The Apollo Command and Service Module was the three-person spacecraft that flew NASA's Apollo missions.
nasa-apollo-command-service-module North American Aviation built the Command and Service Module for NASA. It carried three astronauts to lunar orbit and back. Only the command module, which held the crew, returned to Earth, and each flight ended in a splashdown. The cabin air was pure oxygen at 5 pounds per square inch.
The command module has two walls. Its inner cabin is aluminium honeycomb, a cellular core sandwiched between aluminium sheets. The outer shell is the same idea in stainless steel, covered with an ablative coating. The service module carried the fuel cells, the main propulsion system and tanks of very cold hydrogen and oxygen.
Apollo CSM carried three astronauts to lunar orbit and back. The command module returned at lunar-return speed, so its stainless steel honeycomb shell and ablative coating are a landmark case of reentry heat shield design.
The inner pressure shell around the crew is aluminium honeycomb between aluminium alloy sheets. The outer shell is stainless steel honeycomb between stainless steel sheets, and it carries the heat shield. That is Avcoat 5026-39/HC-G, a low-density glass-filled epoxy-novolac resin held in honeycomb.
The command module had reaction control thrusters for turning the spacecraft. Their fuel and oxidiser tanks were titanium, each with a Teflon bladder to push the propellant out. The thruster chambers combined ablative parts, asbestos and a fibreglass wrap.
The service module's frame included solid aluminium alloy radial beams, machined into shape. The outer panels, 1 inch thick, were aluminium honeycomb between two aluminium sheets. The VHF antennas, shaped like scimitars, were stainless steel.
Three fuel cell power plants supplied the primary electrical power. Spherical tanks held very cold oxygen and hydrogen. The oxygen tanks were made of Inconel and the hydrogen tanks of titanium.
The command module's inner pressure shell and the service module's outer panels, between aluminium sheets.
The honeycomb and sheets of the command module's outer shell, and the service module's VHF antennas.
The ablative heat shield material, a low-density glass-filled epoxy-novolac held in honeycomb.
The command module's helium, fuel and oxidiser tanks, and the service module's hydrogen tanks.
Bladders inside the command module's propellant tanks, used to push the propellant out.
A layer in the thrust chambers of the command module's thrusters, beside an ablative sleeve and a fibreglass wrap.
Apollo 7, the first crewed flight, launched on 11 October 1968 on a Saturn IB. Bell Aerosystems of Buffalo, New York, made the command module's propellant tanks. Beech Aircraft of Boulder, Colorado, built the service module's oxygen tanks, and Air Products & Chemical built its hydrogen tanks.
Service propulsion engine, Aerojet-General; one 20,500 lbf main engine in the service module
Reaction control engine, Marquardt; sixteen ~100 lbf engines in four service module quads
Reaction control engine, Rocketdyne; twelve ablative ~93 lbf command module engines
Lockheed Propulsion Co.; 138,300 lbf solid rocket on the escape tower
Lockheed Propulsion Co.; 2,420 lbf solid rocket on the escape tower
Tower jettison motor, Thiokol; 31,500 lbf solid rocket on the escape tower
Apollo 7, the first crewed Apollo flight, launched on a Saturn IB
Rocketdyne, Division of North American Aviation
Five on the Saturn V S-IC first stage; Saturn V first-stage engines; launcher engine, not carried by the vehicle
Rocketdyne
Five on the Saturn V S-II second stage; Saturn V second-stage engines; launcher engine, not carried by the vehicle
One restartable engine on the S-IVB; Saturn V third stage and Saturn IB second stage engine; launcher engine, not carried by the vehicle
