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The world's first ICBM became the most often used and most reliable launch vehicle in history. The original core+four strap-on booster missile had a small third stage added to produce the Vostok launch vehicle, with a payload of 5 metric tons. Addition of a larger third stage produced the Voskhod/Soyuz vehicle, with a payload over 6 metric tons. Using this with a fourth stage, the resulting Molniya booster placed communications satellites and early lunar and planetary probes in higher energy trajectories. By the year 2000 over 1,628 had been launched with an unmatched success rate of 97.5% for production models. Improved models providing commercial launch services for international customers entered service in the new millenium, and a new launch pad at Kourou was to be inaugurated in 2009. It appeared that the R-7 could easily still be in service 70 years after its first launch. Development of the R-7 began under research project N-3 "Development requirements for a liquid rocket with a range of 5,000 to 10,000 km and a warhead of 1 to 10 tonnes". The research project was authorised in a decree of 4 December 1950. The study was headed by Korolev's NII-88 but involved a wide range of other Soviet research institutes:
Work was well underway when the requirements were suddenly altered on 3 October 1953. The total warhead mass was increased to 5,500 kg, with the net mass of only the nuclear device itself being 3,000 kg. The rocket designed to that point would have a range of only 5,500 km with such a warhead. A meeting was called of the Chief Designers in January 1954 to discuss how to handle the problem. Several weight saving measures were used. The single engines per module were replaced by small diameter engines of reduced length; the propellant tanks were laid out to minimise mass; a unique launch pad design was accepted that suspended the rocket above the flame pit and shielded it from cross winds, which allowed a lighter structure. Another technical challenge were the small vernier rockets used to pitch the rocket. These had to have a high specific impulse, gimbal 45 degrees, and deliver a thrust of 2.5 tonnes. Glushko could not deliver an engine with these characteristics, so Melnikov of OKB-1 was assigned the task of designing the engines in-house. The engine that resulted met the requirements and was the technological basis for later rocket engines developed within OKB-1 (the Lox/Kerosene upper stage engines for the Molniya, N1, and Proton boosters). By February 1954 the stage was reached where a final design was possible. A government declaration of 20 May 1954 authorised development of the two stage R-7 / 8K71 intercontinental ballistic missile. This was followed by a decree of 28 June 1954 'On plans N/R for space research'. Implementation came via a Ministry of Defence decree of 6 July 1954 calling on all industry organisations to work together and assigning the project the highest national priority. The draft project, using much material generated for the T-1 project, was completed in July 1954. The vehicle in the draft project used the 'packet' layout with a hammerhead core stage surrounded by four shorter booster stages. At ignition, the four booster stages ignited. If full thrust was achieved, the core was then ignited and the booster rose on the thrust of all five stages. The rocket could boost the 5500 kg warhead to 7.9 km/s and 8,000 km range, with a maximum miss distance of plus or minus 10 km. The warhead was the German 'sharp point': a 16 degree cone, 7.27 m long, mounted atop a cylindrical interstage section. The rocket had a gross lift-off mass of 280 tonnes, and an empty mass of 27 tonnes. The first stage burned out at 2,170 m/s and the second stage at 6,385 m/s. Thrust at lift-off was 403.4 tonnes. The R-7 incorporated ingenious solutions in ground handling of the large rocket. The rocket would be assembled horizontally, rolled out to the pad, then raised to the vertical position and quickly fuelled. The expert commission deemed the decree requirements to be fulfilled and recommended construction of the rocket with minor changes in the development plan. The government authorised the construction phase in a decree of 20 November 1954. The design was frozen by Korolev on 11 March 1955 and drawing release and parts fabrication began. By 20 March 1956 a decree set forth the impending three stage development test plan:
In the first half of 1956 work began in earnest at 36 factories with the objective of making the first test flight by the end of the year. The first article completed was a full scale mock-up consisting of the core and one booster stage. Two Block A and B stages were delivered for stand tests, but incomplete factory test equipment held up the start. At that point it seemed impossible that a flight would be made within the year. By the second half of 1956 solutions had been found to the outstanding problems. Serial production of rockets had begun. The Progress Aviation Factory in Samara, V Ya Litvinov manager, had been selected to fabricate detailed parts but final assembly of the prototype rockets was carried out at Factory 88 in Kaliningrad. Over time the factory at Samara would be organised as the Third Filial of OKB-1 and take over first production, and then engineering, of future R-7 derivatives. In 1974 it became the TsKB, a separate entity. R-7 systems were developed in the following research program:
In its intended military mission, the R-7 was quickly overtaken by technological improvements. These allowed the Soviet Union to build missiles using 'zero warning launch' storable propellants and smaller nuclear warheads (Yangel's R-16 and R-36, Chelomei's UR-100). Deployment of the R-7 was very limited, and its service life extended only from 1960 to 1966. Only one dedicated ICBM pad was built at Baikonur, and six to eight in the Angara complex at Plesetsk. By 1966 they were all converted to space launch use and the military service life of the rocket was over. But as a space launcher, the R-7, with upper stages, became the most successful in history. By the year 2000 over 1,628 had been launched with a success rate of 97.5% for production models. Manufacturer: Korolev. Launches: 1727. Failures: 99. Success Rate: 94.27%. First Launch Date: 1957-05-15. Last Launch Date: 2007-12-23. Launch data is: continuing.
Version: R-7.
