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Manned spacecraft module
| Gemini AM American manned spacecraft module. 12 launches, 1964.04.08 (Gemini 1) to 1966.11.11 (Gemini 12). |
| Gemini EM American manned spacecraft module. 12 launches, 1964.04.08 (Gemini 1) to 1966.11.11 (Gemini 12). |
| Gemini RM American manned spacecraft module. 12 launches, 1964.04.08 (Gemini 1) to 1966.11.11 (Gemini 12). |
| Apollo CM American manned spacecraft module. 22 launches, 1964.05.28 (Saturn 6) to 1975.07.15 (Apollo (ASTP)). |
| Apollo SM American manned spacecraft module. 22 launches, 1964.05.28 (Saturn 6) to 1975.07.15 (Apollo (ASTP)). |
| Apollo LM DS American manned spacecraft module. 10 launches, 1968.01.22 (Apollo 5) to 1972.12.07 (Apollo 17). |
| Apollo LM AS American manned spacecraft module. 10 launches, 1968.01.22 (Apollo 5) to 1972.12.07 (Apollo 17). |
| Mercury Capsule American manned spacecraft module. 18 launches, 1960.01.21 (Mercury LJ-1B) to 1963.05.15 (Mercury MA-9). Reentry capsule. |
| Mercury Retropack American manned spacecraft module. 18 launches, 1960.01.21 (Mercury LJ-1B) to 1963.05.15 (Mercury MA-9). |
| Vostok SA Russian manned spacecraft module. Reentry capsule. |
| Vostok PO Russian manned spacecraft module. Equipment section. |
| Apollo Direct CM American manned spacecraft module. Study 1961. Conventional spacecraft structures were employed, following the proven materials and concepts demonstrated in the Mercury and Gemini designs. |
| Apollo Direct RM American manned spacecraft module. Study 1961. The retrograde module supplied the velocity increments required during the translunar portion of the mission up to a staging point approximately 1800 m above the lunar surface. |
| Apollo Direct SM American manned spacecraft module. Study 1961. The Service Module housed the fuel cells, environmental control, and other major equipment items required for the mission. |
| Apollo Direct TLM American manned spacecraft module. Study 1961. Final letdown, translation hover and landing on the lunar surface from 1800 m above the surface was performed by the terminal landing module. Engine thrust could be throttled down to 1546 kgf. |
| Soyuz A SA Russian manned spacecraft module. Study 1962. Original Soyuz design, allowing crew of three without spacesuits. Reentry capsule. |
| Soyuz A BO Russian manned spacecraft module. Study 1962. Original design with notional docking system with no probe and internal transfer tunnel. Living section. |
| Soyuz A PAO Russian manned spacecraft module. Study 1962. Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system but with no base flange for a shroud. Equipment-engine section. |
| Dynasoar Glider American manned spacecraft module. Cancelled 1963. Manned space plane. |
| Dynasoar AS American manned spacecraft module. Cancelled 1963. Abort Section, equipped with Thiokol XM-92 Minuteman Stage II motor. Contingency boost. |
| Gemini Ferry AM American manned spacecraft module. Study 1963. |
| Gemini Ferry CM American manned spacecraft module. Study 1963. |
| Gemini Ferry RM American manned spacecraft module. Study 1963. |
| Voskhod SA Russian manned spacecraft module. Study 1965. Reentry capsule. |
| Voskhod PO Russian manned spacecraft module. Study 1965. Equipment section. |
| Voskhod KDU Russian manned spacecraft module. Study 1965. Auxiliary Retrorocket. |
| LK-1 VA Russian manned spacecraft module. Cancelled 1965. Total internal volume 8.37 m3. Assumes capsule was similar to TKS VA. Reentry Capsule. |
| LK-1 PAO Russian manned spacecraft module. Cancelled 1965. Calculated masses, specific impulse based on mission requirements and drawing of spacecraft. Equipment-engine section. |
| Gemini LSRS AM American manned spacecraft module. Study 1966. Calculated mass based on mission requirements, drawing of spacecraft, dimensions of propellant tanks. |
| Gemini LSRS LM American manned spacecraft module. Study 1966. Calculated mass based on mission requirements, drawing of spacecraft, dimensions of propellant tanks. |
| Gemini LSRS LOIM American manned spacecraft module. Study 1966. Calculated mass based on mission requirements, drawing of spacecraft, dimensions of propellant tanks. |
| Gemini LSRS RM American manned spacecraft module. Study 1966. Calculated mass based on mission requirements, drawing of spacecraft. |
