Chronology - Quarter 4 1998 home
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1998 October 3 - 10:04 GMT - Launch Site: Vandenberg. Launch Complex: 576E. Launch Pad: -. Launch Vehicle: Taurus. Model: ARPA Taurus. LV Configuration: ARPA Taurus T3 1110.
  • STEX Nation: USA. Payload: STEX. Class: Technology. Type: Ion Engine. Spacecraft: STEX. Manufacturer: Naval Research Lab, Washington, DC. Agency: NRO. Perigee: 744 km (462 mi). Apogee: 759 km (472 mi). Inclination: 84.99 deg. Period: 99.77 min. COSPAR: 1998-055A. USAF Sat Cat: 25489. Tested TAL-D55 plasma engine and was to be part of the NRO's ATex tether experiment. The ATeX lower end mass was meant to remain attached to the STEX parent spacecraft, but with only 21 m of tether deployed, it appeared the tether was so far off vertical that automatic safety systems jettisoned the base to protect the remainder of the STEX satellite. Thus, the upper and lower ATeX end masses were in orbit as one object connected by a 21 m tether, and designated USA 141 (1998-055C). The main STEX satellite was in orbit as a separate object, 1998-055A. References: 2, 279.
  • USA 141 Nation: USA. Payload: ATEX. Class: Technology. Type: Tether. Spacecraft: TiPS. Agency: NRO/NRL. Perigee: 750 km (466 mi). Apogee: 766 km (476 mi). Inclination: 84.99 deg. Period: 99.90 min. COSPAR: 1998-055C. USAF Sat Cat: 25615. NRO's ATeX (Advanced Tether eXperiment) reportedly failed on January 16. The ATeX lower end mass was meant to remain attached to the STEX parent spacecraft, but with only 21 m of tether deployed, it appeared the tether was so far off vertical that automatic safety systems jettisoned the base to protect the remainder of the STEX satellite. Thus, the upper and lower ATeX end masses were in orbit as one object connected by a 21 m tether, and designated USA 141 (1998-055C). The main STEX satellite was in orbit as a separate object, 1998-055A. References: 2, 279.
1998 October 5 - 22:51 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44L. LV Configuration: Ariane 44L-3 V111.
  • Eutelsat W2 Nation: Europe. Program: Eutelsat. Payload: Eutelsat W2. Class: Communications. Spacecraft: Spacebus 3000. Manufacturer: Alcatel, Cannes, France (was Aerospatiale). Agency: Eutelsat. Perigee: 35,779 km (22,231 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.00 deg. COSPAR: 1998-056A. USAF Sat Cat: 25491. Geostationary at 16.0 degrees E. Positioned in geosynchronous orbit at 16 deg E in 1998-1999 As of 4 September 2001 located at 16.17 deg E drifting at 0.015 deg E per day. As of 2007 Mar 11 located at 16.01E drifting at 0.008W degrees per day. References: 2, 279.
  • Sirius 3 Nation: Sweden. Program: Sirius. Payload: Sirius 3. Class: Communications. Spacecraft: HS 376. Manufacturer: Hughes Space and Communications, El Segundo. Agency: NSAB. Perigee: 35,782 km (22,233 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 1998-056B. USAF Sat Cat: 25492. Geostationary at 23.5 degrees E. Positioned in geosynchronous orbit at 28 deg E in 1998-1999; 5 deg E in 2000.- As of 5 September 2001 located at 5.04 deg E drifting at 0.003 deg E per day. As of 2007 Mar 11 located at 4.97E drifting at 0.000W degrees per day. References: 2, 279.
1998 October 7 - 12:00 GMT - Launch Site: Baikonur. Launch Complex: -. Launch Pad: -. Launch Vehicle: UR-100N. Model: UR-100NU.
  • Operational test Nation: Russia. Agency: RVSN RF. Apogee: 1,000 km (600 mi). References: 2.