The world's first ICBM and first orbital launch vehicle. The 8K71 version was never actually put into military service, being succeeded by the R-7A 8K74. Development of the R-7 began under research project N-3 "Development requirements for a liquid rocket with a range of 5,000 to 10,000 km and a warhead of 1 to 10 tonnes". The research project was authorised in a decree of 4 December 1950. The study was headed by Korolev's NII-88 but involved a wide range of other Soviet research institutes:
Work was well underway when the requirements were suddenly altered on 3 October 1953. Tests at Semipalatinsk had demonstrated the possibility of building a thermonuclear warhead of vastly greater power. However the total warhead mass would have to be increased to 5,500 kg, with the net mass of only the nuclear device itself being 3,000 kg. The rocket designed to that point would have a range of only 5,500 km with such a warhead. A meeting was called of the Chief Designers in January 1954 to discuss how to handle the problem. Several weight saving measures were used. The single engines per module were replaced by small diameter engines of reduced length; the propellant tanks were laid out to minimise mass; a unique launch pad design was accepted that suspended the rocket above the flame pit and shielded it from cross winds, which allowed a lighter structure. Another technical challenge were the small vernier rockets used to pitch the rocket. These had to have a high specific impulse, gimbal 45 degrees, and deliver a thrust of 2.5 tonnes. Glushko could not deliver an engine with these characteristics, so Melnikov of OKB-1 was assigned the task of designing the engines in-house. The engine that resulted met the requirements and was the technological basis for later rocket engines developed within OKB-1 (the Lox/Kerosene upper stage engines for the Molniya, N1, and Proton boosters). By February 1954 the stage was reached where a final design was possible. A government declaration of 20 May 1954 authorised development of the two stage R-7 / 8K71 intercontinental ballistic missile. This was followed by a decree of 28 June 1954 'On plans N/R for space research'. Implementation came via a Ministry of Defence decree of 6 July 1954 calling on all industry organisations to work together and assigning the project the highest national priority. The draft project, using much material generated for the T-1 project, was completed in July 1954. The vehicle in the draft project used the 'packet' layout with a hammerhead core stage surrounded by four shorter booster stages. At ignition, the four booster stages ignited. If full thrust was achieved, the core was then ignited and the booster rose on the thrust of all five stages. The rocket could boost the 5500 kg warhead to 7.9 km/s and 8,000 km range, with a maximum miss distance of plus or minus 10 km. The warhead was the German 'sharp point': a 16 degree cone, 7.27 m long, mounted atop a cylindrical interstage section. The rocket had a gross lift-off mass of 280 tonnes, and an empty mass of 27 tonnes. The first stage burned out at 2,170 m/s and the second stage at 6,385 m/s. Thrust at lift-off was 403.4 tonnes. The R-7 incorporated ingenious solutions in ground handling of the large rocket. The rocket would be assembled horizontally, rolled out to the pad, then raised to the vertical position and quickly fuelled. The expert commission deemed the decree requirements to be fulfilled and recommended construction of the rocket with minor changes in the development plan. The government authorised the construction phase in a decree of 20 November 1954. Korolev froze the design on 11 March 1955 and drawing release and parts fabrication began. Meanwhile work was underway to provide the infrastructure needed for the test programme. The Soviet Union was so vast that it was possible to test a missile with intercontinental range within its borders. A warhead impact area on the Kamchatka peninsula was selected, and in August 1955 at unit was formed at the village of Klyuchan in the Ust-Kamchatka region. Although eventually operated by the strategic rocket forces, his base was originally founded in 1913 to support the Kamchatka Fleet. To track incoming warheads, station NIP-6 was built at Ylizora in addition to NIP-7 at Klyuchan. By 20 March 1956 a decree set forth the impending three stage development test plan:
In the first half of 1956 work began in earnest at 36 factories with the objective of making the first test flight by the end of the year. The first article completed was a full scale mock-up consisting of the core and one booster stage. Two Block A and B stages were delivered for stand tests, but incomplete factory test equipment held up the start. At that point it seemed impossible that a flight would be made within the year. By the second half of 1956 solutions had been found to the outstanding problems. Serial production of rockets had begun. The Progress Aviation Factory in Samara, V Ya Litvinov manager, had been selected to fabricate detailed parts but final assembly of the prototype rockets was carried out at Factory 88 in Kaliningrad. Over time the factory at Samara would be organised as the Third Filial of OKB-1 and take over first production, and then engineering, of future R-7 derivatives. In 1974 it became the TsKB, a separate entity. R-7 systems were developed in the following research program:
Launches: 27. Failures: 10. First Launch Date: 1957-05-15. Last Launch Date: 1961-02-27. Apogee: 1,000 km (600 mi). Associated Spacecraft: Sputnik 1, Sputnik 2, Sputnik 3, VKA Myasishchev 1957, VKA-23 Design 2, Zenit, VKA-23 Design 1. Liftoff Thrust: 3,904.000 kN (877,654 lbf). Total Mass: 279,100 kg (615,300 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 33.50 m (109.90 ft). Standard warhead mass: 5,370 kg (11,830 lb). Maximum range: 8,000 km (4,900 mi). Number Standard Warheads: 1. Standard warhead yield: 3,000 KT. Standard warhead CEP: 3.39 km (2.10 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Boost engine: RD-107. Cruise Propulsion: Liquid rocket, Lox/Kerosene. Cruise engine: RD-108. Guidance: Command Link.
R-7A.
The R-7A was an improved version of the R-7 first ICBM, and the one actually deployed to pads in Baikonur and Plesetsk. The missile saw service from 1960 to 1968. Four pads at Plesetsk, and one reserve pad at Baikonur, were operational at the peak of deployment in 1962. These were the Soviet Union's only strategic missile deterrent during the Cuban Missile Crisis. Development of the R-7A was authorised in a government resolution of 2 July 1958. The original R-7, with a range of 8,000 km, could not reach major strategic centres in the United States from Tyuratam. A 12,000 to 14,000 km range was necessary for this. Another alternative was basing from the more northerly Plesetsk launch site. Flight of trials of a related protoype, the R-7 Lot III with provisions for a nuclear warhead, began on 24 December 1958. Tests of this series concluded on 27 November 1959 and test of the first R-7A came on 24 December 1959. Despite this failed launch, Cold War pressures meant that the R-7A conditionally entered service on 31 December 1959. Of the series of eight prototype launches, only four reached the impact zone in Kamchatka, a range of 9,500 km being demonstrated. The R-7A was fully accepted for service by the military on 12 September 1960. A further updated 12,000 km range R-7A with a lighter warhead was flight tested in the early 1960's, but never put into service. This was identified by the Americans as the 'SS-6 Mod. 3'. Production of the R-7A was done at Aviation Factory Number 1, 'Progress', in Kuibyshev (Samara). Construction of the launch facilities was in advance of the missile testing. Delivery of equipment for four operational launch pads at Plesetsk began in early 1959. The first launch complex (LC41, code name 'Lesobaza') was essentially complete and accepted by the military in November 1959. During 1960 LC16 became the second R-7A ICBM launch complex to become operational. All four R-7A launch complexes at Plesetsk, with LC31 at Tyuratam as an emergency alternate launch pad, were accepted by the military in July 1961. The Plesetsk pads were manned by a Strategic Rocket Forces regiment, consisting of one launch station group and four launch units. A major test of the regiment came on 16 July 1960, when the regiment conducted an exercise with launch of two R-7A's, demonstrating the radio guidance system, within 8 hours of each other. The missiles on the four pads were programmed to hit New York, Washington, Los Angeles, and Chicago. During the Cuban missile crisis (11 September to 21 November 1962), an R-7A with a live thermonuclear weapon was held in readiness on pad LC41 for launch on the United States with an 8 to 12 hour reaction time from the go order. This was the only time an R-7A was actually armed with a nuclear warhead during its service life (early Soviet doctrine was that the warheads be stored and controlled separately). The R-7A, with its slow reaction time and vulnerability to enemy counter-strikes, was withdrawn as more modern ICBM's were deployed in the 1960's. LC 41 was withdrawn from ICBM service in 1963 and converted to a space launch pad for R-7-derived launch vehicles. LC16 and the two pads at LC43 continued in service until the R-7A was withdrawn from military service in 1968. LC 16 was cannibalised to rebuild the LC1 at Baikonur, and LC43 was converted to use as a space launch facility. Each operational R-7A launch site cost 500 million roubles. This included the expense of the down-range radar and the radio control stations, each of which had to be located in taiga or bog and required the building of new roads and power lines. The R-7A generated its cut-off signal internally using a battery-like electronic integrator. This required constant removal, recharge, and recalibration. A third launch base for the R-7A was planned for Krasnoyarsk but never built. Launches: 25. Failures: 2. First Launch Date: 1959-12-23. Last Launch Date: 1967-07-25. Apogee: 1,000 km (600 mi). Liftoff Thrust: 3,996.850 kN (898,528 lbf). Total Mass: 272,900 kg (601,600 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 28.00 m (91.00 ft). Span: 9.76 m (32.02 ft). Standard warhead mass: 5,400 kg (11,900 lb). Maximum range: 9,500 km (5,900 mi). Number Standard Warheads: 1. Standard RV: RDS-37. Standard warhead: 46A. Standard warhead yield: 3,000 KT. Flyaway Unit Cost $: 33.000 million. in: 1985 unit dollars.
