Template:Short description Template:Use American English Template:Use mdy dates {{#invoke:other uses|otheruses}} Template:Infobox spacecraft class
The Apollo command and service module (CSM) was one of two principal components of the United States Apollo spacecraft, used for the Apollo program, which landed astronauts on the Moon between 1969 and 1972. The CSM functioned as a mother ship, which carried a crew of three astronauts and the second Apollo spacecraft, the Apollo Lunar Module, to lunar orbit, and brought the astronauts back to Earth. It consisted of two parts: the conical command module, a cabin that housed the crew and carried equipment needed for atmospheric reentry and splashdown; and the cylindrical service module which provided propulsion, electrical power and storage for various consumables required during a mission. An umbilical connection transferred power and consumables between the two modules. Just before reentry of the command module on the return home, the umbilical connection was severed and the service module was cast off and allowed to burn up in the atmosphere.
The CSM was developed and built for NASA by North American Aviation starting in November 1961. It was initially designed to land on the Moon atop a landing rocket stage and return all three astronauts on a direct-ascent 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 uncrewed missions and a single crewed 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 crew and destroyed their 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 crewed spaceflights.
Nineteen CSMs were launched into space. Of these, nine flew humans to the Moon between 1968 and 1972, and another two performed crewed test flights in low Earth orbit, all as part of the Apollo program. Before these, another four CSMs had flown as uncrewed Apollo tests, of which two were suborbital flights and another two were orbital flights. Following the conclusion of the Apollo program and during 1973–1974, three CSMs ferried astronauts to the orbital Skylab space station. Finally in 1975, the last flown CSM docked with the Soviet craft Soyuz 19 as part of the international Apollo–Soyuz Test Project.
Before ApolloEdit
Concepts of an advanced crewed spacecraft started before the Moon landing goal was announced. The three-person vehicle was to be mainly for orbital use around Earth. It would include a large pressurized auxiliary orbital module where the crew would live and work for weeks at a time. They would perform space station-type activities in the module, while later versions would use the module to carry cargo to space stations. The spacecraft was to service the Project Olympus (LORL), a foldable rotating space station launched on a single Saturn V. Later versions would be used on circumlunar flights, and would be the basis for a direct ascent lunar spacecraft as well as used on interplanetary missions. In late 1960, NASA called on U.S. industry to propose designs for the vehicle. On May 25, 1961 President John F. Kennedy announced the Moon landing goal before 1970, which immediately rendered NASA's Olympus Station plans obsolete.<ref>Template:Cite news</ref><ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
Development historyEdit
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 ascent rather than by lunar orbit rendezvous.<ref name='chariots2-5'>Template:Cite book</ref> 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:<ref name='chariots5-1'>Template:Cite book</ref>
- Block I would continue the preliminary design, to be used for early low Earth orbit test flights only.
- Block II would be the lunar-capable version, including a docking hatch and incorporating weight reduction and lessons learned in Block I. Detailed design of the docking capability depended on design of the LEM, which was contracted to Grumman Aircraft Engineering.
By January 1964, North American started presenting Block II design details to NASA.<ref>Template:Cite book</ref> Block I spacecraft were used for all uncrewed Saturn 1B and Saturn V test flights. Initially two crewed 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. During a dress rehearsal for the launch on January 27, all three astronauts (Gus Grissom, Ed White and Roger Chaffee) were killed in a cabin fire, which revealed serious design, construction and maintenance shortcomings in Block I, many of which had been carried over into Block II command modules being built at the time.
After a thorough investigation by the Apollo 204 Review Board, it was decided to terminate the crewed 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 uncrewed Apollo 4 and Apollo 6 flights, so the first all-up Block II spacecraft flew on the first crewed 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 Template:Convert, while the Block II Apollo 7 weighed Template:Convert. (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 $36.9 billion in 2016 dollars, adjusted from a nominal total of $3.7 billion<ref>Template:Cite book</ref> using the NASA New Start Inflation Indices.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
Command module (CM)Template:AnchorEdit
The command module was a truncated cone (frustum) with a diameter of Template:Convert across the base, and a height of Template:Convert including the docking probe and dish-shaped aft heat shield. The forward compartment contained two reaction control system thrusters, the docking tunnel, and the Earth Landing System. The inner pressure vessel housed the crew accommodation, equipment bays, controls and displays, and many spacecraft systems. The aft compartment contained 10 reaction control engines and their related propellant tanks, freshwater tanks, and the CSM umbilical cables.<ref>Template:Cite news</ref>
ConstructionEdit
The command module was built in North American's factory in Downey, California,<ref name="NPR.org Jul162019">{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref name="Chiotakis and Mesirow Jul152019">{{#invoke:citation/CS1|citation |CitationClass=web }}</ref> and consisted of two basic structures joined together: the inner structure (pressure shell) and the outer structure.
