Chronology - Quarter 3 2000 home
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2000 July 1 - Launch Site: Barking Sands. Launch Complex: POA. Launch Pad: -. Launch Vehicle: Standard-ER. Model: Standard SM-3. LV Configuration: SM-3 FTR-1. FAILURE: Failure.
  • Aegis LEPI test Nation: USA. Agency: USN. Apogee: 100 km (60 mi). References: 2.
2000 July 4 - 23:44 GMT - Launch Site: Baikonur. Launch Complex: LC200/39. Launch Pad: -. Launch Vehicle: Proton. Model: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 389-02.
  • Cosmos 2371 Nation: Russia. Payload: Geyzer. Mass: 2,400 kg (5,200 lb). Class: Communications. Type: Military. Spacecraft: Potok. Manufacturer: NPO Prikladnoi Mekhaniki, Zhelenogorsk. Agency: MO SSSR. Perigee: 35,770 km (22,220 mi). Apogee: 35,802 km (22,246 mi). Inclination: 1.10 deg. COSPAR: 2000-036A. USAF Sat Cat: 26394. Completed Operations Date: 2000-07-05. Second flight using RD-0210 Phase 2 engines. Geizer military communications satellite. The Blok DM upper stage inserted the Geizer into geosynchronous orbit at 06:20 GMT on July 5. Stationed at 80 deg E. Positioned in geosynchronous orbit at 80 deg E in 2000. As of 6 September 2001 located at 79.81 deg E drifting at 0.014 deg E per day. As of 2007 Mar 10 located at 79.73E drifting at 0.022W degrees per day. References: 2, 552, 554.
2000 July 6 - 14:41 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 9. LV Configuration: Black Brant IX NASA 36.166UM.
  • Microgravity mission Nation: USA. Agency: NASA GSFC. Apogee: 300 km (180 mi). References: 2.
2000 July 7 - 10:25 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Terrier. Model: Terrier Oriole.
  • Test mission Nation: USA. Agency: NASA GSFC. Apogee: 368 km (228 mi). References: 2.
2000 July 8 - 04:19 GMT - Launch Site: Vandenberg. Launch Complex: LF03. Launch Pad: -. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 MSLS IFT-5.
  • MSLS IFT-5 Target mission Nation: USA. Agency: USAF AFMC. Apogee: 1,300 km (800 mi). A C-band transponder on the mock warhead provided location information; its data was compared against its GPS receiver to determine its accuracy. The only decoy used was the large balloon from previous tests. It did not inflate properly, causing MDA officials to use a different decoy in the future. References: 2.
2000 July 8 - 04:40 GMT - Launch Site: Kwajalein. Launch Complex: Meck. Launch Pad: -. Launch Vehicle: Payload Launch Vehicle. LV Configuration: Minuteman 2 PLV PLV IFT-5.
  • IFT-5 EKV ABM test Nation: USA. Agency: USA SSDC. Apogee: 230 km (140 mi). ABM test failure. Second end-to-end system test (intercept attempt) using NMD prototype elements and range assets to approximate the objective system. The IFICS served as the communication link between the BMC3 and EKV. The EKV did not separate from the surrogate booster due to an apparent failure in the 1553 data bus in the booster. References: 2.
2000 July 12 - 04:56 GMT - Launch Site: Baikonur. Launch Complex: LC81/23. Launch Pad: -. Launch Vehicle: Proton. Model: Proton-K. LV Configuration: Proton-K 398-01.
  • Zvezda Nation: Russia. Mass: 20,295 kg (44,742 lb). Class: Manned. Type: Space station. Spacecraft: ISS Zvezda. Manufacturer: Khrunichev/Energiya. Agency: RAKA. 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: 2, 552, 554.
2000 July 14 - 05:21 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36B. Launch Pad: SLC36B. Launch Vehicle: Atlas. Model: Atlas IIAS. LV Configuration: Atlas IIAS AC-161.
  • Echostar 6 Nation: USA. Program: Echostar. Mass: 3,700 kg (8,100 lb). Class: Communications. Spacecraft: FS-1300. Manufacturer: Space Systems/Loral, Palo Alto. Agency: Echostar. Perigee: 35,779 km (22,231 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. COSPAR: 2000-038A. USAF Sat Cat: 26402. Communications satellite, positioned in geosynchronous orbit at 149 deg W. By 5 September 2001 located at 119.07 deg W drifting at 0.002 deg W per day. As of 2007 Mar 10 located at 110.39W drifting at 0.006W degrees per day. References: 2, 552, 554.
2000 July 15 - Launch Site: Sriharikota. Launch Complex: -. Launch Pad: -. Launch Vehicle: Shahab. Model: Shahab 3.
  • Test mission Nation: Iran. Agency: Iran. Apogee: 150 km (90 mi). References: 2.
2000 July 15 - 12:00 GMT - Launch Site: Plesetsk. Launch Complex: LC132/1. Launch Pad: -. Launch Vehicle: Kosmos 3. Model: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 47136-414.