| LLV L-I American manned spacecraft module. Study 1966. Lunar Orbit Insertion stage for placing LLV into lunar orbit. Propulsion 2 x RL10-A3 with N2O4/MMH thrusters for orientation, midcourse, and ullage. Lunar orbit insertion of Lunar Logistics Vehicle lander and payload. |
| LLV L-II American manned spacecraft module. Study 1966. Landing stage for delivery of up to 13,400 kg payload from lunar orbit to lunar surface. Propulsion 2 x RL10-A3 with N2O4/MMH thrusters for orientation, midcourse, and ullage. Delivery of lunar base elements from lunar orbit to lunar surface. |
| Soyuz 7K-OK SA Russian manned spacecraft module. 17 launches, 1966.11.28 (Cosmos 133) to 1970.06.01 (Soyuz 9). Post-Soyuz 1 modification, allowing crew of three without spacesuits. Analogue sequencer and computers operate spacecraft. Reentry capsule. |
| Soyuz 7K-OK BO Russian manned spacecraft module. 17 launches, 1966.11.28 (Cosmos 133) to 1970.06.01 (Soyuz 9). Heavy-duty male/female docking system with no internal transfer tunnel. Igla automatic rendezvous and docking system. Living section. |
| Soyuz 7K-OK PAO Russian manned spacecraft module. 17 launches, 1966.11.28 (Cosmos 133) to 1970.06.01 (Soyuz 9). Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section. |
| Gemini Lunar RM American manned spacecraft module. Study 1967. Calculated mass based on mission requirements, drawing of spacecraft. |
| Gemini LSSS LM American manned spacecraft module. Study 1967. Calculated mass based on mission requirements, drawing of spacecraft, dimensions of propellant tanks. |
| Gemini LSSS SM American manned spacecraft module. Study 1967. Calculated mass based on mission requirements, drawing of spacecraft. |
| Gemini LORV RM American manned spacecraft module. Study 1967. Calculated mass based on mission requirements, drawing of spacecraft. |
| Gemini LORV SM American manned spacecraft module. Study 1967. Calculated mass based on mission requirements, drawing of spacecraft, dimensions of propellant tanks. |
| Soyuz 7K-L1 SA Russian manned spacecraft module. 12 launches, 1967.03.10 (Cosmos 146) to 1970.10.20 (Zond 8). Increased heat shield protection and presumably reaction control system propellant for re-entry from lunar distances. Reentry capsule. |
| Soyuz 7K-L1 SOK Russian manned spacecraft module. 12 launches, 1967.03.10 (Cosmos 146) to 1970.10.20 (Zond 8). Separates before trans-lunar injection. Jettisonable support cone. |
| Soyuz 7K-L1 PAO Russian manned spacecraft module. 12 launches, 1967.03.10 (Cosmos 146) to 1970.10.20 (Zond 8). Modification of Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section. |
| EEM American manned spacecraft module. Study 1968. Re-entry at extreme velocities from manned interplanetary missions. |
| LK-700 Block 1 Russian manned spacecraft module. Study 1968. Three identical stages of 34,491 kg each clustered around the core. Translunar Injection Stage. |
| LK-700 Block 11 Russian manned spacecraft module. Study 1968. Differed from the lateral Block 1 stages in having an engine unit for orientation of the assembly. Main engine of 23,500 kgf and three engines for soft landing / midcourse maneuvers of 1,670 kgf each. Midcourse man oeuvre/lunar braking stage. |
| LK-700 Block 111 Russian manned spacecraft module. Study 1968. Soft Landing Stage. |
| LK-700 VA Russian manned spacecraft module. Study 1968. VA Re-entry Capsule. |
| LK-700 Block 1V Russian manned spacecraft module. Study 1968. Main engine of 13,400 kgf and three engines for soft landing / midcourse maneuvers of 1,670 kgf each. Trans-earth injection / midcourse man oeuvre stage. |
| Big Gemini AM American manned spacecraft module. Reached mockup stage 1967. Earth orbit maneuver and retrofire. |
| Big Gemini CM American manned spacecraft module. Reached mockup stage 1967. Space station resupply. |
| Big Gemini RV American manned spacecraft module. Reached mockup stage 1967. Crew and cargo return. |
 | Gemini B AM American manned spacecraft module. Cancelled 1969. Adapter module for Gemini B, the engines serving as both abort motors during ascent to orbit and for retrofire on return to earth. Abort/deorbit propulsion. |
| LOK PAO Russian manned spacecraft module. 2 launches, 1971.06.26 (N-1 6L) to 1972.11.23 (LOK). Unique PAO developed for Soyuz lunar orbiter. Powerful sophisticated engine for lunar orbit rendezvous maneuvers and trans-earth injection. Equipment-engine section. |
