Apollo Command/Service Module

Apollo Command/Service Module

Apollo 15 Command and Service Module in lunar orbit
Manufacturer

North American Aviation

North American Rockwell
Designer Maxime Faget
Country of origin United States
Operator NASA
Applications Manned cislunar flight and lunar orbit
Skylab crew shuttle
Apollo-Soyuz Test Project
Specifications
Design life 14 days
Launch mass 32,390 pounds (14,690 kg) Earth orbit
63,500 pounds (28,800 kg) Lunar
Dry mass 26,300 pounds (11,900 kg)
Payload capacity 2,320 pounds (1,050 kg)
Crew capacity 3
Dimensions 36.2 feet (11.0 m) high
12.8 feet (3.9 m) diameter
Volume 218 cubic feet (6.2 m3)
Power Fuel cells
Regime Low Earth orbit
Cislunar space
Lunar orbit
Production
Status Retired
Built 35
Launched 19
Operational 19
Failed 2
Lost 1
First launch February 26, 1966
Last launch July 15, 1975
Last retirement July 24, 1975
Related spacecraft
Flown with Apollo Lunar Module


Apollo Block II CSM diagram

← Gemini spacecraft Orion (spacecraft) →

The Command/Service Module (CSM) was one of two spacecraft, along with the Lunar Module, used for the United States Apollo program which landed astronauts on the Moon. It was built for NASA by North American Aviation. It was launched by itself on three suborbital and low Earth orbit Apollo test missions using the Saturn IB launch vehicle. It was also launched twelve times on the larger Saturn V launch vehicle, both by itself and with the Lunar Module. It made a total of nine manned flights to the Moon aboard the Saturn V.

After the Apollo lunar program, the CSM saw manned service as a crew shuttle for the Skylab program, and the Apollo-Soyuz Test Project in which an American crew rendezvoused and docked with a Soviet Soyuz spacecraft in Earth orbit.

The CSM consisted of two segments: the Command Module, a cabin that housed a crew of three and 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 was cast off and allowed to burn up in the atmosphere before the Command Module re-entered and brought the crew home.

The CSM was initially designed to return all three astronauts from the lunar surface on a direct-descent mission which would not use a separate Lunar Module, and thus had no provisions for docking with another spacecraft. This, plus other required design changes led to the decision to design two versions of the CSM: Block I was to be used for unmanned missions and a single manned Earth orbit flight (Apollo 1), while the more advanced Block II was designed for use with the Lunar Module. The Apollo 1 flight was cancelled after a cabin fire killed the entire crew and destroyed the Command Module during a launch rehearsal test. Corrections of the problems which caused the fire were applied to the Block II spacecraft, which was used for all manned missions.

Development history

When NASA awarded the initial Apollo contract to North American Aviation on November 28, 1961, it was still assumed the lunar landing would be achieved by direct descent rather than by lunar orbit rendezvous.[1] Therefore, design proceeded without a means of docking the Command Module to a Lunar Excursion Module (LEM). But the change to lunar orbit rendezvous, plus several technical obstacles encountered in some subsystems (such as environmental control), soon made it clear that substantial redesign would be required. In 1963, NASA decided the most efficient way to keep the program on track was to proceed with the development in two versions:[2]

By January 1964, North American started presenting Block II design details to NASA.[3] Block I spacecraft were used for all unmanned Saturn 1B and Saturn V test flights. Initially two manned flights were planned, but this was reduced to one in late 1966. This mission, designated AS-204 but named Apollo 1 by its flight crew, was planned for launch on February 21, 1967. But during a dress rehearsal for the launch on January 27, all three astronauts (Virgil I. "Gus" Grissom, Edward H. White, II and Roger Chaffee), were killed in a cabin fire which revealed serious design, construction and maintenance shortcomings in Block I, many of which would have been carried over into Block II.

After a thorough investigation by the Apollo 204 Review Board, it was decided to terminate the manned Block I phase and redefine Block II to incorporate the review board's recommendations. Block II incorporated a revised CM heat shield design, which was tested on the unmanned Apollo 4 and Apollo 6 flights, so the first all-up Block II spacecraft flew on the first manned mission, Apollo 7.

