{
  "id": "npo-energomash-rd-180",
  "title": "RD-180 engine",
  "maker": "NPO Energomash (sold in the US through RD AMROSS)",
  "maker_type": "Commercial",
  "kind": "mission",
  "category": "engines",
  "page": "https://spacemushroom.com/space-products/npo-energomash-rd-180/",
  "website": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
  "summary": "Two-chamber, oxygen-rich staged-combustion LOX/kerosene engine built by NPO Energomash for the Atlas III and Atlas V first stage; published sources name hot-oxygen coatings, nickel alloys, silver elements and a new high-temperature stainless steel, but no grades.",
  "application": "The RD-180 lifts the first stage of United Launch Alliance's Atlas V rocket and powered the Atlas III before it. It burns kerosene and liquid oxygen in a closed cycle where all the oxygen passes through a preburner and turbine, so its gas path must resist burning in hot oxygen. That makes it a reference case for hot-oxygen coatings and alloys.",
  "story": null,
  "specifications": [
    {
      "label": "Propellants",
      "value": "Liquid oxygen and kerosene",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "The RD-180 is a staged combustion cycle engine that burns liquid oxygen and kerosene propellants."
    },
    {
      "label": "Cycle",
      "value": "Oxygen-rich staged combustion, closed cycle",
      "source_url": "https://www.ulalaunch.com/docs/default-source/evolution/rd-180-engine-an-established-record-of-performance-and-reliability-on-atlas-launch-vehicles.pdf",
      "quote": "The RD-180 is a LOx rich, closed cycle, staged combustion, LOx Kerosene engine, with throttle capability from 47% to 100% power level."
    },
    {
      "label": "Sea-level thrust",
      "value": "860,200 lbf",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "(sea level) 860,200 lb"
    },
    {
      "label": "Vacuum thrust",
      "value": "933,400 lbf",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "(vacuum) 933,400 lb"
    },
    {
      "label": "Specific impulse (sea level / vacuum)",
      "value": "311.3 s / 337.8 s",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "311.3 sec / 337.8 sec"
    },
    {
      "label": "Chamber pressure",
      "value": "3,722 psia",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "Chamber pressure 3,722 psia"
    },
    {
      "label": "Mixture ratio (oxidizer to fuel)",
      "value": "2.72",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "Mixture ratio 2.72"
    },
    {
      "label": "Throttle range",
      "value": "47 to 100 percent of power",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "Smooth and continuous throttling from 47% power to 100% power"
    },
    {
      "label": "Nozzle area ratio",
      "value": "36.87:1",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "Nozzle area ratio 36.87:1"
    },
    {
      "label": "Dry mass (Pratt & Whitney fact sheet)",
      "value": "11,889 lb",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "Total system dry weight 11,889 lb"
    },
    {
      "label": "Dry mass (AIAA 2004 paper)",
      "value": "5,520 kg",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "5,520 kg"
    },
    {
      "label": "Length",
      "value": "140 in.",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "Length 140 in."
    },
    {
      "label": "Diameter",
      "value": "118 in.",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "Diameter 118 in."
    },
    {
      "label": "Chamber gimbal range",
      "value": "Plus or minus 8 degrees",
      "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
      "quote": "The two thrust chambers can gimbal +-8 degrees."
    },
    {
      "label": "Engines per vehicle",
      "value": "One per Atlas III first stage (six MA-5 engines on Atlas IIAS before it)",
      "source_url": "https://www.ulalaunch.com/docs/default-source/evolution/rd-180-engine-an-established-record-of-performance-and-reliability-on-atlas-launch-vehicles.pdf",
      "quote": "When the number of propulsion systems was reduced from six to one during the evolution from Atlas II to Atlas III"
    },
    {
      "label": "First flight",
      "value": "24 May 2000, Atlas IIIA",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "the first successful RD-180 powered Atlas launch took place on 24 May 2000, with the launch of an Atlas IIIA"
    },
    {
      "label": "First Atlas V launch",
      "value": "21 August 2002",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "Atlas V which had its successful maiden launch on 21 August 2002"
    },
    {
      "label": "Hardware shared with RD-170",
      "value": "70 percent common, 30 percent scaled",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "It has 70% common hardware with the RD-170, and 30% is scaled from the RD-170."
