{
  "id": "nasa-lro",
  "title": "Lunar Reconnaissance Orbiter (LRO)",
  "maker": "NASA Goddard Space Flight Center",
  "maker_type": "Space agency",
  "kind": "satellite",
  "category": "platforms",
  "page": "https://spacemushroom.com/space-products/nasa-lro/",
  "website": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
  "summary": "NASA lunar mapping orbiter with an aluminum primary structure, hydrazine propulsion in titanium tanks and a heat-pipe thermal system.",
  "application": "NASA orbiter that has mapped the Moon from lunar orbit since 2009, imaging landing sites, measuring topography and finding polar ice candidates. It carries seven instruments and supported site selection for Artemis.",
  "story": {
    "headline": "LRO is a NASA orbiter that images the Moon's landing sites and measures its terrain.",
    "intro": [
      "The Lunar Reconnaissance Orbiter, or LRO, has mapped the Moon from orbit since 2009. NASA's Goddard Space Flight Center built it, and its seven instruments also look for places where ice may lie near the poles. The maps supported site selection for Artemis.",
      "The main structure is aluminium. The instruments are mounted in a module made of graphite composite, a material that barely expands or shrinks as the temperature changes. Heat pipes carry heat from the electronics to radiators, and a hydrazine propulsion system holds 894 kg of fuel in two titanium tanks."
    ],
    "built": [
      {
        "title": "Structure",
        "text": "The main structure is aluminium, built up from a heating and cooling panel, edge members, fittings and brackets. The instruments sit in a module known as the Wine Box, made from sheets of graphite and cyanate ester. Its optical bench is graphite composite, and flexible titanium mounts hold the instruments.",
        "parts": [
          "Primary structure (heating/cooling panel, edge members, fittings, brackets)",
          "Instrument module (‘Wine Box’ structure)",
          "Instrument optical bench",
          "Instrument mounting flexures"
        ]
      },
      {
        "title": "Fuel and thrusters",
        "text": "Two titanium tanks hold 894 kg of hydrazine. Four 80-newton insertion thrusters are for entering lunar orbit, and eight 20-newton thrusters control attitude and keep the orbit steady. A composite-wrapped helium tank supplies the pressure.",
        "parts": [
          "Propellant tanks (2)",
          "Propellant",
          "Insertion thrusters (x4, 80 N class)",
          "Attitude-control thrusters (x8, 20 N class)",
          "Helium pressurant tank (composite overwrapped)"
        ]
      },
      {
        "title": "Solar array and battery",
        "text": "The solar array is one wing of three graphite composite panels, 10.7 square metres in all, rated at 1,850 W at the end of its life. The wing turns about two axes. An 80 amp-hour lithium-ion battery is built from Sony cells, each a steel can holding rolled electrodes.",
        "parts": [
          "Solar array wing (three panels, 10.7 m2)",
          "Solar array gimbal actuators (2 axes)",
          "Battery cells",
          "Battery cell can"
        ]
      },
      {
        "title": "Keeping cool",
        "text": "Most of the electronics are coupled to an aluminium honeycomb panel with heat pipes built in. Header heat pipes link that panel to a radiator mounted separately on the spacecraft. The high-gain antenna has multilayer insulation and heaters, and two instruments have radiators of their own.",
        "parts": [
          "Iso-thermal panel with embedded heat pipes",
          "Zenith CCHP radiator and header heat pipes",
          "High Gain Antenna multi-layer insulation and heaters",
          "CRaTER and LEND individual radiators"
        ]
      }
    ],
    "materials": [
      {
        "name": "Aluminium",
        "mid": "aluminium",
        "where": "The main structure, and the 18-inch flywheels inside the four reaction wheels."
      },
      {
        "name": "Titanium",
        "mid": "titanium",
        "where": "The two propellant tanks and the flexures that mount the instruments."
      },
      {
        "name": "Hydrazine",
        "mid": "hydrazine",
        "where": "The propellant, 894 kg of it, carried in two tanks."
      },
      {
        "name": "Graphite composite",
        "mid": "graphite-composite",
        "where": "The instrument optical bench and the three panels of the solar array."
      },
      {
        "name": "Graphite and cyanate ester sheets",
        "mid": "graphite-m55-cyanate-ester",
        "where": "The instrument module, known as the Wine Box. It changes size very little with temperature."
      },
      {
        "name": "Lithium-ion cells",
        "mid": "lithium-ion-cell",
        "where": "The 80 amp-hour battery, built from Sony cells."