Sputnik 8K71PS.
Relatively unmodified R-7 ICBM test vehicles used to launch first two Sputniks.
Launches: 2. First Launch Date: 1957-10-04. Last Launch Date: 1957-11-03. LEO Payload: 500 kg (1,100 lb). to: 200 km Orbit. at: 65.00 degrees. Liftoff Thrust: 3,886.000 kN (873,607 lbf). Total Mass: 267,000 kg (588,000 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 30.00 m (98.00 ft). Span: 9.76 m (32.02 ft). Flyaway Unit Cost $: 33.000 million. in: 1985 unit dollars.
Sputnik 8A91.
Modified R-7 ICBM used to launch Sputnik 3.
Launches: 2. Failures: 1. First Launch Date: 1958-04-27. Last Launch Date: 1958-05-15. LEO Payload: 1,327 kg (2,925 lb). to: 217 km Orbit. at: 65.00 degrees. Liftoff Thrust: 3,784.900 kN (850,879 lbf). Total Mass: 269,300 kg (593,700 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 31.10 m (102.00 ft). Span: 9.76 m (32.02 ft). Flyaway Unit Cost $: 33.000 million. in: 1985 unit dollars.
Luna 8K72.
R-7 ICBM with single-engine upper stage used for early Soviet unmanned lunar shots. The problem of start-up of a rocket stage in zero-G was not solved in the Soviet Union until Korolev's Luna upper stage was developed for the R-7. A 20 March 1958 government resolution required the first launch of a Soviet probe to the moon within a year. In this period Glushko was developing the RD-109 engine for a high performance R-7 third stage. This burned liquid oxygen and UDMH propellants, achieving the astonishing specific impulse of 350 seconds. This would potentially double the payload compared to a liquid oxygen/kerosene stage. But the new technology engine was considered too much of a risk by Korolev. It also used the toxic hydrazine fuel he detested on principal. So on 10 October 1958 he gave Kosberg the task of developing a third stage engine for the R-7 derived from the R-7 first stage verniers and burning his preferred liquid oxygen/kerosene propellants. This would power the first Luna probes to the moon and later be developed into the Vostok and Molniya upper stages. Launches: 9. Failures: 7. First Launch Date: 1958-09-23. Last Launch Date: 1960-04-16. LEO Payload: 4,000 kg (8,800 lb). Payload: 280 kg (610 lb). to a: translunar trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: Luna E-1, Luna E-1A, Luna E-3. Liftoff Thrust: 3,956.760 kN (889,515 lbf). Total Mass: 277,000 kg (610,000 lb). Core Diameter: 2.60 m (8.50 ft). Total Length: 30.84 m (101.18 ft).
Vostok 8K72.
8K72 Luna launch vehicle, third stage modified with larger forward cylindrical section to accomodate Vostok-sized spacecraft. Used only for launch of first few prototype Vostoks.
Launches: 4. Failures: 1. First Launch Date: 1960-05-15. Last Launch Date: 1960-12-01. LEO Payload: 4,550 kg (10,030 lb). to: 200 km Orbit. at: 65.00 degrees. Apogee: 500 km (310 mi). Associated Spacecraft: Vostok 1K. Liftoff Thrust: 3,873.740 kN (870,851 lbf). Total Mass: 281,375 kg (620,325 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 30.84 m (101.18 ft).
Vostok 8K72K.
R-7 ICBM with single-engine third stage, uprated from Luna launch vehicle and with forward fairing to accomodate Vostok/Zenit sized spacecraft. 8K72K, used for Vostok manned spacecraft launches and the first Zenit launch attempt.
Launches: 13. Failures: 2. First Launch Date: 1960-12-22. Last Launch Date: 1964-07-10. LEO Payload: 4,730 kg (10,420 lb). to: 200 km Orbit. at: 65.00 degrees. Apogee: 70,000 km (43,000 mi). Associated Spacecraft: Elektron-A, Elektron-B, Vostok 1K, Vostok 3KA, Zenit-2. Liftoff Thrust: 3,894.250 kN (875,462 lbf). Total Mass: 281,375 kg (620,325 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 30.84 m (101.18 ft).
Voskhod 11A57.
The 11A57 took the large third stage originally developed for the 8K78 interplanetary probe projects and applied it to increasing R-7 low earth orbit performance. It was primarily designed to launch the Zenit-4 reconnaisance satellite, but was also used for the Voskhod manned flights and later for a variety of other Zenit series versions.
Launches: 300. Failures: 13. Success Rate: 95.67%. First Launch Date: 1963-11-16. Last Launch Date: 1976-06-29. LEO Payload: 5,900 kg (13,000 lb). to: 200 km Orbit. at: 65.00 degrees. Apogee: 500 km (310 mi). Associated Spacecraft: Energia, Nauka, Voskhod 3KD, Voskhod 3KV, Zenit-2, Zenit-2M, Zenit-4, Zenit-4M, Zenit-4MK. Liftoff Thrust: 3,999.930 kN (899,220 lbf). Total Mass: 298,400 kg (657,800 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 30.84 m (101.18 ft). Launch Price $: 18.000 million. in: 1994 price dollars.