    },
    {
      "label": "Engines flown (early 2011)",
      "value": "29",
      "source_url": "https://www.ulalaunch.com/docs/default-source/evolution/rd-180-engine-an-established-record-of-performance-and-reliability-on-atlas-launch-vehicles.pdf",
      "quote": "twenty-nine engines have flown and have exhibited consistent performance"
    }
  ],
  "features": [
    {
      "text": "All the oxygen passes through the preburner that drives the turbine (oxygen-rich staged combustion)",
      "source_url": "https://www.ulalaunch.com/docs/default-source/evolution/rd-180-engine-an-established-record-of-performance-and-reliability-on-atlas-launch-vehicles.pdf",
      "quote": "For the RD-180, all of the oxygen flows through the preburner which drives the turbine."
    },
    {
      "text": "Two chambers and one preburner taken from the RD-170 design",
      "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
      "quote": "The RD-180 engine has two chambers and one preburner taken from the RD-170 design."
    },
    {
      "text": "One main turbopump unit made of two coaxial shafts joined by a torsional spring",
      "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
      "quote": "two coaxial shafts connected with an elastic torsional spring"
    },
    {
      "text": "Deep throttling from 47 to 100 percent power",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "Smooth and continuous throttling from 47% power to 100% power"
    },
    {
      "text": "Chambers cooled by film cooling and milled channels, with a protective hot-wall film coating",
      "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
      "quote": "internal film cooling (annular slot curtains) and external (milled cooling channels) in combination with a protective hot-wall film coating"
    },
    {
      "text": "Self-contained pneumatics, hydraulics and thrust vector control actuators",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "Self-contained engine pneumatic system, 4 fewer fluid interfaces than with previous engine"
    },
    {
      "text": "Engine-mounted fuel pre-valve added for the Atlas start interface",
      "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
      "quote": "A newly designed engine-mounted fuel pre-valve was also provided to accommodate the necessary interface with the Atlas launch vehicles"
    },
    {
      "text": "Every production engine is hot-fire tested in Russia before delivery",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "Each production RD-180 is hot fire tested for over 200 seconds prior to delivery to the customer."
    },
    {
      "text": "Built by NPO Energomash in Russia and sold to the US through RD AMROSS",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
      "quote": "provided to Lockheed Martin by RD AMROSS, a 50/50 Pratt & Whitney / NPO Energomash Joint Venture company"
    }
  ],
  "parts": [
    {
      "assembly": "Main turbopump unit (MTU)",
      "parts": [
        {
          "part": "Main turbopump unit (single shaft: turbine, LOX pump, fuel pump)",
          "material": null,
          "form": "single-shaft unit; two coaxial shafts joined by an elastic torsional spring",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The MTU assembly contains the single shafted turbine, LOX pump and fuel pump as well as the preburner and main LOX valve.",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Turbine (single stage, driven by oxygen-rich gas)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "the main LOX and main kerosene pumps on a single shaft, driven by a single stage turbine",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Turbine blades and vanes",
          "material": null,
          "form": "coated blades and vanes",
          "finish": "coated (composition not stated in this source)",
          "standard": null,
          "hardware_ref": null,
          "quote": "for retention of coating upon exposure to hot gas",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Turbine gas-path parts",
          "material": "nickel alloys, including heat-resistant grades (grades not stated)",
          "form": "gas-path parts; heat-resistant grades named for hot gas lines",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Чтобы исключить возгорание и разрушение деталей газового тракта турбины, в конструкции применены никелевые сплавы",
          "source_url": "https://www.lpre.de/energomash/RD-180/index.htm",
          "profile": null,
          "mid": "nickel-based-alloy"
        },
        {
          "part": "Oxidizer pump fixed slot seals",
          "material": "silver overlay",
          "form": "fixed slot seals with silver overlay",
          "finish": null,
          "standard": null,
          "hardware_ref": "Used instead of floating rings, per the Russian description",