  • MITA Nation: Italy. Mass: 170 kg (370 lb). Class: Technology. Manufacturer: Carlo Gavazzi Space. Agency: ASI. Perigee: 422 km (262 mi). Apogee: 475 km (295 mi). Inclination: 87.26 deg. Period: 93.48 min. COSPAR: 2000-039A. USAF Sat Cat: 26404. Decay Date: 2001-08-15. MITA was an Italian Space Agency experimental microsatellite built by Carlo Gavazzi Space of Milano and carried the NINA particle detector and an experimental attitude control system. References: 2, 552, 554.
  • CHAMP Nation: Germany. Mass: 522 kg (1,150 lb). Class: Earth. Type: Magnetosphere. Manufacturer: Jena/Astrium-F. Agency: DLR. Perigee: 409 km (254 mi). Apogee: 464 km (288 mi). Inclination: 87.26 deg. Period: 93.22 min. COSPAR: 2000-039B. USAF Sat Cat: 26405. CHAMP was a geophysics research satellite operated by GFZ, Potsdam, to study the earth's magnetic and gravitational field. References: 2, 552, 554.
  • Rubin Nation: Germany. Class: Technology. Manufacturer: OHB System, Bremen. Agency: RVSN. Perigee: 411 km (255 mi). Apogee: 463 km (288 mi). Inclination: 87.26 deg. Period: 93.23 min. COSPAR: 2000-039C. USAF Sat Cat: 26406. Decay Date: 2001-08-30. Rubin was a microsatellite to measure launch vehicle parameters developed by OHB and students of the Hochschule Bremen. Rubin remained attached to the payload adapter of the Kosmos-3M final stage. References: 2, 552, 554.
2000 July 16 - 09:17 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17A. Launch Pad: SLC17A. Launch Vehicle: Delta. Model: Delta 7925-9.5. LV Configuration: Delta 7925-9.5 D279.
  • USA 151 Nation: USA. Program: Navstar. Payload: GPS 2R-5 / GPS SVN 44. Mass: 2,032 kg (4,479 lb). Class: Navigation. Spacecraft: GPS Block 2R. Manufacturer: Lockheed Martin, Sunnyvale. Agency: USAF. Perigee: 20,054 km (12,460 mi). Apogee: 20,309 km (12,619 mi). Inclination: 55.20 deg. COSPAR: 2000-040A. USAF Sat Cat: 26407. Global Positioning satellite, placed in Plane B Slot 5. Launch delayed from June 15 and the June 21. References: 2, 552, 554.
2000 July 16 - 12:39 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Soyuz 11A511U. LV Configuration: Soyuz 11A511U/Fregat A15000-069 ST09.
  • Samba Nation: Europe. Payload: Cluster 2-FM6. Mass: 1,200 kg (2,600 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Cluster 2. Manufacturer: Astrium, Friedrichshafen (former Dornier). Agency: ESA. Perigee: 21,449 km (13,327 mi). Apogee: 116,279 km (72,252 mi). Inclination: 88.50 deg. Period: 3,423.40 min. COSPAR: 2000-041A. USAF Sat Cat: 26410. The first two European Space Agency Cluster II satellites, Samba (FM7) and Salsa (FM6) were launched into an initial 200 km / 64.8 deg circular orbit. The Fregat upper stage then burned once before ejecting the satellites into a 250 x 18072 km x 64.7 deg transfer orbit. Both satellites then used their Astrium (former MBB) S400 liquid engines in a series of four additional burns before reaching their final 16869 x 121098 km x 90.6 deg orbits. Each magnetosphere research satellite deployed four 50-meter wire antennas. References: 2, 552, 554.
  • Salsa Nation: Europe. Mass: 1,200 kg (2,600 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Cluster 2. Manufacturer: Astrium, Friedrichshafen (former Dornier). Agency: ESA. Perigee: 21,430 km (13,310 mi). Apogee: 116,294 km (72,261 mi). Inclination: 88.60 deg. Period: 3,423.20 min. COSPAR: 2000-041B. USAF Sat Cat: 26411. References: 2, 552, 554.
2000 July 17 - 06:17 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 8C. LV Configuration: Black Brant 8C NASA 27.143UE.
  • Ionosphere mission Nation: USA. Agency: NASA GSFC. Apogee: 340 km (210 mi). References: 2.
2000 July 19 - 20:09 GMT - Launch Site: Vandenberg. Launch Complex: SLC8. Launch Pad: -. Launch Vehicle: Minotaur. Model: Minotaur 1. LV Configuration: Minotaur 1 2.
  • Mightysat 2.1 Nation: USA. Payload: SA-200B. Mass: 120 kg (260 lb). Class: Surveillance. Type: Military. Spacecraft: SA-200. Manufacturer: Spectrum Astro. Agency: USAF STP. Perigee: 547 km (340 mi). Apogee: 581 km (361 mi). Inclination: 97.78 deg. Period: 95.86 min. COSPAR: 2000-042A. USAF Sat Cat: 26414. Decay Date: 2002-11-12. Mightysat 2.1, also known as Sindri, used a Spectrum Astro SA-200B satellite bus. The spacecraft carried a hyperspectral imager for earth imaging and spectroscopy, as well as satellite technology experiments such as advanced solar arrays. An Aerospace Corp./DARPA picosatellite experiment, consisting of two small boxes connected by a deployable tether, was deployed later. Similar picosats were deployed on the previous Minotaur launch in January 2000. References: 2, 552, 554.
