| Zenit |
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Zenit was to be a modular new generation medium Soviet launch vehicle, replacing the various ICBM-derived launch vehicles in use since the 1960's (Tsiklon and Soyuz). A version of the first stage was used as strap-ons for the cancelled Energia heavy booster. But it was built by Yuzhnoye in the Ukraine; when the Soviet Union broke up planned large-scale production for the Soviet military was abandoned (Angara development was begun as an indigenous alternative). Launch pads were completed only at Baikonur; those at Plesetsk were never finished and are planned to be completed as Angara pads. However the vehicle found new life as a commercial launch vehicle, launched from a sea platform by an American/Ukrainian consortium. Zenit development began in March 1976 in accordance with the specifications of GUKOS-MO. The Chief designer was V F Utkin at KB Yuzhnoye, with V P Radovskiy at KB Energomash being responsible for the engines, V G Sergeyev at NPO Elektropribor being responsible for the guidance system. Work on the Zenit launch complex began in 1978. Trials of the first stage began in 1982 after a long and difficult development of the first stage engines (see the entry for the Energia launch vehicle for details). The first Zenit pad was ready in December 1983. Although the facilities were ready, the launch vehicles was held up continuing first stage engine problems. Former cosmonaut Gherman Titov was in charge of the state commission overseeing the trials. A series of 11 trials launches finally began on April 13 1985 and extended over the next two years, lofting a series of experimental payloads. In the spring of 1987 the state commission accepted the system for military use. They found that the automated launch system worked well and reliably, and the basic booster was accepted together with the Tselina-2 satellite. However much work remained to be done - construction of a second launch complex at Baikonur, qualification of a third stage for one tonne geostationary payloads, and construction of a third launch complex at Plesetsk for launch of payloads into sun-synchronous and polar orbits. The collapse of the Soviet Union a few years later ended these plans. The pads at Plesetsk were never completed. A three-stage version of Zenit did fly, but as a commercial vehicle from the Boeing Launch platform in the Pacific Ocean. Manufacturer: Yuzhnoye. Launches: 62. Failures: 10. Success Rate: 83.87%. First Launch Date: 1985-04-13. Last Launch Date: 2008-01-15. Launch data is: continuing.
Version: Zenit-2.
Two-stage version that continued to be used for launch of Russian military satellites tailored to it after the fall of the Soviet Union.
Launches: 35. Failures: 6. Success Rate: 82.86%. First Launch Date: 1985-04-13. Last Launch Date: 2004-06-10. LEO Payload: 13,740 kg (30,290 lb). to: 200 km Orbit. at: 51.40 degrees. Payload: 5,000 kg (11,000 lb). to a: sun synchronous, 800 km, 98.6 deg orbital trajectory. Associated Spacecraft: Badr, GFZ-1, Globalstar, Gurwin, Koltso, Kompas, Meteor-3M, Microsat SSTL, Okean-O, Orlets-2, Reflektor, Resurs-O1, Safir, Tselina-2, Tubsat, Uragan Space Interceptor, OK-M, VKK. Liftoff Thrust: 7,300.000 kN (1,641,100 lbf). Total Mass: 459,000 kg (1,011,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 57.00 m (187.00 ft). Launch Price $: 45.000 million. in: 1994 price dollars.
Zenit-2 11K77.05. Status: Retired 1998. Version with a dispenser for multiple Globalstar communications satellite launches.
Launches: 1. Failures: 1. First Launch Date: 1998-09-09. Last Launch Date: 1998-09-09. LEO Payload: 13,500 kg (29,700 lb). Liftoff Thrust: 7,259.000 kN (1,631,888 lbf). Total Mass: 459,000 kg (1,011,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 57.00 m (187.00 ft). Version:Zenit-3SL.
From the beginning of the program a Zenit-3 version was proposed for geosynchronous launches using the N1/Proton Block D third stage. This had the potential of replacing the Proton in the role of geosynchronous launcher. It was considered for launch from Australia / Cape York in the 1980's. Finally a joint US-Norwegian-Ukraininan-Russian consortium was formed to launch the three stage commercial Zenit from the Odyssey floating launch platform in the Pacific Ocean.
Launches: 25. Failures: 3. First Launch Date: 1999-03-28. Last Launch Date: 2008-01-15. LEO Payload: 5,000 kg (11,000 lb). Payload: 5,250 kg (11,570 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: FS-1300, HS 601 , HS 702. Liftoff Thrust: 7,300.000 kN (1,641,100 lbf). Total Mass: 471,000 kg (1,038,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 59.60 m (195.50 ft). Launch Price $: 90.000 million. in: 1999 price dollars.
Zenit-2SLB. Status: Active. Two-stage version of the Zenit-3SL booster developed for the Sea Launch program, modified for launch from ground facilities at Baikonur. Uses the common Zenit-2SB core vehicle with no upper stage.
