Proton 8K82K Media Gallery

Development of a three-stage version of the UR-500 was authorised in the decree of 3 August 1964. Decrees of 12 October and 11 November 1964 authorised development of the Almaz manned military space station and the manned circumlunar spacecraft LK-1 as payloads for the UR-500K. Remarkably, due to continuing failures, the 8K82K did not satisfactorily complete its state trials until its 61st launch (Salyut 6 / serial number 29501 / 29 September 1977). Thereafter it reached a level of launch reliability comparable to that of other world launch vehicles.

Development of a three-stage version of the UR-500 was authorised in the decree of 3 August 1964. During development, in comparison to the original polyblock design, the engine performances were improved by about 5 seconds; the mass of the first stage increased by 71 tonnes; the second stage by 30 tonnes; and the third stage by 27 tonnes (more than doubled). These changes brought the low earth orbit payload from 12,000 kg up to almost 20,000 kg. The UR-500K, although it exceeded the launch mass of the 11A511 Soyuz by 2.22 times and the fuel mass by 2.25 times, was more efficient with a useful load by 2.78 times greater. However putting the new variant of Proton into service proved difficult.

Decrees of 12 October and 11 November 1964 authorised development of the Almaz manned military space station and the manned circumlunar spacecraft LK-1 as payloads for the UR-500K. However at the same time Khrushchev was ousted from power. Chelomei lost his chief patron and his projects came under negative scrutiny by the new leadership.

Although Korolev was opposed to the Proton, he now used it to his advantage. On 8 September 1965 Korolev presented several schemes for using Chelomei’s UR-500K to fly around the moon. One alternate was a two-part spaceship, using the Proton with the upper stage Block D from Korolev’s N1-L3 lunar project. This would launch Korolev’s 7K-L1 spacecraft (derived from the 7K-OK Soyuz spacecraft) onto a translunar trajectory. This project received the name UR-500K-L1, and was adopted in place of Chelomei’s LK-1. It required construction of 18 UR-500K rockets, which, in a combination flight-test and government trials program, would send L1 spacecraft around the moon, at first unmanned, then manned.

As a result of Korolev’s seizure of the project, the first flights of the three stage Proton included Korolev’s fourth Block D stage. Due to delays in the Almaz military space station, it was pre-empted by an OKB-1 civilian derivative, the Zarya. The first launch of the basic three-stage UR-500K vehicle, without the Block D upper stage, did not come until the launch of the Proton 4 physics satellite, almost two years after flights of the four-stage version had begun.

Remarkably, due to continuing failures, the 8K82K did not satisfactorily complete its state trials until its 61st launch (Salyut 6 / serial number 29501 / 29 September 1977). Thereafter it reached a level of launch reliability comparable to that of other world launch vehicles.

Manufacturer: Chelomei. Launches: 31. Failures: 4. Success Rate: 87.10%. First Launch Date: 1968-11-16. Last Launch Date: 2000-07-12. Launch data is: continuing. LEO Payload: 19,760 kg (43,560 lb). to: 186 km Orbit. at: 51.60 degrees. Associated Spacecraft: Almaz-T, Almaz OPS, Iskra, ISS Zarya, ISS Zvezda, Kristall, Kvant, Kvant-2, Mak, Mir , N-6 , Priroda, Salyut 1, Salyut 4, Salyut 6, Salyut 7, Spektr, TKS , TKS VA . Other Associated Spacecraft: OPS + TKS, Almaz OPS-2, KSI, Almaz APOS, Almaz-2, Almaz-1B, LK-1, ISS Commercial Enterprise Module, Tellura, Vega 5VS, Spektr - Original, TGR, 37K-Mir, LKS, Raketoplan, Mars 5M. Further Associated Spacecraft: Space Station Designs - 1982, Space Station Freedom , Power Tower Space Station - 1984, Space Station 1984, Polar Platform, Space Tug, Orbital Manoeuvring Vehicle, Space Operations Center, . Liftoff Thrust: 8,847.000 kN (1,988,884 lbf). Total Mass: 693,810 kg (1,529,580 lb). Core Diameter: 4.15 m (13.61 ft). Total Length: 50.00 m (164.00 ft). Launch Price $: 50.000 million. in: 1994 price dollars.

Production version.

Prototype version.

LEO Payload: 19,000 kg (41,000 lb). Apogee: 300 km (180 mi). Liftoff Thrust: 9,500.000 kN (2,135,600 lbf). Total Mass: 694,000 kg (1,530,000 lb). Core Diameter: 7.40 m (24.20 ft). Total Length: 50.00 m (164.00 ft).

• Stage Number: 1. 1 x Stage: Proton K-1. Gross Mass: 450,510 kg (993,200 lb). Empty Mass: 31,100 kg (68,500 lb). Thrust (vac): 10,470.158 kN (2,353,785 lbf). Isp: 316 sec. Burn time: 124 sec. Isp(sl): 267 sec. Diameter: 4.15 m (13.61 ft). Span: 7.40 m (24.20 ft). Length: 21.20 m (69.50 ft). Propellants: N2O4/UDMH. No Engines: 6. Engine: RD-253-11D48. Other designations: 8S810K.

• Stage Number: 2. 1 x Stage: Proton K-2. Gross Mass: 167,828 kg (369,997 lb). Empty Mass: 11,715 kg (25,827 lb). Thrust (vac): 2,399.216 kN (539,365 lbf). Isp: 327 sec. Burn time: 206 sec. Isp(sl): 230 sec. Diameter: 4.15 m (13.61 ft). Span: 4.15 m (13.61 ft). Length: 14.00 m (45.00 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: RD-0210. Other designations: 8S811K.

• Stage Number: 3. 1 x Stage: Proton K-3. Gross Mass: 50,747 kg (111,877 lb). Empty Mass: 4,185 kg (9,226 lb). Thrust (vac): 630.170 kN (141,668 lbf). Isp: 325 sec. Burn time: 238 sec. Isp(sl): 230 sec. Diameter: 4.15 m (13.61 ft). Span: 4.15 m (13.61 ft). Length: 6.50 m (21.30 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-0212.

1964 August 1 - Launch Vehicle: N1, Proton 8K82K.

• Full scale development of Soviet manned lunar flyby and landing projects authorised. Nation: USSR. Program: Lunar L1, Lunar L3. Spacecraft: LK-1, Soyuz 7K-LOK, LK, Luna Ye-8, Soyuz A. Flight: Soyuz A-1, Soyuz A-2, Soyuz A-3, Soyuz A-4. Central Committee of the Communist Party and Council of Soviet Ministers Decree 655-268 'On Work on the Exploration of the Moon and Mastery of Space--piloted LK-1 circumlunar and L3 lunar landing projects and the Ye-6M lunar lander' was issued. Chelomei was to develop the three-stage UR-500K booster and LK-1 spacecraft for the manned lunar flyby. Korolev was to develop the totally different N1 booster and L3 spacecraft complex for the manned lunar landing. First launch of the N1 was to be by the first quarter 1966, with manned lunar landings in 1967 to 1968. Reprioritization led to work being stopped on Korolev's Zvezda 6-man orbiting weapons platform by mid-1965, after a huge mockup had been built.

  Korolev felt that if he had the full support of the Communist Party, the military, and industry he could achieve this goal, and this decree ordered such support. The USSR would be first on the moon. But in truth the draft project behind the decree had not solved all of the technical problems, or provided a solution on how to achieve the required payload on either the booster or spacecraft side. New technology features required for success of the scheme included an advanced guidance system in the N1 third stage equipment bay, the enormous fuel tanks in the N1 first stage, and the Lox/LH2 fuel cells needed for the LOK lunar orbiter. But the real technical problem with the N1-L3 design was the total lack of any weight growth reserve. Even thought the systems had not even been developed yet, engineers were fighting over tens of grams in their weight allocations, let alone the kilograms normally at issue.

