By January 1986 it was clear that the project, now three years behind schedule, had no prospect of completion due to problems in obtaining deliveries of equipment for Buran, numerous problems in assembling the orbiters and lack of manpower at Baikonur, and a general loss of management focus. Minister O D Bakhnov called large group of industry leaders to the cosmodrome to review measures to concentrate and accelerate the remaining work. Three 'Tiger Teams' were set up. The first, led by Semenov, was to finish the flight Buran orbiter and associated facilities in time for a third quarter 1987 launch. The second, led by B I Gubanov, was to finish the Energia launch vehicle and fly it, without the Buran mock-ups if necessary, at the earliest possible date. The third group, led by S S Banin, was to complete the assembly and launch facilities.

Having completed design and development work on Energia-launched nuclear-electric upper stages, NPO Energia studied a manned Mars project again. The study revamped the 1969 studies to include launch by Energia and use of two reactors in the place of one and the use of tested systems developed on orbital stations.

Manned seven crew. Launched Satcom K1. Payloads: Deploy SATCOM (RCA-Satellite Communi-cations) Ku-1 with Payload Assist Module (PAM)-D II. Materials Science Laboratory, Comet Halley Active Monitoring Experiment (CHAMP), Hitchhiker (HH) Goddard (G)-1, thirteen getaway specials (GAS), student experiment, Initial Blood Storage Equipment (lBSE), Characterization of Space Motion Sickness (SMS).

The Material Science Laboratory was a carrier system designed to utilize the residual space of the Shuttle cargo bay. Based on the multi-purpose experiment support structure (MPESS) carrier, it offered a full complement of power, data, and thermal control services to payloads mounted on it.

Stationed at 335 deg. E. Provision of telephone and telegraph radiocommunications and television broadcasting. Positioned in geosynchronous orbit at 25 deg W in 1986-1989; 170 deg W in 1989-1991 As of 28 August 2001 located at 163.25 deg W drifting at 5.255 deg W per day. As of 2007 Mar 10 located at 22.49E drifting at 5.257W degrees per day.

The Spartan series consists of low-cost, Shuttle-launched, short-duration, sounding-rocket-type payloads. The payloads were retrievable and reusable with a turnaround time of 6 to 9 months. Spartan operated as an autonomous sub-satellite, and the data was stored on an internal tape recorder. Pointing and stabilization were achieved by an attitude control system capable of three-axis stabilized pointing to any target within +/- 3 arc-minutes. The main objective of this spacecraft was to obtain UV spectra of the coma and tail of Comet Halley in January 1986 shortly before its perihelion. This spacecraft was lost when Space Shuttle Challenger exploded on launch.

By January 1986 it was clear that the project, now three years behind schedule, had no prospect of completion due to problems in obtaining deliveries of equipment for Buran, numerous problems in assembling the orbiters and lack of manpower at Baikonur, and a general loss of management focus. Minister O D Bakhnov called a large group of industry leaders to the cosmodrome to review measures to concentrate and accelerate the remaining work. Three 'Tiger Teams' were set up. The first, led by Semenov, was to finish the flight Buran orbiter and associated facilities in time for a third quarter 1987 launch. The second, led by B I Gubanov, was to finish the Energia launch vehicle and fly it, without the Buran mock-ups if necessary, at the earliest possible date. The third group, led by S S Banin, was to complete the assembly and launch facilities.

The first Buran payload, 37KB module s/n 37070, arrived in Baikonur. The 37KB modules, similar to the Kvant module of the Mir space station, were to be standard on the early Buran flights. 37KB-37070 itself primarily contained instrumentation to measure the performance of the orbiter and its structure on its first flight.

Second successful DFH-2 launch. Also designated STW-2, the satellite was positioned at 103 deg E. In comparison to the first two DFH-2's, a parabolic antenna reflector replaced the horn antenna. Operated in geosynchronous orbit at 103 deg E in 1986-1990. As of 3 September 2001 located at 102.75 deg E drifting at 0.030 deg W per day. As of 2007 Mar 10 located at 46.50E drifting at 0.019E degrees per day.

Stationed at 117 deg E. BS-2b (Yuri-2b). Domestic satellite broadcasting; development of broadcasting satellite technology. Launching organization NASDA. N launch vehicle flight no 14. Launch time 0755 GMT. Positioned in geosynchronous orbit at 110 deg E in 1986-1991 As of 5 September 2001 located at 13.60 deg W drifting at 3.524 deg W per day. As of 2007 Mar 11 located at 77.04E drifting at 3.551W degrees per day.