Launches: 1. First Launch Date: 2007-06-29. Last Launch Date: 2007-06-29. LEO Payload: 12,030 kg (26,520 lb). to: 400 km Orbit. at: 51.60 degrees. Liftoff Thrust: 7,300.000 kN (1,641,100 lbf). Total Mass: 458,900 kg (1,011,700 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 57.35 m (188.15 ft). Version:Zenit-3SLB.
Version of the Zenit-3SL modified for launch from existing ground facilities at Baikonur, using the common Zenit-2SB core vehicle with an upper stage Block DM-SLB designed by RSC Energia (Russia) and a new payload fairing designed by NPO Lavochkin (Russia). The Sea Launch Board of Directors voted on September 30, 2003, to offer launch services from Baikonur Cosmodrome in Kazakhstan, in addition to its sea-based launches at the Equator. The new offering, Land Launch, was based on the collaboration of Sea Launch Company and Space International Services, of Russia, to meet the launch needs of commercial customers with medium weight satellites. The Land Launch system uses a version of the Sea Launch Zenit-3SL rocket, the Zenit 3SLB, to lift commercial satellites in the 2,000 to 3,500-kilogram range to GTO and heavier payloads to inclined or lower orbits. The three stages on the Zenit 3SLB were the same as those on the Sea Launch Zenit-3SL, with the only significant difference between two being the fairing. A two-stage configuration of the same rocket, the Zenit 2SLB, was also available for launching heavy payloads, or groups of payloads, to LEO. Payloads and vehicles would be processed and launched from existing Zenit facilities at the Baikonur launch site. The first Land Launch mission, carrying the PAS-11 satellite for PanAmSat, was scheduled for the second quarter of 2007.12 Expanding on its Sea Launch marketing efforts, Boeing Launch Services, Inc., managed marketing and sales for this new offering. Payload: 3,750 kg (8,260 lb). to a: Geosynchronous orbit trajectory. Liftoff Thrust: 7,300.000 kN (1,641,100 lbf). Total Mass: 471,000 kg (1,038,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 59.60 m (195.50 ft).
Zenit Chronology 1976 March 16 - Zenit launch vehicle authorised. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On the Creation of a Universal Space Missile Complex 11K77 'Zenit'--approval of work on the Zenit launcher' was issued. 1982 January - Problems with development of Buran booster rockets Spacecraft: Buran. Continued development problems with the booster rockets led to a management shake-up at Yuzhnoye in January 1982. By this time the project was several years behind schedule. The originally planned first flight in 1983 was obviously unattainable. 1985 April 13 - Baikonur -. FAILURE: Failure. R&D suborbital Zenit launch vehicle test failure Agency: UNKS. 1985 June 21 - 08:29 GMT - Baikonur LC45/1. Zenit launch vehicle test Agency: VKS. Perigee: 197 km (122 mi). Apogee: 338 km (210 mi). Inclination: 64.40 deg. Period: 89.90 min. Intended to be suborbital, but some debris reached orbit. Rocket debris decayed by 6/28/85. 1985 October 22 - 07:00 GMT - Baikonur LC45/1. Cosmos 1697 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 843 km (523 mi). Apogee: 853 km (530 mi). Inclination: 71.00 deg. Period: 101.90 min. First launch of new Tselina-2 ELINT satellite on Zenit-2 launch vehicle. 1985 December 28 - 09:16 GMT - Baikonur LC45/1. FAILURE: Second stage failed to ignite. Partial Failure. Cosmos 1714 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 160 km (90 mi). Apogee: 850 km (520 mi). Inclination: 71.00 deg. Period: 94.70 min. Tselina-2 ELINT satellite placed in unusable orbit due to second stage failure. 1986 July 30 - 08:30 GMT - Baikonur LC45/1. Cosmos 1767 Mass: 15,000 kg (33,000 lb). Agency: MO RF. Perigee: 194 km (120 mi). Apogee: 205 km (127 mi). Inclination: 64.90 deg. Period: 88.50 min. Investigation of the upper atmosphere and outer space. 1986 October 22 - 08:00 GMT - Baikonur LC45/1. Cosmos 1786 Mass: 15,000 kg (33,000 lb). Spacecraft: Koltso. Agency: MO RF. Perigee: 149 km (92 mi). Apogee: 1,054 km (654 mi). Inclination: 64.80 deg. Period: 96.70 min. Radar calibration mission. 1987 February 14 - 08:30 GMT - Baikonur LC45/1. Cosmos 1820 Mass: 15,000 kg (33,000 lb). Spacecraft: Orlets-2. Agency: MO RF. Perigee: 178 km (110 mi). Apogee: 250 km (150 mi). Inclination: 64.80 deg. Period: 88.80 min. Launch vehicle test. Mass model of Orlets-2 reconnaissance satellite. 