Eight on the Saturn IB S-IB first stage; Saturn IB first-stage engines; launcher engine, not carried by the vehicle
NASA
Same three-element layout (launch abort system, crew module, service module); the catalog already links the Avcoat heat shield heritage
Aerojet Rocketdyne
Valve-level heritage only: a NASA technology contract to improve the Apollo SPS bipropellant valve fed the OMS valve design (the 1985 paper says the results were used to design the OMS valve)
Prime contractor; built the command and service modules
Service propulsion engine and gimbal actuators
Service module R-4D reaction control engines
Command module SE-8 reaction control engines
Launch escape motor and pitch control motor
Tower jettison motor TE-M-380
Three fuel cell power plants
Inconel cryogenic oxygen tanks
Titanium cryogenic hydrogen tanks
SPS helium tanks and SM RCS helium tanks
SPS titanium propellant tanks
Command module and service module RCS propellant tanks
Command module RCS helium tanks
Stabilization and control subsystem
Production and integration of the guidance and navigation system; IMU
Guidance and navigation design; computer designer
Built the command module computer
Optical subsystem
Most telecommunications components
Heat shield panels
Ablative heat shield coating
North American Rockwell built the spacecraft under a contract with NASA's Manned Spacecraft Center
Grumman / NASA
R-4D engine. Here: Reaction control engine, Marquardt; sixteen ~100 lbf engines in four service module quads. There: Reaction control thruster, Marquardt; sixteen 100 lbf thrusters in four ascent-stage clusters.
NASA
Titanium. Here: Helium tanks (2); Fuel tanks (2) and more. There: Outboard engine fairings and stabilization fins; Control pressure nitrogen bottle (2,200 cubic in) and more.
Aluminium. Here: Radial beams; Crushable ribs (x4) and more. There: S-IVB forward skirt, aft skirt, thrust structure and aft interstage.
Inconel. Here: Cryogenic oxygen tanks; Q-ball instrument package and Inconel nose cone. There: Q-ball and nose cone.
fiberglass. Here: Thruster outer wrap. There: Boost protective cover.
Impregnated fiberglass, honeycomb-cored laminated fiberglass and cork layers. Here: Boost protective cover. There: Thrust structure heat shield.
Silver oxide-zinc. Here: Silver oxide-zinc batteries in the command module (x5). There: Flight batteries (x4 zinc-silver oxide); Flight batteries (x4 zinc/silver-oxide) and more.
Grumman / NASA
Titanium. Here: Helium tanks (2); Fuel tanks (2) and more. There: Some brackets and fasteners (lunar module); Descent-stage hot-area structure and more.
Aluminium. Here: Radial beams; Crushable ribs (x4) and more. There: Cabin front-face, RCS cluster trusses, decks and bulkheads; Micrometeoroid shield and more.
aluminum honeycomb between aluminum alloy sheets. Here: Inner pressure shell (crew compartment); Sector and RCS exterior panels (1 in thick). There: Primary struts with crushable aluminum-honeycomb cartridge; Footpads (x4, aluminum honeycomb).
Inconel. Here: Cryogenic oxygen tanks; Q-ball instrument package and Inconel nose cone. There: Plume-exposed shield areas; RCS plume deflector.
Silver oxide-zinc. Here: Silver oxide-zinc batteries in the command module (x5). There: Descent stage batteries (x5, silver-zinc); Ascent stage batteries (x2, silver-zinc).
Boeing
Titanium. Here: Helium tanks (2); Fuel tanks (2) and more. There: Tread chevrons; Inner frame (MESH-1 prototype wheel; flight material not stated).
Aluminium. Here: Radial beams; Crushable ribs (x4) and more. There: Hub and wheel disc (MESH-1 prototype wheel).
fiberglass. Here: Thruster outer wrap. There: Fenders.
Silver oxide-zinc. Here: Silver oxide-zinc batteries in the command module (x5). There: Batteries (2).
NASA Goddard Space Flight Center
Titanium. Here: Helium tanks (2); Fuel tanks (2) and more. There: Propellant tanks (2); Instrument mounting flexures.