1998 October 9 - 22:50 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36B. Launch Pad: SLC36B. Launch Vehicle: Atlas. Model: Atlas IIA. LV Configuration: Atlas IIA AC-134.
  • Hot Bird 5 Nation: France. Program: Eutelsat . Mass: 3,000 kg (6,600 lb). Class: Communications. Spacecraft: Eurostar 2000. Manufacturer: Matra Marconi Space-France, Toulouse. Agency: Eutelsat. Perigee: 35,766 km (22,223 mi). Apogee: 35,805 km (22,248 mi). Inclination: 0.00 deg. COSPAR: 1998-057A. USAF Sat Cat: 25495. Geostationary at 10.0 degrees E. Positioned in geosynchronous orbit at 13 deg E in 1998-1999 As of 3 September 2001 located at 12.97 deg E drifting at 0.010 deg E per day. As of 2007 Mar 11 located at 25.56E drifting at 0.014W degrees per day. References: 2.
1998 October 20 - 07:19 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36A. Launch Pad: SLC36A. Launch Vehicle: Atlas. Model: Atlas IIA. LV Configuration: Atlas IIA AC-130.
  • USA 140 Nation: USA. Program: UHF. Payload: UHF F/O F9. Mass: 3,200 kg (7,000 lb). Class: Technology. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: USN. Perigee: 35,773 km (22,228 mi). Apogee: 35,806 km (22,248 mi). Inclination: 3.80 deg. Period: 1,436.20 min. COSPAR: 1998-058A. USAF Sat Cat: 25501. The orbit at burnout of the Centaur was 286 km x 25866 km x 27.0 degree. Modification of the orbit to a geostationary 38,300 km circular x 0.0 degree inclination was accomplished by the Marquardt R-4D liquid propellant motor on the HS-601 spacecraft. The satellite carried UHF and EHF transponders for naval communications, and a Ka-band Global Broadcast Service video relay package. Launch mass of 3200 kg dropped to 1550 kg once geostationary orbit was reached. UHF F/O F9 was placed over the Atlantic Ocean in geosynchronous orbit at 174 deg W in 1998; 22 deg W in 1999. Additional Details: USA 140. References: 2.
1998 October 21 - 16:37 GMT - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5G. LV Configuration: Ariane 5G V112 (503).
  • Maqsat 3 Nation: France. Class: Technology. Spacecraft: MAQSAT. Manufacturer: Kayser-Threde, Munchen. Agency: ESA. Perigee: 1,017 km (631 mi). Apogee: 35,491 km (22,053 mi). Inclination: 7.50 deg. Period: 641.20 min. COSPAR: 1998-059A. USAF Sat Cat: 25503. Maqsat 3 was an instrumentation package used to monitor performance of the Ariane 5 booster. At T+12:43 the Speltra adapter cover separated revealing Maqsat-3. At T+15:14 the EPS stage Aestus engine ignited and burned until T+31:00. At this point on a normal mission the satellite would separate from the EPS, but to avoid creating space debris Maqsat remained attached to the EPS. The EPS/Maqsat-3 was placed in a 1027 km x 35863 km x 7.0 degree geostationary transfer orbit. References: 2.
  • ARD Nation: France. Program: ISS. Payload: Atmospheric Reentry Demonstrator. Class: Technology. Spacecraft: ARD. Agency: Arianespace. COSPAR: 1998-059S. The ARD was an 80 percent scale model of the Apollo Command Module, and a technology test for a possible International Space Station Crew Rescue Vehicle. Equipment included a TDRS satellite communications system; a GPS navigation system; 7 DASA 40 kgf hydrazine attitude control thrusters; a 2.8 m diameter heat shield; three 23 metre diameter parachutes, and a SARSAT recovery beacon. The ARD separated from the Ariane EPS upper stage at 12 minutes 2 seconds after launch. ARD and the EPC stage manoeuvred into a 1 km x 830 km orbit, guaranteeing re-entry at the end of the first orbit. The spacecraft splashed down in the Pacific at 3.69 degrees N, 153.35 degrees W, and was successfully recovered by the French Navy. References: 2.