The two blocks were essentially similar in overall dimensions, but several design improvements resulted in weight reduction in Block II. Also, the Block I Service Module propellant tanks were slightly larger than in Block II. The Apollo 1 spacecraft weighed approximately 45,000 pounds (20,000 kg), while the Block II Apollo 7 weighed 36,400 lb (16,500 kg). (These two Earth orbital craft were lighter than the craft which later went to the Moon, as they carried propellant in only one set of tanks, and did not carry the high gain S-band antenna.) In the specifications given below, unless otherwise noted, all weights given are for the Block II spacecraft.

The total cost of the CSM for development and the units produced was $36.9B in 2016 dollars, adjusted from a nominal total of $3.7B[4] using the NASA New Start Inflation Indices.[5]

Command Module (CM)

The Command Module was a truncated cone (frustum) 10 feet 7 inches (3.23 m) tall with a diameter of 12 feet 10 inches (3.91 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

Apollo Command Module cabin arrangement

The Command Module (CM) consists of two basic structures joined together: the inner structure (pressure shell) and the outer structure (heat shield).

The inner structure is of aluminum sandwich construction which consists of a welded aluminum inner skin, adhesively bonded aluminum honeycomb core and outer face sheet. The thickness of the honeycomb varies from about 1-1/2 inches at the base to about 1/4 inch at the forward access tunnel. This inner structure – basically the crew compartment – is the part of the module that is pressurized and contains an atmosphere.

The outer structure is the heat shield and is made of stainless steel brazed honeycomb brazed between steel alloy face sheets. It varies in thickness from ½ inch to 2½ inches. Part of the area between the inner and outer shells is filled with a layer of fibrous insulation as additional heat protection. [6]

Thermal Protection (Heat Shield)

The principal task of the heat shield that forms the outer structure is to protect the crew from the fiery heat of entry-heat so intense that it melts most metals. The ablative material that does this job is a phenolic epoxy resin, a type of reinforced plastic. This material turns white hot, chars, and then melts away, but it does it in such a way that the heat is rejected by the shield and does not penetrate to the surface of the spacecraft.

The ablative material controls the rate of heat absorption by charring or melting rapidly. This dissipates the heat and keeps it from reaching the inner structure.

The command module enters the atmosphere with its base down; this is covered by the aft heat shield which is the thickest portion. The heat shield varies in thickness: the aft portion is 2 inches and the crew compartment and forward portions are ½ inch. Total weight of the shield is about 3,000 pounds. The heat shield has several outer coverings: a pore seal, a moisture barrier (a white reflective coating), and a silver Mylar thermal coating that looks like aluminum foil. [6]

Impact Attenuation

The impact attenuation system is part internal and part external. The external part consists of four crushable ribs (each about 4 inches thick and a foot in length) installed in the aft compartment. The ribs are made of bonded laminations of corrugated aluminum which absorb energy by collapsing upon themselves at impact. The main parachutes suspend the CM at such an angle that the ribs are the first point of the module that hits the water.[6]

Forward Compartment

The forward compartment is the area around the forward (docking) tunnel. It is separated from the crew compartment by a bulkhead and covered by the forward heat shield. The compartment is divided into four 90-degree segments which contain Earth Ianding equipment (all the parachutes, recovery antennas and beacon light, and sea recovery sling), two reaction control engines, and the forward heat shield release mechanism.

At about 25,000 feet during entry, the forward heat shield is jettisoned to expose the Earth landing equipment and permit deployment of the parachutes.[6]

Aft Compartment

The aft compartment is located around the periphery of the command module at its widest part, just forward of (above) the aft heat shield. The compartment is divided into 24 bays by the 24 frames of the structure. In these bays are 10 reaction control engines; the fuel, oxidizer, and helium tanks for the CM reaction control subsystem; water tanks; the crushable ribs of the impact attenuation system; and a number of instruments. The CM-SM umbilical, the point where wiring and plumbing runs from one module to the other, also is in the aft compartment. The panels of the heat shield around the aft compartment are removable for maintenance of the equipment before flight.[6]