| Soyuz 7K-LOK SA Russian manned spacecraft module. 2 launches, 1971.06.26 (N-1 6L) to 1972.11.23 (LOK). Increased heat shield protection and presumably reaction control system propellant for re-entry from lunar distances. Reentry capsule. |
| Soyuz 7K-OKS SA Russian manned spacecraft module. 2 launches, 1971.04.23 (Soyuz 10) to 1971.06.06 (Soyuz 11). Post-Soyuz 1 modification, allowing crew of three without spacesuits. Analogue sequencer and computers operate spacecraft. Reentry capsule. |
| Soyuz 7K-LOK BO Russian manned spacecraft module. 2 launches, 1971.06.26 (N-1 6L) to 1972.11.23 (LOK). Living section. |
| Soyuz 7K-OKS BO Russian manned spacecraft module. 2 launches, 1971.04.23 (Soyuz 10) to 1971.06.06 (Soyuz 11). Lightweight male/female docking system with roller-type probe, internal transfer tunnel. Living section. |
| Soyuz 7K-OKS PAO Russian manned spacecraft module. 2 launches, 1971.04.23 (Soyuz 10) to 1971.06.06 (Soyuz 11). Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section. |
| Soyuz 7K-T SA Russian manned spacecraft module. 23 launches, 1972.06.26 (Cosmos 496) to 1981.05.14 (Soyuz 40). Post-Soyuz 11 modification for crew of two in spacesuits. Reentry capsule. |
| Soyuz 7K-T BO Russian manned spacecraft module. 23 launches, 1972.06.26 (Cosmos 496) to 1981.05.14 (Soyuz 40). Lightweight male/female docking system with roller-type probe, internal transfer tunnel (Collar Length: 0.22 m. Probe Length: 0. Living section. |
| Soyuz 7K-T PAO Russian manned spacecraft module. 23 launches, 1972.06.26 (Cosmos 496) to 1981.05.14 (Soyuz 40). Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section. |
| LEK SA Russian manned spacecraft module. Study 1973. Descent module was contained within pressurized cabin of LEK ascent stage. Crew may have entered hatch in heat shield. Landing apparatus - Reentry capsule for crew and lunar samples. |
| LEK PS Russian manned spacecraft module. Study 1973. Descent stage very similar in appearance to that of Apollo LM, with same function - descent from lunar orbit to landing of crewed module on surface of moon. Landing stage - Carry LEK ascent stage from lunar orbit to lunar surface; act as launching platform for LEK ascent stage. |
| LEK VS Russian manned spacecraft module. Study 1973. Ascent stage, carried a crew of three from the lunar surface to trans-earth trajectory. Contained within the pressurized cabin was a Soyuz descent module for reentry by the crew into the earth's atmosphere. Ascent stage - Carry crew and Soyuz descent module from lunar surface to trans-earth trajectory. Provide crew quarters and midcourse corrections during return journey from lunar surface to earth. |
| Soyuz ASTP SA Russian manned spacecraft module. 4 launches, 1974.04.03 (Cosmos 638) to 1975.07.15 (Soyuz 19 (ASTP)). Post-Soyuz 11 modification for crew of two in spacesuits. Reentry capsule. |
| Soyuz ASTP BO Russian manned spacecraft module. 4 launches, 1974.04.03 (Cosmos 638) to 1975.07.15 (Soyuz 19 (ASTP)). Universal docking system designed for ASTP with three petaled locating system and internal transfer tunnel. No automated rendezvous and docking system. Living section. |
| Soyuz ASTP PAO Russian manned spacecraft module. 4 launches, 1974.04.03 (Cosmos 638) to 1975.07.15 (Soyuz 19 (ASTP)). Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section. |
 | TKS VA Russian manned spacecraft module. The VA reentry capsule was similar in configuration to the American Apollo, but 30% smaller. Reusable re-entry capsule. |
| Soyuz 7K-MF6 SA Russian manned spacecraft module. One launch, 1976.09.15, Soyuz 22. Post-Soyuz 11 modification for crew of two in spacesuits. Reentry capsule. |
| Soyuz 7K-MF6 BO Russian manned spacecraft module. One launch, 1976.09.15, Soyuz 22. MKF6 Camera replaced docking system and Igla automatic rendezvous and docking system deleted. Four windows, BO separated after retrofire. Living section. |
| Soyuz 7K-MF6 PAO Russian manned spacecraft module. One launch, 1976.09.15, Soyuz 22. Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section. |
| TKS FGB Russian manned spacecraft module. 4 launches, 1977.07.17 (Cosmos 929) to 1985.09.27 (Cosmos 1686). Orbital Living and Service Module. |