2000 July 20 -
  • Discovery of Jupiter Moon Callirrhoe by T. B. Spahr Nation: USA.
2000 July 23 - 2000 July 26 -
  • Russia seeks help to keep GLONASS network operating Nation: China. Spacecraft: Glonass. Russia invited China to participate in financing a new group of Glonass satellites. An operational system would require 24 satellites to be in operation. However by mid-2000 there were only 14 satellites available, and only nine fully operating. The system would require 1.5 billion rubles a year to operate and replenish the satellite constellaton. References: 424.
2000 July 26 - 18:06 GMT - Launch Site: White Sands. Launch Complex: LC36. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 9. LV Configuration: Black Brant IX NASA 36.185GS.
  • SERTS-00 (10) Solar ultraviolet mission Nation: USA. Agency: NASA GSFC. Apogee: 300 km (180 mi). References: 2.
2000 July 27 -
  • NASA Astronaut Training Group 18 selected. Nation: USA. The group was selected to provide pilot, engineer, and scientist astronauts for space shuttle flights.. Qualifications: Pilots: Bachelor's degree in engineering, biological science, physical science or mathematics. Advanced degree desirable. At least 1,000 flight-hours of pilot-in-command time. Flight test experience desirable. Excellent health. Vision minimum 20/50 uncorrected, correctable to 20/20 vision; maximum sitting blood pressure 140/90. Height between 163 and 193 cm.

    Mission Specialists: Bachelor's degree in engineering, biological science, physical science or mathematics and minimum three years of related experience or an advanced degree. Vision minimum 20/150 uncorrected, correctable to 20/20. Maximum sitting blood pressure of 140/90. Height between 150 and 193 cm.. Seven pilots and ten mission specialists; 14 men and 3 women.

2000 July 28 - 22:42 GMT - Launch Site: Kiritimati. Launch Complex: -. Launch Pad: 0.0 N x 154.0 W. Launch Vehicle: Zenit. Model: Zenit-3SL.
  • PAS 9 Nation: USA. Mass: 3,659 kg (8,066 lb). Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. 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. COSPAR: 2000-043A. USAF Sat Cat: 26451. 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. References: 2, 552, 554.
2000 August 1 -
  • Gauchito hybrid tests. Nation: Argentina. Program: X-Prize. Pablo de León (Buenos Aires, Argentina) performs sub-scale, hot fire, hybrid rocket engine tests.
2000 August 1 -
  • Discovery of the SAU 051 Meteorite (Mars Meteorite) Nation: Oman.
2000 August 1 -
  • Discovery of NWA 2737 Mars Meteorite Nation: Morocco.
2000 August 5 - 05:00 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 9. LV Configuration: Black Brant IX NASA 36.189UG.
  • SPINR Ultraviolet astronomy mission Nation: USA. Agency: NASA GSFC. Apogee: 406 km (252 mi). References: 2.
2000 August 6 - 18:26 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Soyuz 11A511U. LV Configuration: Soyuz 11A511U K15000-668.
  • Progress M1-3 Nation: Russia. Program: ISS. Payload: Progress M1 s/n 251. Mass: 7,250 kg (15,980 lb). Class: Manned. Type: Logistics. Spacecraft: Progress M1. Manufacturer: RKK Energiya. Agency: RAKA. Perigee: 347 km (215 mi). Apogee: 362 km (224 mi). Inclination: 51.50 deg. Period: 91.63 min. COSPAR: 2000-044A. USAF Sat Cat: 26461. Duration: 86.53 days. Decay Date: 2000-11-01. Flight: STS-106. Progress M1-3 automatically docked with the International Space Station on August 8 at 20:13 GMT at the rear Zvezda port. The supply ship began refuelling of the station a few days later. It remained attached for offloading of its dry cargo by the STS-106 crew. It later separated from Zvezda's rear port at 0405 GMT November 1 and was deorbited over the Pacific at 0705 GMT. References: 2, 552, 554.
2000 August 9 - 11:13 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Soyuz 11A511U. LV Configuration: Soyuz 11A511U/Fregat A15000-070 ST10.
  • Rumba Nation: Europe. Mass: 1,200 kg (2,600 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Cluster 2. Manufacturer: Astrium, Friedrichshafen (former Dornier). Agency: ESA. Perigee: 21,430 km (13,310 mi). Apogee: 116,297 km (72,263 mi). Inclination: 88.50 deg. Period: 3,423.30 min. COSPAR: 2000-045A. USAF Sat Cat: 26463. References: 2, 552, 554.
  • Tango Nation: Europe. Mass: 1,200 kg (2,600 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Cluster 2. Manufacturer: Astrium, Friedrichshafen (former Dornier). Agency: ESA. Perigee: 21,430 km (13,310 mi). Apogee: 116,300 km (72,200 mi). Inclination: 88.50 deg. Period: 3,423.40 min. COSPAR: 2000-045B. USAF Sat Cat: 26464. Rumba and Tango were the second pair of Cluster II magnetospheric research satellites of the European Space Agency. A series of five burns of the Fregat stage took them from an initial 190 km / 64.8 degree parking orbit to their final 17,200 x 120,600 km orbits inclined 90 degrees to the equator. They then separated from the Fregat and took up operations. References: 2, 552, 554.