The inner structure was an aluminum sandwich construction consisting of a welded aluminum inner skin, adhesively bonded aluminum honeycomb core, and outer face sheet. The thickness of the honeycomb varied from about Template:Convert at the base to about Template:Convert at the forward access tunnel. This inner structure was the pressurized crew compartment.
The outer structure was made of stainless steel brazed-honeycomb brazed between steel alloy face sheets. It varied in thickness from 0.5 inch to 2.5 inches. Part of the area between the inner and outer shells was filled with a layer of fiberglass insulation as additional heat protection.<ref name = "NASA CM">{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
Thermal protection (heat shield)Edit
An ablative heat shield on the outside of the CM protected the capsule from the heat of reentry, which is sufficient to melt most metals. This heat shield was composed of phenolic formaldehyde resin. During reentry, this material charred and melted away, absorbing and carrying away the intense heat in the process. 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.
The heat shield varied in thickness from Template:Convert in the aft portion (the base of the capsule, which faced forward during reentry) to Template:Convert in the crew compartment and forward portions. The total weight of the shield was about Template:Convert.<ref name = "NASA CM" />
Forward compartmentEdit
The Template:Convert-tall forward compartment was the area outside the inner pressure shell in the nose of the capsule, located around the forward docking tunnel and covered by the forward heat shield. The compartment was divided into four 90-degree segments that contained Earth landing equipment (all the parachutes, recovery antennas and beacon light, and sea recovery sling), two reaction control thrusters, and the forward heat shield release mechanism.
At about Template:Convert during reentry, the forward heat shield was jettisoned to expose the Earth landing equipment and permit deployment of the parachutes.<ref name = "NASA CM" />
Aft compartmentEdit
The Template:Convert-tall aft compartment was located around the periphery of the command module at its widest part, just forward of (above) the aft heat shield. The compartment was divided into 24 bays containing 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 ran from one module to the other, was also in the aft compartment. The panels of the heat shield covering the aft compartment were removable for maintenance of the equipment before flight.<ref name = "NASA CM" />
Earth landing systemEdit
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<ref>Hillje, Ernest R., "Entry Aerodynamics at Lunar Return Conditions Obtained from the Flight of Apollo 4 (AS-501)," NASA TN D-5399, (1969).</ref>). 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 Template:Convert, the forward heat shield was jettisoned using four pressurized-gas compression springs. The drogue parachutes were then deployed, slowing the spacecraft to Template:Convert. At Template:Convert the drogues were jettisoned and the pilot parachutes, which pulled out the mains, were deployed. These slowed the CM to Template:Convert for splashdown. The portion of the capsule that first contacted the water surface contained four crushable ribs to further mitigate the force of impact. The command module could safely parachute to an ocean landing with only two parachutes deployed (as occurred on Apollo 15), the third parachute being a safety precaution.
Reaction control systemEdit
The command module attitude control system consisted of twelve Template:Convert attitude control thrusters, ten of which were located in the aft compartment, plus two in the forward compartment. These were supplied by four tanks storing Template:Convert of monomethylhydrazine fuel and nitrogen tetroxide oxidizer, and pressurized by Template:Convert of helium stored at Template:Convert in two tanks.Template:Citation needed
HatchesEdit
The forward docking hatch was mounted at the top of the docking tunnel. It was Template:Convert in diameter and weighed Template:Convert, constructed from two machined rings that were weld-joined to a brazed honeycomb panel. The exterior side was covered with Template:Convert 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 Template:Convert high, Template:Convert wide, and weighed Template:Convert. It was operated by a pump handle, which drove a ratchet mechanism to open or close fifteen latches simultaneously.
