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timelines:spacecraft_and_launch_vehicle_technical_data [2012/05/04 17:11]
Michel Van 		timelines:spacecraft_and_launch_vehicle_technical_data [2013/04/24 12:29] (current)
Petike
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-====== Eyes Turned Skyward ======+====== Eyes Turned Skyward : Spacecraft and Launch Vehicle Data======
-This page lists major spacecraft, space stations, and launch vehicles for the [[Eyes Turned Skywards|Eyes Turned Skyward]] timeline.+This page lists major spacecraft, space stations, and launch vehicles for the //**[[Eyes Turned Skywards|Eyes Turned Skyward]]**// timeline.
===== American Launch Vehicles ===== ===== American Launch Vehicles =====
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=== Delta 4000 === === Delta 4000 ===
-Winner of the ELVRP I competition for a new small-medium class launch vehicle to replace Atlas, (existing) Delta, Titan IIIB, and other ICBM or IRBM-derived launch vehicles in the 1980s ([[http://www.alternatehistory.com/discussion/showpost.php?p=5365658&postcount=170|Post 16]]). Derived from older Delta designs, it however uses a Centaur-derived upper stage rather than the previous hypergolic or solid upper stages. With the same family of Castor strap-on boosters, this significantly improves its potential maximum payload compared to its ancestors. Built by McDonnell Douglas.+Winner of the ELVRP I competition for a new small-medium class launch vehicle to replace Atlas, (existing) Delta, Titan IIIB, and other ICBM or IRBM-derived launch vehicles in the 1980s ([[http://www.alternatehistory.com/discussion/showpost.php?p=5365658&postcount=170|Post 16]]). Derived from older Delta designs, it however differs significantly in two key respects. First, it has a larger diameter kerolox core, allowing it to carry more engines and more boosters than previous versions of the Delta. This allows a useful booster-less launch mode. Second, instead of the hypergolic or solid upper stages previously used, it uses a Centaur-D, significantly improving upper stage ISP and performance. Optionally, for high energy missions it can use a Star 48B solid third stage. Altogether, this greatly increases the maximum payload compared to previous Deltas. Built by McDonnell Douglas. 
 + 
 +==== Delta 4000 Family Elements==== 
 +^ Stage Name ^ Description/Role ^Dry Mass ^Prop Mass ^ Thrust (vac) ^ ISp (vac) ^Thrust (sea level) ^ ISp (sea level) | 
 +^ WBELT | WideBody Extended Long Tank Thor, core first stage for the Delta 4000 | 13,293 kg | 191,207 kg | 3,162 kN | 295 s | 2,670 kN | 264 s | 
 +^ Castor IV | Standard steel-cased Delta solid rocket booster, developed for the Delta 3000 | 1,269 kg | 9,265 kg | 407 kN | 261 s | 355.7 kN | 228 s | 
 +^Centaur-D | Upper stage adapted from Atlas-Centaur | 2,631 kg| 13,627 kg | 146 kN | 444 s | N/A | N/A |  
 +^Star-48B | Optional third stage for extremely demanding missions | 126 kg | 2,011 kg | 66 kN | 286 s| N/A | N/A | 
 + 
 +|       ^ Delta 4000 ^ Delta 4030 ^ Delta 4060 ^ Delta 4090 ^ Delta 4120 ^ 
 +^ Boosters | None | 3xCastor 4 | 6xCastor 4 | 9xCastor 4 | 12xCastor 4 | 
 +^ 185x185 km, 28.5 | 5,785 | 6,751 | 7,633 | 8,453 | 9,225|  
 +^ 700x700 km, 98 | 3,210 | 3,850 | 4,433 | 4,971 | 5,476 | 
 +^ 185x20250 km, 28.5 | 2,026 | 2,530 | 2,987 | 3,410 | 3,806 |  
 +^ 185x35785 km, 28.5 | 1,562 | 2,012 | 2,418 | 2,795 | 3,148 | 
 +^ C3 = 0, 185xinf km | 1,553 | 1,825 | 2,079 | 2,320 | 2,550 | 
 +^ C3 = 15, 185xinf km | 1,158 | 1,365 | 1,559 | 1,744 | 1,921 | 
 + 
 +Payloads beyond Earth orbit use optional Star 48B third stage (are therefore technically for the Delta 4005, etc.) C3 = 0 corresponds to TLI, C3 = 15 to TMI.
==== Saturn Family ==== ==== Saturn Family ====
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=== Saturn 1B === === Saturn 1B ===
-Booster used for unmanned tests of the Lunar Module and Apollo Command and Service Module, as well as the manned Apollo 7 flight and the ASTP I and Skylab missions. Pre-point of divergence, design and capability unchanged by the timeline. One additional flight (Skylab 5). Information can be found at [[http://en.wikipedia.org/wiki/Saturn_IB | Wikipedia]] and [[http://www.astronautix.com/lvs/saturnib.htm | Astronautix]]. +Booster used for unmanned tests of the Lunar Module and Apollo Command and Service Module, as well as the manned Apollo 7 flight and the ASTP I and Skylab missions. Pre-point of divergence, design and capability unchanged by the timeline. One additional flight (Skylab 5). Information can be found at [[http://en.wikipedia.org/wiki/Saturn_IB | Wikipedia]] and [[http://www.astronautix.com/lvs/saturnib.htm | Astron utix]].
