Apollo Command-Service Module

Due to technical limitations, this article uses an unusual title. It should be called  Apollo Command/Service Module.

North American Apollo CSM
Description
Role:	Earth and Lunar Orbit
Crew:	3; CDR, CM pilot, LM pilot
Dimensions
Height:	36.2 ft	11.03 m
Diameter:	12.8 ft	3.9 m
Volume:	218 ft3	6.17 m³
Weights
Command module:	12,807 lb	5,809 kg
Service module:	54,064 lb	24,523 kg
Total:	66,871 lb	30,332 kg
Rocket engines
CM RCS (N2O4/UDMH) x 12:	92 lbf ea	409 N
SM RCS (N2O4/UDMH) x 16:	100 lbf ea	445 N
Service Propulsion System (N2O4/Aerozine 50 ) x 1:	22,000 lbf ea	97.9 kN
Performance
Endurance:	14 days	200 orbits
Apogee:	240,000 miles	386,200 km
Perigee:	100 miles	160 km
Spacecraft delta v:	9,200 ft/s	2,800 m/s
Apollo CSM diagram
Apollo CSM diagram (NASA)
North American Apollo CSM

The Command/Service Module (CSM) was a spacecraft built for NASA by North American Aviation. It was one of the two spacecraft that were utilized for the Apollo program, along with the Lunar Module, to land astronauts on the Moon. Together they were called the Apollo spacecraft. After the conclusion of the Apollo program, the CSM saw service as a ferry for the Skylab program and for the Apollo-Soyuz Test Project where a CSM rendezvoused in orbit with a Soviet Soyuz spacecraft.

The spacecraft, as its name suggests, consisted of two segments, the command module which housed the crew and the equipment needed for re-entry and splashdown, and a service module that provided propulsion, electrical power and storage for various consumables required during a mission. The service module would be cast off and allowed to burn up in the atmosphere before the command module re-entered and brought the crew home.

Command Module (CM)

The Command Module was a truncated cone measuring 10 feet 7 inches (3.2 m) tall and having a diameter of 12 feet 10 inches (3.9 m) across the base. The forward compartment contained two reaction control engines, the docking tunnel, and the components of the Earth Landing System. The inner pressure vessel housed the crew accommodations, equipment bays, controls and displays, and many spacecraft systems. The last section, the aft compartment, contained 10 reaction control engines and their related propellant tanks, fresh water tanks, and the CSM umbilical cables.

Construction

The command module's inner structure was an aluminum "sandwich" consisting of a welded aluminum inner skin, a thermally bonded honeycomb core, and a thin aluminium "face sheet". The central heat shield consisted of 40 individual panels interspersed with several holes and openings for the reaction control engines and after-compartment equipment access. The central compartment structure consisted of an inner aluminium face sheet with a steel honeycomb core, a glass-phenolic ablative honeycomb heat shield, a layer of q-felt fibrous insulation, a pore seal, a moisture barrier, and a layer of aluminized PET film thermal strips.

The aft heat shield consisted of four brazed honeycomb panels, four spot-welded sheet metal fairings, and a circumferential ring. The fairing segments were attached to the honeycomb panels and ring with conventional fasteners. The steel honeycomb core and outer face sheets were then thermally bonded to the inner skin in a giant autoclave. The aft heat shield is nearly identical to the central, with the exception of the outer alluminized PET film layer.

Earth landing system

The components of the ELS were housed around the forward docking tunnel. The forward compartment was separated from the central by a bulkhead and was divided into four 90-degree wedges. The ELS consists of three main parachutes, three pilot parachutes, two drogue parachute motors, three upright bags, a sea recovery cable, a dye marker, and a swimmer umbilical.

The CM had its center of mass offset a foot or so from the axial symmetry of the capsule- this angled the capsule during reentry and gave a small amount of lift. The capsule was then steered by rotating the capsule using thrusters; when no steering was required, the capsule was spun slowly, and the lift effects cancelled out. This system permitted a reasonable amount of cross range and permitted the capsule to be targeted within a few miles.