Docking assemblyEdit
Apollo's mission required the LM to dock with the CSM on return from the Moon, and also in the transposition, docking, and extraction maneuver at the beginning of the translunar coast. The 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:Template:Citation needed
- Allow the two vehicles to connect, and attenuate excess movement and energy caused by docking
- Align and center the two vehicles and pull them together for capture
- Provide a rigid structural connection between both vehicles, and be capable of removal and re-installation by a single crewman
- Provide a means of remote separation of both vehicles for the return to Earth, using pyrotechnic fasteners at the circumference of the CSM docking collar
- Provide redundant power and logic circuits for all electrical and pyrotechnic components.
CouplingEdit
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.
RetractionEdit
After the initial capture and stabilization of the vehicles, the probe was capable of exerting a closing force of Template:Convert 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).
SeparationEdit
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.<ref>Template:Cite tech report</ref> When the command and lunar modules separated for the last time, 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 arrangementEdit
The central pressure vessel of the command module was its sole habitable compartment. It had an interior volume of Template:Convert 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 Template:Convert wide and Template:Convert 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 transposition, docking, and extraction maneuver with the LM, 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:
- The lower equipment bay, which housed the Guidance and Navigation computer, sextant, telescope, and Inertial Measurement Unit; various communications beacons; medical stores; an audio center; the S-band power amplifier; etc. There was also an extra rotation hand controller mounted on the bay wall, so the CM Pilot/navigator could rotate the spacecraft as needed while standing and looking through the telescope to find stars to take navigational measurements with the sextant. This bay provided a significant amount of room for the astronauts to move around in, unlike the cramped conditions which existed in the previous Mercury and Gemini spacecraft.
- The left-hand forward equipment bay, which contained 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, which housed 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, 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, waste management system, food and sanitary supplies, and a waste storage compartment.
- The aft storage bay, 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, 16mm camera equipment, and the contingency lunar sample container.
The CM had five windows. The two side windows measured Template:Convert square next to the left and right-hand couches. Two forward-facing triangular rendezvous windows measured Template:Convert, used to aid in rendezvous and docking with the LM. The circular hatch window was Template:Convert in diameter located 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.
SpecificationsEdit
- Crew: 3
- Crew cabin volume: Template:Convert living space, pressurized Template:Convert
- Length: Template:Convert
- Diameter: Template:Convert
- Mass: Template:Convert
- Structure mass: Template:Convert
- Heat shield mass: Template:Convert
- RCS engine mass: 12 × Template:Convert
- Recovery equipment mass: Template:Convert
- Navigation equipment mass: Template:Convert
- Telemetry equipment mass: Template:Convert
- Electrical equipment mass: Template:Convert
- Communications systems mass: Template:Convert
- Crew couches and provisions mass: Template:Convert
- Environmental Control System mass: Template:Convert
- Misc. contingency mass: Template:Convert
- RCS: twelve Template:Convert thrusters, firing in pairs
- RCS propellants: MMH/Template:Chem
- RCS propellant mass: Template:Convert
- Drinking water capacity: Template:Convert
- Waste water capacity: Template:Convert
- CO2 scrubber: 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 Template:Convert conical ribbon drogue parachutes; three Template:Convert ringslot pilot parachutes; three Template:Convert ringsail main parachutes<ref>West, Robert B., Apollo Experience Report: Earth Landing System, NASA Technical Note D-7437, p. 4, November 1973.</ref>
Sources:<ref name="CM_Astronautix.com">{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref name="ApolloByNumbers">Template:Cite book</ref>
Service module (SM)Edit
ConstructionEdit
The service module was an unpressurized cylindrical structure with a diameter of Template:Convert and Template:Convert long. The service propulsion engine nozzle and heat shield increased the total height to Template:Convert. The interior was a simple structure consisting of a central tunnel section Template:Convert 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.
- Sector 1 (50°) was originally unused, so it was filled with ballast to maintain the SM's center-of gravity.
- On the last three lunar landing (I-J class) missions, it carried the scientific instrument module (SIM) with a powerful Itek Template:Convert focal length camera originally developed for the Lockheed U-2 and SR-71 reconnaissance aircraft. The camera photographed the Moon; had the S-IVB failed to fire causing the CSM to not leave earth orbit, astronauts would have used it to photograph the Earth.<ref name="day20090526">{{#invoke:citation/CS1|citation
|CitationClass=web }}</ref><ref name="day20120611">Template:Cite news</ref> SIM also had other sensors and a subsatellite.