Aluminium. Here: Radial beams; Crushable ribs (x4) and more. There: Primary structure (heating/cooling panel, edge members, fittings, brackets); Optical-bench heater aluminum tape and more.
aluminum honeycomb between aluminum alloy sheets. Here: Inner pressure shell (crew compartment); Sector and RCS exterior panels (1 in thick). There: Iso-thermal panel with embedded heat pipes.
Steel framing and tubing. Here: Crew couch frames (x3); Couch shock-attenuating struts (x8). There: Battery cell can.
NASA
Titanium. Here: Helium tanks (2); Fuel tanks (2) and more. There: Heat shield skeleton.
Aluminium. Here: Radial beams; Crushable ribs (x4) and more. There: Pressure vessel (seven large pieces, friction-stir welded); Backbone assembly (floor structure) and more.
aluminum honeycomb between aluminum alloy sheets. Here: Inner pressure shell (crew compartment); Sector and RCS exterior panels (1 in thick). There: CFRP sandwich panel core.
Avcoat 5026-39/HC-G. Here: Ablative heat shield material. There: Heat shield ablator (186 blocks).
TRW
Titanium. Here: Helium tanks (2); Fuel tanks (2) and more. There: Ablative-lined case to 16:1; Structural shield and more.
stainless steel honeycomb between stainless steel sheets. Here: Outer shell (heat shield structure); VHF scimitar antennas and more. There: Pintle tip, original; Flow-control valve bellows and more.
Columbium. Here: SPS nozzle extension. There: Pintle tip, qualification version.
fiberglass. Here: Thruster outer wrap. There: Radiation heat shield spacer.
The alloys of the face sheets and honeycomb cores are not named, and neither is the window glass. The main engine, fuel cells, parachutes and insulation have no published materials. Published lengths for the service module differ slightly.
What is written above is built from these numbers and quotes. Each row links to the page it was taken from. Get all of it as JSON, or ask our MCP server.
| What | Value |
|---|---|
| Crew | Three astronauts |
| First crewed flight | Apollo 7, launched 11 October 1968 on a Saturn IB |
| Cabin atmosphere | 100 percent oxygen at 5 psi |
| Habitable volume | 210 cubic feet |
| Service module size and mass | 24 ft 2 in long, 12 ft 10 in diameter, 55,000 lb loaded |
| Apollo spacecraft stack height | 82 ft |
| Service module height and mass (ASME landmark record) | 24 ft 9 in tall, 12 ft 10 in diameter, 54,160 lb launch weight |
| Mission duration | 8 to 10 days from launch to Earth landing |
| Cabin air temperature in flight | 70 to 75 F |
| Crew supplies carried | Items for up to 14 days |
| Parachute splashdown speed | 32 ft/s with three main parachutes, 36 ft/s with two |
| Entry heating and speed | About 24,500 mph at entry, heating up to 5,000 F at the aft heat shield |
| Production contract scope | 49 manned or test spacecraft (command and service modules) |
| Prime contract value (3 Feb 1968) | About 2,996,000,000 US dollars |
| CM RCS thrust per engine | About 93 lbf |
| SPS specific impulse | 314 s |
| SPS thrust-vector range | About plus/minus 10 deg (Z) and plus/minus 6 deg (Y) |
| Fuel cell redundancy | Three plants normally run; two are sufficient to complete the mission |
| Cryogenic oxygen tank size | 26 in diameter, 326 lb each |
| Cryogenic hydrogen tank size | 31.75 in diameter, about 29 lb each |
Each material named in the sources: where it is used here, which other products use it, and its key numbers when its material page exists.