At 24,000 feet (7.3 km) the forward heat shield was jettisoned using four pressurized-gas compression springs. The drogue parachutes were then released and slowed the spacecraft to 125 miles per hour (201 km/h). At 10,700 feet (3.3 km) the drogues were jettisoned. The pilot parachutes were deployed, which pulled out the mains. These slowed the CM to 22 miles per hour (35 km/h). The Apollo CM can safely parachute to an ocean landing with at least two parachutes (as it happened on Apollo 15), as the third parachute acted as a safety precaution.

Reaction control system

The Command Module attitude control system consisted of 12 x 93 lbf (414 N) maneuvering jets; 10 were located in the aft compartment, and 2 pitch motors in the forward compartment. Four tanks stored 122 kg of N₂O₄ oxidizer and MMH fuel. They were pressurized by 0.5 kg of helium stored at 28.6 MPa in two tanks.

Hatches

The forward docking hatch was mounted at the top of the docking tunnel. It was 30 inches (760 mm) in diameter and weighed 80 pounds (36 kg). It was constructed from two machined rings that were weld-joined to a brazed honeycomb panel. The exterior side was covered with a half-inch (12.7 mm) of insulation and a layer of aluminium foil. It was latched in six places and operated by a pump handle. At the center was a pressure equalization valve, used to equalize the pressure in the tunnel and lunar module before the hatch was removed.

The Unified Crew Hatch (UCH) measured 29 inches (737 mm) high, 34 inches (864 mm) wide, and weighed 225 pounds (102 kg). It was operated by a pump handle, which drove a ratchet mechanism to open or close 15 latches simultaneously.

Docking assembly

The docking probe allowed the command and lunar modules to "link up" and maintain a pressure-tight seal during the mission. It was mounted to the docking tunnel in three places, and was designed to fold easily for storage.

The docking probe consisted of three shock attenuators, three tension linkages, a retractable and extendable probe, and two power umbilicals. Before docking, a crewman in the CM extended the probe. When it came in contact with the drogue, three capture latches in the probe head held the two modules together. The probe was retracted, pulling the CM and LM together. Twelve latches attached to the forward docking ring automatically activated to form an air-tight seal.

At LM separation, the probe and forward docking ring were pyrotechnically separated leaving all docking equipment with the lunar module.

Cabin interior arrangement

The central pressure vessel of the command module was its sole habitable compartment. It had an interior volume of 210 cubic feet (5.9 m³) and housed the main control panels, crew seats, guidance and navigation systems, food and equipment lockers, the waste management system, and the docking tunnel.

Dominating the forward section of the cabin was the crescent-shaped main display panel measuring nearly seven feet (2.1 m) wide and three feet (0.9 m) tall. It was arranged into three panels, each emphasizing the duties of each crew member. The mission commander’s panel (left side) included the velocity, attitude, and altitude indicators, the primary flight controls, and the main FDAI (Flight Director Attitude Indicator).

The CM pilot’s panel (middle) included the Guidance and Navigation computer controls, the caution and warning indicator panel, the event timer, the service propulsion system and RCS controls, and the environmental control system controls.

The LM pilot’s panel (right) included the fuel cell gauges and controls, the electrical and battery controls, and the communications controls.

Flanking the right side of the main panel were sets of smaller control panels. On the left side were a circuit breaker panel, audio controls, and the SCS power controls. On the right were additional circuit breakers and a redundant audio control panel, along with the environmental control switches. In total, the command module panels included 24 instruments, 566 switches, 40 event indicators, and 71 lights.

The three crew couches were constructed from hollow steel tubing and covered in a heavy, fireproof cloth, known as Armalon. The leg pans of the two outer couches could be folded in a variety of positions, while the hip pan of the center couch can be disconnected and laid on the aft bulkhead. One rotational and one translation hand controller was installed on the armrests of the commander’s couch. The LM pilot and CM pilot couches had rotational controllers only. The couches rested on eight shock attenuation struts to ease the impact of splashdown.