Vostok 8A92.
The 8A92 was a modernized version of the Vostok booster used for launch of Zenit-2 reconnaisance satellites.
Launches: 45. Failures: 5. Success Rate: 88.89%. First Launch Date: 1962-06-01. Last Launch Date: 1967-05-12. LEO Payload: 4,730 kg (10,420 lb). to: 200 km Orbit. at: 65.00 degrees. Apogee: 500 km (310 mi). Associated Spacecraft: Zenit-2. Liftoff Thrust: 3,996.850 kN (898,528 lbf). Total Mass: 281,375 kg (620,325 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 30.84 m (101.18 ft).
Vostok 8A92M.
Second generation space systems required injection of lighter but higher-altitude Meteor and other satellite payloads into sun-synchronous orbits. The 8A92M version was developed for this purpose. First use was the Meteor launch on 29 June 1977.
Launches: 94. Failures: 2. Success Rate: 97.87%. First Launch Date: 1964-08-28. Last Launch Date: 1991-08-29. LEO Payload: 3,800 kg (8,300 lb). to: 850 km Orbit. at: 81.00 degrees. Apogee: 1,000 km (600 mi). Associated Spacecraft: Astrofizika, IK-B-1300, IRS, Iskra, Meteor, Meteor-2, Meteor-Priroda, Meteor M, Resurs-O1, Resurs-OE, Tselina-D. Liftoff Thrust: 3,996.850 kN (898,528 lbf). Total Mass: 282,300 kg (622,300 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 30.84 m (101.18 ft).
Sputnik 11A59. Status: Retired 1964. Other Designations: Polyot. Library of Congress Designation: A. Department of Defence Designation: SL-10. Article Number: 11A59. Two stage version of Vostok 11A57. Used for flight test of prototype Chelomei ASAT after cancellation of UR-200 booster and before availability of Tsiklon.
Launches: 2. First Launch Date: 1963-11-01. Last Launch Date: 1964-04-12. LEO Payload: 1,400 kg (3,000 lb). to: 300 km Orbit. at: 59.00 degrees. Apogee: 1,500 km (900 mi). Associated Spacecraft: Polyot. Liftoff Thrust: 3,999.930 kN (899,220 lbf). Total Mass: 277,000 kg (610,000 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 30.00 m (98.00 ft).
Vostok 11A510. Status: Retired 1966. Library of Congress Designation: A. Department of Defence Designation: SL-5. Article Number: 11A510. Version of R-7 launch vehicle with Vostok second stage and unknown third stage used only twice to launch prototype RORSATs. These satellites were originally to have been launched on the cancelled UR-200 launcher, and operational satellites used Tsyklon-2 launchers.
Launches: 2. First Launch Date: 1965-12-27. Last Launch Date: 1966-07-20. LEO Payload: 4,500 kg (9,900 lb). to: 200 km Orbit. at: 65.00 degrees. Apogee: 250 km (150 mi). Associated Spacecraft: US-A. Liftoff Thrust: 4,037.700 kN (907,711 lbf). Total Mass: 275,000 kg (606,000 lb). Core Diameter: 10.30 m (33.70 ft). Total Length: 31.00 m (101.00 ft).
Soyuz 11A511.
Standardized launch vehicle designed to replace a proliferation of earlier models (8K72, 8A91, 8K74, 8K78, 11A57). Designed initially to support launch of the Soyuz complex (7K manned, 9K rocket stage, and 11k tanker) and Zenit-4 reconnaisance satellite. Later 'U' model extended to cover a range of follow-on satellites. Compared to 11A57, the telemetry system was reduced in mass to no more than 150 kg, and engines were cherry-picked for the vehicle core to ensure that specific impulse was no less than 252 seconds at sea level, 315 in vacuum.
Launches: 30. Failures: 2. Success Rate: 93.33%. First Launch Date: 1966-11-28. Last Launch Date: 1975-05-24. LEO Payload: 6,450 kg (14,210 lb). to: 200 km Orbit. at: 51.60 degrees. Associated Spacecraft: Soyuz 7K-OK, Soyuz 7K-T, Soyuz 7K-T/A9, Soyuz 7KT-OK. Liftoff Thrust: 4,037.700 kN (907,711 lbf). Total Mass: 308,000 kg (679,000 lb). Core Diameter: 10.30 m (33.70 ft). Total Length: 45.60 m (149.60 ft).
Soyuz 11A511L.
11A511 with reinforced second stage, large fairing for earth orbit test of LK lunar lander.
Launches: 3. First Launch Date: 1970-11-24. Last Launch Date: 1971-08-12. LEO Payload: 5,500 kg (12,100 lb). to: 200 km Orbit. at: 51.60 degrees. Apogee: 400 km (240 mi). Associated Spacecraft: LK. Liftoff Thrust: 4,054.000 kN (911,375 lbf). Total Mass: 300,000 kg (660,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 50.00 m (164.00 ft).
Soyuz 11A511M. Status: Retired 1976. Other Designations: Soyuz. Library of Congress Designation: A-2. Department of Defence Designation: SL-4. ASCC Reporting Name: Sapwood. Article Number: 11A511M. Development of the Soyuz-M began in 1967 to launch the 6.6 metric ton Soyuz 7K-VI manned military spacecraft into a 65-degree inclination earth orbit. The spacecraft was cancelled, but development continued, and eight were Soyuz-M's were built and used to launch Zenit-4MT reconnaissance satellites in 1971-1976. The differences compared to the Soyuz-U are not known, and what (if anything) differentiated these Zenit-4MT missions from others is also a mystery. The Kozlov filial of Korolev's OKB-1 was tasked with designing the Soyuz 7K-VI manned military spacecraft. In the first quarter of 1967 a substantially revised design was issued. The new spacecraft, with a crew of two, would have a total mass of 6.6 metric tons and could operate for a month in orbit. However the 11A511 launch vehicle could only put 6.3 metric tons into the 65 degree inclination design orbit. This would limit the crew to one. However the military objected to this. A second cosmonaut, without a spacesuit, but with life support systems and consumables would take another 400 kg of payload. In order to meet the military requirements, Kozlov designed a new variant of the Soyuz launch vehicle, the 11A511M Soyuz-M. The project as reformulated was approved by the central committee on 21 July 1967 by the Central Committee of the Communist Party, with first flight to be in 1968 and operations to begin in 1969. However by the end of the year Kozlov's version of the spacecraft and the project had been taken over by Mishin's main office of OKB-1. Development of the 11A511M continued for a time, perhaps to support planned solo flights of the Soyuz 7K-S military variant (cancelled in 1974). Eight of the 11A511M were built and eventually used to launch a few Zenit-4MT reconnaissance satellite missions from Plesetsk in the early 1970's (all other Zenit-4MT used the standard 11A511U). The differences compared to the 11A511U are not known, and what (if anything) differentiated these Zenit-4MT missions from others is also a mystery. Launches: 8. First Launch Date: 1971-12-27. Last Launch Date: 1976-03-31. LEO Payload: 6,600 kg (14,500 lb). to: 300 km Orbit. at: 65.00 degrees. Apogee: 400 km (240 mi). Associated Spacecraft: Zenit-4MT. Liftoff Thrust: 4,054.000 kN (911,375 lbf). Total Mass: 300,000 kg (660,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 50.00 m (164.00 ft).