Used in 8 partsHelium tanks (2) · Fuel tanks (2) · Oxidizer tanks (2) · +5 more
Used in 4 partsRadial beams · Crushable ribs (x4) · Command module computer (Block II Apollo Guidance Computer) · +1 more
Used in 4 partsOuter shell (heat shield structure) · VHF scimitar antennas · CM-SM tension ties (x3) and compression pads (x6) · +1 more
Used in 2 partsInner pressure shell (crew compartment) · Sector and RCS exterior panels (1 in thick)
Used in 2 partsCryogenic oxygen tanks · Q-ball instrument package and Inconel nose cone
Used in 2 partsCrew couch frames (x3) · Couch shock-attenuating struts (x8)
Used in 1 partFuel cell electrolyte
Used in 1 partWindow outer panes (x5 windows)
Used in 1 partNavigation base
Used in 1 partThruster thrust-chamber insulation
Used in 1 partAblative heat shield material
Used in 1 partInertial measurement unit (IMU)
Used in 1 partLaunch escape tower rubber insulation
Used in 1 partR-4D nozzle extension
Used in 1 partSPS nozzle extension
Used in 1 partThruster outer wrap
Used in 1 partBoost protective cover
Used in 1 partSPS ablative thrust chamber
Used in 1 partBallast compartment (lead and depleted uranium weights)
Used in 1 partMain parachutes (x3)
Used in 1 partSilver oxide-zinc batteries in the command module (x5)
Used in 1 partPropellant bladders
Used in 1 partWindow inner panes (x5 windows)
Used in 1 partR-4D thrust chamber
Command module shells and the heat shield material, plus several RCS and service module parts, have stated materials from the ASME landmark record and EngineHistory.org. Components, suppliers and links were added from public sources. A material is left blank where no source states it.
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Inner pressure shell (crew compartment)“The inner pressurized shell was aluminum honeycomb between aluminum alloy sheets.” | aluminum honeycomb between aluminum alloy sheetsaluminium-honeycomb | — | — |
| Outer shell (heat shield structure)“The outer shell was stainless-steel honeycomb between stainless-steel sheets.” | stainless steel honeycomb between stainless steel sheetsstainless-steel | — | — |
| Ablative heat shield material“a low-density glass-filled epoxy-novolac system designated Avcoat 5026-39/HC-G” | Avcoat 5026-39/HC-Gavcoat | — | — |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Radial beams“The solid aluminum alloy radial beams were machined” | solid aluminum alloyaluminium | — | — |
| Sector and RCS exterior panels (1 in thick)“made of aluminum honeycomb core between two aluminum face sheets” | aluminum honeycomb core with aluminum face sheetsaluminium-honeycomb | — | — |
| Cryogenic oxygen tanks“The Inconel oxygen tanks, built by Beech Aircraft of Boulder, Colorado” | Inconel (alloy not stated)inconel | — | — |
| Cryogenic hydrogen tanks“The titanium hydrogen tanks, built by Air Products & Chemical Co.” | titaniumtitanium | — | — |
| VHF scimitar antennas“Made of stainless steel they were about 13.5” | stainless steelstainless-steel | — | — |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Launch escape motor (solid rocket)Lifts the command module away from a failing launch vehicle on the pad or in first-stage flight“The launch escape motor, built by the Lockheed Propulsion Co. of Redlands, California” | Not said | — | Supplier: Lockheed Propulsion Co. |
| Pitch control motor (solid rocket)Steers the escape path away from the launch vehicle toward the ocean in a low-altitude abort“The pitch control motor pushed the LES and CM toward the Atlantic Ocean and away from the LV during a low-altitude abort.” | Not said | — | Supplier: Lockheed Propulsion Co. |
| Tower jettison motor TE-M-380Pulls the escape tower and boost cover clear of the command module after a normal launch“The TE-M-380 tower jettison motor was used in all missions to jettison the LES.” | Not said | — | Supplier: Thiokol Chemical Corp. |
| Launch escape tower (welded titanium truss)Truss that carries the escape motors above the command module on four legs“The launch escape tower was a welded titanium tubing truss structure” | Titanium tubing (alloy not stated)titanium | — | — |