Protection Panels

Protection panels are mounted throughout the interior of the command module as additional protection for spacecraft equipment. The panels are made of aluminum in varying thicknesses and are used to cover wiring and equipment and to smooth out irregular surfaces of the cabin. The panels prevent loose equipment or debris from getting into crevices of the spacecraft during preparation for flight. They also help suppress fire by sealing off areas and protect critical parts from damage during work by ground personnel.[6]

Mirrors

Internal and external mirrors are provided to aid astronauts' visibility. The internal mirrors (4 by 6 inches) are designed to help the astronaut see to adjust his restraint harness and locate his controls while in his pressurized suit. The external mirrors are 2-1/2 by 3-1/2 inches and are located at the top and bottom of the right-hand rendezvous window so that the astronaut can verify parachute deployment during entry.[6]

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 consisted of two drogue parachutes with mortars, three main parachutes, three pilot parachutes to deploy the mains, three inflation bags for uprighting the capsule if necessary, a sea recovery cable, a dye marker, and a swimmer umbilical.

The Command Module's center of mass was offset a foot or so from the center of pressure (along the symmetry axis). This provided a rotational moment during reentry, angling the capsule and providing some lift (a lift to drag ratio of about 0.368[7]). 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 greatly reduced the g-force experienced by the astronauts, permitted a reasonable amount of directional control and allowed the capsule's splashdown point 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 deployed, slowing the spacecraft to 125 miles per hour (201 kilometres per hour). At 10,700 feet (3.3 km) the drogues were jettisoned and the pilot parachutes, which pulled out the mains, were deployed. These slowed the CM to 22 miles per hour (35 kilometres per hour) for splashdown. The portion of the capsule which first contacted the water surface was built with crushable ribs to further mitigate the force of impact. The Apollo Command Module could safely parachute to an ocean landing with at least two parachutes (as occurred on Apollo 15), the third parachute being a safety precaution.

Reaction Control System

The Command Module attitude control system consisted of twelve 93-pound-force (410 N) attitude control jets; ten were located in the aft compartment, and two pitch motors in the forward compartment. Four tanks stored 270 pounds (120 kg) of mono-methyl hydrazine fuel and nitrogen tetroxide oxidizer. They were pressurized by 1.1 pounds (0.50 kg) of helium stored at 4,150 pounds per square inch (28.6 MPa) in two tanks.

Hatches

The forward docking hatch was mounted at the top of the docking tunnel. It was 30 inches (76 cm) 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 0.5-inch (13 mm) of insulation and a layer of aluminum foil. It was latched in six places and operated by a pump handle. The hatch contained a valve in its center, used to equalize the pressure between the tunnel and the CM so the hatch could be removed.

The Unified Crew Hatch (UCH) measured 29 inches (74 cm) high, 34 inches (86 cm) wide, and weighed 225 pounds (102 kg). It was operated by a pump handle, which drove a ratchet mechanism to open or close fifteen latches simultaneously.

Docking assembly

The Apollo spacecraft docking mechanism was a non-androgynous system, consisting of a probe located in the nose of the CSM, which connected to the drogue, a truncated cone located on the Lunar Module. The probe was extended like a scissor jack to capture the drogue on initial contact, known as soft docking. Then the probe was retracted to pull the vehicles together and establish a firm connection, known as "hard docking". The mechanism was specified by NASA to have the following functions:

Coupling

The probe head located in the CSM was self-centering and gimbal-mounted to the probe piston. As the probe head engaged in the opening of the drogue socket, three spring-loaded latches depressed and engaged. These latches allowed a so-called 'soft dock' state and enabled the pitch and yaw movements in the two vehicles to subside. Excess movement in the vehicles during the 'hard dock' process could cause damage to the docking ring and put stress on the upper tunnel. A depressed locking trigger link at each latch allowed a spring-loaded spool to move forward, maintaining the toggle linkage in an over-center locked position. In the upper end of the Lunar Module tunnel, the drogue, which was constructed of 1-inch-thick aluminum honeycomb core, bonded front and back to aluminum face sheets, was the receiving end of the probe head capture latches.