-Payload to LEO: 21,000 kg+Payload to LEO (237x237 at 51.6 degrees): 16400 kg
Flight Record: 10 flights, 10 successes Flight Record: 10 flights, 10 successes
Line 39: Line 57:
Payload to TLI: 47,000 kg Payload to TLI: 47,000 kg
-Payload to LEO (2 stage): 118,000 kg (Note: capabilities of the Skylab and Spacelab stations mean no more than 80,000 kg is ever used on any flight)+Payload to LEO (2 stage): 118,000 kg (Note: capabilities of the Skylab and Spacelab stations mean no more than 80,000 kg is ever used on any LEO-only flight)
Flight Record: 15 launches, 15 successes Flight Record: 15 launches, 15 successes
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Among the key capabilities of the Saturn 1C was the throttle added to the F-1 as part of F-1A development. While the F-1 (and F-1A) were originally designed with the aim of being used on the Saturn V where late-burn acceleration was controlled by shutting down engines, the F-1A had the ability to throttle to 75%, a capability that was critical in avoiding excessive acceleration later in the S-1E burn on Saturn 1C. Among the key capabilities of the Saturn 1C was the throttle added to the F-1 as part of F-1A development. While the F-1 (and F-1A) were originally designed with the aim of being used on the Saturn V where late-burn acceleration was controlled by shutting down engines, the F-1A had the ability to throttle to 75%, a capability that was critical in avoiding excessive acceleration later in the S-1E burn on Saturn 1C.
-Payload to LEO (430x430 at 51.6 degrees): +**Vehicle info** 
 +|              ^ Stage 1  ^ Stage 2         ^ Stage 3 (optional) ^ 
 +^ Stage Name    | S-1E    | S-IVB        | Centaur-E | 
 +^ Builder    | Boeing     | McDonnell-Douglas  | General Dynamics | 
 +^ Diameter    | 6.6 m     | 6.6 m        | Variable | 
 +^ Dry Mass |  24,000 kg   | 12,900 kg      | 2,800 kg | 
 +^ Fuel Mass|  407,000 kg  | 104,300 kg     | 21,100 kg | 
 +^ Engine | 1xF1-A         | 1xJ2-S        | 2xRL10A-3 | 
 +^ Thrust (vac) | 9189 kN  | 1138 kN        | 146 kN | 
 +^ ISp (vac) | 310         | 436s        | 444s | 
 +^ Thrust (sl) | 8003 kN  |   N/A       | N/A | 
 +^ Isp (sl) | 270          |   N/A       | N/A |
-Payload to LEO (430x430 at 28.5 degrees):+**Vehicle Performance** 
 +| Orbits ^ Payloads ^ 
 +^ 185x185 km, 28.5 | 24,419 kg  | 
 +^ 430x430 km, 51.6 | 20,182 kg | 
 +^ C3=0, 185xinf km | 9,979 kg | 
 +^ C3=15, 185xinf km | 7,960 kg |
-**Vehicle info** +(beyond Earth orbit missions use optional Centaur-E third stage; C3=0 corresponds to TLI, C3=15 to TMI) 
-|              ^ Stage 1  ^ Stage 2         ^ +{{:timelines:saturnic_mb.png|}}
-^ Stage Name    | S-1E    | S-IVB        | +
-^ Builder    | Boeing     | McDonnell-Douglas  | +
-^ Diameter    | 6.6 m     | 6.6 m        | +
-^ Dry Mass |  24,000 kg   | 12,900 kg      | +
-^ Fuel Mass|  407,000 kg  | 104,300 kg     | +
-^ Engine | 1xF1-A         | 1xJ2-S        | +
-^ Thrust (vac) | 9189 kN  | 1138 kN        | +
-^ ISp (vac) | 310         | 436s        | +
-^ Thrust (sl) | 8003 kN  |   N/A       | +
-^ Isp (sl) | 270          |   N/A       |+
-=== Saturn Multibody ===+==== Saturn Multibody ====
-In addition to the small-medium vehicle covered by the ELVRP I competition, the Air Force needed a larger vehicle to fill the medium-large payload role that had previously been provided by the Titan IIIC, especially with the beginning of SDI and the large payloads expected from it. This requirement led to the ELVRP II competition, as in [[http://www.alternatehistory.com/discussion/showpost.php?p=5557907&postcount=286|Post 21]], a competition which was won by the Boeing/McDonnell Douglas Saturn Multibody, as described by [[http://www.alternatehistory.com/discussion/showpost.php?p=5617801&postcount=339|Post 22]]. +In addition to the small-medium vehicle covered by the ELVRP I competition, the Air Force needed a larger vehicle to fill the medium-large payload role that had previously been provided by the Titan IIIC, especially with the beginning of SDI and the large payloads expected from it. This requirement led to the ELVRP II competition, as in [[http://www.alternatehistory.com/discussion/showpost.php?p=5557907&postcount=286|Post 21]], a competition which was won by the Boeing/McDonnell Douglas Saturn Multibody, as described by [[http://www.alternatehistory.com/discussion/showpost.php?p=5617801&postcount=339|Post 22]]. A derivative of the Saturn IC, Saturn Multibody features a number of improvements over that vehicle, most prominently the ability to add Titan-derived solid rocket boosters to increase the maximum payload, a stretched S-IVB (the S-IVC) on some variants to further improve performance, and last but not least the ability to gang up three Saturn Multibody core stages to launch a nearly Saturn V-sized payload into orbit.
