{ "id": "grumman-apollo-lunar-module", "title": "Apollo Lunar Module (LM)", "maker": "Grumman / NASA", "maker_type": "Commercial", "kind": "mission", "category": "crew", "page": "https://spacemushroom.com/space-products/grumman-apollo-lunar-module/", "website": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "summary": "Two-stage crewed lunar lander built by Grumman for Apollo. NASA's structural experience report states the major aluminium alloys (2219, 7075-T6), titanium for hot areas and the layered Mylar/Kapton/Inconel thermal shield is described in a second NASA report.", "application": "Two-stage crewed lunar lander used on Apollo missions 5 to 17 for crew landing on the Moon (four landings among the ten missions covered by the structural report). The descent stage landed and served as launch platform; the ascent stage carried two astronauts back to orbit to meet the command module.", "story": { "headline": "The Apollo Lunar Module was the two-stage Grumman lander that took astronauts down to the Moon.", "intro": [ "Grumman built the Apollo Lunar Module for NASA as a two-stage lander for a crew of two. The descent stage landed on the Moon and was also the launch platform for the ascent stage, which carried the two astronauts back to orbit to meet the command module. It was left behind on the Moon.", "The lander was designed to work only in space, with a minimum-weight structure. Its structure weighed about one fifteenth of the fully loaded spacecraft. The lander is mostly aluminium alloy, with titanium where it gets hot. Layers of metal and plastic film wrap both stages in a shield against heat and micrometeoroids, which are tiny grains of space dust." ], "built": [ { "title": "Ascent stage structure", "text": "The ascent stage is built mainly from aluminium alloys. The major ones are 2219 and 7075-T6, and some brackets and fasteners are titanium. The cabin is a cylindrical shell 92 inches across.", "parts": [ "Ascent-stage cabin, midsection and aft equipment bay shell", "Ascent-stage structure (major alloy)", "Cabin front-face, RCS cluster trusses, decks and bulkheads", "Ascent-stage brackets and fasteners" ] }, { "title": "Cabin windows", "text": "The cabin windows have two panes. The outer one, made of Vycor glass, is not structural and guards against micrometeoroids and radiation. The inner one, made of tempered Chemcor glass, is the structural pane, sealed by a metallic spring inside a Teflon jacket.", "parts": [ "Outer cabin window pane", "Inner cabin window pane", "Inner window seal jacket" ] }, { "title": "Descent stage and landing legs", "text": "The descent stage is mostly 7075-T6 aluminium alloy, with titanium where temperatures are high. Some struts in that alloy developed stress-corrosion cracking, a slow cracking of metal under constant stress, so the heat treatment was changed to one called T73. Crushable honeycomb cartridges in the landing gear absorb the shock of touchdown.", "parts": [ "Descent-stage main structure (beams, decks, bulkheads)", "Descent-stage hot-area structure", "Outrigger truss members and landing-gear struts (redesigned)", "Landing-gear energy absorbers" ] }, { "title": "Engine heat protection", "text": "The descent engine has its own heat protection. A base heat shield is built from alternating layers of nickel foil and a material called Fiberfrax, held on standoffs fixed to a titanium frame. A blast shield of Teflon-coated titanium sits on the upper edge of the engine compartment.", "parts": [ "Base heat shield (BHS) insulation", "Base heat shield support structure", "Engine compartment blast shield" ] }, { "title": "Thermal and micrometeoroid shield", "text": "Both stages are wrapped in a thermal blanket under an outer aluminium micrometeoroid shield. The blanket's core is many layers of aluminised Mylar film, enclosed in aluminised Kapton film. Near the engine plumes, foils and mesh of Inconel and nickel replace the blanket and the aluminium skin.", "parts": [ "Insulation blanket core", "Insulation blanket inner and outer layers", "Micrometeoroid shield", "Plume-exposed shield areas" ] } ], "materials": [ { "name": "Aluminium 7075-T6", "mid": "aluminium-7075", "where": "Most of the descent stage structure, and a major alloy of the ascent stage alongside alloy 2219." }, { "name": "Titanium", "mid": "titanium", "where": "Ascent-stage brackets and fasteners, hot areas of the descent stage, and the frame of the base heat shield." }, { "name": "Inconel", "mid": "inconel", "where": "Foil and mesh in the shield areas near the engine plumes, and in the thruster plume deflector." }, { "name": "Aluminised Mylar", "mid": "aluminised-polyester-mylar", "where": "The core of the thermal blanket, as thin aluminised polyester film in many layers." }, { "name": "Chemcor glass", "mid": "chemcor-glass", "where": "The inner, structural pane of the cabin windows." }, { "name": "Nickel foil and Fiberfrax", "mid": "nickel-foil-fiberfrax-composite", "where": "Alternating layers that insulate the base heat shield, held on standoffs fixed to a titanium frame." } ], "connections": "Grumman built the lander for NASA, and it was used on Apollo missions 5 to 17. The Apollo 11 lander launched on 16 July 1969 on a Saturn V from Cape Canaveral.", "unknown": "The alloys of the propellant, oxygen and helium tanks, the landing-gear honeycomb and the cabin hatch are not named, and nor are the materials of the two engines. Published layer counts for the thermal blanket differ between landers. The masses here are for the Apollo 11 lander only.", "facts": [ { "label": "Total mass, Apollo 11 lander", "value": "15,103 kg incl. propellants" }, { "label": "Descent stage size", "value": "Octagonal prism, 4.2 m across, 1.7 m thick" }, { "label": "Ascent stage size", "value": "About 2.8 m high, 4.0 by 4.3 m wide" }, { "label": "Cabin diameter", "value": "92 inches" }, { "label": "Launch, Apollo 11 lander", "value": "16 July 1969, Saturn 5, Cape Canaveral" }, { "label": "Structural mass ratio", "value": "about 1 to 15 of structural weight to fully loaded weight" } ] }, "specifications": [ { "label": "Total mass (Apollo 11 LM-5)", "value": "15,103 kg incl. propellants", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "The spacecraft mass of 15103 kg was the total mass of the LM ascent and descent stages including propellants" }, { "label": "Ascent stage dry mass", "value": "2,445 kg", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "The dry mass of the ascent stage was 2445 kg" }, { "label": "Descent stage dry mass", "value": "2,034 kg incl. stowed surface equipment", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "The descent stage dry mass (including stowed surface equipment) was 2034 kg" }, { "label": "Descent stage size", "value": "Octagonal prism, 4.2 m across, 1.7 m thick", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "an octagonal prism 4.2 meters across and 1.7 m thick" }, { "label": "Ascent stage size", "value": "About 2.8 m high, 4.0 by 4.3 m wide", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "approximately 2.8 m high and 4.0 by 4.3 meters in width" }, { "label": "Cabin diameter", "value": "92 inches", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "quote": "The cylindrical structural shell of the cabin is 92 inches in diameter" }, { "label": "Crew compartment volume", "value": "6.65 cubic meters", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "a pressurized crew compartment with a volume of 6.65 cubic meters" }, { "label": "Launch (Apollo 11 LM)", "value": "16 July 1969, Saturn 5, Cape Canaveral", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "Launch Date: 1969-07-16" }, { "label": "Structural mass ratio", "value": "about 1 to 15 of structural weight to fully loaded weight", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "quote": "A ratio of approximately 1 to 15 of the structural weight to the fully loaded spacecraft weight was achieved." }, { "label": "Destination", "value": "Moon surface (four landings in 10 Apollo missions)", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "quote": "No problems were associated with the primary lunar module structure during the 10 Apollo missions, including four lunar landings." }, { "label": "Height with legs extended", "value": "22.92 ft", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "LM Height 22.92 ft (legs extended)" }, { "label": "Diameter across extended landing gear", "value": "31.00 ft measured diagonally", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "LM Diameter 31.00 ft (diagonally across extended landing gear)" }, { "label": "Earth-launch mass (Apollo News Reference)", "value": "About 36,100 lb with crew and propellant", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "quote": "Earth launch (with crew and propellant) 36,100 lb. (approx.)" }, { "label": "Dry mass of the whole LM", "value": "About 10,800 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "LM Empty Weight 10,800 lb" }, { "label": "Ascent stage propellant mass", "value": "5,200 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "Ascent Stage Propellant Weight 5,200 lb" }, { "label": "Descent stage propellant mass", "value": "19,500 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "Descent Stage Propellant Weight 19,500 lb" }, { "label": "Ascent stage RCS propellant mass", "value": "600 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "Ascent Stage RCS Propellant Weight 600 lb" }, { "label": "Habitable volume", "value": "160 cubic ft", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "LM Habitable Volume 160 ft³" }, { "label": "Cabin pressure", "value": "4.8 plus or minus 0.2 psia", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "LM Cabin Pressure 4.8 ± 0.2 psia" }, { "label": "Crew compartment depth", "value": "Cylindrical, 92 in diameter and 42 in deep", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "The crew compartment, which occupied the ascent stage front, was cylindrical, with a 92\" diameter and a 42\" depth." }, { "label": "Flight station spacing", "value": "Flight-station centerlines 44 in apart", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "Flight-station centerlines were 44\" apart." }, { "label": "Front window area", "value": "Each triangular front window has about 2 square ft of viewing area", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "The two triangular windows in