AKA: 8K82M;Proton M;Proton/Briz M. Status: Active. First Launch: 2001-04-07. Last Launch: 2018-12-21. Number: 94 . Payload: 21,000 kg (46,000 lb). Thrust: 21,000.00 kN (4,720,000 lbf). Gross mass: 712,800 kg (1,571,400 lb). Height: 53.00 m (173.00 ft). Diameter: 4.15 m (13.61 ft). Span: 7.40 m (24.20 ft). Apogee: 40,000 km (24,000 mi).
LEO Payload: 21,000 kg (46,000 lb). Payload: 4,500 kg (9,900 lb) to a GTO.
Stage Data - Proton 8K82K / Briz-M
Direct Broadcasting satellite. Maiden flight of new version of Proton. Launch delayed from August 2000, March 16 and April 6. Ekran-M No. 18 was a UHF television broadcasting satellite which was to be stationed at 99 deg E to provided television service to the Russian Far East. The satellite had a launch mass of around 2100 kg and was to replace the recently failed Ekran-M 15 that had been operating since October 1992 at the 105 deg-E longitude orbital slot.
The improved 3-stage Proton launch vehicle, with a new digital flight control system and enhanced first stage engines, delivered its payload section to a suborbital trajectory at 0356 GMT. The Briz-M upper stage then fired to enter a 200 km parking orbit. It appears that only two more burns were used to reach geostationary orbit: one at around 0440 GMT to enter a 200 x 35800 km GTO, after which the Briz-M toroidal drop tank was jettisoned, and one at around 1000 GMT, to circularize the orbit at geostationary altitude. Briz-M reportedly separated from its payload at 1031 GMT. Ekran was expected to reach its 99 deg E final location on around April 24. As of 5 September 2001 located at 99.27 deg E drifting at 0.009 deg E per day. As of 2007 Mar 11 located at 99.30E drifting at 0.005W degrees per day.
Moved from Ariane 5. The satellite was to provide a full range of telecommunications applications including digital DVB broadcasting, multimedia, broadband access and pay-per-use bandwidth for corporate networks over a large zone covering Europe and Africa, for a minimum of 12 years. As of 2007 Mar 10 located at 6.95E drifting at 0.006W degrees per day.
Communications satellite for SES Americom, equipped with Ku-band and Ka-band transponders. The Briz-M upper stage made three burns, then released the satellite on October 15 at 03:58 GMT into a 7132 x 35780 km x 18.6 deg orbit. AMC-15's on-board engine would be used to maneuver the spacecraft into its final geostationary orbit. As of 2007 Mar 11 located at 105.02W drifting at 0.003W degrees per day.
Provided United States direct-television broadcast coverage from the 101 degrees West longitude orbital slot. The satellite carried 16 high-power transponders for high-quality national digital video services. Purchased in October 2003 together with DirecTV-9S for a total price of $220 million for both. As of 2007 Mar 11 located at 100.77W drifting at 0.002W degrees per day.
Delayed from November, December 1 and 6. AMC-23 was to provide Ku-band multimedia and telecommunications services to Pacific rim countries over a planned 16 year life. A C-band payload was partly leased to the Japanese JSAT system. The Briz-M upper stage separated from the three-stage Proton launch vehicle at suborbital velocity, then conducted five engine burns before delivering the satellite to a 6193 km x 35,615 km x 18.5 deg geosynchronous transfer orbit at 11:48 GMT. The satellite would use its own Astrium S400 apogee engine to circularize the orbit at geostationary altitude. As of 2007 Mar 9 located at 171.97E drifting at 0.002W degrees per day.
Malaysian communications satellite, to be stationed at 91.5� East together with Measat 1, covering South Asia, Malaysia and Indonesia, and supplementing Measats 1 and 2 launched ten years earlier. The Proton booster released the satellite in a 416 x 35807 x 49.1 deg geosynchronous transfer orbit. The Boeing 601HP 3 axis stabilized spacecraft, had a design lifetime of 15 years. C-band 24 active transponders using 65-watt TWTAs; Ku-band 24 active transponders using 120-watt TWTAs . End of life power of 9.8 kW provided by two solar wings, each with 4 panels of triple-junction gallium arsenide solar cells. A 445N liquid apogee motor circularised the spacecraft in geosynchronous orbit, and 12 x 10 N bipropellant thrusters provided stabilization and stationkeeping. Length in orbit with solar panels deployed 26.2 m; width, with antennas deployed, 7.7 m; stowed diameter 3.8 m. Mass in geostationary orbit after apogee motor maneuver at beginning of life 3220 kg. As of 2007 Mar 11 located at 91.49E drifting at 0.012W degrees per day.
