": "launched_on",
      "target": "F-1 engine",
      "target_slug": "nasa-rocketdyne-f-1",
      "note": "Five on the Saturn V S-IC first stage; Saturn V first-stage engines; launcher engine, not carried by the vehicle",
      "quote": "Note that each F-1 engine produced 1.5 M lbT",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "launched_on",
      "target": "J-2 engine",
      "target_slug": "rocketdyne-j-2",
      "note": "Five on the Saturn V S-II second stage; Saturn V second-stage engines; launcher engine, not carried by the vehicle",
      "quote": "The S-II second stage, using five J-2 engines burning liquid hydrogen (LH2) and LOX",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "launched_on",
      "target": "J-2 engine",
      "target_slug": "rocketdyne-j-2",
      "note": "One restartable engine on the S-IVB; Saturn V third stage and Saturn IB second stage engine; launcher engine, not carried by the vehicle",
      "quote": "The S-IVB, with a single J-2 LH2/LOX engine producing 230,000 lbT",
      "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml"
    },
    {
      "type": "launched_on",
      "target": "H-1 engine",
      "target_slug": null,
      "note": "Eight on the Saturn IB S-IB first stage; Saturn IB first-stage engines; launcher engine, not carried by the vehicle",
      "quote": "Eight Rocketdyne H-1b engines burning RP-1 and LOX provided 1,852,822 lbT",
      "source_url": "https://enginehistory.org/Rockets/RPE07/RPE07.shtml"
    },
    {
      "type": "carries",
      "target": "AJ10-137 engine",
      "target_slug": null,
      "note": "Service propulsion engine, Aerojet-General; one 20,500 lbf main engine in the service module",
      "quote": "The SPS engine, built by the Aerojet General Corporation Space Propulsion Division of Sacramento, California",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
    },
    {
      "type": "carries",
      "target": "R-4D engine",
      "target_slug": null,
      "note": "Reaction control engine, Marquardt; sixteen ~100 lbf engines in four service module quads",
      "quote": "Four Marquardt R-4D reaction control rocket engines were clustered on the quad exterior.",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml"
    },
    {
      "type": "carries",
      "target": "SE-8 engine",
      "target_slug": null,
      "note": "Reaction control engine, Rocketdyne; twelve ablative ~93 lbf command module engines",
      "quote": "Twelve ablatively-cooled SE-8 engines, built by North American Rockwell's Rocketdyne Division, of Canoga Park, California",
      "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml"
    },
    {
      "type": "carries",
      "target": "Apollo launch escape motor",
      "target_slug": null,
      "note": "Lockheed Propulsion Co.; 138,300 lbf solid rocket on the escape tower",
      "quote": "The launch escape motor, built by the Lockheed Propulsion Co. of Redlands, California",
      "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
    },
    {
      "type": "carries",
      "target": "Apollo pitch control motor",
      "target_slug": null,
      "note": "Lockheed Propulsion Co.; 2,420 lbf solid rocket on the escape tower",
      "quote": "The pitch control motor pushed the LES and CM toward the Atlantic Ocean and away from the LV during a low-altitude abort.",
      "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
    },
    {
      "type": "carries",
      "target": "TE-M-380 motor",
      "target_slug": null,
      "note": "Tower jettison motor, Thiokol; 31,500 lbf solid rocket on the escape tower",
      "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"
    },
    {
      "type": "supplied_by",
      "target": "North American Aviation (North American Rockwell)",
      "target_slug": null,
      "note": "Prime contractor; built the command and service modules",
      "quote": "The command module, built by North American Aviation",
      "source_url": "https://www.asme.org/wwwasmeorg/media/ResourceFiles/AboutASME/Who%20We%20Are/Engineering%20History/Landmarks/162-Apollo-Space-Command-Module.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Aerojet-General Corporation",
      "target_slug": null,
      "note": "Service propulsion engine and gimbal actuators",
      "quote": "Aerojet got the Apollo SPS engine development contract in April 1962",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
    },
    {
      "type": "supplied_by",
      "target": "The Marquardt Corporation",
      "target_slug": null,
      "note": "Service module R-4D reaction control engines",
      "quote": "The engines were produced by The Marquardt Corporation of Van Nuys, California.",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.32.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Rocketdyne Division, North American Rockwell",
