Russian earth weather satellite. One launch, 1994.10.31. Elektro was to be the geostationary component of a third generation Soviet meteorological system. Following extended development, it flew only once, in 1994.
The troubled spacecraft could not be put into use, and the whole project was finally cancelled.
On 16 December 1972 the VPK Military-Industrial Commission ordered development of a third generation meteorological system. This used the Planeta-S sensor package in the non-co-orbital Meteor-3 system plus the geostationary system Elektro, which was to begin tests in 1982. The draft project for the Planeta-S was completed in 1979, followed by detailed design in May 1980. A 1981 resolution called for a Planeta unified meteorological system. This was developed at VNIIEM MEP by N N Sheremtyevskiy and Yu V Trifonov. Development of the Elektro component ran into enormous obstacles in the period 1983-1987, with a mock-up not begin completed until 1989. Only then were drawings for a flight article completed. Elektro's numerous delays were due to both equipment and software problems, and the project went through two heads of development (Andronik Iosifiyan and Vladimir Adasko). There was finally only a single launch of Elektro, in 1994. The troubled spacecraft could not be put into use. The whole project was finally cancelled, the official reason being the incompetent head of development at VNIIEM.
In the west Elektro was designated the Geostationary Operational Meteorological Satellite (GOMS) system. Originally publicized for a maiden flight in 1978-1979, GOMS was known to suffer both technical and budgetary problems. The objectives of the program, as stated in 1991, were as follows:
- to acquire, in real time, television images of the Earth surface and cloud within a radius of 60 degrees centered at the sub-satellite point in the visible and IR regions of the spectrum;
- to measure temperature profiles of the Earth surface (land and ocean) as well as cloud cover;
- to measure radiation state and magnetic field of the space environment at the geostationary orbital altitude;
- to transmit via digital radio channels television images, temperature and radiation and magnetometric information to the main and regional data receiving and processing centers;
- to acquire information from Soviet and International data collection platforms (DCPs), located in the GOMS radio visibility, and to transmit the obtained information to the main and regional data and process-centers;
- to retransmit the processed meteorological data in the form of facsimile or alphanumeric information from the receiving station and processing centers to the independent receiving stations via satellites;
- to provide the exchange of high-speed digital data (retransmissions via the satellite) between the Main and regional centers of the USSR State Committee for Hydrometeorology;
- to call for the data collection platforms` to transmit the information to the satellite.
The GOMS network was to consist of three spacecraft spaced 90 degrees apart in the geostationary ring: at 14 degrees W, 76 degrees E, and 166 degrees E. Each 2.6-metric-ton spacecraft would have a payload capacity of 650-900 kg with an estimated operational lifetime of at least three years.
The satellite was 3-axis-stabilised and received a maximum of 1.5 kW (900 W for the payload) produced by two rectangular solar arrays. Twelve communications channels linked the spacecraft to the receiving and processing centers, the independent data receiving centre, and the data collection platforms. The main data receiving and processing centre was in the Moscow region while two regional centers were located at Tashkent and Khabarovsk.
The Elektro satellite equipment suite for the first mission did not include the planned 6 to 7 micrometer scanning radiometer. The telephotometer was limited to a total of 24 frames per day (each framing session lasts 30 minutes of which 15-20 minutes was imaging time), and only 4-5 frames could be successively taken at the 30 minute per-frame imaging rate. This high frame rate would normally were employed around 0000 and 1200 GMT, in part, to permit the calculation of wind speed and direction data. DCP information was to be collected and transmitted at three-hour intervals each day, i.e., 0300 GMT, 0600 GMT, etc.
AKA: 11F652; GOMS.
More... - Chronology...
Gross mass: 2,580 kg (5,680 lb).
First Launch: 1994.10.31.
Number: 1 .
Proton The Proton launch vehicle has been the medium-lift workhorse of the Soviet and Russian space programs for over forty years. Although constantly criticized within Russia for its use of toxic and ecologically-damaging storable liquid propellants, it has out-lasted all challengers, and no replacement is in sight. More...
Associated Launch Vehicles
Proton The Proton launch vehicle has been the medium-lift workhorse of the Soviet and Russian space programs for over forty years. Although constantly criticized within Russia for its use of toxic and ecologically-damaging storable liquid propellants, it has out-lasted all challengers, and no replacement is in sight. Development of the Proton began in 1962 as a two-stage vehicle that could be used to launch large military payloads or act as a ballistic missile with a 100 megaton nuclear warhead. The ICBM was cancelled in 1965, but development of a three-stage version for the crash program to send a Soviet man around the moon began in 1964. The hurried development caused severe reliability problems in early production. But these were eventually solved, and from the 1970's the Proton was used to launch all Russian space stations, medium- and geosynchronous orbit satellites, and lunar and planetary probes. More...
