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R-12

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R-12 Credit: © Mark Wade

AKA: 8K63;Sandal;SS-4 Mod.1. Status: Retired 1965. First Launch: 1957-06-22. Last Launch: 1965-05-12. Number: 377 . Payload: 390 kg (850 lb). Thrust: 625.52 kN (140,622 lbf). Gross mass: 34,610 kg (76,300 lb). Unfuelled mass: 4,810 kg (10,600 lb). Specific impulse: 235 s. Specific impulse sea level: 210 s. Burn time: 108 s. Height: 22.26 m (73.03 ft). Diameter: 1.65 m (5.41 ft). Span: 1.83 m (6.00 ft). Apogee: 500 km (310 mi).

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/kerosene).

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, favored 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 Kapustin 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 unfueled 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:

• Readiness condition 4: the missile was stored at the technical position unfueled, and without the gyro package. Guaranteed life in this condition was seven years, with 205 minutes reaction time from go order to launch.
• Readiness condition 3: the missile was in the technical position with the gyros and warhead installed. Guaranteed life three years, reaction time 140 minutes.
• Readiness condition 2: the missile was installed on the launch pad. The gyro system was installed and brought to readiness, then shut down. Fuel connections were made, but no fuel was pumped into the rocket. The missile could be held for three months in this state, with a 60-minute response time.
• Readiness condition 1: the missile was on the pad as in readiness condition 2, but fuelled with TG-02 kerosene. To launch required only activation of the gyro package and pumping of the corrosive AK-27I oxidizer. In this condition the missile could be held for one month with a 30-minute reaction time.

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 oxidizer tanks. The oxidizer 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 oxidizer was pressurized 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 oxidizer tanks forward. The lower tank was drained first in order to match the shifting center of pressure as the missile accelerated. This had not been a problem in earlier rockets with liquid oxygen oxidizer, 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.

Service History

On 15 May 1960 the first R-12 regiments were activated at Slonim, Novogrudok, and Pinsk in Belarus, 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 Lithuania, 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 Shahab 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.

R-12 Variants

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.

Maximum range: 1,500 km (900 mi). Number Standard Warheads: 1. Warhead yield: 1,000 KT. CEP: 5.16 km (3.20 mi). Boost Propulsion: Storable liquid rocket, Nitric acid/kerosene. Maximum speed: 12,710 kph (7,890 mph). Initial Operational Capability: 1959. Total Number Built: 2300.

Stage Data - R-12

• Stage 1. 1 x R-12. Gross Mass: 34,610 kg (76,300 lb). Empty Mass: 4,810 kg (10,600 lb). Thrust (vac): 625.517 kN (140,622 lbf). Isp: 235 sec. Burn time: 108 sec. Isp(sl): 210 sec. Diameter: 1.60 m (5.20 ft). Span: 1.80 m (5.90 ft). Length: 18.00 m (59.00 ft). Propellants: Nitric acid/Kerosene. No Engines: 1. Engine: RD-214. Other designations: 8K63. Status: Out of Production. Comments: Payload 390 kg. Range 1500 km. Maximum altitude 398 km. Time of flight 11.8 minutes. Max velocity at burnout 3530 m/s. Accuracy 6 km in range, 5 km laterally. Source: wall chart, Russian Space Agency HQ, Moscow.

DF-2 First Chinese IRBM, a single stage missile with the objective of carrying a 1500 kg warhead to Japan. The starting point for the design were R-12 construction drawings and a single exemplar of the missile provided by the Soviet Union prior to the break with Moscow in 1960. Following protracted development the design was accepted by the Chinese military for service in 1970.

EKR Russian intermediate range cruise missile. B Chertok of NII-8 took the preliminary German R-13 cruise missile design and elaborated it, including consideration of the key problem of long-range automatic astronavigation. By 1951 to 1953 Korolev's design bureau had prepared an experimental design, the EKR. I Lisovich had developed a prototype astronavigation system that met the necessary specifications, and solution of basic problems in use of steel and titanium hot airframe technology had been solved at VIAM (All-Union Institute of Aviation Materials) and MVTU Bauman Institute. An expert commission in 1953 examined the EKR design and felt that there were still many technical problems to be solved, most of which were better handled by an aircraft designer rather than Korolev.