- Sector 2 (70°) contained the service propulsion system (SPS) oxidizer sump tank, so called because it directly fed the engine and was kept continuously filled by a separate storage tank, until the latter was empty. The sump tank was a cylinder with hemispherical ends, Template:Convert high, Template:Convert in diameter, and contained Template:Convert of oxidizer. Its total volume was Template:Cvt
- Sector 3 (60°) contained the SPS oxidizer storage tank, which was the same shape as the sump tank but slightly smaller at Template:Convert high and Template:Convert in diameter, and held Template:Convert of oxidizer. Its total volume was Template:Cvt
- Sector 4 (50°) contained the electrical power system (EPS) fuel cells with their hydrogen and oxygen reactants.
- Sector 5 (70°) contained the SPS fuel sump tank. This was the same size as the oxidizer sump tank and held Template:Convert of fuel.
- Sector 6 (60°) contained the SPS fuel storage tank, also the same size as the oxidizer storage tank. It held Template:Convert of fuel.
The forward fairing measured Template:Convert long and housed the reaction control system (RCS) computer, power distribution block, ECS controller, separation controller, and components for the high-gain antenna, and included eight EPS radiators and the umbilical connection arm containing 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 Template:Convert away as a navigation aid for rendezvous with the 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 umbilical 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 systemEdit
The service propulsion system (SPS) engine was originally designed to lift the CSM off the surface of the Moon in the direct ascent mission mode,<ref> Template:Cite book </ref> The engine selected was the AJ10-137,<ref> {{#invoke:citation/CS1|citation |CitationClass=web }}</ref> which used Aerozine 50 as fuel and nitrogen tetroxide (N2O4) as oxidizer to produce Template:Convert of thrust.<ref>Template:Cite book</ref> A contract was signed in April 1962 for the Aerojet-General company to start developing the engine, resulting in a thrust level twice what was needed to accomplish the lunar orbit rendezvous (LOR) mission mode officially chosen in July of that year.<ref> {{#invoke:citation/CS1|citation |CitationClass=web }}</ref> The engine was actually used for mid-course corrections between the Earth and Moon, and to place the spacecraft into and out of lunar orbit. It also served as a retrorocket to perform the deorbit burn for Earth orbital flights.
The propellants were pressure-fed to the engine by Template:Convert of gaseous helium at Template:Convert, carried in two Template:Convert diameter spherical tanks.<ref name="section24">{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
The exhaust nozzle measured Template:Convert long and Template:Convert 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 systemEdit
Four clusters of four reaction control system (RCS) thrusters (known as "quads") 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 measured Template:Convert long by Template:Convert diameter, generated Template:Convert of thrust, and used helium-fed monomethylhydrazine (MMH) as fuel and nitrogen tetroxide (NTO) as oxidizer.<ref>Template:Cite book</ref> Each quad assembly measured Template:Convert and had its own fuel, oxidizer, and helium tanks mounted on the inside of an Template:Convert skin panel. The primary fuel (MMH) tank contained Template:Convert; the secondary fuel tank contained Template:Convert; the primary oxidizer tank contained Template:Convert, and the secondary oxidizer tank contained Template:Convert. The propellant tanks were pressurized from a single tank containing Template:Convert of liquid helium.<ref name="SM2A Block II"/> Back flow was prevented by a series of check valves, and back flow and ullage requirements were resolved by containing the fuel and oxidizer in Teflon bladders which separated the propellants from the helium pressurant.<ref name="SM2A Block II">Template:Cite book</ref>
The four completely independent RCS clusters provided redundancy; only two adjacent functioning units were needed to allow complete attitude control.<ref name="SM2A Block II" />
The lunar module used a similar four-quad arrangement of R-4D thruster engines for its RCS.
Electrical power systemEdit
Electrical power was produced by three fuel cells, each measuring Template:Convert tall by Template:Convert in diameter and weighing Template:Convert. These combined hydrogen and oxygen to generate electrical power, and produced drinkable water as a byproduct. The cells were fed by two hemispherical-cylindrical Template:Convert diameter tanks, each holding Template:Convert of liquid hydrogen, and two spherical Template:Convert diameter tanks, each holding Template:Convert 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 obviate operation below 50% tank capacity. That allowed the elimination 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 had occurred when Apollo 12 was struck twice by lightning during launch.