      }
    ],
    "connections": "An Atlas V 401 launched LRO on 18 June 2009, sharing the ride with a companion spacecraft, LCROSS. The Atlas has a single RD-180 engine in its first stage and a single RL10A-4-2 in its Centaur upper stage. Goddard built the orbiter in-house, using star trackers from SELEX Galileo, gyros from Honeywell, a computer from BAE Systems and cells from Sony. Its power electronics follow the design of an earlier spacecraft, the Microwave Anisotropy Probe.",
    "unknown": "The published figures for the orbiter's total mass do not agree. The makers do not say which aluminium alloy forms the main structure, who built the tanks and thrusters, or what solar cells the array uses. The antenna dish, the insulation films and the optics inside the seven instruments are also not described.",
    "facts": [
      {
        "label": "Launch",
        "value": "18 June 2009"
      },
      {
        "label": "Launch vehicle",
        "value": "Atlas V 401, with LCROSS as companion"
      },
      {
        "label": "Solar array",
        "value": "10.7 m2, 1850 W end-of-life"
      },
      {
        "label": "Battery",
        "value": "80 A-hr lithium-ion"
      },
      {
        "label": "Propellant load",
        "value": "894 kg hydrazine"
      },
      {
        "label": "Data volume",
        "value": "461 Gb per day"
      }
    ]
  },
  "specifications": [
    {
      "label": "Launch",
      "value": "18 June 2009",
      "source_url": "https://science.nasa.gov/mission/lro/",
      "quote": "Launch June 18, 2009"
    },
    {
      "label": "Launch vehicle",
      "value": "Atlas V 401, with LCROSS as companion",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "will be launched on an Atlas 5 401 Launch Vehicle"
    },
    {
      "label": "Mass",
      "value": "Less than 949 kg dry, 1846 kg fully fueled",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "The total mass of the observatory is less than 949 kg dry and 1846 kg"
    },
    {
      "label": "Solar array",
      "value": "10.7 m2, 1850 W end-of-life",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "A 10.7 square meter solar array provides 1850 W end-of-life"
    },
    {
      "label": "Battery",
      "value": "80 A-hr lithium-ion",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "An 80 A-hr Lithium-ion battery maintains"
    },
    {
      "label": "Propellant load",
      "value": "894 kg hydrazine",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "Fuel load is 894 kg of hydrazine"
    },
    {
      "label": "Reaction wheel momentum storage",
      "value": "130 Nms (assembly)",
      "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf",
      "quote": "reaction wheel assembly system momentum storage capacity of 130 Nms"
    },
    {
      "label": "Attitude control accuracy",
      "value": "60 arcsec control; 30 arcsec knowledge",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "Four reaction wheels provide attitude control to 60 arc sec"
    },
    {
      "label": "Recorder capacity",
      "value": "two 100 Gbyte recorders",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "Two 100 Gbyte recorders store science data for playback to the earth at 100 Mbps"
    },
    {
      "label": "Downlink",
      "value": "Ka-band 25 to 100 Mbps; S-band return 125 bps to 256 kbps; S-band forward 4 kbps",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "S-Band forward link data rate is fixed at 4 kbps."
    },
    {
      "label": "Data volume",
      "value": "461 Gb per day",
      "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf",
      "quote": "The data volume is 461 Gb per day and downlink is 100 Mb per second."
    },
    {
      "label": "Battery pack size",
      "value": "700 x 300 x 180 mm maximum",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "The battery dimensions are (L x H x W) 700mm x 300mm x 180mm (max value)."
    },
    {
      "label": "Delta-V capability",
      "value": "over 1300 m/s",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "The spacecraft carries enough fuel to provide over 1300 m/s of velocity change (delta V)"
    },
    {
      "label": "Thermal design stack",
      "value": "heat pipes carry heat to zenith-facing radiators",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "The thermal control system utilizes heat pipes to spread heat and move it to the zenith-facing radiators."
    },
    {
      "label": "Observatory mass",
      "value": "less than 949 kg dry and 1846 kg fully fueled",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "The total mass of the observatory is less than 949 kg dry and 1846 kg fully fueled."
    },
    {
      "label": "Atlas V 401 first-stage thrust",
      "value": "RD-180 delivers 860,200 lb at sea level",
      "source_url": "https://www.ulalaunch.com/docs/default-source/news-items/av_lrolcross_mob.pdf",
      "quote": "delivers 860,200 lb of thrust at sea level"
    },
    {
      "label": "Laser ranging",
      "value": "532 nm pulses from Greenbelt, Maryland",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "The LR site in Greenbelt, Maryland transmits 532 nm laser pulses to the LRO spacecraft."
    }
  ],
  "features": [
    {
      "text": "Monopropellant hydrazine system for lunar capture and station keeping",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "The propulsion system is a monopropellant hydrazine system."
    },
    {
      "text": "Heat pipes carry heat to zenith-facing radiators",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
      "quote": "The thermal control system utilizes heat pipes to spread heat and move"
    }
  ],
  "parts": [
    {
      "assembly": "Primary structure",
      "parts": [
        {
          "part": "Primary structure (heating/cooling panel, edge members, fittings, brackets)",
          "material": "aluminum (alloy not stated)",
          "form": "modular structure",
          "finish": null,
          "standard": null,
          "hardware_ref": "NASA Goddard",
          "quote": "1. Primary Structure (aluminum)",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": "aluminium",
          "mid": "aluminium"
        }
      ]
    },
    {
      "assembly": "Propulsion",
      "parts": [
        {
          "part": "Propellant tanks (2)",
          "material": "titanium",
          "form": "diaphragm tanks, 40 in OD oblate spheroid",
          "finish": null,
          "standard": null,
          "hardware_ref": "TDRSS-type tanks",
          "quote": "titanium diaphragm propellant tanks",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": "titanium",
          "mid": "titanium"
        },
        {
          "part": "Propellant",
          "material": "hydrazine",
          "form": "monopropellant, 894 kg",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Fuel load is 894 kg of hydrazine",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": "hydrazine"
        },
        {
          "part": "Insertion thrusters (x4, 80 N class)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "four of which are on-axis 80 Newton class insertion thrusters",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "on-axis hydrazine thrusters near the centre of gravity for lunar orbit insertion",
