In 1960 the Soviet government decreed development of a lightweight launch vehicle for launch of payloads not requiring R-7 family of boosters. A modification of the R-12 IRBM was selected as the first stage; a new high-performance second stage was developed using a unique Lox/UDMH propellant combination. After two failures, the first successful flight was on March 16, 1962.
Serious consideration of designs for a Soviet light orbital launch vehicle began in the mid-fifties. At the end of 1956 Korolev studied a scientific launch vehicle based on an R-5 first stage and R-11 second stage. He concluded that it could only be used as a sounding rocket, that a new third stage would have to be developed for the combination to have orbital capability.
Yangel studied use of either the R-5M or the R-12 with various 'off the shelf' missile stages developed for surface-to-air missiles, but found that no such combination could reach orbit. Use of the R-12 in parallel stages was also possible, but the problem of in-flight ignition of the core stage was one not solved in the Soviet Union until 1955. Solid rockets available in the Soviet Union at that time had too low a specific impulse and too high a mass fraction to be useful in a satellite launcher. The only solution was a redesign of the R-12 to optimise it for the satellite launch role, and a small, new-design upper stage.
Korolev was anxioius to move on to manned space exploration and was not interested in developing small launch vehicles. He was glad for Yangel to pursue this. However design work at Yangel's bureau was limited and desultory, since there was no outside support for the project until after the worldwide sensation following the launch of the first Sputnik in late 1957. But by then development of Yangel's R-16 ICBM had priority.
A key element in the development of a two-stage space launch vehicle was the solution of in-flight separation and ignition of the second stage following burn-out of the first stage. Yangel's R-16 ICBM was fitted with thrusters on the interstage between the first and second stages to provide thrust between shut-down of the first stage and ignition of the second. This kept the propellants in the tanks and the engine under G-force; there was no coasting period. The solution already adopted for some surface-to-air missiles - a 'hot start' where the second stage ignited while the first stage still was firing - was not adopted due to performance reasons.
Start-up of a rocket stage in zero-G was not solved until Korolev's Luna upper stage for the R-7. This was developed in response to a 20 March 1958 government resolution requiring 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. Meanwhile Glushko pursued further development of the RD-109, which used a 75 atmosphere chamber pressure and a closed engine cycle. By mid-1958 he had encountered various knotty problems in chamber cooling and the gas generator. It was decided to stop all work on the RD-109 in order to concentrate on development of the engines for the R-14 IRBM and R-16 ICBM. The estimated date for completion of development slipped to the end of 1959, too late for it to be used for the Vostok lunar launches. However it could be ready for the Vostok/Zenit manned and reconnaissance spacecraft orbital flights.
Development of the engine on tests stands was finally completed in January 1959, with runs in a 90 cubic metre vacuum chamber at a pressure of 1 mm Hg. The RD-109 that finally emerged had a chamber pressure of 76 to 70 atm and a specific impulse of 334 seconds. The conventional liquid oxygen/kerosene engine that Kosberg had developed as a replacement in the Luna probes (the RD-0105/RO-5) had a specific impulse of 316 seconds. Use of the RD-109 in the Luna stage would have increased payload to 424 kg as opposed to 373 kg with the RD-0105. But for use on the piloted Vostok booster, Korolev refused to consider using UDMH as a fuel due to its toxicity. Therefore he opted to further develop the Kosberg engine for the Vostok, leaving the RD-109 an engine without an application.
However Yangel saw that the engine would be a good match for a high-performance upper stage application. Therefore Glushko agreed to continue to refine the RD-109, now designated the RD-119. The new engine had many improvements in the chamber and nozzle profile and could run at higher chamber temperatures through the use of double-shell wall cooling. The result was a specific impulse of 352 seconds. The engine was run at up to 260 seconds firing durations as opposed to the 150 seconds rated ability.
A government resolution of 8 August 1960 authorised Yangel to develop the 63S1 light orbital launch vehicle for launch of payloads not requiring the R-7 family of boosters and to produce a series of ten for launch of small satellites. The booster had to use the existing R-12 IRBM as a first stage, the existing Mayak launch silo as a launcher, and an existing engine for the upper stage. Since the R-12 was built for silo launch (it could not be held on a surface pad exposed to the elements), the existing R-12 silo 'Mayak-2' at Kapustin Yar was adapted. A swing-back shelter above the top of silo covered the second stage and payload during launch preparations.
The 63S1 was used through May 1966 for a total of 40 launches, of which 12 were failures. The Mayak complex was built for missile launches and was not durable enough for repeated space launches. A space launch complex had to be a virtual 'launch chimney' and endure the flames of many launches and accomodate many different payloads. Therefore the Mayak complex was abandoned and the Voskhod and Raduga complexes were designed for later R-12 and R-14 derived space launchers. The same military cadres designed and built the R-7 Angara complex and missile sites.
The R-12 was the first operationally effective intermediate range ballistic missile, the first Soviet missile deployed with a thermonuclear warhead, and the first mass-produced missile in history. 2,300 of the storable propellant rockets were built and deployed in both mobile and silo-based versions for thirty years, from March 1959 to June 1989. It was a primary element in the Soviet deterrent threatening Western Europe and China throughout the Cold War. Deployment of R-12's to Cuba in 1962 precipitated the Cuba Missile Crisis.
Development of the R-12 was begun in 1950 under Theme N-2 (long range storable propellant missiles). D D Sevruk at OKB-3 of NII-88 conducted the first design work. His pre-draft project envisioned a missile of the same diameter as the R-5, but with 50% to 100% more range. Mikhail Yangel completed the project. He proposed the use of toxic but storable liquid propellants. His bosses, Mishin and Korolev, vehemently opposed this approach. They believed military rockets would be safer using cryogenic liquid oxygen and kerosene propellants. Nevertheless by 13 February 1953 Yangel had completed the development project plan for the missile, with technology tests being conducted at NII-88. Missile tsar Ustinov supported Yangel's approach, and it seemed the only way for the missile to be developed was to move the responsibility away from Korolev.
On 9 May 1951 a resolution had been issued creating an R-1 production facility at Factory 586 at Dnepropetrovsk in the Ukraine, with Vasiliy Budnik as its Chief Constructor. Ukrainian-born Communist Party leader Leonid Brezhnev was promoting the missile production factory and proposed to give Yangel a new design bureau on its premises. This would further the economic development of Ukraine and encourage the development of missiles using storable propellants. The decision was made to move Yangel and the R-12 there as well. A decree issued on 13 December 1953 ordered Factory 586 at Dnepropetrovsk to complete the R-12 design. On 9 July 1954 Yangel was named head of the facility and specifically assigned by Defence Minister Smirnov to develop storable propellant rockets for the army and navy. Development of the R-12 intermediate range ballistic missile was approved on 13 August 1955. The government resolution assigned the missile the industrial index 8K63 and scheduled trials for April 1957.