the front face assembly each had a two ft² viewing area." }, { "label": "Docking window area", "value": "About 80 square in", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "quote": "The docking window above the Commander's flight station had approximately 80 in² of viewing area and provided docking visibility." }, { "label": "Engine count", "value": "18 engines: two large rockets (descent and ascent) plus small attitude control engines", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html", "quote": "The lander had 18 engines: 2 large rockets, one for descent to the moon and another for return to lunar orbit" }, { "label": "Ascent engine thrust (NASA SP-4205)", "value": "About 15,500 N (3,500 lbf)", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html", "quote": "The rocket engine of the ascent stage developed about 15,500 newtons (3,500 pounds) of thrust" }, { "label": "Ascent engine thrust (NSSDC)", "value": "About 15,000 N", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "The ascent engine was a fixed, constant-thrust rocket with a thrust of about 15,000 N." }, { "label": "Descent engine thrust (NSSDC)", "value": "About 45,000 N maximum", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "a maximum thrust of about 45,000 N mounted on a gimbal ring in the center of the descent stage" }, { "label": "Apollo 11 LM lunar surface stay", "value": "21 hours 36 minutes", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "after 21 hours, 36 minutes on the lunar surface" }, { "label": "Lunar roving vehicle use", "value": "Allowed travel up to 5 km from touchdown on the later three missions", "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml", "quote": "A lunar roving vehicle allowed the crew to travel up to 5 km from the touchdown point during the later three missions." }, { "label": "Descent propellant remaining at low-level warning", "value": "Enough for only 2 minutes of burn at hover thrust", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml", "quote": "the propellant remaining quantity was sufficient for only 2 minutes of engine burn at hover thrust" }, { "label": "Landing radar acquisition", "value": "Altitude data from about 38,000 ft, velocity data from about 25,000 ft", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "quote": "altitude data acquisition began at about 38,000 feet above the lunar surface; velocity data at about 25,000 feet" }, { "label": "Late-mission descent engine changes", "value": "Apollo 15, 16 and 17 engines had a 10 in skirt extension and a quartz liner", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "quote": "Apollo 15, 16 and 17 LMDEs were fitted with a 10\" skirt extension and a quartz combustion chamber liner." } ], "features": [ { "text": "Designed to operate exclusively in space, with minimum-weight structure", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "quote": "The lunar module spacecraft was designed to operate exclusively in a space environment.", "quote_check": "not matched on the source page" }, { "text": "Descent stage carries landing rocket, propellant tanks and lunar equipment; ascent stage returns crew to the command module", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C", "quote": "The descent stage served as a platform for launching the ascent stage and was left behind on the Moon." }, { "text": "Enclosed in thermal and micrometeoroid shields", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "quote": "Both ascent and descent stages are enclosed in thermal and micrometeoroid shields.", "quote_check": "not matched on the source page" }, { "text": "Stress-corrosion cracking in 7075-T6 struts led to redesign in the T73 temper", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "quote": "Additional corrective actions included changing the heat treatment from 7075-T6 to 7075-T73" } ], "parts": [ { "assembly": "Ascent stage structure", "parts": [ { "part": "Ascent-stage cabin, midsection and aft equipment bay shell", "material": "Aluminium alloy 2219", "form": "welded and fastened sheet with machined longerons", "finish": null, "standard": null, "hardware_ref": null, "quote": "Aluminum alloys are used primarily in the construction of the ascent stage. The major alloys are 2219 and 7075-T6.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": null, "mid": "aluminium-2219" }, { "part": "Ascent-stage structure (major alloy)", "material": "Aluminium 7075-T6", "form": "sheet, machined parts", "finish": null, "standard": null, "hardware_ref": null, "quote": "The major alloys are 2219 and 7075-T6.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": "aluminium-7075", "mid": "aluminium-7075" }, { "part": "Cabin front-face, RCS cluster trusses, decks and bulkheads", "material": "aluminium alloy (grade not stated)", "form": "sheet, tubular truss, integrally stiffened machined plate", "finish": null, "standard": null, "hardware_ref": null, "quote": "Aluminum alloys are the primary construction material.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": "aluminium", "mid": "aluminium" }, { "part": "Some brackets and fasteners (lunar module)", "material": "Titanium", "form": "brackets, fasteners", "finish": null, "standard": null, "hardware_ref": null, "quote": "Aluminum alloys are the primary construction material. Some brackets and fasteners are made of titanium.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": "titanium", "mid": "titanium" }, { "part": "Outer cabin window pane", "material": "Vycor annealed glass", "form": "pane", "finish": null, "standard": null, "hardware_ref": null, "quote": "The outer nonstructural pane is a micrometeoroid/radiation protective window made from annealed (Vycor) glass.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": null, "mid": "vycor-glass" }, { "part": "Inner cabin window pane", "material": "Chemcor tempered glass", "form": "pane", "finish": null, "standard": null, "hardware_ref": null, "quote": "The inner pane is the structural window made from tempered (Chemcor) glass.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": null, "mid": "chemcor-glass" }, { "part": "Inner window seal jacket", "material": "Teflon", "form": "jacket around metallic spring seal", "finish": null, "standard": null, "hardware_ref": null, "quote": "a seal constructed from metallic spring surrounded by a Teflon jacket", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": null, "mid": "teflon-ptfe" } ] }, { "assembly": "Descent stage structure and landing gear", "parts": [ { "part": "Descent-stage main structure (beams, decks, bulkheads)", "material": "Aluminium 7075-T6", "form": "chemically milled webs, extruded and milled stiffeners, milled cap strips", "finish": null, "standard": null, "hardware_ref": null, "quote": "The material used in the construction of the descent stage is primarily 7075-T6 aluminum alloy.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": "aluminium-7075", "mid": "aluminium-7075" }, { "part": "Descent-stage hot-area structure", "material": "Titanium", "form": "structure", "finish": null, "standard": null, "hardware_ref": null, "quote": "Titanium is used where high temperatures are experienced.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": "titanium", "mid": "titanium" }, { "part": "Outrigger truss members and landing-gear struts (redesigned)", "material": "Aluminium 7075-T73", "form": "tubes and fittings, changed from T6 after stress corrosion cracking", "finish": null, "standard": null, "hardware_ref": null, "quote": "all struts except the outriggers were redesigned to the 7075-T73 condition", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": null, "mid": "aluminium-7075-t73" }, { "part": "Shear-deck webs, interim fatigue fix", "material": "Fibre-glass cloth", "form": "layered cloth 'picture frame' on early vehicles", "finish": null, "standard": null, "hardware_ref": null, "quote": "a fiber-glass \"picture frame\" was applied to each panel of the shear deck", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": null, "mid": "fiberglass-cloth" }, { "part": "Landing-gear energy absorbers", "material": null, "form": "crushable honeycomb cartridge", "finish": null, "standard": null, "hardware_ref": null, "quote": "A honeycomb cartridge that fits in the two cylinders provides 9500 pounds of compression stroking at touchdown.", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": null, "mid": null } ] }, { "assembly": "Descent engine heat protection", "parts": [ { "part": "Base heat shield (BHS) insulation", "material": "Nickel foil and Fiberfrax (alternating layers)", "form": "layered composite", "finish": null, "standard": null, "hardware_ref": null, "quote": "a composite of alternate layers of nickel foil and Fiberfrax supported by standoffs attached to the titanium BHS structure", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": null, "mid": "nickel-foil-fiberfrax-composite" }, { "part": "Base heat shield support structure", "material": "Titanium", "form": "structure with standoffs", "finish": null, "standard": null, "hardware_ref": null, "quote": "attached to the titanium BHS structure", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": "titanium", "mid": "titanium" }, { "part": "Engine compartment blast shield", "material": "Teflon-coated titanium", "form": "shaped shield", "finish": "Teflon coating", "standard": null, "hardware_ref": null, "quote": "A specially shaped blast shield of Teflon-coated titanium is secured to the upper edge of the engine compartment", "source_url": "https://ntrs.nasa.gov/api/citations/19730010174/downloads/19730010174.pdf", "profile": "titanium", "mid": "titanium" } ] }, { "assembly": "Thermal and micrometeoroid shield", "parts": [ { "part": "Insulation blanket core", "material": "Aluminized polyester film (Mylar)", "form": "25 layers of 1/8-mil film", "finish": null, "standard": null, "hardware_ref": null, "quote": "25 layers of 1/8-mil aluminized polyester film encapsulated in inner and outer 1/2-mil layers of aluminized polyimide film", "source_url": "https://ntrs.nasa.gov/api/citations/19720018272/downloads/19720018272.pdf", "profile": null, "mid": "aluminised-polyester-mylar" }, { "part": "Insulation blanket inner and outer layers", "material": "Aluminized polyimide film (H-film / Kapton)", "form": "1/2-mil film", "finish": null, "standard": null, "hardware_ref": null, "quote": "inner and outer 