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R-7

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Vostok Kaluga Museum
Credit: © Mark Wade

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The world's first ICBM became the most often used and most reliable launch vehicle in history. The original core+four strap-on booster missile had a small third stage added to produce the Vostok launch vehicle, with a payload of 5 metric tons. Addition of a larger third stage produced the Voskhod/Soyuz vehicle, with a payload over 6 metric tons. Using this with a fourth stage, the resulting Molniya booster placed communications satellites and early lunar and planetary probes in higher energy trajectories. By the year 2000 over 1,628 had been launched with an unmatched success rate of 97.5% for production models. Improved models providing commercial launch services for international customers entered service in the new millennium, and a new launch pad at Kourou was to be inaugurated in 2009. It appeared that the R-7 could easily still be in service 70 years after its first launch.

AKA: 8K71;Sapwood;SS-6 Mod 1. Status: Retired 1961. First Launch: 1957-05-15. Last Launch: 1960-06-04. Number: 26 . Payload: 5,370 kg (11,830 lb). Thrust: 3,904.00 kN (877,654 lbf). Gross mass: 279,100 kg (615,300 lb). Height: 33.50 m (109.90 ft). Diameter: 2.95 m (9.67 ft). Apogee: 1,000 km (600 mi).

Development of the R-7 began under research project N-3 "Development requirements for a liquid rocket with a range of 5,000 to 10,000 km and a warhead of 1 to 10 metric tons". The research project was authorized in a decree of 4 December 1950. The study was headed by Korolev's NII-88 but involved a wide range of other Soviet research institutes:

• OKB-456 - Glushko - Engines
• NII-885 - Ryazanskiy, Pilyugin - Guidance
• NII-3 - Shebanin / GSKB Spetsmash - Launch facility
• KB-11 - Nuclear warhead
• NII-4 - Sokolov - Launch pad development
• TSIAM - Svishchev
• TsAGI - Dorognitsin, Struminskiy - aerodynamics
• NII-6 - Sukhikh
• NII-125 - Zhukov
• NII-137 - Kostrov
• NII-504 - Karpov
• NII-10 - Kuznetsov - gyro platform
• NII-49 - Charin
• Mathematics Institute - Steklov and Keldysh

• Engines of 200 to 300 metric tons thrust, burning Lox/Kerosene propellant in place of the Lox/Alcohol used in rockets derived from German work, with a vacuum specific impulse of 325 seconds
• Nuclear payload reduction to the 3 to 5 metric ton range
• Autonomous inertial and radio guidance systems
• Heat shield and re-entry vehicle development to enable the warhead to survive re-entry into the atmosphere at 6 to 7 km/sec
• Parametric studies to determine the optimum rocket configuration

Work was well underway when the requirements were suddenly altered on 3 October 1953. Tests at Semipalatinsk had demonstrated the possibility of building a thermonuclear warhead of vastly greater power. However the total warhead mass would have to be increased to 5,500 kg, with the net mass of only the nuclear device itself being 3,000 kg. The rocket designed to that point would have a range of only 5,500 km with such a warhead. A meeting was called of the Chief Designers in January 1954 to discuss how to handle the problem. Several weight saving measures were used. The single engines per module were replaced by small diameter engines of reduced length; the propellant tanks were laid out to minimize mass; a unique launch pad design was accepted that suspended the rocket above the flame pit and shielded it from cross winds, which allowed a lighter structure.

Another technical challenge were the small vernier rockets used to pitch the rocket. These had to have a high specific impulse, gimbal 45 degrees, and deliver a thrust of 2.5 metric tons. Glushko could not deliver an engine with these characteristics, so Melnikov of OKB-1 was assigned the task of designing the engines in-house. The engine that resulted met the requirements and was the technological basis for later rocket engines developed within OKB-1 (the Lox/Kerosene upper stage engines for the Molniya, N1, and Proton boosters).

By February 1954 the stage was reached where a final design was possible. A government declaration of 20 May 1954 authorized development of the two stage R-7 / 8K71 intercontinental ballistic missile. This was followed by a decree of 28 June 1954 'On plans N/R for space research'. Implementation came via a Ministry of Defence decree of 6 July 1954 calling on all industry organizations to work together and assigning the project the highest national priority. The draft project, using much material generated for the T-1 project, was completed in July 1954.

The vehicle in the draft project used the 'packet' layout with a hammerhead core stage surrounded by four shorter booster stages. At ignition, the four booster stages ignited. If full thrust was achieved, the core was then ignited and the booster rose on the thrust of all five stages. The rocket could boost the 5500 kg warhead to 7.9 km/s and 8,000 km range, with a maximum miss distance of plus or minus 10 km. The warhead was the German 'sharp point': a 16 degree cone, 7.27 m long, mounted atop a cylindrical interstage section. The rocket had a gross lift-off mass of 280 metric tons, and an empty mass of 27 metric tons. The first stage burned out at 2,170 m/s and the second stage at 6,385 m/s. Thrust at lift-off was 403.4 metric tons. The R-7 incorporated ingenious solutions in ground handling of the large rocket. The rocket would be assembled horizontally, rolled out to the pad, then raised to the vertical position and quickly fuelled.

The expert commission deemed the decree requirements to be fulfilled and recommended construction of the rocket with minor changes in the development plan. The government authorized the construction phase in a decree of 20 November 1954. Korolev froze the design on 11 March 1955 and drawing release and parts fabrication began.

Meanwhile work was underway to provide the infrastructure needed for the test program. The Soviet Union was so vast that it was possible to test a missile with intercontinental range within its borders. A warhead impact area on the Kamchatka peninsula was selected, and in August 1955 at unit was formed at the village of Klyuchan in the Ust-Kamchatka region. Although eventually operated by the strategic rocket forces, his base was originally founded in 1913 to support the Kamchatka Fleet. To track incoming warheads, station NIP-6 was built at Ylizora in addition to NIP-7 at Klyuchan.

By 20 March 1956 a decree set forth the impending three stage development test plan:

• Two lots of prototype rockets for stand tests and one lot for flight tests
• Following completion of the prototype test series, incorporate necessary changes into next lot of rockets
• Final lot of rockets representing production configuration flight tested to verify changes

In the first half of 1956 work began in earnest at 36 factories with the objective of making the first test flight by the end of the year. The first article completed was a full scale mock-up consisting of the core and one booster stage. Two Block A and B stages were delivered for stand tests, but incomplete factory test equipment held up the start. At that point it seemed impossible that a flight would be made within the year.

By the second half of 1956 solutions had been found to the outstanding problems. Serial production of rockets had begun. The Progress Aviation Factory in Samara, V Ya Litvinov manager, had been selected to fabricate detailed parts but final assembly of the prototype rockets was carried out at Factory 88 in Kaliningrad. Over time the factory at Samara would be organised as the Third Filial of OKB-1 and take over first production, and then engineering, of future R-7 derivatives. In 1974 it became the TsKB, a separate entity.

R-7 systems were developed in the following research program:

• The radio guidance system was flight tested on R-5R modifications of the R-5 IRBM. Launches on 31 May and 15 June 1956 proved the system.
• The R-7's propellant utilization system, velocity integrator, stabilization system, Tral telemetry system, and Fakel control system were tested in two phases of 5 flights each of the M5RD modification of the R-5. Five Phase 1 flights took place from 16 February to 23 March 1956, followed by five Phase 2 flights from 20 July to 18 August 1956.
• The unique Tyulpan launch concept - suspension of the rocket from its 'shoulders' over the flame pit - was tested at a huge mock-up, 19 m in diameter, at the LMZ Leningrad Metal Foundry Factory. The rig also allowed hydraulics test of a mock-up booster with water in the tanks (protected by an anti-corrosion agent). The increasingly elaborated mock-up allowed the interface between the suspension arms and the rocket to be worked out in detail. Simulated launches allowed the separation of the vehicles and the umbilicals to be worked out, as well as the zero-shock launch concept (there were no hold-down clamps - once thrust built up, the rocket rose, and the suspension arms rotate away on counter-weights). LMZ also used the mock-up to develop ground handling, horizontal assembly, and installation protocols for the launch vehicle. The methods worked out in that summer remained in continuous use until well into the 21st Century.
• Rocket engine stand test were conducted at Filial 2 of NII-88 from July 1956 to March 1957. These included determining the best arrangement of engines and their components to minimize thermal and vibration effects. Also conducted were liquid oxygen / liquid nitrogen loading, control systems and vernier tests.
• Five test stand firings using three complete booster stages, were conducted on 15 August, 1 September, 24 September, 11 October, and 3 December 1956
• Three test stand firing using two core stages were conducted on 27 December 1956 and 10 and 26 January 1957.
• Two test stand firing were conducted using the complete rocket with four booster stages and the core stage. Ground test article s/n 2S was fired on 20 February 1957 and flight article s/n 4SL was fired on 30 March 1957.
• Ground test article s/n 5N was delivered to Baikonur in December 1956 for facilities verification tests, including ground handling, transport, assembly, erection, and propellant loading.
• The first flight article M1-5 was delivered to Baikonur in March 1957. The launch commission met on 10 April and certain questions were raised regarding the flight readiness due to test stand and ground test adequacy. Once these were resolved M1-5 was cleared for flight, and the first launch took place on 15 May 1957.

Maximum range: 8,000 km (4,900 mi). Number Standard Warheads: 1. Warhead yield: 3,000 KT. CEP: 3.39 km (2.10 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Cruise engine: RD-108. Initial Operational Capability: 1959.

Stage Data - R-7

• Stage 0. 4 x R-7 8K71-0. Gross Mass: 43,100 kg (95,000 lb). Empty Mass: 3,500 kg (7,700 lb). Thrust (vac): 970.000 kN (218,060 lbf). Isp: 306 sec. Burn time: 120 sec. Isp(sl): 250 sec. Diameter: 2.68 m (8.79 ft). Span: 2.68 m (8.79 ft). Length: 19.00 m (62.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-107-8D74. Status: Out of Production.

• Stage 1. 1 x R-7 8K71-1. Gross Mass: 95,300 kg (210,100 lb). Empty Mass: 7,500 kg (16,500 lb). Thrust (vac): 912.000 kN (205,025 lbf). Isp: 308 sec. Burn time: 330 sec. Isp(sl): 241 sec. Diameter: 2.99 m (9.80 ft). Span: 2.99 m (9.80 ft). Length: 28.00 m (91.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-108-8D75. Status: Out of Production.

Molniya 8K78 Russian orbital launch vehicle. Four stage derivative of the R-7 ICBM developed on a crash-program basis in 1960 for Soviet lunar and planetary deep space probe missions. The third stage found later use in the Voskhod and Soyuz launchers. By the 1970's mature versions of the launch vehicle were used almost entirely for launch of Molniya communications satellites and Oko missile early warning spacecraft into elliptical, 12-hour earth orbits.

Molniya 8K78M Russian orbital launch vehicle. Improved Molniya, in variants with Blocks ML, 2BL, or SO-L third stages according to payload.

Onega Russian orbital launch vehicle. Launch vehicle proposed for the 'Kliper' manned spaceplane in 2004. The 'Onega' was a hitherto-unrevealed massive improvement of the reliable Soyuz. It would deliver double the payload to a space station orbit, and could be available by 2010 if funding was made available.

R-7A Russian intercontinental ballistic missile. The R-7A was an improved version of the R-7 first ICBM, and the one actually deployed to pads in Baikonur and Plesetsk. The missile saw service from 1960 to 1968. Four pads at Plesetsk, and one reserve pad at Baikonur, were operational at the peak of deployment in 1962. These were the Soviet Union's only strategic missile deterrent during the Cuban Missile Crisis.

Soyuz 11A511 Russian orbital launch vehicle. Standardized launch vehicle designed to replace a proliferation of earlier models (8K72, 8A91, 8K74, 8K78, 11A57). Designed initially to support launch of the Soyuz complex (7K manned, 9K rocket stage, and 11k tanker) and Zenit-4 reconnaissance satellite. Later 'U' model extended to cover a range of follow-on satellites. Compared to 11A57, the telemetry system was reduced in mass to no more than 150 kg, and engines were cherry-picked for the vehicle core to ensure that specific impulse was no less than 252 seconds at sea level, 315 in vacuum.

Soyuz 11A511L Russian orbital launch vehicle. 11A511 with reinforced second stage, large fairing for earth orbit test of LK lunar lander.

Soyuz 11A511M Russian orbital launch vehicle. Development of the Soyuz-M began in 1967 to launch the 6.6 metric ton Soyuz 7K-VI manned military spacecraft into a 65-degree inclination earth orbit. The spacecraft was cancelled, but development continued, and eight Soyuz-M's were built and used to launch Zenit-4MT reconnaissance satellites in 1971-1976. It has been said that these missions flew elements of the 11A511U modifications (such as the 11D511/11D512 variants of the RD-107/8 engines).

Soyuz 11A511U / Ikar Russian orbital launch vehicle. Standard Soyuz universal booster with the Ikar upper stage, derived from the propulsion system for the Kozlov Yantar series of spy satellites.

Soyuz 11A514 Russian orbital launch vehicle. Version of Soyuz launcher with increased payload, designed to launch Soyuz R military reconnaissance satellite. Cancelled along with the Soyuz R project in 1966. Unknown differences to standard Soyuz to reach payload requirement of circa 6700 kg to 65 degree orbit.

Soyuz M Rus project was to result in first major propulsion upgrade to R-7 family in forty years, using first stage engines derived from those developed for Zenit second stage to boost performance. It would have permitted launches from Plesetsk with same or greater payload than launch of standard Soyuz-U from Baikonur, permitting move of more launch operations back onto Russian territory. Instead the more modest Soyuz ST / Soyuz FG upgrades were made.

Soyuz-ST-B Uprated Soyuz booster designed for commercial customers. Upgraded engines, modern digital avionics, reduced non-Russian content. Can be used with either Ikar or Fregat upper stages. The 'FG' was the military version.

Soyuz-U Russian standardized man-rated orbital launch vehicle derived from the original R-7 ICBM of 1957. It has been launched in greater numbers than any orbital launch vehicle in history. Not coincidentally, it has been the most reliable as well. After over 40 years service in Russia, ESA built a new launch pad at Kourou which will keep it in service from three launch sites in three countries well into the mid-21st Century.

Soyuz-U2 Russian orbital launch vehicle. Soyuz 11A511U2 used synthetic kerosene ('Sintin') in first stage for launch of premium reconnaissance satellite and manned payloads requiring just a bit more payload (200 kg) than the standard 11A511 could offer. Further use of the 11A511U2 abandoned in 1996 due to Sintin production stoppage. Later Soyuz spacecraft launched on standard Soyuz, with reduced payload and rendezvous with Mir in lower orbit accepted.

Sputnik 8A91 Russian intercontinental ballistic orbital launch vehicle. Modified R-7 ICBM used to launch Sputnik 3.

Sputnik 8K71PS Russian intercontinental ballistic orbital launch vehicle. Relatively unmodified R-7 ICBM test vehicles used to launch first two Sputniks.

Voskhod 11A57 Russian orbital launch vehicle. The 11A57 took the large third stage originally developed for the 8K78 interplanetary probe projects and applied it to increasing R-7 low earth orbit performance. It was primarily designed to launch the Zenit-4 reconnaissance satellite, but was also used for the Voskhod manned flights and later for a variety of other Zenit series versions.

Vostok 8A92 Russian orbital launch vehicle. The 8A92 was a modernized version of the Vostok booster used for launch of Zenit-2 reconnaissance satellites.

Vostok 8A92M Russian orbital launch vehicle. Second generation space systems required injection of lighter but higher-altitude Meteor and other satellite payloads into sun-synchronous orbits. The 8A92M version was developed for this purpose. First use was the Meteor launch on 29 June 1977.

Vostok 8K72 Russian orbital launch vehicle. 8K72 Luna launch vehicle, third stage modified with larger forward cylindrical section to accommodate Vostok-sized spacecraft. Used only for launch of first few prototype Vostoks.

Vostok 8K72K Russian orbital launch vehicle. R-7 ICBM with single-engine third stage, uprated from Luna launch vehicle and with forward fairing to accommodate Vostok/Zenit sized spacecraft. 8K72K, used for Vostok manned spacecraft launches and the first Zenit launch attempt.