  Development of Korolev's Soyuz A-B-V, a competing circumlunar project, was evidently still authorised, although it duplicated Chelomei's LK-1.References: 75, 367, 474.

• Chief Designers review of Voskhod at OKB-1 Nation: USSR. Program: Voskhod. Spacecraft: Voskhod, LK-1. Flight: Voskhod 1. All concerned designers, bureaux, and institutes certify the reliability of the systems of the spacecraft and launch vehicle. The second phase of trials of the soft landing system have been successful. Of 10 drops, 9 landed with vertical velocity under 7.5 m/s, and of those, 6 landed with a speed of only 0.0 to 1.5 m/s. There are still concerns about how the system will function in soft soils or adverse weather conditions. Nevertheless the decision is taken to ship the spacecraft to the cosmodrome for final preparations between 18 and 25 August. It is likely that the manned flight cannot occur until the end of September. Later in the day Kamanin is visited by Sergei Nikitovich Khrushchev and other experts from Chelomei's design bureau. They brief Kamanin on plans for a manned circumnavigation of the moon using their spacecraft launched by their UR-500 booster by the end of 1967.References: 376.

• Voskhod abort system Nation: USSR. Program: Voskhod, Lunar L1, Lunar . Spacecraft: Voskhod, LK-1. Flight: Voskhod 1. Kamanin reviews the Voskhod abort system with Korolev. Up to T+27 seconds, there is no possibility of saving the crew in the event of a booster failure; from T+27 seconds to T+44 seconds, escape would be difficult, but is possible; and from T+44 seconds to T+501 seconds abort should be possible, with the capsule landing on Soviet territory. Afterwards, Korolev speaks with Kamanin secretly and privately. Korolev reveals that he has discussed a greater VVS role in space with Marshal Krylov, but that Krylov is adamantly opposed to the VVS assuming such a mission. Korolev is seeking a resolution from the Communist Party that will authorise him to develop a manned lunar flyby and landing system using his N1 booster. He believes that Chelomei's UR-500 booster will not have sufficient payload to mount a manned flyby - a docking in low earth orbit will be required. But Chelomei has rejected the use of docking, and is even designing his UR-700 to allow a lunar landing without the use of docking.

  Finally Korolev gets to the purpose of the secret meeting. He wants Feoktistov to be aboard Voskhod 1, despite the opinion of Kamanin and the physicians. Kamanin reiterates that the most qualified crew would be Komarov, Volynov, and Lazarev; and if he gives in on Feoktistov, then Komarov, Feoktistov, Lazarev. But Korolev is opposed to Lazarev, and insists that the crew should be Komarov, Feoktistov, and Yegorov. From Kamanin's point of view this is flying a space mission with two invalids aboard. Lazarev is a qualified and fit flight surgeon, a qualified pilot as well as a physician with 15 years of research experience in aviation medicine. Korolev is adamant that the two passengers should be civilian, not military. No agreement is possible.References: 376.

• Almaz project starts Nation: USSR. Spacecraft: Almaz APOS, Soyuz R. The day before the overthrow of his patron, Chelomei obtained permission to begin development of a larger military space station, the Almaz. This 20 tonne station would take three cosmonauts to orbit in a single launch of his UR-500K Proton rocket. Therefore there were now two competing projects for the same mission - Almaz and Soyuz-R. First flight of the Almaz, with a one year operational period, was set for 1968.

• Khrushchev ousted from power. Nation: USSR. Spacecraft: Kosmoplan, OGCh, IS-A, US-P, US-A, LK-1. Brezhnev faction assumes control of Politubro. Brezhnev was adverse to all projects Khrushchev had supported. These included those of Chelomei and his OKB-52.

• Lunar project orders issued to industry. Nation: USSR. Program: Lunar L1, Lunar L3. Spacecraft: LK-1, Soyuz 7K-LOK, LK, Luna Ye-8. Military-Industrial Commission (VPK) Decree 'On assignment of lunar programs to OKB-52 and OKB-1' was issued. References: 474.

• Development of the manned circumlunar spacecraft LK-1 authorised Nation: USSR.

• L1 manned circumlunar mission taken from Chelomei, given to Korolev. Nation: USSR. Spacecraft: Soyuz 7K-L1, Soyuz 7K-OK, LK-1. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On the Concentration of Forces of Industrial Design Organisations for the Creation of Rocket-Space Complex Means for Circling the Moon--work on the UR-500K-L1 program' was issued. As a result of a presentation to the Military Industrial Commission, Afanasyev backed Korolev in wresting control of the manned circumlunar project from Chelomei. The Chelomei LK-1 circumlunar spacecraft was cancelled. In its place, Korolev would use a derivative of the Soyuz 7K-OK, the 7K-L1, launched by Chelomei’s UR-500K, but with a Block D translunar injection stage from the N1. He envisioned launch of the unmanned 7K-L1 into low earth orbit, followed by launch and docking of a 7K-OK with the 7K-L1. The crew would then transfer to the L1, which would then be boosted toward the moon. This was the original reason for the development of the 7K-OK.References: 474.

• Industrial orders to cancel LK-1 spacecraft and implement L1. Nation: USSR. Spacecraft: Soyuz 7K-L1, LK-1. Ministry of General Machine Building (MOM) Decree 'On work on the UR-500K-L1 program' was issued. References: 474.

• Cosmonaut training for lunar flights announced Nation: USSR. Program: Lunar L1. Class: Manned. Type: Spacecraft. Spacecraft: Soyuz 7K-L1. Leonov announces that cosmonauts are in training for lunar missions. References: 72.

• Soyuz L1 full scale development, LK-1 cancellation approved. Nation: USSR. Spacecraft: Soyuz 7K-L1, LK-1. Decree 10 'On approving the work plan to build the p8loted spacecraft 7K-L1 -- approving the plan for for the UR-500K-L1 and terminating the UR-500K-LK-1' was issued. References: 474.

• Lunar flight cosmonauts assignments. Nation: USSR. Program: Lunar L1. Class: Manned. Type: Spacecraft. Spacecraft: Soyuz 7K-L1. In the period 1966 to 1968 there were five simultaneous Soviet manned space projects (Soyuz 7K-OK orbital; Soyuz 7K-L1 circumlunar; Soyuz VI military; L3 manned lunar landing; Almaz space station). Cosmonaut assignments were in constant flux, resulting in many claims in later years that 'I was being trained for the first moon flight'.Additional Details: Lunar flight cosmonauts assignments.(5388). References: 23.

• First session of State Commission for the L1 Nation: USSR. Program: Lunar L1. Spacecraft: Soyuz 7K-OK, Soyuz 7K-L1. Flight: Soyuz 7K-L1 mission 1, Soyuz 7K-L1 mission 2, Soyuz 7K-L1 mission 3. Tyulin chairs the meeting. Mishin, Chelomei and Barmin brief the status of the spacecraft, booster, and launch site. There is much to be done in order to fly cosmonauts around the moon by 7 November 1967 - the 50th anniversary of the October Revolution. The first manned flight around the moon is planned for 26 June 1967. To achieve this, four flights of the L1 without a crew have to be completed first. The UR-500K booster should be capable of launching the L1 on a direct flight around the Moon and back to the earth. But since the UR-500K has not yet flown, and its 19-tonne low earth payload has not bee verified, Mishin plans to follow the podsadka scenario. The UR-500K will place in low earth orbit an L1 without a crew, and then a Soyuz booster will place a manned Soyuz 7K-OK Soyuz in orbit. The Soyuz crew will rendezvous and dock with the L1, and the crew for the circumlunar mission will spacewalk through open space from the 7K-OK into the L1. The spacecraft will then separate. The 7K-OK returns to earth, while the L1 is boosted on a circumlunar trajectory. After 4 to 6 launches of the UR-500K to verify its reliability and payload margins, it should be possible to make the direct flight to the moon on subsequent versions. For the time being it is necessary to develop both versions in parallel. References: 376.