1/2-mil layers of aluminized polyimide film", "source_url": "https://ntrs.nasa.gov/api/citations/19720018272/downloads/19720018272.pdf", "profile": null, "mid": "aluminised-polyimide-h-film" }, { "part": "Micrometeoroid shield", "material": "aluminium (alloy not stated)", "form": "outer skin", "finish": null, "standard": null, "hardware_ref": null, "quote": "an outer micrometeoroid shield of aluminum", "source_url": "https://ntrs.nasa.gov/api/citations/19720018272/downloads/19720018272.pdf", "profile": "aluminium", "mid": "aluminium" }, { "part": "Plume-exposed shield areas", "material": "Inconel foil and Inconel mesh", "form": "foil and mesh substituted for blanket and aluminium skin", "finish": null, "standard": null, "hardware_ref": null, "quote": "substituting layers of polyimide film, nickel foil, Inconel mesh, and Inconel foil", "source_url": "https://ntrs.nasa.gov/api/citations/19720018272/downloads/19720018272.pdf", "profile": null, "mid": "inconel" }, { "part": "Plume-exposed shield areas, underlayer", "material": "Nickel foil", "form": "foil", "finish": null, "standard": null, "hardware_ref": null, "quote": "substituting layers of polyimide film, nickel foil, Inconel mesh, and Inconel foil", "source_url": "https://ntrs.nasa.gov/api/citations/19720018272/downloads/19720018272.pdf", "profile": null, "mid": "nickel-foil" }, { "part": "RCS plume deflector", "material": "Inconel, Inconel mesh and nickel foil", "form": "layered cone, attached to titanium strap", "finish": null, "standard": null, "hardware_ref": null, "quote": "The deflector is constructed of Inconel, Inconel mesh, and nickel foil.", "source_url": "https://ntrs.nasa.gov/api/citations/19720018272/downloads/19720018272.pdf", "profile": null, "mid": "inconel" } ] }, { "assembly": "Ascent stage cabin and interfaces", "parts": [ { "part": "Control and display panels", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "Control and display panels contained everything necessary to control and monitor subsystem performance.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Panels from which either astronaut can control and monitor every subsystem and fly the LM", "specs": [ { "label": "Front panels", "value": "Six panels sit in front of the flight stations, canted for viewing", "quote": "Six of the panels were in front of the flight stations.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "label": "Circuit breaker panels", "value": "A five-tier circuit breaker panel sits left of the Commander's station", "quote": "a five-tier circuit breaker panel at the top", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Flight stations: attitude and thrust/translation controllers with adjustable armrests", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "Each flight station has an attitude controller, a thrust/translation controller, and adjustable armrests.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "profile": null, "mid": null, "function": "Hand controllers at each flight station for rotation and translation" }, { "part": "Window heaters and shades", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "All three windows were electrically heated to prevent fogging.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Electric heaters keep the windows from fogging; a shade with antireflective coating covers each window", "specs": [ { "label": "Shades", "value": "A shade with an antireflective coating on its outboard side is provided for each window", "quote": "A window shade, with an antireflective coating on its outboard side, was provided for each window.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "label": "Window layout", "value": "Two triangular front windows plus a docking window above the Commander's station", "quote": "The docking window above the Commander's flight station had approximately 80 in² of viewing area and provided docking visibility.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Forward hatch", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The forward hatch was in the front face assembly, just below the lower display panels.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Hatch in the front face used to go between the cabin and the lunar surface or for EVA while docked", "specs": [ { "label": "Size and motion", "value": "About 32 in square, hinged to swing inboard", "quote": "The hatch was approximately 32\" square and was hinged to swing inboard when opened.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "label": "Latch", "value": "Cam latch forces a lip into a preloaded elastomeric silicone seal", "quote": "A cam latch assembly held the hatch closed and forced a circumferential lip into a preloaded elastomeric silicone seal secured to the LM structure.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Overhead (docking) hatch", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The 33\" overhead hatch was at the top midsection centerline.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Hatch at the top of the midsection that gives access to the docking tunnel and the command module", "specs": [ { "label": "Latch", "value": "Off-center latch operable from either side; opens inward by turning the handle 90 degrees", "quote": "The hatch opened inward by rotating the latch handle 90°.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Hatch seals (elastomeric silicone)", "material": "Elastomeric silicone compound", "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "A preloaded elastomeric silicone seal was mounted in the hatch frame structure.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": "elastomeric-silicone-seal", "function": "Preloaded seals in the hatch frames that the hatch lip presses into for a pressure-tight fit" }, { "part": "Docking tunnel and ring", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The docking tunnel, immediately above the overhead hatch, provided a structural interface between the LM and the CSM", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Structural passage between the LM and the command module, topped by a docking ring", "specs": [ { "label": "Size", "value": "32 in diameter, 16 in long", "quote": "The tunnel diameter was 32\" and it was 16\" long.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Docking drogue", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The drogue, a portion of the docking mechanism, was secured below the ring to three mounts in the LM tunnel", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Cone in the LM tunnel that receives the CSM docking probe for soft capture", "specs": [ { "label": "Capture role", "value": "Mates with the CSM docking probe", "quote": "A drogue within the LM, which mated with the CSM docking probe, was installed in the LM docking tunnel, just below the ring.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Crew compartment deck Velcro pile", "material": "Nonflammable Velcro pile", "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "covered with nonflammable Velcro pile that interfaced with hooked Velcro on the astronauts' boot soles", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": "velcro", "function": "Hooked boot soles grip the pile to hold the crew to the deck in zero gravity" }, { "part": "Midsection", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The midsection housed the ascent engine, part of which protruded up through the lower deck.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Walk-through space aft of the crew compartment that houses the ascent engine and ECS components", "specs": [ { "label": "Size", "value": "54 in deep and about 60 in high", "quote": "The midsection was 54\" deep and about 60\" high.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Aft equipment bay and equipment rack", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The unpressurized aft equipment bay was formed by the aft midsection bulkhead and the equipment rack", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Unpressurized bay with electronics on a water-glycol cold-rail rack, plus gas tanks", "specs": [ { "label": "Cold rails", "value": "Water-glycol flows through vertical cold rails that carry heat from the electronics", "quote": "Water-glycol flowed through the cold rails.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "label": "Tanks", "value": "Two gaseous oxygen tanks and two gaseous helium tanks on trusses", "quote": "Two gaseous oxygen tanks and two gaseous helium tanks were secured to truss members between the midsection aft bulkhead and the equipment rack.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] } ] }, { "assembly": "Descent stage and interfaces", "parts": [ { "part": "Modularized equipment stowage assembly (MESA)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "Quad No. 4 housed the modularized equipment stowage assembly (MESA), which consisted of television equipment, lunar sample stowage, and PLSS components.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Descent stage quad that carries television equipment, lunar sample stowage and PLSS components" }, { "part": "Quad 3 pallets: lunar roving vehicle and Lunar Retro-Ranging Reflector", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The quad No. 3 contained the lunar roving vehicle (LRV) and the Lunar Retro-Ranging Reflector.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Descent stage quad that stowed the rover on the later J missions and the laser reflector" }, { "part": "Interstage fittings (x4)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The LM ascent and descent stages were joined by four interstage fittings that were explosively severed at staging.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Join the ascent and descent stages; severed explosively at staging" }, { "part": "Explosive devices (cartridges, nuts and bolts, cable guillotine)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "Electro-chemical explosive devices were operated by the astronauts to pressurize the propellant tanks, separate the ascent and descent stages", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Fire to pressurize tanks, deploy the landing gear, vent the tanks and separate the stages", "specs": [ { "label": "Stage separation", "value": "Explosive nuts and bolts join the stages and are fired at separation", "quote": "Next, explosive nuts and bolts joining the stages were ignited.