First launch of a pair of satellites, DirecTV 10 and 11, that will beam HDTV programs to 500 local markets from the company's primary orbital slot at 101 degrees west longitude. Acquisition and launch cost of $300 million per satellite; one ground spare also built.
Sirius 4 carried Ku-band and Ka-band communications payloads for Nordic, Baltic and East European communications. Three upper-stage burns placed Sirius 4 into a 6916 km x 35478 km x 17.4 deg geostationary transfer orbit. A series of maneuvers by the satellite using its own Leros engine maneuvered the satellite into geosynchronous orbit, stationed at 5 deg East.
The Briz M stage failed during its second burn, shutting down by 2 minutes 13 seconds early, leaving the satellite in a 770 km x 26447 km x 49.2 deg orbit. The spacecraft separated and raised this to 772 km x 35576 km x 49.0 deg, but operational geostationary orbit could not be attained and the satellite was a writeoff. AMC 14 had a total mass at launch of 4140 kg of which 2130 kg was propellant. The final orbit attained was an inclined orbit at geostationary altitude.
ASTRA 1M was positioned at Astra's prime 19.2 deg E position, providing pan-European coverage for Direct-to-Home services. Its entry into service would have allowed Astra to redeploy other satellites to its orbital position of 23.5� east. Total power consumption: 9.3 kW BOL, 8.3 kW EOL; Transponder capacity: 36/32 at 26 and 33 MHz; TWTA output power: 150 W; Channel capacity in10.7 - 12.75 GHz: 72 channels (bands D, B, E and F) .
Communications satellite delivered to an incorrect orbit when the Briz-M upper stage malfunctioned. The first two Briz-M burns, to a 173 km x 173 km, and then to a 270 km x 4998 km orbit, were successful. The third burn, at 00:52 GMT on 18 August, seemed to have gone wrong, with early separation of the wrap-around DTB propellant tank. A fourth burn left the payload stranded in a 694 km x 20242 km orbit. Cause was a timing error in the inertial platform, leading to incorrect orientiation of the stage during the later burns.
The satellite hosted an Intelsat C- and Ku-band commercial communications payload and a UHF communications payload for the Australian Defense Forces. First Proton launch to use a supersynchronous orbit to maximize use of booster propellant and conserve spacecraft fuel.
Communications satellite to provide Ku and C band communications services for the Americas, Europe and Africa from 53 deg W. First Star-2 class satellite to be directly inserted into geosynchronous orbit by its launch vehicle rather than using spacecraft liquid apogee motor burns from a transfer orbit.
Geosynchronous direct broadcast satellite leased to DISH Network for use in direct-to-Home services in the United States. Payload 32 Ku-band high-power transponders, stationed at 61.5 deg W. Carried a Ku-band television payload, had a dry mass of 3520 kg plus 3130 kg of propellant.
AM-5 used a Reshetnev Ekspress-2000 bus with C, Ku, Ka and L-band communications payloads developed in collaboration with the Canadian company MDA. The Briz-M made four burns to deliver Ekspress AM-5 to a sub-geostationary orbit of around 33,800 x 37,800 km x 0.18 deg. It used its on-board electric propulsion system (ion drive) to complete the trek to GEO.
Follow-on relay satellites, replacing the Luch (Altair) and Luch-2 (Gelios) satellites. Data relay channels pass on communications between other orbiting satellites to the ground. Also can receive COSPAS/SARSAT ground-based distress signals and relay them to ground stations, and collect and retransmit Planet-S System hydrometeorological data.
Launch vehicle suffered a third stage failure and the stage and payload reentered over China. Debris was found north of Harbin, in Heilongjiang province. The communications satellite payload, Ekspress AM-4R, had been built to replace a satellite lost in an earlier Proton failure; it used an Astrium Eurostar 3000 bus and was intended for the Russian domestic operator Kosmicheskaya Svyaz.
The final Briz-M burn was incomplete, leaving the communications satellite in an orbit with a 1373 min period - significantly below the planned orbit. Ekspress AM-6 had to reach its geosynchronous destination using extra xenon propellant from its own electric propulsion system at the cost of operational lifetime. Ekspress AM-6 orbit is 1373.2 min, 31307 x 37784 km x 0.7 deg; the Briz-M's auxiliary SOZ thrusters disposed of the stage into a 1512.4 min, 34984 x 39549 km x 1.0 deg orbit. Stationed in geosynchronous orbit at 140 deg east.