Environmental control systemEdit
Cabin atmosphere was maintained at Template:Convert of pure oxygen from the same liquid oxygen tanks that fed the electrical power system's fuel cells. Potable water supplied by the fuel cells was stored for drinking and food preparation. A thermal control system using a mixture of water and ethylene glycol as coolant dumped waste heat from the CM cabin and electronics to outer space via two Template:Convert radiators located on the lower section of the exterior walls, one covering sectors 2 and 3 and the other covering sectors 5 and 6.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
Communications systemEdit
Short-range communications between the CSM and LM employed two VHF scimitar antennas mounted on the SM just above the ECS radiators. These antennas were originally located on the Block I command module and performed a double function as aerodynamic strakes to stabilize the capsule after a launch abort. The antennas were moved to the Block II service module when this function was found unnecessary.
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 Template:Convert diameter reflectors surrounding a single Template:Convert 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.
Four 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.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
SpecificationsEdit
- Length: Template:Convert
- Diameter: Template:Convert
- Mass: Template:Convert
- Structure mass: Template:Convert
- Electrical equipment mass: Template:Convert
- Service Propulsion (SPS) engine mass: Template:Convert
- SPS engine propellants: Template:Convert
- RCS thrust: 2 or 4 × Template:Convert
- RCS propellants: MMH/Template:Chem
- SPS engine thrust: Template:Convert
- SPS engine propellants: (UDMH/Template:Chem)/Template:Chem
- SPS Isp: 314 s (3,100 N·s/kg)
- Spacecraft delta-v: Template:Convert
- Electrical system: three 1.4 kW 30 V DC fuel cells
Modifications for Saturn IB missionsEdit
The payload capability of the Saturn IB launch vehicle 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 Template:Convert mass of the fully fueled CSM. This was not a problem, because the spacecraft 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 Template:Convert (Apollo–Soyuz), to Template:Convert (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.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }} </ref> 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.<ref> Template:Cite book </ref>
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 was also partially painted white, to provide passive thermal control for the extended time it would remain in orbit.
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.<ref name="missionreq">" Mission Requirements, Skylab Rescue Mission, SL-R" NASA, 24 August 1973.</ref>
Major differences between Block I and Block IIEdit
Command moduleEdit
- The Block II used a one-piece, quick-release, outward opening hatch instead of the two-piece plug hatch used on Block I, in which the inner piece had to be unbolted and placed inside the cabin in order to enter or exit the spacecraft (a flaw that doomed the Apollo 1 crew). The Block II hatch could be opened quickly in case of an emergency. (Both hatch versions were covered with an extra, removable section of the Boost Protective Cover which surrounded the CM to protect it in case of a launch abort.)
- The Block I forward access tunnel was smaller than Block II, and intended only for emergency crew egress after splashdown in case of problems with the main hatch. It was covered by the nose of the forward heat shield during flight. Block II contained a shorter forward heat shield with a flat removable hatch, beneath a docking ring and probe mechanism which captured and held the LM.
- The aluminized PET film layer, which gave the Block II heat shield a shiny mirrored appearance, was absent on Block I, exposing the light gray epoxy resin material, which on some flights was painted white.
- The Block I VHF scimitar antennas were located in two semicircular strakes originally thought necessary to help stabilize the CM during reentry. However, the uncrewed reentry tests proved these to be unnecessary for stability, and also aerodynamically ineffective at high simulated lunar reentry speeds. Therefore, the strakes were removed from Block II and the antennas were moved to the service module.
- The Block I CM/SM umbilical connector was smaller than on Block II, located near the crew hatch instead of nearly 180 degrees away from it. The separation point was between the modules, instead of the larger hinged arm mounted on the service module, separating at the CM sidewall on Block II.
- The two negative pitch RCS engines located in the forward compartment were arranged vertically on Block I, and horizontally on Block II.
Service moduleEdit
- On the Apollo 6 uncrewed Block I flight, the SM was painted white to match the command module's appearance. On Apollo 1, Apollo 4, and all the Block II spacecraft, the SM walls were left unpainted except for the EPS and ECS radiators, which were white.
- The EPS and ECS radiators were redesigned for Block II. Block I had three larger EPS radiators located on Sectors 1 and 4. The ECS radiators were located on the aft section of Sectors 2 and 5.
- The Block I fuel cells were located at the aft bulkhead in Sector 4, and their hydrogen and oxygen tanks were located in Sector 1.
- Block I had slightly longer SPS fuel and oxidizer tanks which carried more propellant than Block II.