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "label": "Wire and line cutting", "value": "Explosive cable-cutter guillotine severs wires, cables and water lines between stages", "quote": "Finally, an explosive cable-cutter guillotine automatically severed all wires, cables, and water lines connected between the stages.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "SLA attachment pads and explosive tiedown straps", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "Pads at the descent stage outrigger apexes mated with the SLA attachment fittings.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Outrigger apex pads that mate with the adapter fittings and are released after docking" } ] }, { "assembly": "Landing gear", "parts": [ { "part": "Landing gear assemblies (x4, cantilever)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The cantilever landing gear consists of four assemblies, each connected to an outrigger that extends from the ends of the structural parallel beams.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "profile": null, "mid": null, "function": "Four legs that absorb landing impact and support the LM on the surface", "specs": [ { "label": "Stability", "value": "Prevents tip-over on a 6 degree slope with 24 in depressions or protuberances", "quote": "prevents tipover of the LM on a lunar surface with a 6° general slope having 24-inch depressions or protuberances", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf" } ] }, { "part": "Primary struts with crushable aluminum-honeycomb cartridge", "material": "Aluminum honeycomb (alloy not stated)", "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "by a crushable aluminum-honeycomb cartridge in each strut", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "profile": null, "mid": "aluminium-honeycomb", "function": "Piston-cylinder strut whose honeycomb cartridge crushes to absorb the landing", "specs": [ { "label": "Stroke", "value": "Maximum compression length 32 in", "quote": "Maximum compression length of the primary strut is 32 inches.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf" }, { "label": "Footpad joint", "value": "Lower end has a ball joint for the footpad", "quote": "the lower end has a ball joint for the footpad", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf" } ] }, { "part": "Footpads (x4, aluminum honeycomb)", "material": "Aluminum honeycomb (alloy not stated)", "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "is aluminum-honeycomb; its diameter is 37 inches. This large diameter ensures minimal penetration of the LM", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "profile": null, "mid": "aluminium-honeycomb", "function": "37 in diameter pads that limit sinking into low-strength soil" }, { "part": "Lunar surface sensing probes (x3)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The lunar surface sensing probe attached to each landing gear footpad, except the forward one, is an electromechanical device.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "profile": null, "mid": null, "function": "Contact probes about 5 ft below the footpads that tell the crew to shut down the descent engine", "specs": [ { "label": "Reach", "value": "Probe head about 5 ft below the footpad after deployment", "quote": "spring energy to extend the probes so that the probe head is approximately 5 feet below the", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf" } ] }, { "part": "Uplock assemblies (x4) with detonator cartridges", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "One uplock assembly is attached to each landing gear assembly.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "profile": null, "mid": null, "function": "Explosive-severed straps that hold the legs retracted until deployment in lunar orbit", "specs": [ { "label": "Construction", "value": "Fixed link (strap) and two end detonator cartridges in one case", "quote": "It consists of a fixed link (strap) and two end detonator cartridges in a single case.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf" } ] }, { "part": "Ladder and external platform", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The ladder affixed to the primary strut of the forward landing gear assembly has nine rungs between two railings.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "profile": null, "mid": null, "function": "Nine-rung ladder on the forward leg and a platform below the forward hatch for access to the surface", "specs": [ { "label": "Platform size", "value": "About 32 in wide and 45 in long, corrugated upper surface", "quote": "An external platform, approximately 32 inches wide and 45 inches long", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf" } ] } ] }, { "assembly": "Descent propulsion", "parts": [ { "part": "Descent engine (TRW Lunar Module Descent Engine, LMDE)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: TRW (Space Technology Laboratories)", "quote": "The TRW Lunar Module Descent Engine (LMDE, VTR-10) was a pressure-fed, variable thrust, gimbaling, liquid-propellant rocket engine with a 9,850 lbT maximum nominal thrust.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "profile": null, "mid": null, "function": "Throttleable, gimbaled engine that brakes the LM from lunar orbit, lands it and can hover", "specs": [ { "label": "Thrust at full throttle (table)", "value": "10,500 lbf in vacuum at full throttle position", "quote": "Thrust (FTP, Vacuum) 10,500 lbT", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "label": "Thrust (NASA SP-4205)", "value": "Maximum 9,870 lbf, minimum 1,050 lbf", "quote": "reached a maximum of 43,900 newtons (9,870 pounds) and operated at a minimum of 4,700 newtons (1,050 pounds)", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" }, { "label": "Throttle range", "value": "10:1", "quote": "Throttle Range 10:1", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "label": "Specific impulse", "value": "305 s", "quote": "Specific Impulse 305 sec", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "label": "Mass", "value": "About 394 lb", "quote": "Approximate Weight 394 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "label": "Restarts", "value": "20 restarts", "quote": "Engine Restart Capability 20 Times", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "label": "Gimbal range", "value": "Plus or minus 6 degrees along Y and Z axes", "quote": "Engine-Gimbaling Capability ± 6°from Center, along Y- and Z-axis", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "label": "Propellants", "value": "Aerozine 50 fuel and nitrogen tetroxide oxidizer", "quote": "DPS propellants, Aerozine 50 fuel and nitrogen tetroxide oxidizer", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml" } ] }, { "part": "Variable-area pintle injector", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The variable-area injector consisted of a pintle assembly, drive assembly, and manifold assembly.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "profile": null, "mid": null, "function": "Sleeve-controlled injector whose area changes with thrust to keep combustion stable", "specs": [ { "label": "Fuel and oxidizer injection", "value": "Fuel through an annular orifice plus a 36-hole barrier ring; oxidizer through 36 variable-area ports", "quote": "Oxidizer entered the injector assembly center, where it was directed into the combustion chamber radially through 36 variable-area ports", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" } ] }, { "part": "Cavitating venturi flow control valves", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The flow control valves were non-redundant cavitating venturis with movable pintle sleeves.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "profile": null, "mid": null, "function": "Mechanically linked valves that meter fuel and oxidizer flow to set thrust" }, { "part": "Combustion chamber case (titanium alloy)", "material": "6Al-4V titanium alloy forgings (printed '6A1-4V')", "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The engine chamber and exit cone portions were machined from 6A1-4V titanium alloy forgings and welded into one unit at the throat centerline.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "profile": null, "mid": "titanium-6al-4v", "function": "Titanium case around the ablative liner, welded to the exit cone at the throat" }, { "part": "Ablative chamber liner", "material": "Silica cloth/phenolic ablative with needle-felted silica mat/phenolic insulation", "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The selected configuration consisted of a high density, erosion-resistant silica cloth/phenolic material surrounded by a lightweight needle-felted silica mat/phenolic insulation.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "profile": null, "mid": "silica-phenolic-ablative", "function": "Composite ablative heat sink that keeps the case near 800 F", "specs": [ { "label": "Heat shield", "value": "Two layers of 0.0015 in stainless steel foil separated by fiberglass wool on the case exterior", "quote": "Two layers of 0.0015\" stainless steel foil separated by fiberglass wool comprised the heat shield.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" } ] }, { "part": "Radiation-cooled nozzle extension (columbium C-103)", "material": "Columbium (niobium) alloy C-103 with an aluminide coating", "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Wah Chang Company", "quote": "Columbium alloy C-103 was selected as the nozzle extension material because of its high-temperature (2,700°F) structural properties.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "profile": null, "mid": "columbium-alloy-c-103", "function": "Thin, crushable nozzle skirt from the 16:1 area ratio to 47.5:1", "specs": [ { "label": "Supplier", "value": "Wah Chang Company supplied the columbium nozzle and coatings", "quote": "The Wah Chang Company supplied the very thin columbium nozzle and coatings.