Kosmos 11K63 Ukrainian orbital launch vehicle. 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.

Kosmos 2 Ukrainian orbital launch vehicle. 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.

Kosmos 63S1 Ukrainian orbital launch vehicle. 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.

Kosmos 63S1M Ukrainian orbital launch vehicle. Modernized version of 63S1 initial configuration of the first Kosmos launcher and the prototype for the production 11K63 launch vehicle. Suborbital launches from Plesetsk from 1965 at from the modified R-12 silo 'Dvina'. Flown only a few times in 1965-1967. Succeeded by the 11K63 production model launched from the 'Raduga' complex.

Photo Gallery

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MR-12 rocket MR-12 sounding rocket and R-12 IRBM at Kaluga Credit: © Mark Wade

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R-12 Credit: Ukrainian Space Agency

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• Expert commission examined the EKR design - . Nation: Russia. Related Persons: Korolev, Lavochkin, Myasishchev. Program: Navaho. Spacecraft Bus: Buran M. Spacecraft: Buran M-42.

  In 1951 to 1953 Korolev's design bureau had prepared an experimental trisonic ramjet design, the EKR.The expert commission ifelt that there were still many technical problems to be solved, most of which were better handled by an aircraft designer rather than Korolev. Further, Korolev had to place the highest priority on development of the R-7 ICBM. Therefore a final government decree on 20 May 1954 authorised the Lavochkin and Myasishchev aircraft design bureaux to proceed in parallel with full-scale development of trisonic intercontinental cruise missiles.

• Authorisation for development of Soviet intermediate and intercontinental range missiles. - . Nation: Russia.

  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.

• Khrushchev and Ustinov decide to create additional independent missile design bureaux - . Nation: Russia. Related Persons: Khrushchev, Korolev, Makeyev, Ustinov, Yangel.

  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.

• R-12 development authorised. - . Nation: Russia. Decree 'On the Creation and preparation of the R-12 (8K63) missile--start of work an the R-12' was issued..

• Test mission - . Nation: Russia. Agency: MVS. Apogee: 402 km (249 mi).

• 63M No. 3? - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 63M No. 4? - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 63M No. 2? - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 63M No. 6? - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 63M No. 5? - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• USSR sells R-12 missiles to China. - . Nation: Russia. Ministry of Armaments Decree 'On transfer of two R-12 missiles to China (on August 6)' was issued..

• Test mission - . Nation: Russia. Agency: MVS. Apogee: 402 km (249 mi).

• Project 581 - . Nation: China. Related Persons: Tsien. Spacecraft: Project 581. The first project to build a Chinese satellite is set in motion..

• K63 No. 1 (LKI2-1) - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Project 581 pressure. - . Nation: China. Related Persons: Tsien. 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..

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 (LKI2 2 of 24) - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 63M No. 8 (LKI1-8) - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• K63 - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 8K63 control flight - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 8K63 control flight - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 8K63 control flight - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 8K63 control flight - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• 8K63 control flight - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Chinese plan satellite launch by December 1959 - . Nation: China. Related Persons: Tsien. 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.

• R-12 accepted into military service. - . Nation: Russia. Decree 'On adoption of the R-12 into armaments' was issued..

• GCh Gruzomaket - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Decision to withhold R-12 and nuclear warhead drawing package from China over Sidewinder affair - . Nation: China. Related Persons: Khrushchev, Tsien. 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.

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Test mission - . Nation: Russia. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Test mission - . Nation: Russia. Agency: MVS. Apogee: 402 km (249 mi).

• Test mission - . Nation: Russia. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Kosmos 63S1 small booster and DS small satellites authorised. - . Nation: Russia. 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'

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• V-1000 target mission - . Nation: Russia. Agency: OKB-30. Apogee: 402 km (249 mi).

• V-1000 target mission - . Nation: Russia. Agency: OKB-30. Apogee: 460 km (280 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Op. Rosa (to NZEM) - . Nation: Russia. Agency: MVS. Apogee: 400 km (240 mi).

• V-1000 target - . Nation: Ukraine. Agency: OKB-30. Apogee: 402 km (249 mi).