- The Block II aft heat shield was a rectangular shape with slightly rounded corners at the propellant tank sectors. The Block I shield was the same basic shape, but bulged out slightly near the ends more like an hourglass or figure eight, to cover more of the tanks.
CSMs producedEdit
| Serial number | Name | Use | Launch date | Current location | Image | |||
|---|---|---|---|---|---|---|---|---|
| Block I<ref name="MajorEndItems" /><ref name="CSM Contract" /><ref name="FieldGuide">{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> | |||||||
| CSM-001 | systems compatibility test vehicle | scrappedTemplate:Sfn | ||||||
| CSM-002 | A-004 flight | January 20, 1966 | Command module on display at Cradle of Aviation, Long Island, New York<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:CM-002 at Cradle of Aviation Museum, Garden City, NY.jpg | |||
| CSM-004 | static and thermal structural ground tests | scrapped<ref name="FieldGuide" /> | ||||||
| CSM-006 | used for demonstrating tumbling debris removal system | Command module scrapped;Template:Sfn service module (redesignated as SM-010)<ref name="CSM Contract" /> on display at U.S. Space & Rocket Center, Huntsville, AlabamaTemplate:Sfn | File:CM-010 at U.S. Space & Rocket Center, Huntsville, AL.jpg | |||||
| CSM-007 | various tests including acoustic vibration and drop tests, and water egress training. CM was refitted with Block II improvements.<ref>These included the crew couches, quick escape hatch, and metallic heat shield coating. See Apollo command module (image @ Wikimedia Commons).</ref> Underwent testing for Skylab at the McKinley Climatic Laboratory, Eglin AFB, Florida, 1971–1973. | Command module on display at Museum of Flight, Seattle, Washington<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:ApolloCommandModule1.jpg | ||||
| CSM-008 | complete systems spacecraft used in thermal vacuum tests | scrappedTemplate:Sfn | File:Command Sevice Module in vacuum chamber.jpg | |||||
| 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<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:AS201 Command Module.jpg | |||
| CSM-010 | Thermal test (command module redesignated as CM-004A / BP-27 for dynamic tests);Template:Sfn service module never completed<ref name="CSM Contract" /> | Command module on display at U.S. Space & Rocket Center, Huntsville, AlabamaTemplate:Sfn | File:CM-010 at U.S. Space & Rocket Center, Huntsville, AL.jpg | |||||
| 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<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:USS Hornet Apollo CM.jpg | |||
| 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;<ref>Template:Cite news</ref> three-part door hatch on display at Kennedy Space Center;<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> service module scrappedTemplate:Sfn |
File:Apollo 1's Command Module - GPN-2003-00057.jpg | ||||
| CSM-014 | Command module disassembled as part of Apollo 1 investigation. Service module (SM-014) used on Apollo 6 mission. Command module (CM-014) later modified and used for ground testing (as CM-014A).<ref name="CSM Contract">{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
Scrapped May 1977.<ref name="MajorEndItems">Template:Cite book, p. 4</ref> | |||||
| CSM-017 | CM-017 flew on Apollo 4 with SM-020 after SM-017 was destroyed in a propellant tank explosion during ground testing.<ref name="CSM Contract" /><ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
November 9, 1967 | Command module on display at Stennis Space Center, Bay St. Louis, Mississippi<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:Apollo 4 Stennis Space Center.JPG | ||
| CSM-020 | CM-020 flew on Apollo 6 with SM-014.<ref name="CSM Contract" /> | April 4, 1968 | Command module on display at Fernbank Science Center, Atlanta | File:Fernbank-07.jpg | ||||
| Block II<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref><ref name="NASM List">{{#invoke:citation/CS1|citation |
CitationClass=web
}}</ref> | ||||||