• First L-1 Zond spacecraft mated to Proton Nation: USSR. Program: Lunar L1. Payload: Soyuz 7K-L1P #1. Class: Manned. Type: Spacecraft. Spacecraft: Soyuz 7K-L1. Fit tests at Tyuratam. Not launched (Interavia SD). References: 23.

• Soviet of Chief Designers Nation: USSR. Program: Lunar L1, Soyuz. Spacecraft: Soyuz 7K-OK, Soyuz 7K-L1. In Moscow, Mishin heads a meeting of all the Chief Designers (including Chelomei, Mishin, and Glushko). Glushko says that the last UR-500K failure was due to errors made during manufacture of an engine in 1965 at Factory 19 at Perm. Ustinov notes that the failure has cost the state 100 million roubles and has delayed the program two to three months. He brutally attacks Dementiev, Minister of Aviation Industry, for the poor work of his factories on the space program. Another issue is continued delays in the Salyut computer for the L1. Ustinov orders an alternate technical solution to be developed in parallel with the digital computer development. The next Soyuz flight is set for the end of December, the next L1 attempt for 21-22 November.References: 376.

• UR-500 launch vehicle version for military payloads authorised. Nation: USSR. Central Committee of the Communist Party and Council of Soviet Ministers Decree 1070-363 'On approval of work on the UR-500 launch vehicle' was issued. References: 474.

• Cause of Proton failure in last launch. Nation: USSR. Program: Lunar L1. Glushko at Baikonur. He reports the Perm factory is under close supervision - the engine that failed on the last launch was found to have resin in the main fuel line. References: 376.

• DIA/CIA warn of impending Zond circumlunar flight Nation: USSR. Program: Lunar L1. Class: Manned. Type: Spacecraft. Spacecraft: Soyuz 7K-L1. The information led NASA to decide to send Apollo 8 on a risky lunar orbital mission at the end of December 1968. Interestingly enough the CIA warning to NASA came within days of the L1 State Commission's meeting and decision to press for a November circumlunar flight.References: 72.

• Zond 7K-L1 s/n 8L Nation: USSR. Program: Lunar L1. Payload: Zond 7K-L1 s/n 8L. Mass: 5,140 kg (11,330 lb). Class: Manned. Type: Spacecraft. Spacecraft: Soyuz 7K-L1. Decay Date: 1968-07-21. Block D stage exploded on pad, killing three people. Booster and 7K-L1 spacecraft were still intact however. References: 23.

• Proton 4 Nation: USSR. Program: Proton. Payload: N-6 s/n 1. Mass: 16,000 kg (35,000 lb). Class: Astronomy. Spacecraft: N-6 . Agency: MOM. Perigee: 248 km (154 mi). Apogee: 477 km (296 mi). Inclination: 51.60 deg. Period: 91.80 min. COSPAR: 1968-103A. USAF Sat Cat: 3544. Decay Date: 1969-07-24. First launch of the Proton three-stage variant. The satellite studied the nature of high and ultra-high energy cosmic rays and their interaction with atomic nuclei. Scientific payload 12,500 kg; operated for 100 days in orbit. References: 1, 2, 5, 6, 67, 273, 274.

• First flight Almaz station close to completion Nation: USSR. Program: Almaz. Class: Manned. Type: Space station. Spacecraft: Almaz OPS. Ten stations 'in advanced stage of completion' by end of year. References: 76.

• Space station programs rationalised. Nation: USSR. Program: Almaz. Class: Manned. Type: Space station. Spacecraft: Almaz OPS, Soyuz 7K-S, Soyuz OB-VI, Salyut 1. Brezhnev orders a cooperative crash program to build a civilian space station to beat Skylab into orbit. The civilian station (later named Salyut) will use the Almaz spaceframe fitted out with Soyuz functional equipment. Mishin's OIS military station was cancelled and Chelomei's Almaz would continue, but as second priority to the civilian station. The Soyuz 7K-S station ferry, the 7K-ST, would be revised to be a more conservative modification of the Soyuz 7K-OK. The OIS cosmonaut group was incorporated into the Almaz group.References: 76.

• Development of TKS ferry for Almaz authorised. Soyuz 7K-TK cancelled Nation: USSR. Spacecraft: TKS, Soyuz 7K-TK. Decree 437-160 'On creation of the TKS and termination of the 7K-TK' was issued. In 1969 Chelomei proposed replacement of the 11F72 Soyuz 7K-TK with his own transport-supply spacecraft 11F72 (transportnovo korablya snabzheniya - TKS). This would consist of the same 11F74 VA landing capsule used on the Almaz station, together with a new 11F77 functional-cargo block (funktsionalno-gruzovovo blok, FGB). This would transport three crew and sufficient supplies for 90 day operation of the Almaz.References: 474.

• 82-EV Test mission Nation: USSR. Payload: GVM 82EV Mass Model. Spacecraft: Raduga. Agency: RVSN. Apogee: 200 km (120 mi). Heavily instrumented suborbital flight to provide data to root out causes of continuing launch vehicle failures. Heavy mass model of an unspecified spacecraft used to simulate payload.. References: 5, 67, 274, 274.

• Soyuz 7K-L1 s/n 10L and 15L Nation: USSR. Program: Lunar L1. Payload: Soyuz 7K-L1 s/n 10L and 15L. Class: Manned. Type: Spacecraft. Spacecraft: Soyuz 7K-L1. Despite decision to cancel immediate manned circumlunar flights after Apollo 8, the remaining two L-1 spacecraft were kept in reserve for support of the L3 lunar landing program and possible later manned flights. They were never used. References: 23.

• Salyut 1 Nation: USSR. Program: Salyut. Payload: Zarya s/n 121. Mass: 18,500 kg (40,700 lb). Class: Manned. Type: Space station. Spacecraft: Salyut 1. Agency: MOM. Perigee: 180 km (110 mi). Apogee: 214 km (132 mi). Inclination: 51.40 deg. Period: 88.50 min. COSPAR: 1971-032A. USAF Sat Cat: 5160. Duration: 179.93 days. Decay Date: 1971-10-11. Flight: Soyuz 10, Soyuz 11, Soyuz 12 / DOS 1. First manned space station. Salyut 1 included a number of military experiments, including the OD-4 optical visual ranger, the Orion ultraviolet instrument for characterising rocket plumes, and the highly classified Svinets radiometer. Primary objectives included photography of the earth, spectrographs of the earth's horizon, experiments with intense gamma rays, and studying manual methods for station orientation.

  At 05:20 the State Commission and their guests arrive at the Area 95 observation point to view the launch. The booster takes off on schedule at 06:40 in light rain and 60 km/hr wind. The tracking station reports good orbital insertion, separation from the third stage, and antennae and solar panel deployment. But the cover of the scientific equipment bay does not separate. This will mean that many experiments cannot be accomplished. It is decided to launch the crew to the station anyway, since the station is otherwise functioning normally. The cosmonauts go to the baths in the evening.Additional Details: Salyut 1(1260). References: 1, 2, 5, 6, 67, 274, 376.

• Almaz / TKS project rescheduled. Nation: USSR. Spacecraft: Almaz OPS, Almaz OPS-2, TKS. Ministry of General Machine Building (MOM) Decree 'On schedule of work for the Almaz and TKS programs' was issued. References: 474.

• Zarya s/n 122 Nation: USSR. Program: Salyut. Payload: Zarya s/n 122. Mass: 18,000 kg (39,000 lb). Class: Manned. Type: Space station. Spacecraft: Salyut 1. Agency: RVSN. COSPAR: F720729A. Decay Date: 1972-07-29. Second Salyut space station (DOS 2), failed to reach orbit. References: 5, 67, 274.

• Brezhnev selects Almaz for next space station Nation: USSR. Program: Almaz. Class: Manned. Type: Space station. Spacecraft: Almaz OPS. Brezhnev personally selects Almaz for next space station launch. Following two successive failures of DOS-7K station (Salyut 1 and the July 29, 1972 launch failure), Brezhnev personally selects Almaz for next launch (Salyut 2). References: 76.