The first Buran payload, 37KB module s/n 37070, is delivered by freight car. The 37KB modules, similar to the Kvant module of the Mir space station, were to be standard on the early Buran flights. 37KB-37070 itself primarily contained instrumentation to measure the performance of the orbiter and its structure on its first flight.

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: here....

Studied magnetic, electric, UV properties of auroral regions. Scientific satellite for the investigation of space plasma physics in the part of the magnetosphere close to the Earth, particularly in connection with the auroral phenomena. The nominal mission period is eight months but an extension can be envisaged. ST /SG/SER.E/167: The satellite Viking has ceased to function on 12 May 1987 due to a gradual degradation of its electrical power supply system. The satellite remains, however, in Earth orbit.

Mir Main Expedition EO-01. Epic repair mission. The crew, consisting of ship's commander L D Kizim and flight engineer V A Solovyov first docked with the Mir orbital station to conduct scientific and technical studies and experiments. Mir then maneuvered 17 April to match Salyut 7's orbit at 4000 km separation, then again on 4 May to catch up. After six weeks aboard Mir, Soyuz T-15 undocked on 5 May, then rendezvoused and manually docked with the inoperative Salyut 7 station. This was the only flight in history by a single spacecraft between two space stations. The Salyut-7 station was found to be ice bound and without electrical power. The crew repaired the station, regaining power, heat, and environmental control. The also removed experimental results left behind by last crew. Soyuz T-15 undocked Salyut 7 on 25 June, and redocked with Mir on 26 June, delivering 400 kg of scientific material from Salyut 7, including a multichannel spectrometer. Following further work aboard Mir, the crew landed on July 16, 1986 at 12:34 GMT. No crew ever revisited Salyut 7; it made an uncontrolled reentry over Argentina.

Unmanned supply vessel transporting sundry cargoes to the Mir orbital station. Docked with Mir on 21 Mar 1986 11:16:02 GMT. Undocked on 20 Apr 1986 19:24:08 GMT. Destroyed in reentry on 21 Apr 1986 00:48:30 GMT. Total free-flight time 2.27 days. Total docked time 30.34 days.

This was to be the first 20 second Energia main engine firing test. It was terminated at 2.58 seconds when the automatic control system detected a slow spool up of an engine turbine. In a the first attempt at a full-duration test helium leaks contaminated electro-hydraulic systems, leading to a situation where the tanks could not be drained. An engineering brigade had to work on the fuelled booster for 55 minutes, attach another helium tank, which led to successful de-fuelling of the vehicle.

Ku band communications satellite. Stationed at 70 degrees W. Positioned in geosynchronous orbit at 105 deg W in 1986-1992; 125 deg W in 1992-1997 As of 5 September 2001 located at 148.11 deg W drifting at 1.728 deg W per day. As of 2007 Mar 10 located at 2.39W drifting at 1.699W degrees per day.

Stationed at 105 deg W. Brazilsat 1 & 2 provide telecommunications services to Brazil. Canada's Spar Aerospace was awarded a $125 million contract to build, under license, two satellites based on Hughes' HS-376 design (similar to Anik D). Brazilsat 1 & 2 were the first two elements of Brazil's national Sistema Barasilero de Telecommunicacoes por Satelite (SBTS) network. Spacecraft: Based on Hughes HS-376, single antenna on despun platform, spin stabilised, hydrazine thrusters, body mounted solar cells provide 982 W BOL. Payload: 24 C-band transponders with 6 spares, 10 W TWTA, EIRP >34 dBW over most of Brazilian territory
Financial/Operational:
Contract issued in 1990 for 2 units HS-376W. B1-B2 have dedicated transponders for government use. Positioned in geosynchronous orbit at 70 deg W in 1986-1995; 92 deg W in 1995-1999 As of 4 September 2001 located at 62.91 deg W drifting at 0.007 deg W per day. As of 2007 Mar 7 located at 32.58W drifting at 2.263W degrees per day.

Stationed at 13.5 deg W. Continuation of the investigation of outer space; experimental retransmission of telephone and telegraph data in the centimetre band. Positioned in geosynchronous orbit at 14 deg W in 1986-1989 As of 3 September 2001 located at 0.26 deg W drifting at 0.077 deg E per day. As of 2007 Mar 9 located at 55.28W drifting at 0.287W degrees per day.

Replaced Molniya 3-23. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network and within the framework of international cooperation.