Soyuz 11A511U.
A standardised orbital launch vehicle derived from the original R-7 ICBM that was launched in the greatest numbers in history. Not coincidentally, the most reliable launch vehicle as well. After over 30 years service in Russia, ESA is building a new launch pad at Kourou which will likely extend its service deep into the 21st Century. Soyuz-U was a standardised, modernised version of the R-7 launch vehicle with higher performance first and second stage engines. Improvements were made to the launch complexes, including unified test-launch ground support equipment. The booster was first used for the Apollo-Soyuz launches. Military applications included Zenit and Yantar military reconnaisance satellites. Soyuz 11A511U used chilled higher density fuel in the core stage to improve payload. This became the most-widely used version, launching a range of military and manned spacecraft for over thirty years. Starsem Official Description Considered in Russian terminology to be a three-stage vehicle, Soyuz is composed of a lower portion consisting of four boosters (first stage) and a central core stage (second stage); and an upper portion, composed of a third stage, payload adapter and fairings. Liquid oxygen and kerosene are used as propellants for the complete Soyuz launch vehicle. The four first stage boosters are assembled laterally around the second stage central core. The boosters are identical and cylindrical-conic in shape -- with the oxygen tank in the upper cone-shaped portion and the kerosene tank in the lower cylindrical portion. Ignition of the boosters and second stage central core occur simultaneously on the ground. When the boosters have completed their powered flight during ascent, they are separated and the core second stage continues to function. The boosters' NPO Energomash RD-107 engines have four main chambers and a set of two gimballed vernier thrusters. Three-axis flight control is ensured by the four sets of vernier thrusters. The RD 107 engines' main chambers, like the vernier thrusters, are fed by a turbopump, which is powered by gasses generated from the catalytic decomposition of hydrogen peroxide in a gas generator. A pyrotechnic ignition switch provides ignition for the RD-107 engines. Booster separation occurs when the predefined velocity is reached, and occurs at about 118 seconds after lift-off. An NPO Energomash RD 108 engine powers the Soyuz second stage. This engine differs from those of the boosters by the presence of four vernier thrusters, which are necessary for three-axis flight control after booster separation. An equipment bay located on top of the second stage operates during the entire flight of the first stage/second stages. The third stage is linked to the second stage by a latticework structure. When the second stage's powered flight is complete, the third stage engine is ignited. Separation of the two stages occurs by the direct ignition forces of the third stage engine. A single-turbopump RD 0110 engine from KB KhA powers the Soyuz third stage. It is fuelled by gases coming from the combustion of propellants through a generator. At the turbine exit, the gases are recovered to feed four vernier thrusters to ensure three-axis flight control. The third stage engine is fired for about 240 seconds, and cut-off occurs when the calculated velocity increment is reached. The upper section with payload is separated by springs. The third stage then performs an avoidance manoeuvre by opening an outgassing valve in the liquid oxygen tank. Soyuz launcher tracking and telemetry is provided through systems in the second and third stages. These two stages have their own radar transponder systems for ground tracking. Individual telemetry transmitters are in each stage. Launcher health status is downlinked to ground stations along the flight path. Telemetry and tracking data are transmitted to the TsUP mission control centre near Moscow, where the incoming data flow is recorded. Partial real-time data processing and plotting is performed for flight following and initial performance assessment. All flight data is analysed and documented within a few hours after launch. Launches: 699. Failures: 18. Success Rate: 97.42%. First Launch Date: 1973-05-18. Last Launch Date: 2003-02-02. LEO Payload: 7,200 kg (15,800 lb). to: 200 km Orbit. at: 51.60 degrees. Payload: 6,220 kg (13,710 lb). to a: 240 km, 51.8 deg trajectory. Associated Spacecraft: AMOS, Bion, Cluster 2, Efir, Energia, Foton, GFZ-1, Globalstar, Inspector, Mirka, Nauka, Orlets-1, OSCAR, Pion, Progress, Progress M, Progress M-SO, Progress M1, PS Model, Resurs F1-14F40, Resurs F1-14F43, Resurs F1-17F41, Resurs F1M, Resurs F2. Other Associated Spacecraft: Soyuz 7K-MF6, Soyuz 7K-S, Soyuz 7K-T, Soyuz 7K-T/A9, Soyuz 7K-TM, Soyuz T, Soyuz TM, Yantar-1KFT, Yantar-2K, Yantar-4K1, Yantar-4KS1, Zenit-2M, Zenit-4MK, Zenit-4MKM, Zenit-4MKT, Zenit-4MT, Zenit-6U, Zenit-8. Liftoff Thrust: 4,030.000 kN (905,980 lbf). Total Mass: 310,000 kg (680,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 50.67 m (166.24 ft). Launch Price $: 40.000 million. in: 1999 price dollars.
Soyuz-U. Status: Active.
Manufacturer: Kozlov. Launches: 26. First Launch Date: 2003-06-08. Last Launch Date: 2007-12-23. Liftoff Thrust: 7,200.000 kN (1,618,600 lbf). Total Mass: 310,000 kg (680,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 50.70 m (166.30 ft).
Soyuz 11A511U2.
Soyuz 11A511U2 used synthetic kerosene ('Sintin') in first stage for launch of premium reconnaisance satellite and manned payloads requiring just a bit more payload than the standard 11A511 could offer. Further use of the 11A511U2 abandoned in 1996 due to Sintin production stoppage. Later Soyuz spacecraft launched on standard Soyuz, with reduced payload and rendezvous with Mir in lower orbit accepted.