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "label": "Expansion ratio (early engines)", "value": "47.5:1", "quote": "Expansion Area Ratio (ε = Ae/At) (Early) 47.5:1", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "label": "Expansion ratio (late engines)", "value": "53.6:1", "quote": "Expansion Area Ratio (ε = Ae/At) (Late) 53.6:1", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" } ] }, { "part": "Throttle valve actuator", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Bendix Commercial Vehicle Systems", "quote": "The throttle valve actuator, built by Bendix Commercial Vehicle Systems, was a linear-motion electromechanical servo actuator that moved the throttle linkage", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "profile": null, "mid": null, "function": "Electromechanical servo actuator that moves the throttle linkage on command" }, { "part": "Gimbal ring and gimbal drive actuators", "material": "7075-T73 aluminum alloy", "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: AiResearch Manufacturing Co. of Los Angeles (gimbal drive actuators)", "quote": "The gimbal assembly was a rectangular frame composed of four beams with a modified I section machined from 7075-T73 aluminum alloy.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml", "profile": null, "mid": "aluminium-7075-t73", "function": "Frame and two actuators that tilt the engine through the center of gravity", "specs": [ { "label": "Actuator maker", "value": "Gimbal drive actuators built by Airesearch Mfg. Company of Los Angeles", "quote": "The gimbal drive actuators, built by Airesearch Mfg. Company of Los Angeles, California", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" } ] }, { "part": "Descent propellant tanks (x4, titanium)", "material": "Titanium (alloy not stated)", "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: General Motors Allison Division (initial); Sargent Industries Airite Division (later)", "quote": "The DPS propellant supply was contained in four cylindrical, hemispherical-ended titanium tanks of identical construction", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml", "profile": "titanium", "mid": "titanium", "function": "Four tanks, two fuel and two oxidizer, feeding the descent engine", "specs": [ { "label": "Makers", "value": "Initially General Motors Allison Division, later Sargent Industries Airite Division", "quote": "initially built by the General Motors Allison Division of Indianapolis, Indiana, and later built by Sargent Industries Airite Division of El Segundo, California", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml" }, { "label": "Total fuel", "value": "7,513 lb", "quote": "Total Fuel 7,513 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml" }, { "label": "Total oxidizer", "value": "11,993 lb", "quote": "Total Oxidizer 11,993 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml" } ] }, { "part": "Supercritical helium tank (cryogenic)", "material": "Aluminized Mylar insulation in the vacuum space between tank and jacket", "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Garrett Corporation AiResearch Manufacturing Company", "quote": "The double-walled supercritical helium tank consisted of an inner spherical tank and an outer jacket.", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml", "profile": null, "mid": "aluminised-polyester-mylar", "function": "Double-walled tank of supercritical helium that pressurizes the descent propellant tanks", "specs": [ { "label": "Maker", "value": "Tanks manufactured by The Garrett Corporation's Airesearch Manufacturing Company, Los Angeles", "quote": "with the tanks being manufactured by The Garrett Corporation's Airesearch Manufaturing Company of Los Angeles, California", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml" }, { "label": "Insulation", "value": "Void between inner tank and outer jacket filled with aluminized Mylar and evacuated", "quote": "The void between the tank and jacket was filled with aluminized Mylar insulation and evacuated", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml" }, { "label": "Burst disks", "value": "Two burst disks in series rupture between 1,881 and 1,967 psi", "quote": "The identical burst disks burst at a pressure between 1,881 and 1,967 psi", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml" } ] }, { "part": "Propellant quantity gauging system (PQGS)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "A propellant quantity gauging system (PQGS) enabled astronauts to monitor propellants remaining quantities in the four DPS tanks.", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml", "profile": null, "mid": null, "function": "Four probes and a control unit that show remaining fuel and oxidizer and give a low-level warning" } ] }, { "assembly": "Ascent propulsion", "parts": [ { "part": "Ascent engine (Lunar Module Ascent Engine, LMAE, RS-1801)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Rocketdyne Division of North American Rockwell (injector, final assembly); Bell Aerosystems (valves, thrust chamber)", "quote": "The Lunar Module Ascent Engine (LMAE, RS-1801) provided the astronauts' only escape from the lunar surface.", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml", "profile": null, "mid": null, "function": "Fixed-thrust restartable engine that lifts the ascent stage off the Moon", "specs": [ { "label": "Thrust", "value": "3,500 lbf", "quote": "The LMAE produced 3,500 lbT", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml" }, { "label": "Maker", "value": "Built by Rocketdyne with nozzle and valve designs and components from Bell Aerosystems", "quote": "The LMAE was built by North American Rockwell, Rocketdyne Division, Canoga Park, California", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml" }, { "label": "Propellants", "value": "Nitrogen tetroxide oxidizer and Aerozine 50 fuel", "quote": "The APS used nitrogen tetroxide (N2O4) as the oxidizer and Aerozine 50 as the fuel.", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml" }, { "label": "Burn requirement", "value": "550 s total duration", "quote": "fire for a 550-second total duration", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml" }, { "label": "Mass after weight reduction", "value": "A 171 lb engine reduced by 30 lb", "quote": "reduced the 171-lb engine's weight by 30 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml" } ] }, { "part": "Ascent engine injector (Rocketdyne)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Rocketdyne Division of North American Rockwell", "quote": "Rocketdyne's new injector design was a baffled, flat-faced, multi-ring unit with integral propellant-distribution manifolding and acoustic cavities.", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml", "profile": null, "mid": null, "function": "Baffled flat-faced multi-ring injector with acoustic cavities that cured combustion instability" }, { "part": "Ascent engine ablative chamber and nozzle extension", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Bell Aerosystems", "quote": "The combustion chamber assembly consisted of the engine case and mount assembly and an ablative material (plastic) assembly, which included the nozzle extension.", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml", "profile": null, "mid": null, "function": "Plastic ablative assembly that cools the chamber and the nozzle out to a 45.6:1 area ratio", "specs": [ { "label": "Expansion ratio", "value": "Nozzle extension ablative material runs from 4.5:1 to the 45.6:1 exit plane", "quote": "The nozzle extension ablative material extended from the expansion ratio of 4.5:1 to the 45.6:1 exit plane", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml" }, { "label": "Bell role", "value": "Bell had the valves and thrust chamber", "quote": "Rocketdyne was responsible for the injector and final assembly but Bell had the valves and thrust chamber.", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml" } ] }, { "part": "Ascent engine bipropellant valve package", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The four individual bipropellant valve assemblies that made up the bipropellant valve package were arranged in a series-parallel arrangement", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml", "profile": null, "mid": null, "function": "Four series-parallel valve assemblies giving redundant start and stop" }, { "part": "Ascent propellant tanks (x2, spherical titanium)", "material": "Titanium (alloy not stated)", "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Aerojet General Corporation, Downey plant", "quote": "The propellant supply was contained in two spherical titanium tanks.", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml", "profile": "titanium", "mid": "titanium", "function": "One fuel tank and one oxidizer tank for the ascent engine, linked to the RCS", "specs": [ { "label": "Maker", "value": "Built by the Aerojet General Corporation Downey plant", "quote": "The APS oxidizer and fuel tanks, built by the Aerojet General Corporation Downey Plant in Downey, California", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml" } ] }, { "part": "Ascent helium tanks (x2)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Sargent Industries Airite Division", "quote": "which was stored in two identical tanks that were made by Sargent Industries, Airite Division, El Segundo, California", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml", "profile": null, "mid": null, "function": "Ambient-temperature helium that pressurizes the ascent propellant tanks" } ] }, { "assembly": "Reaction control", "parts": [ { "part": "RCS thrusters (x16, Marquardt R-4D)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: The Marquardt Corporation", "quote": "The R-4D RCS thrusters, supplied by the Marquardt Corporation of Van Nuys, California", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml", "profile": null, "mid": null, "function": "Four clusters of four 100 lbf thrusters for attitude, translation, ullage and docking", "specs": [ { "label": "Count", "value": "16 thrusters in or on the ascent stage", "quote": "The 16 thrust chamber assemblies (thrusters), propellant and helium subsystems that comprised the RCS were located in or on the ascent stage.", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml" }, { "label": "Thrust", "value": "100 lbf each", "quote": "The thrusters were small rocket engines, each capable of delivering 100 lbT.", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml" }, { "label": "Arrangement", "value": "Clusters of four on four outriggers around the ascent stage", "quote": "They were arranged in clusters of four, mounted on four outriggers equally spaced around the ascent