1998 October 22 - 12:53 GMT - Launch Site: Plesetsk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Topol. Model: Topol M. LV Configuration: Topol-M 5. FAILURE: Failure.
  • Test mission Nation: Russia. Agency: RVSN RF. Apogee: 0 km ( mi). References: 2.
1998 October 23 - 00:02 GMT - Launch Site: Mayport DZ. Launch Complex: -. Launch Pad: 29.0 N x 78.3 W. Launch Vehicle: Pegasus. Model: Pegasus H. LV Configuration: Pegasus H F24/P-33.
  • SCD-2 Nation: Brazil. Mass: 110 kg (240 lb). Class: Communications. Spacecraft: SCD. Manufacturer: Instituto Nacional de Pesquisas Espacias, Sao Jose dos Campos. Agency: INPE. Perigee: 742 km (461 mi). Apogee: 768 km (477 mi). Inclination: 25.00 deg. COSPAR: 1998-060A. USAF Sat Cat: 25504. Brazil's SCD-2 satellite was aboard Orbital Science's L-1011 Stargazer aircraft when it took off from the Cape Canaveral Air Station's Skid Strip (Runway 02/20, 28.2N 80.6W) at 23:05 GMT on Oct 22 and flew to the drop zone near Cape Canaveral (in the Mayport, Florida, Warning Area) at 29.0N 78.3W. The Pegasus ignited 5 seconds after drop. The first stage carried a NASA experiment attached to its right wing, to study hypersonic boundary layer separation. The 115 kg Satelite de Coleta de Dados (Data Collection Satellite) relays data from environmental monitoring stations. References: 2.
1998 October 24 - 12:08 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17A. Launch Pad: SLC17A. Launch Vehicle: Delta. Model: Delta 7326-9.5. LV Configuration: Delta 7326-9.5 D261.
  • Deep Space 1 Nation: USA. Mass: 486 kg (1,071 lb). Class: Planetary. Type: Asteroids. Spacecraft: Deep Space 1. Manufacturer: JPL/SA. Agency: NASA/JPL. COSPAR: 1998-061A. USAF Sat Cat: 25508. The primary mission of Deep Space 1 probe was to test new technology for future interplanetary spacecraft, the main experiment being an ion propulsion engine using xenon propellant. It had an initial mass of 486.3 kg, including 81.5 kg of Xenon and 31.1 kg of hydrazine propellants. The Delta 7326 used three Alliant GEM-40 solid strap-on motors, the standard Delta II core vehicle, and a Thiokol Star 37FM solid motor as the third stage. The Delta second stage entered a 185 km parking orbit, then fired again to enter a 174 km x 2744 km x 28.5 degree orbit. The Star 37FM then separated and accelerated to place Deep Space 1 to escape velocity. Deep Space 1 successfully started its ion engine on November 24 after an initial attempt failed after four minutes on November 10. From its initial solar orbit of 0.99 AU x 1.32 AU x 0.4 degree, Deep Space 1 was to fly past the 3 km diameter asteroid 1992 KD at its perihelion of 1.33 AU. The spacecraft then flew past the nucleus of comet 19P/Borrelly at a distance of 2200 km at 2230 GMT on Sep 22 2001. It survived the encounter in good shape, sending back photos of the comet. At the encounter DS1 was in a 1.3 x 1.5 AU x 0 deg (ecliptic) solar orbit; Borrelly's orbit was 1.3 x 5.9 AU. References: 2, 296.