Retraction

After the initial capture and stabilization of the vehicles, the probe was capable of exerting a closing force of 1,000 pounds-force (4.4 kN) to draw the vehicles together. This force was generated by gas pressure acting on the center piston within the probe cylinder. Piston retraction compressed the probe and interface seals and actuated the 12 automatic ring latches which were located radially around the inner surface of the CSM docking ring. The latches were manually re-cocked in the docking tunnel by an astronaut after each hard docking event (lunar missions required two dockings).

Separation

An automatic extension latch attached to the probe cylinder body engaged and retained the probe center piston in the retracted position. Before vehicle separation in lunar orbit, manual cocking of the twelve ring latches was accomplished. The separating force from the internal pressure in the tunnel area was then transmitted from the ring latches to the probe and drogue. In undocking, the release of the capture latches was accomplished by electrically energizing tandem-mounted DC rotary solenoids located in the center piston. In a temperature degraded condition, a single motor release operation was done manually in the Lunar Module by depressing the locking spool through an open hole in the probe heads, while release from the CSM was done by rotating a release handle at the back of the probe to rotate the motor torque shaft manually.[8] When the Command and Lunar Modules separated for the last time just before re-entry, the probe and forward docking ring were pyrotechnically separated, leaving all docking equipment attached to the lunar module. In the event of an abort during launch from Earth, the same system would have explosively jettisoned the docking ring and probe from the CM as it separated from the boost protective cover.

Cabin interior arrangement

Apollo Command Module main control panel

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 7 feet (2.1 m) wide and 3 feet (0.91 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 served as navigator, so his control panel (center) 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 served as systems engineer, so his control panel (right-hand side) included the fuel cell gauges and controls, the electrical and battery controls, and the communications controls.

Flanking the sides 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 could be disconnected and laid on the aft bulkhead. One rotation and one translation hand controller was installed on the armrests of the left-hand couch. The translation controller was used by the crew member performing the LM docking maneuver, usually the CM Pilot. The center and right-hand couches had duplicate rotational controllers. The couches were supported by eight shock-attenuating struts, designed to ease the impact of touchdown on water or, in case of an emergency landing, on solid ground.

The contiguous cabin space was organized into six equipment bays:

Apollo command module G&N equipment

The CM had five windows. The two side windows measured 13 inches (330 mm) square next to the left and right-hand couches. Two forward-facing triangular rendezvous windows measured 8 by 13 inches (200 by 330 millimetres), used to aid in rendezvous and docking with the LM. The circular hatch window was 10 5/8 in. diameter (27 cm) and was directly over the center couch. Each window assembly consisted of three thick panes of glass. The inner two panes, which were made of aluminosilicate, made up part of the module's pressure vessel. The fused silica outer pane served as both a debris shield and as part of the heat shield. Each pane had an anti-reflective coating and a blue-red reflective coating on the inner surface.

Specifications

Apollo 14 Command Module at Kennedy Space Center.

Service Module (SM)

Block II Service Module interior components

Construction

The Service Module was an unpressurized cylindrical structure, measuring 24 feet 7 inches (7.49 m) long and 12 feet 10 inches (3.91 m) in diameter. The interior was a simple structure consisting of a central tunnel section 44 inches (1.1 m) in diameter, surrounded by six pie-shaped sectors. The sectors were topped by a forward bulkhead and fairing, separated by six radial beams, covered on the outside by four honeycomb panels, and supported by an aft bulkhead and engine heat shield. The sectors were not all equal 60° angles, but varied according to required size.

The forward fairing measured 2 feet 10 inches (860 mm) long and included the Reaction Control System (RCS) computer, umbilical connection, power distribution block, ECS controller, separation controller, components for the high-gain antenna, and eight EPS radiators. The umbilical housing contained the main electrical and plumbing connections to the CM. The fairing externally contained a retractable forward-facing spotlight; an EVA floodlight to aid the Command Module pilot in SIM film retrieval; and a flashing rendezvous beacon visible from 54 nautical miles (100 km) away as a navigation aid for rendezvous with the Lunar Module (LM).