stage.", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml" }, { "label": "Mass", "value": "About 5.25 lb", "quote": "Approximate weight 5.25 lb", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml" }, { "label": "Cooling and ratio", "value": "Radiation and fuel-film cooled; nozzle area ratio 40:1", "quote": "Nozzle Expansion Area Ratio 40:1", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml" }, { "label": "Total life", "value": "1,000 s", "quote": "Engine Life Total 1000 sec", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml" }, { "label": "Restarts", "value": "10,000 restarts", "quote": "Restart Capability 10,000 times", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml" } ] }, { "part": "RCS cluster frames and thermal shields (x4)", "material": "Aluminum alloy casting (alloy not stated)", "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The frame was an aluminum-alloy casting, shaped like a hollow cylinder, to which the four thrusters were attached", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml", "profile": "aluminium", "mid": "aluminium", "function": "Aluminum cluster casting holding four thrusters, heater elements and plumbing" }, { "part": "RCS propellant tanks with flexible bladders", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Bell Aerosystems (tanks purchased by Grumman)", "quote": "Fuel and oxidizer were contained within flexible propellant tank bladders.", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml", "profile": null, "mid": null, "function": "Two fuel and two oxidizer tanks in systems A and B that expel propellant under zero gravity", "specs": [ { "label": "Tank source", "value": "Grumman provided the tanks, purchased from Bell", "quote": "Grumman would provide tanks (purchased from Bell), propellant lines, and the pressurization system.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" } ] }, { "part": "RCS helium tanks and isolation valves", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The helium tank outlet was sealed by parallel-connected, redundant helium-isolation explosive valves", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml", "profile": null, "mid": null, "function": "Helium supply, sealed by redundant explosive valves until the astronauts prepare the RCS" } ] }, { "assembly": "Guidance, navigation and control", "parts": [ { "part": "Inertial measurement unit (IMU) and inertial subsection", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The IMU, which continuously measured attitude and acceleration, was the primary LM inertial sensing device.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "profile": null, "mid": null, "function": "Primary LM inertial sensor measuring attitude and acceleration", "specs": [ { "label": "Inertial subsection contents", "value": "Navigation base, IMU, coupling data unit, pulse torque assembly, power and servo assembly, signal conditioner", "quote": "The ISS consisted of a navigation base, an inertial measurement unit (IMU), a coupling data unit, a pulse torque assembly", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" } ] }, { "part": "Navigation base", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The navigation base was a lightweight (~ 3 lb) mount that supported, in accurate alignment, the IMU, AOT, and an abort sensor assembly (ASA).", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "profile": null, "mid": null, "function": "Lightweight mount that holds the IMU, optical telescope and abort sensor assembly in alignment" }, { "part": "Alignment optical telescope (AOT)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The AOT and a computer control and reticle dimmer (CCRD) assembly comprised the OSS.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "profile": null, "mid": null, "function": "Sighting telescope used to align the inertial platform on stars", "specs": [ { "label": "Line of sight", "value": "Fixed in elevation, movable in azimuth to six detent positions at 60 degree intervals", "quote": "The LoS was fixed in elevation and movable in azimuth to six detent positions at 60° intervals.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" } ] }, { "part": "Lunar module guidance computer (LGC, Block II Apollo Guidance Computer)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: MIT Instrumentation Laboratory (design)", "quote": "The Block II AGCs became known as the command module computer (CMC) and lunar module guidance computer (LGC).", "source_url": "https://enginehistory.org/Rockets/RPE09.50/RPE09.50.shtml", "profile": null, "mid": null, "function": "Digital computer that aligns the platform, runs guidance and commands engines, radars and RCS", "specs": [ { "label": "Memory", "value": "36,864 words fixed and 2,048 words erasable", "quote": "Both fixed and erasable memory sizes were increased to 36,864 and 2,048 words.", "source_url": "https://enginehistory.org/Rockets/RPE09.50/RPE09.50.shtml" }, { "label": "Role", "value": "Aligns the stable platform and positions both radar antennas", "quote": "The LGC aligned the stable platform and positioned both radar antennas.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" }, { "label": "Design origin", "value": "MIT Instrumentation Laboratory Apollo Guidance Computer", "quote": "the Massachusetts Institute of Technology Instrumentation Laboratory (MIT/IL) Apollo Guidance Computer, which was used to navigate from the earth to the moon and back", "source_url": "https://enginehistory.org/Rockets/RPE09.50/RPE09.50.shtml" } ] }, { "part": "Display and keyboard (DSKY)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The DSKY allowed the astronaut to load information into the LGC, retrieve and display information contained in the LGC", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "profile": null, "mid": null, "function": "Astronaut interface to the LGC, on panel 4 above the forward hatch" }, { "part": "Abort guidance section (ASA, AEA, DEDA)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The AGS consisted of an abort sensor assembly (ASA), abort electronics assembly (AEA), and a data entry and display assembly (DEDA).", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "profile": null, "mid": null, "function": "Strapped-down backup guidance for aborts: sensor assembly, 4,096-word computer and data entry panel", "specs": [ { "label": "Computer", "value": "General-purpose 4,096-word digital computer", "quote": "The AEA was a general-purpose, high-speed, 4,096 word digital computer", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" }, { "label": "Inertial type", "value": "Strapped to the LM rather than on a gimbaled stable platform", "quote": "The AGS was an inertial system rigidly strapped to the LM rather than mounted on a gimbaled stabilized platform.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" } ] }, { "part": "Control electronics section (CES)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "Functionally, this equipment was contained in a primary guidance and navigation section (PGNS), an abort guidance section (AGS), and a control electronics section (CES).", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "profile": null, "mid": null, "function": "Analog autopilot and attitude/translation control electronics tying controllers to the thrusters", "specs": [ { "label": "Abort path", "value": "The CES functions as an analog autopilot when the abort guidance path is selected", "quote": "The CES functioned as an analog autopilot when the abort guidance path was selected.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" } ] }, { "part": "Landing radar", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The landing radar (LR), located on the descent stage, provided altitude and velocity data during lunar descent.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "profile": null, "mid": null, "function": "Four-beam radar on the descent stage giving altitude and velocity during descent", "specs": [ { "label": "Beams", "value": "Three Doppler velocity beams and one FM altimeter beam", "quote": "The landing radar used four microwave beams: three, to measure velocity by Doppler shift continuous wave; one, to measure altitude by continuous-wave frequency modulation.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" }, { "label": "Frequencies", "value": "10.51 GHz velocity beams and a 9.58 GHz altimeter beam", "quote": "The antenna assembly transmitted 10.51 GHz velocity beams and a 9.58 GH altimeter beam to the lunar surface.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" }, { "label": "Antenna", "value": "Six planar arrays, two transmitting and four receiving, on a tilt mechanism beneath the descent stage", "quote": "The antenna consists of six planar arrays, two for transmission and four for reception.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" } ] }, { "part": "Rendezvous radar", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "The rendezvous radar, which operated in conjunction with a CSM transponder, acquired and tracked the CSM before and during rendezvous and docking.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml", "profile": null, "mid": null, "function": "Ascent-stage radar that tracks the CSM transponder for rendezvous and docking", "specs": [ { "label": "Signal", "value": "X-band three-tone phase-modulated continuous wave", "quote": "The CSM transponder received an X-band three-tone phase-modulated, continuous-wave signal from the rendezvous radar", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" }, { "label": "Range", "value": "Transponder gives about 400 nautical miles of range", "quote": "The transponder provided the long range (400 nm) required for the mission.", "source_url": "https://enginehistory.org/Rockets/RPE09.46/RPE09.46.shtml" } ] } ] }, { "assembly": "Environmental control", "parts": [ { "part": "Atmosphere revitalization section and lithium hydroxide canister", "material": "Lithium hydroxide (spare canister and PLSS cartridge)", "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Hamilton Standard Division of United Aircraft Corporation (ECS subcontractor)", "quote": "Atmosphere revitalization section (ARS), which removed CO2, odors, particulates and excess water vapor from the oxygen environment", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": "lithium-hydroxide", "mid": "lithium-hydroxide", "function": "Removes CO2, odors, particulates and excess water vapor and controls cabin and suit temperature", "specs": [ { "label": "ECS subcontractor", "value": "Hamilton Standard Division of United Aircraft Corporation", "quote": "Hamilton Standard Division of United Aircraft Corporation, environmental control.