          "quote": "применены неподвижные щелевые уплотнения с серебряной накладкой",
          "source_url": "https://www.lpre.de/energomash/RD-180/index.htm",
          "profile": "silver",
          "mid": "silver"
        },
        {
          "part": "Anti-ignition elements at rubbing contacts in the turbopump",
          "material": "silver or bronze (source gives either)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "серебряные или бронзовые элементы, исключающие возгорание даже при возможном касании",
          "source_url": "https://www.lpre.de/energomash/RD-180/index.htm",
          "profile": null,
          "mid": "silver-or-bronze"
        },
        {
          "part": "Rotor and stator blade coating (nickel)",
          "material": "nickel coating",
          "form": "thermal protection coating on rotor and stator blades",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "используются разного рода теплозащитные покрытия (никелевые для лопаток ротора и статора, металлокерамического для ротора)",
          "source_url": "https://www.lpre.de/energomash/RD-180/index.htm",
          "profile": null,
          "mid": "nickel-coating"
        },
        {
          "part": "Rotor coating (metal-ceramic)",
          "material": "metal-ceramic coating (composition not stated here)",
          "form": "coating on the rotor",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "используются разного рода теплозащитные покрытия (никелевые для лопаток ротора и статора, металлокерамического для ротора)",
          "source_url": "https://www.lpre.de/energomash/RD-180/index.htm",
          "profile": null,
          "mid": "metal-ceramic-coating"
        },
        {
          "part": "Ignition-resistant coating on the oxidizer turbopump turbine",
          "material": "nickel, cerium borate and barium alumino-borate glass composite",
          "form": "coating that prevents ignition from particle impact",
          "finish": null,
          "standard": null,
          "hardware_ref": "MIT thesis abstract: coating formulation first developed for Russian RD-180 engines; composition from the author's experiments",
          "quote": "a three-phase metal-ceramic composite composed of nickel, cerium borate, and barium alumino-borate glass",
          "source_url": "https://dspace.mit.edu/handle/1721.1/154026",
          "profile": null,
          "mid": "nickel-cerium-borate-glass-composite-coating"
        },
        {
          "part": "Low-pressure boost pumps (LOX and kerosene)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "included new scaled boost pumps and thrust frame and the new valves mentioned previously",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        }
      ]
    },
    {
      "assembly": "Preburner and hot-gas path",
      "parts": [
        {
          "part": "Oxygen-rich preburner",
          "material": null,
          "form": "modular injector head with raised injectors",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "staged combustion oxidizer rich preburner",
          "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
          "profile": null,
          "mid": null
        },
        {
          "part": "Preburner and main chamber injector heads",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "modular construction of the preburner and main chamber injector heads with raised injectors",
          "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Hot gas ducts and ducting coating",
          "material": "inert enamel coating on turbine alloys and hot-gas ducting",
          "form": "coating",
          "finish": null,
          "standard": null,
          "hardware_ref": "National Research Council text covers Russian oxygen-rich staged-combustion engine designs in general (the RD-180 is the Russian engine of that type it names as sold in the US)",
          "quote": "Russian engine designs have overcome this material incompatibility challenge by using inert enamel coatings on traditional high-strength turbine alloys and hot-gas ducting",
          "source_url": "https://www.nationalacademies.org/read/13534/chapter/5",
          "profile": null,
          "mid": "inert-enamel-coating"
        },
        {
          "part": "Hot-gas internals exposed to the oxygen-rich environment",
          "material": "high-temperature resistant stainless steel (new class, grade not stated)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "ULA paper does not name the parts; it refers to protecting internal components from fire risk",
          "quote": "a new class of high temperature resistant stainless steel invented to cope with the risks of the LOx rich environment",
          "source_url": "https://www.ulalaunch.com/docs/default-source/evolution/rd-180-engine-an-established-record-of-performance-and-reliability-on-atlas-launch-vehicles.pdf",
          "profile": null,