Launches: 92. Failures: 2. Success Rate: 97.83%. First Launch Date: 1982-12-23. Last Launch Date: 1995-09-03. LEO Payload: 7,050 kg (15,540 lb). to: 200 km Orbit. at: 51.60 degrees. Apogee: 500 km (310 mi). Associated Spacecraft: Foton, Gamma, Mak, Orlets-1, Progress, Progress M, Soyuz T, Soyuz TM, Yantar-4KS1, Zenit-6U. Liftoff Thrust: 4,060.650 kN (912,870 lbf). Total Mass: 297,800 kg (656,500 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 34.54 m (113.32 ft).
Soyuz 11A511U / Fregat. Status: Design 2000. Standard Soyuz universal booster with the Fregat upper stage, derived from the propulsion system for Lavochkin interplanetary probes. The Fregat upper stage has a flight-proved propulsion subsystem that is based on a single-chamber Lavochkin engine. Four clusters of three 50-N hydrazine thrusters provide attitude control. The Fregat propulsion system powered the Fobos probe to Mars, and the main engine was fitted on nearly 30 interplanetary spacecraft. During its numerous missions, the engine demonstrated the highest reliability under extreme conditions, exceeding technical specifications. This application of proven, in-production hardware ensures high reliability and lower cost for the Fregat upper stage. Fregat operates on UDMH fuel and N2O4 oxidizer, and has a liftoff mass of up to 6,535 kg. The weight at burnout is 950-1,100 kg.. Vacuum thrust is 19.6 kN., and burn time is up to 877 sec. The engine can be restarted as many as 20 times. LEO Payload: 5,000 kg (11,000 lb). to: 450 km Orbit. at: 51.80 degrees. Payload: 2,700 kg (5,900 lb). to a: sun synchronous, 800 km, 98.6 deg inclination trajectory. Apogee: 500 km (310 mi). Liftoff Thrust: 4,030.000 kN (905,980 lbf). Total Mass: 305,000 kg (672,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 46.10 m (151.20 ft). Launch Price $: 50.000 million. in: 1999 price dollars.
Soyuz 11A511U / Ikar.
Standard Soyuz universal booster with the Ikar upper stage, derived from the propulsion system for the Kozlov Yantar series of spy satellites. The Ikar upper stage was part of the Soyuz launch system upgrade policy. Built by TsSKB in Samara, this fourth stage was derived from an existing flight-proven module that has been used successfully more than 30 times on Yantar spy satellite missions. Equipment and subsystems from the module were used to the maximum extent to limit new development. Modifications were primarily limited to some of command/control equipment and certain mechanical/electrical interfaces with the payload. Ikar had a mass of 820 kg. and was located under the payload fairing. With an in-flight restart capability of up to 50 times, it can handle deployment of multi-satellite payloads to different orbits. The stage can be controlled from the ground or in an operate autonomous mode. The stage was powered by a 17D61 engine from KB Melnikov and had a vacuum thrust of 2.943 kN. It operated on UDMH/N2O4 propellant and had 16 vernier engines for flight control. LEO Payload: 4,100 kg (9,000 lb). to: 450 km Orbit. at: 51.80 degrees. Payload: 2,750 kg (6,060 lb). to a: sun synchronous, 800 km, 98.6 deg inclination trajectory. Apogee: 500 km (310 mi). Liftoff Thrust: 4,030.000 kN (905,980 lbf). Total Mass: 305,000 kg (672,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 43.40 m (142.30 ft). Launch Price $: 50.000 million. in: 1999 price dollars.
Soyuz FG. Status: Active. Library of Congress Designation: A-2. Department of Defence Designation: SL-4. ASCC Reporting Name: Sapwood. Uprated Soyuz booster designed for high performance Russian government missions - delivery of Soyuz and Progress spacecraft to the International Space Station. Upgraded engines, modern avionics, reduced non-Russian content. Unknown differences to Soyuz ST. Modernisation of the Soyuz launcher that increased general performance. The basic launch vehicle design remained the same. Changes on the commercial ST version were limited to:
The standard fourth stage was the Fregat orbital module. Launches: 22. First Launch Date: 2001-05-20. Last Launch Date: 2007-12-14. LEO Payload: 7,420 kg (16,350 lb). to: 193 km Orbit. at: 51.80 degrees. Apogee: 500 km (310 mi). Associated Spacecraft: Kolibri, Progress M1, Soyuz TMA. Liftoff Thrust: 4,143.000 kN (931,383 lbf). Total Mass: 305,000 kg (672,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 46.10 m (151.20 ft). Launch Price $: 50.000 million. in: 1999 price dollars.
Soyuz ST.
Uprated Soyuz booster designed for commercial customers. Upgraded engines, modern digital avionics, reduced non-Russian content. Can be used with either Ikar or Fregat upper stages. The 'FG' was the military version. Also known as the Soyuz 2, it was a modernisation of the Soyuz launcher that increased general performance. The basic launch vehicle design remained the same. Changes were limited to:
The standard fourth stage was the Fregat orbital module. Launches: 3. First Launch Date: 2004-11-08. Last Launch Date: 2006-12-24. LEO Payload: 7,800 kg (17,100 lb). to: 240 km Orbit. at: 51.80 degrees. Liftoff Thrust: 4,144.700 kN (931,766 lbf). Total Mass: 310,000 kg (680,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 43.40 m (142.30 ft). Launch Price $: 40.000 million. in: 1999 price dollars. Cost comments: $ 30 to 50 million price per launch quoted ca. 1999 by Starsem.
Soyuz ST / Fregat ST. Status: In production. Library of Congress Designation: A-2. Department of Defence Designation: SL-4. ASCC Reporting Name: Sapwood. Uprated Soyuz booster designed for commercial customers. Upgraded engines, modern avionics, reduced non-Russian content. Uses Fregat upper stage. Also known as the Soyuz 2, it was a modernisation of the Soyuz launcher that increased general performance. The basic launch vehicle design remained the same. Changes were limited to:
The standard fourth stage was the Fregat orbital module. The Fregat upper stage has a flight-proved propulsion subsystem that is based on a single-chamber Lavochkin engine. Four clusters of three 50-N hydrazine thrusters provide attitude control. The Fregat propulsion system powered the Fobos probe to Mars, and the main engine was fitted on nearly 30 interplanetary spacecraft. During its numerous missions, the engine demonstrated the highest reliability under extreme conditions, exceeding technical specifications. This application of proven, in-production hardware ensures high reliability and lower cost for the Fregat upper stage. Fregat operates on UDMH fuel and N2O4 oxidizer, and has a liftoff mass of up to 6,535 kg. The weight at burnout is 950-1,100 kg.. Vacuum thrust is 19.6 kN., and burn time is up to 877 sec. The engine can be restarted as many as 20 times. LEO Payload: 5,500 kg (12,100 lb). to: 450 km Orbit. at: 51.80 degrees. Payload: 4,500 kg (9,900 lb). to a: Sun synchronous, 800 km, 98.5 deg orbital trajectory. Liftoff Thrust: 4,144.700 kN (931,766 lbf). Total Mass: 305,000 kg (672,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 46.10 m (151.20 ft). Launch Price $: 35.000 million. in: 1999 price dollars.