          "specs": [
            {
              "label": "Thruster type",
              "value": "dual-coil catalytic hydrazine thrusters, twelve in total",
              "quote": "The system includes twelve dual coil catalytic hydrazine thrusters",
              "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
            }
          ]
        },
        {
          "part": "Attitude-control thrusters (x8, 20 N class)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Eight canted 20 Newton class attitude control thrusters provide attitude control, lunar orbit maintenance maneuvers, and momentum dumping.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "canted thrusters for attitude control, orbit maintenance and momentum dumping"
        },
        {
          "part": "Helium pressurant tank (composite overwrapped)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Helium Pressure Regulated System is a 4200 psi COPV Helium pressurant tank",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "4200 psi tank, 17 in diameter by 29.6 in long, that pressurizes the propellant tanks"
        },
        {
          "part": "Two-stage pressure regulator",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A two stage regulator (single fault tolerant) is set at 270 psi nominal.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "single-fault-tolerant regulator set at 270 psi nominal"
        },
        {
          "part": "Pyro valves and high-pressure latch valve",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Redundant pyro valves provide for high pressure isolation during ground and launch operations",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "redundant pyro valves isolate high pressure on the ground and at launch; the latch valve isolates it in flight"
        },
        {
          "part": "Isolation valves and flow-control orifices",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Isolation valves with redundant coils are used to isolate thruster banks in the event of a thruster failure.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "valves with redundant coils isolate thruster banks; orifices prevent water-hammer surges"
        },
        {
          "part": "Propulsion Deployment Electronics (PDE)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "the PDE commands the firing of the thrusters when desired",
          "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf",
          "profile": null,
          "mid": null,
          "function": "fires the thrusters and the initiators; four identical boards give redundant drive",
          "specs": [
            {
              "label": "Design",
              "value": "four identical electronic boards",
              "quote": "with four identical electronic boards and one module",
              "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf"
            }
          ]
        },
        {
          "part": "NASA Standard Initiators (NSI)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "firing of the Propulsion NASA Standard Initiators (NSI) for opening of the propulsion pressurization tank",
          "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf",
          "profile": null,
          "mid": null,
          "function": "pyrotechnic initiators that open the propulsion pressurization tank"
        }
      ]
    },
    {
      "assembly": "Power",
      "parts": [
        {
          "part": "Battery cells",
          "material": "lithium-ion",
          "form": "80 A-hr battery",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "An 80 A-hr Lithium-ion battery maintains",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": "lithium-ion-cell"
        }
      ]
    },
    {
      "assembly": "Thermal control",
      "parts": [
        {
          "part": "Avionics radiator surface",
          "material": null,
          "form": "Optical Solar Reflector (OSR) covered heat pipe radiator",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Optical Solar Reflector (OSR) covered heat pipe radiator",
          "source_url": "https://ntrs.nasa.gov/api/citations/20090027710/downloads/20090027710.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Iso-thermal panel with embedded heat pipes",
          "material": "aluminum honeycomb with embedded heat pipes",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Most avionics are thermally coupled into an embedded constant conductance heat pipe (CCHP) aluminum honeycomb panel.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": "aluminium-honeycomb",
          "function": "aluminum honeycomb panel that couples most avionics to a radiator"
        },
        {
          "part": "Zenith CCHP radiator and header heat pipes",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Dual bore header heat pipes couple the isothermal panel to a CCHP radiator that is separately mounted on the zenith surface of the spacecraft.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "dual-bore header heat pipes carry heat to the zenith-mounted radiator"
        },
        {
          "part": "Heat-pipe working fluid",
          "material": "ammonia",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "stratified with ammonia liquid and vapor",
          "source_url": "https://ntrs.nasa.gov/api/citations/20090027710/downloads/20090027710.pdf",
          "profile": null,
          "mid": "ammonia",
          "function": "fluid inside the heat pipes"
        },
        {
          "part": "Battery heat-pipe network",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Lithium Ion battery is maintained on a separate CCHP network with two heat pipes mounted on its sidewalls",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "separate CCHP network with heat pipes on the battery sidewalls"
        },
        {
          "part": "Reaction-wheel baseplate heat pipes",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "two baseplate heat pipes are connected to two header pipes",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "two baseplate heat pipes connect to two header pipes"
        },
        {
          "part": "CRaTER and LEND individual radiators",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The CRaTER and LEND instruments are provided with individual radiators that are thermostatically controlled.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "thermostatically controlled radiators for two instruments"
        },
        {
          "part": "High Gain Antenna multi-layer insulation and heaters",
          "material": "multilayer insulation (film types not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The High Gain Antenna uses multi-layer insulation (MLI), thermal isolation, and heaters to maintain temperatures within allowable limits.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": "multilayer-insulation-mli",
          "mid": "multilayer-insulation-mli",
          "function": "blankets and heaters keep the antenna within limits"