• Salyut 2 Nation: USSR. Program: Almaz. Payload: Almaz s/n 101-01. Mass: 18,500 kg (40,700 lb). Class: Manned. Type: Space station. Spacecraft: Almaz OPS. Agency: MOM. Perigee: 216 km (134 mi). Apogee: 248 km (154 mi). Inclination: 51.60 deg. Period: 89.10 min. COSPAR: 1973-017A. USAF Sat Cat: 6398. Duration: 54.62 days. Decay Date: 1973-05-28. The first flight of the Almaz manned military space station. In January 1973 the first Almaz OPS was delivered to Baikonur. Launch and initial orbital checkout went according to plan. But before a crew could be launched the station depressurized. It was concluded that a short in electrical equipment started a fire in pressure vessel, leading to rupture of hull and depressurization. An alternate theory was that debris from an explosion of the third stage of Proton penetrated the hull. Control was lost on April 25, 1973, and the OPS cased operations on 29 April. Decayed May 28, 1973. Initial crew was to have been Popovich and Artyukhin.
  Officially: Testing of improved design, on-board systems and equipment; conduct of scientific and technical research and experiments.Additional Details: Salyut 2(1518). References: 1, 2, 5, 6, 67, 274.

• Cosmos 557 Nation: USSR. Program: Salyut. Payload: Zarya s/n 123. Mass: 19,400 kg (42,700 lb). Class: Manned. Type: Space station. Spacecraft: Salyut 4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 225 km (139 mi). Inclination: 51.60 deg. Period: 88.90 min. COSPAR: 1973-026A. USAF Sat Cat: 6498. Duration: 10.98 days. Decay Date: 1973-05-22. Salyut failure. Unsuccessful mission. Salyut out of control. Decayed May 22, 1973. Was to have been manned by initial crew of Leonov and Kubasov. Last chance to upstage Skylab, launched three days later. References: 1, 2, 5, 6, 67, 274.

• Salyut 3 Nation: USSR. Program: Almaz. Payload: Almaz s/n 101-02. Mass: 18,500 kg (40,700 lb). Class: Manned. Type: Space station. Spacecraft: Almaz OPS. Agency: MOM. Perigee: 213 km (132 mi). Apogee: 253 km (157 mi). Inclination: 51.60 deg. Period: 89.10 min. COSPAR: 1974-046A. USAF Sat Cat: 7342. Duration: 90.00 days. Decay Date: 1975-01-24. First successful Almaz military manned space station flight. Tested a wide array of reconnaissance sensors. Following the successful Soyuz 14 and unsuccessful Soyuz 15 missions, on 23 September 1974 the station ejected a film return capsule. The KSI capsule suffered damage during re-entry but all the film was recoverable. On 24 January 1975 trials of the on-board 23 mm Nudelmann aircraft cannon (other sources say it was a Nudelmann NR-30 30 mm gun) were conducted. The next day the station was commanded to retrofire to a destructive re-entry over the Pacific Ocean. Although only one of three planned crews managed to board the station, that crew did complete the first completely successful Soviet space station flight.Additional Details: Salyut 3(1678). References: 1, 2, 5, 6, 67, 274.

• Salyut 4 Nation: USSR. Program: Salyut. Payload: Zarya s/n 124. Mass: 18,500 kg (40,700 lb). Class: Manned. Type: Space station. Spacecraft: Salyut 4. Agency: MOM. Perigee: 212 km (131 mi). Apogee: 251 km (155 mi). Inclination: 51.60 deg. Period: 89.10 min. COSPAR: 1974-104A. USAF Sat Cat: 7591. Duration: 768.82 days. Decay Date: 1977-02-02. Deorbited February 2, 1977.
  Maneuver Summary:
  211km X 250km orbit to 215km X 286km orbit. Delta V: 11 m/s
  211km X 284km orbit to 276km X 344km orbit. Delta V: 35 m/s
  277km X 342km orbit to 338km X 351km orbit. Delta V: 19 m/s
  330km X 340km orbit to 337km X 350km orbit. Delta V: 4 m/s
  337km X 349km orbit to 339km X 351km orbit. Delta V: 1 m/s
  332km X 348km orbit to 348km X 355km orbit. Delta V: 6 m/s
  347km X 354km orbit to 343km X 351km orbit. Delta V: 1 m/s
  335km X 344km orbit to 335km X 360km orbit. Delta V: 4 m/s
  335km X 360km orbit to 342km X 361km orbit. Delta V: 2 m/s
  330km X 351km orbit to 344km X 353km orbit. Delta V: 4 m/s
  186km X 187km orbit to 90km X 186km orbit. Delta V: 28 m/s
  Total Delta V: 87/115 m/s.
  Officially: Further testing of station design, on-board systems and equipment; conduct of scientific and technical research and experiments in outer space. Further testing of station design, on-board systems and equipment; conduct of scientific and technical researc h and experiments in outer space. References: 1, 2, 5, 6, 67, 274.

• Salyut 5 Nation: USSR. Program: Almaz. Payload: Almaz s/n 103-01. Mass: 19,000 kg (41,000 lb). Class: Manned. Type: Space station. Spacecraft: Almaz OPS. Agency: MOM. Perigee: 215 km (133 mi). Apogee: 232 km (144 mi). Inclination: 51.60 deg. Period: 88.90 min. COSPAR: 1976-057A. USAF Sat Cat: 8911. Duration: 411.24 days. Decay Date: 1977-08-08. Second successful flight of the Almaz manned military space station. It had taken only 60 days and 1450 man-hours to prepare Almaz 0101-2 for flight, using the services of 368 officers and 337 non-commissioned officers. The tracking ships Academician Sergei Korolev and Cosmonaut Yuri Gagarin were stationed in the Atlantic and Caribean to provide communications when out of tracking range of the USSR. Salyut 5 operated for 409 days, during which the crews of Soyuz 22 and 24 visited the station. Soyuz 23 was to have docked but its long-distance rendezvous system failed. Soyuz 25 was planned, but the mission would have been incomplete due to low orientation fuel on Salyut 5, so it was cancelled.

  During the flight of Salyut 5 a 'parallel crew' was aboard a duplicate station on the ground. They conducted the same operations in support of over 300 astrophysical, geophysical, technological, and medical/biological experiments. Astrophysics studies included an infrared telescope-spectrometer in the 2-15 micrometer range which also obtained solar spectra. Earth resources studies were conducted as well as Kristall, Potok, Diffuziya, Sfera, and Reatsiya technology experiments. Presumably Salyut 5 was equipped with a SAR side-looking radar for reconnaissance of land and sea targets even through cloud cover.

  The film capsule was ejected 22 February 1977 (and sold at Sotheby's, New York, on December 11, 1993!). The station was deorbited on 8 August 1977. In addition to the human crew two Russian tortoises (Testudo horsfieldi) and Zebrafish (Danio rerio) were flown.

  The results of the Salyut 3 and 5 flights showed that manned reconnaissance was not worth the expense. There was minimal time to operate the equipment after the crew took the necessary time for maintenance of station housekeeping and environmental control systems. The experiments themselves showed good results and especially the value of reconnaissance of the same location in many different spectral bands and parts of the electromagnetic spectrum.Additional Details: Salyut 5(2008). References: 1, 2, 5, 6, 67, 274.