There are a total of six equipment bays in the cabin:

• The lower equipment bay, which houses the guidance and control telescope, various communications beacons, the SCS gyro assemblies, the command module computer, medical stores, the audio center, the S-band power amplifier, etc.
• The left-hand forward equipment bay, containing four food storage compartments, the cabin heat exchanger, pressure suit connector, potable water supply, and G&N telescope eyepieces.
• The right-hand forward equipment bay, housing two survival kit containers, a data card kit, flight data books and files, and other mission documentation.
• The left hand intermediate equipment bay, housing the oxygen surge tank, the water delivery system, food supplies, the cabin pressure relief valve controls, and the ECS package.
• The right hand intermediate equipment bay, which contained the bio instrument kits, the waste management system, food and sanitary supplies, and a waste storage compartment.
• The aft storage, compartment, behind the crew couches. This housed the 70 mm camera equipment, the astronaut’s garments, tool sets, storage bags, a fire extinguisher, CO₂ absorbers, sleep restraint ropes, spacesuit maintenance kits, the 16mm camera equipment, and the contingency lunar sample container.

The CM had five windows. The side windows measured 13 inches (330 mm) square and were installed to the side of the left and right-hand couches. The triangular rendezvous windows measured 8 by 13 inches (204 by 330 mm) and were used to aid in docking and rendezvous maneuvers. The hatch window was 9 inches (229 mm) in diameter and was directly over the cm pilot’s couch. Each window was constructed of 4¼ inch (110 mm) thick layers of tempered silica glass separated by 1/10 of an inch (2.5 mm). Each pane had an anti-reflective coating and a blue-red reflective coating on the inner surface.

Specifications

• Crew: 3
• Crew cabin volume: 6.17 m³
• Length: 3.47 m
• Diameter: 3.90 m
• Mass: 5,806 kg
• Structure mass: 1,567 kg
• Heat shield mass: 848 kg
• RCS mass: 400 kg
• Recovery equipment mass: 245 kg
• Navigation equipment mass: 505 kg
• Telemetry equipment mass: 200 kg
• Electrical equipment mass: 700 kg
• Communications systems mass: 100 kg
• Crew couches and provisions mass: 550 kg
• Environmental control system mass: 200 kg
• Mis. contingency mass: 200 kg
• RCS thrust: 12 x 410 N
• RCS propellants: N₂O₄/UDMH
• RCS engine propellants: 122 kg
• Drinking water capacity: 15 kg
• Waste water capacity: 26.5 kg
• Atmosphere cleanser: lithium hydroxide
• Odor absorber: activated charcoal
• Electric system batteries: three 40 ampere-hour silver zinc batteries, two 0.75 ampere-hour silver zinc pyrotechnic batteries
• Parachutes: two 5 meter conical ribbon drogue parachutes, three 2.2 meter ringshot pilot parachutes, three 25.45 meter ringsail main parachutes

Service Module (SM)

The Service Module was an unpressurized cylindrical structure, measuring 24 feet 7 inches (7.5 m) long and 12 feet 10 inches (3.9 m) in diameter. It housed the service propulsion system and its propellants, the fuel cell power system, four maneuvering thruster quads, the S-band antenna for communication with Mission Control, and storage tanks for water and air. On Apollo 15, 16 and 17 it also carried a scientific instrument package. It was connected to the Command module using three tension ties and six compression pads. The tension ties were stainless steel straps bolted to the CM's aft heat shield.

The 98 kN Service Propulsion System was used to place the Apollo spacecraft into and out of lunar orbit, and for mid-course corrections between the Earth and Moon.

The Service module remained attached to the Command Module throughout the mission. It was jettisoned just prior to re-entry into the Earth's atmosphere.

The Service Module was a simple structure consisting of a center section and six pie-shaped sectors. The basic components were the forward bulkhead and fairing, six radial beams, four honeycomb panels, and the aft bulkhead and heat shield.

The forward fairing measured 2 feet 10 inches (864 mm) long and included the RCS computer, umbilical connection, power distribution block, ECS controller, separation controller, and components for the high-gain antenna. The umbilical housing contained the main electrical and plumbing connections from the SM. At SM jettison, the connections were cut using a pyrotechnic-activated guillotine assembly.