Unmanned supply vessel to Mir. Rendezvoused with Mir on 25 April, but problem with Mir's radio communication system delays docking until the next day. Docked with Mir on 26 Apr 1986 21:26:06 GMT. Undocked on 22 Jun 1986 18:25:00 GMT. Destroyed in reentry on 23 Jun 1986 15:41:01 GMT. Total free-flight time 3.96 days. Total docked time 56.87 days.

Tests of the orbiter's ODU engine unit uncovered an apparent defect in gaseous oxygen valves of the reaction control system. Although it threatened to delay flight of the Buran, it was eventually discovered to be a software problem and remedied within days.

Test of new Soyuz vehicle. Recovered May 30, 1986 6:49 GMT. Unmanned test of Soyuz TM. Docked with Mir May 23 1987. Undocked 29 May.
Officially: Comprehensive experimental testing of spacecraft in independent flight and jointly with the Mir orbital station.

Stationed at 99 deg E. Transmission of Central Television programmes to a network of receivers for collective use. Positioned in geosynchronous orbit at 99 deg E in 1986-1988 As of 5 September 2001 located at 80.69 deg W drifting at 13.420 deg W per day. As of 2007 Mar 9 located at 63.41W drifting at 13.419W degrees per day.

Stationed at 345 deg E. Provision of telephone and telegraph radiocommunications and television broadcasting. Positioned in geosynchronous orbit at 14 deg W in 1986-1989; 40 deg E in 1989-1990 As of 28 August 2001 located at 84.75 deg E drifting at 0.265 deg W per day. As of 2007 Mar 10 located at 45.79E drifting at 0.142E degrees per day.

Replaced Molniya 3-20. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network and within the framework of international cooperation.

Oceanographic. Acquisition of operational oceanographic information in the interests of various branches of the national economy of the USSR and international cooperation; continued trials of new types of informational and measurement apparatus and methods of remote sen sing of the earth's surface and atmosphere.

Further UKSS tests of Energia were conducted in preparation of a test launch without Buran. These were conducted using a dummy payload and solid rocket motors to simulate loads from the booster rockets. Following this vehicle 6SL was selected for the first actual launch. The launch vehicle used by itself without Buran was named Energia by Glushko only just before the launch.

Experimental Geophysical Payload; new launch vehicle test flight. EGS (Ajisai). Improvement of the accuracy of domestic geodetic triangulation network. Determination of accurate location of remote islands. Clarification of the relationship between Japanese geodetic system network and those of other areas of the world. L aunch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA.

Japanese Amateur Satellite. JAS-1 (Fuji). Amateur satellite communications. Development of amateur satellite technology. Launch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA. Fuji-OSCAR 12 was launched piggyback with a Japanese experimental geodetic satellite Ajisai (EGS). Weight 50 kg. 26-sided polyhedron, 40 x 40 x 47 cm. FO-12 was the first Japanese amateur satellite developed by the Japan Amateur Radio League (English version) with system design and integration performed at NEC. FO-12 was taken out of service November 5, 1989 because of battery failure.

The Ministry of Defence issued technical specifications on 1 September for an MVKS, a single-stage reusable aerospaceplane system. The MKVS was to provide effective and economic delivery to near-earth orbit; develop the technology for effective transatmospheric flight; provide super high-speed intercontinental transport, and fulfil military objectives in and from space.

Replaced Molniya 3-21. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network and within the framework of international cooperation.

Stationed at 36 deg E. Provision of telephone and telegraph radiocommunications and television broadcasting. Positioned in geosynchronous orbit at 45 deg E in 1986-1991; 34 deg E in 1991-1993. Raduga 19 performed an end-of-life maneuver in September, 1993. As of 28 August 2001 located at 160.57 deg E drifting at 6.520 deg W per day. As of 2007 Mar 10 located at 57.63W drifting at 6.529W degrees per day.

Tranist O-17 had been turned over to the National Air and Space Museum in 1976 and was displayed to the public for more than 8 years. In 1984, it was refurbished at APL and launched as the Polar Beacon Experiment and Auroral Research satellite to collect data for studying communications over the Earth's polar regions.

Stationed at 90 deg E. Provision of telephone and telegraph radiocommunications and television broadcasting. Positioned in geosynchronous orbit at 90 deg E in 1986-1991 As of 5 September 2001 located at 132.70 deg W drifting at 12.791 deg W per day. As of 2007 Mar 10 located at 94.81E drifting at 12.778W degrees per day.

Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 100 deg W in 1987-1999 Last known longitude (27 July 1999) 100.33 deg W drifting at 0.027 deg W per day.