2000 August 15 - Launch Vehicle: KT. Model: KT-1.
  • KT-1 solid rocket launcher Nation: China. China completed the overall design of the rocket engine that is to be used on its first all-solid space launch vehicle. References: 424.
2000 August 17 - 23:16 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44LP. LV Configuration: Ariane 44LP-3 V131.
  • Brasilsat B-4 Nation: Brazil. Program: Brasilsat. Mass: 1,757 kg (3,873 lb). Class: Communications. Spacecraft: HS 376W. Manufacturer: Hughes Space and Communications, El Segundo. Agency: Embratel. Perigee: 35,776 km (22,230 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 2000-046A. USAF Sat Cat: 26469. Brasilsat B4 was a C-band geosynchronous communications satellite, replacing the 15-year-old Brasilsat A2 for the Brazilian communications company Embratel. Positioned in geosynchronous orbit at 75 deg W in 2000. As of 2 September 2001 located at 92.03 deg W drifting at 0.011 deg W per day. As of 2007 Mar 9 located at 70.08W drifting at 0.020W degrees per day. References: 2, 552, 554.
  • Nilesat 102 Nation: Egypt. Mass: 1,827 kg (4,027 lb). Class: Communications. Spacecraft: Eurostar 2000. Manufacturer: Astrium, Toulouse (former Matra). Agency: Nilesat. Perigee: 35,775 km (22,229 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2000-046B. USAF Sat Cat: 26470. Geosynchronous communications satellite of the Egyptian company Nilesat SA. The satellite joined Nilesat 101 in providing Ku-band broadcast services. Stationed at 7 deg W. Positioned in geosynchronous orbit at 7 deg W in 2000. As of 2 September 2001 located at 6.98 deg W drifting at 0.002 deg W per day. As of 2007 Mar 9 located at 6.97W drifting at 0.004W degrees per day. References: 2, 552, 554.
2000 August 17 - 23:45 GMT - Launch Site: Vandenberg. Launch Complex: SLC4E. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 403B. LV Configuration: Titan 403B 4B-28 / K-25.
  • USA 152 Nation: USA. Payload: Onyx F1. Mass: 14,500 kg (31,900 lb). Class: Surveillance. Type: Radarsat. Spacecraft: Lacrosse. Manufacturer: Lockheed Martin Astronautics, Denver. Agency: NRO. Perigee: 689 km (428 mi). Apogee: 695 km (432 mi). Inclination: 68.00 deg. Period: 98.53 min. COSPAR: 2000-047A. USAF Sat Cat: 26473. The National Reconnaissance Office satellite was reported to be an Onyx (formerly Lacrosse) radar imaging spacecraft built by Lockheed Martin. The Titan second stage reached a 572 x 675 km x 68.0 deg orbit and separated from the payload. Amateur observers reported the payload has made two small maneuvers and by Aug 23 was in a 681 x 695 km x 68.1 deg orbit. References: 2, 552, 554.
2000 August 21 - 20:14 GMT - Launch Site: Alcantara. Launch Complex: -. Launch Pad: -. Launch Vehicle: Sonda. Model: VS-30/Orion. LV Configuration: VS-30/Orion XV-01.
  • Baronesa Microgravity mission Nation: Germany. Agency: AEB/DLR. Apogee: 315 km (195 mi). References: 2.
2000 August 23 - 11:05 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: SLC17B. Launch Vehicle: Delta. Model: Delta 3. LV Configuration: Delta 8930 D280.
  • DM-F3 Nation: USA. Payload: Dummy Payload. Mass: 4,348 kg (9,585 lb). Class: Technology. Manufacturer: Boeing/HB. Agency: Boeing/H. Perigee: 212 km (131 mi). Apogee: 19,547 km (12,145 mi). Inclination: 27.60 deg. COSPAR: 2000-048A. USAF Sat Cat: 26475. Vehicle Demonstration. Return to flight following earlier failure. The third Boeing Delta III launch was financed by the company and carried a dummy payload in order to bolster customer confidence in the new launch vehicle. The second stage ignited at an altitude of 158 km and the RL-10 shut off as planned in a 157 x 1363 km x 29.5 deg parking orbit. The engine fired again until fuel depletion, to place the vehicle in a geostationary transfer orbit of 190 x 20,655 km x 27.6 deg. This was much lower than that planned (23,400 km plus or minus 3,000 km) due to the fuel temperature and atmospheric conditions on the day of launch. The DM-F3 dummy payload was a mass model of the Orion 3 HS-601 satellite launched on the second Delta 3. The 4348 kg model was a 2.0m diameter, 1.7m high cylinder with two circular end plates, painted with black and white patterns. It was to be used by US Air Force researchers as a calibration target. References: 2, 552, 554.
2000 August 24 - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Standard-ER. Model: Standard SM-2ER Block IV. LV Configuration: SM-2-IV CTV-2.