Vostok-L 8K72 Russian orbital launch vehicle. R-7 ICBM with single-engine upper stage used for early Soviet unmanned lunar shots.

Yamal launch vehicle Version of the Soyuz proposed with an Ariane 4 or Russian LOx/LH2 upper stage.

Photo Gallery

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R-7 Sputnik

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R-7 aft end Credit: © Mark Wade

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Korolev/Kurchatov Architects of the Soviet nuclear deterrent. Credit: RKK Energia

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R-7 ICBM in assembly R-7 ICBM in assembly hall Credit: RKK Energia

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R-7 raised R-7 raised to launch position Credit: RKK Energia

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R-7 Credit: © Mark Wade

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R-7 Credit: © Mark Wade

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R-7 test console Credit: © Mark Wade

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Sputnik LV Credit: © Mark Wade

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• Russian satellite predicted. - . Nation: USA. M. K. Tikhonravov in New York Times said U.S.S.R. science made feasible space flight and creation of artificial earth satellite; reported U.S.S.R. rocket advance equaled or exceeded West..

• Go-ahead for R-7 ICBM by designers council - . Nation: Russia. Council of Chief designers approval to proceed with development of R-7..

• R-7 development plans. - . Nation: Russia. Council of Soviet Ministers (SM) Decree 'On NIP Plan for Special Product--course of work on the R-7 ICBM' was issued..

• R-7 draft project approved. - . Nation: Russia. Council of Soviet Ministers (SM) Decree 'On approval of the R-7 draft project' was issued..

• Tyuratam selected for ICBM test range. - . Nation: Russia.

  Council of Ministers selects Tyuratam for ICBM test site. The first 30 construction workers arrive at Tyuratam. The town founded at the rail staion is called Zarya (Dawn). The name will be changed to Leninsk in January 1958, but Zarya will remain the call sign of Soviet ground control.

• Housing/road constructions starts at Tyuratam - . Nation: Russia.

• First surveyors arrive at Tyuratam. - . Nation: Russia.

• LC 1 launch pad excavation starts - . Nation: Russia.

• Soviet Leadership tours Korolev's design bureau - . Nation: Russia. Related Persons: Bulganin, Khrushchev, Korolev, Ustinov.

  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).

• R-7 flight test authorised. - . Nation: Russia. Decree 'On means to ensure testing or the R-7' was issued..

• First concrete poured at pad A at Tyuratam - . Nation: Russia.

• First studies by Korolev OKB of manned spacecraft - . Nation: Russia. Related Persons: Feoktistov, Korolev. Program: Vostok. Class: Manned. Type: Manned spacecraft. Spacecraft: Vostok. First studies by Korolev and Feoktistov of manned spacecraft. The first stage would be suborbital ballistic flights (like the US Mercury-Redstone flights) from Kapustin Yar using IRBM's. First flights not planned until 1964 - 1967..

• Zenit preliminary design complete - . Nation: Russia. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit satellite. Design was original concept of Zenit reconnaisance spacecraft. The effort would later be included in the Vostok program under the name of Zenit..

• OKB-1 completed draft project for the first earth satellite - . Nation: Russia. Spacecraft: Sputnik 3.

  Tikhonravov's unit of OKB-1 completed the preliminary design of the ISZ satellite (launched as Sputnik 3). The Fourth Scientific Research Institute of the Ministry of Defence had meanwhile completed a draft project for the KIK ground control system. Tikhonravov's 1.4 tonne ISZ satellite was to have been launched by the new R-7 ICBM as the Soviet Union's first satellite, but the R-7 was ready before the satellite, so it was preceded by Sputnik 1 and Sputnik 2. The ISZ was a miniature physics laboratory, but was launched with a known faulty recorder, limiting data to that received when the spacecraft was over Soviet tracking stations. As a result, the Van Allen radiation belts were discovered by the United States rather than Russia.

• First ground equipment installed at Tyuratam - . Nation: Russia.

• State Commission formed to oversee R-7 flight test. - . Nation: Russia. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On creation of the State Commission for the R-7' was issued..

• Soviet space and ballistic missile tracking network established. - . Nation: Russia. Spacecraft: Sputnik 3.

  Decree 1241-632 '0n creation or the Command Measurement Complex' was issued. The decree marked the beginning of development of the KIK satellite tracking system. This network was put together using a combination of PVO (Air Defence) and ICBM tracking systems. Trajectory information was fed into the KIK Centre for orbital calculations. The Centre was staffed by 680 officers and 151 civilian scientists of the Soviet Army in four sections.

• Sputnik 3 draft project approved. - . Nation: Russia. Spacecraft: Sputnik 3.

  Decree 'On approval of the draft project for Object D' was issued. The decree gave the go-ahead for Tikhonravov's 1.4 tonne ISZ physics satellite to be launched by the new R-7 ICBM during the International Geophysical Year . The ISZ, a miniature physics laboratory,.was to have been the first artificial satellite of the earth. In the event, it was preceded by Sputniks 1 and 2.

• First Soviet ICBM base at Plesetsk is authorised. - . Nation: Russia. Decree 61-39ss 'On creation of launch complex Angara at NIIP-53' was issued..

• Flight test program for R-7 approved. - . Nation: Russia. Decree 'On approval of flight-testing program for the R-7 ICBM' was issued..

• Decision to build Sputnik 1 due to delays in Sputnik 3 design. - . Nation: Russia. Spacecraft: Sputnik 1. Council of Soviet Ministers (SM) Decree 171-83ss 'On Measures to Carry Out During the International Geophysical Year.--Launch of simple satellites in mid-1957' was issued..

• Checkout of first R-7 starts - . Nation: Russia.

• 1st R-7 rolled out to pad - . Nation: Russia.

• M1-5 (I-1) test - . Nation: Russia. Agency: MVS. Apogee: 100 km (60 mi). R-7 test flight. (M1-5 (I-1)).

• R-7 launch attempt - . Nation: Russia. After third attempt in three days to launch R-7 8K71 M1-6, the rocket is pulled from the pad. It is found that a nitrogen scavenging valve was installed backwards..

• Tikhonravov defined the development tasks for the Zenit reconnaissance satellite. - . Nation: Russia. Spacecraft Bus: Vostok. Spacecraft: Zenit satellite.

  These included development of a three stage version of R-7, development of satellite guidance and control systems of the precision required for photography from orbit, satellite control equipment, ELINT sensors, guidance systems, film cassette return systems, and tracking systems for recovery of the re-entry vehicle with the film cassette.

• M1-7 (I-2) test - . Nation: Russia. Agency: MVS. Apogee: 20 km (12 mi). R-7 test flight. (M1-7 (I-2)).

• M1-9 (I-3) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). First successful ICBM flight. Problems with the curing of the nose cone material, known before launch, led to the dummy warhead disintegrating over the Kamchatka Peninsula..

• R-7 ICBM announced publicly. - . Nation: Russia. Soviet Union announces successful launch of a "super longdistance intercontinental multistage ballistic rocket ...a few days ago," according to Tass Soviet News Agency..

• M1-10 (I-4) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). Second successful ICBM flight..

• Sputnik 1 - . Payload: PS. Mass: 84 kg (185 lb). Nation: Russia. Agency: MVS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Sputnik 1. Decay Date: 1958-01-03 . USAF Sat Cat: 2 . COSPAR: 1957-Alpha-2. Apogee: 945 km (587 mi). Perigee: 227 km (141 mi). Inclination: 65.00 deg. Period: 96.10 min.

  First artificial satellite; transmitted signals for 21 days. Launching of first ever artificial satellite of the Earth; physical study of the atmosphere; remained in orbit until January 4, 1958. This event began the space race by galvanizing interest and action on the part of the American public to support an active role in space research, technology, and exploration.

• Sputnik 2 - . Payload: PS-2. Mass: 508 kg (1,119 lb). Nation: Russia. Agency: MVS. Class: Biology. Type: Biology satellite. Spacecraft: Sputnik 2. Decay Date: 1958-04-14 . USAF Sat Cat: 3 . COSPAR: 1957-Beta-1. Apogee: 1,660 km (1,030 mi). Perigee: 212 km (131 mi). Inclination: 65.30 deg. Period: 103.70 min.

  Carried dog Laika. Study of the physical processes and conditions of life in outer space. After the surprise public impact of Sputnik 1, the satellite and launch teams were called back from vacation and in one month assembled the satellite (using equipment already developed for dog sounding rocket flights). After the launch, Soviet space officials said that the spacecraft would not return and that the dog had enough food and oxygen to live for up to 10 days. Only 45 years later was it revealed that Laika overheated, panicked and died within 5 to 7 hours of launch. What turned out to be the first space crypt remained in orbit a total of 162 days, then burned up in the atmosphere on April 14, 1958.

• Work begun on Vostok spacecraft and third stage - . Nation: Russia. Program: Vostok. Class: Manned. Type: Manned spacecraft. Spacecraft: Vostok.

• M1-12 (I-5) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). Last test of the original R-7 8K71 test series. Suborbital launch test..

• Soviet lunar probes authorised. - . Nation: Russia. Program: Luna. Spacecraft: Luna E-1. Decree 'On work on automated lunar probes and three-stage launch vehicles for them' was issued..

• M1-6A (I-6) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). R-7 test flight. (M1-6A (I-6)).

• Plesetsk construction begins. - . Nation: Russia. Construction work begins on Angara (R-7) base at Plesetsk..

• B1-11 (I-7) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). R-7 test flight. (B1-11 (I-7)).

• Sputnik failure - . Payload: D-1 s/n 1. Mass: 1,327 kg (2,925 lb). Nation: Russia. Agency: MVS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Sputnik 3. Decay Date: 1958-04-01 .

• Sputnik 3 - . Payload: D-1 s/n 2. Mass: 1,327 kg (2,925 lb). Nation: Russia. Agency: MVS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Sputnik 3. Decay Date: 1960-04-06 . USAF Sat Cat: 8 . COSPAR: 1958-Delta-2. Apogee: 1,864 km (1,158 mi). Perigee: 217 km (134 mi). Inclination: 65.20 deg. Period: 106.00 min. Variety of scientific data. Research in the upper atmosphere and outer space.

• B1-3 (II-1) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). R-7 test flight. (B1-3 (II-1)).

• R-14 IRBM, R-7A ICBM, and Raketoplan development authorised. - . Nation: Russia. Spacecraft: Raketoplan. Central Committee of the Communist Party and Council of Soviet Ministers Decree 726-346 'On start of work on the R-14 missile, on creation of the R-7A ICBM, and on creation of the winged-ballistic rocket at OKB-52' was issued..

• B1-14 (II-5)/Blok E test - . Nation: Russia. Agency: MVS. Apogee: 0 km (0 mi).

• Luna launch delayed. - . Nation: Russia. Class: Technology. Type: Navigation technology satellite.

  Planned August launch rescheduled after failure of American lunar probe on August 17. Inability to complete final tests of the new engines and malfunctions during pre-launch preparations indicated a lot of work had to be done on the new launch vehicle before the first launch could be attempted.

• Launch of Soviet Luna probes authorised. - . Nation: Russia. Program: Luna. Spacecraft: Luna E-1. Decree 'On launch of automated lunar probes November' was issued..

• Luna failure - booster disintegrated at T+92 seconds - . Payload: E-1 s/n 1. Mass: 361 kg (795 lb). Nation: Russia. Related Persons: Glushko, Korolev. Agency: MVS. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-1. This was the start of an acrimonious debated between Glushko and Korolev design bureaux over the fault and fix for the problem..

• Luna failure - booster disintegrated at T+104 seconds - . Payload: E-1 s/n 2. Mass: 361 kg (795 lb). Nation: Russia. Agency: MVS. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-1.

• Luna failure - booster core shut down at T+245 seconds - . Payload: E-1 s/n 3. Mass: 361 kg (795 lb). Nation: Russia. Agency: MVS. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-1.

• III-1 - . Nation: Kazakhstan. Agency: MVS. Apogee: 200 km (120 mi).

• Luna 1 - . Payload: E-1 s/n 4. Mass: 361 kg (795 lb). Nation: Russia. Agency: MVS. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-1. USAF Sat Cat: 112 . COSPAR: 1959-Mu-1.

  Lunar probe; passed within 5,995 km of moon but did not hit it as planned due to a failure of the launch vehicle control system. Went into solar orbit. First manmade object to attain of escape velocity. Also known as Mechta ("Dream"), popularly called Lunik I. Because of its high velocity and its announced package of various metallic emblems with the Soviet coat of arms, it was concluded that Luna 1 was intended to impact the Moon. After reaching escape velocity, Luna 1 separated from its 1472 kg third stage. The third stage, 5.2 m long and 2.4 m in diameter, travelled along with Luna 1. On 3 January, at a distance of 113,000 km from Earth, a large (1 kg) cloud of sodium gas was released by the spacecraft. This glowing orange trail of gas, visible over the Indian Ocean with the brightness of a sixth-magnitude star, allowed astronomers to track the spacecraft. It also served as an experiment on the behavior of gas in outer space. Luna 1 passed within 5,995 km of the Moon's surface on 4 January after 34 hours of flight. It went into orbit around the Sun, between the orbits of Earth and Mars. The measurements obtained during this mission provided new data on the Earth's radiation belt and outer space, including the discovery that the Moon had no magnetic field and that a solar wind, a strong flow of ionized plasma emmanating from the Sun, streamed through interplanetary space.

• R-7A flight test plan approved. - . Nation: Russia. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On Work on the R-7 Product and Flight-Design Testing of the R-7A Product-- testing of the R-7 and R-7A ICBMs' was issued..

• GCh No. 13 (III-2) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). First test flight serial production model..

• GCh No. 15 (III-3) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). R-7 development test flight. (GCh No. 15 (III-3)).

• GCh No. IZ-20 (III) test - . Nation: Russia. Agency: MVS. Apogee: 1,000 km (600 mi).

• R-7A ICBM production approved. - . Nation: Russia. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On production of the R-7A missile at Plant No. 1001 at Krasnoyarsk-26 and establishment of a branch' was issued..

• GCh No. 17 (III) test - . Nation: Russia. Agency: MVS. Apogee: 1,000 km (600 mi). R-7 development test flight. (GCh No. 17 (III)).

• GCh No. IZ-22 (III) test - . Nation: Russia. Agency: MVS. Apogee: 1,000 km (600 mi). Landed far from aim point..

• GCh No. IZ-23 (III) test - . Nation: Russia. Agency: MVS. Apogee: 1,000 km (600 mi). Landed far from aim point..

• Luna failure - inertial system failed at T+153 seconds - . Payload: E-1A s/n 5. Mass: 387 kg (853 lb). Nation: Russia. Agency: MVS. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft Bus: Luna E-1. Spacecraft: Luna E-1A.

• Samara Filial 1 takes over design responsibility for R-7 and its derivatives. - . Nation: Russia. Decree 'On formation of the Design Department of OKB-1 at the Progress Plant in Kuibyshev' was issued..

• GCh No. IZ-24 (III) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). R-7 development test flight. (GCh No. IZ-24 (III)).

• GCh (III) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). First successful flight of series production model..

• GCh No. IZ-25 (III) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi).

• Luna 2 - . Payload: E-1A s/n 6. Mass: 387 kg (853 lb). Nation: Russia. Agency: MVS. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft Bus: Luna E-1. Spacecraft: Luna E-1A. Decay Date: 1959-09-13 . USAF Sat Cat: 114 . COSPAR: 1959-Xi-1.

  First probe to impact lunar surface. Delivered a pennant to the surface of the Moon and conducted research during flight to the Moon. Impacted Moon 13 Sep 1959 at 22:02:04 UT, Latitude 29.10 N, Longitude 0.00 - Palus Putredinis, east of Mare Serenitatis near the Aristides, Archimedes, and Autolycus craters. After launch and attainment of escape velocity, Luna 2 separated from its third stage, which travelled along with it towards the Moon. On 13 September the spacecraft released a bright orange cloud of sodium gas which aided in spacecraft tracking and acted as an experiment on the behavior of gas in space. On 14 September, after 33.5 hours of flight, radio signals from Luna 2 abruptly ceased, indicating it had impacted on the Moon. Some 30 minutes after Luna 2, the third stage of its rocket also impacted the Moon. The mission confirmed that the Moon had no appreciable magnetic field, and found no evidence of radiation belts at the Moon.