• Cosmos 881 Nation: USSR. Program: Almaz. Payload: TKS VA s/n 009P. Mass: 4,250 kg (9,360 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS VA . Agency: MOM. Perigee: 201 km (124 mi). Apogee: 241 km (149 mi). Inclination: 51.60 deg. Period: 88.90 min. COSPAR: 1976-121A. USAF Sat Cat: 9606. Duration: 0.0600 days. Decay Date: 1976-12-15. Launch of mission LVI-1 came at 04:00 on 15 December. At 176 seconds the ADU escape tower separated from the LVI. Once the final stage had shut down in orbit, by command from the launch vehicle sequencer, the VA 009A (also given as 009P) and its TDU separated from the LVI. Two seconds later VA 009 (or 009L) was ejected. Fifteen minutes after launch all systems of the both VA capsules were in operation. The guidance system detected the direction of flight and oriented each spacecraft for retro-fire, and the pair began the return to earth after less than one revolution. At an external atmospheric pressure of 165 mm (10 km altitude) the NO section jettisoned, the three-cupola drogue parachute ejected, and the antennae and altimeter were deployed. The Komara landing radio beacon (installed on the landing section of the parachute) was activated when the spacecraft was 1.0 to 1.5 m above the ground - which occurred at the same moment on both 009 and 009A. The Kaktus special system tripped the soft landing PRSP (parachute landing propulsion system). The soft landing was accomplished with higher accuracy than Soyuz, both capsules being recovered at 44 deg N, 73 deg E, on December 15, 1976 3:00 GMT. The flights were officially given the designations Cosmos 881 (VA 009A) and Cosmos 882 (VA 009). US intelligence believed them to be tests of recoverable manned spaceplane prototypes.References: 1, 2, 5, 6, 67, 274, 439.

• Cosmos 882 Nation: USSR. Program: Almaz. Payload: TKS VA s/n 009L. Mass: 4,250 kg (9,360 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS VA. Agency: MOM. Perigee: 191 km (118 mi). Apogee: 213 km (132 mi). Inclination: 51.60 deg. Period: 88.50 min. COSPAR: 1976-121B. USAF Sat Cat: 9607. Decay Date: 1976-12-15. Test of TKS-VA capsule. Two satellites launched by a single rocket. References: 1, 2, 5, 6, 67, 274, 439.

• Cosmos 929 Nation: USSR. Program: Almaz. Payload: TKS s/n 16101. Mass: 19,000 kg (41,000 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS . Agency: MOM. Perigee: 226 km (140 mi). Apogee: 260 km (160 mi). Inclination: 51.60 deg. Period: 89.40 min. COSPAR: 1977-066A. USAF Sat Cat: 10146. Duration: 199.62 days. Decay Date: 1978-02-02. First test of TKS manned shuttle. Maneuvered extensively. TKS-VA capsule returned to earth August 16, 1977. Deorbited February 2, 1978.
  Maneuver Summary:
  214 km X 261 km orbit to 215 km X 279 km orbit. Delta V: 5 m/s
  207 km X 261 km orbit to 208 km X 264 km orbit. Delta V: 1 m/s
  208 km X 260 km orbit to 209 km X 267 km orbit. Delta V: 2 m/s
  192 km X 222 km orbit to 219 km X 232 km orbit. Delta V: 9 m/s
  219 km X 232 km orbit to 303 km X 327 km orbit. Delta V: 51 m/s
  303 km X 327 km orbit to 312 km X 318 km orbit. Delta V: 4 m/s
  312 km X 319 km orbit to 314 km X 325 km orbit. Delta V: 1 m/s
  284 km X 294 km orbit to 290 km X 301 km orbit. Delta V: 3 m/s
  288 km X 300 km orbit to 286 km X 305 km orbit. Delta V: 1 m/s
  285 km X 303 km orbit to 439 km X 447 km orbit. Delta V: 84 m/s
  437 km X 448 km orbit to 335 km X 437 km orbit. Delta V: 31 m/s
  335 km X 437 km orbit to 337 km X 438 km orbit. Delta V: 1 m/s
  337 km X 438 km orbit to 90 km X 337 km orbit. Delta V: 100 m/s
  Total Delta V: 193/293 m/s
  Officially: Investigation of the upper atmosphere and outer space. References: 1, 2, 5, 6, 67, 274, 439.

• TKS VA s/n 009L/P Nation: USSR. Program: Almaz. Payload: TKS VA s/n 009L/P. Mass: 4,250 kg (9,360 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS VA. Agency: RVSN. COSPAR: F770804A. Decay Date: 1977-08-04. Spacecraft lost in booster explosion. References: 5, 67, 274, 439.

• TKS VA s/n 009P/P Nation: USSR. Program: Almaz. Payload: TKS VA s/n 009P/P. Spacecraft: TKS VA. Agency: RVSN. COSPAR: F770804C. A repeat test of the VA capsules from LVI-1 of a month earlier were atop the Proton (VA's 009P and 009L). However the booster failed at 49 seconds after launch. The SAS launch escape system pulled the top capsule (009P) away from the exploding Proton rocket and it was successfully recovered. The lower capsule was lost with the booster.References: 279, 439.

• Proton 8K82K launch vehicle completes its state trials tests and is accepted into service. Nation: USSR. Remarkably, due to continuing failures, the 8K82K did not satisfactorily complete its state trials until its 61st launch (Salyut 6 / serial number 29501 / 29 September 1977). Thereafter it reached a level of launch reliability comparable to that of other world launch vehicles.

• Salyut 6 Nation: USSR. Program: Salyut 6. Payload: Zarya s/n 125 s/n 5L. Mass: 19,824 kg (43,704 lb). Class: Manned. Type: Space station. Spacecraft: Salyut 6. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 237 km (147 mi). Inclination: 51.60 deg. Period: 88.70 min. COSPAR: 1977-097A. USAF Sat Cat: 10382. Duration: 1,763.71 days. Decay Date: 1982-07-29. Conduct of scientific and technical research and experiments; further testing of station design, on-board system and equipment. Soyuz 25 docking unsuccessful. EVA 20 Dec 1977 to examine forward docking port (no damage). EVA 29 July 1978 to retrieve externally mounted experiments (micrometeorites, biopolymers, radiation plates, materials tests). Soyuz 33 failure to dock due to propulsion failure April 1979. Soyuz 34 launched unmanned to provide replacement vehicle June 1979. EVA August 15 to dislodge 10 m diameter KRT-10 radio telescope from aft docking collar. Repair mission Soyuz T-3 December 1980 (temperature control hydraulics). Repair mission Soyuz T-4 March 1981 (stuck solar array). Salyut ejected a module on May 31 (perhaps retained Soyuz Orbital Module). Kosmos 1267 docks 19 June 1981. Commanded to reentry using Kosmos 1267 propulsion system over Pacific July 29 1982.Additional Details: Salyut 6(2186). References: 1, 2, 5, 6, 67, 274.

• Cosmos 997 Nation: USSR. Program: Almaz. Payload: TKS VA s/n 102L. Mass: 4,250 kg (9,360 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS VA . Agency: MOM. Perigee: 200 km (120 mi). Apogee: 230 km (140 mi). Inclination: 51.60 deg. Period: 88.70 min. COSPAR: 1978-032A. USAF Sat Cat: 10770. Decay Date: 1978-03-30. Flight: Cosmos 997. Given the on-pad explosion of the LVI-2 launch attempt, plans to crew the upper VA re-entry capsule in the next test was abandoned. LVI-3 (VA's 102P and 102L / Cosmos 997 and Cosmos 998) was launched unmanned four months behind the original schedule. Both capsules were recovered after one orbit. One source indicates that one of the capsules was 009P, on its third launch and second flight to orbit. This was said to have demonstrated the multiple re-entry capability of the heat shield and the first planned reuse of a spacecraft (Gemini 2 was refurbished and reflown as MOL-1 in the 1960's, but was not designed for that purpose).References: 1, 2, 5, 6, 67, 274, 439.

• Cosmos 998 Nation: USSR. Program: Almaz. Payload: TKS VA s/n 102P. Mass: 4,250 kg (9,360 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS VA. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 230 km (140 mi). Inclination: 51.60 deg. Period: 88.70 min. COSPAR: 1978-032B. USAF Sat Cat: 10771. Decay Date: 1978-03-30. Dual reentry test of two TKS-VA capsules. Recovered March 30, 1978 after one orbit. References: 1, 2, 5, 6, 67, 274, 439.