        },
        {
          "part": "White-painted calorimeter (NS43C)",
          "material": "NS43C white paint",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "LRO is flying a NS43C (white) painted calorimeter and a MSA94B (black) painted calorimeter",
          "source_url": "https://ntrs.nasa.gov/api/citations/20090027710/downloads/20090027710.pdf",
          "profile": null,
          "mid": "ns43c-white-paint",
          "function": "measures orbital variations of lunar infrared flux"
        },
        {
          "part": "Black-painted calorimeter (MSA94B)",
          "material": "MSA94B black paint",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "LRO is flying a NS43C (white) painted calorimeter and a MSA94B (black) painted calorimeter",
          "source_url": "https://ntrs.nasa.gov/api/citations/20090027710/downloads/20090027710.pdf",
          "profile": null,
          "mid": "msa94b-black-paint",
          "function": "second calorimeter with a black coating"
        },
        {
          "part": "Constant-conductance heat pipes embedded in the avionics iso-thermal panel",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Most avionics are thermally coupled into an embedded constant conductance heat pipe (CCHP) aluminum honeycomb panel.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "heat pipes that couple most avionics to a radiator (the aluminum panel itself is in the entry bom)"
        }
      ]
    },
    {
      "assembly": "Structure and instrument module",
      "parts": [
        {
          "part": "Instrument module (‘Wine Box’ structure)",
          "material": "graphite M55 / cyanate ester quasi-isotropic sheets",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The entire structure has a low coefficient of thermal expansion (CTE) made of graphite material (M55/CyanateEster Q.I. sheets).",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": "graphite-m55-cyanate-ester",
          "function": "low-CTE graphite structure that carries the optical bench and star trackers; fewer fasteners and continuous bond lines",
          "specs": [
            {
              "label": "Design",
              "value": "'Wine Box' design that cuts mass and raises stiffness",
              "quote": "The Instrument module (IM) is of a 'Wine Box' design",
              "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
            }
          ]
        },
        {
          "part": "Instrument optical bench",
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          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The instrument module includes a graphite composite optical bench with honeycomb panels, inserts, and spools.",
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          "profile": null,
          "mid": "graphite-composite",
          "function": "graphite composite bench with honeycomb panels, inserts and spools for LAMP, LOLA and LROC",
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            {
              "label": "Fibre grade",
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              "source_url": "https://ntrs.nasa.gov/api/citations/20090027710/downloads/20090027710.pdf"
            }
          ]
        },
        {
          "part": "Instrument mounting flexures",
          "material": "titanium",
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          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Flexures for mounting the instruments are titanium.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": "titanium",
          "mid": "titanium",
          "function": "titanium flexures that mount the instruments on the bench"
        },
        {
          "part": "Bench inserts with BR127 primer",
          "material": "titanium inserts with BR127 conductive primer",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Insert material is Titanium with BR127 electrical conductive primer.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": "br127-primer",
          "function": "titanium inserts coated with an electrically conductive primer"
        },
        {
          "part": "Optical-bench heater aluminum tape",
          "material": "aluminum tape (3 mil, alloy not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "2 to 3 layers of 3 mil aluminum tape was required to keep the bench relatively isothermal",
          "source_url": "https://ntrs.nasa.gov/api/citations/20090027710/downloads/20090027710.pdf",
          "profile": "aluminium",
          "mid": "aluminium",
          "function": "2 to 3 layers of tape spread heat across the bench heaters (about 25 heater circuits)"
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      ]
    },
    {
      "assembly": "Electrical power",
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        {
          "part": "Solar array wing (three panels, 10.7 m2)",
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          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Three low-CTE graphite composite solar array panels are contained within one articulated wing.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": "graphite-composite",
          "function": "one articulated wing of three low-CTE graphite composite panels"
        },
        {
          "part": "Solar array gimbal actuators (2 axes)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Once fully deployed, the wing rotates about two axes, with power going through Gimbal Actuators at each axis.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "turn the wing 180 degrees in azimuth and 90 degrees in elevation to track the Sun"
        },
        {
          "part": "Solar array deployment hardware",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Separation nuts release rods that restrain the array in the stowed configuration.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "separation nuts, restraining rods, panel springs, viscous dampers and cam latches release and unfold the panels",
          "specs": [
            {
              "label": "Panel latching",
              "value": "cam latches control individual panel deployment",
              "quote": "Individual panel deployment is controlled by cam latches.",
              "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
            }
          ]
        },
        {
          "part": "Power Subsystem Electronics (PSE)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The basic design and operation of the LRO PSE architecture is modeled after the Microwave Anisotropy Probe (MAP)",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "conditions solar power, charges the battery and distributes power"
        },
        {
          "part": "Battery cell can",
          "material": "steel (grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The cell is a steel can (anode) containing a roll of interleaved electrodes soaked in electrolyte",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": "steel-grade-unstated",
          "function": "steel can that forms the anode of each lithium-ion cell",