• V-1000 target mission - . Nation: Russia. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• V-1000 target - . Nation: Ukraine. Agency: OKB-30. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• V-1000 target - . Nation: Ukraine. Agency: OKB-30. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nuclear test - . Nation: Russia. Agency: RVSN. Apogee: 100 km (60 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nuclear test - . Nation: Russia. Agency: RVSN. Apogee: 100 km (60 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nuclear Test K-2 Nuclear test - . Nation: Russia. Agency: RVSN. Apogee: 180 km (110 mi). Two R-12's (other sources say R-5M's or an R-12 and an R-5M) were salvo fired, at least one with a live nuclear warhead, to Sary Shagan to support ABM-related research on the effects of nuclear explosions on rocket systems..

• Nuclear Test K-1 Nuclear test - . Nation: Russia. Agency: RVSN. Apogee: 300 km (180 mi). Two R-12's (other sources say R-5M's or an R-12 and an R-5M) were salvo fired, at least one with a live nuclear warhead, to Sary Shagan to support ABM-related research on the effects of nuclear explosions on rocket systems..

• DS-2 s/n 1 - . Payload: DS-1. Mass: 300 kg (660 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SA-200. Spacecraft: DS-1. 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..

• First launch of R-12U from silo. - . Nation: Russia. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• DS-1 s/n 1 - . Payload: DS-1. Mass: 300 kg (660 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SA-200. Spacecraft: DS-1.

  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.

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• MP-1 - . Nation: Russia. Agency: RVSN. Apogee: 405 km (251 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 1 - . Payload: DS-2 s/n 2. Mass: 47 kg (103 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-2. Completed Operations Date: 1962-03-26 . Decay Date: 1962-05-25 . USAF Sat Cat: 266 . COSPAR: 1962-Theta-1. Apogee: 649 km (403 mi). Perigee: 207 km (128 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.

• Nation: China. Agency: PRC. Apogee: 0 km (0 mi).

  First DF-2 launch attempt. The rocket impacted the earth after only 69 seconds of flight. Fundamental design errors were discovered in calculating flexing of the rocket in flight, placement of the guidance system, and engine mounting. The missile was completely redesigned for reduced thrust.

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 2 - . Payload: 1MS s/n 1. Mass: 285 kg (628 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 1MS. Decay Date: 1963-08-20 . USAF Sat Cat: 269 . COSPAR: 1962-Iota-1. Apogee: 1,485 km (922 mi). Perigee: 207 km (128 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. .

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 3 - . Payload: 2MS s/n 1. Mass: 330 kg (720 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 2MS. Decay Date: 1962-10-17 . USAF Sat Cat: 281 . COSPAR: 1962-Nu-1. Apogee: 707 km (439 mi). Perigee: 216 km (134 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. .

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 5 - . Payload: 2MS s/n 2. Mass: 280 kg (610 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 2MS. Decay Date: 1963-05-02 . USAF Sat Cat: 297 . COSPAR: 1962-Upsilon-1. Apogee: 1,578 km (980 mi). Perigee: 192 km (119 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. .

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 6 - . Payload: DS-P1 s/n 1. Mass: 355 kg (782 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1. Completed Operations Date: 1962-07-06 . Decay Date: 1962-09-08 . USAF Sat Cat: 338 . COSPAR: 1962-A-Delta-1. Apogee: 348 km (216 mi). Perigee: 261 km (162 mi). Inclination: 48.90 deg. Period: 90.60 min. Prototype ABM radar target; supported developmental experiments for ABM systems..

• SSATC Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• SSATC Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• SSATC Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 8 - . Payload: DS-K-8 s/n 1. Mass: 337 kg (742 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Earth. Type: Micrometeoroid satellite. Spacecraft Bus: DS. Spacecraft: DS-K-8. Completed Operations Date: 1962-08-23 . Decay Date: 1963-08-17 . USAF Sat Cat: 367 . COSPAR: 1962-A-Xi-1. Apogee: 598 km (371 mi). Perigee: 244 km (151 mi). Inclination: 49.00 deg. Period: 92.90 min. Detected meteoroid flux in near-earth space and carried unspecified military research equipment..