The draft project was completed in October 1955. A key issue during design was whether the missile could reach the 2,000 km specified range with the maximum allowable payload mass using the planned RD-211 engines - the thrust was simply too low. Engine designer Glushko had designed the RD-211 with four combustion chamber / nozzle assemblies. Each was double the thrust of the V-2-based RD-100 engine, but all four were fed by common turbopumps. Initial tests of the new-design cylindrical combustion chamber showed good results, and versions of this engine were being simultaneously developed for the R-7 ICBM (the RD-107, using liquid oxygen/kerosene propellants) and the Buran intercontinental cruise missile booster (RD-212, using nitric acid/kersosene).
The RD-212 was underpowered for the Buran application, so the design was abandoned and development undertaken of the RD-213 with 22% more thrust. A similar decision was taken in regard to the RD-211 for the R-12, which resulted in the RD-214. Development of the RD-214 began in 1955, and trials started in 1957. These included experimental tests to thoroughly ring out the motor, including on/off operations, off-stand component tests, and demonstrations of pulsed engine operation. Following this first series, necessary modifications were made, and the second test stand series was completely successful. In March 1957 a complete four-chamber prototype engine was installed in the R-12 'iron bird' at Zagorsk for integrated firings with the missile.
Yangel was also committed to providing the R-12 with the Soviet Union's first autonomous inertial navigation system. Korolev's rockets had all used radio-corrected guidance, which could be jammed in wartime. The inertial navigation system planned for the R-12 was tested on R-5M missiles before the R-12 began its flight tests.
For the R-12 Yangel selected the same simple cylindrical 'pencil' configuration as had been used on the R-5M. Korolev, passionately committed to optimum aerodynamics in rockets, favoured the conical designs and 'sharp point' configurations originated by captured German engineers. He declared 'this pencil will not fly'. In defiance of Korolev, the first R-12 test launch was made from Area 21 at Kaputsin Yar on 22 June 1957. 25 R-12's were launched in three phases of test and trials launches through 27 December 1958. The pad-launched version was accepted for military service on 4 March 1959. Khrushchev visited Yangel's Factory 586 in Dnepropetrovsk in July 1959, handed out awards to OKB-586 collectively, and personal awards to Yangel, L V Smirnov, and B S Rudnik.
Between 1956 and 1959 there was an internal controversy as to whether long-range rocket units should be formed within the Red Army, the Long Range AIr Force, or both. This was finally settled on 17 December 1959, when a new branch of the armed services, the RVSN Strategic Rocket Forces, was formed under Marshal Nedelin. The R-12 was to be the first widely-deployed missile for the new service.
Mass production was undertaken beginning in 1958 at three factories in addition to Factory 586: Factory 172 (PMZ Lenin) in Perm, Factory 47 (PO Strela) in Krasnoyarsk, and Aviation Factory 166 (PO Polyot) in Omsk. Omsk and Krasnoyarsk became subsidiaries of OKB-456 in December 1958 and September 1959, and production was stopped there in the early 1960's. Production finally was completed at Perm in 1967, with 2,300 of the missile being built.
Special launches of modified R-12's were made to test subscale versions of the Raketoplan and BOR series of spaceplanes. From 1967 Perm built several special variants for ABM field exercises and testing of ballistic missile countermeasure systems. These included the 8K63E 'List', 8K63K 'Kaktus', 8K63V 'Verba', and 8K63Kr 'Krot'.
Spetsmash began development of the mobile launch system for the missile in 1953. The R-12's launcher was a modification of that already designed for the R-5M. The concept was that the missiles would be stored in a shelter (the 'technical position'). In the vicinity of the shelter were numerous pre-surveyed concrete hard stands, from any of which the missile could be launched. The missiles had a guaranteed seven-year storage life in unfuelled condition. The response time of the missile (from go order to launch) depended on the 'readiness condition'. There were four of these defined for the R-12:
Compared to earlier missiles the R-12 differed in having the 430 kg inertial guidance system located in the intertank section between the fuel and oxidiser tanks. The oxidiser was AK-27I (27% N2O4 and 73% nitric acid) and the fuel TM-185 kerosene. The TG-02 Samin catalyst for the fuel was a Russian version of the German Tonka-250 formulation (50% Triethylamine / 50% Xylidine). The oxidiser was pressurised by gaseous oxygen, the fuel by air. Following burn-out of the single-stage rocket, explosive bolts separated the warhead and it was ejected pneumatically from the missile. Once launched, the missile had a time of flight of 11.8 minutes. Maximum velocity at burnout was 3530 m/s, and warhead accuracy 6 km in range, 5 km laterally.
In order for the missile to keep stability in transonic and supersonic flight, there were two oxidiser tanks forward. The lower tank was drained first in order to match the shifting centre of pressure as the missile accelerated. This had not been a problem in earlier rockets with liquid oxygen oxidiser, which was 33% less dense. The missile's control system regulated the flow from each tank before and after the missile went through the sound barrier.
On 15 May 1960 the first R-12 regiments were activated at Slonim, Novogrudok, and Pinsk in Byelorus, Pulnge in Lithuania, Gezgaly in Kazakhstan, and Sovietsk in Kaliningrad. Each regiment consisted of 2 to 3 launch divisions, each division of two batteries with one launcher. Therefore there were 4 to 6 launchers per regiment.
The engines in the first production missiles were found to pulse due to hot catalyst in the turbopumps. The problem was only fixed following a series of controlled tests of the engine and an aggressive quality assurance program for production missiles. The R-12 was first displayed publicly at a Moscow parade in 1961. American intelligence estimated that 2,300 R-12 missiles were built, with peak deployment being 608 silos and missile launchers in 1965. No Russian figures for production or deployment have been declassified.
The R-12 obtained international notoriety during the Cuban missile crisis. Khrushchev and the Soviet leadership decided to deploy three regiments of the 13th Rocket Division with R-12 IRBM's (24 launchers) and two regiments of longer-range R-14's (16 launchers) to the island of Cuba. The missiles would provide a deterrent to US attack on the island. It would also provide the Soviet Union with a missile deterrent force matching the American Thor and Jupiter missiles in Britain, Italy, and Turkey. By the middle of October 1962, 36 R-12's with nuclear warheads were in Cuba. This precipitated the Cuban Missile Crisis, bringing forces of the US and Soviet Union into direct armed confrontation. In the end Khrushchev agreed to withdrawal the missiles from Cuba. In exchange he obtained secret US assurances never to invade Cuba and to withdraw the Thor and Jupiter missiles.