          "specs": [
            {
              "label": "Cell model",
              "value": "SONY US18650HC, 18 mm by 65 mm, 40.3 g",
              "quote": "The SONY US18650HC Li-Ion Cell is 18 mm diameter by 65 mm high with a mass of 40.3 grams.",
              "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
            },
            {
              "label": "Pack layout",
              "value": "seven blocks of 8s12p, 8s84p in total",
              "quote": "The basic block size is 8s12p (i.e. 12 strings of 8 cells each) and seven blocks are used, to give a total of 8s84p.",
              "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
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          ]
        }
      ]
    },
    {
      "assembly": "Guidance, navigation and control",
      "parts": [
        {
          "part": "Reaction wheels (x4)",
          "material": "aluminum (flywheel; alloy not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: NASA Goddard GN&C Hardware Branch (in-house)",
          "quote": "Each RW uses an 18-inch aluminum flywheel, providing inertia for momentum exchange.",
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          "profile": "aluminium",
          "mid": "aluminium",
          "function": "fine pointing and momentum storage; the fourth wheel gives redundancy",
          "specs": [
            {
              "label": "Supplier",
              "value": "NASA Goddard GN&C Hardware Branch",
              "quote": "These actuators were developed, built, tested, and delivered in-house by the NASA Goddard GN&C Hardware Branch.",
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            },
            {
              "label": "Size and mass",
              "value": "13.2 kg each, 18 in diameter, 6 in high",
              "quote": "The mass of each wheel is 13.2 kg, 18 inches in diameter, and 6 inches in height.",
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            },
            {
              "label": "Momentum storage",
              "value": "130 Nms for the assembly",
              "quote": "reaction wheel assembly system momentum storage capacity of 130 Nms",
              "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf"
            }
          ]
        },
        {
          "part": "Star trackers (x2)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: SELEX Galileo",
          "quote": "Fine pointing attitude determination is accomplished by two SELEX Galileo Star Trackers.",
          "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf",
          "profile": null,
          "mid": null,
          "function": "fine attitude determination, 16 x 16 degree field of view"
        },
        {
          "part": "Inertial reference unit (Honeywell MIMU)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Honeywell",
          "quote": "Honeywell’s Miniature Inertial Measurement Unit (MIMU) serves as a single IRU.",
          "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf",
          "profile": null,
          "mid": null,
          "function": "three ring-laser gyros, one per axis, give spacecraft body rates",
          "specs": [
            {
              "label": "Gyros",
              "value": "3 ring-laser gyros, one per axis",
              "quote": "It contains 3 ring-laser gyros (one gyro per axis)",
              "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf"
            }
          ]
        },
        {
          "part": "Coarse sun sensors (x10)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: Adcole",
          "quote": "The most basic sensors used on LRO to determine spacecraft attitude are ten Adcole coarse sun sensors.",
          "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf",
          "profile": null,
          "mid": null,
          "function": "small sunlight-current sensors that give a Sun direction for the safe-hold mode"
        }
      ]
    },
    {
      "assembly": "Command and data handling",
      "parts": [
        {
          "part": "Flight computer (single board computer)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Supplier: BAE (British Aerospace Engineering) off-the-shelf board",
          "quote": "The flight computer is a RAD-750 processor executing at 133 MHz.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "RAD750-class processor at 133 MHz hosting the attitude control and flight software",
          "specs": [
            {
              "label": "Supplier",
              "value": "BAE (British Aerospace Engineering)",
              "quote": "The Single Board Computer (SBC) is a British Aerospace Engineering (BAE) off the shelf product",
              "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
            }
          ]
        },
        {
          "part": "Data Storage Boards (x4)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Four Data Storage Boards (DSBs) operate as a mass storage system for the spacecraft.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "mass storage of 384 Gbit at beginning of life, about 17.5 hours of science and housekeeping data"
        },
        {
          "part": "Housekeeping / Input-Output (HK/IO) card",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "provides an interface to the LAMP instrument as well as providing synchronization to all instruments",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "LAMP interface and timing synchronization for all instruments"
        },
        {
          "part": "Multi-function Analog Card (MAC)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Multi-function Analog Card (MAC) has been custom designed to manage the wide range of thermal environments in the lunar orbit.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "custom card that manages thermal environments in lunar orbit"
        },
        {
          "part": "Ultra-stable oscillators (primary and redundant)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The primary and redundant USOs are components of the C&DH subsystem, but are externally mounted separate assemblies.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "externally mounted timing references belonging to the C&DH subsystem"
        }
      ]
    },
    {
      "assembly": "Communications",
      "parts": [
        {
          "part": "Ka-band modulator",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Ka-band sub-system includes a Ka-Band modulator",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "modulates the 25 to 100 Mbps science downlink"
        },
        {
          "part": "Ka-band traveling-wave tube amplifier (TWTA)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a Traveling Wave Tube Amplifier (TWTA) consisting of a traveling wave tube (TWT), an Electronic Power Conditioner (EPC), and a High Power Isolator",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "TWT, electronic power conditioner and high-power isolator; at least 40 W output",
          "specs": [
            {
              "label": "Output power",
              "value": "minimum 40 W",