The European communications operator Eutelsat will use the satellite's 66 Ku-band transponders to increase performance at the 9 degrees East location. The satellite also carried a European Space Agency laser communications package, EDRS-A, as part of the European Data Relay System. EDRS will relay data from low-orbiting satellites, converting an optical communications signal from the satellite to a Ka-band radio downlink.
first ESA ExoMars mission. The main spacecraft on this mission was the ExoMars Trace Gas Orbiter (TGO), which entered Mars orbit to study its atmosphere. Attached to it was the Schiaparelli EDM lander. The TGO carried a color and stereo camera, IR and UV spectrometers, a neutron detector, and a communications relay package to support future surface missions. The combined spacecraft had a mass of 4332 kg. TGO was built by Thales/Cannes (formerly GTC/Sud Aviation) and EDM by Thales/Torino (formerly Fiat). Proton-M No. 93560 put the stack into a suborbital trajectory. The Briz-M upper stage, S/N 99560, separated at 0941 UTC and fired for 6 minutes to enter a 185 x 185 km x 51.5 deg parking orbit at 0947 UTC. After completing one orbit, a second burn at 1110 UTC raised the orbit to 250 x 5800 km. At the next perigee, at 1324 UTC, the orbit was raised to 696 x 21086 km and the Briz-M additional propellant tank was jettisoned. On completing this orbit, the fourth burn began at 1948 UTC to propel the vehicle to escape velocity. ExoMars TGO/EDM separated from the Briz-M at 2013 UTC in a hyperbolic Earth escape orbit (C3 = 13.78 km**2/s**2). The ExoMars spacecraft entered the Martian gravitational Hill sphere at 0110 UTC Oct 16, and at 1442 UTC Oct 16 split into the separate TGO (Trace Gas Orbiter) and EDM (Entry-Descent-Landing Demonstrator Module) vehicles. TGO made an insertion burn on Oct 19 from 1304 to 1523 UTC, entering a 4-day-period, 346 x 95228 km x 9.7 orbit deg around Mars.
ExoMars-2016 mass breakdown as follows:
Schiaparelli
EDM Surface Platform 280 kg
SP hydrazine 46 kg
Front Shield 200 kg?
Back Cover 54 kg?
Parachute system 20 kg?
-------------------------------------
EDM total 600 kg
TGO spacecraft 1365 kg (including 41 kg separation assembly)
TGO propellant 2367 kg
-------------------------------------
ExoMars-2016 launch total 4332 kgThe Schiaparelli EDM was the EDL Demonstrator Module, where EDL was "Entry, Descent and Landing". EDM consisted of an aeroshell containing the EDM Surface Platform (ESP, a triply-nested three-letter-acronym proving that ESA can compete with NASA in the TLA race). EDM attempted o land on the surface as a technology demonstration, and carried a small meteorology payload. The EDM separated from TGO three days before Mars arrival and entered the Martian atmosphere on a hyperbolic trajectory towards a landing site at 6.1W 1.9S in Meridiani Planum. After entry a parachute slowed the vehicle, the back cover and forward shield were jettisoned, and thrusters slowed the ESP further. The ESP underside consisted of a crushable structure to absorb impact with the surface. In the event, Schiaparelli approached on a 62 x -13982 km x 8.2 deg hyperbola and entered the Martian atmosphere at 1442 UTC at a speed of 5.86 km/s and an angle of -11.9 degrees. During descent, data was relayed to Mars orbiting spacecraft for later retransmission as well as sent on a live link picked up by the GMRT radio telescope near Pune, India.Schiaparelli survived the entry and deployed its parachute 4 minutes later at an altitude of 11 km. The heatshield was jettisoned 30 seconds later, and at 1447 UTC the parachute and attached backshell were separated at an altitude of 1.3 km over the Meridiani Planum landing site at 6.11W 2.07S. It appeared that the parachute / backshell separated 15 seconds earlier than expected. The thrusters fired for only 3 seconds, and the lander transitioned to landing mode while still well above the surface. A free fall of 19 seconds ensued, followed by a high speed (hundreds of km/hr) impact. At this point communications from the lander ceased. MRO imaged the EDM lander's impact scar at 6.11W 2.07S. The parachute was 0.16 km E 0.91km S of the lander.
Satellite with the DirecTV Latin America 2 (DLA-2) Ku-band payload was launched into a supersynchronous transfer orbit. The Proton second stage suffered an early shutdown of one of its 4 engines, leaving the vehicle 28m/s slow at stage 3 separation. Fortunately the Briz-M stage was able to correct the problem by adjusting its burn times and delivered the satellite to the correct orbit.
See Kosmos 2533 (Blagovest 13L). Blagovest military communications satellite. Some reports suggested a problem with the final Briz-M burn, but on December 29 it was shown by US tracking in a 35421 x 35802 km x 0.2 deg orbit drifting over 77E.
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