          "mid": "high-temperature-stainless-steel-lox-rich"
        },
        {
          "part": "Hot gas bellows assemblies",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "the two hot gas bellows assemblies bolt to the hot gas duct outlets",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Hot-gas bellows inside the gimbal joint",
          "material": null,
          "form": "12-layer composite bellows",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "через 12-слойный составной сильфон, размещенный внутри карданного подвеса",
          "source_url": "https://www.lpre.de/energomash/RD-180/index.htm",
          "profile": null,
          "mid": null
        },
        {
          "part": "Start fuel (triethylaluminum) in the start ampoule",
          "material": null,
          "form": "ampoule of triethylaluminum start fuel",
          "finish": null,
          "standard": null,
          "hardware_ref": "Labelled Hypergolic Start Ampoule in the engine schematic of AIAA 2004-3998",
          "quote": "пусковым горючим триэтилалюминием",
          "source_url": "https://www.lpre.de/energomash/RD-180/index.htm",
          "profile": null,
          "mid": null
        }
      ]
    },
    {
      "assembly": "Thrust chambers and nozzles (two)",
      "parts": [
        {
          "part": "Combustion chambers (two)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "Chamber assemblies are designed by Energomash and made off-site (AIAA paper); ULA names Metalist in Samara as chamber manufacturer",
          "quote": "The two chambers are bolted to the bellows assemblies and the gimbal actuators are attached.",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Chamber assembly construction",
          "material": null,
          "form": "brazed and welded, non-separable assembly of mixing head, combustion chamber and nozzle",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Камера представляет собой паяно-сварной неразъемный узел и состоит из смесительной головки, камеры сгорания и сопла.",
          "source_url": "https://www.lpre.de/energomash/RD-180/index.htm",
          "profile": null,
          "mid": null
        },
        {
          "part": "Chamber cooling channels and film cooling",
          "material": null,
          "form": "milled external cooling channels plus internal film cooling slots",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "internal film cooling (annular slot curtains) and external (milled cooling channels) in combination with a protective hot-wall film coating",
          "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Nozzles (two)",
          "material": null,
          "form": "area ratio 36.87:1",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Nozzle area ratio 36.87:1",
          "source_url": "https://spaceflightnow.com/atlas/ac204/020219rd180.html",
          "profile": null,
          "mid": null
        }
      ]
    },
    {
      "assembly": "Gimbal and thrust vector control",
      "parts": [
        {
          "part": "Gimbal units (one per chamber)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Each Chamber assembly is gimballed in two planes for thrust vector control.",
          "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Gimbal actuators (four)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": "ULA paper names Arsenal in St. Petersburg as the thrust vector control actuator supplier",
          "quote": "all four gimbal actuators are activated",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Engine frame (thrust frame)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The frame is installed to the hot gas ducts",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        }
      ]
    },
    {
      "assembly": "Valves, control and ancillary systems",
      "parts": [
        {
          "part": "Thrust control valve and mixture ratio control valve (electro-hydraulic)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "electro-hydraulically actuated (EHA) thrust control valve and mixture ratio control valve",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Engine-mounted fuel pre-valve",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A newly designed engine-mounted fuel pre-valve was also provided",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Pneumatic system and helium bottles",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The pneumatic system and helium bottles are installed.",
          "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Heat exchanger (helium heating for LOX tank pressurisation)",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "heat exchanger for helium heating to pressurize the boost stage oxygen tank",
          "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Integral hydraulic system",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "integral hydraulic system for TVC and EHA control valves",