              "quote": "Output power is a minimum of 40 Watts.",
              "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
            }
          ]
        },
        {
          "part": "S-band transponder and RF switch",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The S-Band subsystem consists of one Spacecraft Tracking and Data Network (STDN) compatible transponder, an S-band RF Switch",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "STDN-compatible transponder for commands, telemetry and tracking"
        },
        {
          "part": "Omni-directional TT&C antennas",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "the RF paths to and from the TT&C omni-directional antennas and the S-band feed on the High Gain Antenna (HGA)",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "continuous receive capability on the S-band"
        },
        {
          "part": "Diplexers",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Diplexers allow the transponder's receiver and transmitter to connect to a common antenna port",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "let the transponder receiver and transmitter share one antenna port"
        },
        {
          "part": "High Gain Antenna System: Ka-band antenna with S-band patch",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "RF components include Ka-band antenna with an S-band patch antenna, an S-band coax cable and a Ka band waveguide",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "Ka-band dish with an S-band patch, coax cable, Ka waveguide and rotary joints"
        },
        {
          "part": "High Gain Antenna two-axis gimbal",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The articulation system is a two axis gimbal system capable of slightly greater than 180 degrees of rotation about each axis",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "two-axis gimbal with slightly more than 180 degrees of rotation per axis and two rotating cable wraps"
        },
        {
          "part": "High Gain Antenna deployment and non-explosive actuators",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The High Gain Antenna System (HGAS) includes a deployment system with two latches requiring mechanical release, and three restraint areas.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "two latches, three restraint areas and a non-explosive actuator that releases a spring-wound split spool",
          "specs": [
            {
              "label": "Actuator principle",
              "value": "tensile load against a spring-wound split spool",
              "quote": "The principle of operation of the NEA involves a tensile load reacting against a spring-wound split spool.",
              "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
            }
          ]
        },
        {
          "part": "Laser ranging telescope on the high-gain antenna",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A small laser ranging telescope is mounted on the wave guide with fiber optic cable providing the connectivity to the LOLA instrument.",
          "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat",
          "profile": null,
          "mid": null,
          "function": "receives 532 nm laser pulses from Earth; fiber optic cable feeds the LOLA instrument"
        }
      ]
    },
    {
      "assembly": "Science instruments",
      "parts": [
        {
          "part": "Cosmic Ray Telescope for the Effects of Radiation (CRaTER)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "CRaTER characterizes the lunar radiation environment and determine its potential biological impacts.",
          "source_url": "https://science.nasa.gov/mission/lro/spacecraft-and-instruments/",
          "profile": null,
          "mid": null,
          "function": "measures the lunar radiation environment and its biological impact",
          "specs": [
            {
              "label": "Principal investigator (press-kit table order)",
              "value": "Harlan Spence, Boston University",
              "quote": "The Principal Investigator is Dr. Harlan Spence, Boston University, Boston.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            },
            {
              "label": "Mass and average power",
              "value": "5.4 kg, 7.3 W",
              "quote": "The instrument mass is 5.4 kilograms (12 pounds) and the average power is 7.3 watts.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            }
          ]
        },
        {
          "part": "Diviner Lunar Radiometer (DLRE)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Diviner provides orbital thermal mapping measurements, giving detailed information about surface and subsurface temperatures",
          "source_url": "https://science.nasa.gov/mission/lro/spacecraft-and-instruments/",
          "profile": null,
          "mid": null,
          "function": "orbital thermal mapping of surface and subsurface temperatures",
          "specs": [
            {
              "label": "Principal investigator (press-kit table order)",
              "value": "David Paige, UCLA",
              "quote": "The Principal Investigator is Dr. David Paige, University of California, Los Angeles, Calif.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            },
            {
              "label": "Mass and average power",
              "value": "11.0 kg, 24.7 W",
              "quote": "The instrument mass is 11.0 kilograms (24 pounds) with average power of 24.7 watts.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            }
          ]
        },
        {
          "part": "Lyman Alpha Mapping Project (LAMP)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "LAMP maps the entire lunar surface in the far ultraviolet spectrum.",
          "source_url": "https://science.nasa.gov/mission/lro/spacecraft-and-instruments/",
          "profile": null,
          "mid": null,
          "function": "far-ultraviolet mapping of the surface, searching for ice and frost; mounted on the optical bench",
          "specs": [
            {
              "label": "Principal investigator (press-kit table order)",
              "value": "Randy Gladstone, Southwest Research Institute",
              "quote": "The Principal Investigator is Dr. Randy Gladstone, Southwest Research Institute, San Antonio, Texas.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            },
            {
              "label": "Mass and average power",
              "value": "6.1 kg, 4.0 W",
              "quote": "The instrument mass is 6.1 kilograms (13 pounds) and the average power is 4.0 watts.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            }
          ]
        },
        {
          "part": "Lunar Exploration Neutron Detector (LEND)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "LEND creates high-resolution hydrogen distribution maps and provides information about the lunar radiation environment.",
          "source_url": "https://science.nasa.gov/mission/lro/spacecraft-and-instruments/",
          "profile": null,
          "mid": null,
