The Apollo spacecraft was composed of three parts designed to accomplish the American Apollo program's goal of landing astronauts on the Moon by the end of the 1960s and returning them safely to Earth. The expendable (single-use) spacecraft consisted of a combined Command/Service Module (CSM) and a Lunar Module (LM). Two additional components complemented the spacecraft stack for launch vehicle assembly: a Launch Escape System (LES) to be used only in the event of a launch emergency, and a Spacecraft/Lunar Module Adapter (SLA) designed to connect the CSM to the launch vehicle and to house the LM.
The design was based on the Lunar Orbit Rendezvous approach: two docked spacecraft were sent to the Moon and went into lunar orbit. While the LM separated and landed, the CSM remained in orbit. After the lunar excursion, the two craft rendezvoused and docked in lunar orbit, and the CSM returned the crew to Earth. The Command Module was the only part of the spacecraft that returned with the crew to the Earth's surface.
The LES was jettisoned during launch upon reaching the point where it was no longer needed, and the SLA remained attached to the launch vehicle's upper stage. Two unmanned CSM's, one unmanned LM and one manned CSM were carried into space by Saturn IB launch vehicles for low Earth orbit Apollo missions. Larger Saturn Vs launched two unmanned CSM's on high Earth orbit test flights, the CSM on one manned lunar mission, the complete spacecraft on one manned low Earth orbit mission and eight manned lunar missions. After conclusion of the Apollo program, four CSM's were launched on Saturn IBs for three Skylab Earth orbital missions and the Apollo-Soyuz Test Project.
Command/Service Module 
The major part of the Apollo spacecraft was a three-man vehicle designed for Earth orbital, translunar, and lunar orbital flight, and return to Earth. This consisted of a command module supported by a service module, built by North American Aviation (later North American Rockwell).
Command Module (CM) 
The Command Module, was the control center for the Apollo spacecraft and living quarters for the three crewmen. It contained the pressurized main crew cabin, crew couches, control and instrument panel, optical and electronic guidance systems, communications systems, environmental control system, batteries, heat shield, reaction control system, forward docking hatch, side hatch, five windows and the parachute recovery system. It was the only part of the Apollo/Saturn space vehicle that returned to Earth intact.
Service Module (SM) 
The Service Module was unpressurized and contained a main service propulsion engine and propellant to enter and leave lunar orbit, a reaction control system to provide attitude control and translational capability, fuel cells with hydrogen and oxygen reactants, radiators to dump waste heat into space, and a high gain antenna. The oxygen was also used for breathing, and the fuel cells produced water for drinking and environmental control. On Apollo 15, 16 and 17 it also carried a scientific instrument package, with a mapping camera and a small sub-satellite to study the moon.
A major portion of the service module was taken up by propellant and the main rocket engine. Capable of multiple restarts, this engine placed the Apollo spacecraft into and out of lunar orbit, and was used for mid-course corrections between the earth and the moon.
The Service Module remained attached to the Command Module throughout the mission. It was jettisoned just prior to reentry into the Earth's atmosphere.
Lunar Module (LM) 
The Lunar Module was a separate vehicle designed to land on the Moon and return to lunar orbit, and was the first true "spaceship" since it flew solely in the vacuum of space. It consisted of a descent stage and an ascent stage. It supplied life support systems for two astronauts for up to four to five days on the Apollo 15, 16 and 17 missions. The spacecraft was designed and manufactured by the Grumman Aircraft Company.
The descent stage contained the landing gear, landing radar antenna, descent rocket engine, and fuel to land on the moon. It also had several cargo compartments used to carry among other things, the Apollo Lunar Surface Experiment Packages ALSEP, the Modularized Equipment Transporter (MET) (a hand-pulled equipment cart used on Apollo 14), the Lunar Rover (Apollo 15, 16 and 17), surface television camera, surface tools, and lunar sample collection boxes.
The ascent stage contained the crew cabin, instrument panels, overhead hatch/docking port, forward hatch, optical and electronic guidance systems, reaction control system, radar and communications antennas, ascent rocket engine and fuel to return to lunar orbit and rendezvous with the Apollo Command and Service Modules.