| Launch escape tower rubber insulationProtects the tower tubing from the rocket motor exhaust“were covered with Buna -N rubber insulation, which protected it from the rocket motor exhaust” | Buna-N rubberbuna-n-rubber | — | — |
| Boost protective coverFiberglass-and-cork shroud that shields the command module from launch heating and motor exhaust“Impregnated fiberglass, honeycomb-cored laminated fiberglass, and cork layers comprised the boost protective cover's structure.” | Impregnated fiberglass, honeycomb-cored laminated fiberglass and cork layersfiberglass-honeycomb | — | — |
| Canards (x2)Two clamshell control surfaces that turn the command module heat-shield-first during an abort“The canards were two metallic clamshell aerodynamic control surfaces” | Not said | — | — |
| Q-ball instrument package and Inconel nose coneQ-ball senses angle of attack and dynamic pressure for abort decisions; the cone caps the escape system“The Inconel nose cone was 13.37" long” | Inconel (alloy not stated)inconel | — | — |
| Ballast compartment (lead and depleted uranium weights)Tapered compartment that keeps the escape system stable at all speeds and modes“a tapered ballast compartment contained lead and depleted uranium weights” | Lead and depleted uranium weightslead-depleted-uranium-ballast | — | — |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Forward heat shield with release mechanismCovers the apex and earth landing equipment; jettisoned during entry to free the parachutes“At about 25,000 feet during entry, the forward heat shield is jettisoned to expose the earth landing equipment” | Not said | — | — |
| Aft heat shieldThickest part of the heat shield; faces forward through entry and carries the highest heating“The command module enters the atmosphere with its base down; this is covered by the aft heat shield which is the thickest portion.” | Not said | — | Supplier: Aeronca Manufacturing Co. (panels); Avco Corp. (ablative coating) |
| Crushable ribs (x4)External impact-attenuation ribs in the aft compartment that hit the water first“The ribs are made of bonded laminations of corrugated aluminum which absorb energy by collapsing upon themselves at impact.” | Bonded laminations of corrugated aluminumaluminium | — | — |
| Crew couch frames (x3)Support the three crew; can be adjusted so the crew can stand and move around“The couches were made of steel framing and tubing and covered with a heavy, fireproof fiberglass cloth.” | Steel framing and tubing (grade not stated), covered with fireproof fiberglass clothsteel-grade-unstated | — | — |
| Couch shock-attenuating struts (x8)Connect the couches to the structure and absorb landing impact“The internal portion of the system consists of eight struts which connect the crew couches to the CM” | Steel wire rings between an inner and outer piston (grade not stated)steel-grade-unstated | — | — |
| Side (unified crew) hatchSingle outward-opening hatch for entering and leaving the module“The side hatch is a single integrated assembly which opens outward” | Not said | — | — |
| Forward (docking) hatchPressure-and-ablative hatch at the top of the docking tunnel used for transfer to the lunar module“ablative hatch mounted at the top of the docking tunnel.” | Not said | — | — |
| Window outer panes (x5 windows)Single outer pane of each window“The outer windows are made of amorphous-fused silicon” | Amorphous fused silica glass (printed as 'silicon' in the source)fused-silica-glass | — | — |
| Window inner panes (x5 windows)Double inner panes of each window“The inner windows are made of tempered silica glass” | Tempered silica glasstempered-silica-glass | — | — |
| Lower equipment bay (navigation station)Largest equipment bay; holds guidance electronics, optics, computer and batteries“It is the navigation station and contains most of the guidance and navigation electronics” | Not said | — | — |
| CM-SM tension ties (x3) and compression pads (x6)Hold the command module on the service module until separation“three tension ties which extend from the CM's aft heat shield to six compression pads on the top of the SM” | Stainless steel straps (grade not stated)stainless-steel | — | — |