      "target_slug": null,
      "note": "Command module SE-8 reaction control engines",
      "quote": "Rocketdyne would supply the command module thrusters",
      "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html"
    },
    {
      "type": "supplied_by",
      "target": "Lockheed Propulsion Co.",
      "target_slug": null,
      "note": "Launch escape motor and pitch control motor",
      "quote": "Built by the Lockheed Propulsion Co. of Redlands, California",
      "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Thiokol Chemical Corp.",
      "target_slug": null,
      "note": "Tower jettison motor TE-M-380",
      "quote": "Built by the Thiokol Chemical Corp. of Elkton, Maryland",
      "source_url": "https://enginehistory.org/Rockets/RPE09.10/RPE09.10.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Pratt & Whitney Aircraft",
      "target_slug": null,
      "note": "Three fuel cell power plants",
      "quote": "The fuel cell powerplants, built by Pratt & Whitney Aircraft of Hartford, Connecticut",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Beech Aircraft",
      "target_slug": null,
      "note": "Inconel cryogenic oxygen tanks",
      "quote": "The Inconel oxygen tanks, built by Beech Aircraft of Boulder, Colorado",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Air Products & Chemical Co.",
      "target_slug": null,
      "note": "Titanium cryogenic hydrogen tanks",
      "quote": "The titanium hydrogen tanks, built by Air Products & Chemical Co., Inc. of Allentown, Pennsylvania",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.30.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Sargent Industries (including its Airite Division)",
      "target_slug": null,
      "note": "SPS helium tanks and SM RCS helium tanks",
      "quote": "Two 40\" diameter spherical helium tanks, manufactured by Sargent Industries of El Segundo, California",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
    },
    {
      "type": "supplied_by",
      "target": "General Motors Allison Division",
      "target_slug": null,
      "note": "SPS titanium propellant tanks",
      "quote": "all manufactured by General Motors Corp's Allison Division of Indianapolis, Indiana",
      "source_url": "https://enginehistory.org/Rockets/RPE09.30/RPE09.31.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Bell Aerosystems Company",
      "target_slug": null,
      "note": "Command module and service module RCS propellant tanks",
      "quote": "Two titanium fuel tanks, manufactured by Bell Aerosystems Co. of Buffalo, New York",
      "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Menasco Manufacturing Co.",
      "target_slug": null,
      "note": "Command module RCS helium tanks",
      "quote": "Two spherical titanium helium tanks, manufactured by the Menasco Manufacturing Co., of Burbank, California",
      "source_url": "https://enginehistory.org/Rockets/RPE09.20/RPE09.20.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Honeywell, Inc.",
      "target_slug": null,
      "note": "Stabilization and control subsystem",
      "quote": "The SCS, produced by Honeywell, Inc., Minneapolis, Minnesota",
      "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
    },
    {
      "type": "supplied_by",
      "target": "AC Electronics Division of General Motors",
      "target_slug": null,
      "note": "Production and integration of the guidance and navigation system; IMU",
      "quote": "AC Electronics Division of General Motors was responsible for its production, operation, and integration.",
      "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
    },
    {
      "type": "supplied_by",
      "target": "MIT Instrumentation Laboratory",
      "target_slug": null,
      "note": "Guidance and navigation design; computer designer",
      "quote": "MIT was responsible for GNS design and development.",
      "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Raytheon Co.",
      "target_slug": null,
      "note": "Built the command module computer",
      "quote": "The CMC was manufactured by the Raytheon Co.",
      "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Kollsman Instrument Co.",
      "target_slug": null,
      "note": "Optical subsystem",
      "quote": "the optics was produced by Kollsman Instrument Co.",
      "source_url": "https://enginehistory.org/Rockets/RPE09.21/RPE09.21.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Collins Radio Co.",
      "target_slug": null,
      "note": "Most telecommunications components",
      "quote": "Most of the components of the telecommunications subsystem are produced by the Collins Radio Co., Cedar Rapids, Iowa.",
      "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM18_Telecommunications_Subsystem_pp173-188.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Aeronca Manufacturing Co.",