1987 March 18 - 08:30 GMT - Baikonur LC45/1. Cosmos 1833 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 845 km (525 mi). Apogee: 855 km (531 mi). Inclination: 70.90 deg. Period: 101.90 min. 1987 May 13 - 05:40 GMT - Baikonur LC45/1. Cosmos 1844 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 844 km (524 mi). Apogee: 851 km (528 mi). Inclination: 70.90 deg. Period: 101.90 min. 1987 August 1 - 03:59 GMT - Baikonur LC45/1. Cosmos 1871 Mass: 15,000 kg (33,000 lb). Spacecraft: Uragan Space Interceptor. Agency: MO RF. Perigee: 168 km (104 mi). Apogee: 188 km (116 mi). Inclination: 97.00 deg. Period: 88.10 min. Considered by some observors as possible spite test of Uragan space interceptor boilerplate mass model, just prior to project cancellation. 1987 August 28 - 08:20 GMT - Baikonur LC45/1. Cosmos 1873 Mass: 15,000 kg (33,000 lb). Spacecraft: Uragan Space Interceptor. Agency: MO RF. Perigee: 175 km (108 mi). Apogee: 241 km (149 mi). Inclination: 64.80 deg. Period: 88.70 min. Considered by some observors as possible spite test of Uragan space interceptor boilerplate mass model, just prior to project cancellation. 1987 September - Uragan spaceplane allegedly cancelled Spacecraft: Uragan Space Interceptor. Uragan was said to have been cancelled before the first flight of the Buran shuttle. Possibly the cancellation of US Shuttle polar orbit military missions from Vandenberg after the Challenger explosion eliminated the space interceptor's mission. Or perhaps it never existed and was merely the subject of a very successful disinformation campaign. Adding even more confusion is that it is now known that at least two spaceplanes - Chelomei's LKS, for launch on Proton, and Molniya's OK-M, for launch on Zenit, were being designed concurrently with Buran. And the official history of the MiG OKB, states cryptically that after completion of the 105-11 flight tests development of the spaceplane continued.... 1988 May 15 - 09:20 GMT - Baikonur LC45/1. Cosmos 1943 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 837 km (520 mi). Apogee: 851 km (528 mi). Inclination: 71.00 deg. Period: 101.80 min. 1988 November 23 - 14:50 GMT - Baikonur LC45/1. Cosmos 1980 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 841 km (522 mi). Apogee: 849 km (527 mi). Inclination: 71.00 deg. Period: 101.80 min. 1990 May 22 - 05:14 GMT - Baikonur LC45/2. Cosmos 2082 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 838 km (520 mi). Apogee: 857 km (532 mi). Inclination: 71.00 deg. Period: 101.90 min. 1990 October 4 - Baikonur LC45/2. FAILURE: First stage engine exploded after 3 seconds. Tselina-2 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: UNKS. 1991 August 30 - 08:58 GMT - Baikonur LC45/1. FAILURE: Second stage exploded due to heating problems in main engine. Tselina-2 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: UNKS. 1992 February 5 - Baikonur LC45/1. FAILURE: Second stage malfunction due to heating problems in main engine. Tselina-2 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: UNKS. 1992 November 17 - 07:47 GMT - Baikonur LC45/1. Cosmos 2219 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 845 km (525 mi). Apogee: 854 km (530 mi). Inclination: 71.00 deg. Period: 101.90 min. 1992 December 25 - 05:56 GMT - Baikonur LC45/1. Cosmos 2227 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 845 km (525 mi). Apogee: 855 km (531 mi). Inclination: 71.00 deg. Period: 101.90 min. 1993 March 26 - 02:21 GMT - Baikonur LC45/1. Cosmos 2237 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 847 km (526 mi). Apogee: 855 km (531 mi). Inclination: 70.90 deg. Period: 102.00 min. 1993 September 16 - 07:36 GMT - Baikonur LC45/1. Cosmos 2263 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 845 km (525 mi). Apogee: 857 km (532 mi). Inclination: 70.90 deg. Period: 102.00 min. 1994 April 23 - 08:01 GMT - Baikonur LC45/1. Cosmos 2278 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 846 km (525 mi). Apogee: 857 km (532 mi). Inclination: 71.00 deg. Period: 102.00 min. 1994 August 26 - 12:00 GMT - Baikonur LC45/1. Cosmos 2290 Mass: 13,000 kg (28,000 lb). Spacecraft: Orlets-2. Agency: MO RF. Perigee: 181 km (112 mi). Apogee: 392 km (243 mi). Inclination: 64.80 deg. Period: 90.25 min. Only flight of Orlets-2 long-duration military reconnaissance satellite with 22 film-return capsules. 1994 November 4 - 05:47 GMT - Baikonur LC45/1. Resurs-O1 No. 3 Mass: 1,900 kg (4,100 lb). Spacecraft: Resurs-O1. Agency: RKA. Perigee: 660 km (410 mi). Apogee: 663 km (411 mi). Inclination: 98.03 deg. Period: 97.98 min. Studied natural resources. It carried the German Safir-R1 communications experiment as a secondary attached payload. Expected life 3 to 5 years. The spacecraft mass of 1,907 kg was slightly higher than earlier models. The principal Earth observation sensors were MSU-SK and MSU-E instruments along with an experimental PVM-E local vertical sensor . 