By the mid-1970's a typical R-12 regiment consisted of two fixed base divisions and one mobile division. Each fixed division consisted of 2 batteries, each battery with 2 rockets. A mobile rocket regiment consisted of 5-8 launchers, 11-14 transport vehicles, 6-7 support trucks, and 41-52 fuel transports. During launch operations the control vehicle and the launcher were separated by 175 m.
A missile forces veteran remembers that the R-12 and R-14 were deployed primarily on surface launch pads. While he was in service he visited at least 15 launch sites: Sovietsk, Gvardeisk, and Znamensk in the Kaliningrad enclave; Taurage and Ukmerge in Lituania, Elgava and Dobele in Latvia, and Postavy and Lida in Belorussia. His own regiment in Priekule, Latvia had 6 silo-based R-14's and 3 R-14 on surface pads. Both the R-12 and R-14 used the same SP6 surface launch pad complex.
The R-12 was replaced beginning in 1977 by the SS-20 Pioner solid propellant missile. In 1987 the US and the Soviet Union signed the INF Treaty, eliminating intermediate range nuclear missiles in Europe. Under the treaty 149 remaining R-12 missiles were scrapped. Of these 65 were in military service at the time of the treaty signature and 84 were stored in weapons dumps. The R-12 missiles were withdrawn from service in June 1989 and destroyed in the presence of US inspectors at Lesnaya in Belarus. The final R-12 was destroyed on 23 May 1990. However the R-12 story was not quite over. It was reported in January 1998 that the R-12 design had been sold to Iran and formed the basis of their Shabad 4 IRBM. By 2004 it was said that this had been abandoned, but that R-12 technology had been applied to an improved version of the Shahab 3 IRBM.
A train-based R-12 with 'hot reload' capability was designed but never got into development. At the beginning of the 1960's a chemical warhead was developed for the R-12. This used the 'Tuman' cassette-type warhead to disperse the agent over a wide area after re-entry. A silo-based R-12U and a light orbital launch vehicle, the 11K63 Kosmos-2, were developed from the R-12, and are treated in separate entries. The latter used a new second stage to reach orbital velocity.
The R-12 was launched with live nuclear warheads on several occasions. In June 1961, in preparation for the first such test series, an attempt was made to fire an R-12 with a functional nuclear warhead without a fissile core toward the Arctic atomic test ground on Novaya Zemlya from a position east of the city of Vorkut. This launch attempt was aborted when an electrical fault was detected. Rather than risk firing the faulty missile, Yangel and Omsk Factory Head Kolnpayev shipped a new production rocket from Omsk.
The first live warhead tests were on 10/12 or 12/16 September 1961 as part of Operation Roza. Two R-12's propelled thermonuclear warheads with different yields from Vorkut and Salekhard to target areas on Novaya Zemlya. These launches were made by the same batteries that would be deployed to Cuba a year later.
Further end-to-end tests of the R-12 with a live nuclear warhead were made in June-July 1962 as part of Operations K1 and K2. In this case the prime purpose was to evaluate the electromagnetic pulse effect of nuclear explosions in order to design anti-ballistic missile systems, survivable radars, and missile silos.
The R-12's were launched toward the prototype ABM site at Sary Shagan.
In October-November 1962 R-12's were used in operations K-3, K-4, and K-5 to explode thermonuclear warheads at altitudes of 300, 150, and 60 km. These high altitude tests were designed to test electromagnetic pulse effects on electronics, especially ABM system radars. They disrupted communications over a wide area for over an hour.
In 1958 the R-12 was selected, together with the R-2 and R-5, as target vehicles for tests of the Dunay-2 ABM system. 11 target flights were undertaken, 3 of them by R-12's. The first R-12 target flight was conducted on 4 March 1961 in a test of the V-1000 ABM missile. After completion of the state trials the Aldan ABM complex was declared operational. The S63U target version of the missile was used again in certification tests in 1976-1977 of the 3(V)350Zh missile.
The 63S1 initial production version was used through May 1966 for a total of 40 launches, of which 12 were failures. It was succeeded by the 63S1M prototype for the 11K63 production space launcher.
Version: Kosmos 11K63. Other Designations: Kosmos 2I. Library of Congress Designation: B-1. Department of Defence Designation: SL-7. ASCC Reporting Name: Sandal. Article Number: 11K63. Manufacturer's Designation: 63SM.
Series production version of satellite launcher based on Yangel R-12 IRBM. Succeeded 63S1M prototype from 1965, using same 'Dvina' launch complex. From March 16, 1967 orbital launches from Plesetsk were from the purpose-built 'Raduga' launch complex LC133. Total of 123 launches, of which 8 were failures.
Launches: 126. Failures: 8. Success Rate: 93.65%. First Launch Date: 1965-10-19. Last Launch Date: 1977-06-18. LEO Payload: 450 kg (990 lb). to: 270 km Orbit. at: 71.00 degrees. Apogee: 2,000 km (1,200 mi). Associated Spacecraft: DS-MO, DS-P1-I, DS-P1-Yu, DS-U1-A, DS-U1-IK, DS-U1-R, DS-U1-Ya, DS-U2-D, DS-U2-GF, DS-U2-GK, DS-U2-I, DS-U2-IK, DS-U2-M, DS-U2-MG, DS-U2-MP, DS-U2-V, DS-U3-IK, DS-U3-S. Other Associated Spacecraft: Oreol. Liftoff Thrust: 636.500 kN (143,091 lbf). Total Mass: 48,110 kg (106,060 lb). Core Diameter: 1.60 m (5.20 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 7.500 million. in: 1985 unit dollars.
- Stage1: 1 x Kosmos A-1. Gross Mass: 39,515 kg (87,115 lb). Empty Mass: 3,150 kg (6,940 lb). Motor: 1 x RD-214. Thrust (vac): 730.500 kN (164,223 lbf). Isp: 264 sec. Burn time: 125 sec. Length: 18.00 m (59.00 ft). Diameter: 1.60 m (5.20 ft). Propellants: Nitric acid/Kerosene.