| CSM-098 | 2TV-1 (Block II Thermal Vacuum no.1)Template:Sfn | used in thermal vacuum tests | CSM on display at Academy of Science Museum, Moscow, Russia as part of the Apollo Soyuz Test Project display.<ref name="FieldGuide" /> | File:Apollo-Soyuz display at the RKK Energia Museum.jpg | ||||
| CM-099 | 2S-1Template:Sfn | Skylab flight crew interface training;Template:Sfn impact tests<ref name="CSM Contract" /> | scrappedTemplate:Sfn | |||||
| CSM-100 | 2S-2Template:Sfn | static structural testing<ref name="CSM Contract" /> | Command module "transferred to Smithsonian as an artifact", service module on display at New Mexico Museum of Space HistoryTemplate:Sfn | |||||
| CSM-101 | Apollo 7 | October 11, 1968 | Command module was on display at National Museum of Science and Technology, Ottawa, Ontario, Canada from 1974 until 2004, now at the Frontiers of Flight Museum, Dallas, Texas after 30 years of being on loan.<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:Apollo 7 Phoenix Frontiers of Flight Museum.JPG | |||
| CSM-102 | Launch Complex 34 checkout vehicle | Command module scrapped;Template:Sfn service module is at JSC on top of the Little Joe II in Rocket Park with Boiler Plate 22 command module.<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:SM-102 with BP22 and Little Joe II at Johnson Space Center, Houston, TX.jpg | ||||
| CSM-103 | Apollo 8 | December 21, 1968 | Command module on display at the Museum of Science and Industry in Chicago<ref name="NASM List" /> | File:Apollo 8 command module.jpg | ||||
| CSM-104 | Gumdrop | Apollo 9 | March 3, 1969 | Command module on display at San Diego Air and Space Museum<ref name="NASM List" /> | File:Apollo 9 Command Module.jpg | |||
| CSM-105 | acoustic tests | On display at National Air and Space Museum, Washington, D.C. as part of the Apollo Soyuz Test Project display.Template:Sfn (Photo) | File:Soyuz replica at smithsonian - from-DC1.jpg | |||||
| CSM-106 | Charlie Brown | Apollo 10 | May 18, 1969 | Command module on display at Science Museum, London<ref name="NASM List" /> | File:Apollo 10 Command Module 1.jpg | |||
| CSM-107 | Columbia | Apollo 11 | July 16, 1969 | Command module on display at National Air and Space Museum, Washington, D.C.<ref name="NASM List" /> | File:Apollo11Smithonian.JPG | |||
| CSM-108 | Yankee Clipper | Apollo 12 | November 14, 1969 | Command module on display at Virginia Air & Space Center, Hampton, Virginia;<ref name="NASM List" /> previously on display at the National Naval Aviation Museum at Naval Air Station Pensacola, Pensacola, Florida (exchanged for CSM-116) | File:Apollo12 CommandModule Hampton.JPG | |||
| CSM-109 | Odyssey | Apollo 13 | April 11, 1970 | Command module on display at Kansas Cosmosphere and Space Center<ref name="NASM List" /> | File:Apollo13 CommandModule Kansas.JPG | |||
| CSM-110 | Kitty Hawk | Apollo 14 | January 31, 1971 | Command module on display at the Kennedy Space Center<ref name="NASM List" /> | File:Apollo 14 Command Module "Kitty Hawk".JPG | |||
| CSM-111 | Apollo Soyuz Test Project | July 15, 1975 | Command module currently on display at California Science Center in Los Angeles, California<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref><ref>{{#invoke:citation/CS1|citation |
CitationClass=web
}}</ref><ref>{{#invoke:citation/CS1|citation |
CitationClass=web
}}</ref> (formerly displayed at the Kennedy Space Center Visitor Complex) |
File:California Science Center (8089345453).jpg | |
| 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<ref name="NASM List" /> | File:Apollo 15 Command Module at the National Museum of the United States Air Force.jpg | |||
| CSM-113 | Casper | Apollo 16 | April 16, 1972 | Command module on display at U.S. Space & Rocket Center, Huntsville, Alabama<ref name="NASM List" /> | File:Apollo16 CommandModule Huntsville.JPG | |||
| CSM-114 | America | Apollo 17 | December 7, 1972 | Command module on display at Space Center Houston, Houston, Texas<ref name="NASM List" /> | File:Apollo 17 America Space Center Houston.JPG | |||