• Phase 3 test flight - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). R-7 development test flight..

• Luna 3 - . Payload: E-2A s/n 1. Mass: 279 kg (615 lb). Nation: Russia. Agency: MVS. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-3. Decay Date: 1960-04-20 . USAF Sat Cat: 21 . COSPAR: 1959-Theta-1. Apogee: 499,998 km (310,683 mi). Perigee: 500 km (310 mi). Inclination: 55.00 deg. Period: 21,563.20 min.

  Luna 3 was the third spacecraft successfully launched to the Moon and the first to return images of the lunar far side. It was launched on a figure-eight trajectory which brought it over the Moon (closest approach to the Moon was 6200 km) and around the far side, which was sunlit at the time. It was stabilized while in optical view of the far side of the Moon. On October 7, 1959, the television system obtained a series of 29 photographs over 40 minutes, covering 70% of the surface, that were developed on-board the spacecraft. The photographs were scanned and 17 were radio transmitted to ground stations in facsimile form on October 18, 1959, as the spacecraft, in a barycentric orbit, returned near the Earth. The photographs were to be retransmitted at another point close to Earth but were not received. The spacecraft returned very indistinct pictures, but, through computer enhancement, a tentative atlas of the lunar farside was produced. These first views of the lunar far side showed mountainous terrain, very different from the near side, and two dark regions which were named Mare Moscovrae (Sea of Moscow) and Mare Desiderii (Sea of Dreams).

• Phase 3 test flight - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi).

• Phase 3 test flight - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi).

• First R-7 missiles go on alert at Plesetsk. - . Nation: Russia.

• Phase 3 test flight - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). Flight over full missile design range..

• Phase 3 test flight - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). Flight over full missile design range..

• GCh No. IZ-33 (III) test - . Nation: Russia. Agency: MVS. Apogee: 1,350 km (830 mi). Sixteenth and last launch of the third production batch..

• Flight test series of production R-7A ICBM begins - . Nation: Russia. These tests proved the design of the missile actually deployed to pads in Baikonur and Plesetsk..

• R-7A I-1 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi). Failure in first test of R-7A ICBM. Despite this failed launch, Cold War pressures meant that the R-7A conditionally entered service on 31 December 1959..

• Molniya 8K78 design begins - . Nation: Russia. Related Persons: Korolev. Korolev signed the order for development of a four stage rocket based on the R-7..

• R-7 accepted into military service. - . Nation: Russia. Decree 'On adoption of the R-7 ICBM into armaments' was issued..

• R-7A I-2/Dummy L test - . Nation: Russia. Agency: RVSN. Apogee: 1,000 km (600 mi). Suborbital aerodynamic test flight with R-7A 8K74 lower stages, dummy upper stages..

• R-7A I-3 test - . Nation: Russia. Agency: RVSN. Apogee: 20 km (12 mi).

• R-7A I-4/Dummy L test - . Nation: Russia. Agency: RVSN. Apogee: 1,000 km (600 mi). Suborbital aerodynamic test flight with R-7A 8K74 lower stages, dummy upper stages..

• R-7A I-4 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• R-7A I-5 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Luna failure - third stage insufficient delta V - . Payload: E-3 s/n 1. Mass: 279 kg (615 lb). Nation: Russia. Agency: RVSN. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-3. Decay Date: 1960-04-15 . COSPAR: F600415A. Reached an altitude of 200,000 km before plunging back to earth..

• Luna failure at lift-off - . Payload: E-3 s/n 2. Mass: 279 kg (615 lb). Nation: Russia. Agency: RVSN. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-3. Decay Date: 1960-04-16 . This dramatic failure resulted in a loss of thrust, and the lateral strap-on units separated and flew over the tracking stations and living areas. The core continued on its trajectory..

• Molniya 8K78 draft project completed - . Nation: Russia. The original design was intended for launch of unmanned probes toward Mars, but it had universal uses..

• Korabl-Sputnik 1 - . Payload: Vostok 1KP. Mass: 2,500 kg (5,500 lb). Nation: Russia. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Spacecraft: Vostok. Duration: 1,979.00 days. Decay Date: 1962-09-05 . USAF Sat Cat: 34 . COSPAR: 1960-Epsilon-1. Apogee: 514 km (319 mi). Perigee: 284 km (176 mi). Inclination: 65.00 deg. Period: 92.50 min.

  The Soviet Union launched a Vostok 1KP prototype manned spacecraft (without heat shield; not recoverable) into near-earth orbit. Called Sputnik IV by the Western press. On May 19, at 15:52 Moscow time, the spacecraft was commanded to retrofire. However the guidance system had oriented the spacecraft incorrectly and the TDU engine instead put the spacecraft into a higher orbit. Soviet scientists said that conditions in the cabin, which had separated from the remainder of the spacecraft, were normal.
  Officially: Development and checking of the main systems of the space ship satellite, which ensure its safe flight and control in flight, return to Earth and conditions needed for a man in flight.

• Molniya launch vehicle and initial Vostok flights approved. - . Nation: Russia. Spacecraft: Vostok. Central Committee and Council of Soviet Ministers Decree 587-238 'On the Realisation of the Plan to Master Cosmic Space in 1960 and the First Half of 1961 -creation of a four-stage launcher for interplanetary missions and schedule for the Korabl-Sputniks'.

• UBP (Readiness) operational test launch - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi). R-7 readiness verification test..

• Flight test series of production R-7A ICBM completed - . Nation: Russia. 15 launches were in the flight test series, with 14 successes. These rockets were completed at Aviation Factory Number 1, 'Progress', in Kuibyshev (Samara)..

• R-7A I-6 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• R-7A I-7 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Korabl-Sputnik - . Payload: Vostok 1K s/n 1. Mass: 4,730 kg (10,420 lb). Nation: Russia. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Spacecraft: Vostok. Decay Date: 1960-07-23 . First attempted flight of the Vostok 1K manned spacecraft prototype. Dogs Chaika and Lisichka perished in the explosion of the rocket..

• Korabl-Sputnik 2 - . Payload: Vostok 1K s/n 2. Mass: 1,440 kg (3,170 lb). Nation: Russia. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Spacecraft: Vostok. Duration: 1.09 days. Decay Date: 1960-08-20 . USAF Sat Cat: 55 . COSPAR: 1960-Lambda-1. Apogee: 340 km (210 mi). Perigee: 281 km (174 mi). Inclination: 64.60 deg. Period: 90.70 min.

  The Soviet Union launched its second unmanned test of the Vostok spacecraft, the Korabl Sputnik II, or Sputnik V. The spacecraft carried two dogs, Strelka and Belka, in addition to a gray rabbit, rats, mice, flies, plants, fungi, microscopic water plants, and seeds. Electrodes attached to the dogs and linked with the spacecraft communications system, which included a television camera, enabled Soviet scientists to check the animals' hearts, blood pressure, breathing, and actions during the trip. After the spacecraft reentered and landed safely the next day, the animals and biological specimens were reported to be in good condition.
  Officially: Development of systems ensuring man's life functions and safety in flight and his return to Earth.

• R-7A accepted for military service. - . Nation: Russia. Decree 'On adoption of the R-7A into armaments' was issued..

• Mars probe 1M s/n 1 failure. - . Payload: 1M s/n 1. Mass: 640 kg (1,410 lb). Nation: Russia. Agency: RVSN. Program: Mars. Class: Mars. Type: Mars probe. Spacecraft Bus: 1MV. Spacecraft: Mars 1M. Decay Date: 1960-10-10 .

  This was the Soviet Union's first attempt at a planetary probe. Mars probe intended to photograph Mars on a flyby trajectory. The possible cause lay in resonance vibrations of upper stages during Stage 2 burning, which led to break of contact in the command potentiometer of the gyrohorizon. As a result a pitch control malfunctioned and the launcher began to veer off the desired ascent profile. On exceeding 7 degrees of veering in pitch, the control system failed. The upper stage with the payload reached an altitude of 120 km before burning up on re-entry into the atmosphere above East Siberia.

• Mars probe 1M s/n 2 failure. - . Payload: 1M s/n 2. Mass: 640 kg (1,410 lb). Nation: Russia. Agency: RVSN. Program: Mars. Class: Mars. Type: Mars probe. Spacecraft Bus: 1MV. Spacecraft: Mars 1M. Decay Date: 1960-10-14 . Mars probe intended to photograph Mars on a flyby trajectory. This was the Soviet Union's second attempt at a planetary probe. The upper stages and payload broke up on re-entry into the atmosphere..

• Korabl-Sputnik 3 - . Payload: Vostok 1K s/n 3. Mass: 4,563 kg (10,059 lb). Nation: Russia. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Spacecraft: Vostok. Duration: 0.99 days. Decay Date: 1960-12-02 . USAF Sat Cat: 65 . COSPAR: 1960-Rho-1. Apogee: 269 km (167 mi). Perigee: 123 km (76 mi). Inclination: 65.00 deg. Period: 88.40 min.

  The Soviet Union launched its third spaceship satellite, Korabl Sputnik III, or Sputnik VI. The spacecraft, similar to those launched on May 15 and August 19, carried the dogs Pcheka and Mushka in addition to other animals, insects, and plants. Deorbited December 2, 1960 7:15 GMT. Burned up on reentry due to steep entry angle (retrofire engine did not shut off on schedule and burned to fuel depletion).
  Officially: Medical and biological research under space flight conditions.
  Officially: Medical and biological research under space flight conditions.

• Korabl-Sputnik - . Payload: Vostok 1K s/n 4. Mass: 4,730 kg (10,420 lb). Nation: Russia. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Spacecraft: Vostok. Decay Date: 1960-12-20 .

  Unable to reach orbital velocity, the Vostok prototype separated while the third stage was still firing. While the ejection seat failed to operate, the capsule did make a hard landing in severe winter conditons in Siberia. It was recovered after some time, and the dogs Kometa and Shutka were alive. As a result of this flight the ejection seat was developed with a heat shield designed to protect the pilot in the event of a launch vehicle failure up to shut down of the first stage. Additional Details: here....

• R-7A II-1 operational test launch - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi). Some sources say first launch from LC31 was not until 27 February..

• Venera preparations - . Nation: Russia. Spacecraft Bus: 2MV. Spacecraft: Mars 2MV-2.

  The VVS contingent arrives at Tyuratam at 23:45 aboard an Il-14 for the Venera launch. Chertok is in charge of launch preparations. Due to various radio system problems, there can be no launch until 26 January. The death of Nedelin and the others still hangs over the cosmodrome.

• Venera rolled out to pad - . Nation: Russia. Spacecraft Bus: 2MV. Spacecraft: Mars 2MV-2. The booster is 5 to 7 m taller than the Vostok. One gyroscope has to be replaced on the pad. Fuelling begins at 23:30. At 02:00 the launch is scrubbed due to continuing gyro problems. Next attempt is set for 4 February..

• Sputnik 7 - . Payload: 2MV-2 s/n 1. Mass: 6,483 kg (14,292 lb). Nation: Russia. Related Persons: Glushko, Korolev. Agency: RVSN. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 1MV. Spacecraft: Venera 1VA. Decay Date: 1961-02-26 . USAF Sat Cat: 71 . COSPAR: 1961-Beta-1. Apogee: 318 km (197 mi). Perigee: 212 km (131 mi). Inclination: 64.90 deg. Period: 89.80 min.

  The escape stage entered parking orbit but the main engine cut off just 0.8 s after ignition due to cavitation in the oxidiser pump and pump failure.. The payload attached together with escape stage remained in Earth orbit.

  The booster launched into a beautiful clear sky, and it could be followed by the naked eye for four minutes after launch. The third stage reached earth parking orbit, but the fourth stage didn't ignite. It was at first believed a radio antenna did not deploy from the interior of the stage, and it did not receive the ignition commands. Therefore the Soviet Union has successfully orbited a record eight-tonne 'Big Zero' into orbit. The State Commission meets two hours after the launch, and argues whether to make the launch public or not, and how to announce it. Glushko proposes the following language for a public announcement: 'with the objective of developing larger spacecraft, a payload was successfully orbited which provided on the first revolution the necessary telemetry'. Korolev and the others want to minimize any statement, to prevent speculation that it was a reconnaissance satellite or a failed manned launch. Kamanin's conclusion - the rocket didn't reach Venus, but it did demonstrated a new rocket that could deliver an 8 tonne thermonuclear warhead anywhere on the planet. The commission heads back to Moscow.

• Venera 1 - . Payload: 1VA s/n 2, Venera 1 (Sputnik 8, AMS). Mass: 644 kg (1,419 lb). Nation: Russia. Related Persons: Korolev. Agency: RVSN. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 1MV. Spacecraft: Venera 1VA. USAF Sat Cat: 80 . COSPAR: 1961-Gamma-1.

  Venera 1 was the first spacecraft to fly by Venus. The 6424 kg assembly was launched first into a 229 x 282 km parking orbit, then boosted toward Venus by the restartable Molniya upper stage. On 19 February, 7 days after launch, at a distance of about two million km from Earth, contact with the spacecraft was lost. On May 19 and 20, 1961, Venera 1 passed within 100,000 km of Venus and entered a heliocentric orbit. This failure resulted in only the following objectives being met: checking of methods of setting space objects on an interplanetary course; checking of extra-long-range communications with and control of the space station; more accurate calculation of the dimension of the solar system; a number of physical investigations in space. Additional Details: here....

• R-7A II-2 operational test launch - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi). Some sources say first launch from LC31 was not until 27 February..

• Operational missile test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• R-7 Failure Commission - . Nation: Russia. Related Persons: Bogomolov, Glushko, Keldysh, Korolev, Kosberg, Sokolov. Program: Vostok. Flight: Vostok 1. Spacecraft: Vostok.

  Keldysh, Korolev, Sokolov, Glushko, Bogomolov hear testimony from Kosberg on the causes of the RO-7 engine failure on the 22 December 1960 launch, that resulted in the suborbital flight of the Vostok capsule with a landing in Tura. The causes are not completely understood, but the bottom line is that a fuel line must have leaked. Further testimony is offered on the booster trajectory, landing time at various points along the trajectory, tracking station readiness, communications lessons, and recovery efforts. The communications are clearly unreliable. The radius of the HF radio is 5000 km, and 1500 km for UHF. TsP Moscow and PU Tyuratam, plus Novosibirsk, Kolpachev, Khabarovsk, and Yelizov (Kamchatka) all have HF and UHF transceivers. But due to practical reception problems, only UHF communications were available at Tyuratam, Kolpachev, and Yelizov, and only HF at Novosibirsk and Khabarovsk. It is recommended that each IP tracking station should have a Chief Communications Officer, a cosmonaut to act as capsule communicator, a physician, and a representative from the Ministry of Communications to assure action on problems.

• Korabl-Sputnik 4 - . Payload: Vostok 3KA s/n 1. Mass: 4,700 kg (10,300 lb). Nation: Russia. Related Persons: Mozzhorin, Yazdovskiy. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 1. Spacecraft: Vostok. Duration: 0.0700 days. Decay Date: 1961-03-09 . USAF Sat Cat: 91 . COSPAR: 1961-Theta-1. Apogee: 239 km (148 mi). Perigee: 173 km (107 mi). Inclination: 64.90 deg. Period: 88.60 min.

  Carried dog Chernushka, mannequin Ivan Ivanovich, and other biological specimens. Ivanovich was ejected from the capsule and recovered by parachute, and Chernsuhka was successfully recovered with the capsule on March 9, 1961 8:10 GMT.
  Officially: Development of the design of the space ship satellite and of the systems on board, which ensure necessary conditions for man's flight. Additional Details: here....

• Flight preparations - . Nation: Russia. Related Persons: Barmin, Gagarin, Keldysh, Korolev, Nelyubov, Titov. Program: Vostok. Flight: Vostok 1.

  Between 10:00 and 12:00 Chief Designer of Launch Facilities Barmin meets with the cosmonauts. He reviews the launch mechanism. The rocket is suspended at the 'shoulders' of the strap-ons, on four swivelled supports. After the rocket has lifted 49 mm, it is free from these, and counterweights weighing dozens of tonnes will swing them back and away from the rising booster. At 12:00 Kamanin meets with Keldysh and Korolev. They agree with his position that the flight be announced as soon as the cosmonaut is safely in orbit.