- Stage2: 1 x S1. Gross Mass: 8,595 kg (18,948 lb). Empty Mass: 840 kg (1,850 lb). Motor: 1 x RD-119. Thrust (vac): 105.510 kN (23,720 lbf). Isp: 352 sec. Burn time: 250 sec. Length: 7.80 m (25.50 ft). Diameter: 1.60 m (5.20 ft). Propellants: Lox/UDMH.
Kosmos 2 Chronology
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.
End of 1953 - Khrushchev and Ustinov decide to create additional independent missile design bureaux Khrushchev desired to decentralise the missile industry, since a single nuclear bomb on Moscow would wipe out Korolev’s factories. Ustinov was requested to draw up a plan for two additional completely independent missile design bureaux, one in the south of the Soviet Union, the other in the Urals. It was also envisioned a third bureau would be built in the east, in Siberia, but this was never done. This effort cost tens of billions of roubles. While the managers and lead technical staff would be taken from Korolev’s bureau, the working engineers, technicians, and workers for the bureau and associated factories would be recruited locally at each site. This would avoid the additional expense of building extra housing. Korolev fought to keep control, wanting to make the new bureaux just branches of his own, but Khrushchev was adamant that only completely autonomous organisations would be acceptable. Yangel was easily selected for the southern bureau, and the young Makeyev was a more contentious selection for the Ural bureau.
1954 August 13 - R-12 development authorised. Decree 'On the Creation and preparation of the R-12 (8K63) missile--start of work an the R-12' was issued.
1956 February 27 - Soviet Leadership tours Korolev's design bureau Khrushchev, Molotov, Bulganin, and other leaders are given a tour of Korolev’s OKB-1 in Kaliningrad. They are shown the R-1, R-2 and R-5 missiles as well as a mock-up of the R-7 and are awed. Ustinov reports that only five warheads would be needed to destroy Britain, and seven to nine for France. The need for the R-12 was discussed - the longer range was essential so that the missiles could be based farther from NATO’s borders (the experience of the German invasion and quick destruction of forward-based units and equipment was on everyone’s minds).
1957 June 22 - Kapustin Yar V-2. R-12 63M No. 1 (LKI1-1) Test mission Agency: MVS. Apogee: 402 km (249 mi).
1957 July 1 - Kapustin Yar V-2. R-12 63M No. 3? Agency: MVS. Apogee: 402 km (249 mi).
1957 July 1 - Kapustin Yar V-2. R-12 63M No. 2? Agency: MVS. Apogee: 402 km (249 mi).
1957 July 1 - Kapustin Yar V-2. R-12 63M No. 4? Agency: MVS. Apogee: 402 km (249 mi).
1957 August 1 - Kapustin Yar V-2. R-12 63M No. 5? Agency: MVS. Apogee: 402 km (249 mi).
1957 August 1 - Kapustin Yar V-2. R-12 63M No. 6? Agency: MVS. Apogee: 402 km (249 mi).
1957 August 20 - USSR sells R-12 missiles to China. Ministry of Armaments Decree 'On transfer of two R-12 missiles to China (on August 6)' was issued.
1957 September 1 - Kapustin Yar V-2. R-12 63M No. 7? LKI-7 Test mission Agency: MVS. Apogee: 402 km (249 mi).
January 1958 - Project 581 Spacecraft: Project 581. The first project to build a Chinese satellite is set in motion.
1958 May 1 - Kapustin Yar V-2. K63 No. 1 (LKI2-1) Agency: MVS. Apogee: 402 km (249 mi).
1958 May 17 - Project 581 pressure. Spacecraft: Project 581. Chairman Mao says that China must orbit a satellite at the earliest possible date in order to match the Americans and Russians.
1958 June 1 - Kapustin Yar V-2. R-12 63M No. 8 (LKI-8) Agency: MVS. Apogee: 402 km (249 mi).
1958 June 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 June 1 - Kapustin Yar V-2. K63 (LKI2 2 of 24) Agency: MVS. Apogee: 402 km (249 mi).
Summer 1958 - Khrushchev conceives of use of silos for Soviet long range missiles Khrushchev independently conceived of the idea of storing and launching ballistic missiles from subterranean silos. He called Korolev to his dacha in the Crimea. Korolev told him his idea was not feasible. He then called Barmin and Yangel. Barmin said he would study the idea. Yangel remained silent. Some time later Khrushchev’s son saw a drawing of the same concept in a US aerospace magazine. He informed his father, who ordered immediate crash development of the first generation of Soviet missile silos.
1958 August 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 August 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 September 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 September 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 October 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 October 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 November 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 December 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 December 1 - Kapustin Yar V-2. K63 Agency: MVS. Apogee: 402 km (249 mi).
1958 December 12 - Kapustin Yar V-2. 8K63 control flight Agency: MVS. Apogee: 402 km (249 mi).
1958 December 24 - Kapustin Yar V-2. 8K63 control flight Agency: MVS. Apogee: 402 km (249 mi).
1958 December 25 - Kapustin Yar V-2. 8K63 control flight Agency: MVS. Apogee: 402 km (249 mi).
1958 December 27 - Kapustin Yar V-2. 8K63 control flight Agency: MVS. Apogee: 402 km (249 mi).
1958 December 30 - Kapustin Yar V-2. 8K63 control flight Agency: MVS. Apogee: 402 km (249 mi).
Early 1959 - Chinese plan satellite launch by December 1959 Spacecraft: Project 581. Tsien and his colleagues set an initial goal of launching a satellite by the end of 1959. They see no reason to copy the antiquated R-2 missile being transferred from Russia, and want to make a great leap to an intermediate range missile capable of serving as the first stage of a satellite launcher. It very quickly becomes that this is much too ambitious and totally impossible.
1959 March 4 - R-12 accepted into military service. Decree 'On adoption of the R-12 into armaments' was issued.
1959 March 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 April 11 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 April 14 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 April 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 May 12 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 May 14 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 May 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 May 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 June 2 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 June 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 June 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 June 20 - Decision to withhold R-12 and nuclear warhead drawing package from China over Sidewinder affair Spacecraft: Project 581. The Soviet Central Committee advises China it will not provide prototype or drawings of atomic bombs as agreed previously. Khrushchev promised China that he would provide the drawing package for the R-12 IRBM as soon as testing was completed. However then came the affair of the Sidewinder. At the end of 1958 or early 1959 a complete missile fell into the hands of the Chinese. They promised to provide it to the Russians, but then dragged their feet. They were finally told in February 1959 that unless they provided the Sidewinder, they would not be given the R-12 package. The missile was finally delivered but it was found that the key crystal in the infrared homing sensor was missing. The Chinese had also been caught disassembling a P-15 cruise missile at a training facility in China. It had taken the Russian trainers two days to get it reassembled correctly. Therefore on June 20 1959 the decision was taken not to transfer the R-12 or the promised nuclear warhead design to China.