- +
-A derivative of the Saturn IC, Saturn Multibody features a number of improvements over that vehicle, most prominently the ability to add Titan-derived solid rocket boosters to increase the maximum payload, a stretched S-IVB (the S-IVC) on some variants to further improve performance, and last but not least the ability to gang up three Saturn Multibody core stages to launch a nearly Saturn V-sized payload into orbit.+
The Saturn Multibody designation system is composed of a letter followed by two numbers. The letter says whether the vehicle is Medium or Heavy, that is whether it has one or three Saturn Multibody cores. The first number can have the values 0, 2, or 4, and describes the number of solid rocket boosters attached. The second number can have the values 2 or 3 and indicates whether the upper stage is the S-IVB (2) or the S-IVC (3). The S-IVC is only used on the M43 or H03 versions of the vehicle, since it is too heavy to offer much of a performance benefit to the smaller variants. The Saturn Multibody designation system is composed of a letter followed by two numbers. The letter says whether the vehicle is Medium or Heavy, that is whether it has one or three Saturn Multibody cores. The first number can have the values 0, 2, or 4, and describes the number of solid rocket boosters attached. The second number can have the values 2 or 3 and indicates whether the upper stage is the S-IVB (2) or the S-IVC (3). The S-IVC is only used on the M43 or H03 versions of the vehicle, since it is too heavy to offer much of a performance benefit to the smaller variants.
-== Saturn M02 == +Vehicle contracted 1981 under ELVRP II, first flight planned for 1985/86.
- +
-== Saturn M22 ==+
-== Saturn M42 ==+=== Saturn Multibody Family Elements === 
 +^ Stage Name ^ Description/Role ^Dry Mass ^Prop Mass ^ Thrust (vac) ^ ISp (vac) ^Thrust (sea level) ^ ISp (sea level) | 
 +^ S-1F (SCC) | Saturn Common Core, common first-stage core of all Multibody Vehicles | 29,760 kg | 504,742 kg | 9,189 kN | 310 s | 8,003 kN | 270 s | 
 +^ S-1G (SCB) | Saturn Common Booster, common liquid booster for all Saturn Heavies | 27,760 kg | 504,742 kg | 9,189 kN | 310 s | 8,003 kN | 270 s | 
 +^Titan UA1207| Titan 7-segment solid rocket motor used on Multibody | 51,230 kg | 268,070 kg | 7,112 kN | 272 s | 6,406 kN | 245 s | 
 +^S-IVB | Upper stage adapted from Saturn 1B and Saturn V | 13,100 kg | 104,326 kg | 1,136 kN | 436 s | N/A | N/A |  
 +^S-IVC | Upper stage derived from S-IVB for large Multibody LVs | 28,820 kg | 229,517 kg | 2,272 kN | 436 s| N/A | N/A | 
 +^Centaur-E | Optional third stage for extremely demanding missions | 2,800 kg | 21,100 kg | 146 kN | 444 s | N/A | N/A |
-== Saturn M43 ==+=== Saturn Multibody Family Rockets=== 
 +|       ^ Saturn M02 ^ Saturn M22 ^ Saturn M42 ^ Saturn M43 ^Saturn H02 ^Saturn H03 ^ 
 +^ Boosters | None | 2xTitan UA1207 | 4xTitan UA1207 | 4xTitan UA1207 | 2xSCB | 2xSCB | 
 +^Upper Stage | S-IVB | S-IVB | S-IVB | S-IVC | S-IVB | S-IVC | 
 +^ 185x185 km, 28.5 | 27,707 | 43,890 | 53,965 | 65,961 | 63,603 | 77,765 | 
 +^ 430x430 km, 51.6 | 23,143 | 37,318 | 46,060 | 55,353 | 54,345 | 65,863 | 
 +^ 430x430 km, 28.5 | 24,359 | 39,087 | 48,190 | 58,240 | 56,876 | 69,131 | 
 +^ 185x35785 km, 28.5 | 7,858 | 15,808 | 20,526 | 19,783 | 24,986 | 25,987 | 
 +^ C3 = 0, 185xinf km | 11,163 | 10,423 | 14,198 | 10,761 | 17,707 | 15,845 | 
 +^ C3 = 15, 185xinf km | 8,955 | 6,620 | 9,753 | 4,368 | 12,628 | 8,663 | 
 +^Liftoff T/W | 1.20 | 1.61 | 1.75 | 1.66 | 1.37 | 1.26 | 
 +^2nd Stage T/W | 0.80 | 0.72 | 0.68 | 0.71 | 0.36 | 0.69 | 
 +^ Cost (2011 millions) | $150m | $190m | $230m | $280m | $350m | $380m |
-== Saturn H02 ==+For Saturn M02 only, Centaur-E third stage assumed for all beyond Earth orbit missions. C3 = 0 corresponds to TLI, C3 = 15 to TMI.