• Korabl-Sputnik 5 - . Payload: Vostok 3KA s/n 2. Mass: 4,695 kg (10,350 lb). Nation: Russia. Related Persons: Bykovsky, Gagarin, Goreglyad, Kamanin, Karpov, Keldysh, Kirillov, Korolev, Nelyubov, Nikolayev, Popovich, Titov, Voskresenskiy, Yazdovskiy. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 1. Spacecraft: Vostok. Duration: 0.0600 days. Decay Date: 1961-03-25 . USAF Sat Cat: 95 . COSPAR: 1961-Iota-1. Apogee: 175 km (108 mi). Perigee: 175 km (108 mi). Inclination: 64.90 deg. Period: 88.00 min.

  Carried dog Zvezdochka and mannequin Ivan Ivanovich. Ivanovich was again ejected from the capsule and recovered by parachute, and Zvezdochka was successfully recovered with the capsule on March 25, 1961 7:40 GMT.
  Officially: Development of the design of the space ship satellite and of the systems on board, designed to ensure man's life functions during flight in outer space and return to Earth. Additional Details: here....

• Vostok 1 - . Call Sign: Kedr (Cedar ). Crew: Gagarin. Backup Crew: Nelyubov, Titov. Payload: Vostok 3KA s/n 3. Mass: 4,725 kg (10,416 lb). Nation: Russia. Related Persons: Karpov, Keldysh, Korolev, Moskalenko, Rudnev. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 1. Spacecraft: Vostok. Duration: 0.0750 days. Decay Date: 1961-04-12 . USAF Sat Cat: 103 . COSPAR: 1961-Mu-1. Apogee: 315 km (195 mi). Perigee: 169 km (105 mi). Inclination: 65.00 deg. Period: 89.30 min.

  First manned spaceflight, one orbit of the earth. Three press releases were prepared, one for success, two for failures. It was only known ten minutes after burnout, 25 minutes after launch, if a stable orbit had been achieved.

  The payload included life-support equipment and radio and television to relay information on the condition of the pilot. The flight was automated; Gagarin's controls were locked to prevent him from taking control of the ship. The combination to unlock the controls was available in a sealed envelope in case it became necessary to take control in an emergency. After retrofire, the service module remained attached to the Sharik reentry sphere by a wire bundle. The joined craft went through wild gyrations at the beginning of re-entry, before the wires burned through. The Sharik, as it was designed to do, then naturally reached aerodynamic equilibrium with the heat shield positioned correctly.

  Gagarin ejected after re-entry and descended under his own parachute, as was planned. However for many years the Soviet Union denied this, because the flight would not have been recognized for various FAI world records unless the pilot had accompanied his craft to a landing. Recovered April 12, 1961 8:05 GMT. Landed Southwest of Engels Smelovka, Saratov. Additional Details: here....

• R-7A II-3 test - . Nation: Russia. Agency: RVSN. Apogee: 0 km (0 mi). Failure occurred only two days after Yuri Gagarin's flight..

• R-7A II-4 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• R-7A II-5 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• R-7A II-6 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi). Two launches from one launch complex in the same day..

• Vostok 2 - . Call Sign: Oryel (Eagle ). Crew: Titov. Backup Crew: Nelyubov, Nikolayev. Payload: Vostok 3KA s/n 4. Mass: 4,730 kg (10,420 lb). Nation: Russia. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 2. Spacecraft: Vostok. Duration: 1.00 days. Decay Date: 1961-08-07 . USAF Sat Cat: 168 . COSPAR: 1961-Tau-1. Apogee: 221 km (137 mi). Perigee: 172 km (106 mi). Inclination: 64.80 deg. Period: 88.40 min.

  Second manned orbital flight. The Soviet Union successfully launched Vostok II into orbit with Gherman S. Titov as pilot. The spacecraft carried life-support equipment, radio and television for monitoring the condition of the cosmonaut, tape recorder, telemetry system, biological experiments, and automatic and manual control equipment. Flight objectives: Investigation of the effects on the human organism of a prolonged flight in orbit and subsequent return to the surface of the Earth; investigation of man's ability to work during a prolonged period of weightlessness. Titov took manual control of spacecraft but suffered from space sickness. He was equipped with a professional quality Konvas movie camera, with which ten minutes of film of the earth were taken through the porthole. Both television and film images were taken of the interior of the spacecraft. Like Gagarin, Titov experienced problems with separation of the service module after retrofire. Titov was never to fly again, after being assigned to the Spiral spaceplane, which turned out to be a dead-end project. A biography of him by Martin Caidin ('I Am Eagle') made him somewhat more accessible than Gagarin to the West.

• R-7A II-7 test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi). R-7A readiness verification test..

• Operational test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Zenit-2 11F61 s/n 1 - . Payload: Zenit-2 11F61 s/n 1. Mass: 4,610 kg (10,160 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Decay Date: 1961-12-11 .

  First attempted launch of Zenit photo-reconnaisance satellite. According to Kamanin, there was a problem with the third stage, and the capsule landed between Novosibirsk and Yakutsk, but could not be located. There was no information on the nature of the problem. Korolev stayed at Tyuratam, preparing for the next launch attempt.

• Vostok-Zh studies - . Nation: Russia. Program: Lunar L1. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Vostok. Spacecraft: Vostok-Zh.

  Vostok-Zh studies conducted for multiple dockings of rocket blocks and payloads in orbit for circumlunar missions, using Vostok rocket. Vostok-Zh spacecraft used to for manual dockings only. Manned reentry vehicle from circumlunar distance is Sever/Soyuz design. Korolev's reaction to Chelomei's exclusive assignment by Khrushchev to circumlunar mission.

• Korolev requests new Vostoks - . Nation: Russia. Related Persons: Korolev. Program: Vostok. Spacecraft: Vostok, Vostok-Zh, Zenit-4.

  Korolev has issued a letter requested eight new Vostok 3A spacecraft to be built in 1962-1963. He recommends that they should be finished as the 1100 to 1300 kg heavier 'Vostok-2', to be boosted by the 11A57 rocket, developed originally for the Zenit-4 spy satellite. These Vostok-2's will be used for docking experiments, to form EO Experimental Orbital stations, and to develop spacecraft systems for flight to the moon. The VVS fully supports these plans. One of the docking spacecraft will be piloted, the other unpiloted.

• Cosmos 4 - . Payload: Zenit-2 11F61 s/n 2. Mass: 4,610 kg (10,160 lb). Nation: Russia. Related Persons: Nikolayev, Popovich. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Flight: Vostok 3, Vostok 4. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 3.00 days. Decay Date: 1962-04-29 . USAF Sat Cat: 287 . COSPAR: 1962-Xi-1. Apogee: 317 km (196 mi). Perigee: 285 km (177 mi). Inclination: 65.00 deg. Period: 90.50 min.

  Area survey photo reconnaissance satellite. Program partially completed. Failure of primary spacecraft orientation system. It was to spend four days in space, to be followed by another mission during 5-10 May. This meant that Vostok 3/4 could not be launched before 20-30 May. The cosmonaut prime crew returned from their in-suit parachute training at Fedosiya.

• Zenit-2 11F61 s/n 3 - . Payload: Zenit-2 11F61 s/n 3. Mass: 4,610 kg (10,160 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Decay Date: 1962-06-01 .

  Area survey photo reconnaissance satellite. Third attempted launch of Zenit photo-reconnaissance satellite. It blew up 300 m from the pad, and did enough damage to put the launch complex out of operation for a month. Therefore the Vostok 3/4 launches could not take place until the end of July at the earliest.

• Operational test - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Molniya 8K78L preliminary design completed - . Nation: Russia. Related Persons: Korolev.

  The Molniya 8K78L was designed by Korolev's design bureau for launching a manned spacecraft on a flyby of the Moon and return to earth. To achieve this it would have used Lox/LH2 engines in the third and fourth stages. Such technology was years away in the Soviet Union and the project was not pursued further.

• Cosmos 7 - . Payload: Zenit-2 11F61 s/n 4. Mass: 4,610 kg (10,160 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 4.00 days. Decay Date: 1962-08-01 . USAF Sat Cat: 346 . COSPAR: 1962-A-Iota-1. Apogee: 356 km (221 mi). Perigee: 197 km (122 mi). Inclination: 64.90 deg. Period: 90.00 min. Area survey photo reconnaissance satellite. Also performed radiation measurements..

• Vostok 3 - . Call Sign: Sokol (Falcon ). Crew: Nikolayev. Backup Crew: Bykovsky, Volynov. Payload: Vostok 3KA s/n 5. Mass: 4,722 kg (10,410 lb). Nation: Russia. Related Persons: Barmin, Gagarin, Khrushchev, Kirillov, Kozlov, Frol, Popovich, Smirnov, Ustinov. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 3. Spacecraft: Vostok. Duration: 3.93 days. Decay Date: 1962-08-15 . USAF Sat Cat: 363 . COSPAR: 1962-A-Mu-1. Apogee: 218 km (135 mi). Perigee: 166 km (103 mi). Inclination: 65.00 deg. Period: 88.30 min.

  Joint flight with Vostok 4. The first such flight, where Vostok capsules were launched one day apart, coming within a few kilometers of each other at the orbital insertion of the second spacecraft. The flight was supposed to occur in March, but following various delays, one of the two Vostok pads was damaged in the explosion of the booster of the third Zenit-2 reconnsat in May. Repairs were not completed until August. Vostok 3 studied man's ability to function under conditions of weightlessness; conducted scientific observations; furthered improvement of space ship systems, communications, guidance and landing. Immediately at orbital insertion of Vostok 4, the spacecraft were less than 5 km apart. Popovich made radio contact with Cosmonaut Nikolayev. Nikolayev reported shortly thereafter that he had sighted Vostok 4. Since the Vostok had no maneuvering capability, they could not rendezvous or dock, and quickly drifted apart. The launches did allow Korolev to offer something new and different, and gave the launch and ground control crews practice in launching and handling more than one manned spacecraft at a time. The cosmonaut took colour motion pictures of the earth and the cabin interior. Additional Details: here....

• Vostok 4 - . Call Sign: Berkut (Golden Eagle ). Crew: Popovich. Backup Crew: Komarov, Volynov. Payload: Vostok 3KA s/n 6. Mass: 4,728 kg (10,423 lb). Nation: Russia. Related Persons: Nikolayev. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 4. Spacecraft: Vostok. Duration: 2.96 days. Decay Date: 1962-08-15 . USAF Sat Cat: 365 . COSPAR: 1962-A-Nu-1. Apogee: 211 km (131 mi). Perigee: 159 km (98 mi). Inclination: 65.00 deg. Period: 88.20 min.

  Joint flight with Vostok 3. Acquisition of experimental data on the possibility of establishing a direct link between two space ships; coordination of astronauts' operations; study of the effects of identical spaceflight conditions on the human organism. The launch of Popovich proceeds exactly on schedule, the spacecraft launching with 0.5 seconds of the planned time, entering orbit just a few kilometers away from Nikolayev in Vostok 3. Popovich had problems with his life support system, resulting in the cabin temperature dropping to 10 degrees Centigrade and the humidity to 35%. The cosmonaut still managed to conduct experiments, including taking colour motion pictures of the terminator between night and day and the cabin interior.

  Despite the conditions, Popovich felt able to go for the full four days scheduled. But before the mission, Popovich had been briefed to tell ground control that he was 'observing thunderstorms' if he felt the motion sickness that had plagued Titov and needed to return on the next opportunity. Unfortunately he actually did report seeing thunderstorms over the Gulf of Mexico, and ground control took this as a request for an early return. He was ordered down a day early, landing within a few mintutes of Nikolayev. Only on the ground was it discovered that he was willing to go the full duration, and that ground control had thought he had given the code.

• Sputnik 19 - . Payload: 2MV-1 s/n 1. Mass: 890 kg (1,960 lb). Nation: Russia. Related Persons: Kuznetsova, Ponomaryova, Solovyova, Tereshkova, Yerkina. Agency: RVSN. Program: Venera, Vostok. Class: Venus. Type: Venus probe. Spacecraft Bus: 2MV. Spacecraft: Mars 2MV-1. Decay Date: 1962-08-28 . USAF Sat Cat: 371 . COSPAR: 1962-A-Pi-1. Apogee: 252 km (156 mi). Perigee: 173 km (107 mi). Inclination: 64.90 deg. Period: 88.70 min.

  Attempt to launch a probe towards Mars. The launch went well, but the fourth stage motor burnt for only 45s of the planned 240s. The stage remained in Earth orbit. However Kamanin notes that it was good that the launch of the basic vehicle was a success - it gave the visiting female cosmonauts confidence in the rocket they will have to ride.

• Sputnik 20 - . Payload: 2MV-1 s/n 2. Mass: 6,500 kg (14,300 lb). Nation: Russia. Agency: RVSN. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 2MV. Spacecraft: Mars 2MV-1. Decay Date: 1962-09-06 . USAF Sat Cat: 381 . COSPAR: 1962-A-Tau-1. Apogee: 246 km (152 mi). Perigee: 185 km (114 mi). Inclination: 64.70 deg. Period: 88.80 min.

• Sputnik 21 - . Payload: 2MV-2 s/n 1. Mass: 6,500 kg (14,300 lb). Nation: Russia. Agency: RVSN. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 2MV. Spacecraft: Mars 2MV-2. Decay Date: 1962-09-14 . USAF Sat Cat: 389 . COSPAR: 1962-A-Phi-1. Apogee: 218 km (135 mi). Perigee: 179 km (111 mi). Inclination: 64.90 deg. Period: 88.40 min. The escape stage entered parking orbit but the main engine cut off just 0.8 s after ignition due to cavitation in the oxidiser pump and pump failure..

• Cosmos 9 - . Payload: Zenit-2 11F61 s/n 7. Mass: 4,700 kg (10,300 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 4.00 days. Decay Date: 1962-10-01 . USAF Sat Cat: 422 . COSPAR: 1962-A-Omega-1. Apogee: 981 km (609 mi). Perigee: 829 km (515 mi). Inclination: 67.60 deg. Period: 103.10 min. Area survey photo reconnaissance satellite. Also performed radiation measurements..

• Cosmos 10 - . Payload: Zenit-2 11F61 s/n 5. Mass: 4,700 kg (10,300 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 4.00 days. Decay Date: 1962-10-21 . USAF Sat Cat: 437 . COSPAR: 1962-B-Zeta-1. Apogee: 376 km (233 mi). Perigee: 178 km (110 mi). Inclination: 64.90 deg. Period: 90.00 min. Area survey photo reconnaissance satellite. Also performed radiation measurements..

• Sputnik 22 - . Payload: 2MV-4 s/n 3. Mass: 6,500 kg (14,300 lb). Nation: Russia. Agency: RVSN. Program: Mars. Class: Mars. Type: Mars probe. Spacecraft Bus: 2MV. Spacecraft: Mars 2MV-4. Decay Date: 1962-10-29 . USAF Sat Cat: 443 . COSPAR: 1962-B-Iota-1. Apogee: 260 km (160 mi). Perigee: 202 km (125 mi). Inclination: 65.10 deg. Period: 89.10 min.

  Mars probe intended to photograph Mars on a flyby trajectory. The spacecraft broke into many pieces, some of which apparently remained in Earth orbit for a few days. This occurred during the Cuban missile crisis and was picked up by U.S. military radar installations, who originally feared it might by the start of a Soviet nuclear attack.

• Mars 1 - . Payload: 2MV-4 s/n 4 / Sputnik 23. Mass: 894 kg (1,970 lb). Nation: Russia. Agency: RVSN. Program: Mars. Class: Mars. Type: Mars probe. Spacecraft Bus: 2MV. Spacecraft: Mars 2MV-4. USAF Sat Cat: 450 . COSPAR: 1962-B-Nu-3.

  Mars probe intended to photograph Mars on a flyby trajectory. Launched from Sputnik 23 in a 157 x 238 km, 65 degree parking orbit. Sixty-one radio transmissions were held in which a large amount of data was collected. On March 21, 1963, when the spacecraft was at a distance of 106 million km communications ceased, possibly due to a malfunction in the spacecraft orientation system. Mars 1 closest approach to Mars occurred on June 19, 1963 at a distance of approximately 193,000 km, after which the spacecraft entered a heliocentric orbit. Announced mission: Prolonged exploration of outer space during flight to the planet Mars; establishment of inter-planetary radio communications; photgraphing of the planet Mars and subsquent radio-transmission to Earth of the photographs of the surface of Mars thus obtained.