The Soviets created a new design bureau to copy the Sidewinder. Fabrication of the crystal for the infrared sensor was the main obstacle. The initial production batches had a 99% rejection rate. A state commission was set up to get to the bottom of the problem, but couldn’t find a solution. The main problem seemed to be low-quality ore provided by the mines.
1959 July 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 July 25 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 July 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 July 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 July 31 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 August 7 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 August 13 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1959 August 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 August 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 September 2 - Kapustin Yar Mayak-1. FAILURE: Failure. Test mission Agency: MVS. Apogee: 0 km ( mi).
1959 September 5 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 September 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 September 25 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 September 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 October 8 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 October 9 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 October 9 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1959 October 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 October 27 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1959 November 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 December 16 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 December 18 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1959 December 21 - Kapustin Yar Mayak-2. Test mission Agency: MVS. Apogee: 402 km (249 mi).
1959 December 27 - Kapustin Yar Mayak-2. Test mission Agency: MVS. Apogee: 402 km (249 mi).
1959 December 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 January 18 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 January 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 February 13 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1960 March 20 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 March 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 March 25 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 March 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 March 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 March 31 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 April 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 May 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 May 5 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 May 6 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 May 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 June 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 June 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 June 14 - Development of Silo-Launched IRBM's and ICBM's approved. State Committee for Defence Technology (GKOT) Decree 'On creation of shaft units (silos) for the R-12, R-14, R-16, and R-9 missiles' was issued.
1960 June 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 June 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 12 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 13 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 July 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 2 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1960 August 4 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 4 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 8 - Kosmos 63S1 small booster and DS small satellites authorised. Spacecraft: DS-1, DS-2. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On the Creation of the Rocket-Carrier 63S1 Based on the R-12 Missile, and the Development and Launch of Small Artificial Satellite--start of work on launcher and satellites at OKB-586'
1960 August 8 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 11 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 12 - Soviet/China break. In the preceding months relations between the Soviet advisors and Chinese engineers had been strained by increasing Soviet secrecy. The Russians catch Chinese students at the Moscow Aviation Institute stealing restricted missile data. Finally Khrushchev declared the suspension of military assistance to China. All 1,343 Soviet specialists are withdrawn from the Fifth Academy in Beijing and return to Russia. They leave behind 343 uncompleted contracts. A total of 257 technical development projects were cancelled as a result.
1960 August 12 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 20 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 August 23 - Last Russian advisers leave China. The last Russian technical advisers are withdrawn from China.
1960 September 5 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 September 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 September 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 September 22 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 September 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 September 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 September 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 September 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 September 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 1 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1960 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 7 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 18 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 18 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 19 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 20 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 21 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 October 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 November 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 November 4 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 November 4 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 November 4 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 November 12 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 November 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 11 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 12 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 20 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 22 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 22 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 23 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1960 December 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 January 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 January 13 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 January 14 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 February 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 February 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 February 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 March 1 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1961 March 2 - Makat -. V-1000 target mission Agency: OKB-30. Apogee: 402 km (249 mi).
1961 March 4 - Makat -. V-1000 target mission Agency: OKB-30. Apogee: 460 km (280 mi).
1961 March 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 March 11 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 March 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 March 25 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 March 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 March 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 April 3 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 April 4 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 April 7 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 April 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 April 19 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 April 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 April 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 May 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 May 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 June 9 - Kapustin Yar V-2. V-1000 target mission Agency: MVS. Apogee: 402 km (249 mi).
1961 June 9 - Makat -. V-1000 target Agency: OKB-30. Apogee: 402 km (249 mi).
1961 June 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 June 24 - Makat -. V-1000 target Agency: OKB-30. Apogee: 402 km (249 mi).
1961 June 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 June 30 - Makat -. V-1000 target Agency: OKB-30. Apogee: 402 km (249 mi).
1961 July 22 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 July 25 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 July 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 August 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 August 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 August 31 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 September 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 September 10 - 05:50 GMT - Novaya Zemlya -. Nuclear test Agency: RVSN. Apogee: 100 km (60 mi).
1961 September 11 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 September 12 - 05:00 GMT - Novaya Zemlya -. Nuclear test Agency: RVSN. Apogee: 100 km (60 mi).
1961 September 13 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 September 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 September 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 October 27 - 16:30 GMT - Kapustin Yar Mayak-2. FAILURE: First stage failed. DS-2 s/n 1 Mass: 300 kg (660 lb). Spacecraft: DS-1. Agency: RVSN. Failed first attempt to launch a DS-1 technology test version of the DS satellite atop a Cosmos 63S1 small launch vehicle. The boster didn't reach orbital velocity due to the failure of an acceleration integrator in the velocity regulation control.
1961 October 31 - Kapustin Yar V-2. First launch of R-12U from silo. Agency: MVS. Apogee: 402 km (249 mi).
1961 November 25 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 December 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 December 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 December 2 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 December 21 - 12:30 GMT - Kapustin Yar Mayak-2. FAILURE: Second stage failed 354 seconds after launch. DS-1 s/n 1 Mass: 300 kg (660 lb). Spacecraft: DS-1. Agency: RVSN. Second attempted launch of Cosmos 63S1 small launch vehicle 2LK with a DS-1 satgellite. This time the new second stage failed. The oxidiser was exhausted before orbital velocity could be reached due to uncontrolled pumping of liquid oxygen into the combustion chamber. The upper stage and satellite impacted in the Kurile Islands. An Expert Commission headed by Ustinov was convened to review the program.
1961 December 23 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 December 27 - Kapustin Yar PL1. MP-1 Agency: RVSN. Apogee: 405 km (251 mi).
1961 December 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1961 December 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 January 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 January 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 February 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 February 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 February 21 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 March 6 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 March 16 - 11:59 GMT - Kapustin Yar Mayak-2. Kosmos 63S1 6LK Cosmos 1 Mass: 47 kg (103 lb). Spacecraft: DS-2. Agency: RVSN. Perigee: 207 km (128 mi). Apogee: 649 km (403 mi). Inclination: 49.00 deg. Period: 93.10 min. After five months of further work and tests to improve the reliability of the second stage, Yangel's team felt it was ready to again attempt a launch of the 63S1 booster. 63S1 s/n 6LK put a DS-2 satellite into orbit, which conducted studies of the ionosphere. This was the first successful launch of the Kosmos 63S1 launch vehicle. A decision was made after two unsuccessful launches of the DS-1 to create a simplified DS-2 spacecraft based on the equipment and structural elements of DS-1 spacecraft. The cylindrical section for mission avionics was completely omitted.