• SSATC Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 11 - . Payload: DS-A1 s/n 1. Mass: 315 kg (694 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1962-10-28 . Decay Date: 1964-05-18 . USAF Sat Cat: 441 . COSPAR: 1962-B-Theta-1. Apogee: 858 km (533 mi). Perigee: 240 km (140 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.

• Nuclear test K-3 Nuclear test - . Nation: Russia. Agency: RVSN. Apogee: 500 km (310 mi). The R-12 (other sources say an R-5M) launched a live thermonuclear warheads toward Sary Shagan which was detonated at an altitude of 300 km. High altitude tests designed to test electromagnetic pulse effects on electronics, especially ABM system radars..

• 1MS - . Mass: 285 kg (628 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 1MS.

• Nuclear test K-4 Nuclear test - . Nation: Russia. Agency: RVSN. Apogee: 500 km (310 mi).

  In a test of nuclear fratricide and ABM effectiveness, an R-5M (some sources say an R-12) launched a live thermonuclear warhead toward Semipalitinsk/Sary Shagan which was detonated at an altitude of 150 km. Two R-9 ICBM's were launched minutes earlier, timed to pass through the zone of the explosion. Both missiles guided to the planned impact zone without apparent ill-effect. This high altitude test was designed to test electromagnetic pulse effects on electronics, especially ABM system radars and incoming 'friendly' ICBM's.

• SSATC Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nuclear Test K-5 Nuclear test - . Nation: Russia. 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.

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• SSATC Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• SSATC Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• M-12 re-entry vehicle test flight - . Nation: Russia. 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..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• DS-P1 s/n 2 - . Payload: DS-P1. Mass: 355 kg (782 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1. Prototype ABM radar target; supported developmental experiments for ABM systems..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 14 - . Payload: DS-U / Omega-1. Mass: 347 kg (765 lb). Nation: Russia. Agency: MO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: Omega. Decay Date: 1963-08-29 . USAF Sat Cat: 567 . COSPAR: 1963-010A. Apogee: 410 km (250 mi). Perigee: 250 km (150 mi). Inclination: 48.90 deg. Period: 91.10 min. Tested VNIIEM electric gyrodyne satellite orientation technology..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 17 - . Payload: DS-A1 s/n 2. Mass: 322 kg (709 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1963-05-30 . Decay Date: 1965-06-02 . USAF Sat Cat: 580 . COSPAR: 1963-017A. Apogee: 658 km (408 mi). Perigee: 251 km (155 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.

• DS-MT s/n 1 - . Payload: DS-MT. Mass: 340 kg (740 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• R-12U (8K63U) - . Nation: Ukraine. Agency: RVSN. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 19 - . Payload: DS-P1 s/n 3. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1. Completed Operations Date: 1964-03-29 . Decay Date: 1964-03-30 . USAF Sat Cat: 632 . COSPAR: 1963-033A. Apogee: 497 km (308 mi). Perigee: 267 km (165 mi). Inclination: 49.00 deg. Period: 92.10 min. Prototype ABM radar target; supported developmental experiments for ABM systems..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• DS-A1 s/n 3 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

  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.

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Kosmos scientific satellites authorised. - . Nation: Russia. Spacecraft Bus: SA-200. 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..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• DS-A1 s/n 4 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

  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.

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Cosmos 23 - . Payload: DS-U / Omega-1. Mass: 347 kg (765 lb). Nation: Russia. Agency: MO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: Omega. Decay Date: 1964-03-27 . USAF Sat Cat: 707 . COSPAR: 1963-050A. Apogee: 560 km (340 mi). Perigee: 232 km (144 mi). Inclination: 48.90 deg. Period: 92.40 min. Tested VNIIEM electric gyrodyne satellite orientation technology..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 25 - . Payload: DS-P1 s/n 4. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1. Completed Operations Date: 1964-11-21 . Decay Date: 1964-11-21 . USAF Sat Cat: 757 . COSPAR: 1964-010A. Apogee: 495 km (307 mi). Perigee: 260 km (160 mi). Inclination: 49.10 deg. Period: 92.10 min. Prototype ABM radar target; supported developmental experiments for ABM systems..

• Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Target - . Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 26 - . Payload: DS-MG s/n 1. Mass: 365 kg (804 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MG. Completed Operations Date: 1964-04-01 . Decay Date: 1964-09-28 . USAF Sat Cat: 766 . COSPAR: 1964-013A. Apogee: 376 km (233 mi). Perigee: 268 km (166 mi). Inclination: 48.90 deg. Period: 91.00 min. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also obtained radiation data..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 31 - . Payload: DS-MT s/n 2. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Completed Operations Date: 1964-06-23 . Decay Date: 1964-10-20 . USAF Sat Cat: 803 . COSPAR: 1964-028A. Apogee: 485 km (301 mi). Perigee: 221 km (137 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..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: China. Agency: PRC. Apogee: 200 km (120 mi). This followed a two-year complete redesign and test program following the first launch failure in 1962. The reduced-thrust missile had a range of 1050 km with a 1550 kg warhead, barely enough to reach Japan..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Test mission - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Test mission - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 0 km (0 mi).

• Cosmos 36 - . Payload: DS-P1-Yu s/n 1. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1965-02-27 . Decay Date: 1965-02-28 . USAF Sat Cat: 844 . COSPAR: 1964-042A. Apogee: 488 km (303 mi). Perigee: 253 km (157 mi). Inclination: 49.00 deg. Period: 92.00 min. Development of systems for air defence and the control of outer space..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 42 - . Mass: 100 kg (220 lb). Nation: Russia. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft Bus: Strela. Spacecraft: Strela-1. Decay Date: 1965-12-19 . USAF Sat Cat: 864 . COSPAR: 1964-050A. Apogee: 1,105 km (686 mi). Perigee: 228 km (141 mi). Inclination: 48.90 deg. Period: 98.10 min.

• Cosmos 43 - . Mass: 100 kg (220 lb). Nation: Russia. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft Bus: Strela. Spacecraft: Strela-1. Decay Date: 1965-12-27 . USAF Sat Cat: 867 . COSPAR: 1964-050C. Apogee: 1,093 km (679 mi). Perigee: 227 km (141 mi). Inclination: 48.90 deg. Period: 98.00 min.

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• First Chinese atomic bomb tested. - . Nation: China. Program: Long March. The warhead had a yield of 20 kilotons..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 49 - . Payload: DS-MG s/n 2. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MG. Completed Operations Date: 1964-11-09 . Decay Date: 1965-08-21 . USAF Sat Cat: 913 . COSPAR: 1964-069A. Apogee: 472 km (293 mi). Perigee: 260 km (160 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..

• Go-ahead for DF-2A. - . Nation: China. Related Persons: Tsien. Program: Long March. Decision to proceed with DF-2A extended range version of DF-2.

• DS-2 s/n 2 - . Payload: DS-2. Mass: 315 kg (694 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-2. 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..

• Cosmos 51 - . Payload: DS-MT s/n 3. Mass: 350 kg (770 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Completed Operations Date: 1965-01-04 . Decay Date: 1965-11-14 . USAF Sat Cat: 947 . COSPAR: 1964-080A. Apogee: 537 km (333 mi). Perigee: 258 km (160 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..

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Cosmos 53 - . Payload: DS-A1 s/n 5. Mass: 310 kg (680 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1965-02-09 . Decay Date: 1966-08-12 . USAF Sat Cat: 983 . COSPAR: 1965-006A. Apogee: 1,172 km (728 mi). Perigee: 221 km (137 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.

• DS-P1-Yu s/n 2 - . Payload: DS-P1-Yu. Mass: 330 kg (720 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Development of systems for air defence and the control of outer space..

• DS-A1 s/n 6 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

  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.

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Nation: Ukraine. Agency: MVS. Apogee: 402 km (249 mi).

• Scientific Kosmos satellites approved. - . Nation: Russia. Spacecraft Bus: DS. 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..

• Cosmos 70 - . Payload: DS-A1 s/n 7. Mass: 250 kg (550 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1965-07-12 . Decay Date: 1966-12-18 . USAF Sat Cat: 1431 . COSPAR: 1965-052A. Apogee: 1,176 km (730 mi). Perigee: 223 km (138 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.