Four clusters of reaction control jets were installed around the upper section of the SM every 90 degrees. Each thruster generated approximately 445 N of thrust, and used MMH for fuel and N204 as oxidizer. Each quad assembly measures 8 by 3 feet (2.4 by 0.9 m) and has a single fuel tank, an oxidizer tank, and its associated valves and regulators.

The central tunnel housed the service propulsion engine and its two helium pressurant tanks. The engine used Aerozine 50 (hydrazine/UDMH) fuel and nitrogen tetroxide oxidizer and had a maximum thrust of 20,500 lbf (91.2 kN). It is 152.82 inches (3.882 m) long and 98.48 inches (2.501 m) wide at the base.

Service Module sectors

The Service Module was divided into six sectors:

• Sector 1 was usually filled with ballast to maintain the SM's center-of gravity. On Apollo 15-17, it housed a Scientific Instrument Module (SIM) for lunar study. The equipment included a panoramic camera, gamma ray spectrometer, mapping camera, laser altimeter, mass spectrometer, and lunar sub-satellite.
• Sector 2 contained the oxidizer sump tank, from which oxidizer was fed to the engine. It was 51 inches (1.3 m) wide, 153.8 inches (3.9 m) wide, and contained 6,315 kilograms of oxidizer.
• Sector 3 held the main oxidizer storage tank, which was 154.47 inches (3.924 m) high, 45 inches (1.14 m) wide, and held 5,118 kilograms (11,283 lb) of oxidizer.
• Sector 4 contained most of the electrical power subsystem. Two oxygen tanks contained 290 kilograms of liquid oxygen, and two hydrogen tanks 25 kilograms of hydrogen. The oxygen tanks supplied the environmental control system and fuel cells, and the hydrogen tanks the fuel cells only. The fuel cells combine the two elements to generate electrical power for the spacecraft, along with a small amount of drinking water. Each fuel cell weighed 112 kilograms.
• Sector 5 housed the fuel sump tank. It was the same size as the oxidizer tank and held 3,950 kilograms of propellant. Feed lines connected the tank to the SPS.
• Sector 6 contained the main fuel tank, also the same size as the oxidizer tank. It held 3,201 kilograms of fuel.

Mounted on the top of the aft bulkhead was the S-band high-gain antenna. This was used for deep space communications, and was composed of 4 x 31 inch (787 mm) diameter reflectors and a single 11 inch (279 mm) square reflector. During launch, it was folded down parallel to the main engine. After launch, it deployed at a right angle to the SM.
Also on the SM exterior were a retractable forward-facing spotlight, an EVA floodlight, and a flashing rendezvous beacon visible from 100 kilometers away. Following jettison, the SM translation jets automatically fired aft to distance it from the CM. The roll jets were fired for five seconds to ensure faster break-up on re-entry.

Specifications

• Length: 7.56 m
• Diameter: 3.90 m
• Mass: 24,523 kg
• Structure mass: 1,910 kg
• Electrical equipment mass: 1,200 kg
• RCS thrust: 16 x 446 N
• Propellants: N2O4/UDMH
• Service Propulsion (SPS) engine mass: 3,000 kg
• SPS engine thrust: 91.2 kN
• SPS engine propellants: N2O4/Aerozine 50 (UDMH/N2H4)
• SPS engine propellants: 18,413 kg
• SPS ISP: 314 s (3.1 kN·s/kg)
• Spacecraft delta v: 2,804 m/s
• Electrical System: three 1.4 kW dc/30-volt fuel cells