1962 April 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 April 6 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 April 6 - 17:15 GMT - Kapustin Yar Mayak-2. Kosmos 63S1 5LK Cosmos 2 Mass: 285 kg (628 lb). Spacecraft: 1MS. Agency: RVSN. Perigee: 207 km (128 mi). Apogee: 1,485 km (922 mi). Inclination: 49.00 deg. Period: 101.80 min. Radiation, cosmic ray data. Decay date suspect Investigation of the upper atmosphere and outer space; development of elements in the design of space craft.
1962 April 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 April 13 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 April 13 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 April 14 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 April 24 - 04:00 GMT - Kapustin Yar Mayak-2. Kosmos 63S1 4LK Cosmos 3 Mass: 330 kg (720 lb). Spacecraft: 2MS. Agency: RVSN. Perigee: 216 km (134 mi). Apogee: 707 km (439 mi). Inclination: 49.00 deg. Period: 93.80 min. Cosmic ray, radiation data. Investigation of the upper atmosphere and outer space; development of elements in the design of space craft.
1962 April 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 May 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 May 22 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 May 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 May 28 - 03:00 GMT - Kapustin Yar Mayak-2. Kosmos 63S1 3LK Cosmos 5 Mass: 280 kg (610 lb). Spacecraft: 2MS. Agency: RVSN. Perigee: 192 km (119 mi). Apogee: 1,578 km (980 mi). Inclination: 49.10 deg. Period: 102.60 min. Monitored artificial radiation. Investigation of the upper atmosphere and outer space; development of elements in the design of space craft.
1962 May 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 7 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 19 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 22 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 June 30 - 16:00 GMT - Kapustin Yar Mayak-2. Cosmos 6 Mass: 355 kg (782 lb). Spacecraft: DS-P1. Agency: RVSN. Perigee: 261 km (162 mi). Apogee: 348 km (216 mi). Inclination: 48.90 deg. Period: 90.60 min. Prototype ABM radar target; supported developmental experiments for ABM systems.
1962 July 4 - Kapustin Yar V-2. SSATC Target Agency: MVS. Apogee: 402 km (249 mi).
1962 July 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 July 28 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1962 July 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 August 8 - Kapustin Yar V-2. SSATC Target Agency: MVS. Apogee: 402 km (249 mi).
1962 August 10 - Kapustin Yar V-2. SSATC Target Agency: MVS. Apogee: 402 km (249 mi).
1962 August 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 August 18 - 15:00 GMT - Kapustin Yar Mayak-2. Cosmos 8 Mass: 337 kg (742 lb). Spacecraft: DS-K-8. Agency: RVSN. Perigee: 244 km (151 mi). Apogee: 598 km (371 mi). Inclination: 49.00 deg. Period: 92.90 min. Detected meteoroid flux in near-earth space and carried unspecified military research equipment.
1962 September 4 - Kapustin Yar V-2. SSATC Target Agency: MVS. Apogee: 402 km (249 mi).
1962 September 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 September 19 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 September 20 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 September 20 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 October 20 - 04:00 GMT - Kapustin Yar Mayak-2. Cosmos 11 Mass: 315 kg (694 lb). Spacecraft: DS-A1. Agency: RVSN. Perigee: 240 km (140 mi). Apogee: 858 km (533 mi). Inclination: 48.90 deg. Period: 95.60 min. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.
1962 October 25 - Kapustin Yar Mayak-2. FAILURE: Launch vehicle failed to orbit - unknown cause. 1MS Spacecraft: 1MS. Agency: RVSN.
1962 October 31 - Kapustin Yar V-2. SSATC Target Agency: MVS. Apogee: 402 km (249 mi).
1962 November 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 November 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 November 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 November 1 - 11:15 GMT - Kapustin Yar V-2. Nuclear Test K-5 Nuclear test Agency: RVSN. Apogee: 60 km (37 mi). R-12 test flight with live nuclear warhead, successful warhead detonation in Semipalitinsk at an altitude of 60 km. High altitude test designed to study electromagnetic pulse effects on electronics, especially ABM system radars. Communications were disrupted over a wide area for over an hour.
1962 November 19 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 November 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 November 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 December 6 - Makat -. SSATC Target Agency: MVS. Apogee: 402 km (249 mi).
1962 December 7 - Kapustin Yar V-2. SSATC Target Agency: MVS. Apogee: 402 km (249 mi).
1962 December 11 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1962 December 14 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1962 December 19 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1962 December 21 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1962 December 25 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1962 December 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1962 December 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 January 22 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 February 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 February 5 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 February 8 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 February 13 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 February 14 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 February 14 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 March 1 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 March 7 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 March 12 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 March 15 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 March 16 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 March 19 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 March 21 - 11:40 GMT - Kapustin Yar PL1. M-12 re-entry vehicle test flight Agency: RVSN. Apogee: 405 km (251 mi). First flight of Raketoplan Chelomei, launched at 16:40 Moscow Time. The reentry vehicle was destroyed during reentry. Maximum Altitude - 400 km. Maximum Speed - 14,400 kph. Distance of free flight - 1900 km.
1963 March 25 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 March 28 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 April 6 - Kapustin Yar Mayak-2. FAILURE: First stage failed. DS-P1 s/n 2 Spacecraft: DS-P1. Agency: RVSN. Prototype ABM radar target; supported developmental experiments for ABM systems.
1963 April 9 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 April 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 April 13 - 11:00 GMT - Kapustin Yar Mayak-2. Cosmos 14 Spacecraft: Omega. Agency: MO SSSR. Perigee: 250 km (150 mi). Apogee: 410 km (250 mi). Inclination: 48.90 deg. Period: 91.10 min. Tested VNIIEM electric gyrodyne satellite orientation technology.
1963 April 25 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 April 28 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 May 22 - 03:00 GMT - Kapustin Yar Mayak-2. Cosmos 17 Mass: 322 kg (709 lb). Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 251 km (155 mi). Apogee: 658 km (408 mi). Inclination: 48.90 deg. Period: 93.70 min. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.
1963 June 1 - 02:50 GMT - Kapustin Yar Mayak-2. FAILURE: First stage failed 4 seconds after launch. DS-MT s/n 1 Spacecraft: DS-MT. Agency: RVSN. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays.