Soyuz-2-1B. Status: Active.
Manufacturer: Kozlov. Launches: 1. First Launch Date: 2006-12-27. Last Launch Date: 2006-12-27. Liftoff Thrust: 7,600.000 kN (1,708,500 lbf). Total Mass: 313,000 kg (690,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 50.70 m (166.30 ft).
Soyuz 11A514. Status: Development ended 1966. Other Designations: Vostok. Library of Congress Designation: A-2. Department of Defence Designation: SL-4. ASCC Reporting Name: Sapwood. Article Number: 11A514. Version of Soyuz launcher with increased payload, designed to launch Soyuz R military reconnaisance satellite. Cancelled along with the Soyuz R project in 1966. Unknown differences to standard Soyuz to reach payload requirement of circa 6700 kg to 65 degree orbit.
LEO Payload: 6,700 kg (14,700 lb). to: 200 km Orbit. at: 65.00 degrees. Associated Spacecraft: Soyuz VI.
Version: Soyuz 11K55. Status: Design 1963. Article Number: 11K55. Complex: 11K55. Version of the Soyuz launcher envisioned for the cancelled Soyuz B translunar rocket stage.
Rus project was to result in first major propulsion upgrade to R-7 family in forty years, using first stage engines derived from those developed for Zenit second stage to boost performance. It would have permitted launches from Plesetsk with same or greater payload than launch of standard Soyuz-U from Baikonur, permitting move of more launch operations back onto Russian territory. Instead the more modest Soyuz ST / Soyuz FG upgrades were made.
LEO Payload: 7,900 kg (17,400 lb). to: 200 km Orbit. Payload: 2,900 kg (6,300 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: Obzor. Liftoff Thrust: 4,334.300 kN (974,389 lbf). Total Mass: 309,180 kg (681,620 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 45.00 m (147.00 ft). Flyaway Unit Cost $: 3.000 million. in: 1985 unit dollars.
Onega.
Launch vehicle proposed for the 'Kliper' manned spaceplane in 2004. The 'Onega' was a hitherto-unrevealed massive improvement of the reliable Soyuz. It would deliver double the payload to a space station orbit, and could be available by 2010 if funding was made available. In order to achieve a payload double that of the current vehicle, it would seem a high-energy Lox/LH2 upper stage would be needed. Such an improvement was proposed as far back as July 1962 (the Molniya 8K78L) but never developed. An existing pad at Baikonur would be modified initially. A pad at Plesetsk, or the new Soyuz pad at Kourou could be modified eventually to accommodate the Onega. LEO Payload: 15,000 kg (33,000 lb). to: 200 km Orbit. at: 51.60 degrees. Associated Spacecraft: Kliper.
Version: Molniya 8K78.
Four stage derivative of the R-7 ICBM developed on a crash-program basis in 1960 for Soviet lunar and planetary deep space probe missions. The third stage found later use in the Voskhod and Soyuz launchers. By the 1970's mature versions of the launch vehicle were used almost entirely for launch of Molniya communications satellites and Oko missile early warning spacecraft into elliptical, 12-hour earth orbits. On 15 January 1960 Korolev signed the order for development of a four stage rocket based on the R-7. The draft project was completed on 10 May 1960. The original design was intended for launch of unmanned probes toward Mars, but it had universal uses. The first two stages - the four strap-ons of the first stage and the second core stage - were based on the R-7 ICBM, but reinforced for the heavier upper stages. On aerodynamic grounds the new third stage had to follow closely the diameter of the Vostok third stage. Therefore it could only be increased from the Vostok's 2.58 m to 2.66 m diameter. The new third stage used engines developed for the R-9 ICBM. Although first developed for the Monlniya four-stage booster, it later would be used with modifications in the three-stage Soyuz launch vehicle. The fourth stage would have to restart in weightless conditions in an earth parking orbit, presenting a number of problems. It needed to be equipped with an orientation and stabilization system (SOIS) and a jettisonable engine section (BOZ). The BOZ had to start in weightlessness provide a low thrust to settle the propellants in the main stage so that the main engine could ignite. The stage was based on the existing Vostok third stage, with two toroidal tanks of 600 mm cross section, and a single S1-5400 Lox/kerosene engine. Launches: 20. Failures: 11. First Launch Date: 1960-10-10. Last Launch Date: 1965-12-03. Payload: 900 kg (1,980 lb). to a: interplanetary trajectory. Associated Spacecraft: Luna E-6, Mars 1M, Mars 2MV-1, Mars 2MV-2, Mars 2MV-3, Mars 2MV-4, Mars 3MV-4A, Molniya-1, Molniya-1T, Venera 1VA, Venera 3MV-1A. Liftoff Thrust: 3,999.930 kN (899,220 lbf). Total Mass: 303,500 kg (669,100 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 40.00 m (131.00 ft). Flyaway Unit Cost $: 39.000 million. in: 1985 unit dollars.
Molniya 8K78/E6. Status: Retired 1965. Molniya adaptation for launch of E-6 lunar probes.
Launches: 4. Failures: 3. First Launch Date: 1963-01-04. Last Launch Date: 1965-03-12. Apogee: 400,000 km (240,000 mi). Liftoff Thrust: 4,054.000 kN (911,375 lbf). Total Mass: 306,200 kg (675,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 44.40 m (145.60 ft).
Molniya 8K78L. Status: Study 1962. Article Number: 8K78L. The Molniya 8K78L was designed by Korolev's design bureau for launching a manned spacecraft on a flyby of the Moon and return to earth. To achieve this it would have used Lox/LH2 engines in the third and fourth stages. Preliminary design was completed on 8 July 1962, but such technology was years away in the Soviet Union and the project was not pursued further.
Payload: 5,000 kg (11,000 lb). to a: translunar trajectory.
Version: Molniya 8K78M.