• Sputnik 24 - . Payload: 2MV-3 s/n 1. Mass: 890 kg (1,960 lb). Nation: Russia. Agency: RVSN. Program: Mars. Class: Venus. Type: Venus probe. Spacecraft Bus: 2MV. Spacecraft: Mars 2MV-3. Decay Date: 1962-11-05 . USAF Sat Cat: 451 . COSPAR: 1962-B-Xi-1. Apogee: 170 km (100 mi). Perigee: 170 km (100 mi). Inclination: 64.80 deg. Period: 87.90 min.

  Mars probe intended to make a soft landing on Mars. Although the escape stage and payload reached orbit, the strong third stage vibrations shook a fuse loose from its mount in the main nozzle of the escape stage Block L's engine. The engine could not be ignited and remained in Earth orbit. It decayed about two months after insertion.

• Cosmos 12 - . Payload: Zenit-2 11F61 s/n 6. Mass: 4,700 kg (10,300 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1962-12-30 . USAF Sat Cat: 517 . COSPAR: 1962-B-Omega-1. Apogee: 385 km (239 mi). Perigee: 202 km (125 mi). Inclination: 64.80 deg. Period: 90.40 min. Area survey photo reconnaissance satellite. Also performed radiation measurements..

• Sputnik 25 - . Payload: E-6 s/n 1. Mass: 1,422 kg (3,134 lb). Nation: Russia. Agency: Korolev bureau. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1963-01-05 . USAF Sat Cat: 522 . COSPAR: 1963-001B. Apogee: 189 km (117 mi). Perigee: 165 km (102 mi). Inclination: 64.60 deg. Period: 88.00 min.

• Soyuz 'leaves drafting boards' - . Nation: Russia. Program: Lunar L1. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Soyuz. Spacecraft: Soyuz A. Soyuz 'leaves drafting boards'..

• E-6 s/n 2 failure. - . Payload: E-6 s/n 2. Mass: 1,422 kg (3,134 lb). Nation: Russia. Agency: RVSN. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1963-02-03 . Apparent causes were instabilities in the torque sensor circuit and the pitch-free floating gyro device. The upper stages and payload broke up on re-entry into the atmosphere over the Pacific..

• Korolev approves draft plan for 'Soyuz Complex' - . Nation: Russia. Related Persons: Chelomei, Korolev. Program: Lunar L1. Class: Manned. Type: Manned spacecraft. Spacecraft: Soyuz 7K-OK, Soyuz A, Soyuz B, Soyuz V.

  Final design approval for Soyuz A spacecraft for earth orbit and circumlunar flight using orbital rendezvous, docking, and refuelling technques. Except for change of orbital module from cylindrical to spherical design, and changes to rendezvous radar tower arrangement, this design was essentially identical to the Soyuz 7K-OK that flew three years later. Additional Details: here....

• Cosmos 13 - . Payload: Zenit-2 11F61 s/n 9. Mass: 4,700 kg (10,300 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1963-03-29 . USAF Sat Cat: 554 . COSPAR: 1963-006A. Apogee: 303 km (188 mi). Perigee: 214 km (132 mi). Inclination: 65.20 deg. Period: 89.60 min. Area survey photo reconnaissance satellite. Also performed radiation measurements..

• Luna 4 - . Payload: E-6 s/n 3. Mass: 1,422 kg (3,134 lb). Nation: Russia. Agency: RVSN. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1963-04-03 . USAF Sat Cat: 563 . COSPAR: 1963-008A. Apogee: 182 km (113 mi). Perigee: 167 km (103 mi). Inclination: 64.70 deg. Period: 87.98 min.

  Luna 4 was the second attempted Soviet unmanned lunar soft lander probe. The spacecraft, rather than being sent on a straight trajectory toward the Moon, was placed first in an earth parking orbit. The rocket stage then reignited and put the spaccecraft on a translunar trajectory. Failure of Luna 4 to make a required midcourse correction resulted in it missing the Moon by 8336.2 km on April 6, at 4:26 a.m. Moscow time. It thereafter entered a barycentric Earth orbit. The Soviet news agency, Tass, reported that data had been received from the spacecraft throughout its flight and that radio communication would continue for a few more days.

• Combat training launch - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Cosmos 15 - . Payload: Zenit-2 11F61 s/n 8. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 5.00 days. Decay Date: 1963-04-27 . USAF Sat Cat: 569 . COSPAR: 1963-011A. Apogee: 336 km (208 mi). Perigee: 194 km (120 mi). Inclination: 65.00 deg. Period: 89.80 min. Area survey photo reconnaissance satellite. Also carried weather, radiation experiments..

• Cosmos 16 - . Payload: Zenit-2 11F61 s/n 10. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 10.00 days. Decay Date: 1963-05-08 . USAF Sat Cat: 571 . COSPAR: 1963-012A. Apogee: 379 km (235 mi). Perigee: 201 km (124 mi). Inclination: 64.70 deg. Period: 90.30 min. Program partially completed. Part of the information lost due to failure of engine block stabilization system. Area survey photo reconnaissance satellite. Also performed radiation measurements..

• Combat training launch - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Cosmos 18 - . Payload: Zenit-2 11F61 s/n 11. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 9.00 days. Decay Date: 1963-06-02 . USAF Sat Cat: 586 . COSPAR: 1963-018A. Apogee: 269 km (167 mi). Perigee: 212 km (131 mi). Inclination: 64.60 deg. Period: 89.30 min. Area survey photo reconnaissance satellite. Also performed radiation measurements..

• Vostok 5 - . Call Sign: Yastreb (Hawk ). Crew: Bykovsky. Backup Crew: Leonov, Volynov. Payload: Vostok 3KA s/n 7. Mass: 4,720 kg (10,400 lb). Nation: Russia. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 5. Spacecraft: Vostok. Duration: 4.96 days. Decay Date: 1963-06-19 . USAF Sat Cat: 591 . COSPAR: 1963-020A. Apogee: 131 km (81 mi). Perigee: 130 km (80 mi). Inclination: 64.90 deg. Period: 87.10 min.

  Joint flight with Vostok 6. The Soviet Union launched Vostok 5, piloted by Lt. Col. Valery F. Bykovsky. Two days later Lt. Valentina V. Tereshkova, the first spacewoman, followed in Vostok 6. On its first orbit, Vostok 6 came within about five km of Vostok 5, the closest distance achieved during the flight, and established radio contact. Both cosmonauts landed safely on June 19. The space spectacular featured television coverage of Bykovsky that was viewed in the West as well as in Russia. Unlike earlier missions, only a black and white film camera was carried. Photometric measurements of the earth's horizon were made.

  Mission objectives were officially: further study of the effect of various space-flight factors in the human organism; extensive medico-biological experiments under conditions of prolonged flight; further elaboration and improvement of spaceship systems.

  Vostok 5 was originally planned to go for a record eight days. The launch was delayed repeatedly due to high solar activity and technical problems. Finally the spacecraft ended up in a lower than planned orbit. Combined with increased atmospheric activity due to solar levels, Vostok 5 quickly decayed temperatures in the service module reached very high levels.

  Bykovsky also experienced an unspecified problem with his waste management system (a spill?) which made conditions in the cabin 'very uncomfortable'. He was finally ordered to return after only five days in space.

  To top it all off, once again the Vostok service module failed to separate cleanly from the reentry sphere. Wild gyrations ensued until the heat of reentry burned through the non-separating retraining strap.

• Vostok 6 - . Call Sign: Chayka (Seagull ). Crew: Tereshkova. Backup Crew: Ponomaryova, Solovyova. Payload: Vostok 3KA s/n 8. Mass: 4,713 kg (10,390 lb). Nation: Russia. Related Persons: Korolev. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 6. Spacecraft: Vostok. Duration: 2.95 days. Decay Date: 1963-06-19 . USAF Sat Cat: 595 . COSPAR: 1963-023A. Apogee: 166 km (103 mi). Perigee: 165 km (102 mi). Inclination: 64.90 deg. Period: 87.80 min.

  Joint flight with Vostok 5. First woman in space, and the only Russian woman to go into space until Svetlana Savitskaya 19 years later. On its first orbit, Vostok 6 came within about five km of Vostok 5, the closest distance achieved during the flight, and established radio contact. Flight objectives included: Comparative analysis of the effect of various space-flight factors on the male and female organisms; medico-biological research; further elaboration and improvement of spaceship systems under conditions of joint flight. It was Korolev's idea just after Gagarin's flight to put a woman into space as yet another novelty. Khrushchev made the final crew selection. Korolev was unhappy with Tereshkova's performance in orbit and she was not permitted to take manual control of the spacecraft as had been planned.

• Zenit-2 11F61 s/n 12 - . Payload: Zenit-2 11F61 s/n 12. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Decay Date: 1963-07-10 . Area survey photo reconnaissance satellite..

• Combat training launch - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Cosmos 20 - . Payload: Zenit-2 11F61 s/n 13. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1963-10-26 . USAF Sat Cat: 673 . COSPAR: 1963-040A. Apogee: 296 km (183 mi). Perigee: 201 km (124 mi). Inclination: 64.80 deg. Period: 89.40 min. Area survey photo reconnaissance satellite..

• Polet 1; Polyot 1 - . Payload: I-2B s/n 1. Mass: 1,400 kg (3,000 lb). Nation: Russia. Related Persons: Chelomei. Agency: Korolev bureau. Class: Military. Type: Anti-satellite system. Spacecraft Bus: Kosmoplan. Spacecraft: Polyot. Decay Date: 1982-10-16 . USAF Sat Cat: 683 . COSPAR: 1963-043A. Apogee: 1,420 km (880 mi). Perigee: 331 km (205 mi). Inclination: 58.90 deg. Period: 102.40 min.

  ASAT interceptor control and propulsion test. Launched by Korolev R-7 because Chelomei's own UR-200 was not yet available. Purpose - elaboration of system providing for the extensive manoeuvring of space apparatuses. Flight was considered a great success. Micro-engine fired 350 times and main stabilizing engine fired 300 times. Orbit given is final orbit after manoeuvres.

• Cosmos 21 - . Payload: 3MV-1A s/n 1. Mass: 890 kg (1,960 lb). Nation: Russia. Agency: Korolev bureau. Program: Mars. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-1A. Decay Date: 1963-11-14 . USAF Sat Cat: 687 . COSPAR: 1963-044A. Apogee: 231 km (143 mi). Perigee: 192 km (119 mi). Inclination: 64.80 deg. Period: 88.70 min. The stage with payload remained in Earth orbit as Cosmos-51 and burnt up on re-entry..

• Cosmos 22 - . Payload: Zenit-4 no. 1. Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 6.00 days. Decay Date: 1963-11-22 . USAF Sat Cat: 689 . COSPAR: 1963-045A. Apogee: 376 km (233 mi). Perigee: 193 km (119 mi). Inclination: 64.90 deg. Period: 90.20 min. High resolution photo reconnaissance satellite; returned film capsule.

• Zenit-2 11F61 s/n 14 - . Payload: Zenit-2 11F61 s/n 14. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Decay Date: 1963-11-28 . Area survey photo reconnaissance satellite..

• Cosmos 24 - . Payload: Zenit-2 11F61 s/n 15. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 9.00 days. Decay Date: 1963-12-28 . USAF Sat Cat: 712 . COSPAR: 1963-052A. Apogee: 391 km (242 mi). Perigee: 204 km (126 mi). Inclination: 65.00 deg. Period: 90.50 min. Area survey photo reconnaissance satellite..

• Development of Soyuz-R and Soyuz-P begun. - . Nation: Russia. Related Persons: Kozlov. Program: Almaz. Class: Manned. Type: Manned spacecraft. Spacecraft: Soyuz 7K-TK, Soyuz P, Soyuz PPK, Soyuz R.

  KB Kozlov began active development of the military applied versions of the Soyuz. A new version of the R-7 launch vehicle, the 11A514, was put into development to support launch of the Soyuz-P, now designated the 7K-PPK (pilotiruemovo korablya-perekhvatchika, manned interceptor spacecraft). The Soyuz-R would include the small orbital station 11F71 with photo-reconnaissance and ELINT equipment. To dock with the 11F71 station Kuibishev developed the transport spacecraft 11F72 7K-TK. This version of the Soyuz was equipped with rendezvous, docking, and transition equipment, including an airlock, that allowed the two cosmonauts to enter the station without using EVA. The launch vehicle for the 7K-TK would be the 11A511, known today as the Soyuz.

• Elektron 1 - . Payload: 2D s/n 1. Mass: 329 kg (725 lb). Nation: Russia. Agency: Korolev bureau. Program: Elektron. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Elektron-A. USAF Sat Cat: 746 . COSPAR: 1964-006A. Apogee: 6,439 km (4,001 mi). Perigee: 413 km (256 mi). Inclination: 60.90 deg. Period: 161.00 min.

  Studied inner Van Allen belt. Electron I and II launched by a single carrier rocket. Electron I: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and upper atmosphere. Electron II: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and outer space.

• Elektron 2 - . Payload: 2D s/n 2. Mass: 444 kg (978 lb). Nation: Russia. Agency: Korolev bureau. Program: Elektron. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Elektron-B. Decay Date: 1997-04-22 . USAF Sat Cat: 748 . COSPAR: 1964-006B. Apogee: 62,811 km (39,028 mi). Perigee: 5,611 km (3,486 mi). Inclination: 60.20 deg. Period: 1,356.40 min.

  Studied outer Van Allen belt. Electron I and II launched by a single carrier rocket. Electron I: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and upper atmosphere. Electron II: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and outer space.

• 3MV-1A - . Payload: 3MV-1A s/n 2. Mass: 890 kg (1,960 lb). Nation: Russia. Agency: RVSN. Program: Mars. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-1A. Decay Date: 1964-02-19 .

• 3MV-1 No. 2 SA - . Mass: 890 kg (1,960 lb). Nation: Russia. Agency: RVSN. Program: Mars. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-1.

• Venus launch delayed. - . Payload: 3MV-1. Nation: Russia. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-1. Decay Date: 1964-03-01 . The launch was delayed due to malfunctions during prelaunch service..

• Zenit-2 spy satellite accepted into mlitary service - . Nation: Russia. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Defence Ministry of the USSR decree 0045 'On adopting the Zenit-2 satellite launched on the 8A92 into armaments' was issued..

• Luna failure - . Payload: E-6 s/n 4. Mass: 1,422 kg (3,134 lb). Nation: Russia. Agency: RVSN. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1964-03-21 . The upper stages burnt on re-entry into the atmosphere..

• Cosmos 27 - . Payload: 3MV-1 s/n 3. Mass: 890 kg (1,960 lb). Nation: Russia. Agency: Korolev bureau. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-1. Decay Date: 1964-03-29 . USAF Sat Cat: 772 . COSPAR: 1964-014A. Apogee: 209 km (129 mi). Perigee: 197 km (122 mi). Inclination: 64.80 deg. Period: 88.50 min. The stage with payload remained in Earth orbit as Cosmos-27..

• Zond 1 - . Payload: 3MV-1 s/n 4. Mass: 890 kg (1,960 lb). Nation: Russia. Agency: Korolev bureau. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-1. USAF Sat Cat: 785 . COSPAR: 1964-016D. Failed Venus probe. Solar Orbit (Heliocentric). Elaboration of a long range space system and conduct of scientific research..

• Cosmos 28 - . Payload: Zenit-2 11F61 s/n 16. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1964-04-12 . USAF Sat Cat: 779 . COSPAR: 1964-017A. Apogee: 373 km (231 mi). Perigee: 213 km (132 mi). Inclination: 65.00 deg. Period: 90.40 min. Area survey photo reconnaissance satellite..

• Polet 2; Polyot 2 - . Payload: I-2B s/n 2. Mass: 1,400 kg (3,000 lb). Nation: Russia. Agency: Korolev bureau. Class: Military. Type: Anti-satellite system. Spacecraft Bus: Kosmoplan. Spacecraft: Polyot. Decay Date: 1966-06-08 . USAF Sat Cat: 783 . COSPAR: 1964-019A. Apogee: 479 km (297 mi). Perigee: 303 km (188 mi). Inclination: 58.10 deg. Period: 92.30 min. ASAT interceptor control and propulsion test. Elaboration of systems providing for the extensive manouevring of space apparatuses..