• Nation: USSR. Program: Almaz. Payload: TKS VA s/n 008. Class: Manned. Type: Spacecraft. Spacecraft: TKS VA . USAF Sat Cat: 11362. Decay Date: 1979-05-23. References: 1, 2, 5, 6, 67, 274, 439.

• Cosmos 1100 Nation: USSR. Program: Almaz. Payload: TKS VA s/n 102P. Mass: 4,250 kg (9,360 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS VA . Agency: MOM. Perigee: 193 km (119 mi). Apogee: 222 km (137 mi). Inclination: 51.60 deg. Period: 88.60 min. COSPAR: 1979-042A. USAF Sat Cat: 11362. Duration: 0.0600 days. Decay Date: 1979-05-23. Flight: Cosmos 1100. The Proton launch vehicle that shut down on the original LVI-4 launch attempt was undamaged, and just a month later, with a switch of payload, LVI-4 was orbited as Cosmos 1100 and 1101. The pair launched were the 102P/102L twins from LVI-3. One capsule failed when the automatic system suffered an electrical distribution failure and it did not land correctly, spending two orbits in space, while the other landed as planned after one orbit. The launch again successfully demonstrated the reusability of the VA capsule. Plans to launch the upper capsule manned were scrubbed due to the inability to get two consecutive failure-free launches of the Proton/TKS-VA.References: 1, 2, 5, 6, 67, 274, 439.

• Cosmos 1101 Nation: USSR. Program: Almaz. Payload: TKS VA s/n 102L. Mass: 4,250 kg (9,360 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS VA. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 222 km (137 mi). Inclination: 51.60 deg. Period: 88.60 min. COSPAR: 1979-042B. USAF Sat Cat: 11363. Decay Date: 1979-05-23. Test of TKS-VA manned capsule. Two satellites launched by a single rocket. References: 1, 2, 5, 6, 67, 274, 439.

• Cosmos 1267 Nation: USSR. Program: Almaz. Payload: TKS s/n 16301. Mass: 19,000 kg (41,000 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS . Agency: MOM. Perigee: 192 km (119 mi). Apogee: 259 km (160 mi). Inclination: 51.60 deg. Period: 88.90 min. COSPAR: 1981-039A. USAF Sat Cat: 12419. Duration: 459.91 days. Decay Date: 1982-07-29. TKS space station ferry. Flown unmanned to the Salyut 6 space station after the Almaz military station program was cancelled. Capsule recovered 24 May 1981. Docked with Salyut 6 on June 19 at 10:52 AM MT after 57 days autonomous flight. Deorbited and destroyed with Salyut July 29, 1982.Additional Details: Cosmos 1267(2689). References: 1, 2, 5, 6, 67, 274, 439.

• Salyut 7 Nation: USSR. Program: Salyut 7. Payload: Zarya s/n 125-2. Mass: 18,900 kg (41,600 lb). Class: Manned. Type: Space station. Spacecraft: Salyut 7. Agency: MOM. Perigee: 279 km (173 mi). Apogee: 284 km (176 mi). Inclination: 51.60 deg. Period: 90.20 min. COSPAR: 1982-033A. USAF Sat Cat: 13138. Duration: 3,215.34 days. Decay Date: 1991-02-07. Second Soviet replenishable long-duration ‘civilian’ space station. Objectives: Continuation of scientific research on board manned space complexes in the interests of science and the Soviet national economy; testing of advanced systems and apparatus for orbital stations. Continuation of the scientific research in progress on board manned space complexes in the interests of science and the national economy; testing of advanced systems and apparatus for orbital stations. Although of the same design as Salyut 6, technical breakdowns throughout its life made Salyut 7 a much less productive station. Replaced finally by Mir. Two different TKS resupply craft, originally designed for the Almaz military station, docked with Salyut 7 to provide a larger complex. With the cancellation of Almaz, a large proportion of the experiments carried out on board had military objectives. As of January 1990 out of fuel, unable to manoeuvre, uncontrolled re-entry expected in three to four years. Re-entered in 1991 with 70 kg fuel remaining over Argentina. Controllers attempted to control impact point (set for Atlantic Ocean) by setting Salyut 7/Kosmos 1686 assembly into a tumble. This however failed and Salyut 7 re-entered February 7, 1991 04:00 GMT. Many fragments fell on the town of Capitan Bermudez, 25 km from Rosario and 400 km from Buenos Aires, Argentina. At 1 am local time the sky was lit up with hundreds of incandescent meteors travelling from Southwest to Northeast. At dawn the inhabitants discovered numerous metal fragments, which seemed to have fallen in distinct groups at various locations in the city. Luckily no one was hurt in the metallic shower.Additional Details: Salyut 7(2822). References: 1, 2, 5, 6, 67, 274, 299.

• Iskra 2 Nation: USSR. Program: Salyut 7. Payload: RK-02. Mass: 28 kg (61 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Iskra. Agency: MOM. Perigee: 336 km (208 mi). Apogee: 345 km (214 mi). Inclination: 51.60 deg. Period: 91.40 min. COSPAR: 1982-033C. USAF Sat Cat: 13176. Decay Date: 1982-07-09. Deployed from Salyut 7 5/17/82. Launched from Salyut 7. Experiments in amateur radio communications. Launched into orbit from aboard the Salyut-7 orbital scientific station. References: 1, 2, 5, 6, 67, 274.

• Iskra 3 Nation: USSR. Program: Salyut 7. Payload: RK-03. Class: Communications. Type: Amateur Radio. Spacecraft: Iskra. Agency: MOM. Perigee: 349 km (216 mi). Apogee: 356 km (221 mi). Inclination: 51.60 deg. Period: 91.60 min. COSPAR: 1982-033AD. USAF Sat Cat: 13663. Decay Date: 1982-12-16. Flight: Salyut 7 EO-1. Launched from Salyut 7 airlock. Conduct of experiments in the field of amateur radiocommunications. References: 1, 2, 6.

• Cosmos 1443 Nation: USSR. Program: Almaz. Payload: TKS-M s/n 16401L. Mass: 20,000 kg (44,000 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS . Agency: MOM. Perigee: 194 km (120 mi). Apogee: 261 km (162 mi). Inclination: 51.60 deg. Period: 89.00 min. COSPAR: 1983-013A. USAF Sat Cat: 13868. Duration: 200.62 days. Decay Date: 1983-09-19. TKS manned ferry spacecraft from the cancelled Almaz OPS-4 mission. Flown unmanned to the Salyut 7 space station. Docked with Salyut 7 on 4 March 1983. Separated from Salyut 7 on 14 August. The VA re-entry capsule separated and the space station deorbited itself on September 19, 1983 at 0:28 GMT. The VA capsule continued in space for four more days, demonstrating autonomous flight, before successfully re-entering on 23 August 1983. Returned 350 kg of material from the station.Additional Details: Cosmos 1443(2958). References: 1, 2, 5, 6, 67, 274, 439.

• Cosmos 1686 Nation: USSR. Program: Almaz. Payload: TKS-M s/n 16501. Mass: 20,000 kg (44,000 lb). Class: Manned. Type: Spacecraft. Spacecraft: TKS . Agency: MOM. Perigee: 280 km (170 mi). Apogee: 284 km (176 mi). Inclination: 51.60 deg. Period: 90.20 min. COSPAR: 1985-086A. USAF Sat Cat: 16095. Duration: 1,958.80 days. Decay Date: 1991-02-07. Flight: Salyut 7 EO-4-1a, Salyut 7 EO-4-2. Modification of cancelled TKS manned ferry; docked with Salyut 7. All landing systems were removed from the VA re-entry capsule and replaced with military optical sensor experiments (infrared telescope and Ozon spectrometer). Burned up in the atmosphere and together with the Salyut 7 station over Argentina on February 7, 1991 04:00 GMT. Re-entered with unused 3 m diameter recoverable capsule of 2-3,000 kg mass, solid rocket motors, and cesium sensors.
  