• Cosmos 76 - . Payload: DS-P1-Yu s/n 3. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1965-10-28 . Decay Date: 1966-03-16 . USAF Sat Cat: 1464 . COSPAR: 1965-059A. Apogee: 513 km (318 mi). Perigee: 256 km (159 mi). Inclination: 48.80 deg. Period: 92.20 min. Development of systems for air defence and the control of outer space..

• Cosmos 93 - . Payload: DS-U2-V s/n 1. Mass: 305 kg (672 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Military technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-V. Completed Operations Date: 1965-12-16 . Decay Date: 1966-01-03 . USAF Sat Cat: 1629 . COSPAR: 1965-084A. Apogee: 513 km (318 mi). Perigee: 216 km (134 mi). Inclination: 48.40 deg. Period: 91.80 min. Military technology development satellite - mission still classified..

• First successful test of DF-2A. - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi). First launch of redesigned DF-2. The flight demonstrated a 20% improvement in range for the same 1500 kg payload, and replaced the radio guidance of the DF-2 with an autonoumous gyroscopic system..

• Cosmos 95 - . Payload: DS-U2-V s/n 2. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Military technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-V. Completed Operations Date: 1965-11-04 . Decay Date: 1966-01-18 . USAF Sat Cat: 1706 . COSPAR: 1965-088A. Apogee: 521 km (323 mi). Perigee: 211 km (131 mi). Inclination: 48.40 deg. Period: 91.90 min. Military technology development satellite - mission still classified..

• Cosmos 97 - . Payload: DS-U2-M s/n 1. Mass: 267 kg (588 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-M. Completed Operations Date: 1966-01-23 . Decay Date: 1967-04-02 . USAF Sat Cat: 1777 . COSPAR: 1965-095A. Apogee: 2,144 km (1,332 mi). Perigee: 214 km (132 mi). Inclination: 48.40 deg. Period: 108.90 min. Development tests of atomic clocks..

• Cosmos 101 - . Payload: DS-P1-Yu s/n 4. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1966-03-11 . Decay Date: 1966-07-12 . USAF Sat Cat: 1846 . COSPAR: 1965-107A. Apogee: 533 km (331 mi). Perigee: 256 km (159 mi). Inclination: 48.80 deg. Period: 92.50 min. Development of systems for air defence and the control of outer space..

• DS-K-40 s/n 1 - . Payload: DS-K-40. Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-K-40. Development of systems for the later operational Tselina satellites..

• Cosmos 106 - . Payload: DS-P1-I s/n 1. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-I. Completed Operations Date: 1966-11-15 . Decay Date: 1966-11-14 . USAF Sat Cat: 1949 . COSPAR: 1966-004A. Apogee: 553 km (343 mi). Perigee: 281 km (174 mi). Inclination: 48.40 deg. Period: 92.80 min. Operational radar target for the ABM forces..

• Cosmos 108 - . Payload: DS-U1-G s/n 1. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Earth. Type: Ionosphere satellite. Spacecraft Bus: DS. Spacecraft: DS-U1-G. Completed Operations Date: 1966-02-26 . Decay Date: 1966-11-21 . USAF Sat Cat: 2002 . COSPAR: 1966-011A. Apogee: 850 km (520 mi). Perigee: 220 km (130 mi). Inclination: 48.80 deg. Period: 95.30 min. Studied the relationship between variations in the upper atmosphere and solar activity..

• DS-K-40 s/n 2 - . Payload: DS-K-40. Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-K-40. Development of systems for the later operational Tselina satellites..

• Cosmos 116 - . Payload: DS-P1-Yu s/n 6. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1966-12-03 . Decay Date: 1966-12-03 . USAF Sat Cat: 2152 . COSPAR: 1966-036A. Apogee: 464 km (288 mi). Perigee: 288 km (178 mi). Inclination: 48.40 deg. Period: 92.00 min. Development of systems for air defence and the control of outer space..