CSMs produced

Block I
Serial number	Use	Launch date	Current location
CSM-001	systems compatibility test vehicle		presumably scrapped
CSM-002	A-004	January 20, 1966	Command Module on display at Cradle of Aviation, Long Island, New York
CSM-004	static and thermal structural ground tests		scrapped
CSM-006			scrapped
CSM-007	various tests including acoustic vibrations and drop tests		Command Module on display at Museum of Flight, Seattle, Washington
CSM-008	complete systems spacecraft used in thermal vacuum tests		scrapped
CSM-009	AS-201 and drop tests	February 26, 1966	Command Module on display at Strategic Air and Space Museum, Ashland, Nebraska
CSM-010			Command Module on display at U.S. Space & Rocket Center, Huntsville, Alabama
CSM-011	AS-202	August 25, 1966	Command Module on display at National Air and Space Museum, Washington DC
CSM-012	Apollo 1; The Command Module was severely damaged in the Apollo 1 fire		Command Module in storage at the Langley Research Center, Hampton, Virginia
CSM-014	Command Module disassembled as part of Apollo 1 investigation. Service Module (SM-014) used on Apollo 6 mission	April 4, 1968
CSM-017	Apollo 4	November 9, 1967	Command Module on display at Stennis Space Center, Bay St. Louis, Mississippi
CSM-020	CM-020 flew on Apollo 6 with SM-014 after SM-020 was destroyed in an explosion	April 4, 1968	Command Module on display at Fernbank Science Center, Atlanta
Block II
Serial number	Use	Launch date	Current location
CSM-098	used in thermal vacuum test		CSM on display at Academy of Science Museum, Moscow, Russia
CSM-099	static structural testing		scrapped
CSM-100	static structural testing		unknown
CSM-101	Apollo 7	October 11, 1968	Command Module was on display at National Museum of Science & Technology, Ottawa, Canada from 1974 until 2004, now at the Frontiers of Flight Museum, Dallas, TX after 30 years of being on loan.
CSM-102	Launch Complex 34 checkout vehicle		scrapped
CSM-103	Apollo 8	December 21, 1968	Command Module on display at Museum of Science and Industry in Chicago
CSM-104 Gumdrop	Apollo 9	March 3, 1969	Command Module on display at San Diego Aerospace Museum
CSM-105	acoustic tests		Command Module on display at National Air & Space Museum, Washington DC as part of the Apollo Soyuz Test Project display. (Photo)
CSM-106 Charlie Brown	Apollo 10	May 18, 1969	Command Module on display at Science Museum (London), London
CSM-107 Columbia	Apollo 11	July 16, 1969	Command Module on display at National Air & Space Museum, Washington DC
CSM-108 Yankee Clipper	Apollo 12	November 14, 1969	Command Module on display at Virginia Air & Space Center, Hampton, Virginia
CSM-109 Odyssey	Apollo 13	April 11, 1970	Command Module on display at Kansas Cosmosphere and Space Center
CSM-110 Kitty Hawk	Apollo 14	January 31, 1971	Command Module on display at United States Astronaut Hall of Fame, Titusville, Florida
CSM-111	Apollo Soyuz Test Project	July 15, 1975	Command Module on display at Kennedy Space Center Visitor's Complex
CSM-112 Endeavour	Apollo 15	July 26, 1971	Command Module on display at National Museum of the United States Air Force, Wright-Patterson Air Force Base, Dayton, Ohio
CSM-113 Casper	Apollo 16	April 16, 1972	Command Module on display at U.S. Space & Rocket Center, Huntsville, Alabama
CSM-114 America	Apollo 17	December 7, 1972	Command Module on display at Space Center Houston, Houston, Texas
CSM-115	cancelled		Never fully completed. On display as part of the Saturn V display at Johnson Space Center, Houston, Texas
CSM-115a	cancelled		never completed
CSM-116	Skylab 2	May 25, 1973	Command Module on display at National Museum of Naval Aviation, Pensacola, Florida
CSM-117	Skylab 3	July 28, 1973	Command Module on display at Glenn Research Center, Cleveland, Ohio
CSM-118	Skylab 4	November 16, 1973	Command Module on display at National Air & Space Museum, Washington DC
CSM-119	Skylab Rescue and ASTP backup		On display at the Kennedy Space Center

In fiction

In Shane Johnson's novel Ice, the CSM figures prominently in two fictional post-Apollo 17 missions:

• In Apollo 19, the Command Module Pilot must abandon his buddies on the Moon after their LM ascent engine fails to fire. A later scene describes the CM being sealed shut after only one man has egressed from it.
• In Apollo 20, the CM is outfitted for Skylab rescue, like CM-119 (see Table above), as three astronauts return to the Moon to recover what they assume will be the remains of their fallen comrades.