  Maneuver Summary:
  172 km X 302 km orbit to 284 km X 319 km orbit. Delta V: 36 m/s
  281 km X 315 km orbit to 290 km X 336 km orbit. Delta V: 8 m/s
  290 km X 336 km orbit to 335 km X 352 km orbit. Delta V: 16 m/s
  Maneuvers after docking with Salyut 7:
  336 km X 353 km orbit to 338 km X 358 km orbit. Delta V: 1 m/s
  338 km X 358 km orbit to 358 km X 359 km orbit. Delta V: 5 m/s
  331 km X 333 km orbit to 333 km X 385 km orbit. Delta V: 14 m/s
  333 km X 385 km orbit to 332 km X 468 km orbit. Delta V: 23 m/s
  332 km X 468 km orbit to 466 km X 468 km orbit. Delta V: 37 m/s
  466 km X 468 km orbit to 470 km X 475 km orbit. Delta V: 2 m/s
  470 km X 475 km orbit to 475 km X 475 km orbit. Delta V: 1 m/s
  Total Delta V: 143 m/s
  Officially: Testing the equipment, assemblies and design components of a satellite in various modes of flight, including joint flight with the Salyut-7 station.References: 1, 2, 5, 6, 67, 274, 439.

• Mir Nation: USSR. Program: Mir. Payload: Mir s/n 127-01. Mass: 20,100 kg (44,300 lb). Class: Manned. Type: Space station. Spacecraft: Mir . Agency: MOM. Perigee: 387 km (240 mi). Apogee: 395 km (245 mi). Inclination: 51.60 deg. Period: 92.40 min. COSPAR: 1986-017A. USAF Sat Cat: 16609. Decay Date: 2001-03-23. The core module of Russia's new space station was placed in an initial orbit of 172 x 301 km. It was established in its operational orbit on 6 March. It passed just 10 km from Salyut 7 on 8 March. First use of the geosynchronous Luch relay sattelite for communications with the station was on 29 March. Equipment launched with the core module included:

  • Splav-2 crystal growth facility
  • Zona zone melt facility
  • Kashtan electrophoresis unit
  • Bulgarian Rozhen photometer
  • Spektr-256 and MKS-M spectrometers
  • Pion-M multipurpose physics unit (41 kg)
  • Biryuza semiconductor materials unit
  • -Ruchei electrophoresis installation
  • Yantar metal coating equipment
  • Mariye magnetic spectrometer
  • Korund furnace (136 kg)

  Total costs of Mir from February 1986 through return of Soyuz TM-9 in April 1989 were given as 1.471 billion rubles. This sum ncluded Mir, Kvant, all Soyuz and Progress spacecraft, and 2 new modules. As of April 1989 50% of the scientific equipment was inoperable and the interior was cramped due to lack of extension modules. Electric power supply problems were first reported in April 1989 (batteries would not hold charge from panels). Mass 27,300 kg as of January 1990. Complex mass with Kvant-2 65,790 kg; with Kristall, Soyuz TM, and Progress M, 89,990 kg.Additional Details: Mir(3425). References: 1, 2, 5, 6, 67, 274.

• Almaz-T s/n 303 Failure Nation: USSR. Program: Almaz. Payload: Almaz-K s/n 303. Mass: 18,550 kg (40,890 lb). Class: Surveillance. Type: Radarsat. Spacecraft: Almaz-T. Agency: UNKS. COSPAR: F861129A. Decay Date: 1986-12-29. In the second half of 1986 the first Almaz-T s/n 303 was readied for launch. General V V Favorskiy ordered it to be completed and launched with a full-up lab module in place of trials equipment. Unfortunately did not reach orbit. References: 5, 274.

• Kvant 1 Nation: USSR. Program: Mir. Payload: 37KE s/n 010 / 77KE s/n 16601. Mass: 20,000 kg (44,000 lb). Class: Manned. Type: Space station. Spacecraft: Kvant. Agency: MOM. Perigee: 385 km (239 mi). Apogee: 393 km (244 mi). Inclination: 51.60 deg. Period: 92.30 min. COSPAR: 1987-030A. USAF Sat Cat: 17845. Duration: 2,586.99 days. Decay Date: 2001-03-23. Flight: Mir EO-2, Mir LD-1. MIR module; high energy observatory. Docked with Mir. Rendezvous with Mir 5 April; soft dock 9 April; EVA on 11 April to remove fabric strip from docking apparatus and hard dock; jettisoned service module on 12 April at 22:18
  
  Maneuver Summary:
  168 km X 278 km orbit to 172 km X 300 km orbit. Delta V: 7 m/s
  169 km X 296 km orbit to 172 km X 314 km orbit. Delta V: 5 m/s
  170 km X 313 km orbit to 297 km X 345 km orbit. Delta V: 46 m/s
  298 km X 344 km orbit to 345 km X 364 km orbit. Delta V: 18 m/s
  Service Module only, after undocking with Mir:
  345 km X 364 km orbit to 341 km X 363 km orbit. Delta V: 1 m/s
  340 km X 361 km orbit to 383 km X 406 km orbit. Delta V: 24 m/s
  Total Delta V: 101 m/s
  Officially: Extra-atmospheric astronomic research and resolution of a number of problems with scientific and economic applications. References: 1, 2, 5, 6, 67, 274.

• FSB Nation: USSR. Program: Mir. Payload: FSB No. 16601. Spacecraft: Kvant. Agency: MOM. Perigee: 380 km (230 mi). Apogee: 404 km (251 mi). Inclination: 51.60 deg. Period: 92.40 min. COSPAR: 1987-030C. USAF Sat Cat: 17851. Decay Date: 1988-08-25. Flight: Mir EO-2, Mir LD-1. References: 279.

• Cosmos 1870 Nation: USSR. Program: Almaz. Payload: Almaz-K s/n 304. Mass: 18,550 kg (40,890 lb). Class: Surveillance. Type: Radarsat. Spacecraft: Almaz-T. Agency: MOM. Perigee: 263 km (163 mi). Apogee: 278 km (172 mi). Inclination: 71.90 deg. Period: 89.90 min. COSPAR: 1987-064A. USAF Sat Cat: 18225. Duration: 734.00 days. Decay Date: 1989-07-29. First flight of Almaz radars imaging satellite taken out of mothballs after death of Ustinov. At the beginning of 1987 it was decided not to man the Almaz-T, instead operate it in a fully automatic mode. Thus the final Almaz cosmonaut training group was disbanded. Cosmos 1870 conducted remote sensing of the earth's surface, oceans and seas in the interests of various branches of science and the economy. Its side-looking radar had a 20-25 m ground resolution and functioned throughout its two year service life.References: 1, 2, 5, 6, 67, 274.

• Kvant 2 Nation: USSR. Program: Mir. Payload: 77KSD s/n 17101. Mass: 19,565 kg (43,133 lb). Class: Manned. Type: Space station. Spacecraft: Kvant-2. Agency: MOM. Perigee: 388 km (241 mi). Apogee: 397 km (246 mi). Inclination: 51.60 deg. Period: 92.40 min. COSPAR: 1989-093A. USAF Sat Cat: 20335. Duration: 1,615.45 days. Decay Date: 2001-03-23. Flight: Mir EO-5. Mir expansion module. Scheduled docking 2 December delayed due to failure of solar panel to extend and failure of automatic rendezvous system. Faults corrected by ground control and docked with Mir December 6, 1989 at 12:21 GMT. Transferred to lateral port December 8.
  Officially: Delivery to the Mir orbital station of additional equipment and apparatus for the purpose of expanding the research and experiments conducted in the interests of science and the national economy.References: 1, 2, 5, 6, 67, 274.