-== Saturn H03 ==+==Launch Costs For Evolved Saturn/Apollo== 
 +See [[http://www.alternatehistory.com/discussion/showpost.php?p=7141325&postcount=1116| Post 1116]] for discussion of unit costs for Apollo Block IV, AARDV, and Saturn Multibody launches.
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=== Titan I === === Titan I ===
-Backup system for SM-65 Atlas ICBM +Backup system for SM-65 Atlas ICBM.
=== Titan II === === Titan II ===
-Backup System for LGM-30 Minuteman ICBM, 63 Titan II were in Service as ICBM+Backup system for LGM-30 Minuteman ICBM, 63 Titan IIs were in put into service as ICBMs.
=== Titan II GLV === === Titan II GLV ===
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=== Titan IIIF === === Titan IIIF ===
-Unmanned Version of Titan IIIM, to use by NASA with different types of third Stage. Centaur, Transstage, Agena. cancelled together with Titan IIIM in 1968 and replace by Titan IIIE+Unmanned version of Titan IIIM for NASA use. Offered with a variety of third stages: Centaur, Transstage, and Agena. Titan IIIF was cancelled along with Titan IIIM in 1968 and replaced by Titan IIIE in NASA plans.
=== Titan IIIM === === Titan IIIM ===
-A modified Titan IIIC with 7 segmented Solid rocket booster and advance control system for Manned launches, had to be used for USAF program M.O.L, +A modified Titan IIIC with 7-segment solid rocket motors and advanced controls, Titan IIIM was fitted with advanced control systems that were intended to make it usable for manned launches as part of the USAF Manned Orbiting Laboratory Program. While all work on Titan IIIM would end with MOL's cancellation, the 7-segment solids would survive as elements both in the ELVRP II Titan V proposal and the successful Saturn Multibody proposal.
-the Program was cancelled - All work on Titan IIIM and NASA version Titan IIIF stopped in 1968+
===== Soviet/Russian Launch Vehicles ===== ===== Soviet/Russian Launch Vehicles =====
==== Proton ==== ==== Proton ====
-Start as "Super ICBM" program for 100 Megatons H-Bombs. After Khrushchev was ousted by the Soviet Union leaders, the Project was transform into medium Launch Vehicles  +The Proton was started as a Chelomei "Super ICBM" program for 100 megaton H-Bombs (GRAU index 8K82K). After Khrushchev was ousted by the Soviet Union leaders, the project was transformed into one aiming to provide a medium launch vehicle, something for which the design was much better suited. The Proton was used for the unsuccessful Zond program to fly a cosmonaut around the Moon and launched first Alamaz and Salyut space stations before replaced in 1980s by the Vulkan Standard Launch vehicle  
-replace in 1980s by the Vulkan Standard Launch vehicles + 
 +Payload to LEO (200x200 km at 52°) from the Baikonur Cosmodrome: 19600 kg
==== Soyuz (Rocket) ==== ==== Soyuz (Rocket) ====
-Start as R-7a ICBM program, became a family of Launch Vehicles. It launch the first Satellite "Sputnik", the First Human Yuri Gagarin in Space also used to launch the Soyuz manned spacecraft from 1960s to early 1980s. After termination of the Soyuz spacecraft program in 1980 the Soyuz rocket is still used to launch Satellite.+Started as R-7a ICBM program, became a family of launch vehicles (GRAU index 11A511). Its importance in spaceflight history is undeniable, as it served as the launch vehicle for first satellite ("Sputnik"), the first human to orbit Earth (Yuri Gagarin) and all Russian manned vehicles from the 1960s to early 1980s. After the termination of the Soyuz spacecraft program in favor of TKS in 1980, the Soyuz rocket is still used to launch smaller satellites than would be viable for the Vulkan, but which are too large for Tsyklon or Cosmos.