          "function": "maps neutron flux to find hydrogen and possible water ice",
          "specs": [
            {
              "label": "Principal investigator (press-kit table order)",
              "value": "Igor Mitrofanov, Space Research Institute, Moscow",
              "quote": "The Principal Investigator is Dr. Igor Mitrofanov, Institute for Space Research, Moscow, Russia.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            },
            {
              "label": "Mass and average power",
              "value": "25.8 kg, 11.6 W",
              "quote": "The instrument mass is 25.8 kilograms (57 pounds) and the average power is 11.6 watts.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            }
          ]
        },
        {
          "part": "Lunar Orbiter Laser Altimeter (LOLA)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "LOLA measures landing site slopes and lunar surface roughness, and generates a high-resolution 3D maps of the Moon.",
          "source_url": "https://science.nasa.gov/mission/lro/spacecraft-and-instruments/",
          "profile": null,
          "mid": null,
          "function": "laser altimeter that builds the global topography and measures slopes and roughness; on the optical bench",
          "specs": [
            {
              "label": "Principal investigator (press-kit table order)",
              "value": "David Smith, NASA Goddard",
              "quote": "The Principal Investigator is Dr. David Smith, NASA Goddard Space Flight Center, Greenbelt, Md.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            },
            {
              "label": "Mass and average power",
              "value": "11.3 kg, 33.4 W",
              "quote": "The instrument mass is 11.3 kilograms (25 pounds) and the average power is 33.4 watts.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            }
          ]
        },
        {
          "part": "Lunar Reconnaissance Orbiter Camera (LROC)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "LROC retrieves high resolution black-and-white images of the lunar surface.",
          "source_url": "https://science.nasa.gov/mission/lro/spacecraft-and-instruments/",
          "profile": null,
          "mid": null,
          "function": "black-and-white narrow-angle imaging plus wide-angle imaging; on the optical bench",
          "specs": [
            {
              "label": "Principal investigator (press-kit table order)",
              "value": "Mark Robinson, Arizona State University",
              "quote": "The Principal Investigator is Dr. Mark Robinson, Arizona State University, Tempe, Ariz.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            },
            {
              "label": "Mass and average power",
              "value": "19.2 kg, 24.0 W",
              "quote": "The instrument mass is 19.2 kilograms (42 pounds) and the average power is 24.0 watts.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            }
          ]
        },
        {
          "part": "Mini-RF Technology Demonstration",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The primary goal of Mini-RF is to search for subsurface water ice deposits.",
          "source_url": "https://science.nasa.gov/mission/lro/spacecraft-and-instruments/",
          "profile": null,
          "mid": null,
          "function": "radar that searches for subsurface water ice and images permanently shadowed regions",
          "specs": [
            {
              "label": "Principal investigator (press-kit table order)",
              "value": "Stewart Nozette, Lunar and Planetary Institute",
              "quote": "The Principal Investigator is Dr. Stewart Nozette, Lunar and Planetary Institute, Houston.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            },
            {
              "label": "Mass and average power",
              "value": "13.8 kg, 7.0 W",
              "quote": "The instrument mass is 13.8 kilograms (30 pounds) and the average power is 7.0 watts.",
              "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
            }
          ]
        }
      ]
    }
  ],
  "materials": [
    {
      "id": "aluminium",
      "name": "aluminum (flywheel; alloy not stated)",
      "material_page": "https://spacemushroom.com/profiles/aluminium/"
    },
    {
      "id": "titanium",
      "name": "titanium",
      "material_page": "https://spacemushroom.com/profiles/titanium/"
    },
    {
      "id": "hydrazine",
      "name": "hydrazine",
      "material_page": null
    },
    {
      "id": "lithium-ion-cell",
      "name": "lithium-ion",
      "material_page": null
    },
    {
      "id": "graphite-m55-cyanate-ester",
      "name": "graphite M55 / cyanate ester quasi-isotropic sheets",
      "material_page": null
    },
    {
      "id": "graphite-composite",
      "name": "graphite composite (low CTE)",
      "material_page": null
    },
    {
      "id": "br127-primer",
      "name": "titanium inserts with BR127 conductive primer",
      "material_page": null
    },
    {
      "id": "steel-grade-unstated",
      "name": "steel (grade not stated)",
      "material_page": null
    },
    {
      "id": "aluminium-honeycomb",
      "name": "aluminum honeycomb with embedded heat pipes",
      "material_page": null
    },
    {
      "id": "ammonia",
      "name": "ammonia",
      "material_page": null
    },
    {
      "id": "multilayer-insulation-mli",
      "name": "multilayer insulation (film types not stated)",
      "material_page": "https://spacemushroom.com/profiles/multilayer-insulation-mli/"
    },
    {
      "id": "ns43c-white-paint",
      "name": "NS43C white paint",
      "material_page": null
    },
    {
      "id": "msa94b-black-paint",
      "name": "MSA94B black paint",
      "material_page": null
    }
  ],
  "standards": [],
  "relations": [
    {
      "type": "launched_on",
      "target": "Atlas V 401",
      "target_slug": "ula-atlas-v",
      "note": "launched 18 June 2009 with LCROSS as companion; one booster and a Centaur, no solid boosters",
      "quote": "LRO will be launched on an Atlas 5 401 Launch Vehicle along with its companion spacecraft, the Lunar CRater Observation and Sensing Satellite (LCROSS)",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
    },
    {
      "type": "launched_on",
      "target": "RD-180 engine (Atlas V 401 booster)",
      "target_slug": "npo-energomash-rd-180",
      "note": "single RD-180 with two thrust chambers burning RP-1 and liquid oxygen",
      "quote": "Atlas booster propulsion is provided by the RD-180 engine system (a single engine with two thrust chambers).",
      "source_url": "https://www.ulalaunch.com/docs/default-source/news-items/av_lrolcross_mob.pdf"
    },
    {
      "type": "launched_on",
      "target": "RL10A-4-2 engine (Centaur upper stage)",
      "target_slug": "ula-rl10",
      "note": "single RL10A-4-2 on Centaur, 22,300 lb thrust; RL10 hub is ula-rl10",
      "quote": "It uses a single RL10A-4-2 engine that produces 22,300 lb of thrust.",
      "source_url": "https://www.ulalaunch.com/docs/default-source/news-items/av_lrolcross_mob.pdf"