• Kristall Nation: USSR. Program: Mir. Payload: 77KST s/n 17201. Mass: 19,640 kg (43,290 lb). Class: Manned. Type: Space station. Spacecraft: Kristall. Agency: MOM. Perigee: 388 km (241 mi). Apogee: 397 km (246 mi). Inclination: 51.60 deg. Period: 92.40 min. COSPAR: 1990-048A. USAF Sat Cat: 20635. Decay Date: 2001-03-23. Flight: Mir EO-6. Mir module; materials processing laboratory. Docked with Mir. Kristall: Mass: 19,500 kg. Mass on docking 17,200 kg. Length: 11. 9 m or 13. 73 m?. Solar array span 36 m. Diameter: 4. 35 m. Payload: 7,000 kg. Two compartments. Instrument-Payload Compartment contains food containers, and industrial processing units Krater 3, Optizon 1, Zona 02, and Zona 03. 0. 8 m hatch leads to Junction-Docking compartment. This contains spherical universal docker with two APAS-89 androgynous docking units. These will be used to dock with Buran shuttle and 1,000 kg X-ray telescope to be delivered by Buran in 1991. Third opening houses earth observation cameras.
  Launch originally planned for 30 March 1990. Delayed to April 18, then further delayed due to computer chip problems.
  Launched 31 May 1990 12:33 GMT. Docking scheduled June 6 at 12:36 but delayed due to problem with one of Kristall's orientation engines. Docking successful 10 June at 12:47. On June 11 moved to side port. Work within module began 15 June.
  Spektr: Late 1991 launch. Remote sensing work. Occupies port opposite Kvant 2. Before this occurs Kristall solar arrays will be relocated to Kvant.
  Officially: Specialized module. Experimental-industrial production of semi-conducting materials; refinement of biologically active substances for the production of new medicinal preparations. Cultivation of crystals of different albumine compositions and hybridizatio n of cells. Conduct of astrophysical and technical experiments. References: 1, 2, 5, 6, 67, 274.

• Almaz 1 Nation: USSR. Program: Almaz. Payload: Almaz-K s/n 305. Mass: 18,550 kg (40,890 lb). Class: Surveillance. Type: Radarsat. Spacecraft: Almaz-T. Agency: MOM. Perigee: 337 km (209 mi). Apogee: 351 km (218 mi). Inclination: 72.70 deg. Period: 91.40 min. COSPAR: 1991-024A. USAF Sat Cat: 21213. Decay Date: 1992-10-17. Second flight of Almaz radar imaging satellite. Surveyed the territory of the Soviet Union and of other countries for purposes of geology, cartography, oceanology, ecology and agriculture, and studied the ice situation at high latitudes. Launched eight months after its target date into an initial operational orbit of approximately 270 km with an inclination of 72.7 degrees, slightly higher than the 71.9 degrees inclination of Cosmos 1870. Unfortunately, the failure of one of the SAR antennas to deploy fully rendered that side inoperable. Returned images of 10 to 15 meter resolution through 17 October 1992. Its radiometer provided images of 10 to 30 km radiometer resolution over a 600 km swath. Its engines completed 760,000 firings during its 18 month service life.References: 1, 2, 5, 6, 67, 274.

• Mak 1 Nation: USSR. Program: Mir. Payload: Mak. Class: Earth. Type: Atmosphere. Spacecraft: Mak. Agency: MOM. Perigee: 377 km (234 mi). Apogee: 389 km (241 mi). Inclination: 51.60 deg. Period: 92.20 min. COSPAR: 1986-017DV. USAF Sat Cat: 21425. Decay Date: 1991-10-18. Flight: Mir EO-9, Mir LD-3. Deployed from MIR 6/17/91. Launched from Mir airlock. Investigation of features at the Earth's atmosphere. Launched with the Mir orbital station. References: 1, 2, 6.

• Spektr Nation: Russia. Program: Mir. Payload: 77KSO s/n 17301. Mass: 19,640 kg (43,290 lb). Class: Manned. Type: Space station. Spacecraft: Spektr. Agency: MOM. Perigee: 221 km (137 mi). Apogee: 335 km (208 mi). Inclination: 51.68 deg. Period: 89.78 min. COSPAR: 1995-024A. USAF Sat Cat: 23579. Decay Date: 2001-03-23. Flight: Mir EO-18. MIR experiment module. Docked to Mir Jun 1
  Officially: Docked to Mir Jun 1 References: 2, 5, 6, 67, 274.

• Priroda Nation: Russia. Program: Mir. Payload: 77KSI s/n 17401. Mass: 19,000 kg (41,000 lb). Class: Manned. Type: Space station. Spacecraft: Priroda. Agency: RKA. Perigee: 220 km (130 mi). Apogee: 347 km (215 mi). Inclination: 51.67 deg. Period: 89.89 min. COSPAR: 1996-023A. USAF Sat Cat: 23848. Decay Date: 2001-03-23. Flight: Mir NASA-1, Mir EO-21. LEO. Remote sensing module for Mir space station Docked with Mir Apr 26. References: 4, 6, 67, 274.

• Zarya Nation: USA. Program: ISS. Payload: FGB 77KM s/n 175-01. Class: Manned. Type: Space station. Spacecraft: ISS Zarya. Agency: NASA. Manufacturer: Khrunichev. Perigee: 397 km (246 mi). Apogee: 402 km (249 mi). Inclination: 51.60 deg. COSPAR: 1998-067A. USAF Sat Cat: 25544. This was the first launch in the assembly of the International Space Station. The Zarya FGB was funded by NASA and built by Khrunichev in Moscow under subcontract from Boeing for NASA. Its design from the TKS military station resupply spacecraft of the 1970’s and the later 77KS Mir modules. Zarya included a multiple docking adapter, a pressurised cabin section, and a propulsion/instrument section with a rear docking port. Initial orbit was 176 lm x 343 km x 51.6 degrees. By November 25 it had manoeuvred to a 383 km x 396 km x 51.7 degree orbit, awaiting the launch of Shuttle mission STS-88 which docked the Unity node to it.

• Zvezda Nation: Russia. Mass: 20,295 kg (44,742 lb). Class: Manned. Type: Space station. Spacecraft: ISS Zvezda. Agency: RAKA. Manufacturer: Khrunichev/Energiya. Perigee: 179 km (111 mi). Apogee: 332 km (206 mi). Inclination: 51.60 deg. COSPAR: 2000-037A. USAF Sat Cat: 26400. Years behind schedule, the Zvezda living module of the International Space Station, built and financed by Russia, finally reached orbit. Zvezda's initial orbit was 179 x 332 km x 51.6 deg. On July 14 the orbit was raised to 288 x 357 km. ISS was then in a 365 x 372 km orbit. After matching orbits with the ISS, Zvezda then became the passive docking target for the Russian-built, US-financed Zarya module already attached to the station. The Zarya/Unity stack docked with the Zvezda module at 00:45 GMT on July 26, forming the basic core of the International Space Station. A flood of NASA missions would follow to bring the station into operation.References: 4, 552, 554.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Kaesmann, Ferdinand, et. al., Journal of the British Interplanetary Society, "Proton - Development of A Russian Launch Vehicle", 1998, Volume 51, page 3.

• Clark, P S, Journal of the British Interplanetary Society, "Soviet Spacecraft Masses for Earth Orbital Programmes", 1985, Volume 38, page 19.

• Pesavento, Peter, Spaceflight, "Soviet Circumlunar Programme Hardware Revealed", 1994, Volume 36, page 390.

• Placard, TsNIIMASH Museum, .

• Placard, Baikonur Museum, .

• Mission Planner's Manual - Proton Commercial Launch Vehicle, Space Commerce Corporation, Houston, TX 1989.

• Afanasyev, Igor, Novosti kosmonavtiki, "35 let RN Proton", 1998, Issue 5, page 40.

• Vladimirov, A, Novosti kosmonavtiki, "Tablitsa zapuskov RN 'Proton' i 'Proton K'", 1998, Issue 10, page 25.