The SM was connected to the CM using three tension ties and six compression pads. The tension ties were stainless steel straps bolted to the CM's aft heat shield. It remained attached to the Command Module throughout most of the mission, until being jettisoned just prior to re-entry into the Earth's atmosphere. At jettison, the CM umbillical connections were cut using a pyrotechnic-activated guillotine assembly. Following jettison, the SM aft translation thrusters automatically fired continuously to distance it from the CM, until either the RCS fuel or the fuel cell power was depleted. The roll thrusters were also fired for five seconds to make sure it followed a different trajectory from the CM and faster break-up on re-entry.

Service Propulsion System

The SPS engine was used to place the Apollo spacecraft into and out of lunar orbit, and for mid-course corrections between the Earth and Moon. It also served as a retrorocket to perform the deorbit burn for Earth orbital Apollo flights. The engine selected was the AJ10-137,[9] which used Aerozine 50 as fuel and nitrogen tetroxide (N2O4) as oxidizer to produce 20,500 lbf (91 kN) of thrust. The thrust level was twice what was needed to accomplish the lunar orbit rendezvous (LOR) mission mode, because the engine was originally sized to lift the CSM off of the lunar surface in the direct ascent mode assumed in original planning[10] (see Choosing a mission mode.) A contract was signed in April 1962 for the Aerojet-General company to start developing the engine, before the LOR mode was officially chosen in July of that year.[11]

The propellants were pressure-fed to the engine by 39.2 cubic feet (1.11 m3) of gaseous helium at 3,600 pounds per square inch (25 MPa), carried in two 40-inch (1.0 m) diameter spherical tanks.[12]

The exhaust nozzle engine bell measured 152.82 inches (3.882 m) long and 98.48 inches (2.501 m) wide at the base. It was mounted on two gimbals to keep the thrust vector aligned with the spacecraft's center of mass during SPS firings. The combustion chamber and pressurant tanks were housed in the central tunnel.

Reaction Control System

Four clusters of four reaction control system (RCS) thrusters were installed around the upper section of the SM every 90°. The sixteen-thruster arrangement provided rotation and translation control in all three spacecraft axes. Each R-4D thruster generated 100 pounds-force (440 N) of thrust, and used mono-methyl hydrazine (MMH) as fuel and nitrogen tetroxide (NTO) as oxidizer. Each quad assembly measured 8 by 3 feet (2.44 by 0.91 m) and had its own fuel tank, oxidizer tank, helium pressurant tank, and associated valves and regulators.

The Lunar Module used a similar four-quad arrangement of the identical thruster engines for its RCS.

Electrical power system

Three of these fuel cells were used to power the spacecraft on lunar flights.

Electrical power was produced by three fuel cells, each measuring 44 inches (1.1 m) tall by 22 inches (0.56 m) in diameter and weighing 245 pounds (111 kg). These combined hydrogen and oxygen to generate electrical power, along with some of the water used for drinking and other purposes. The cells were fed by two hemispherical-cylindrical 31.75-inch (0.806 m) diameter tanks, each holding 29 pounds (13 kg) of liquid hydrogen, and two spherical 26-inch (0.66 m) diameter tanks, each holding 326 pounds (148 kg) of liquid oxygen (which also supplied the environmental control system).

On the flight of Apollo 13, the EPS was disabled by an explosive rupture of one oxygen tank, which punctured the second tank and led to the loss of all oxygen. After the accident, a third oxygen tank was added to prevent operation below 50% tank capacity which allowed removal of the tank's internal stirring fan equipment, which had contributed to the failure.

Also starting with Apollo 14, a 400 Ah auxiliary battery was added to the SM for emergency use. Apollo 13 had drawn heavily on its entry batteries in the first hours after the explosion, and while this new battery could not power the CM for more than 5–10 hours it would buy time in the event of a temporary loss of all three fuel cells. Such an event occurred when Apollo 12 was struck twice by lightning during launch.

Environmental control system

Storage tanks were carried for water and oxygen. Waste heat from the CM cabin was dumped to space by two 30-square-foot (2.8 m2) radiators located on the lower section of the exterior walls, one covering sectors 2 and 3, and the other covering sectors 5 and 6.

Communications system

Short-range communications between the CSM and Lunar Module employed two VHF scimitar antennas mounted on the SM just above the ECS radiators.