1963 June 6 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 June 8 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 June 8 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 June 14 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 June 26 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 July 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 July 5 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 July 11 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 July 15 - R-12U, R-14U, and R-16U silo-based missiles accepted into service. Decree 'On adoption into armaments of the R-12U, R-14U, and R-16U shaft versions' was issued.
1963 July 19 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 July 25 - Kapustin Yar V-2. R-12U (8K63U) Agency: RVSN. Apogee: 402 km (249 mi).
1963 July 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 July 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 July 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 July 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 August 6 - 06:00 GMT - Kapustin Yar Mayak-2. Cosmos 19 Mass: 355 kg (782 lb). Spacecraft: DS-P1. Agency: MO SSSR. Perigee: 267 km (165 mi). Apogee: 497 km (308 mi). Inclination: 49.00 deg. Period: 92.10 min. Prototype ABM radar target; supported developmental experiments for ABM systems.
1963 August 9 - Sovetskaya Gavan -. Agency: MVS. Apogee: 402 km (249 mi).
1963 August 22 - Kapustin Yar Mayak-2. FAILURE: First stage failed. DS-A1 s/n 3 Spacecraft: DS-A1. Agency: RVSN. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.
1963 August 23 - Sovetskaya Gavan -. Agency: MVS. Apogee: 402 km (249 mi).
1963 August 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 August 31 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 September 6 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 September 19 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 September 20 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 September 21 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 October 1 - Kosmos scientific satellites authorised. Spacecraft: DS-1. All-Russian Council of the National Economy (VSNKh) Decree 'Program for Space Investigations With Small Artificial Satellite, Launched on the Kosmos -- On course of work on small satellites at OKB-586' was issued.
1963 October 1 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 October 4 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1963 October 11 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 October 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 October 24 - Kapustin Yar Mayak-2. FAILURE: Second stage failed 353 seconds after launch. DS-A1 s/n 4 Spacecraft: DS-A1. Agency: RVSN. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.
1963 October 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 November 5 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 November 16 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 November 23 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 November 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 November 29 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 December 3 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 December 3 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 December 4 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 December 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1963 December 12 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1963 December 13 - 14:15 GMT - Kapustin Yar Mayak-2. Cosmos 23 Mass: 347 kg (765 lb). Spacecraft: Omega. Agency: MO SSSR. Perigee: 232 km (144 mi). Apogee: 560 km (340 mi). Inclination: 48.90 deg. Period: 92.40 min. Tested VNIIEM electric gyrodyne satellite orientation technology.
1963 December 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 January 9 - R-12U and R-14U accepted into military service. Decree 'On adoption of the R-12U and R-14U shaft versions into armaments' was issued.
1964 January 9 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 January 14 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 January 23 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 January 31 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 February 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 February 8 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 February 13 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 February 18 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 February 27 - 13:26 GMT - Kapustin Yar Mayak-2. Cosmos 25 Mass: 355 kg (782 lb). Spacecraft: DS-P1. Agency: MO SSSR. Perigee: 260 km (160 mi). Apogee: 495 km (307 mi). Inclination: 49.10 deg. Period: 92.10 min. Prototype ABM radar target; supported developmental experiments for ABM systems.
1964 February 29 - Makat -. Target Agency: MVS. Apogee: 402 km (249 mi).
1964 March 4 - Makat -. Target Agency: MVS. Apogee: 402 km (249 mi).
1964 March 10 - Makat -. Target Agency: MVS. Apogee: 402 km (249 mi).
1964 March 11 - Makat -. Target Agency: MVS. Apogee: 402 km (249 mi).
1964 March 18 - 15:07 GMT - Kapustin Yar Mayak-2. Cosmos 26 Mass: 365 kg (804 lb). Spacecraft: DS-MG. Agency: MO SSSR. Perigee: 268 km (166 mi). Apogee: 376 km (233 mi). Inclination: 48.90 deg. Period: 91.00 min. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also obtained radiation data.
1964 March 23 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 March 24 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 March 27 - Kapustin Yar V-2. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1964 April 27 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 June 5 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 June 6 - 06:00 GMT - Kapustin Yar Mayak-2. Cosmos 31 Mass: 325 kg (716 lb). Spacecraft: DS-MT. Agency: MO SSSR. Perigee: 221 km (137 mi). Apogee: 485 km (301 mi). Inclination: 48.90 deg. Period: 91.70 min. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays.
1964 June 11 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 1 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 2 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 7 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 8 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 10 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 14 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 17 - Sovetskaya Gavan -. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 17 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 July 21 - Sovetskaya Gavan -. FAILURE: Failure. Agency: MVS. Apogee: 0 km ( mi).
1964 July 30 - 03:36 GMT - Kapustin Yar Mayak-2. Cosmos 36 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 253 km (157 mi). Apogee: 488 km (303 mi). Inclination: 49.00 deg. Period: 92.00 min. Development of systems for air defence and the control of outer space.
1964 July 31 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 August 4 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 August 6 - Sovetskaya Gavan -. Agency: MVS. Apogee: 402 km (249 mi).
1964 August 6 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 August 20 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 August 22 - 11:02 GMT - Kapustin Yar Mayak-2. Cosmos 42 Mass: 100 kg (220 lb). Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 228 km (141 mi). Apogee: 1,105 km (686 mi). Inclination: 48.90 deg. Period: 98.10 min.
1964 August 26 - Sovetskaya Gavan -. Agency: MVS. Apogee: 402 km (249 mi).
1964 September 16 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 September 30 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 October 6 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 October 9 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 October 16 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 October 24 - 05:16 GMT - Kapustin Yar Mayak-2. Cosmos 49 Mass: 355 kg (782 lb). Spacecraft: DS-MG. Agency: MO SSSR. Perigee: 260 km (160 mi). Apogee: 472 km (293 mi). Inclination: 48.90 deg. Period: 91.90 min. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also studied measured Earth infrared and ultraviolet flux.
1964 December 1 - Kapustin Yar LC86/1. FAILURE: Payload shroud did not separate. DS-2 s/n 2 Spacecraft: DS-2. Agency: RVSN. A decision was made after two unsuccessful launches of the DS-1 to create a simplified DS-2 spacecraft based on the equipment and structural elements of DS-1 spacecraft. The cylindrical section for mission avionics was completely omitted.