| TKS BSO Russian manned spacecraft module. 4 launches, 1977.07.17 (Cosmos 929) to 1985.09.27 (Cosmos 1686). The BSO was equipped with the retro-rocket for deorbit of the VA capsule following separation from the space station. Deorbit Block. |
| TKS SAS Russian manned spacecraft module. 4 launches, 1977.07.17 (Cosmos 929) to 1985.09.27 (Cosmos 1686). Emergency escape system. |
| Progress OKD Russian manned spacecraft module. 43 launches, 1978.01.20 (Progress 1) to 1990.05.06 (Progress 42). Fuel module for refueling space stations. |
| Progress GO Russian manned spacecraft module. 43 launches, 1978.01.20 (Progress 1) to 1990.05.06 (Progress 42). Igla automatic rendezvous and docking system. Cargo section. |
| Progress PAO Russian manned spacecraft module. 43 launches, 1978.01.20 (Progress 1) to 1990.05.06 (Progress 42). Derived from Soyuz 7K-OK basic PAO service module with pump-fed main engines and separate RCS/main engine propellant feed system. Equipment-engine section. |
| Soyuz T SA Russian manned spacecraft module. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Significantly improved Soyuz re-entry capsule, based on development done in Soyuz 7K-S program. Accommodation for crew of three in spacesuits. Reentry capsule. |
| Soyuz T BO Russian manned spacecraft module. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Lightweight male/female docking system with flange-type probe, internal transfer tunnel. Igla automatic rendezvous and docking system. Living section. |
| Soyuz T PAO Russian manned spacecraft module. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Improved PAO service module derived from Soyuz 7K-S with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section. |
| Soyuz TM SA Russian manned spacecraft module. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). Significantly improved Soyuz re-entry capsule, based on development done in Soyuz 7K-S program. Accommodation for crew of three in spacesuits. Reentry capsule. |
| Soyuz TM BO Russian manned spacecraft module. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). Lightweight male/female docking system with flange-type probe, internal transfer tunnel. Kurs automatic rendezvous and docking system . Living section. |
| Soyuz TM PAO Russian manned spacecraft module. 34 launches, 1986.05.21 (Soyuz TM-1) to 2002.04.25 (Soyuz TM-34). Further improvement of Soyuz T PAO service module with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section. |
| Kvant FGB Russian manned spacecraft module. One launch, 1987.03.31 (Kvant 1). Used only once, tug docked Kvant module to station, then separated and was commanded to destructive reentry over Pacific Ocean. Space station module tug. |
| MRC DM British manned spacecraft module. Study 1987. Reusable re-entry capsule. |
| MRC SM British manned spacecraft module. Study 1987. Expendable equipment section. |
| LOK Energia SA Russian manned spacecraft module. Study 1988. Descent module of Soyuz configuration but 50% larger dimensionally and nearly twice as heavy. Reentry capsule for crew and lunar samples. |
| LOK Energia PAO Russian manned spacecraft module. Study 1988. The LOK provided a pressurized volume for three crew. Within the cabin was a descent module of the same configuration as Soyuz, but almost 50% larger. Equipment-engine section - Lunar orbit maneuver, trans-orbit propulsion, pressurized crew quarters. |
| LK Energia PS Russian manned spacecraft module. Study 1988. Descent stage similar in appearance to Apollo LM and LEK stages, but of differing dimensions. Descent from lunar orbit to lunar surface, launch platform for ascent stage. |
| LK Energia VS Russian manned spacecraft module. Study 1988. Although similar in appearance to LEK ascent stage, 80% smaller and no descent module for reentry into earth's atmosphere. Ascent from lunar surface to lunar orbit, dock with LOK Energia. |
| Progress M OKD Russian manned spacecraft module. Operational, first launch 1989.08.23 (Progress M-1). Fuel module for refueling space stations. |
| Progress M GO Russian manned spacecraft module. Operational, first launch 1989.08.23 (Progress M-1). Two Kurs-type rendezvous antennas. Cargo section. |
| Progress M PAO Russian manned spacecraft module. Operational, first launch 1989.08.23 (Progress M-1). Improved PAO service module derived from Soyuz 7K-S with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section. |