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" }, { "label": "Spare canister", "value": "A cabinet left of the Commander holds a spare ECS lithium hydroxide canister", "quote": "contained a spare Environmental Control Subsystem (ECS) lithium hydroxide canister", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Oxygen supply and cabin pressure control section (four oxygen tanks)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Hamilton Standard Division of United Aircraft Corporation (ECS subcontractor)", "quote": "Two descent stage oxygen tanks provided oxygen during descent and lunar stay.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Stores gaseous oxygen for the atmosphere section; two descent-stage and two ascent-stage tanks", "specs": [ { "label": "Ascent stage tanks", "value": "Two ascent stage oxygen tanks used during ascent and CSM rendezvous", "quote": "Two ascent stage oxygen tanks were used during ascent and CSM rendezvous.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "label": "ECS subcontractor", "value": "Hamilton Standard Division of United Aircraft Corporation", "quote": "Hamilton Standard Division of United Aircraft Corporation, environmental control.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" } ] }, { "part": "Water management section", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Hamilton Standard Division of United Aircraft Corporation (ECS subcontractor)", "quote": "The water management section (WMS) supplied water for drinking, cooling, fire extinguishing, food preparation", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Supplies water for drinking, cooling, fire fighting and food, and refills the PLSS cooling tank", "specs": [ { "label": "ECS subcontractor", "value": "Hamilton Standard Division of United Aircraft Corporation", "quote": "Hamilton Standard Division of United Aircraft Corporation, environmental control.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" } ] }, { "part": "Heat transport section and sublimators (x2)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Hamilton Standard Division of United Aircraft Corporation (ECS subcontractor)", "quote": "The waste heat was rejected by two sublimators and transferred overboard.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Water-glycol loops carry heat to two sublimators that reject it to space", "specs": [ { "label": "ECS subcontractor", "value": "Hamilton Standard Division of United Aircraft Corporation", "quote": "Hamilton Standard Division of United Aircraft Corporation, environmental control.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" }, { "label": "Sublimator principle", "value": "Move excess heat out of the LM instead of transferring it to another medium", "quote": "The HTS sublimators, unlike heat exchangers, moved excess heat out of the LM rather than just transferring it to another medium.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] } ] }, { "assembly": "Electrical power", "parts": [ { "part": "Descent stage batteries (x5, silver-zinc)", "material": "Silver-zinc plates with potassium hydroxide electrolyte", "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Eagle-Picher Company", "quote": "Each of the five identical descent stage batteries was composed of silver-zinc plates with a potassium hydroxide electrolyte.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": "silver-zinc-battery", "function": "Primary power from T-30 minutes; paralleled with the ascent batteries for powered descent", "specs": [ { "label": "Maker", "value": "Eagle-Picher Company of Joplin, Missouri", "quote": "The ascent and descent stage batteries were made by the Eagle-Picher Company of Joplin, Missouri.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "label": "Cells, mass and capacity", "value": "20 cells, 155 lb, 415 Ah each", "quote": "Each battery had 20 cells, weighed 155 lb, and had a 415-Ah capacity.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "Ascent stage batteries (x2, silver-zinc)", "material": "Silver-zinc", "form": null, "finish": null, "standard": null, "hardware_ref": "Supplier: Eagle-Picher Company", "quote": "The two identical silver-zinc batteries resided in the ascent stage.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": "silver-zinc-battery", "function": "Independent batteries enabled before lunar liftoff", "specs": [ { "label": "Mass and capacity", "value": "125 lb and 296 Ah each", "quote": "Each battery weighed 125 lb, and had a 296 Ah capacity.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] }, { "part": "400 Hz inverters (x2)", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "Two identical redundant 400-Hz inverters individually supplied the primary LM AC power.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml", "profile": null, "mid": null, "function": "Redundant 115 VAC supplies from 28 VDC" } ] }, { "assembly": "Communications and tracking", "parts": [ { "part": "S-band steerable and VHF in-flight antennas", "material": null, "form": null, "finish": null, "standard": null, "hardware_ref": null, "quote": "S-band steerable and VHF in-flight antennas", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf", "profile": null, "mid": null, "function": "Antennas on the ascent stage midsection structure for Earth and command module links", "specs": [ { "label": "Rendezvous radar and S-band antenna mounts", "value": "S-band and rendezvous radar antennas attach to the crew compartment exterior", "quote": "S-band and rendezvous radar antennas were attached to the crew compartment exterior.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" } ] } ] } ], "materials": [ { "id": "aluminium-2219", "name": "Aluminium alloy 2219", "material_page": null }, { "id": "aluminium-7075", "name": "Aluminium 7075-T6", "material_page": "https://spacemushroom.com/profiles/aluminium-7075/" }, { "id": "aluminium", "name": "Aluminum alloy casting (alloy not stated)", "material_page": "https://spacemushroom.com/profiles/aluminium/" }, { "id": "titanium", "name": "Titanium (alloy not stated)", "material_page": "https://spacemushroom.com/profiles/titanium/" }, { "id": "vycor-glass", "name": "Vycor annealed glass", "material_page": null }, { "id": "chemcor-glass", "name": "Chemcor tempered glass", "material_page": null }, { "id": "teflon-ptfe", "name": "Teflon", "material_page": null }, { "id": "aluminium-7075-t73", "name": "7075-T73 aluminum alloy", "material_page": null }, { "id": "fiberglass-cloth", "name": "Fibre-glass cloth", "material_page": null }, { "id": "nickel-foil-fiberfrax-composite", "name": "Nickel foil and Fiberfrax (alternating layers)", "material_page": null }, { "id": "aluminised-polyester-mylar", "name": "Aluminized Mylar insulation in the vacuum space between tank and jacket", "material_page": null }, { "id": "aluminised-polyimide-h-film", "name": "Aluminized polyimide film (H-film / Kapton)", "material_page": null }, { "id": "inconel", "name": "Inconel, Inconel mesh and nickel foil", "material_page": null }, { "id": "nickel-foil", "name": "Nickel foil", "material_page": null }, { "id": "elastomeric-silicone-seal", "name": "Elastomeric silicone compound", "material_page": null }, { "id": "velcro", "name": "Nonflammable Velcro pile", "material_page": null }, { "id": "aluminium-honeycomb", "name": "Aluminum honeycomb (alloy not stated)", "material_page": null }, { "id": "titanium-6al-4v", "name": "6Al-4V titanium alloy forgings (printed '6A1-4V')", "material_page": null }, { "id": "silica-phenolic-ablative", "name": "Silica cloth/phenolic ablative with needle-felted silica mat/phenolic insulation", "material_page": null }, { "id": "columbium-alloy-c-103", "name": "Columbium (niobium) alloy C-103 with an aluminide coating", "material_page": null }, { "id": "lithium-hydroxide", "name": "Lithium hydroxide (spare canister and PLSS cartridge)", "material_page": "https://spacemushroom.com/profiles/lithium-hydroxide/" }, { "id": "silver-zinc-battery", "name": "Silver-zinc", "material_page": null } ], "standards": [ "NASA TN D-7084 (Weiss, 1973)", "NASA TN D-6844 (Taylor, 1972)" ], "relations": [ { "type": "launched_on", "target": "Saturn V (Apollo 11 LM-5 launch vehicle)", "target_slug": "nasa-saturn-v", "note": "Apollo 11's LM-5 launched on a Saturn 5 (NSSDC)", "quote": "Launch Vehicle: Saturn 5", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1969-059C" }, { "type": "launched_on", "target": "Saturn IB (Apollo 5 / LM-1)", "target_slug": null, "note": "The first LM test flight (uncrewed LM-1, AS-204) launched on a Saturn IB", "quote": "Launch Vehicle: Saturn 1B", "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1968-007A" }, { "type": "launched_on", "target": "F-1 engine", "target_slug": "nasa-rocketdyne-f-1", "note": "Five on the Saturn V S-IC first stage; Saturn V first-stage engines under the stack that carried the LM; launcher engine, not carried by the vehicle", "quote": "Note that each F-1 engine produced 1.5 M lbT", "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml" }, { "type": "launched_on", "target": "J-2 engine", "target_slug": "rocketdyne-j-2", "note": "Five on the Saturn V S-II second stage; Saturn V second-stage engines; launcher engine, not carried by the vehicle", "quote": "The S-II second stage, using five J-2 engines burning liquid hydrogen (LH2) and LOX", "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml" }, { "type": "launched_on", "target": "J-2 engine", "target_slug": "rocketdyne-j-2", "note": "One restartable engine on the S-IVB; Saturn V third-stage engine; launcher engine, not carried by the vehicle", "quote": "The S-IVB, with a single J-2 LH2/LOX engine producing 230,000 lbT", "source_url": "https://enginehistory.org/Rockets/RPE08.00/RPE08.00.shtml" }, { "type": "launched_on", "target": "H-1 engine", "target_slug": null, "note": "Eight on the Saturn IB S-IB first stage; Saturn IB first-stage engines for the LM-1 flight; launcher engine, not carried by the vehicle", "quote": "Eight Rocketdyne H-1b engines burning RP-1 and LOX provided 1,852,822 lbT", "source_url": "https://enginehistory.org/Rockets/RPE07/RPE07.shtml" }, { "type": "carries", "target": "Lunar Module Descent Engine (LMDE)", "target_slug": "grumman-lunar-module-descent-engine", "note": "TRW; one throttleable 9,850 to 10,500 lbf engine in the descent stage", "quote": "The TRW Lunar Module Descent Engine (LMDE, VTR-10) was a pressure-fed, variable thrust, gimbaling, liquid-propellant rocket engine", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "type": "carries", "target": "Lunar Module Ascent Engine", "target_slug": null, "note": "Rocketdyne/Bell, designation RS-1801; one 3,500 lbf fixed-thrust engine in the ascent stage midsection", "quote": "The LMAE was installed in the ascent stage midsection", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml" }, { "type": "carries", "target": "R-4D engine", "target_slug": null, "note": "Reaction control thruster, Marquardt; sixteen 100 lbf thrusters in four ascent-stage clusters", "quote": "The R-4D RCS thrusters, supplied by the Marquardt Corporation of Van Nuys, California", "source_url": "https://enginehistory.org/Rockets/RPE09.45/RPE09.45.shtml" }, { "type": "carries", "target": "Lunar Roving Vehicle", "target_slug": "boeing-lunar-roving-vehicle", "note": "Stowed in descent stage quad 3 on the later (J) missions", "quote": "The quad No. 3 contained the lunar roving vehicle (LRV) and the Lunar Retro-Ranging Reflector.