Launch Escape System (LES) 
The Apollo launch escape system was built by the Lockheed Propulsion Company. Its purpose was to pull the Command Module (which contained the crew cabin) away from the launch vehicle in an abort. The emergency could be a pad fire, exploding launch vehicle or a launch vehicle going off course.
The Launch Escape System would work automatically (or through manual activation) to fire a solid fuel escape rocket and open a canard system to direct the Command Module away from, and off the path of, a launch vehicle in trouble. The Launch Escape System would then jettison and the Command Module would land with its parachute recovery system.
If the emergency happened on the launch pad, the Launch Escape System would lift the Command Module to a sufficient height to allow the recovery parachutes to deploy safely before coming in contact with the ground.
In the absence of an emergency, the LES was routinely jettisoned about 20 or 30 seconds after the launch vehicle's second-stage ignition. (Abort modes after this point would be accomplished without the LES.) The jettison motor was a separate solid fuel rocket manufactured by the Thiokol Chemical Company.
Major components of the Launch Escape System 
- Nose Cone and Q-Ball—The nosecone of the LES contained an array of 8 pressure-measuring pitot tubes in a structure known as the "Q-ball". These sensors were connected to the command module and Saturn launch vehicle guidance computers, allowing calculation of dynamic pressure (q) during atmospheric flight, and also the angle of attack in the event of an abort.
- Q-Ball cover—A styrofoam cover, removed a few seconds before launch, protected the pitot tubes from being clogged by debris. The cover was split in half vertically and held together by a 2-inch (51 mm) rubber band. A razor blade was positioned behind the rubber band, pinched between the halves of the cover. A wire rope was connected to the top and bottom of the razor blade and to both halves of the cover. The wire rope was routed through a pulley on the hammerhead crane at the top of the launch umbilical tower (LUT) down to a tube on the right side of the 360-foot (110 m) level of the LUT. The wire rope was connected to a cylindrical weight inside a tube. The weight rested on a lever controlled by a pneumatic solenoid valve. When the valve was actuated from the Launch Control Center (LCC), the pneumatic pressure of 600 PSI GN2 (nitrogen gas) rotated the lever down allowing the weight to drop down the tube. The dropping weight pulled the wire rope, which pulled the blade cutting the rubber band, and the wire rope pulled the halves of the cover away from the launch vehicle. The apparent overengineering of this simple system was due to the fact that the launch escape system, which depended on the Q-ball data, was armed 5 minutes before launch, so retraction of the Q-ball cover was a life-critical part of a possible pad abort.
- Canard Assembly and Pitch Motor—These worked in combination to direct the Command Module off a straight path and to the side during an emergency. This would direct the Command Module off the flight path of an exploding launch vehicle. It would also direct the Command Module to land off to the side of any launch pad fire and not in the middle of it.
- Tower Jettison Motor—A smaller solid fuel motor that jettisons the Launch Escape System after it is no longer needed. This usually happens after second stage ignition.
- Launch Escape Motor—The main solid fuel rocket motor that, firing through four rocket nozzles, pulls the Command Module rapidly away from a launch emergency.
- Launch Escape Tower—Assembly that attaches the Launch Escape System rocket motors to the Command Module.
- Boost Protective Cover—Hollow conical structure that fit over the Command Module during launch. It protected the Command Module heat shield and windows during ascent through the atmosphere. It also protected the Command Module from rocket exhaust should the Launch Escape System have to be used.
- Length minus BPC: 32 ft 6 in (9.92 m)
- Length with BPC: 39 ft 5 in (12.02 m)
- Diameter: 2 ft 2 in (0.66 m)
- Total mass: 9,200 pounds (4,200 kg)
- Thrust, 36,000 ft: 147,000 pounds-force (650 kN)
- Thrust, maximum: 200,000 pounds-force (890 kN)
- Burn time: 4.0 seconds
Abort tests 
- Pad Abort Test-1—Launch Escape System (LES) abort test from launch pad with Apollo Boilerplate BP-6.
- Pad Abort Test-2—LES pad abort test of near Block-I CM with Apollo Boilerplate B-23A.