| Environmental control unit and oxygen surge tank (left-hand equipment bay)Key cabin environmental control hardware, with its displays and controls“including the environmental control unit, the oxygen surge tank, and displays and controls.” | Not said | — | — |
| Main display consoleSwitches and displays that let the crew control the spacecraft from their couches“The main display console contained the switches and displays that allowed astronauts to control the spacecraft while in their couches.” | Not said | — | — |
| Docking probe assemblyExtendable probe that soft-captures the LM drogue, then retracts to pull the vehicles together“The primary function of the docking probe assembly is to provide initial vehicle CSM/LM coupling and attenuate impact energy imposed by vehicle contact.” | Not said | — | — |
| Docking ring with 12 automatic latchesRing on the command module that mates with the lunar module tunnel ring and seals the interface“the LM tunnel ring will activate the 12 automatic docking ring latches on the CM and effect a pressure seal” | Not said | — | — |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| SM center section and six sectorsCenter section holds the engine and helium tanks; six sectors hold tanks, fuel cells and equipment“The SM consisted of a circular center section surrounded by six pie-shaped sectors.” | Not said | — | — |
| Space radiators: ECS (x2) and EPS (x8, in the forward fairing)Reject cabin, equipment and fuel cell waste heat through water-glycol tubes“Two large (30 ft²) ECS space radiators radiated CM cabin and equipment heat to the cold of space.” | Not said | — | — |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| SPS engine AJ10-137Main engine for mid-course corrections, lunar orbit insertion, return to Earth and post-tower abort“The SPS engine, built by the Aerojet General Corporation Space Propulsion Division of Sacramento, California” | Not said | — | Supplier: Aerojet-General Corporation |
| SPS injectorBaffled injector that distributes fuel and oxidizer; baffles added to stop combustion instability“The injector was baffled to enhance combustion stability.” | Not said | — | — |
| SPS ablative thrust chamberAblative and film-cooled combustion chamber with an aluminum flange at each end“The ablative thrust chamber consisted of laid-up ablative material with an aluminum flange at each end.” | Laid-up ablative material (hand-laid coated glass fiber in ablative epoxy) with aluminum end flangesglass-epoxy-ablative | — | — |
| SPS nozzle extensionRadiation-cooled bell that raises the expansion ratio to 62.5:1“The final nozzle was made of columbium to the 40:1 area ratio point and titanium to the end.” | Columbium (niobium) to the 40:1 area ratio point, titanium beyondcolumbium-niobium | — | — |
| SPS bipropellant valve assembly (eight ball valves)Series-parallel ball valves that guarantee engine start and shutdown with one actuator failed“Eight bipropellant ball valves distributed fuel and oxidizer to the engine injector assembly.” | Stainless steel valve balls with fiberglass-impregnated Teflon sealsstainless-steel | — | — |
| SPS thrust mount and gimbal actuatorsGimbal ring and dual electromechanical servo actuators that steer the engine“Dual sealed electromechanical servo actuators articulated the SPS engine for thrust vector control.” | Not said | — | Supplier: Aerojet-General Corporation |
| SPS helium tanks (x2)Spherical tanks holding the helium that pressurizes the propellant tanks“Two 40" diameter spherical helium tanks, manufactured by Sargent Industries of El Segundo, California” | Not said | — | Supplier: Sargent Industries |
| SPS propellant tanks (x4: fuel storage and sump, oxidizer storage and sump)Hold Aerozine 50 and nitrogen tetroxide for the main engine“The propellant subsystem consisted of two titanium fuel tanks (storage and sump) located in Sector 5, two titanium oxidizer tanks” | Titanium (alloy not stated)titanium | — | Supplier: General Motors Allison Division |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| SM RCS thrusters (x16, Marquardt R-4D)Four quads of four engines for attitude control, translation, ullage and separation“Four Marquardt R-4D reaction control rocket engines were clustered on the quad exterior.” | Not said | — | Supplier: The Marquardt Corporation |