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "type": "supplied_by", "target": "Grumman (prime contractor)", "target_slug": null, "note": "Designed and built the lunar module", "quote": "The Grumman lunar module (LM) was an exquisite, complicated, ingenious, miraculous, complete spacecraft", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "type": "supplied_by", "target": "TRW (Space Technology Laboratories)", "target_slug": null, "note": "Descent engine developer selected by NASA and Grumman", "quote": "Shea and Contracting Officer James L. Neal then directed Grumman to proceed with STL.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" }, { "type": "supplied_by", "target": "Rocketdyne Division of North American Rockwell", "target_slug": null, "note": "Ascent engine injector and final assembly", "quote": "Rocketdyne was responsible for the injector and final assembly but Bell had the valves and thrust chamber.", "source_url": "https://enginehistory.org/Rockets/RPE09.44/RPE09.44.shtml" }, { "type": "supplied_by", "target": "Bell Aerosystems Company", "target_slug": null, "note": "Ascent engine development; Bell also supplied the valves, thrust chamber and RCS tanks", "quote": "During the spring of 1963, Grumman hired Bell to develop the ascent engine", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" }, { "type": "supplied_by", "target": "The Marquardt Corporation", "target_slug": null, "note": "100 lbf reaction control thrusters", "quote": "Grumman chose Marquardt to build the lunar module's third engine system, the small 100-pound-thrust attitude control thrusters.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" }, { "type": "supplied_by", "target": "Hamilton Standard Division of United Aircraft Corporation", "target_slug": null, "note": "Environmental control subsystem", "quote": "Hamilton Standard Division of United Aircraft Corporation, environmental control.", "source_url": "https://web.archive.org/web/2020/https://www.hq.nasa.gov/office/pao/History/SP-4205/ch6-5.html" }, { "type": "supplied_by", "target": "Eagle-Picher Company", "target_slug": null, "note": "Ascent and descent stage silver-zinc batteries", "quote": "The ascent and descent stage batteries were made by the Eagle-Picher Company of Joplin, Missouri.", "source_url": "https://enginehistory.org/Rockets/RPE09.40/RPE09.40.shtml" }, { "type": "supplied_by", "target": "Wah Chang Company", "target_slug": null, "note": "Columbium nozzle extension of the descent engine", "quote": "The Wah Chang Company supplied the very thin columbium nozzle and coatings.", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "type": "supplied_by", "target": "Bendix Commercial Vehicle Systems", "target_slug": null, "note": "Descent engine throttle valve actuator", "quote": "The throttle valve actuator, built by Bendix Commercial Vehicle Systems", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "type": "supplied_by", "target": "AiResearch Manufacturing Co. (Garrett Corporation)", "target_slug": null, "note": "Descent engine gimbal drive actuators (and the supercritical helium tanks)", "quote": "The gimbal drive actuators, built by Airesearch Mfg. Company of Los Angeles, California", "source_url": "https://enginehistory.org/Rockets/RPE09.42/RPE09.42.shtml" }, { "type": "supplied_by", "target": "Sargent Industries (Airite Division)", "target_slug": null, "note": "Later descent propellant tanks and ascent helium tanks", "quote": "which was stored in two identical tanks that were made by Sargent Industries, Airite Division, El Segundo, California", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml" }, { "type": "supplied_by", "target": "General Motors Allison Division", "target_slug": null, "note": "Initial descent propellant tanks", "quote": "initially built by the General Motors Allison Division of Indianapolis, Indiana", "source_url": "https://enginehistory.org/Rockets/RPE09.41/RPE09.41.shtml" }, { "type": "supplied_by", "target": "Aerojet General Corporation (Downey plant)", "target_slug": null, "note": "Ascent propellant tanks", "quote": "The APS oxidizer and fuel tanks, built by the Aerojet General Corporation Downey Plant in Downey, California", "source_url": "https://enginehistory.org/Rockets/RPE09.43/RPE09.43.shtml" }, { "type": "supplied_by", "target": "MIT Instrumentation Laboratory", "target_slug": null, "note": "Apollo Guidance Computer design used as the LM guidance computer", "quote": "the Massachusetts Institute of Technology Instrumentation Laboratory (MIT/IL) Apollo Guidance Computer, which was used to navigate from the earth to the moon and back", "source_url": "https://enginehistory.org/Rockets/RPE09.50/RPE09.50.shtml" } ], "not_published": "Alloys for tanks (descent and ascent propellant, oxygen, helium), landing-gear honeycomb cartridges, the cabin pressure hatch and the ascent/descent engines were not found in the sources read. 2014-series alloy was not found. The Kapton grade is given only as 'polyimide film (H-film)'. Layer counts differ between LM units and sources; the 25-layer blanket is the 'basic design' per TN D-6844. Quotes from OCR text of the NASA PDFs, with OCR spacing corrected. Mass is for Apollo 11 LM-5 only; later J-mission LMs were heavier (not checked). More detail: Not found in public sources that could be fetched: the manufacturers of the lunar module guidance computer, abort guidance system, landing radar and rendezvous radar (secondary sources name TRW for the abort guidance system and Raytheon for the computer, but no primary page with a quotable statement was reached), the S-band and VHF antenna makers, the waste-management and window-heater hardware, and the builders of the landing gear struts and footpads. Materials stated only for the parts listed: titanium propellant tanks, 6Al-4V titanium and silica-phenolic descent engine chamber, columbium C-103 nozzle, 7075-T73 gimbal frame, aluminum-honeycomb strut cartridges and footpads, aluminized Mylar helium-tank insulation, Velcro deck pile, silicone hatch seals and silver-zinc batteries; thruster body, ascent engine chamber and tank alloys are not given. Tank, hatch and radar quotes from the Grumman Apollo News Reference (LM04) and NASA SP-4205 are taken from Wayback Machine copies of hq.nasa.gov pages because the ALSJ PDFs now return 404; the enginehistory.org series (Part 9.40 to 9.46) is a secondary compilation of Grumman manuals and NASA Apollo Experience Reports that I used for most numbers. enginehistory.org lists a gross LM weight of 46,100 lb in its particulars table, which does not agree with its own stage figures or the Apollo News Reference (about 36,100 lb); only the News Reference value is given. The descent engine maximum thrust appears as 9,850 lbf (enginehistory.org), 9,870 lbf (NASA SP-4205) and 10,500 lbf at full throttle in vacuum (enginehistory.org table); all are listed. No fetched source ties the A7L suit name to the lunar module, so no relation to nasa-apollo-a7l-spacesuit is given. The Apollo 11 Press Kit and Apollo Experience Report PDFs for the LM propulsion systems were not reachable as clean text, and the web search budget ran out before NASM object pages could be checked.", "depth": "partial", "photos": [ { "file": "products/context/grumman-apollo-lunar-module-1.jpg", "alt": "Apollo 17-era lunar surface view: distant Lunar Module on the Moon seen past the rover's umbrella-style high-gain antenna", "long": "Apollo 17-era lunar surface view: distant Lunar Module on the Moon seen past the rover's umbrella-style high-gain antenna and TV camera (Apollo 17 mission image, LM small in centre)", "kind": "product", "credit": "NASA Johnson Space Center (public domain, via Wikimedia Commons)", "license": "Public domain", "page_url": "https://commons.wikimedia.org/wiki/File:Apollo_16_lunar_module_%22Orion%22_photographed_from_distance_during_EVA_(as16-116-18678).jpg" }, { "file": "products/context/grumman-apollo-lunar-module-2.jpg", "alt": "Black and white photo of a Lunar Module with exposed electronics bay and thermal foil being lifted by a crane in a hangar", "long": "Black and white photo of a Lunar Module with exposed electronics bay and thermal foil being lifted by a crane in a hangar with technicians", "kind": "product", "credit": "NASA (public domain, via Wikimedia Commons)", "license": "Public domain", "page_url": "https://commons.wikimedia.org/wiki/File:Apollo_11_Lunar_Module_(48286345716).jpg" }, { "file": "products/context/grumman-apollo-lunar-module-3.jpg", "alt": "Apollo 11 Lunar Module Eagle ascent stage in lunar orbit with the Moon below and Earth in the distance", "long": "Apollo 11 Lunar Module Eagle ascent stage in lunar orbit with the Moon below and Earth in the distance", "kind": "product", "credit": "NASA / Apollo 11 (public domain, via Wikimedia Commons)", "license": "Public domain", "page_url": "https://commons.wikimedia.org/wiki/File:Earth,_Moon_and_Lunar_Module,_AS11-44-6643.jpg" } ], "context": { "size": [], "mass": [], "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" }