          "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Vacuum ejector for kerosene lines",
          "material": null,
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "vacuum ejector for evacuation of kerosene lines before fuel fill and launch",
          "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf",
          "profile": null,
          "mid": null
        }
      ]
    }
  ],
  "materials": [
    {
      "id": "nickel-based-alloy",
      "name": "nickel alloys, including heat-resistant grades (grades not stated)",
      "material_page": null
    },
    {
      "id": "silver",
      "name": "silver overlay",
      "material_page": "https://spacemushroom.com/profiles/silver/"
    },
    {
      "id": "silver-or-bronze",
      "name": "silver or bronze (source gives either)",
      "material_page": null
    },
    {
      "id": "nickel-coating",
      "name": "nickel coating",
      "material_page": null
    },
    {
      "id": "metal-ceramic-coating",
      "name": "metal-ceramic coating (composition not stated here)",
      "material_page": null
    },
    {
      "id": "nickel-cerium-borate-glass-composite-coating",
      "name": "nickel, cerium borate and barium alumino-borate glass composite",
      "material_page": null
    },
    {
      "id": "inert-enamel-coating",
      "name": "inert enamel coating on turbine alloys and hot-gas ducting",
      "material_page": null
    },
    {
      "id": "high-temperature-stainless-steel-lox-rich",
      "name": "high-temperature resistant stainless steel (new class, grade not stated)",
      "material_page": null
    }
  ],
  "standards": [],
  "relations": [
    {
      "type": "part_of",
      "target": "Atlas V",
      "target_slug": "ula-atlas-v",
      "note": "Booster engine of the Atlas V first stage (Common Core Booster)",
      "quote": "After engine delivery, the RD-180 engine is integrated with the Atlas V booster.",
      "source_url": "https://www.ulalaunch.com/docs/default-source/supporting-technologies/incorporation-of-rd-180-failure-response-2011.pdf"
    },
    {
      "type": "part_of",
      "target": "Atlas III launch vehicle",
      "target_slug": null,
      "note": "First flight of the RD-180, Atlas IIIA, 24 May 2000; one engine per first stage",
      "quote": "the first successful RD-180 powered Atlas launch took place on 24 May 2000, with the launch of an Atlas IIIA",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf"
    },
    {
      "type": "heritage_of",
      "target": "RD-170 engine",
      "target_slug": null,
      "note": "Two-chamber derivative of the four-chamber RD-170; 70 percent common hardware",
      "quote": "The engine was derived from the flight-proven NPO Energomash designed man-rated and reusable RD-170 engine.",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf"
    },
    {
      "type": "supplied_by",
      "target": "NPO Energomash",
      "target_slug": null,
      "note": "Designer and manufacturer of the engine, Khimki, Russia",
      "quote": "Designed and manufactured by NPO Energomash",
      "source_url": "https://www.ulalaunch.com/rockets/atlas-v"
    },
    {
      "type": "supplied_by",
      "target": "RD AMROSS",
      "target_slug": null,
      "note": "Pratt & Whitney / NPO Energomash joint venture that supplies the engines to the Atlas customer",
      "quote": "provided to Lockheed Martin by RD AMROSS, a 50/50 Pratt & Whitney / NPO Energomash Joint Venture company",
      "source_url": "https://www.lpre.de/resources/articles/AIAA-2004-3998.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Metalist (Samara)",
      "target_slug": null,
      "note": "Chamber manufacturer named in a ULA supplier-visit passage",
      "quote": "the chamber manufacturers at Metalist in Samara",
      "source_url": "https://www.ulalaunch.com/docs/default-source/evolution/rd-180-engine-an-established-record-of-performance-and-reliability-on-atlas-launch-vehicles.pdf"
    },
    {
      "type": "supplied_by",
      "target": "Arsenal (St. Petersburg)",
      "target_slug": null,
      "note": "Thrust vector control actuator supplier",
      "quote": "the RD-180 thrust vector control actuator supplier, Arsenal in St. Petersburg",
      "source_url": "https://www.ulalaunch.com/docs/default-source/evolution/rd-180-engine-an-established-record-of-performance-and-reliability-on-atlas-launch-vehicles.pdf"
    }
  ],
  "not_published": "Grades are not given for any alloy. No material is stated for the chambers, nozzles, injector heads, pump rotors, valves, gimbal parts or thrust frame. The enamel coating, the nickel and metal-ceramic coatings and the MIT-thesis composite may or may not be the same coating.",
  "depth": "partial",
  "photos": [],
  "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"
}