    },
    {
      "type": "launched_on",
      "target": "LCROSS (companion spacecraft on the same Atlas V)",
      "target_slug": null,
      "note": "shared the launch; Centaur later impacted the Moon as part of LCROSS",
      "quote": "along with its companion spacecraft, the Lunar CRater Observation and Sensing Satellite (LCROSS)",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
    },
    {
      "type": "operated_by",
      "target": "NASA Goddard Space Flight Center",
      "target_slug": null,
      "note": "built the spacecraft in-house and runs the Mission Operations Center",
      "quote": "The spacecraft was built by engineers at NASA Goddard Space Flight Center in Greenbelt, Md.",
      "source_url": "https://webarchive.library.unt.edu/web/20090922191046id_/http://lro.gsfc.nasa.gov/images/LRO_LCROSS_presskit.pdf"
    },
    {
      "type": "supplied_by",
      "target": "SELEX Galileo",
      "target_slug": null,
      "note": "two star trackers",
      "quote": "Fine pointing attitude determination is accomplished by two SELEX Galileo Star Trackers.",
      "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Honeywell",
      "target_slug": null,
      "note": "Miniature Inertial Measurement Unit (3 ring-laser gyros)",
      "quote": "Honeywell’s Miniature Inertial Measurement Unit (MIMU) serves as a single IRU.",
      "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Adcole",
      "target_slug": null,
      "note": "ten coarse sun sensors",
      "quote": "The most basic sensors used on LRO to determine spacecraft attitude are ten Adcole coarse sun sensors.",
      "source_url": "https://ntrs.nasa.gov/api/citations/20100014880/downloads/20100014880.pdf"
    },
    {
      "type": "supplied_by",
      "target": "BAE Systems",
      "target_slug": null,
      "note": "single board computer (off-the-shelf)",
      "quote": "The Single Board Computer (SBC) is a British Aerospace Engineering (BAE) off the shelf product",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
    },
    {
      "type": "supplied_by",
      "target": "Sony",
      "target_slug": null,
      "note": "US18650HC lithium-ion cells for the battery",
      "quote": "The SONY US18650HC Li-Ion Cell is 18 mm diameter by 65 mm high with a mass of 40.3 grams.",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
    },
    {
      "type": "heritage_of",
      "target": "Microwave Anisotropy Probe (MAP)",
      "target_slug": null,
      "note": "LRO's power electronics architecture is modeled after MAP",
      "quote": "The basic design and operation of the LRO PSE architecture is modeled after the Microwave Anisotropy Probe (MAP)",
      "source_url": "https://naif.jpl.nasa.gov/pub/naif/pds/data/lro-l-spice-6-v1.0/lrosp_1000/catalog/insthost.cat"
    }
  ],
  "not_published": "Aluminum alloy, solar cell type, heat pipe working fluid, OSR and blanket materials, antenna and instrument optics materials are not stated on the NASA pages read. Structure composites, if any, were not confirmed. Mass figures differ between NAIF (1846 kg fueled) and a NASA paper (about 1850 kg). More detail: Not published on the pages read: who built the propellant tanks, helium tank and the 80 N and 20 N thrusters (the paper says a Goddard in-house propulsion system); the solar cell type and maker; the high-gain antenna dish material; the builders of the seven instruments (only principal investigators are named; the press kit lists PIs in the same order as the instrument list, which is how they are matched here); instrument optics and detector materials; the TWT and transponder makers; MLI film types. Mass in the NASA page (about 1000 kg) differs from the PDS catalog (1846 kg fuelled). The 4-by-20-lb and 8-by-5-lb thruster sizes in the thermal paper are the same thrusters as the 80 N and 20 N classes in the PDS text. Atlas V engines are linked as launch-vehicle engines, not spacecraft engines. More detail: Not published on the pages read: who built the propellant tanks, helium tank and the 80 N and 20 N thrusters (the paper says a Goddard in-house propulsion system); the solar cell type and maker; the high-gain antenna dish material; the builders of the seven instruments (only principal investigators are named; the press kit lists PIs in the same order as the instrument list, which is how they are matched here); instrument optics and detector materials; the TWT and transponder makers; MLI film types. Mass in the NASA page (about 1000 kg) differs from the PDS catalog (1846 kg fuelled). The 4-by-20-lb and 8-by-5-lb thruster sizes in the thermal paper are the same thrusters as the 80 N and 20 N classes in the PDS text. Atlas V engines are linked as launch-vehicle engines, not spacecraft engines.",
  "depth": "partial",
  "photos": [
    {
      "file": "products/context/nasa-lro-1.jpg",
      "alt": "Close-up of LRO hardware wrapped in silver multilayer insulation at Goddard Space Flight Center, 2008 (NARA archive photo by",
      "long": "Close-up of LRO hardware wrapped in silver multilayer insulation at Goddard Space Flight Center, 2008 (NARA archive photo by Pat Izzo).",
      "kind": "product",
      "credit": "NASA Goddard Space Flight Center / photographer Pat Izzo (National Archives and Records Administration, via Wikimedia Commons)",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:NASA%27s_Lunar_Reconnaissance_Orbiter_(LRO)_spacecraft_-_DPLA_-_6048b7dbbfd309d33d9ff4594aeb904e.jpg"
    },
    {
      "file": "products/context/nasa-lro-2.jpg",
      "alt": "Close-up of exposed LRO instrument/structure panel with wiring harnesses and a technician behind, Goddard, 2008 (NARA, Pat",
      "long": "Close-up of exposed LRO instrument/structure panel with wiring harnesses and a technician behind, Goddard, 2008 (NARA, Pat Izzo).",
      "kind": "product",
      "credit": "NASA Goddard Space Flight Center / photographer Pat Izzo (National Archives and Records Administration, via Wikimedia Commons)",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:NASA%27s_Lunar_Reconnaissance_Orbiter_(LRO)_spacecraft_-_DPLA_-_1ce3a9213e934020aa6988e93b8848db.jpg"
    },
    {
      "file": "products/context/nasa-lro-3.jpg",
      "alt": "Close-up of exposed LRO hardware panel with wiring and taped fittings, Goddard, 2008 (NARA, Pat Izzo)",
      "long": "Close-up of exposed LRO hardware panel with wiring and taped fittings, Goddard, 2008 (NARA, Pat Izzo).",
      "kind": "product",
      "credit": "NASA Goddard Space Flight Center / photographer Pat Izzo (National Archives and Records Administration, via Wikimedia Commons)",
      "license": "Public domain",
      "page_url": "https://commons.wikimedia.org/wiki/File:NASA%27s_Lunar_Reconnaissance_Orbiter_(LRO)_spacecraft_-_DPLA_-_c2de7992dda73914aa7834008e82d21b.jpg"
    }
  ],
  "context": {
    "size": [
      "6U and larger"
    ],
    "mass": [
      "Over 100 kg"
    ],
    "orbit": [
      "Deep space"
    ]
  },
  "licence": "Product data CC BY 4.0, cite Space Mushroom. Photos keep their own licences, given per photo.",
  "mcp": "https://spacemushroom.com/mcp"
}