Improved Molniya, in variants with Blocks ML, 2BL, or SO-L third stages according to payload.
Launches: 294. Failures: 20. Success Rate: 93.20%. First Launch Date: 1964-02-19. Last Launch Date: 2007-10-23. LEO Payload: 1,800 kg (3,900 lb). to: 820 km Orbit. Payload: 1,600 kg (3,500 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: IRS, Luna E-6, Luna E-6LF, Luna E-6LS, Luna E-6M, Luna E-6S, Magion, Microsat, Molniya-1, Molniya-1T, Molniya-2, Molniya-3, Oko, Prognoz, Prognoz-M, Skipper, SRET, Venera 1V (V-67), Venera 2V (V-69), Venera 2V (V-69), Venera 3MV-1, Venera 3MV-1A. Other Associated Spacecraft: Venera 3MV-3, Venera 3MV-4, Venera 3V (V-70), Venera 3V (V-72). Liftoff Thrust: 4,016.000 kN (902,832 lbf). Total Mass: 305,460 kg (673,420 lb). Core Diameter: 2.99 m (9.80 ft). Total Length: 40.00 m (131.00 ft). Launch Price $: 25.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 39.000 million. in: 1985 unit dollars.
Molniya 8K78M 2BL. Improved Molniya variant with Blok-2BL upper stage for placement of Oko early-warning satellites into Molniya-class orbits with apogees of 38,000 km.
Payload: 2,000 kg (4,400 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 4,054.000 kN (911,375 lbf). Total Mass: 305,000 kg (672,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 43.40 m (142.30 ft).
Molniya 8K78M ML. Improved Molniya variant with Blok-ML upper stage for placement of communications satellites into Molniya-class orbits with apogees of 38,500 km.
Payload: 2,000 kg (4,400 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 4,054.000 kN (911,375 lbf). Total Mass: 305,000 kg (672,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 43.40 m (142.30 ft).
Molniya 8K78M SOL. Improved Molniya variant with Blok SO-L upper stage for placement of Prognoz-class satellites in orbits with apogees of 200,000 km.
Payload: 2,000 kg (4,400 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 400,000 km (240,000 mi). Liftoff Thrust: 4,054.000 kN (911,375 lbf). Total Mass: 305,000 kg (672,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 43.40 m (142.30 ft).
Yamal. Orbital launch vehicle. Country: Russia. Status: Study 1997. Version of the Soyuz proposed with an Ariane 4 or Russian Lox/LH2 upper stage. In order to achieve a payload double that of the current vehicle, it would seem a high-energy Lox/LH2 upper stage would be needed. Such an improvement was proposed as far back as July 1962 (the Molniya 8K78L) but never developed. The version with the Ariane 4 upper stage would be capable of putting 3900 kg into geosynchronous transfer orbit when launched from Kourou. Manufacturer: Korolev. Payload: 3,900 kg (8,500 lb). to a: geosynchronous transfer orbit, 1 deg inclination, trajectory. Soyuz Chronology 1949 December 7 - Groettrup G-4 IRBM evaluated against Korolev's R-3. R-3 project reformulated The NTS (Scientific-Technical Soviet) of NII-88 met in plenary session and subjected Korolev's proposal to withering criticism. The G-4 was found to be superior. After heated discussion, the Soviet approved further development of technology for the R-3, but not the missile itself. The decisions were: an R-3A technology demonstrator would be built and flown under Project N-1 (probably to prove G-4 concepts). Under Project N-2 both the RD-110 and D-2 engines would proceed into development test in order to prove Lox/Kerosene propellant technology. Packet rocket and lightweight structure research for use in an ICBM would continue under project N-3 / T-1. Winged intercontinental cruise missile studies would continue under project N-3 / T-2. Neither the G-4 or R-3 ended up in production, but the design concepts of the G-4 led directly to Korolev's R-7 ICBM (essentially a cluster of G-4's or R-3A's) and the N1 superbooster. Work on the G-4 continued through 1952. 1950 December 4 - Research into intercontinental missile approaches authorised. Council of Soviet Ministers (SM) Decree 'On themes N1, N2, and N3 in the ballistic missile program.' was issued. 1951 October 4 - Russian satellite predicted. M. K. Tikhonravov in New York Times said U.S.S.R. science made feasible space flight and creation of artificial earth satellite; reported U.S.S.R. rocket advance equaled or exceeded West. 1953 February 13 - Authorisation for development of Soviet intermediate and intercontinental range missiles. Council of Soviet Ministers (SM) Decree 'On approval of work on themes T1 and T2, on approval of work on the R-5, R-11, and EKR missiles, and on transferring draft project work for the R-12 from NII-88 to SKB-586' was issued. The decree set forth three phases of state trials tests for the R-5 missile. 1953 April - USSR Council of Ministers approve R-7 ICBM, Buran and Burya intercontinental cruise missiles Informal go-ahead was given for Korolev to start design work on the R-7. In parallel, Myasishchev OKB-23 and Lavochkin OKB-301 began design of intercontinental ramjet cruise missiles. 1954 March 17 - Baikonur and Vladimirovka launch site plans. Council of Soviet Ministers (SM) Decree 'On selection of launch area for the R-7, 40 Buran, and 350 Burya' was issued. 1954 May 20 - R-7 full-scale development authorised. Council of Soviet Ministers (SM) Decree 956-4088s 'On approval of work on the R-7 ICBM, R-5R, and M5RD missiles' was issued. 1954 May 30 - Baikonur -. Go-ahead for R-7 ICBM by designers council Council of Chief designers approval to proceed with development of R-7. 1954 June 28 - R-7 development plans. Council of Soviet Ministers (SM) Decree 'On NIP Plan for Special Product--course of work on the R-7 ICBM' was issued. 1954 November 20 - R-7 draft project approved. Council of Soviet Ministers (SM) Decree 'On approval of the R-7 draft project' was issued. 1955 January 12 - Baikonur -. Tyuratam selected for ICBM test range. Council of Ministers selects Tyuratam for ICBM test site. The first 30 construction workers arrive at Tyuratam. The town founded at the rail staion is called Zarya (Dawn). The name will be changed to Leninsk in January 1958, but Zarya will remain the call sign of Soviet ground control. 1955 April - Baikonur -. Housing/road constructions starts at Tyuratam 1955 June 19 - Baikonur -. First surveyors arrive at Tyuratam. 1955 August - Baikonur -. LC 1 launch pad excavation starts 1956 February 27 - Soviet Leadership tours Korolev's design bureau Khrushche |