1994 November 24 - 09:15 GMT - Baikonur LC45/1. Cosmos 2297 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 845 km (525 mi). Apogee: 857 km (532 mi). Inclination: 71.01 deg. Period: 101.96 min. 1995 October 31 - 20:19 GMT - Baikonur LC45/1. Cosmos 2322 Mass: 6,000 kg (13,200 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 847 km (526 mi). Apogee: 854 km (530 mi). Inclination: 71.00 deg. Period: 102.00 min. 1996 September 4 - 09:01 GMT - Baikonur LC45/1. Cosmos 2333 Spacecraft: Tselina-2. Agency: MO RF. Perigee: 849 km (527 mi). Apogee: 852 km (529 mi). Inclination: 70.90 deg. Period: 101.90 min. New heavy ELINT class. 1997 May 20 - 07:07 GMT - Baikonur LC45/1. FAILURE: Strut in first stage engine failed at T+48 seconds. Heavy ELINT Spacecraft: Tselina-2. Agency: VKS. 1998 July 10 - 06:30 GMT - Baikonur LC45/1. Resurs-O1 No. 4 Spacecraft: Resurs-O1. Agency: RKA. Perigee: 815 km (506 mi). Apogee: 818 km (508 mi). Inclination: 98.80 deg. Period: 101.20 min. In addition to its remote sensing equipment, the satellite carried the Belgian LLMS (Little LEO Messaging System) communications payload for the IRIS system. The launch was critical in restoring confidence in the Zenit vehicle prior to planned commercial launches of Globalstar satellites from Baikonur and the first Sea Launch flights using a three-stage Zenit from a California-based floating launch platform. Expected life 3 to 5 years. 1998 July 28 - 09:15 GMT - Baikonur LC45/1. Cosmos 2360 Spacecraft: Tselina-2. Agency: MO RF. Perigee: 847 km (526 mi). Apogee: 855 km (531 mi). Inclination: 71.00 deg. Period: 102.00 min. 1998 September 9 - 20:29 GMT - Baikonur LC45/1. Zenit-2 11K77.05 22D (67047801) FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Globalstar FM5 Mass: 222 kg (489 lb). Spacecraft: Globalstar. Agency: Globalstar Comms Corp., San Jose. Fell in Siberia. 1999 March 28 - 01:29 GMT - Kiritimati -. DemoSat Mass: 4,500 kg (9,900 lb). Agency: SeaLaunc. Perigee: 658 km (408 mi). Apogee: 36,045 km (22,397 mi). Inclination: 1.40 deg. The first Boeing Sea Launch mission. The Zenit-3SL lifted off from the Odyssey floating platform on the equator at 154 degrees West longitude. The DemoSat payload was an instrumented dynamic model of an HS-702 satellite built by Boeing Commercial Space/Kent. 13 minutes after launch, the Block DM-SL upper stage completed its first burn and entered a 180 km x 735 km x 1.2 degree parking orbit. A second burn 47 minutes after launch placed DemoSat in a 638 km x 36,064 km x 1.2 degree geostationary transfer orbit. Three hours later, a third DM-SL burn lowered the stage's perigee so that it would re-enter quickly. 1999 July 17 - 06:38 GMT - Baikonur LC45/1. Zenit-2 17L Okean-O Mass: 4,360 kg (9,610 lb). Spacecraft: Okean-O. Agency: RAKA. Perigee: 660 km (410 mi). Apogee: 663 km (411 mi). Inclination: 98.00 deg. First of a new generation of larger Okean oceanographic satellites, carried a side-looking radar (RSL-BO), and a set of visible and infrared scanners and radiometers. It is built by the Ukrainian Yuzhnoye company and is a joint project of the Russian Aviation/Space Agency (RAKA) and the Ukrainian National Space Agency (NKAU). 1999 October 10 - 03:28 GMT - Kiritimati -. DirecTV 1R Spacecraft: HS 601 . Agency: DirecTV. Perigee: 35,785 km (22,235 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.00 deg. Second successful Zenit-3SL flight from the Odyssey launch platform in the Pacific Ocean at 154 deg W, 0 deg N. First flight to carry a commercial payload. The satellite used its R-4D apogee engine to enter geostationary orbit at 81.6 deg W. Finally stationed at 101 deg W. Positioned in geosynchronous orbit at 81 deg W in 1999. As of 5 September 2001 located at 101.19 deg W drifting at 0.004 deg W per day. As of 2007 Mar 10 located at 100.87W drifting at 0.007W degrees per day. 2000 February 3 - 09:26 GMT - Baikonur LC45/1. Zenit-2 45025801 Cosmos 2369 Mass: 3,200 kg (7,000 lb). Spacecraft: Tselina-2. Agency: MO RF. Perigee: 849 km (528 mi). Apogee: 860 km (534 mi). Inclination: 71.00 deg. Period: 101.95 min. ELINT satellite. 