| R-4D thrust chamberRadiation-cooled combustion chamber; the only non-ablative engines on the command and service module“The combustion chamber was constructed of unalloyed molybdenum coated with molybdenum disilicide to prevent oxidation of the base metal.” | Unalloyed molybdenum coated with molybdenum disilicidemolybdenum | — | — |
| R-4D nozzle extensionRadiation-cooled nozzle skirt with integral stiffener rings“nozzle extensions were a cobalt-base alloy” | Cobalt-base alloy (grade not stated)cobalt-base-alloy | — | — |
| SM RCS helium tanks (x4, one per quad)Spherical titanium tank pressurizing each quad's propellant tanks“A spherical titanium helium tank, manufactured by the Airite Division of Sargent Industries, El Segundo, California” | Titanium (alloy not stated)titanium | — | Supplier: Airite Division of Sargent Industries |
| SM RCS propellant tanks (two fuel and two oxidizer per quad)Titanium tanks with Teflon bladders for positive expulsion“The cylindrical titanium fuel and oxidizer tanks had domed ends and were manufactured by Bell Aerosystems Company of Buffalo, New York.” | Titanium (alloy not stated)titanium | — | Supplier: Bell Aerosystems Company |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Fuel cell power plants (x3, Bacon-type)Primary DC power from hydrogen and oxygen; also supply drinking water“The fuel cell powerplants, built by Pratt & Whitney Aircraft of Hartford, Connecticut were 44" high, 22" in diameter, and weighed about 245 lb.” | Not said | — | Supplier: Pratt & Whitney Aircraft |
| Fuel cell electrolytePotassium hydroxide solution in each cell“Each power plant cell contained electrolyte consisting of 83% potassium hydroxide (KOH) and 17% water by weight.” | 83% potassium hydroxide, 17% water by weightpotassium-hydroxide-electrolyte | — | — |
| Silver oxide-zinc batteries in the command module (x5)Secondary power; three rechargeable batteries power entry and post-landing“Five silver oxide-zinc storage batteries were located in the CM lower equipment bay.” | Silver oxide-zincsilver-zinc-battery | — | — |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Unified S-band, VHF/AM and data equipmentVoice, data, TV, tracking and ranging links to Earth and the lunar module“Most of the components of the telecommunications subsystem are produced by the Collins Radio Co., Cedar Rapids, Iowa.” | Not said | — | Supplier: Collins Radio Co. |
| S-band high-gain antennas (x4)Deep-space Earth link, folded inside the adapter at launch“Four S-band high-gain antennas, mounted outside the SM aft bulkhead, were used for deep space communications.” | Not said | — | — |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Inertial measurement unit (IMU)Three-gimbal stable platform with gyros and accelerometers that senses attitude and velocity change“The IMU, manfactured by AC Electronics Division of General Motors, had a 12.6" diameter and weighed 42.5 lb.” | Beryllium stable memberberyllium | — | Supplier: AC Electronics Division, General Motors |
| Navigation baseRigid mount for the IMU and optics“weighed 17.4 lb, and was made of riveted and bonded preformed anodized aluminum alloy sheet” | Anodized aluminum alloy sheet, filled with polyurethane foamanodized-aluminium | — | Supplier: AC Electronics Division, General Motors |
| Optical subsystem (scanning telescope and sextant)Star and landmark sightings for navigation“It consisted of a navigation base, a scanning telescope, a sextant, and equipment to permit operation with the CMC and IGS.” | Not said | — | Supplier: Kollsman Instrument Co. |
| Command module computer (Block II Apollo Guidance Computer)Digital computer for guidance, navigation and engine commands“was 24" x 12.5" x 6" (0.97 ft³) gold-alodined aluminum alloy box that weighed 70.1 lb” | Gold-alodined aluminum alloy boxaluminium | — | Supplier: Raytheon Co. (built); MIT Instrumentation Laboratory (designed) |
| Display and keyboard (DSKY) panels (x2)Crew interface to the computer“The information display that resulted from computations, and the control of the computer by the astronauts was accomplished with two display-keyboard (DSKY) panels.” | Not said | — | — |