- Little Joe II—In-air LES abort tests.
Spacecraft Lunar Module Adapter (SLA) 
The Spacecraft Lunar Module Adapter (SLA), built by North American Aviation (Rockwell), was a conical aluminum structure which supported the Service Module above the Saturn S-IVB rocket stage. It protected the Lunar Module (LM), the Service Propulsion System engine nozzle, and the launch vehicle to Service Module umbilical during launch and ascent through the atmosphere.
The SLA was composed of four fixed 7-foot-tall (2.1 m) panels bolted to the Instrument Unit on top of the S-IVB stage, which were connected via hinges to four 21-foot-tall (6.4 m) panels which would open from the top similar to flower petals.
The SLA was made from 1.7 inches (43 mm) thick aluminum honeycomb material. The exterior of the SLA was covered by a thin (0.03–0.2 inch or 0.76–5.1 millimetres) layer of cork and painted white to minimize thermal stresses during launch and ascent.
The Service Module was bolted to a flange at the top of the longer panels, and power to the SLA multiply redundant pyrotechnics was provided by an umbilical. Because a failure to separate from the S-IVB stage could leave the crew stranded in orbit, the separation system used multiple signal paths, multiple detonators and multiple explosive charges where the detonation of one charge would set off another even if the detonator on that charge failed to function.
Once in space, the astronauts pressed the 'CSM/LV Sep' button on the control panel to separate the Command and Service Module (CSM) from the launch vehicle. Detonating cord was ignited around the flange between the Service Module and SLA, and along the joints between the four SLA panels, releasing the Service Module and blowing apart the connections between the panels. Dual-redundant pyrotechnic thrusters at the lower end of the SLA panels then fired to rotate them around the hinges at 30-60 degrees per second.
On all flights through Apollo 7, the SLA panels remained hinged to the S-IVB and opened to a 45 degree angle, as originally designed. But as the Apollo 7 crew practiced rendezvous with the S-IVB/SLA containing a dummy docking target, concerns surfaced about the possibility of collision between the spacecraft and the SLA panels during docking and extraction of the Lunar Module in a lunar mission. This led to a redesign using a spring-loaded hinge release system which released the panels at the 45 degree angle and pushed them away from the S-IVB at a velocity of about five miles per hour, putting them a safe distance away by the time the astronauts pulled the Command/Service Module away, rotated it through 180 degrees, and came back for docking.
The Lunar Module was connected to the SLA at four points around the lower panels. After the astronauts docked the CSM to the LM, they blew charges to separate those connections and a guillotine severed the LM to Instrument Unit umbilical. After the charges fired, springs pushed the LM away from the S-IVB and the astronauts were free to continue their trip to the Moon.
- Height: 28 ft (8.5 m)
- Apex Diameter: 12 ft 10 in (3.9 m) Service Module end
- Base Diameter: 21 ft 8 in (6.6 m) S-IVB end
- Weight: 4,050 lb (1,840 kg)
- Volume: 6,700 cu ft (190 m3), 4,900 cu ft (140 m3) usable
Current locations of spacecraft 
The disposition of all Command Modules, and all unflown Service Modules is listed at Apollo Command/Service Module#CSMs produced. (All flown Service Modules burned up in the Earth's atmosphere at termination of the missions.)
The disposition of all Lunar Modules is listed at Apollo Lunar Module#Lunar Modules produced.
- No Command/Service Module was carried on the Apollo 5 unmanned Lunar Module flight, and an aerodynamic nose cone was fastened to the top of the SLA instead.
- North American Rockwell, 'Apollo Command Module News Reference', 1968.
- NASA TN D-7083: Launch Escape Propulsion Subsystem
- Apollo Operations Handbook Lunar Module Subsystems Data
- NASA report JSC-03600 Apollo/Skylab ASTP and Shuttle Orbiter Major End Items, Final Report, March 1978; NASA report listing dispositions of all rockets and spacecraft used in the Apollo, Skylab, Apollo-Soyez Test Project and early shuttle missions, as of 1978.
- Apollo D-2 Proposal by General Electric, Encyclopedia Astronautica