| Zarya VA Russian manned spacecraft module. Cancelled 1989. The Zarya landing module was enlarged from the Soyuz 2.4 m diameter to 4.1 m diameter, while keeping the same shape and L/D coefficient of 0.26 at Mach 6. Reusable re-entry capsule. |
| Zarya NO Russian manned spacecraft module. Cancelled 1989. Maneuver system consisted of two engines, each of 300 kgf. Expendable module for orbital maneuvering and experiments. |
| Progress M VBK Russian manned spacecraft module. Two launched, 1993-1994. This payload return capsule was brought to the Mir space station aboard a Progress M freighter. It was loaded by the cosmonauts aboard the station, then reinstalled in the Progress M. Ballistic landing capsule - return of experimental materials from Mir space station. |
 | Shenzhou SM Chinese manned spacecraft module. Operational, first launch 1999.11.19. The service module, developed by the Shanghai Academy of Space Technology, provides the electrical power, attitude, control and propulsion for the spacecraft in orbit. |
 | Shenzhou RV Chinese manned spacecraft module. Operational, first launch 1999.11.19. The re-entry vehicle was conceptually based on the Soyuz, but was not a copy. |
| Soyuz TMA SA Russian manned spacecraft module. Operational. First launch 2002.10.30. Reentry capsule. |
| Soyuz TMA BO Russian manned spacecraft module. Operational. First launch 2002.10.30. Lightweight male/female docking system with flange-type probe, internal transfer tunnel. Kurs automatic rendezvous and docking system with two Kurs antennae, no tower. Living section. |
| Soyuz TMA PAO Russian manned spacecraft module. Operational. First launch 2002.10.30. Further improvement of Soyuz T PAO service module with pressure-fed main engines and unitary RCS/main engine propellant feed system. Equipment-engine section. |
 | Shenzhou OM Chinese manned spacecraft module. The orbital module provided quarters for the crew during the space mission, and could be fitted out with different internal and external equipment according to mission requirements. |
 | CEV CM American manned spacecraft module. Study 2006. |
| CEV SM American manned spacecraft module. Study 2006. The Service Module of NASA's Crew Exploration Vehicle provided basic consumables, control systems, and sufficient delta-V for return of the CEV from lunar orbit to the earth. |
| CEV Andrews MM American manned spacecraft module. Study 2005. The Andrews CEV mission module provided a pressurized cabin for use by the crew while in transit from the moon to the earth. |
| CEV Andrews OTV American manned spacecraft module. Study 2005. The Andrews CEV used a standard Orbital Transfer Vehicle for propulsion in low earth orbit or lunar transfer operations. |
| CEV Andrews RM American manned spacecraft module. Study 2005. The Andrews CEV Re-entry Module would be reusable and normally accommodate four crew. Six could be fitted in for the space-station ferry role. |
| CEV Spacehab CM American manned spacecraft module. Study 2005. A 10% enlargement of the Apollo capsule, this re-entry vehicle provided the minimum volume for four crew to make re-entry from lunar distances. |
| CEV Spacehab SHM American manned spacecraft module. Study 2005. The Stowage/Habitation Module (SHM) provided generous living space for the crew during cislunar transit. |
| CEV Spacehab SM American manned spacecraft module. Study 2005. The Support Module (SM) could provide 2.3 km/s delta-V, enough for lunar orbit insertion and trans-earth injection. It also was the primary source for electrical power during the mission. |
 | Orion CM American manned spacecraft module. Orion re-entry vehicle (crew module). A 25% scale-up of the Apollo capsule of the 1960's. |
 | Orion SM American manned spacecraft module. Orion service module. Masses estimated based on delta-V released by NASA. |
| Orion SA American manned spacecraft module. Orion spacecraft adapter. Transition section between Service Module and Ares booster. |
 | Orion LAS American manned spacecraft module. Orion launch abort system; consists of launch escape tower, adapter cone, and boost protective cover. Provides emergency crew escape during early boost phase of ascent to orbit. |
| CTV CM European manned spacecraft module. Study 2008. Re-entry vehicle portion of the proposed European CTV manned spacecraft. |
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