| CSM-115 | Apollo 19<ref>Template:Cite book</ref> (canceled) | Never fully completed<ref name=":0" /> – service module does not have its SPS nozzle installed. On display as part of the Saturn V display at Johnson Space Center, Houston, Texas<ref>Template:Cite news</ref> | File:SATURN V Rocket Lyndon B. Johnson Space Center Johnson Space Center JSC NASA Houston Space City(24118629963).jpg | |||||
| CSM-115a | Apollo 20<ref>Template:Cite book</ref> (canceled) | Never fully completed<ref name=":0">Template:Cite book</ref> – internal structures not installed,<ref>Template:Cite book</ref> used for spare parts. Remaining items sent to Japan for exhibition in 1978 and never returned, possibly scrapped.<ref>Template:Cite book</ref><ref>Template:Harvnb</ref> | ||||||
| CSM-116 | Skylab 2 | May 25, 1973 | Command module on display at National Museum of Naval Aviation, Naval Air Station Pensacola, Pensacola, Florida<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:SKYLAB 1 SL-2 National Museum of Naval Aviation.JPG | |||
| 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<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
File:SKYLAB 2 SL-3 Glenn Research Center, Cleveland, Ohio.JPG | |||
| CSM-118 | Skylab 4 | November 16, 1973 | Command module on display at Oklahoma History Center<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> (formerly displayed at the National Air and Space Museum, Washington, D.C.)<ref>{{#invoke:citation/CS1|citation |
CitationClass=web
}}</ref> |
File:SKYLAB 3 SL-4 National Air & Space Museum, Washington DC.JPG | ||
| CSM-119 | Skylab Rescue and ASTP backup | On display at the Kennedy Space CenterTemplate:Sfn | File:CSM-119 Skylab Rescue Kennedy Space Center, FL.JPG | |||||
.jpg){kind=link}
.jpg){kind=link}
See alsoEdit
- Orbital module
- Reentry capsule
- Space capsule
- Space suit
- Space exploration
- U.S. Space Exploration History on U.S. Stamps
- Apollo Lunar Module
- Mars Piloted Orbital Station
FootnotesEdit
Notes Template:Notelist Citations Template:Reflist
{{#invoke:navbox|navbox | name = Apollo program | title = Apollo program | state = autocollapse | image = Emblem of the Apollo program | bodyclass = hlist | above =
| below =
- Symbol † indicates failure or partial failure
| group1 = Launch complexes | list1 =
| group2 = Ground facilities | list2 =
- Mission Control Center
- Cape Kennedy Air Force Station
- Crawler-transporter
- Kennedy Space Center
- Manned Space Flight Network
| group3 = Launch vehicles | list3 =
| group4 = Spacecraft and rover | list4 =
| group5 = Flights | list5 = {{#invoke:navbox|navbox|child
| group1 = Uncrewed | list1 =
| group2 = Crewed | list2 =
- Apollo 1†
- Apollo 7
- Apollo 8
- Apollo 9
- Apollo 10
- Apollo 11
- Apollo 12
- Apollo 13†
- Apollo 14
- Apollo 15
- Apollo 16
- Apollo 17
| group5 = Saturn
development
| list5 =
| group6 = Abort tests | list6 =
| group7 = Pegasus flights | list7 =
}}
|group6 = Apollo 8 specific |list6 =
|group7 = Apollo 11 specific |list7 =
- Command Module Columbia
- Lunar Module Eagle
- Tranquility Base
- Double crater
- Little West crater
- Goodwill messages
- Lunar sample displays
- Missing tapes
- Anniversaries
- In popular culture
|group8 = Apollo 12 specific |list8 =
- Statio Cognitum
- Bench Crater meteorite
- J002E3
- Moon Museum
- Reports of Streptococcus mitis on the Moon
|group9 = Apollo 13 specific |list9 =
|group10 = Apollo 14 specific |list10 =
|group11 = Apollo 15 specific |list11 =
- Journey
- Lunar operations
- Solo operations
- Return to Earth
- Hadley–Apennine
- Fallen Astronaut
- Genesis Rock
- Great Scott
- Hadley Rille meteorite
- Seatbelt basalt
- Postal covers incident
|group12 = Apollo 16 specific |list12 =
|group13 = Apollo 17 specific |list13 =
- The Blue Marble
- Taurus–Littrow
- Tracy's Rock
- Nansen-Apollo crater
- Shorty crater
- Lunar sample display
- Troctolite 76535
- Apollo Lunar Sounder Experiment
- Fe, Fi, Fo, Fum, and Phooey
|group14 = Post-Apollo
capsule use
|list14 =
|group15 = Related |list15 =
}} Template:Apollo program hardware Template:Crewed spacecraft Template:Crewed lunar spacecraft {{#invoke:Navbox|navbox}} Template:NASA space program Template:People who have traveled to the Moon