  • Block IVA test Nation: USA. Agency: USN. Apogee: 10 km (6 mi). References: 2.
2000 August 28 - 20:08 GMT - Launch Site: Baikonur. Launch Complex: LC81/24. Launch Pad: -. Launch Vehicle: Proton. Model: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 401-02.
  • Raduga-1 Nation: Russia. Mass: 2,400 kg (5,200 lb). Class: Communications. Spacecraft: Raduga-1. Manufacturer: NPO Prikladnoi Mekhaniki, Zhelenogorsk. Agency: MO RF. Perigee: 35,776 km (22,230 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.10 deg. Period: 1,435.90 min. COSPAR: 2000-049A. USAF Sat Cat: 26477. Raduga-1 military communications satellite initially named Cosmos 2372 by the RVSN press service. Stationed at 50 deg E. As of 5 September 2001 located at 49.25 deg E drifting at 0.048 deg W per day. As of 2007 Mar 10 located at 45.70E drifting at 0.012W degrees per day. References: 2, 552, 554.
2000 September 1 - Launch Site: Hama-Allepo. Launch Complex: -. Launch Pad: -. Launch Vehicle: R-17. Model: Scud D.
  • Test mission Nation: Syria. Agency: Syria. Apogee: 150 km (90 mi). References: 2.
2000 September 1 - 03:25 GMT - Launch Site: Taiyuan. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: CZ. Model: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-3 (62).
  • ZY-2 Nation: China. Payload: Zi Yuan 2. Class: Surveillance. Type: Military. Spacecraft: ZY. Manufacturer: China Acad. Space Tech., Beijing. Agency: CAST. Perigee: 489 km (304 mi). Apogee: 501 km (311 mi). Inclination: 97.41 deg. Period: 94.43 min. COSPAR: 2000-050A. USAF Sat Cat: 26481. The ZY-2 (Ziyuan-2 ('Resource-2'), while disguised as a civilian earth monitoring system, was actually code-named Jianbing-3 and was China's first high-resolution military imaging satellite. The cover story of the official Xinhua news agency was that the civilian remote sensing system would be used primarily in territorial surveying, city planning, crop yield assessment, disaster monitoring and space science experimentation. However the satellite was placed at a much lower altitude than the ZY-1 satellite and US intelligence sources indicated that it was a photo-reconnaissance satellite for exclusively military purposes, such as targeting missiles at US and Taiwanese forces. The new satellite was believed to employ digital-imaging technology and to have a resolution of 2 m or less. The satellite was designed and built by the Chinese Academy of Space Technology and was developed indigenously. It was said to be more advanced than earlier sensing satellites and was expected to have an orbital life of two years. The camera provided more than three times the resolution of the ZY-1 earth resources satellite. The Zi Yuan 2 satellite may have used the CBERS Sino-Brazilian bus of the earlier ZY-1. However it was also said to be of new design and demonstrated the capability to maneuver in orbit, adjusting its orbit after launch. In October 2000 Chinese scientists denied that the ZY-2 satellite had a military mission. It was said to be a remote-sensing satellite equipped with CCD cameras and an infrared multispectral scanner that could only identify objects on the ground with a resolution of several dozen meters to 1 km. References: 2, 552, 554.
2000 September 5 - 09:43 GMT - Launch Site: Baikonur. Launch Complex: LC81/23. Launch Pad: -. Launch Vehicle: Proton. Model: Proton-K/DM-2M. LV Configuration: Proton-K/DM-2M (DM3) 400-02.
  • Sirius 2 Nation: USA. Program: Sirius Radio. Mass: 3,800 kg (8,300 lb). Class: Communications. Spacecraft: FS-1300. Manufacturer: Space Systems/Loral, Palo Alto. Agency: Sirius R. Perigee: 24,521 km (15,236 mi). Apogee: 47,051 km (29,236 mi). Inclination: 63.40 deg. COSPAR: 2000-051A. USAF Sat Cat: 26483. Sirius Radio's Sirius 2 was launched into a 144 x 168 km x 64.8 deg parking orbit. The Blok DM3 stage then made two burns to deliver Sirius 2 to an elliptical 6192 x 47057 km x 63.4 deg orbit. The was to provide digital radio broadcasts to mobile users in North America. Stationed at 64 deg W. As of 31 August 2001 located at 64.56 deg W drifting at 0.003 deg W per day. As of 2007 Mar 10 located at 67.77W drifting at 0.049E degrees per day. References: 2, 552, 554.
2000 September 5 - 18:02 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 9. LV Configuration: Black Brant IX NASA 36.151US.
  • Solar x-ray mission Nation: USA. Agency: NASA GSFC. Apogee: 300 km (180 mi). References: 2.