2000 March 12 - 14:49 GMT - Kiritimati -. FAILURE: Second stage shut down prematurely due to a valve software command mistake. The satellite fell in the South Pacific, south of Pitcairn Island. ICO F-1 Mass: 2,750 kg (6,060 lb). Spacecraft: HS 601. Agency: ICO. Apogee: 200 km (120 mi). First ICO Global Communications satellite. Lost due to launch vehicle failure; was to have entered a 10,300 km x 45 deg circular orbit. ICO's satellites would carry multiple spot beams for mobile communications. 2000 July 28 - 22:42 GMT - Kiritimati -. PAS 9 Mass: 3,659 kg (8,066 lb). Spacecraft: HS 601. Agency: Panamsat. Perigee: 35,778 km (22,231 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Panamsat geosynchronous communications satellite to replace PAS 5 at 58 deg W. Stationed at 58 deg W. Positioned in geosynchronous orbit at 58 deg W in 2000. As of 30 August 2001 located at 58.03 deg W drifting at 0.012 deg W per day. As of 2007 Mar 9 located at 58.06W drifting at 0.013W degrees per day. 2000 September 25 - 10:10 GMT - Baikonur LC45/1. Cosmos 2372 Mass: 12,000 kg (26,000 lb). Spacecraft: Orlets-2. Agency: MO RF. Perigee: 211 km (131 mi). Apogee: 343 km (213 mi). Inclination: 64.78 deg. Period: 89.97 min. Reported code name Yenisey. It is speculated that this is an improved version of the Orlets satellite launched as Cosmos 2290 in 1994. Re-entered on Apr 20, 2001 after a 7 month mission. 2000 October 21 - Kiritimati -. Thuraya 1 Mass: 5,108 kg (11,261 lb). Spacecraft: HS 702. Agency: Thuraya. Perigee: 35,764 km (22,222 mi). Apogee: 35,808 km (22,250 mi). Inclination: 5.20 deg. Period: 1,436.10 min. Mobile Communications satellite. Launch delayed from September 18 and October 19. Stationed at 44 deg E. The first Boeing GEM satellite, Thuraya 1, was built by Boeing/El Segundo (formerly Hughes). It was based on the HS-702 design but featured a large 12-m diameter truss antenna for L-band mobile telephone service. Launch mass of Thuraya was 5108 kg; dry mass probably around 3000 kg. The satellite was to be delivered after on orbit testing to Etisalat, the Emirates Telecom Corp of Abu Dhabi, and its Thuraya Satellite subsidiary. Thuraya was launched from the Odyssey platform in the Pacific Ocean positioned on the equator at 154 deg W. The two-stage Yuzhnoe Zenit core delivered Thuraya and its Energiya Blok DM-SL upper stage to a -2212 x 182 km suborbital trajectory. The first DM-SL burn placed the stack in a 180 x 200 km x 6.3 deg parking orbit at 0604 GMT; a second burn at 0733 GMTput Thuraya in a 210 x 35891 km x 6.3 deg geostationary transfer orbit. A later depletion burn lowered the DM-SL stage perigee to 180 km, as burns by Thuraya's liquid engine raised it towards geosynchronous orbit. Positioned in geosynchronous orbit at 44 deg E in 2000. As of 5 September 2001 located at 44.22 deg E drifting at 0.003 deg E per day. As of 2007 Mar 11 located at 98.57E drifting at 0.007W degrees per day. 2001 March 18 - Kiritimati -. XM-2 Rock Mass: 4,666 kg (10,286 lb). Spacecraft: HS 702. Agency: XM Radio. Perigee: 35,785 km (22,235 mi). Apogee: 35,788 km (22,237 mi). Inclination: 0.00 deg. Period: 1,436.10 min. The XM Radio satellites (using Boeing 702 buses) provided digital radio entertainment broadcast to the US. The XM-2 Rock satellite was accompanied by the XM-1 Roll spacecraft launched later in 2001. A Boeing Sea Launch Zenit-3SL took off from the Odyssey floating launch platform at 154W 0 N in the Pacific. The two-stage Zenit put the Blok DM in a suborbital trajectory with a 190 km apogee; the DM first burn went to a 180 x 990 km x 1.3 deg orbit, with the second burn delivering Rock to geostationary transfer orbit. The 4.7 tonne (with fuel), 18 kW satellite carried two transmitters (3 kW each) in the S-band to relay 100 channels of digital quality music uplinked in the X-band from one or more ground stations. It was parked over 114.9 deg-W longitude. The investors include several auto manufacturers who were to be equipping the special receivers in their models. As of 4 September 2001 located at 114.98 deg W drifting at 0.001 deg W per day. As of 2007 Mar 10 located at 115.14W drifting at 0.003W degrees per day. 2001 May 8 - 22:10 GMT - Kiritimati -. XM-1 Roll Mass: 37,032 kg (81,641 lb). Spacecraft: HS 702. Agency: XM Radio. Perigee: 35,784 km (22,235 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Direct Radio Broadcasting satellite. Second launch attempt following pad abort on January 8. Launch delayed from May 7. XM-1 "Roll" was launched from Sea Launch's Odyssey Launch Platform in the Pacific, on the equator at 154.0 W. Roll joined Rock, launched on March 18, to complete the XM Satellite Radio space segment. The XM-1 satellite