• Luna failure - . Payload: E-6 s/n 5. Mass: 1,422 kg (3,134 lb). Nation: Russia. Agency: RVSN. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1964-04-20 . The upper stages broke up on re-entry into the atmosphere...

• Cosmos 29 - . Payload: Zenit-2 11F61 s/n 19. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 7.00 days. Decay Date: 1964-05-02 . USAF Sat Cat: 791 . COSPAR: 1964-021A. Apogee: 292 km (181 mi). Perigee: 203 km (126 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite..

• Cosmos 30 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1964-05-26 . USAF Sat Cat: 797 . COSPAR: 1964-023A. Apogee: 366 km (227 mi). Perigee: 206 km (128 mi). Inclination: 64.90 deg. Period: 90.30 min. High resolution photo reconnaissance satellite; returned film capsule.

• Test? - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Molniya-1 s/n 2 Failure - . Payload: Molniya-1 s/n 2. Mass: 1,600 kg (3,500 lb). Nation: Russia. Agency: RVSN. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft Bus: KAUR-2. Spacecraft: Molniya-1. Unsuccessful first attempt to launch Molniya communications satellite..

• Cosmos 32 - . Payload: Zenit-2 11F61 s/n 18. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1964-06-18 . USAF Sat Cat: 807 . COSPAR: 1964-029A. Apogee: 322 km (200 mi). Perigee: 205 km (127 mi). Inclination: 51.30 deg. Period: 89.80 min. Area survey photo reconnaissance satellite..

• Cosmos 33 - . Payload: Zenit-2 11F61 s/n 20. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1964-07-01 . USAF Sat Cat: 816 . COSPAR: 1964-033A. Apogee: 279 km (173 mi). Perigee: 205 km (127 mi). Inclination: 64.90 deg. Period: 89.40 min. Area survey photo reconnaissance satellite..

• Cosmos 34 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1964-07-09 . USAF Sat Cat: 822 . COSPAR: 1964-034A. Apogee: 342 km (212 mi). Perigee: 201 km (124 mi). Inclination: 64.90 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule.

• Elektron 3 - . Payload: 2D s/n 3. Mass: 350 kg (770 lb). Nation: Russia. Agency: Korolev bureau. Program: Elektron. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Elektron-A. USAF Sat Cat: 829 . COSPAR: 1964-038A. Apogee: 6,302 km (3,915 mi). Perigee: 408 km (253 mi). Inclination: 60.90 deg. Period: 159.30 min. Studied inner Van Allen belt. Electron 3 and 4 launched by a single carrier rocket. Simultaneous study of the inner and outer radiation belts of the earth, cosmic rays and the upper atmosphere. .

• Elektron 4 - . Payload: 2D s/n 4. Mass: 444 kg (978 lb). Nation: Russia. Agency: Korolev bureau. Program: Elektron. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Elektron-B. Decay Date: 1983-10-12 . USAF Sat Cat: 830 . COSPAR: 1964-038B. Apogee: 66,269 km (41,177 mi). Perigee: 447 km (277 mi). Inclination: 60.80 deg. Period: 1,313.80 min. Studied outer Van Allen belt. Electron 3 and 4 launched by a single carrier rocket. Simultaneous study of the inner and outer radiation belts of the earth, cosmic rays and the upper atmosphere. .

• Cosmos 35 - . Payload: Zenit-2 11F61 s/n 21. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1964-07-23 . USAF Sat Cat: 833 . COSPAR: 1964-039A. Apogee: 258 km (160 mi). Perigee: 218 km (135 mi). Inclination: 51.30 deg. Period: 89.20 min. Area survey photo reconnaissance satellite..

• Test? - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Cosmos 37 - . Payload: Zenit-2 11F61 s/n 22. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1964-08-22 . USAF Sat Cat: 848 . COSPAR: 1964-044A. Apogee: 240 km (140 mi). Perigee: 208 km (129 mi). Inclination: 64.90 deg. Period: 88.90 min. Area survey photo reconnaissance satellite. Program partially completed. Break in the film fof the SA-10 camera..

• Cosmos 41 - . Payload: Molniya-1. Mass: 1,500 kg (3,300 lb). Nation: Russia. Agency: Korolev bureau. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft Bus: KAUR-2. Spacecraft: Molniya-1. Decay Date: 2004-04-09 . USAF Sat Cat: 869 . COSPAR: 1964-049D. Apogee: 39,169 km (24,338 mi). Perigee: 1,023 km (635 mi). Inclination: 68.40 deg. Period: 714.50 min.

  Successful launch of first Soviet communications satellite. This is the second Molniya launch attempt. (the first was a launch failure). The failure of the antennae to deploy means the spacecraft can only be tested in a limited manner and cannot be used for the planned relay of television.

• Cosmos 44 - . Payload: Meteor no. 1. Mass: 4,730 kg (10,420 lb). Nation: Russia. Agency: Korolev bureau. Class: Earth. Type: Weather satellite. Spacecraft: Meteor. USAF Sat Cat: 876 . COSPAR: 1964-053A. Apogee: 778 km (483 mi). Perigee: 599 km (372 mi). Inclination: 65.10 deg. Period: 98.50 min. Investigation of the upper atmosphere and outer space. .

• Voskhod preparations - . Nation: Russia. Related Persons: Korolev, Krylov, Rudenko. Program: Voskhod. Flight: Voskhod 1. Spacecraft: Voskhod, Zenit-4.

  Kamanin arrives at the cosmodrome, only to find the launch of the manned Voskhod delayed to October. The launch of a Zenit-4 spy satellite, that uses the same launch vehicle as planned for Voskhod, has aborted on the pad after the Block A strap-on failed to ignite. This is the first block A failure in over 100 R-7 launches. That evening Kamanin views a launch of an R-36 heavy ICBM. Marshall Krylov reveals it will have a range of 14,000 km with a CEP of under 1 km with a 40 megaton warhead - one missile is sufficient to wipe out a city like New York. Rudenko believes that the victor in any nuclear war will be the one who pushes the button first. Krylov disagrees, saying that if the Americans would launch an attack on Soviet missile forces, the Soviet Union would launch its missiles on a counter-strike before the American missiles arrive - total and senseless destruction. Rudenko believes that Rudenko is more correct, since in the real-world responses will not conform to theoretical possibilities of instant reaction.

  Later the state commission meets to consider the launch of the first Voskhod. The unpleasantness at the landing trials in the Crimea reveal only the inadequacy of the design of the test capsules, and do not reflect the flight system, says Korolev. He certifies the reliability of the Voskhod for flight. The commission decides to set the launch of the next Zenit-4 reconnaissance satellite for 14 September; that of the Voskhod with mannequins on 18-20 September; the definitive landing system trial at Fedosiya on 23 September; and if that is successful, launch of a manned Voskhod by the end of September.

• Cosmos 45 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Related Persons: Korolev. Agency: Korolev bureau. Program: Voskhod. Class: Surveillance. Type: Military surveillance satellite. Flight: Voskhod 1. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 5.00 days. Decay Date: 1964-09-18 . USAF Sat Cat: 880 . COSPAR: 1964-055A. Apogee: 311 km (193 mi). Perigee: 203 km (126 mi). Inclination: 64.90 deg. Period: 89.60 min.

  High resolution photo reconnaissance satellite; returned film capsule; also carried weather experiments. The Zenit-4 launches a day ahead of schedule. The booster rocket performs perfectly as Korolev and Kamanin watch from the veranda of the IP-1 tracking station. This confirms readiness of the same launch vehicle for the Voskhod launch.

• Cosmos 46 - . Payload: Zenit-2 11F61 s/n 23. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1964-10-02 . USAF Sat Cat: 885 . COSPAR: 1964-059A. Apogee: 264 km (164 mi). Perigee: 211 km (131 mi). Inclination: 51.30 deg. Period: 89.20 min. Area survey photo reconnaissance satellite. Demonstration launch witnessed by Khrushchev..

• Cosmos 47 - . Payload: Voskhod 3KV s/n 2. Mass: 5,320 kg (11,720 lb). Nation: Russia. Related Persons: Kirillov, Korolev, Rudenko, Tyulin. Agency: Korolev bureau. Program: Voskhod. Class: Manned. Type: Manned spacecraft. Flight: Voskhod 1. Spacecraft Bus: Vostok. Spacecraft: Voskhod. Duration: 1.01 days. Decay Date: 1964-10-07 . USAF Sat Cat: 891 . COSPAR: 1964-062A. Apogee: 383 km (237 mi). Perigee: 174 km (108 mi). Inclination: 64.60 deg. Period: 90.10 min.

  Unmanned test of Voskhod spacecraft. At 07:00 the State Commission meets at Area 2. All Chief Designers, Commanders, and Section report that all is ready for flight. The commission gives the order to proceed with the launch. Weather at the pad is 7 balls, 8-10 m/s wind with gusts to 15 m/s, temperature 9 to 12 deg C. Weather in the recovery zones is reported as winds up to 15 m/s. Weather in the recovery zone is not clear, but that is not considered an impediment, and in fact Kamanin would like to see how the landing system functions in bad conditions. Kamanin visits the pad at T-30 seconds; at T-20 seconds, the veranda at IP-1 has over 50 viewers of the launch, including 15 cosmonaut candidates and the 7 Voskhod cosmonauts. Kamanin is relegated to the IP-1 veranda this time, with Rudenko, Kirillov, and Tyulin the bunker adjacent to the pad. Korolev stays with the booster until T-5 minutes, then enters the bunker. The booster ignites precisely at 10:00; the strap-ons burn out and are jettisoned at T+120 seconds; the core burns out and the final stage ignites at T+290 seconds; and at T+523 seconds spacecraft 3KV number 2 is placed in orbit as the final stage shuts down. The spacecraft separates and all systems look normal.

  Recovered October 7, 1964 7:28 GMT. Officially: Investigation of the upper atmosphere and outer space.

• Cosmos 47 returns to earth. - . Nation: Russia. Program: Voskhod. Flight: Voskhod 1. Spacecraft Bus: Vostok. Spacecraft: Voskhod.

  At 7 am the Cosmos 47 landing commission convenes. Kamanin has had only three hours sleep. The spacecraft is to conduct retrofire on its 17th orbit of the earth and land in Kustan, where winds are 15-17 m/s. The capsule made a good landing, with the parachute-rocket soft landing system working perfectly - the spacecraft had zero velocity on impact with the ground. The spacecraft penetrated 90 mm into the ground. The strong winds caught the parachute after landing and dragged it 160 m, but if a crew had been aboard they could have quickly commanded separation of the parachute. All systems of the booster and spacecraft worked perfectly, except that the third stage engines' thrust fell by 10% for three seconds, but the engine controller detected the shortfall and made up the velocity.

• Cosmos 47 capsule returned to Baikonur. - . Nation: Russia. Related Persons: Kosberg. Program: Voskhod. Flight: Voskhod 1. Spacecraft Bus: Vostok. Spacecraft: Voskhod.

  The capsule arrived aboard an An-12 at 11:30. All systems performed well. It is reported that one of Kosberg's third stage engines developed an out-of-control high frequency oscillation in a stand test, and exploded. The State Commission decides to delay the manned Voskhod launch 3 or 4 days while the safety of the engines on the booster are verified. A special commission is sent to Voronezh to assess the situation. Kosberg's engines have flown 60 times, and been tested on the stand 400 times, without this problem having occurred before. In the evening seven reporters arrive from the Soviet press and begin their work leading up to the manned launch.

• Voskhod 1 - . Call Sign: Rubin (Ruby ). Crew: Feoktistov, Komarov, Yegorov. Backup Crew: Katys, Lazarev, Volynov. Payload: Voskhod 3KV s/n 3. Mass: 5,320 kg (11,720 lb). Nation: Russia. Related Persons: Gagarin, Korolev, Rudenko, Tyulin. Program: Voskhod. Class: Manned. Type: Manned spacecraft. Flight: Voskhod 1. Spacecraft Bus: Vostok. Spacecraft: Voskhod. Duration: 1.01 days. Decay Date: 1964-10-13 . USAF Sat Cat: 904 . COSPAR: 1964-065A. Apogee: 336 km (208 mi). Perigee: 178 km (110 mi). Inclination: 64.70 deg. Period: 89.60 min.

  The U.S.S.R. launched the world's first multi-manned spacecraft, Voskhod I, the first to carry a scientist and a physician into space. The crew were Col. Vladimir Komarov, pilot; Konstantin Feoktistov, scientist; and Boris Yegorov, physician. Potentially dangerous modification of Vostok to upstage American Gemini flights; no spacesuits, ejection seats, or escape tower. One concession was backup solid retrorocket package mounted on nose of spacecraft. Seats mounted perpendicular to Vostok ejection seat position, so crew had to crane their necks to read instruments, still mounted in their original orientation. Tested the new multi-seat space ship; investigated the in-flight work potential and co-operation of a group of cosmonauts consisting of specialists in different branches of science and technology; conducted scientific physico-technical and medico-biological research. The mission featured television pictures of the crew from space.

  Coming before the two-man Gemini flights, Voskhod 1 had a significant worldwide impact. In the United States, the "space race" was again running under the green flag. NASA Administrator James E. Webb, commenting on the spectacular, called it a "significant space accomplishment." It was, he said, "a clear indication that the Russians are continuing a large space program for the achievement of national power and prestige." Additional Details: here....

• Cosmos 48 - . Payload: Zenit-2 11F61 s/n 24. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 6.00 days. Decay Date: 1964-10-20 . USAF Sat Cat: 908 . COSPAR: 1964-066A. Apogee: 284 km (176 mi). Perigee: 204 km (126 mi). Inclination: 65.10 deg. Period: 89.30 min. Area survey photo reconnaissance satellite. Program partially completed. Returned early due to failure of spacecraft thermoregulation system; internal temperature rose to 43 degrees C..

• Cosmos 50 - . Payload: Zenit-2 11F61 s/n 25. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1964-11-05 . USAF Sat Cat: 919 . COSPAR: 1964-070A. Apogee: 232 km (144 mi). Perigee: 190 km (110 mi). Inclination: 51.20 deg. Period: 88.70 min. Area survey photo reconnaissance satellite. Unsuccessful mission. Failure of the braking engine system. Spacecraft ordered to self destruct..

• Zond 2 - . Payload: 3MV-4A s/n 2. Mass: 890 kg (1,960 lb). Nation: Russia. Agency: Korolev bureau. Program: Mars. Class: Mars. Type: Mars probe. Spacecraft Bus: 3MV. Spacecraft: Mars 3MV-4A. USAF Sat Cat: 945 . COSPAR: 1964-078C.

  Mars probe intended to photograph Mars on a flyby trajectory. Zond 2 was launched from an earth parking orbit towards Mars to test space-borne systems and to carry out scientific investigations. Zond 2 carried six electric rocket engines of plasma type that served as actuators of the attitude control system. The communications system failed during April 1965. The spacecraft flew by Mars on August 6, 1965, at a distance of 1500 km.

• Cosmos 52 - . Payload: Zenit-2 11F61 s/n 26. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: Korolev bureau. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1965-01-19 . USAF Sat Cat: 968 . COSPAR: 1965-001A. Apogee: 298 km (185 mi). Perigee: 203 km (126 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite..

• Cosmos 57 roll-out - . Nation: Russia. Program: Voskhod. Flight: Voskhod 2. Spacecraft Bus: Vostok. Spacecraft: Voskhod. The booster is rolled out to the pad at 08:00, slightly behind schedule after delays in mating the spacecraft the day before. It is -22 deg C at the launch centre; conditions at the landing site are poor, but his will not delay the launch. .

• Cosmos 57 - . Payload: Voskhod 3KD s/n 1. Mass: 5,682 kg (12,526 lb). Nation: Russia. Related Persons: Korolev. Agency: Korolev bureau. Program: Voskhod. Class: Manned. Type: Manned spacecraft. Flight: Voskhod 2. Spacecraft Bus: Vostok. Spacecraft: Voskhod. Duration: 0.22 days. Decay Date: 1965-02-22 . USAF Sat Cat: 1093 . COSPAR: 1965-012A. Apogee: 708 km (439 mi). Perigee: 159 km (98 mi). Inclination: 64.80 deg. Period: 93.20 min.