2000 September 6 - 22:33 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44P. LV Configuration: Ariane 44P-3 V132.
  • Eutelsat W1 Nation: Europe. Program: Eutelsat. Mass: 3,250 kg (7,160 lb). Class: Communications. Spacecraft: Eurostar 2000. Manufacturer: Astrium, Toulouse (former Matra). Agency: Eutelsat. Perigee: 35,776 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. COSPAR: 2000-052A. USAF Sat Cat: 26487. European Telecommunications Satellite Organization's Eutelsat W1 was launched into a geostationary transfer orbit, targetted for a final 10 deg E orbital position. The box-shaped 2.5 x 5.0 m satellite has two rectangular solar panel arrays spanning 31.7m and two dishes, a European beam and a steerable beam. The payload includes 28 Ku-band transponders. Stationed at 10 deg E. Positioned in geosynchronous orbit at 1 deg E in 2000. As of 1 September 2001 located at 9.92 deg E drifting at 0.005 deg E per day. As of 2007 Mar 8 located at 10.05E drifting at 0.006W degrees per day. References: 2, 552, 554.
2000 September 8 - 12:45 GMT - Launch Site: Cape Canaveral. Launch Complex: LC39B. Launch Pad: -. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-106.
  • STS-106 Nation: USA. Program: ISS. Payload: Atlantis F22. Class: Manned. Type: Spaceplane. Spacecraft: Atlantis. Manufacturer: Boeing. Agency: NASA JSC. Perigee: 374 km (232 mi). Apogee: 386 km (239 mi). Inclination: 51.60 deg. COSPAR: 2000-053A. USAF Sat Cat: 26489. Duration: 11.80 days. Decay Date: 2000-09-20. Crew: Wilcutt, Altman, Burbank, Lu, Mastracchio, Malenchenko, Morukov. Flight: STS-106. Atlantis was launched from Kennedy Space Center's Launch Complex 39B. Solid rocket boosters RSRM-75 and external tank ET-103 were used to loft the orbiter into space. The inital orbit of 72 x 328 km x 51.6 deg was circularised by the Shuttle's OMS engines at apogee.

    Atlantis docked with the PMA-2 adapter on the International Space Station at 05:51 GMT on September 10. The orbiter's small RCS engines were used to gently reboost the station's orbit several times.

    Astronauts Lu and Malenchenko made a spacewalk on September 11 beginning at 04:47 GMT. They rode the RMS arm up to Zvezda and began installing cables, reaching a distance of 30 meters from the airlock when installing Zvezda's magnetometer. Total EVA duration was 6 hours 21 minutes.

    During their 12-day flight, the astronauts spent a week docked to the International Space Station during which they worked as movers, cleaners, plumbers, electricians and cable installers. In all, they spent 7 days, 21 hours and 54 minutes docked to the International Space Station, outfitting the new Zvezda module for the arrival of the Expedition One crew later this fall.

    The Shuttle undocked from ISS at 03:44 GMT on September 18 and made two circuits of the station each lasting half an orbit, before separating finally at 05:34 GMT. The payload bay doors were closed at 04:14 GMT on September 20 and at 06:50 GMT the OMS engines ignited for a three minute burn lowering the orbit from 374 x 386 km x 51.6 deg to 22 x 380 km x 51.6 deg. After entry interface at 07:25 GMT, the orbiter glided to a landing on runway 15 at Kennedy Space Center with main gear touchdown at 07:56:48 GMT for a mission duration of 283 hr 11min. References: 2, 7, 552, 554.

2000 September 11 - 04:47 GMT -
  • EVA STS-106-1 Nation: USA. Program: ISS. Class: Manned. Type: Space station. Spacecraft: International Space Station. Crew: Lu, Malenchenko. Flight: STS-106. EVA Duration: 0.26 days. Astronauts Lu and Malenchenko made a spacewalk on September 11 beginning at 04:47 GMT. They rode the RMS arm up to Zvezda and began installing cables, reaching a distance of 30 meters from the airlock when installing Zvezda's magnetometer.
2000 September 12 - Launch Site: Barents Sea Launch Area. Launch Complex: -. Launch Pad: 69.5 N x 34.2 E. Launch Vehicle: R-29. Model: Shtil. LV Configuration: Shtil VMF RF.
  • Operational test Nation: Russia. Agency: VMF RF. Apogee: 1,000 km (600 mi). References: 2.
2000 September 14 - 22:54 GMT - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5G. LV Configuration: Ariane 5G V130 (506).
  • Astra 2B Nation: Europe. Program: Astra. Mass: 3,320 kg (7,310 lb). Class: Communications. Spacecraft: Eurostar 2000. Manufacturer: Astrium, Toulouse (former Matra). Agency: SES. Perigee: 35,768 km (22,225 mi). Apogee: 35,804 km (22,247 mi). Inclination: 0.00 deg. COSPAR: 2000-054A. USAF Sat Cat: 26494. Direct Broadcasting satellite. Launch postponed from July 25. Astra 2B was an Astrium/Toulouse Eurostar 2000+ television broadcast satellite owned by the Luxembourg-based Societe Europeene de Satellites. The satellite was to be stationed at 28.2E to replace the German DFS Kopernikus. It carried 28 Ku-band transponders. By September 19 Astra 2B was in a 31,153 x 35,762 km x 0.3 deg orbit, approaching geosynchronous altitude. Stationed at 28 deg E. Positioned in geosynchronous orbit at 28 deg E in 2000. As of 20 August 2001 located at 28.50 deg E drifting at 0.011 deg E per day. As of 2007 Mar 10 located at 28.15E drifting at 0.017W degrees per day. References: 2, 552, 554.