was a Boeing Satellite Systems (El Segundo) BSS 702 with a launch mass of 4667 kg and a dry mass of about 2500 kg. It carried an R-4D liquid apogee engine and a XIPS ion station-keeping engine. The satellite's Alcatel communications payload featured an X-band receive antenna which passed digital radio broadcasts on to the two 5-meter S-band transmit antennas. It was to provide one hundred channels of digital music and entertainment to motorists in North America after parking over 85 deg-W. The XM satellites, like the three rival Sirius Radio satellites in inclined elliptical synchronous orbits, were to provide radio broadcasting to North America. The first two stages of the Zenit launch vehicle placed the Block DM-SL upper stage and payload in a 191 km apogee suborbital trajectory at 2219 GMT; the Block-DM-SL then ignited for its first burn, entering a 180 x 990 km x 1.3 deg parking orbit at 2223 GMT. The second burn at 2258 GMT accelerated the stack to a 935 x 35797 km x 1.3 deg geostationary transfer orbit. The XM-1 Roll satellite separated at 2315 GMT. As of 5 September 2001 located at 85.12 deg W drifting at 0.009 deg W per day. As of 2007 Mar 10 located at 115.09W drifting at 0.002W degrees per day. 2001 December 10 - 17:18 GMT - Baikonur LC45/1. Zenit-2 19L (1381573091) Meteor-3M Mass: 2,500 kg (5,500 lb). Spacecraft: Meteor-3M. Agency: Rosaviakosmos (Russia). Perigee: 996 km (618 mi). Apogee: 1,015 km (630 mi). Inclination: 99.70 deg. Meteorology satellite. Launch postponed from late 2000, then delayed from November30. The Meteor-3M weather satellite carried visible and IR sensors as well as NASA's SAGE III instrument which studied aerosols and the ozone layer. This was the first launched of a modernised version of the spacecraft. Launch be Zenit launch vehicle from Baikonur rather than Tsyklon 3 from Plesetsk allowed the spacecraft to be 350 kg heavier, carrying additional sensors and various piggy-back payloads. 2002 June 15 - 22:39 GMT - Kiritimati -. Galaxy 3C Mass: 4,850 kg (10,690 lb). Spacecraft: HS 702. Agency: PanAmSat (U.S.). Perigee: 35,786 km (22,236 mi). Apogee: 35,788 km (22,237 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Launch delayed from July 2001 and May 28, June 2 and 9, 2002. The Galaxy 3C satellite was launched from the Odyssey floating launch platform at its standard 154W 0N location. The Zenit second stage and the DM third stage with payload entered a -2160 x 195 km suborbital trajectory at 2248:10. At about 2252 UTC the DM stage entered a 180 x 393 km x 0 deg parking orbit. A second burn of the DM at 2324 to 2330 UTC put Galaxy 3C in a 358 x 41440 km x 0.02 deg transfer orbit This was a record low inclination for a geostationary transfer orbit. The satellite's R-4D apogee engine was to put the Boeing BSS-702 satellite in geostationary orbit. The satellite was the first 702 model to use extra solar panels instead of the solar concentrators which ran into fogging problems on the earlier 702 flights. As of 2007 Mar 10 located at 95.06W drifting at 0.007W degrees per day. 2003 June 10 - Kiritimati -. Thuraya 2 Mass: 5,177 kg (11,413 lb). Spacecraft: HS 702. Agency: Thuraya Satellite Telecommunications. Perigee: 35,766 km (22,223 mi). Apogee: 35,806 km (22,248 mi). Inclination: 5.00 deg. Period: 1,436.10 min. The Boeing 'GEM' spacecraft was a modified BSS-702 with a 12 m wide antenna for L-band mobile communications. Launch delayed from January 20, then April 4. As of 2007 Mar 9 located at 43.94E drifting at 0.004E degrees per day. 2003 August 8 - 03:31 GMT - Kiritimati -. Zenit-3SL 10 Echostar 9 (Telstar 13) Mass: 4,737 kg (10,443 lb). Spacecraft: FS-1300. Agency: Echostar. Perigee: 35,764 km (22,222 mi). Apogee: 35,809 km (22,250 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Originally to have launched December 2002. Echostar 9 carried a Ku and Ka band communications payload for Echostar, and a C-band payload owned by Loral Skynet but about to be sold to Intelsat. Loral called the satellite Telstar 13. As of 2007 Mar 10 located at 121.04W drifting at 0.007W degrees per day. 2003 October 1 - 04:03 GMT - Kiritimati -. Zenit-3SL 13 Horizons 1 (Galaxy 13) Mass: 4,060 kg (8,950 lb). Spacecraft: HS 601. Agency: PanAmSat. Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Delayed from late 2002, September 27 2003. The satellite carried both C-band and Ku-band communications payloads. The C-band payload was referred to as Galaxy 13; the Ku-band payload was jointly owned by Panamsat and the Japanese JSAT company and was called Horizons-1. Horizons-1 was to provide digital data services between the Americas and Asia via a relay station in Hawaii. As of 2007 Mar 11 located at 127.00W drifting at 0.002E degrees per day. 2004 January 11 - 04:13 GMT - Kiritimati -. Zenit-3SL 12 Estrela do Sul 1 (Skynet Brazil 1, Telstar 14) Mass: 4,694 kg (10,348 lb). Spacecraft: FS-1300. Agency: Loral Skynet do Brasil. Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Period: 1,436.10 min. Initially planned for launch on Delta 4M+ (4,2). Launch delayed from January 10. Placed in geosynchronous orbit but reports indicated there were problems deploying one of the solar panels. As of 2007 Mar 11 located at 63.07W drifting at 0.006W degrees per day. 2004 May 4 - 12:42 GMT - Kiritimati -. DirecTV 7S Mass: 5,483 kg (12,087 lb). Spacecraft: FS-1300. Agency: DirecTV. Perigee: 35,730 km (22,200 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,434.80 min. Delayed from February 29, May 2. Transferred from Ariane 5 under launch backup agreement. Record single payload to geosynchronous transfer orbit. As of 2007 Mar 11 located at 119.04W drifting at 0.000E degrees per day. 2004 June 10 - 01:28 GMT - Baikonur LC45/1. Zenit-2 1-95 Cosmos 2406 Mass: 3,200 kg (7,000 lb). Spacecraft: Tselina-2. Agency: VKA. Perigee: 846 km (525 mi). Apogee: 866 km (538 mi). Inclination: 71.00 deg. Period: 102.10 min. Delayed from February 17 and 18; March 17 and 31; April 6, 25 and 26. 2004 June 29 - 03:58 GMT - Kiritimati -. Zenit-3SL 11 FAILURE: Partial failure - upper stage left satellite stranded in useless orbit. Apstar 5 Mass: 4,640 kg (10,220 lb). Spacecraft: FS-1300. Agency: APT Satellite (China). Perigee: 35,775 km (22,229 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Delayed from November 2003, April 28 2004. Partial failure (upper stage). As of 2007 Mar 11 located at 138.01E drifting at 0.009W degrees per day. 2005 March 1 - 03:51 GMT - Kiritimati -. Zenit-3SL 17 XM-3 Mass: 4,703 kg (10,368 lb). Spacecraft: HS 702. Agency: XM Radio. Perigee: 35,785 km (22,235 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Delayed from February 17, 18 and 23, 2005 due to of heavy seas. The satellite would supplement the American XM network's satellite direct-broadcast digital radio service. As of 2007 Mar 9 located at 85.14W drifting at 0.010W degrees per day. 2005 April 26 - 07:31 GMT - Kiritimati -. Zenit-3SL 15 Spaceway 1 Mass: 6,080 kg (13,400 lb). Spacecraft: HS 702. Agency: DirecTV. Perigee: 35,785 km (22,235 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Heaviest single payload to geosynchronous transfer orbit to that date. Carried 48 high-frequency Ka-band transponders for data transmission and television broadcasting. As of 2007 Mar 10 located at 102.80W drifting at 0.005W degrees per day. 2005 June 23 - 14:03 GMT - Kiritimati -. Zenit-3SL 14 (04L?) Intelsat Americas 8 Mass: 5,500 kg (12,100 lb). Spacecraft: FS-1300. Agency: Intelsat. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Delayed since 2002; most recently delayed from December 4 and 17, 2004. Communications satellite with Ku-, C- and Ka-band transponders, owned by Intelsat, which had been privatized. As of 2007 Mar 11 located at 89.01W drifting at 0.007W degrees per day. 2005 November 8 - 14:07 GMT - Kiritimati -. Zenit-3SL 23 Inmarsat 4F-2 Mass: 5,958 kg (13,135 lb). Spacecraft: Eurostar 3000. Agency: Inmarsat. Perigee: 35,902 km (22,308 mi). Apogee: 35,965 km (22,347 mi). Inclination: 2.90 deg. Period: 1,443.60 min. The satellite was fitted with a 10 meter diameter antenna for mobile communications. Payload moved from Ariane 5 EC-A. Launch delayed from September, November 4 and 5, 2005. As of 2007 Mar 11 located at 52.87W drifting at 0.010W degrees per day. 2006 February 15 - 23:35 GMT - Kiritimati -. Zenit-3SL 15 Echostar 10 Mass: 4,333 kg (9,552 lb). Spacecraft: AS 2100. Agency: Echostar. Perigee: 35,780 km (22,230 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Ku-band communications payload; station in geosynchronous orbit at 110.17 deg W. As of 2007 Mar 11 located at 110.21W drifting at 0.004W degrees per day. 2006 April 12 - 23:30 GMT - Kiritimati -. Zenit-3SL 21 JCSAT 9 Mass: 4,401 kg (9,702 lb). Spacecraft: AS 2100. Agency: JSAT. Perigee: 35,785 km (22,235 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. As of 2007 Mar 8 located at 132.01E drifting at 0.014W degrees per day. 2006 June 18 - 07:50 GMT - Kiritimati -. Zenit-3SL 29 Galaxy 16 Mass: 4,640 kg (10,220 lb). Spacecraft: FS-1300. Agency: PanAmSat. Perigee: 