| Stabilization and control gyro assemblies (x2)Attitude gyros for the backup stabilization and control subsystem“Gyro Assemblies (Honeywell) – Two gyroscope assemblies, each 6.00" x 7.00" by 14.25" and weighing 22.44 lb” | Welded aluminum alloy enclosurealuminium | — | Supplier: Honeywell, Inc. |
| Rotation controls (x2), translation control and flight director attitude indicators (x2)Honeywell hand controllers and attitude displays of the stabilization and control subsystem“Rotation Controls (Honeywell) – Two identical three-axes rotation controls provided proportional rate command signals” | Not said | — | Supplier: Honeywell, Inc. |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Drogue parachutes (x2)Stabilize and slow the command module after forward heat shield jettison“Two 16.5-foot-diameter conical ribbon drogue parachutes are mortar-deployed” | Not said | — | — |
| Pilot parachutes (x3)Pull the main parachutes out of their packs“three 7.2-foot-diameter ringslot pilot parachutes” | Not said | — | — |
| Main parachutes (x3)Final descent canopies, each opening through two reefing stages“Each main parachute then inflates through two reefing stages to a full-open condition.” | Lightweight 1.1 oz nylon clothnylon | — | — |
| Uprighting flotation bags (x3)Inflate after splashdown to right the capsule“At splashdown, the crew jettisoned the main parachutes, deployed CM flotation bags to keep it upright” | Not said | — | — |
| VHF recovery antennas (x2) and flashing beaconDeployed after main parachute opening to help recovery forces find the capsule“Deploy the two VHF recovery antennas and the flashing beacon light.” | Not said | — | — |
| Part | Material | Finish and standard | Made by |
|---|---|---|---|
| Spacecraft-lunar module adapter (SLA)Aerodynamic enclosure for the LM and link to the launch vehicle; jettisoned after translunar injection“The SLA served as a smooth aerodynamic enclosure for the lunar module during boost” | Not said | — | — |
| Emergency detection system (EDS)Detects launch vehicle emergencies, displays them and can start an automatic abort“The emergency detection system (EDS) operated from LV umbilical separation until 100 seconds after liftoff.” | Not said | — | — |
Missing: face sheet and core alloys, window glass, service propulsion engine, fuel cell, parachute and insulation materials; standards. More detail: Not found in public sources that could be fetched: suppliers of the environmental control system, cabin fans and suit loop, waste management, food and water hardware, the launch escape and CM forward-compartment hardware beyond the motors, the parachute maker (Northrop Ventura appears in NASA TN D-7437 only as maker of a failed parachute link assembly, in a garbled appendix), the SLA builder, and the batteries and inverters. Materials not stated for most structures: the stated ones are titanium tower tubing, Buna-N insulation, Inconel nose cone, lead and depleted uranium ballast, fiberglass and cork boost cover, steel couch framing, silica window glass, molybdenum and cobalt-base R-4D parts, columbium and titanium SPS nozzle, stainless steel SPS valve balls, beryllium IMU stable member and nylon main parachute cloth. Conflicting values are listed side by side: boost protective cover 100 lb versus 700 lb, SPS thrust 20,000 versus 20,500 lbf, forward heat shield jettison 24,000 versus 25,000 ft, couch struts honeycomb versus steel wire rings, service module height 24 ft 2 in (existing entry) versus 24 ft 9 in (ASME). The Apollo 11 Press Kit and the Apollo Operations Handbook text were only readable as OCR; quotes come from cleaner enginehistory.org, NASA SP-4205 and Apollo News Reference chapters. No fetched source ties the A7L suit name to the command module, so no relation to nasa-apollo-a7l-spacesuit is given; the lunar module was not made a carries target because it docks rather than rides inside the CSM. The Apollo 11 Press Kit PDFs on nasa.gov returned 404 and the web search budget ran out before NASM object pages could be checked.
Maker credit: North American Aviation (Rockwell) for NASA. Collected from public pages and documents, checked 4 Nov 2026.
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