  • GE 7 Nation: USA. Program: Americom. Mass: 3,320 kg (7,310 lb). Class: Communications. Spacecraft: AS 2100. Manufacturer: Lockheed Martin, Sunnyvale. Agency: GE Americom. Perigee: 35,783 km (22,234 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.00 deg. COSPAR: 2000-054B. USAF Sat Cat: 26495. Direct Broadcasting satellite. GE Americom satellite to provide cable TV distribution coverage to the USA. Equipped with 24 C-band transponders. Its dry mass was 912 kg and it carried 1023 kg of fuel at launch. The satellite is an A2100A model built by Lockheed Martin/Sunnyvale, the first lightweight A2100 with a mass about half that of earlier A2100 satellites. By September 19 GE 7 was in a 35,832 x 35,869 km x 0.1 deg orbit drifting over 146 deg W. Stationed at 137 deg W. Positioned in geosynchronous orbit at 137 deg W in 2000. As of 4 September 2001 located at 136.92 deg W drifting at 0.003 deg E per day. As of 2007 Mar 9 located at 137.03W drifting at 0.000E degrees per day. References: 2, 552, 554.
2000 September 20 - 2000 September 20 -
  • Landing of STS-106 Nation: USA. Program: ISS. Flight: STS-106. STS-106 landed at 07:56 GMT.
2000 September 21 - Launch Vehicle: CZ-NGLV. Model: CZ-NGLV-320.
  • Chinese Rocket Plans Nation: China. Chief Designer of Chinese rockets Long Lehao described China's three-phase future space launcher plan. Phase 1, 2001-2003: Modify existing launchers to increase their reliability and payload capacity. Phase 2, by 2005: Develop non-toxic, non-polluting launchers, and increase low-Earth-orbit launch capacity to over 20 tonnes and geosynchronous transfer orbit capacity from the current 5.5 tonnes to about 14 tonnes. Phase 3: Develop a recoverable launch vehicle with lower launch costs. References: 424.
2000 September 21 - Launch Site: Sriharikota. Launch Complex: -. Launch Pad: -. Launch Vehicle: Shahab. Model: Shahab 3. LV Configuration: Shahab 3 Shahab-3D. FAILURE: Failure.
  • Test mission Nation: Iran. Agency: Iran. Apogee: 150 km (90 mi). References: 2.
2000 September 21 - 10:22 GMT - Launch Site: Vandenberg. Launch Complex: SLC4W. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 2G. LV Configuration: Titan II SLV 23G-13 / M68B-39 + M68B-96.
  • NOAA 16 Nation: USA. Program: Tiros. Payload: NOAA-L. Mass: 1,476 kg (3,254 lb). Class: Earth. Type: Weather. Spacecraft: Advanced Tiros N. Manufacturer: Lockheed Martin. Agency: NOAA. Perigee: 853 km (530 mi). Apogee: 867 km (539 mi). Inclination: 98.79 deg. Period: 102.06 min. COSPAR: 2000-055A. USAF Sat Cat: 26536. Launch attempt on September 20 scrubbed. The NOAA polar orbit weather satellite, an Advanced Tiros N with a suite of imaging and sounding instruments. The two-stage Titan II launch vehicle, serial 23G-13, put NOAA-L into a suborbital -2500 x 800 km x 98.0 deg trajectory. The spacecraft's Thiokol Star 37XFP solid motor fired at apogee to circularize the sun-synchronous orbit at 800 km. References: 2, 552, 554.
2000 September 21 - 20:50 GMT - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Trident. Model: Trident D-5. LV Configuration: Trident D-5 DASO-7.
  • 90ss Nation: UK. Agency: RN. Apogee: 1,000 km (600 mi). References: 2.
2000 September 25 - 10:10 GMT - Launch Site: Baikonur. Launch Complex: LC45/1. Launch Pad: -. Launch Vehicle: Zenit. Model: Zenit-2.
  • Cosmos 2372 Nation: Russia. Mass: 12,000 kg (26,000 lb). Class: Surveillance. Type: Military. Spacecraft: Orlets-2. Manufacturer: TsSKB-Progress, Samara. Agency: MO RF. Perigee: 211 km (131 mi). Apogee: 343 km (213 mi). Inclination: 64.78 deg. Period: 89.97 min. COSPAR: 2000-056A. USAF Sat Cat: 26538. Duration: 269.00 days. Decay Date: 2001-04-20. 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. References: 2, 552, 554.
2000 September 26 - 10:05 GMT - Launch Site: Baikonur. Launch Complex: LC109. Launch Pad: LC109/95. Launch Vehicle: R-36M. Model: Dnepr.
  • Tiungsat-1 Nation: Malaysia. Payload: MY-Sat 1. Mass: 50 kg (110 lb). Class: Earth. Type: Landsat. Spacecraft: MicroSat-70. Manufacturer: Surrey/ATSB. Agency: BKSA. Perigee: 644 km (400 mi). Apogee: 658 km (409 mi). Inclination: 64.56 deg. Period: 97.67 min. COSPAR: 2000-057A. USAF Sat Cat: 26545. Launch delayed from August 25/26. Customer: Astonautic Technology (M) SDN. BHD. Malaysia's first microsatellite built through a technology transfer programme with Surrey Satellite Technology Ltd Carried multi-spectral Earth imaging CCD cameras, meteorological Earth imaging CCD camera, digital store and forward communications, cosmic-ray energy deposition experiment (CEDEX) References: 2, 552, 554.