      "target_slug": null,
      "note": "Heat shield panels",
      "quote": "The heat shield panels are produced by Aeronca Manufacturing Co., Middletown, Ohio",
      "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Avco Corp.",
      "target_slug": null,
      "note": "Ablative heat shield coating",
      "quote": "the ablative coating was developed and applied by Avco Corp., Lowell, Mass.",
      "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM06_Command_Module_Overview_pp39-52.pdf"
    },
    {
      "type": "operated_by",
      "target": "NASA Manned Spacecraft Center (customer)",
      "target_slug": null,
      "note": "North American Rockwell built the spacecraft under a contract with NASA's Manned Spacecraft Center",
      "quote": "Value of the North American Rockwell Space Division contract with NASA's Manned Spacecraft Center on the Apollo program is approximately $2,996,000,000",
      "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/CSM27_CSM_Contract_pp257-264.pdf"
    }
  ],
  "not_published": "Missing: face sheet and core alloys, window glass, service propulsion engine, fuel cell, parachute and insulation materials; standards. More detail: Not found in public sources that could be fetched: suppliers of the environmental control system, cabin fans and suit loop, waste management, food and water hardware, the launch escape and CM forward-compartment hardware beyond the motors, the parachute maker (Northrop Ventura appears in NASA TN D-7437 only as maker of a failed parachute link assembly, in a garbled appendix), the SLA builder, and the batteries and inverters. Materials not stated for most structures: the stated ones are titanium tower tubing, Buna-N insulation, Inconel nose cone, lead and depleted uranium ballast, fiberglass and cork boost cover, steel couch framing, silica window glass, molybdenum and cobalt-base R-4D parts, columbium and titanium SPS nozzle, stainless steel SPS valve balls, beryllium IMU stable member and nylon main parachute cloth. Conflicting values are listed side by side: boost protective cover 100 lb versus 700 lb, SPS thrust 20,000 versus 20,500 lbf, forward heat shield jettison 24,000 versus 25,000 ft, couch struts honeycomb versus steel wire rings, service module height 24 ft 2 in (existing entry) versus 24 ft 9 in (ASME). The Apollo 11 Press Kit and the Apollo Operations Handbook text were only readable as OCR; quotes come from cleaner enginehistory.org, NASA SP-4205 and Apollo News Reference chapters. No fetched source ties the A7L suit name to the command module, so no relation to nasa-apollo-a7l-spacesuit is given; the lunar module was not made a carries target because it docks rather than rides inside the CSM. The Apollo 11 Press Kit PDFs on nasa.gov returned 404 and the web search budget ran out before NASM object pages could be checked.",
  "depth": "partial",
  "photos": [
    {
      "file": "products/context/nasa-apollo-command-service-module-1.jpg",
      "alt": "Apollo 17 Command and Service Module in lunar orbit photographed from the Lunar Module, service module panel bay open, Moon",
      "long": "Apollo 17 Command and Service Module in lunar orbit photographed from the Lunar Module, service module panel bay open, Moon below",
      "kind": "product",
      "credit": "NASA Johnson Space Center (public domain, via Wikimedia Commons)",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:Apollo_17_Command-Service_modules_photographed_from_lunar_module_in_orbit_(as17-145-22254).jpg"
    },
    {
      "file": "products/context/nasa-apollo-command-service-module-2.jpg",
      "alt": "Apollo 15 Command and Service Module in lunar orbit seen from the Lunar Module window with the Moon surface behind",
      "long": "Apollo 15 Command and Service Module in lunar orbit seen from the Lunar Module window with the Moon surface behind",
      "kind": "product",
      "credit": "NASA Johnson Space Center (public domain, via Wikimedia Commons)",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:View_of_the_Apollo_15_Command-Service_Module_in_lunar_orbit_(as15-88-11974).jpg"
    },
    {
      "file": "products/context/nasa-apollo-command-service-module-3.jpg",
      "alt": "Apollo 11 Command Module Columbia, scorched heat shield and windows, on display at the Smithsonian National Air and Space",
      "long": "Apollo 11 Command Module Columbia, scorched heat shield and windows, on display at the Smithsonian National Air and Space Museum",
      "kind": "product",
      "credit": "Smithsonian Institution/Eric Long (CC0, via Wikimedia Commons)",
      "license": "CC0",
      "page_url": "https://commons.wikimedia.org/wiki/File:Apollo_11_Command_Module_Columbia_(NASM2016-04274).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"
}