==== N-1 ==== ==== N-1 ====
-Korolev Moonrocket, after his death Vasiliy Mishin takes over project and produce four consecutive failures, the troubled N-1 program was canceled in 1972.+Soviet moonrocket designed by Korolev. After his death, Vasiliy Mishin took over the project. Various issues produced four consecutive failures. The troubled N-1 program was canceled in 1972, and Mishin would be replaced by Glushko in the same year.
==== Vulkan Family ==== ==== Vulkan Family ====
 +After the cancellation of N-1, Valentin Glushko proposed a family of rockets that could fulfill a wide range of needs for the military and the space program, including the Soyuz and Proton rocket. Much like the Saturn Multibody concept proposed three years later, it would be a common-core design using up to five cores powered by a new high-thrust kerolox engine, the RD-150.
=== Vulkan Standard === === Vulkan Standard ===
 +The core version of the launcher family (GRAU index 11K55 )
 +
 +Payload to LEO (200 km at 52°) from the Baikonur Cosmodrome: 21000 kg
 +
 +**Vehicle info**
 +|                     ^ Stage 1 ^ Stage 2 ^
 +^ Stage Name | ? | ? |
 +^ Builder         | NPO Energia | NPO Energia |
 +^ Diameter      | ? m | ? m   |
 +^ Dry Mass      | ? kg | ? kg |
 +^ Fuel Mass     | ? kg | ? kg |
 +^ Engine          | 1xRD-150 | 1xRD-160 |
 +^ Thrust (vac) | 7900  kN | 2000 kN |
 +^ ISp (vac) | 337 s | 349s |
 +^ Thrust (sl) | 7600 kN | N/A  |
 +^ Isp (sl) | 309s | N/A |
=== Vulkan-Herakles === === Vulkan-Herakles ===
 +To boost performance to light heavy-lift levels, the Vulkan-Herakles gangs together three standard Vulkan cores as a first stage (GRAU index 11K77 )
-=== Vulkan-Atlas ===+Payload to LEO (200 km at 52°) from the Baikonur Cosmodrome: 60000 kg 
 + 
 +=== Vulkan-Atlas ===  
 +The ultimate version of the Vulkan, the Vulkan-Atlas uses five Vulkan cores as a first stage to provide true heavy-lift performance (GRAU index 11K37 ) 
 + 
 +Payload to LEO (200 km at 52°) from the Baikonur Cosmodrome: ~100000 kg
=====European Launch Vehicles===== =====European Launch Vehicles=====
-For story of ESA and there Europa launch vehicle is described in detail here [[http://www.alternatehistory.com/discussion/showpost.php?p=5172084&postcount=87|Post 9]] [[http://www.alternatehistory.com/discussion/showpost.php?p=5260377&postcount=119|Post 12]] [[http://www.alternatehistory.com/discussion/showpost.php?p=5390517&postcount=181|Post 17]]+The history of ESA and their Europa launch vehicles is discussed primarily in the three posts [[http://www.alternatehistory.com/discussion/showpost.php?p=5172084&postcount=87|Post 9]], [[http://www.alternatehistory.com/discussion/showpost.php?p=5260377&postcount=119|Post 12]], and [[http://www.alternatehistory.com/discussion/showpost.php?p=5390517&postcount=181|Post 17]]
==== Europa 1 ==== ==== Europa 1 ====
-Unusual Launch rocket because its stages are build from different Europeans states and put together. So the Europa-1 was more a technical & political feasibility demonstrator.+Constructed of stages from all of the major ELDO member states, the Europa 1 functioned more as a political and technical feasibility test than a functional launch vehicle.
Payload to LEO (200 km at polar orbit) from Woomera: 1200 kg Payload to LEO (200 km at polar orbit) from Woomera: 1200 kg
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==== Europa 2 ==== ==== Europa 2 ====
-The Advance Version of Europa 1 launch vehicle, optimized for GEO mission. Launch most of ESA satellites from 1970s +Advanced variant of Europa 1, with an additional P0.7 kick stage used to optimize payload to geostationary tranfer orbit. Main launch vehicle for ESA from 1971 until the introduction of Europa 2-TA in 1975.
Payload to LEO (200 km equator) from Kourou: 1440 kg Payload to LEO (200 km equator) from Kourou: 1440 kg
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^ Engine          | 2xRZ.2 | 4xVexin | 1x and 2 vernier | 1x P0.7 | ^ Engine          | 2xRZ.2 | 4xVexin | 1x and 2 vernier | 1x P0.7 |
^ Thrust (vac) | 1576 kN | 284 kN | 22.56 kN + 2x0.4 kN | 41.2 kN | ^ Thrust (vac) | 1576 kN | 284 kN | 22.56 kN + 2x0.4 kN | 41.2 kN |
-^ ISp (vac) | 284s | 277s | 292s | 276s |+^ ISp (vac) | 284s | 277s | 292s | 310s |
^ Thrust (sl) | 1334 kN | N/A  | N/A | N/A | ^ Thrust (sl) | 1334 kN | N/A  | N/A | N/A |
^ Isp (sl) | 248s | N/A | N/A | N/A | ^ Isp (sl) | 248s | N/A | N/A | N/A |
==== Europa 2-TA ==== ==== Europa 2-TA ====
-Europa 2 Thrust Augmented. With two Black Diamant Solid Booster attache on side of first stage Blue Streak +Thrust-augmented variant of Europa 2. Using two Black Diamant solid rocket boosters attached to the first stage to boost payload. Active from 1975 in parallel with continuing Europa 2 launches. As of 1982, intended to be replaced by the all-liquid Europa 2-HE after Europa 3 introduction.