1964 December 9 - 23:02 GMT - Kapustin Yar LC86/1. Cosmos 51 Mass: 350 kg (770 lb). Spacecraft: DS-MT. Agency: MO SSSR. Perigee: 258 km (160 mi). Apogee: 537 km (333 mi). Inclination: 48.80 deg. Period: 92.60 min. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays, and measured the luminosity of the starry sky.
1964 December 15 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 December 22 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 December 23 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 December 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1964 December 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1965 January 30 - 09:36 GMT - Kapustin Yar LC86/1. Cosmos 53 Mass: 310 kg (680 lb). Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 221 km (137 mi). Apogee: 1,172 km (728 mi). Inclination: 48.70 deg. Period: 98.70 min. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.
1965 February 12 - Kapustin Yar LC86/1. FAILURE: Second stage failed. DS-P1-Yu s/n 2 Spacecraft: DS-P1-Yu. Agency: RVSN. Development of systems for air defence and the control of outer space.
1965 February 20 - Kapustin Yar LC86/1. FAILURE: First stage failed 64 seconds after launch. DS-A1 s/n 6 Spacecraft: DS-A1. Agency: RVSN. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.
1965 March 16 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1965 March 26 - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1965 April 16 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1965 April 24 - Makat -. Agency: MVS. Apogee: 402 km (249 mi).
1965 May 12 - 12:30 GMT - Kapustin Yar V-2. Agency: MVS. Apogee: 402 km (249 mi).
1965 June 22 - Scientific Kosmos satellites approved. Spacecraft: DS-U1-A. Ministry of General Machine Building (MOM) Decree 'On Preparations in 1965-66 of 18 Small Unifunctional Earth Satellites for Carrying out Scientific Investigations-creation of small scientific satellites at OKB-586' was issued.
1965 July 2 - 06:30 GMT - Kapustin Yar LC86/1. Cosmos 70 Mass: 250 kg (550 lb). Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 223 km (138 mi). Apogee: 1,176 km (730 mi). Inclination: 48.80 deg. Period: 98.80 min. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.
1965 July 23 - 04:33 GMT - Kapustin Yar LC86/1. Cosmos 76 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 256 km (159 mi). Apogee: 513 km (318 mi). Inclination: 48.80 deg. Period: 92.20 min. Development of systems for air defence and the control of outer space.
1965 October 19 - 05:44 GMT - Kapustin Yar LC86/1. Cosmos 93 Mass: 305 kg (672 lb). Spacecraft: DS-U2-V. Agency: MO SSSR. Perigee: 216 km (134 mi). Apogee: 513 km (318 mi). Inclination: 48.40 deg. Period: 91.80 min. Military technology development satellite - mission still classified.
1965 November 4 - 05:31 GMT - Kapustin Yar LC86/1. Cosmos 95 Mass: 325 kg (716 lb). Spacecraft: DS-U2-V. Agency: MO SSSR. Perigee: 211 km (131 mi). Apogee: 521 km (323 mi). Inclination: 48.40 deg. Period: 91.90 min. Military technology development satellite - mission still classified.
1965 November 26 - 12:14 GMT - Kapustin Yar LC86/1. Cosmos 97 Mass: 267 kg (588 lb). Spacecraft: DS-U2-M. Agency: MO SSSR. Perigee: 214 km (132 mi). Apogee: 2,144 km (1,332 mi). Inclination: 48.40 deg. Period: 108.90 min. Development tests of atomic clocks.
1965 December 21 - 06:14 GMT - Kapustin Yar LC86/1. Cosmos 101 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 256 km (159 mi). Apogee: 533 km (331 mi). Inclination: 48.80 deg. Period: 92.50 min. Development of systems for air defence and the control of outer space.
1965 December 28 - Kapustin Yar LC86/1. FAILURE: First stage failed. DS-K-40 s/n 1 Spacecraft: DS-K-40. Agency: RVSN. Development of systems for the later operational Tselina satellites.
1966 January 25 - 12:28 GMT - Kapustin Yar LC86/1. Cosmos 106 Mass: 325 kg (716 lb). Spacecraft: DS-P1-I. Agency: MO SSSR. Perigee: 281 km (174 mi). Apogee: 553 km (343 mi). Inclination: 48.40 deg. Period: 92.80 min. Operational radar target for the ABM forces.
1966 February 11 - 18:00 GMT - Kapustin Yar LC86/1. Cosmos 108 Mass: 355 kg (782 lb). Spacecraft: DS-U1-G. Agency: MO SSSR. Perigee: 220 km (130 mi). Apogee: 850 km (520 mi). Inclination: 48.80 deg. Period: 95.30 min. Studied the relationship between variations in the upper atmosphere and solar activity.
1966 February 21 - Kapustin Yar LC86/1. FAILURE: First stage failed 83 seconds after launch. DS-K-40 s/n 2 Spacecraft: DS-K-40. Agency: RVSN. Development of systems for the later operational Tselina satellites.
1966 April 26 - 10:04 GMT - Kapustin Yar LC86/1. Cosmos 116 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 288 km (178 mi). Apogee: 464 km (288 mi). Inclination: 48.40 deg. Period: 92.00 min. Development of systems for air defence and the control of outer space.
1966 May 24 - 05:31 GMT - Kapustin Yar LC86/1. Cosmos 119 Mass: 250 kg (550 lb). Spacecraft: DS-U2-I. Agency: MO SSSR. Perigee: 209 km (129 mi). Apogee: 1,278 km (794 mi). Inclination: 48.40 deg. Period: 99.70 min. Studied the influence of the ionosphere on passing VLF radio waves.
1966 July 8 - 05:31 GMT - Kapustin Yar LC86/1. Cosmos 123 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 256 km (159 mi). Apogee: 512 km (318 mi). Inclination: 48.80 deg. Period: 92.30 min. Development of systems for air defence and the control of outer space.
1966 December 12 - 20:38 GMT - Kapustin Yar LC86/1. Cosmos 135 Mass: 355 kg (782 lb). Spacecraft: DS-U2-MP. Agency: MO SSSR. Perigee: 253 km (157 mi). Apogee: 648 km (402 mi). Inclination: 48.40 deg. Period: 93.60 min. Studied cosmic dust particles in near-Earth space.
1966 December 21 - 13:12 GMT - Kapustin Yar LC86/1. Cosmos 137 Mass: 295 kg (650 lb). Spacecraft: DS-U2-D. Agency: MO SSSR. Perigee: 219 km (136 mi). Apogee: 1,718 km (1,067 mi). Inclination: 48.80 deg. Period: 104.40 min. Studied charged particle flows.
1967 February 14 - 10:04 GMT -