A steerable unified S-band high-gain antenna for long-range communications with Earth was mounted on the aft bulkhead. This was an array of four 31-inch (0.79 m) diameter reflectors surrounding a single 11-inch (0.28 m) square reflector. During launch it was folded down parallel to the main engine to fit inside the Spacecraft-to-LM Adapter (SLA). After CSM separation from the SLA, it deployed at a right angle to the SM.

Two omnidirectional S-band antennas on the CM were used when the attitude of the CSM kept the high gain antenna from being pointed at Earth. These antennas were also used between SM jettison and landing.

Specifications

Modifications for Saturn IB missions

The Low Earth Orbit payload capability of the Saturn IB booster used to launch the Low Earth Orbit missions (Apollo 1 (planned), Apollo 7, Skylab 2, Skylab 3, Skylab 4, and Apollo-Soyuz) could not handle the 66,900-pound (30,300 kg) mass of the fully fueled CSM. This was not a problem, because the delta-V requirement of these missions was much smaller than that of the lunar mission; therefore they could be launched with less than half of the full SPS propellant load, by filling only the SPS sump tanks and leaving the storage tanks empty. The CSMs launched in orbit on Saturn IB ranged from 32,558 pounds (14,768 kg) (Apollo-Soyuz), to 46,000 pounds (21,000 kg) (Skylab 4).

The omnidirectional antennas sufficed for ground communications during the Earth orbital missions, so the high gain S-band antenna on the SM was omitted from Apollo 1, Apollo 7, and the three Skylab flights. It was restored for the Apollo-Soyuz mission to communicate through the ATS-6 satellite in geostationary orbit, an experimental precursor to the current TDRSS system.

On the Skylab and Apollo-Soyuz missions, some additional dry weight was saved by removing the otherwise empty fuel and oxidizer storage tanks (leaving the partially filled sump tanks), along with one of the two helium pressurant tanks.[13] This permitted the addition of some extra RCS propellant to allow for use as a backup for the deorbit burn in case of possible SPS failure.[14]

Since the spacecraft for the Skylab missions would not be occupied for most of the mission, there was lower demand on the power system, so one of the three fuel cells was deleted from these SMs.

The Command Module could be modified to carry extra astronauts as passengers by adding jump seat couches in the aft equipment bay. CM-119 was fitted with two jump seats as a Skylab Rescue vehicle, which was never used.[15]

Major differences between Block I and Block II

Command Module

Block I Command Module exterior

Service Module

Block I Service Module interior components

CSMs produced

Serial number Name Use Launch date Current location
Block I
CSM-001 systems compatibility test vehicle
CSM-002 A-004 flight 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 used for demonstrating tumbling debris removal system scrapped
CSM-007 various tests including acoustic vibration and drop tests, and water egress training. CM was refitted with Block II improvements.[16] Underwent testing for Skylab at the McKinley Climatic Laboratory, Eglin AFB, Florida, 1971-1973. 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 flight and drop tests February 26, 1966 Command Module on display at Strategic Air and Space Museum, adjacent to Offutt Air Force Base in Ashland, Nebraska
CSM-010 Command Module on display at U.S. Space & Rocket Center, Huntsville, Alabama
CSM-011 AS-202 flight August 25, 1966 Command Module on display on the USS Hornet museum at the former Naval Air Station Alameda, Alameda, California
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[17]
CSM-098 used in thermal vacuum test CSM on display at Academy of Science Museum, Moscow, Russia as part of the Apollo Soyuz Test Project display.
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, Texas after 30 years of being on loan.[18]
CSM-102 Launch Complex 34 checkout vehicle Service Module is at JSC on top of the Little Joe II in Rocket Park. The command module is Boiler Plate 22.
CSM-103 Apollo 8 December 21, 1968 Command Module on display at the Museum of Science and Industry in Chicago
CSM-104 Gumdrop Apollo 9 March 3, 1969 Command Module on display at San Diego Air and Space Museum
CSM-105 acoustic tests Command Module on display at National Air and Space Museum, Washington, D.C. 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
CSM-107 Columbia Apollo 11 July 16, 1969 Command Module on display at National Air and Space Museum, Washington, D.C.
CSM-108 Yankee Clipper Apollo 12 November 14, 1969 Command Module on display at Virginia Air & Space Center, Hampton, Virginia; previously on display at the National Naval Aviation Museum at Naval Air Station Pensacola, Pensacola, Florida (exchanged for CSM-116)
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 the Kennedy Space Center
CSM-111 Apollo Soyuz Test Project July 15, 1975 Command Module currently on display at California Science Center in Los Angeles, California (formerly displayed at the Kennedy Space Center Visitor 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 canceled Never fully completed – service module does not have its SPS nozzle installed. On display as part of the Saturn V display at Johnson Space Center, Houston, Texas; command module restored in 2005 prior to the dedication of the JSC Saturn V Center
CSM-115a canceled never completed
CSM-116 Skylab 2 May 25, 1973 Command Module on display at National Museum of Naval Aviation, Naval Air Station Pensacola, Pensacola, Florida
CSM-117 Skylab 3 July 28, 1973 Command Module on display at Great Lakes Science Center, current location of the NASA Glenn Research Center Visitor Center, Cleveland, Ohio
CSM-118 Skylab 4 November 16, 1973 Command Module on display at National Air and Space Museum, Washington, D.C.
CSM-119 Skylab Rescue and ASTP backup On display at the Kennedy Space Center