Payload to LEO (200 km equator) from Kourou: 2110 kg Payload to LEO (200 km equator) from Kourou: 2110 kg
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Payload to GEO (35700 km at equator) from Kourou: 300 kg Payload to GEO (35700 km at equator) from Kourou: 300 kg
 +
 +==== Europa 2-HE ====
 +Europa 2 variant with new high-energy Aurore-B upper stage replacing Coralie. Studied as part of Europa 3 development in early 1980s, intended to be developed alongside Europa 4 family to fufill European launch needs with single set of common components. Notably, designing for this potential drove the selection of the 4.0m dimeter for the Aurore stage--a balance between insufficient diameter and excessive length for Europa 3/4 and excessive overhang on Europa 2 that might result in flight instabilities. First flight unscheduled.
 +
 +** Vehicle Info **
 +^  ^ Stage 1 ^ Stage 2^
 +^ Stage Name | Blue Streak | Aurore-B |
 +^ Builder | BAe | Aerospatiale |
 +^ Diameter | 3.05m | 4.0m |
 +^ Dry Mass | 7000 kg | 1792 kg |
 +^ Fuel Mass | 82400 kg | 18121 kg |
 +^ Engine | 2xRZ.2 | 3xHM-7B |
 +^ Thrust (vac) | 1576 kN | 188 kN |
 +^ ISp (vac) | 287s | 444s |
 +^ Thrust (sl) | 1334 kN | N/A |
 +^ ISp (sl) | 248s | N/A |
 +
 +Payload to LEO (Spacelab, 430x430 km, 51.6 degrees): 3800 kg
 +
 +Payload to GTO (185x35786 km at 3.5 degrees) from Korou: 650 kg
==== Europa 3 ==== ==== Europa 3 ====
-More Powerful version of Europa launch vehicle, the first stage is new design with 4xRZ.3 engine , Second and third stage are French-built using LH2/LOX engines. +More powerful vehicle developed to supplement existing Europa 2-TA and open up new lines of incremental evolution with introduction of two new stages, the French-built Aurore hydrogen/oxygen stage using 6xHM-7B and the UK-built kerosene-LOX Griffin first stage, a "super Blue Streak" powered by 4xRZ.2 engines. Development begun in late 70s, first flight projected as 1985.
-Payload to LEO (200 km equator) from Kourou: 12000 kg+**Vehicle info** 
 +|                     ^ Stage 1 ^ Stage 2 ^ (Opt Stage 3) ^ 
 +^ Stage Name | Griffin | Aurore | Astris | 
 +^ Builder | BAe | Aerospatiale | ERNO | 
 +^ Diameter | 4.31m | 4.0m | 2.01m | 
 +^ Dry Mass | 14000 kg| 3584kg | 540 kg | 
 +^ Fuel Mass | 164800 kg | 36243kg | 3195 kg | 
 +^ Engine | 4xRZ.2 | 6xHM-7B | 1x and 2 vernier | 
 +^ Thrust (vac) | 3152 kN | 376 kN | 22.56 kN + 2x0.4 kN | 
 +^ ISp (vac) | 287s | 444s | 310s | 
 +^ Thrust (sl) | 2668 kN | N/A | N/A | 
 +^ ISp (sl) | 248s | N/A | N/A |
-Payload to LEO (430×430 at 51.6 degrees): 7000~10000 kg+Payload to LEO (430×430 at 51.6 degrees): 7600 kg
-Payload to GEO (35700 km at equator) from Kourou:2500 kg+Payload to GTO (35786x185 km at 3.5 degrees) from Kourou: 1800 kg (with Astris third stage) 
 + 
 +==== Europa 4 Family ==== 
 + 
 +Europa 4 was part of Europa 3 planning, intended as a future development of a flexible system of launch options via the combination of the already-developed Aurore and Griffin stages, combined with a variable mix of up to 4 Blue Streak boosters and assorted upper stages. Combining heritage of the Europa 2 and Europa 3 development cycles, it was intended to offer the capacity necesary for the late 80s and 90s to support Earth-focused flights like comsats and commercial payloads, interplanetary probes, or even the long-discussed European manned space launch capability. Many variants were studied with a common designation systems of the form "Europa 4XY" where X was the number of Blue Streak boosters and Y indicated the precence of additional third stages, with "u" indicating the standard third stage, the half-length Aurore-B, and "a" indicating any Astris stage used. Europa 40 and 40a are identical to existing Europa 3 configurations. The system was intended for development following first Europa 3 launch. 