Proton-K/DM-2 Russian orbital launch vehicle. This improved four stage version uses the Block DM-2 / 11S861 fourth stage, which has its own guidance unit. This reduces payload but does not require the spacecraft's guidance system to provide steering commands to booster. Replaced the original Block DM / 11S86 version from 1982 to 1995. Used for launch of Glonass navigation satellites into medium earth orbit; and launch of Luch, Ekran-M, Potok, Raduga, Gorizont, Raduga-1, Elektro, and Gals communications satellites into geosynchronous orbit. Commercial version with Saab payload adapter-seperation system for Western payloads was dubbed 'Block DM1'. More...
Associated Manufacturers and Agencies
MOM Russian agency overseeing development of spacecraft. Ministry of General Machine Building (Moskva, Russia), Moscow, Russia. More...
VNIIEM Russian manufacturer of spacecraft. VNII Elektromekhaniki (Russian abbreviation for All-Union Scientific-Research Institute for Electro-Mechanics), Russia. More...
McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: here.
Kaesmann, Ferdinand, et. al., "Proton - Development of A Russian Launch Vehicle", Journal of the British Interplanetary Society, 1998, Volume 51, page 3.
Voevodin, Sergey A, "Sergey A. Voevodin's Reports", VSA072 - Space Apparatus, Web Address when accessed: here.
Johnson, Nicholas L; and Rodvold, David M, Europe and Asia in Space 1993-1994, USAF Phillips Laboratory, Kirtland AFB, NM 80907, 1995..
Vladimirov, A, "Tablitsa zapuskov RN 'Proton' i 'Proton K'", Novosti kosmonavtiki, 1998, Issue 10, page 25.
Melnik, T G, Voenno-Kosmicheskiy Siliy, Nauka, Moscow, 1997..
Associated Launch Sites
Baikonur Russia's largest cosmodrome, the only one used for manned launches and with facilities for the larger Proton, N1, and Energia launch vehicles. The spaceport ended up on foreign soil after the break-up of Soviet Union. The official designations NIIP-5 and GIK-5 are used in official Soviet histories. It was also universally referred to as Tyuratam by both Soviet military staff and engineers, and the US intelligence agencies. Since the dissolution of the Soviet Union the Russian Federation has insisted on continued use of the old Soviet 'public' name of Baikonur. In its Kazakh (Kazak) version this is rendered Baykonur. More...
1972 December 16 -
- Elektro, Meteor-3 weather satellites authorised - .
Nation: USSR. Spacecraft: Elektro; Meteor-3. Military-Industrial Commission (VPK) Decree 'On establishment of the Planeta-S weather satellite system' was issued. The resolution ordered development of a third generation system. This used the Planeta-S sensor package in the non-co-orbital Meteor-3 system plus the geostationary system Elektro, which was to begin tests in 1982. Elektro suffered numerous delays due to equipment and software problems. Flight trials of Meteor-3 did not begin until 1984, and there was only a single launch of Elektro, in 1994.
1994 October 31 -
14:30 GMT - .
. Launch Complex
: Baikonur LC81/23
. LV Family
. Launch Vehicle
. LV Configuration
: Proton-K/DM-2 361-02.
- Elektro 1 - .
Payload: Elektro s/n 1L. Mass: 2,850 kg (6,280 lb). Nation: Russia. Agency: MOM. Class: Earth. Type: Weather satellite. Spacecraft: Elektro . Completed Operations Date: 1998-09-01 . USAF Sat Cat: 23327 . COSPAR: 1994-069A. Apogee: 35,799 km (22,244 mi). Perigee: 35,782 km (22,233 mi). Inclination: 4.7000 deg. Period: 1,436.30 min. Stationed at 76.61 deg E. Elektro 1 was finally launched on 31 October 1994, 15 years after its original public schedule. Malfunction of the local vertical sensor and the attitude control system delayed the positioning of the spacecraft at its intended location of 76 degrees E, but by early December Elektro 1 was on station. However problems with the local vertical sensor continued to plague the spacecraft, and useful images were not available. Stayed in geosynchronous orbit at 76 deg E in 1995-1998 before being shut down. As of 4 September 2001 located at 71.89 deg E drifting at 0.069 deg E per day. As of 2007 Mar 10 located at 67.89E drifting at 0.000W degrees per day.
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