  Unsuccessful mission. Voskhod 2 test. Immediately after orbital insertion airlock and spacesuit inflated normally. Then two ground control stations sent commands to the spacecraft simultaneously. The combined signals accidentally set off the retrofire sequence, which some time later triggered the self destruct mechanism (designed to prevent the spacecraft from falling into enemy hands).
  Officially: Investigation of the upper atmosphere and outer space. Additional Details: here....

• Cosmos 58 - . Payload: Meteor no. 2. Mass: 4,730 kg (10,420 lb). Nation: Russia. Agency: Korolev bureau. Class: Earth. Type: Weather satellite. Spacecraft: Meteor. Decay Date: 1990-02-25 . USAF Sat Cat: 1097 . COSPAR: 1965-014A. Apogee: 345 km (214 mi). Perigee: 333 km (206 mi). Inclination: 65.00 deg. Period: 91.30 min. Probable weather satellite. Investigation of the upper atmosphere and outer space. .

• Cosmos 59 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-03-15 . USAF Sat Cat: 1191 . COSPAR: 1965-015A. Apogee: 321 km (199 mi). Perigee: 205 km (127 mi). Inclination: 64.90 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule fitted with airlock mating ring planned for Voskhod-2 spacecraft..

• Cosmos 60 - . Payload: E-6 s/n 9. Mass: 6,530 kg (14,390 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1965-03-17 . USAF Sat Cat: 1246 . COSPAR: 1965-018A. Apogee: 248 km (154 mi). Perigee: 195 km (121 mi). Inclination: 64.70 deg. Period: 88.90 min. The stage with the payload remained in Earth orbit as Kosmos-60..

• Voskhod 2 - . Call Sign: Almaz (Diamond ). Crew: Belyayev, Leonov. Backup Crew: Gorbatko, Khrunov, Zaikin. Payload: Voskhod 3KD s/n 4. Mass: 5,682 kg (12,526 lb). Nation: Russia. Related Persons: Gagarin, Korolev, Rudenko, Tyulin. Agency: MOM. Program: Voskhod. Class: Manned. Type: Manned spacecraft. Flight: Voskhod 2. Spacecraft Bus: Vostok. Spacecraft: Voskhod. Duration: 1.08 days. Decay Date: 1965-03-19 . USAF Sat Cat: 1274 . COSPAR: 1965-022A. Apogee: 475 km (295 mi). Perigee: 167 km (103 mi). Inclination: 64.80 deg. Period: 90.90 min.

  First spacewalk, with a two man crew of Colonel Pavel Belyayev and Lt. Colonel Aleksey Leonov. During Voskhod 2's second orbit, Leonov stepped from the vehicle and performed mankind's first "walk in space." After 10 min of extravehicular activity, he returned safely to the spacecraft through an inflatable airlock.

  This mission was originally named 'Vykhod ('Exit/Advance'). It almost ended in disaster when Leonov was unable to reenter the airlock due to stiffness of the inflated spacesuit. He had to bleed air from the suit in order to get into the airlock. After Leonov finally managed to get back into the spacecraft cabin, the primary hatch would not seal completely. The environmental control system compensated by flooding the cabin with oxygen, creating a serious fire hazard in a craft only qualified for sea level nitrogen-oxygen gas mixes (Cosmonaut Bondarenko had burned to death in a ground accident in such circumstances, preceding the Apollo 204 disaster by many years). Additional Details: here....

• Cosmos 64 - . Payload: Zenit-2 11F61 s/n 17. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1965-04-02 . USAF Sat Cat: 1305 . COSPAR: 1965-025A. Apogee: 250 km (150 mi). Perigee: 205 km (127 mi). Inclination: 65.00 deg. Period: 89.10 min. Area survey photo reconnaissance satellite..

• Luna failure - stage 3 engine failure. - . Payload: E-6 s/n 8. Mass: 1,422 kg (3,134 lb). Nation: Russia. Agency: RVSN. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1965-04-10 . The upper stages fell apart on re-entry into the atmosphere...

• Cosmos 65 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-04-25 . USAF Sat Cat: 1320 . COSPAR: 1965-029A. Apogee: 315 km (195 mi). Perigee: 207 km (128 mi). Inclination: 65.00 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule; also carried weather experiments..

• Molniya 1-01 - . Payload: Molniya-1. Mass: 1,600 kg (3,500 lb). Nation: Russia. Agency: MOM. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft Bus: KAUR-2. Spacecraft: Molniya-1. Decay Date: 1979-08-16 . USAF Sat Cat: 1324 . COSPAR: 1965-030A. Apogee: 39,300 km (24,400 mi). Perigee: 538 km (334 mi). Inclination: 65.50 deg. Period: 707.30 min. First announced launch of Soviet communications satellite. Television programme transmission and long range two way multi channel telephone and telegraph communications. Orbital characteristics after correction of 2 May 1965..

• Cosmos 66 - . Payload: Zenit-2 11F61 s/n 27. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1965-05-15 . USAF Sat Cat: 1362 . COSPAR: 1965-035A. Apogee: 397 km (246 mi). Perigee: 285 km (177 mi). Inclination: 64.90 deg. Period: 91.30 min. Returned after 8 days. Unsuccessful mission. Parachute deployment failure. Spacecraft destroyed in crash..

• Luna 5 - . Payload: E-6 s/n 10. Mass: 1,474 kg (3,249 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1965-05-12 . USAF Sat Cat: 1366 . COSPAR: 1965-036A. Apogee: 219 km (136 mi). Perigee: 159 km (98 mi). Inclination: 64.80 deg. Period: 88.27 min.

  Soft lunar landing attempt. Western observers, among them England's Sir Bernard Lovell, correctly speculated that the craft's mission was a soft landing. After launch fom Baikonur and five successful communications sessions the spacecraft performed a midcourse correction maneuver on 10 May. Unfortunately a problem developed in a flotation gyroscope (it did not have enough time to warm up properly) in the I-100 guidance control unit and control was lost so the spacecraft began spinning around its main axis. It was brought back under control, but at the time of the next maneuver, the main retrorocket system failed due to a ground control error in calculating the setpoints, and the spacecraft, though still headed for the Moon, was far off its intended landing site. Problems again cropped up with the I-100 unit so a retrorocket burn could not take place and Luna 5 impacted the lunar surface some 700 km from the target point at about 19:10 UT on 12 May 1965, becoming the second Soviet probe to hit the Moon. A Soviet announcement gave the impact point as the Sea of Clouds at roughly 31 degrees S, 8 degrees W. (Although a later analysis gave a very different estimate of 8 degrees N, 23 degrees W.)

• Cosmos 67 - . Payload: Zenit-4. Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-06-02 . USAF Sat Cat: 1382 . COSPAR: 1965-040A. Apogee: 351 km (218 mi). Perigee: 203 km (126 mi). Inclination: 51.80 deg. Period: 90.10 min. High resolution photo reconnaissance satellite; returned film capsule.

• Luna 6 - . Payload: E-6 s/n 7. Mass: 1,440 kg (3,170 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. USAF Sat Cat: 1393 . COSPAR: 1965-044A.

  Attempted unmanned lunar soft lander. Tass reported that all onboard equipment was functioning normally. During the mid-course correction on 9 June the main retro-rocket failed to cut off as scheduled and fired until all of its propellant was exhausted, due to an erroneous ground command sent to the timer. This put the spacecraft on a trajectory to miss the Moon. The spacecraft was put through all the motions of an actual landing, jettisoning the lander and deploying the airbags, as an apparently successful practice run for the ground crew despite the fact that it flew by the Moon at a distance of 161,000 km on 11 June. Contact was lost at a distance of 600,000 km from Earth, the spacecraft presumably entering a heliocentric orbit.

• Cosmos 68 - . Payload: Zenit-2 11F61 s/n 29. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1965-06-23 . USAF Sat Cat: 1404 . COSPAR: 1965-046A. Apogee: 306 km (190 mi). Perigee: 208 km (129 mi). Inclination: 65.00 deg. Period: 89.70 min. Area survey photo reconnaissance satellite..

• Cosmos 69 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-07-03 . USAF Sat Cat: 1421 . COSPAR: 1965-049A. Apogee: 310 km (190 mi). Perigee: 206 km (128 mi). Inclination: 64.90 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule.

• Zenit-2 11F61 s/n 28 - . Payload: Zenit-2 11F61 s/n 28. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Decay Date: 1965-07-13 . Area survey photo reconnaissance satellite..

• Zond 3 - . Payload: 3MV-4A s/n 3. Mass: 959 kg (2,114 lb). Nation: Russia. Agency: MOM. Program: Mars. Class: Mars. Type: Mars probe. Spacecraft Bus: 3MV. Spacecraft: Mars 3MV-4A. USAF Sat Cat: 1454 . COSPAR: 1965-056A.

  Zond 3 was towards the moon and interplanetary space. The spacecraft was equipped with a TV system that provided automatic inflight film processing. On July 20, during lunar flyby, 25 pictures of very good quality were taken of the lunar farside from distances of 11,570 to 9960 km. The photos covered 19,000,000 km square of the lunar surface. Photo transmissions by facsimile were returned to earth from a distance of 2,200,000 km on July 29 and were retransmitted later from a distance of 31,500,000 km, thus proving the ability of the communications system. After the lunar flyby, Zond 3 continued space exploration in a heliocentric orbit. Those pictures showed clearly the heavily cratered nature of the surface. This mission dramatized the advances in space photography that the U.S.S.R. had made since its first far-side effort six years earlier.

• Cosmos 77 - . Payload: Zenit-4. Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-08-11 . USAF Sat Cat: 1469 . COSPAR: 1965-061A. Apogee: 281 km (174 mi). Perigee: 200 km (120 mi). Inclination: 51.80 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule.

• Cosmos 78 - . Payload: Zenit-2 11F61 s/n 30. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1965-08-22 . USAF Sat Cat: 1505 . COSPAR: 1965-066A. Apogee: 379 km (235 mi). Perigee: 330 km (200 mi). Inclination: 69.00 deg. Period: 91.60 min. Area survey photo reconnaissance satellite..

• Cosmos 79 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-09-02 . USAF Sat Cat: 1523 . COSPAR: 1965-069A. Apogee: 338 km (210 mi). Perigee: 206 km (128 mi). Inclination: 64.90 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule.

• E-6 Launch Postponement - . Payload: E-6. Nation: Russia. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. The launch was delayed due to malfunction of the RKS system of the Stages 1/2's control system during pre-launch service..

• Cosmos 85 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-09-17 . USAF Sat Cat: 1578 . COSPAR: 1965-071A. Apogee: 291 km (180 mi). Perigee: 202 km (125 mi). Inclination: 64.90 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule.

• Cosmos 91 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-10-01 . USAF Sat Cat: 1603 . COSPAR: 1965-075A. Apogee: 324 km (201 mi). Perigee: 203 km (126 mi). Inclination: 65.00 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule.

• Luna 7 - . Payload: E-6 s/n 11. Mass: 1,504 kg (3,315 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1965-10-07 . USAF Sat Cat: 1610 . COSPAR: 1965-077A.

  Lunar soft landing attempt. The Luna 7 spacecraft was intended to achieve a soft landing on the Moon. However, due to loss of attitude control during the final approach to the lunar surface, the retrorockets were prevented from firing to slow the spacecraft and it impacted the lunar surface at 9.8 N, 47.8 W in the Sea of Storms on 7 October 1965 at 22:08:24 UT.

• Molniya 1-02 - . Payload: Molniya-1. Mass: 1,600 kg (3,500 lb). Nation: Russia. Agency: MOM. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft Bus: KAUR-2. Spacecraft: Molniya-1. Decay Date: 1967-03-17 . USAF Sat Cat: 1621 . COSPAR: 1965-080A. Apogee: 39,921 km (24,805 mi). Perigee: 487 km (302 mi). Inclination: 65.20 deg. Period: 718.80 min. France - USSR communications link. Second communications satellite 'Molniya-1'. Television programme transmission and long-range, two-way multi-channel telephone, phototelegraph and telegraph communications..

• Cosmos 92 - . Payload: Bion precursor. Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-10-24 . USAF Sat Cat: 1626 . COSPAR: 1965-083A. Apogee: 331 km (205 mi). Perigee: 204 km (126 mi). Inclination: 64.90 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule; also carried weather and biological experiments..

• Cosmos 94 - . Payload: Bion precursor. Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1965-11-05 . USAF Sat Cat: 1636 . COSPAR: 1965-085A. Apogee: 271 km (168 mi). Perigee: 205 km (127 mi). Inclination: 65.00 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule; also carried biological experiments..

• Venera 2 - . Payload: 3MV-4 s/n 4. Mass: 962 kg (2,120 lb). Nation: Russia. Agency: MOM. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-4. USAF Sat Cat: 1730 . COSPAR: 1965-091A. Apogee: 315 km (195 mi). Perigee: 205 km (127 mi). Inclination: 51.80 deg. Period: 89.71 min.

  Venera 2 was launched towards the planet Venus and carried a TV system and scientific instruments. On February 27, 1966, the spacecraft passed Venus at a distance of 24,000 km and entered a heliocentric orbit. The spacecraft system had ceased to operate before the planet was reached and returned no data.

• Venera 3 - . Payload: 3MV-3 s/n 1. Mass: 958 kg (2,112 lb). Nation: Russia. Agency: MOM. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-3. Decay Date: 1966-03-01 . USAF Sat Cat: 1733 . COSPAR: 1965-092A.

  Venera 3 was launched towards the planet Venus. The mission was to land on the Venusian surface. The entry vehicle contained a radio communication system, scientific instruments, electrical power sources, and medallions bearing the coat of arms of the U.S.S.R. The station impacted Venus on March 1, 1966. However, the communications systems had failed before planetary data could be returned.

• Cosmos 96 - . Payload: 3MV-4 s/n 6. Mass: 960 kg (2,110 lb). Nation: Russia. Agency: MOM. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-4. Decay Date: 1965-12-09 . USAF Sat Cat: 1742 . COSPAR: 1965-094A. Apogee: 296 km (183 mi). Perigee: 222 km (137 mi). Inclination: 51.90 deg. Period: 89.70 min. The escape stage Block L entered parking orbit tumbling and was not able to operate properly..

• Venus launch delayed. - . Payload: 3MV-3. Nation: Russia. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft Bus: 3MV. Spacecraft: Venera 3MV-3. Decay Date: 1965-11-26 . The launch attempt was abandoned due to a launch vehicle malfunction during pre-launch preparations..

• Cosmos 98 - . Payload: Zenit-2 11F61 s/n 31. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1965-12-05 . USAF Sat Cat: 1780 . COSPAR: 1965-097A. Apogee: 547 km (339 mi). Perigee: 205 km (127 mi). Inclination: 65.00 deg. Period: 92.10 min. Area survey photo reconnaissance satellite..

• Luna 8 - . Payload: E-6 s/n 12. Mass: 1,550 kg (3,410 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1965-12-06 . USAF Sat Cat: 1810 . COSPAR: 1965-099A.

  Lunar soft landing attempt failed. Luna 8's objectives were to test a soft lunar landing system and scientific research. Weighing 1,552 kg (3,422 lbs), the spacecraft was following a trajectory close to the calculated one and the equipment was functioning normally. However, a puncture to a cushioning airbag caused the spacecraft to spin, losing attitude control and preventing full firing of the retrorockets. The spacecraft impacted the lunar surface at 9.1 N, 63.3 W in the Sea of Storms at 21:51:30 UT on 6 December 1965. The mission did complete the experimental development of the star-orientation system and ground control of radio equipment, flight trajectory, and other instrumentation.

• Cosmos 99 - . Payload: Zenit-2 11F61 s/n 32. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1965-12-18 . USAF Sat Cat: 1817 . COSPAR: 1965-103A. Apogee: 309 km (192 mi). Perigee: 203 km (126 mi). Inclination: 65.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite..

• Test mission - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Cosmos 100 - . Payload: Meteor no. 3. Mass: 4,730 kg (10,420 lb). Nation: Russia. Agency: MOM. Class: Earth. Type: Weather satellite. Spacecraft: Meteor. Decay Date: 2002-02-15 . USAF Sat Cat: 1843 . COSPAR: 1965-106A. Apogee: 547 km (339 mi). Perigee: 485 km (301 mi). Inclination: 65.00 deg. Period: 95.00 min. Probable weather satellite. Investigation of the upper atmosphere and outer space. .