 + 
 +**Component info** 
 +|                     ^ Stage 0 | Stage 1 ^ Stage 2 ^ (Opt Stage 3) ^ (Opt Stage 3+) ^ 
 +^ Stage Name | Blue Streak | Griffin | Aurore | Aurore-B | Astris | 
 +^ Builder | BAe | BAe | Aerospatiale | Aerospatiale | ERNO | 
 +^ Diameter | 3.05m | 4.31m | 4.0m | 4.0m | 2.01m | 
 +^ Dry Mass | 7000kg | 14000 kg| 3584 kg | 1792 kg | 540 kg | 
 +^ Fuel Mass | 82400kg | 164800 kg | 36243kg | 18121 kg | 3195 kg | 
 +^ Engine | 2x RZ.2 | 4xRZ.2 | 6xHM-7B | 3xHM-7B | 1x and 2 vernier | 
 +^ Thrust (vac) | 1576 kN | 3152 kN | 376 kN | 188 kN | 22.56 kN + 2x0.4 kN | 
 +^ ISp (vac) | 287s | 287s | 444s | 444s | 310s | 
 +^ Thrust (sl) | 2668 kN | N/A | N/A | N/A | N/A | 
 +^ ISp (sl) | 248s | N/A | N/A | N/A | N/A | 
 + 
 +**Configurations and Payload Info** 
 + 
 +|  |  Europa 40 | Europa 40a| Europa 42 | Europa 44 | Europa 42u | Europa 44u |  
 +| 430x430 km, 51.6 | 7600 kg | 7000 kg | 11850 kg | 14850 kg | 14983 | 18422 | 
 +| 185x35785 km, 5.25 | 1500 kg | 2500 kg| 3041 kg | 4169 kg | 6000 kg | 7500 kg |
===== American Space Stations ===== ===== American Space Stations =====
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Sole American space station as of 1982. Heavily modified and upgraded version of Skylab, it was designed to serve as the home of ASTP II, where Soviet and American spacefarers would spend several months together in space. After doing so, it became a joint US-European station with the addition of the European Research Module, ERM, in October 1979. Routinely plays host to American and European astronauts. Sole American space station as of 1982. Heavily modified and upgraded version of Skylab, it was designed to serve as the home of ASTP II, where Soviet and American spacefarers would spend several months together in space. After doing so, it became a joint US-European station with the addition of the European Research Module, ERM, in October 1979. Routinely plays host to American and European astronauts.
 +
 +==== Freedom ====
 +
 +American-led space station program started in the wake of the Vulkan panic by President Reagan. Building on the experience gained from Spacelab and the capabilities of the Multibody rocket family, Freedom is much larger and more capable than the previous station, having been designed from the ground up to serve as a research outpost in space. It also includes significant material contributions from Europe, Japan, and Canada, making it a more international station than Spacelab.
===== Soviet Space Stations ===== ===== Soviet Space Stations =====
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Workhorse of the NASA human spaceflight program. Gemini and Mercury were test vehicles; Apollo is the real operational vessel. The Block II version was used for lunar landings and early station flights before the introduction of the Block III, while the Block III and Block III+ have become reliable crew taxis by 1983, shuttling personnel back and forth from Spacelab. Workhorse of the NASA human spaceflight program. Gemini and Mercury were test vehicles; Apollo is the real operational vessel. The Block II version was used for lunar landings and early station flights before the introduction of the Block III, while the Block III and Block III+ have become reliable crew taxis by 1983, shuttling personnel back and forth from Spacelab.
 +== Block I ==
 +
 +Early model of the Apollo spacecraft lacking a docking adapter and designed for use on the Earth orbital test flights Apollo 1 and 2. After fire broke out in the Apollo 1 capsule, killing Virgil I. "Gus" Grisson, Edward H. White II, and Roger B. Chaffee, NASA cancelled all plans to use the Block I for human flights, skipping directly to the Block II for the Apollo 7 test flight. Several did fly on uncrewed test flights, however.
 + 
== Block II == == Block II ==
 +Apollo spacecraft model designed for use in lunar missions. Besides being used as the principal Earth-Moon and Moon-Earth transport spacecraft on all Apollo lunar flights, it also served as a crew transport vehicle for the Skylab 2, 3, and 4 missions.
 +
== Block III == == Block III ==
 +Model for low Earth orbit. Although the designation was first used in the Apollo Application Project, it was later reused for the Apollo ferry spacecraft that served on the Skylab 5 and early Spacelab missions. Significant changes were made to better adapt Apollo to its new role as a crew shuttle, such as shortening the Service Module, reducing the size of the fuel tanks, and replacing the fuel cell power generation system by batteries.
 +
== Block III+ == == Block III+ ==
 +Advanced model for 5 astronauts with a separate Mission Module. After launch the CSM docks with the MM stored on top of the S-IVB stage (similar to the transposition and docking maneuver during lunar missions) and then proceeds to the space station.  