See also

References

  1. ↑ Courtney G Brooks; James M. Grimwood; Loyd S. Swenson (1979). "Contracting for the Command Module". Chariots for Apollo: A History of Manned Lunar Spacecraft. NASA. ISBN 0-486-46756-2. Archived from the original on 9 February 2008. Retrieved 2008-01-29.
  2. ↑ Courtney G Brooks; James M. Grimwood; Loyd S. Swenson (1979). "Command Modules and Program Changes". Chariots for Apollo: A History of Manned Lunar Spacecraft. NASA. ISBN 0-486-46756-2. Archived from the original on 9 February 2008. Retrieved 2008-01-29.
  3. ↑ Morse, Mary Louise; Bays, Jean Kernahan (September 20, 2007). The Apollo Spacecraft: A Chronology. SP-4009II. Vol. II, Part 2(C): Developing Hardware Distinctions. NASA.
  4. ↑ Orloff, Richard (1996). Apollo by the Numbers (PDF). National Aeronautics and Space Administration. p. 22.
  5. ↑ "NASA New Start Inflation Indices". National Aeronautics and Space Administration. Retrieved May 23, 2016.
  6. 1 2 3 4 5 6 7 "CSM06 Command Module Overview pp 39 - 52" (PDF). National Aeronautics and Space Administration. Retrieved November 1, 2016.
  7. ↑ Hillje, Ernest R., "Entry Aerodynamics at Lunar Return Conditions Obtained from the Flight of Apollo 4 (AS-501)," NASA TN D-5399, (1969).
  8. ↑ Bloom, Kenneth A. 2006.
  9. ↑ "Apollo CSM". Encyclopedia Astronautica.
  10. ↑ Wilford, John (1969). We Reach the Moon: The New York Times Story of Man's Greatest Adventure. New York: Bantam Paperbacks. p. 167. ISBN 0-373-06369-0.
  11. ↑ "Apollo CSM SPS". Encyclopedia Astronautica.
  12. ↑ "Apollo Operations Handbook, SM2A-03-Block II-(1)" (PDF). NASA.
  13. ↑ "Reduced Apollo Block II service propulsion system for Saturn IB Missions". Encyclopedia Astronautica. Archived from the original on 2010-02-01.
  14. ↑ Gatland, Kenneth (1976). Manned Spacecraft, Second Revision. New York: Macmillan Publishing Co. p. 292. ISBN 0-02-542820-9.
  15. ↑ " Mission Requirements, Skylab Rescue Mission, SL-R" NASA, 24 August 1973.
  16. ↑ These included the crew couches, quick escape hatch, and metallic heat shield coating. See Apollo Command Module (image @ Wikimedia Commons).
  17. ↑ "Apollo Command and Service Module Documentation". NASA.
  18. ↑ "Apollo 7 Command Module and Wally Schirra's Training Suit Leave Science and Tech Museum After 30 Years". Canada Science and Technology Museum. March 12, 2004.

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