• Test mission - . Nation: Russia. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Cosmos 102 - . Mass: 3,800 kg (8,300 lb). Nation: Russia. Agency: MOM. Program: RORSAT. Class: Surveillance. Type: Naval Radarsat. Spacecraft Bus: Kosmoplan. Spacecraft: US-A. Decay Date: 1966-01-13 . USAF Sat Cat: 1867 . COSPAR: 1965-111A. Apogee: 267 km (165 mi). Perigee: 205 km (127 mi). Inclination: 64.90 deg. Period: 89.20 min. Prototype RORSAT hardware using chemical batteries in place of nuclear reactor..

• Cosmos 104 - . Payload: Zenit-2 11F61 s/n 36. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1966-01-15 . USAF Sat Cat: 1903 . COSPAR: 1966-001A. Apogee: 379 km (235 mi). Perigee: 195 km (121 mi). Inclination: 65.00 deg. Period: 90.20 min. Area survey photo reconnaissance satellite. Program not completely met. Spacecraft put into incorrect orbit by abnormal function of second and third stages of booster..

• Cosmos 105 - . Payload: Zenit-2 11F61 s/n 38. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1966-01-30 . USAF Sat Cat: 1945 . COSPAR: 1966-003A. Apogee: 311 km (193 mi). Perigee: 203 km (126 mi). Inclination: 65.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite..

• Luna 9 - . Payload: E-6M s/n 13. Mass: 1,580 kg (3,480 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6. Decay Date: 1966-02-03 . USAF Sat Cat: 1954 . COSPAR: 1966-006A.

  Soft landed on Moon; photographed surface for 3 days. Landed on Moon 3 February 1966 at 18:44:52 GMT, Latitude 7.08 N, Longitude 295.63 E - Oceanus Procellarum. The Luna 9 spacecraft was the first spacecraft to achieve a lunar soft landing and to transmit photographic data to Earth. Seven radio sessions, totaling 8 hours and 5 minutes, were transmitted as were three series of TV pictures. When assembled, the photographs provided a panoramic view of the nearby lunar surface. The pictures included views of nearby rocks and of the horizon 1.4 Km away from the spacecraft.

• Cosmos 107 - . Payload: Zenit-2 11F61 s/n 34. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1966-02-18 . USAF Sat Cat: 1998 . COSPAR: 1966-010A. Apogee: 313 km (194 mi). Perigee: 216 km (134 mi). Inclination: 65.00 deg. Period: 89.70 min. Area survey photo reconnaissance satellite..

• Cosmos 109 - . Payload: Bion precursor. Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1966-02-27 . USAF Sat Cat: 2019 . COSPAR: 1966-014A. Apogee: 288 km (178 mi). Perigee: 204 km (126 mi). Inclination: 64.90 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule; also carried biological experiments..

• Cosmos 110 - . Payload: Voskhod 3KV s/n 5. Mass: 5,700 kg (12,500 lb). Nation: Russia. Related Persons: Beregovoi, Shatalov, Shonin, Volynov. Agency: MOM. Program: Voskhod. Class: Manned. Type: Manned spacecraft. Flight: Voskhod 3. Spacecraft Bus: Vostok. Spacecraft: Voskhod. Duration: 20.69 days. Decay Date: 1966-03-16 . USAF Sat Cat: 2070 . COSPAR: 1966-015A. Apogee: 887 km (551 mi). Perigee: 181 km (112 mi). Inclination: 51.80 deg. Period: 95.30 min.

  Successfully recovered March 15, 1966 13:00 GMT. Precursor mission for Voskhod 3 hardware. Two dogs carried into lower Van Allen radiation belts.
  Officially: Biological research.

  Voskhod s/n 5 launched at 23:10 Moscow time, with two dogs, Veterka and Ygolka, aboard. This will be a 25-day mission. Kamanin is disgusted, he had proposed this as a 25-day mission by a single cosmonaut, but Korolev had constantly held with the 'dog variant'. Preparations for Voskhod-3 are proceeding well. The prime and back-up crews have completed their training and will take their examinations on 28 February. Parallel trials of the oxygen regeneration system at IMBP and OKB-124 both went well (IMBP, 12 days so far, temperature 16-24 deg C, 70% humidity; OKB-124, 10 days so far, temperature 18-16 deg C, 65% humidity).

• Cosmos 111 - . Payload: Ye-6S s/n 204. Mass: 6,540 kg (14,410 lb). Nation: Russia. Agency: Korolev bureau. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft Bus: Luna E-6. Spacecraft: Luna E-6S. Decay Date: 1966-03-03 . USAF Sat Cat: 2093 . COSPAR: 1966-017A. Apogee: 180 km (110 mi). Perigee: 168 km (104 mi). Inclination: 51.80 deg. Period: 88.00 min.

• Cosmos 112 - . Payload: Zenit-2 11F61 s/n 37. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1966-03-25 . USAF Sat Cat: 2107 . COSPAR: 1966-021A. Apogee: 664 km (412 mi). Perigee: 214 km (132 mi). Inclination: 72.00 deg. Period: 93.30 min. Area survey photo reconnaissance satellite..

• Cosmos 113 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1966-03-29 . USAF Sat Cat: 2114 . COSPAR: 1966-023A. Apogee: 314 km (195 mi). Perigee: 202 km (125 mi). Inclination: 64.90 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule.

• Molniya-1 s/n 5 Failure - . Payload: Molniya-1 s/n 5. Mass: 1,600 kg (3,500 lb). Nation: Russia. Agency: RVSN. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft Bus: KAUR-2. Spacecraft: Molniya-1.

• Luna 10 - . Payload: E-6S s/n 206 ISL. Mass: 1,597 kg (3,520 lb). Nation: Russia. Agency: Korolev bureau. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft Bus: Luna E-6. Spacecraft: Luna E-6S. USAF Sat Cat: 2126 . COSPAR: 1966-027A.

  Lunar Orbit (Selenocentric). Development of system to permit the creation of an artificial lunar satellite for the investigation of circumlunar space; development of onboard systems for putting a station into a selenocentric (circumlunar) orbit. Orbit: Lunar Orbiter. The Luna 10 spacecraft was launched towards the Moon from an Earth orbiting platform. The spacecraft entered lunar orbit 3 50 x 1017 km, inclination 71.9 deg to plane of the lunar equator. on April 4, 1966. Scientific instruments included a gamma-ray spectrometer for energies between 0.3--3 MeV, a triaxial magnetometer, a meteorite detector, instruments for solar-plasma studies, and devices for measuring infrared emissions from the Moon and radiation conditions of the lunar environment. Gravitational studies were also conducted. The spacecraft played back to Earth the `Internationale' during the Twenty-third Congress of the Communist Party of the Soviet Union. Luna 10 was battery powered and operated for 460 lunar orbits and 219 active data transmissions before radio signals were discontinued on May 30, 1966.

• Cosmos 114 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1966-04-14 . USAF Sat Cat: 2133 . COSPAR: 1966-028A. Apogee: 337 km (209 mi). Perigee: 202 km (125 mi). Inclination: 72.80 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule.

• Cosmos 115 - . Payload: Zenit-2 11F61 s/n 35. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1966-04-28 . USAF Sat Cat: 2147 . COSPAR: 1966-033A. Apogee: 283 km (175 mi). Perigee: 189 km (117 mi). Inclination: 65.00 deg. Period: 89.20 min. . Program partially completed. Abnormal operation of SA-10 camera..

• Waiting on Voskhod - . Nation: Russia. Related Persons: Popovich, Tereshkova. Program: Voskhod. Flight: Voskhod 3.

  The search for the cause of the Molniya booster failure continues. A high oscillation vibration problem with the engine that has cropped up twice (but only on the test stand) has been cleared of responsibility. Tereshkova is going on a tour of Sweden. The cosmonauts' wives are preparing a letter denouncing Popovich for shutting down his wife's career and his abuse of her. Throughout the period April to May Kamanin is preoccupied with his wife, who is extremely ill in the hospital.

• Molniya 1-03 - . Payload: Molniya-1. Mass: 1,600 kg (3,500 lb). Nation: Russia. Agency: MOM. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft Bus: KAUR-2. Spacecraft: Molniya-1. Decay Date: 1973-06-11 . USAF Sat Cat: 2151 . COSPAR: 1966-035A. Apogee: 39,414 km (24,490 mi). Perigee: 546 km (339 mi). Inclination: 65.00 deg. Period: 709.80 min. Also transmitted cloud cover images. Television programme transmission and long-range two-way multi-channel telephone, phototelegraph and telegraph communicaitons. .

• Cosmos 117 - . Payload: Zenit-2 11F61 s/n 39. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1966-05-14 . USAF Sat Cat: 2163 . COSPAR: 1966-037A. Apogee: 314 km (195 mi). Perigee: 200 km (120 mi). Inclination: 64.90 deg. Period: 89.60 min. Area survey photo reconnaissance satellite..

• Cosmos 118 - . Payload: Meteor no. 4. Mass: 4,730 kg (10,420 lb). Nation: Russia. Agency: MOM. Class: Earth. Type: Weather satellite. Spacecraft: Meteor. Decay Date: 1988-11-23 . USAF Sat Cat: 2168 . COSPAR: 1966-038A. Apogee: 339 km (210 mi). Perigee: 316 km (196 mi). Inclination: 65.00 deg. Period: 91.10 min. Probable weather satellite. Investigation of the upper atmosphere and outer space. .

• Voskhod 3 State Commission - . Nation: Russia. Related Persons: Shabarov, Tsybin, Voronin. Program: Voskhod. Flight: Voskhod 3. Spacecraft Bus: Vostok. Spacecraft: Voskhod.

  Chief Designer A A Golubev from OKB-154 Voronezh discusses the failure of his engines on the third stage of the Molniya launch on 27 March. He points out that the third stage has operated successfully in 500 stand trials and over 100 flights. It is true there have been seven instances of high-frequency oscillations in test stand runs of the engines, going back to the time of Tereshkova's flight, but these are felt to be due to the test stand propellant feed set-up and would not occur in flight engines. Despite no definite cause having been found for the third stage failure on 27 March, he guarantees his engines ready for flight. Other commission members question his optimism, but finally his guarantee is accepted, dependent on a thorough quality assurance review and certification by military officials responsible for control of the production processes at the factory. Voronin certifies the ECS system for an 18 day flight. Tsybin certifies the readiness of the spacecraft, and Shabarov the readiness of the booster at the launch centre. The absence of Korolev's presence is sorely felt, especially in handling the opposition of Smirnov and Pashkov to the flight. Nevertheless, the order is given for final preparations to proceed, with launch set for 22-28 May. However the confidence of the commission members in standing up to Smirnov is tenuous, and it is clear that any delay into June or July will kill the flight.

• Voskhod 3 delays - . Nation: Russia. Related Persons: Tyulin. Program: Voskhod. Flight: Voskhod 3. Spacecraft Bus: Vostok. Spacecraft: Voskhod.

  Tyulin has already warned that military crews at Baikonur are 'going slow' in Voskhod 3 preparations. Now it is reported from Voronezh that the military quality control official is refusing to certify the engines for the third stage of Voskhod 3 as ready for flight. It is clear that the flight will slip into June at this rate...

• Zenit-4 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: RVSN. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. High resolution photo reconnaissance mission..

• Nation: Kazakhstan. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Cosmos 120 - . Payload: Zenit-2 11F61 s/n 41. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1966-06-16 . USAF Sat Cat: 2196 . COSPAR: 1966-050A. Apogee: 331 km (205 mi). Perigee: 201 km (124 mi). Inclination: 51.70 deg. Period: 89.80 min. Area survey photo reconnaissance satellite..

• Cosmos 121 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1966-06-25 . USAF Sat Cat: 2210 . COSPAR: 1966-054A. Apogee: 327 km (203 mi). Perigee: 205 km (127 mi). Inclination: 72.80 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule.

• Nation: Kazakhstan. Agency: RVSN. Apogee: 1,350 km (830 mi).

• Cosmos 122 - . Payload: Meteor no. 5. Mass: 4,730 kg (10,420 lb). Nation: Russia. Agency: MOM. Class: Earth. Type: Weather satellite. Spacecraft: Meteor. Decay Date: 1989-11-14 . USAF Sat Cat: 2254 . COSPAR: 1966-057A. Apogee: 388 km (241 mi). Perigee: 371 km (230 mi). Inclination: 65.00 deg. Period: 92.10 min. Investigation of the upper atmosphere and outer space. .

• Cosmos 124 - . Payload: Zenit-2 11F61 s/n 42. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 8.00 days. Decay Date: 1966-07-22 . USAF Sat Cat: 2325 . COSPAR: 1966-064A. Apogee: 282 km (175 mi). Perigee: 205 km (127 mi). Inclination: 51.80 deg. Period: 89.40 min. Area survey photo reconnaissance satellite..

• Cosmos 125 - . Mass: 3,800 kg (8,300 lb). Nation: Russia. Agency: MOM. Program: RORSAT. Class: Surveillance. Type: Naval Radarsat. Spacecraft Bus: Kosmoplan. Spacecraft: US-A. Decay Date: 1966-08-02 . USAF Sat Cat: 2351 . COSPAR: 1966-067A. Apogee: 260 km (160 mi). Perigee: 204 km (126 mi). Inclination: 64.90 deg. Period: 89.10 min. Prototype RORSAT hardware using chemical batteries in place of nuclear reactor. Lost on the 52nd revolution as a result of a possible failure in the chemical power units placed on board instead of the nuclear BES-5..

• Cosmos 126 - . Payload: Zenit-4. Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 9.00 days. Decay Date: 1966-08-06 . USAF Sat Cat: 2368 . COSPAR: 1966-068A. Apogee: 343 km (213 mi). Perigee: 209 km (129 mi). Inclination: 51.80 deg. Period: 90.10 min. High resolution photo reconnaissance satellite; returned film capsule.

• Cosmos 127 - . Payload: Zenit-4. Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1966-08-16 . USAF Sat Cat: 2391 . COSPAR: 1966-071A. Apogee: 263 km (163 mi). Perigee: 201 km (124 mi). Inclination: 51.80 deg. Period: 89.10 min. High resolution photo reconnaissance satellite; returned film capsule.

• Luna 11 - . Payload: E-6LF s/n 101. Mass: 1,638 kg (3,611 lb). Nation: Russia. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft Bus: Luna E-6. Spacecraft: Luna E-6LF. USAF Sat Cat: 2406 . COSPAR: 1966-078A.

  Automatic station Luna 11. Further development of artificial lunar satellite systems and conduct of scientific experiments in circumlunar space. Lunar orbit 160 km x 1200 km x 27 degrees. Luna 11 was launched towards the Moon from an earth-orbiting platform and entered lunar orbit on August 28, 1966. The objectives of the mission included the study of: (1) lunar gamma- and X-ray emissions in order to determine the Moon's chemical composition; (2) lunar gravitational anomalies; (3) the concentration of meteorite streams near the Moon; and, (4) the intensity of hard corpuscular radiation near the Moon. A total of 137 radio transmissions and 277 orbits of the Moon were completed before the batteries failed on October 1, 1966.

• Cosmos 128 - . Mass: 6,300 kg (13,800 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1966-09-04 . USAF Sat Cat: 2409 . COSPAR: 1966-079A. Apogee: 343 km (213 mi). Perigee: 207 km (128 mi). Inclination: 64.90 deg. Period: 90.00 min. High resolution photo reconnaissance satellite; returned film capsule.

• Zenit-2 11F61 s/n 40 - . Payload: Zenit-2 11F61 s/n 40. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: RVSN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Decay Date: 1966-09-16 . Area survey photo reconnaissance satellite..

• Cosmos 129 - . Payload: Zenit-2 11F61 s/n 33. Mass: 4,720 kg (10,400 lb). Nation: Russia. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Vostok. Spacecraft: Zenit-2 satellite. Duration: 7.00 days. Decay Date: 1966-10-21 . USAF Sat Cat: 2491 . COSPAR: 1966-091A. Apogee: 288 km (178 mi). Perigee: 199 km (123 mi). Inclination: 65.40 deg. Period: 89.40 min. Area survey photo reconnaissance satellite..