6,484 km (4,028 mi). Apogee: 35,646 km (22,149 mi). Inclination: 0.10 deg. Period: 754.10 min. As of 2007 Mar 11 located at 98.98W drifting at 0.005W degrees per day. 2006 August 22 - 03:27 GMT - Kiritimati -. Zenit-3SL 22/DM-SL-23L Koreasat 5 Mass: 4,465 kg (9,843 lb). Spacecraft: Spacebus 4000. Agency: KT. Perigee: 35,780 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.20 min. The satellite will was to provide Ku-band service for Korea Telecom and Ka-band and SHF band transponders for the South Korean Agency for Defense Development. As of 2007 Mar 11 located at 113.05E drifting at 0.012W degrees per day. 2006 October 30 - 23:49 GMT - Kiritimati -. Zenit-3SL 22SL/DM-SL-24L XM-Blues Mass: 6,100 kg (13,400 lb). Spacecraft: HS 702. Agency: XM Radio. Perigee: 35,785 km (22,235 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.00 deg. Period: 1,436.09 min. Adds to XM Satellite Radio's constellation of direct-broadcast radio to North America (XM Rock, Roll, and Rhythm launched earlier). As of 2007 Mar 10 located at 115.02W drifting at 0.006W degrees per day. 2007 January 30 - 23:22 GMT - Kiritimati -. Zenit-3SL 24SL FAILURE: First stage exploded just after ignition, damaging launch platform. NSS 8 Mass: 6,100 kg (13,400 lb). Spacecraft: HS 702. Agency: New Skies Satellites (International). The platform was designed to survive such an explosion, but the flame deflector was blown off and the blast doors unhinged. The launch platform was towed back to Long Beach for repairs. The time required to repair the platform and the investigation to determine and fix the cause would certainly impact the 2007 Zenit-3SL and Zenit-2 launch schedules, probably forcing customers to be diverted to other boosters. NSS-8 was to have been placed at a 57º East orbital position to satisfy demand in the Indian Ocean region with 56 C-band and 36 Ku-band transponders. NSS-703, with an expected end-of-life in 2009, would have to continue in service until a replacement was built and launched. 2007 June 29 - 10:00 GMT - Baikonur LC45/1. LV Model: Zenit-2SLB . Zenit-2M 1-2005 Cosmos 2428 Mass: 3,200 kg (7,000 lb). Spacecraft: Tselina-2. Agency: VKS. Perigee: 846 km (525 mi). Apogee: 857 km (532 mi). Inclination: 71.00 deg. Period: 102.00 min. Signals intelligence satellite. First launch in three years, and first with the improved version of the Zenit-2 launch vehicle using components developed for the Zenit-3SL. 2008 January 15 - 11:49 GMT - Sea-launched -. Thuraya 3 Mass: 5,173 kg (11,404 lb). Spacecraft: HS 702. Agency: Thuraya. Perigee: 35,756 km (22,217 mi). Apogee: 35,820 km (22,250 mi). Inclination: 6.20 deg. Period: 1,436.20 min. Launch vehicle return-to-flight after on-pad explosion one year earlier damaged launch platform. The satellite was positioned at 98.5 degrees East Longitude to provide L-band and C-band mobile voice, broadband, maritime, rural telephony, and fleet management to Thuraya subscribers. Design lifetime of 12 years. 2008 March 19 - 22:48 GMT - Kiritimati . DirecTV 11 Spacecraft: HS 702. Perigee: 35,787 km (22,236 mi). Apogee: 35,788 km (22,237 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Placed in orbital slot 99.2° W Longitude. In combination with DirecTV 10, the satellite would allow the parent company to direct broadcast local HDTV to 90 percent of its customers in North America. The Ka-band satellite was equipped with 28 active and 8 spare TWTAs for direct broadcast to the continental United States and Alaska; 4 active and 4 spare for broadcast to the 48 stages and Hawaii; and 55 active and 15 spares for spot transmissions. Total power was 18 kW / 16 kW at beginning/end of life. Propulsion was provided by 445 N liquid apogee engine and four XIPS 35-cm ion thrusters. Mass at launch was 6060 kg and 3700 kg after on-board propellants were consumed to place the satellite in its operational geosynchronous orbit. 2008 April 28 - 05:00 GMT - Baikonur . AMOS 3 Spacecraft: Amos. Perigee: 35,784 km (22,235 mi). Apogee: 35,788 km (22,237 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Communications satellite. The Block DM stage made three burns to deliver the payload into geostationary orbit. 2008 May 21 - 09:43 GMT - Kiritimati . Galaxy 18 Spacecraft: FS-1300. Perigee: 35,774 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Intelsat communications satellite, located at 123° W as a replacement for Galaxy 10R. 24 C-band, and 24 Ku-band transponders serving North American customers. Bibliography:
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