  • MegSat-1 Nation: Italy. Mass: 50 kg (110 lb). Class: Technology. Spacecraft: MegSat. Manufacturer: MegSat, Gruppo Meggiorin, Brescia. Agency: Megsat. Perigee: 643 km (399 mi). Apogee: 649 km (403 mi). Inclination: 64.56 deg. Period: 97.56 min. COSPAR: 2000-057B. USAF Sat Cat: 26546. Research satellite owned and built by MegSat Space Division, part of the Gruppo Meggiorin companies in Brescia, Italy. References: 2, 552, 554.
  • UniSat Nation: Italy. Mass: 10 kg (22 lb). Class: Technology. Spacecraft: UniSat. Manufacturer: Universita degli Studi "la Sapienza", Roma. Agency: Sapienza. Perigee: 643 km (399 mi). Apogee: 670 km (416 mi). Inclination: 64.56 deg. Period: 97.78 min. COSPAR: 2000-057C. USAF Sat Cat: 26547. Experimental satellite developed by the GAUSS (Gruppo di Astrodinamica dell' Universita degli Studi 'la Sapienza') in Roma. Unisat was financed by ASI and MURST (Ministero dell'Universtia e della Ricerca Scientifica e Tecnologica). It carried NiMH batteries, a magnetometer, and a payload consisting of a space debris sensor and a camera. References: 2, 552, 554.
  • SaudiSat 1A Nation: Saudi Arabia. Mass: 10 kg (22 lb). Class: Communications. Spacecraft: SaudiSat. Manufacturer: King Abdulaziz City for Science and Tech, Riyadh. Agency: KACST. Perigee: 644 km (400 mi). Apogee: 651 km (404 mi). Inclination: 64.56 deg. Period: 97.59 min. COSPAR: 2000-057D. USAF Sat Cat: 26548. Saudisat 1A and 1B were developed by the Saudi Institute for Space Research at KACST (King Abdulaziz City for Science and Technology), Riyadh, and carried amateur store-forward communications payloads. References: 2, 552, 554.
  • SaudiSat 1B Nation: Saudi Arabia. Mass: 10 kg (22 lb). Class: Communications. Spacecraft: SaudiSat. Manufacturer: King Abdulaziz City for Science and Tech, Riyadh. Agency: KACST. Perigee: 644 km (400 mi). Apogee: 664 km (413 mi). Inclination: 64.55 deg. Period: 97.73 min. COSPAR: 2000-057E. USAF Sat Cat: 26549. Saudisat 1A and 1B were developed by the Saudi Institute for Space Research at KACST (King Abdulaziz City for Science and Technology), Riyadh, and carried amateur store-forward communications payloads. References: 2, 552, 554.
2000 September 26 - 11:00 GMT - Launch Site: Plesetsk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Topol. Model: Topol M. LV Configuration: Topol-M 11.
  • Test mission Nation: Russia. Agency: RVSN RF. Apogee: 1,000 km (600 mi). References: 2.
2000 September 27 - 09:50 GMT - Launch Site: Plesetsk. Launch Complex: LC167. Launch Pad: -. Launch Vehicle: Topol. Model: Topol M. LV Configuration: Topol-M 12 (1M).
  • Test mission Nation: Russia. Agency: RVSN RF. Apogee: 1,000 km (600 mi). References: 2.
2000 September 28 - 08:01 GMT - Launch Site: Vandenberg. Launch Complex: LF09. Launch Pad: LF09?. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 GT174GM.
  • SHARP operational test launch Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi). RCT-2 FOT, 20 decoys References: 2.
2000 September 28 - 10:01 GMT - Launch Site: Vandenberg. Launch Complex: LF04. Launch Pad: -. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 GT173GM.
  • RCT-2 FOT, 20 decoys/Target missile Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi). References: 2.
2000 September 29 - 09:30 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Soyuz 11A511U.
  • Cosmos 2373 Nation: Russia. Mass: 6,600 kg (14,500 lb). Class: Surveillance. Type: Cartography. Spacecraft: Yantar-1KFT. Manufacturer: TsSKB-Progress, Samara. Agency: MO RF. Perigee: 211 km (131 mi). Apogee: 285 km (177 mi). Inclination: 70.30 deg. Period: 89.46 min. COSPAR: 2000-058A. USAF Sat Cat: 26552. Duration: 46.56 days. Decay Date: 2000-11-14. Twentieth Kometa cartographic satellite, using the Yantar service module with a Vostok-type reentry vehicle. It was announced as a dual civil-military geodetic mission. After a day it raised its orbit to 211 x 285 km x 70.4 deg. Landed near Orenburg, Russia on November 14. Deorbit burn was probably around 2230 GMT; the Vostok-style sphere landed at 2253 GMT. References: 2, 552, 554.
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