• Cosmos 119 - . Payload: DS-U2-I s/n 1. Mass: 250 kg (550 lb). Nation: Russia. Agency: MO. Program: DS. Class: Earth. Type: Ionosphere satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-I. Completed Operations Date: 1966-05-26 . Decay Date: 1966-11-30 . USAF Sat Cat: 2182 . COSPAR: 1966-043A. Apogee: 1,278 km (794 mi). Perigee: 209 km (129 mi). Inclination: 48.40 deg. Period: 99.70 min. Studied the influence of the ionosphere on passing VLF radio waves..

• Cosmos 123 - . Payload: DS-P1-Yu s/n 5. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1966-12-10 . Decay Date: 1966-12-10 . USAF Sat Cat: 2295 . COSPAR: 1966-061A. Apogee: 512 km (318 mi). Perigee: 256 km (159 mi). Inclination: 48.80 deg. Period: 92.30 min. Development of systems for air defence and the control of outer space..

• Nuclear test - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi).

  DF-2A launched with a 1290 kg, 12 kt warhead from Jiuquan flew over a range of 800 km to Lop Nor, where the warhead successfully exploded. The Ninth Academy was responsible for development of the nuclear package. Tsien protégé Guo Yonghuai was the liaison between the Fifth and Ninth Academies for the development.

• Cosmos 135 - . Payload: DS-U2-MP s/n 1. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Earth. Type: Micrometeoroid satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-MP. Completed Operations Date: 1967-04-12 . Decay Date: 1967-04-12 . USAF Sat Cat: 2612 . COSPAR: 1966-112A. Apogee: 648 km (402 mi). Perigee: 253 km (157 mi). Inclination: 48.40 deg. Period: 93.60 min. Studied cosmic dust particles in near-Earth space..

• Cosmos 137 - . Payload: DS-U2-D s/n 1. Mass: 295 kg (650 lb). Nation: Russia. Agency: MO. Program: DS. Class: Earth. Type: Magnetosphere satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-D. Completed Operations Date: 1969-05-12 . Decay Date: 1967-11-23 . USAF Sat Cat: 2627 . COSPAR: 1966-117A. Apogee: 1,718 km (1,067 mi). Perigee: 219 km (136 mi). Inclination: 48.80 deg. Period: 104.40 min. Studied charged particle flows..

• Cosmos 142 - . Payload: DS-U2-I s/n 2. Mass: 315 kg (694 lb). Nation: Russia. Agency: MO. Program: DS. Class: Earth. Type: Ionosphere satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-I. Completed Operations Date: 1967-07-06 . Decay Date: 1967-07-06 . USAF Sat Cat: 2678 . COSPAR: 1967-013A. Apogee: 1,320 km (820 mi). Perigee: 216 km (134 mi). Inclination: 48.40 deg. Period: 100.10 min. Studied the influence of the ionosphere on passing VLF radio waves..

• Cosmos 145 - . Payload: DS-U2-M s/n 2. Mass: 250 kg (550 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-M. Completed Operations Date: 1967-04-30 . Decay Date: 1968-03-08 . USAF Sat Cat: 2697 . COSPAR: 1967-019A. Apogee: 2,107 km (1,309 mi). Perigee: 226 km (140 mi). Inclination: 48.40 deg. Period: 108.70 min. Development tests of atomic clocks..

• Cosmos 148 - . Payload: DS-P1-I s/n 2. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-I. Completed Operations Date: 1967-05-07 . Decay Date: 1967-05-07 . USAF Sat Cat: 2712 . COSPAR: 1967-023A. Apogee: 404 km (251 mi). Perigee: 270 km (160 mi). Inclination: 71.00 deg. Period: 91.30 min. Operational radar target for the ABM forces. First launch of 63SM/11K63 version of Kosmos launch vehicle; first launch from the Raduga launch complex at Plesetsk..

• Cosmos 149 - . Payload: DS-MO s/n 1. Mass: 321 kg (707 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MO. Completed Operations Date: 1967-04-08 . Decay Date: 1967-04-07 . USAF Sat Cat: 2714 . COSPAR: 1967-024A. Apogee: 284 km (176 mi). Perigee: 246 km (152 mi). Inclination: 48.40 deg. Period: 89.80 min. Used in development of aerodynamic systems for stabilisation and orientation of spacecraft. Also carried military optical equipment experiments..