 +
 +==Block IV ==
 +Apollo model developed for use with Space Station Freedom and Saturn Multibody. Built to use additional payload allowed by Saturn M02 compared to Saturn IC, Block IV is built on an enhanced-capacity service module (common with Aardvark Block II) and features a larger, more capable Mission Module, but retains the Block III command module with minor avionics updates.
 +
 +== Apollo Model Specifications ==
 +
 +^ Model Name ^ First Flight ^ Last Flight ^ Number Flown ^ CSM Mass ^ MM Mass ^ Cargo Mass ^ Fuel Capacity ^ Habitable Volume |
 +^ Apollo Block I | Feb 1966 | April 1968 | 4 | 12,200 kg | N/A | ?? | max 18,124 kg | 6.2 m3 |
 +^ Apollo Block II | Oct 1968 | July 1974 | 16* | 12,200 kg | N/A | ?? | max 18,124 kg | 6.2 m3 |
 +^ Apollo Block III | May 1976 | Jan 1980 | 8* | 11,200 kg | N/A | ?? | 1,600 kg | 6.2 m3 |
 +^ Apollo Block III+ | May 1980 | Jan 1988 | 24 | 11,200 kg | 3,250 kg | 750 kg | 1,600 kg | 23 m3 |
 +^ Apollo Block IV | ?? | ?? | 0 | 12,000 kg| 4,500 kg | 2,500 kg | 2,000 kg | 23 m3 |
 +
 +*A 17th Block II CM was flown as part of Spacelab 5, mated to a Block III SM for systems checkout since the Block III CM was incompatible with Skylab's air mixture compared to that of Spacelab. CM-119 was cannibalized for this purpose. As the critical components tested were Block III, this flight is counted as a primarily Block III flight.
 +
 +* As of the present post, Block IV has yet to be introduced.
==== AARDVark ==== ==== AARDVark ====
-Developed to complement Block III Apollo by providing a cargo transport capability, it consists of a Block III Service Module with a large Pressurized Module replacing the Command Module of the Apollo. This allows it to transport tons of food, water, scientific equipment, and other vital supplies to the station. A derivative of this Pressurized Module was used to develop the Block III+ Mission Module.+== Block I AARDV == 
 +Developed to complement Block III Apollo by providing a cargo transport capability, the Aardvark consists of a Block III Service Module with a large Pressurized Module replacing the Command Module of the Apollo. This allows it to transport tons of food, water, scientific equipment, and other vital supplies to the station. A derivative of this Pressurized Module was used to develop the Block III+ Mission Module. The name is based on the acronym for Autonomous Automated Rendezvous and Docking Vehicle. AARDV mission code with -T suffix also used for assembly flights using AARDV bus as a delivery tug. 
 + 
 +Cargo capacity: up to 2 tons of liquids, total capacity of 9,900 kg 
 + 
 +== Block II AARDV == 
 +As part of the buildup to Freedom, a new Aardvark variant was introduced. This used an enhanced bus to allow the -T variant to serve as a tug for the larger station components such as the inboard truss. Additionally, the pressurized cargo pod was switched to a new 5m diameter, and a new non-pressurized cargo bay inserted between it and the SM. 
 + 
 +== AARDVARK Block II Specifications == 
 + 
 +^ Model Name ^ SM Mass ^ PM Mass ^ Pressurized Cargo Mass ^ Unpressurized Cargo Mass ^ Fluids Mass ^ Fuel Capacity ^ Pressurized Volume | 
 +^ AARDV Block II | 6400 kg | 2400 kg | ~8000 kg | ~1000 kg | ~3000 kg | 3500 kg max | 45 m3 | 
===== Soviet Spacecraft ===== ===== Soviet Spacecraft =====
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Chelomei vehicle designed to serve as a crew and supply transport to his Almaz stations. While Almaz has not been especially successful, it has been adapted to serve as the main Soviet crew transport to the new Vulkan-launched MOK station, and (while that is being readied for launch) to the interim Salyut 7 station. Chelomei vehicle designed to serve as a crew and supply transport to his Almaz stations. While Almaz has not been especially successful, it has been adapted to serve as the main Soviet crew transport to the new Vulkan-launched MOK station, and (while that is being readied for launch) to the interim Salyut 7 station.
 +
 +==== See Also ====
 +
 +**[[Eyes Turned Skywards]]**
 +
 +**[[list of eyes turned skyward posts|Chapters (Eyes Turned Skywards)]]**
 +
 +**[[mission_list|Mission List (Eyes Turned Skywards)]]**
 +
 +**[[Eyes Turned Skywards Images and Fanworks|Media (Eyes Turned Skywards)]]**
 +
 

timelines/spacecraft_and_launch_vehicle_technical_data.1336165919.txt.gz · Last modified: 2012/05/04 17:11 by Michel Van

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