  • SEDSAT 1 Nation: USA. Program: STS. Class: Technology. Spacecraft: SEDSAT. Manufacturer: SEDS, Univ. Alabama-Huntsville chapter. Agency: SEDS. Perigee: 546 km (339 mi). Apogee: 1,078 km (669 mi). Inclination: 31.40 deg. COSPAR: 1998-061B. USAF Sat Cat: 25509. Following separation of the third stage and the primary Deep Space 1 payload, the Delta second stage manoeuvred from its 185 km parking orbit to a 174 km x 2744 km x 28.5 degree orbit. It then released the SEDSAT micro-satellite, built by the Huntsville, Alabama chapter of SEDS (the Students for the Exploration and Development of Space). SEDSAT has two amateur radio transponders and an earth imaging camera. References: 2.
1998 October 25 - 04:14 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Soyuz 11A511U. LV Configuration: Soyuz 11A511U 660.
  • Progress M-40 Nation: Russia. Program: Mir. Payload: Progress M s/n 239. Class: Manned. Type: Logistics. Spacecraft: Progress M. Manufacturer: RKK Energiya im. S.P. Korolyov, Kaliningrad-Korolyov. Agency: RKA. Perigee: 349 km (216 mi). Apogee: 360 km (220 mi). Inclination: 51.60 deg. Period: 91.63 min. COSPAR: 1998-062A. USAF Sat Cat: 25512. Duration: 103.25 days. Decay Date: 1999-02-05. Flight: Mir EO-26, Mir EO-26/-27. Docked with the rear (+X, Kvant) docking port of the Mir station on October 27. Delivered fuel, dry cargo, and the Znamya-2.5 solar illumination experiment. This was a follow-on to the earlier Znamya-2 experiment on Progress M-15 in 1992. The 25 m diameter Znamya reflector, which would unfold from the nose of the Progress, was to reflect sunlight over a 6 km area onto selected cities. Znamya-2.5 was developed by the Space Regatta Consortium, led by RKK Energia. Energia had long studied such space mirrors as a means of providing lighting to Siberian towns. The project was opposed by environmentalists and astronomers, who feared light pollution. Progress M-40 undocked on February 4, 1999 at 09:59 GMT, but the attempted deployment of the Znamya-2.5 reflector was thwarted when it snagged on a rendezvous system antenna. After two more failed attempts to deploy the antenna the experiment was abandoned. Progress M-40 fired its engines at 10:16 GMT on February 5, braked out of orbit, and burned up over the Pacific Ocean. References: 2.
  • Spoutnik-41 Nation: France. Program: Oscar. Class: Communications. Spacecraft: PS Model. Manufacturer: Astronautical Federation of Russia. Agency: ACF/RuAF. Perigee: 313 km (194 mi). Apogee: 318 km (197 mi). Inclination: 51.70 deg. COSPAR: 1998-062C. USAF Sat Cat: 25533. Decay Date: 1999-01-11. On a space walk from Mir on November 10, Padalka and Avdeyev hand-launched the Spoutnik-41 amateur-radio mini-satellite at around 19:30 GMT. Spoutnik-41, also designated RS-18, was another scale model of the first satellite, Sputnik 1, launched 41 years ago. It carried a small transmitter and was sponsored by Aero Club de France, AMSAT-France, and the Astronautical Federation of Russia. A similar model was launched in 1997 for the fortieth anniversary of Sputnik. On that occasion, two flight models were carried to Mir but only one was launched. The second Spoutnik-40 flight model was still aboard Mir as of 1998. The second Spoutnik-40 would perhaps be deployed prior to the abandonment of Mir in 1999. References: 2.
1998 October 28 - 22:15 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44L. LV Configuration: Ariane 44L-3 V113.
  • Afristar Nation: France. Program: WorldSpace. Class: Communications. Spacecraft: Eurostar 2000. Manufacturer: Matra Marconi Space-France, Toulouse. Agency: Worldspa. Perigee: 35,769 km (22,225 mi). Apogee: 35,805 km (22,248 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1998-063A. USAF Sat Cat: 25515. Afristar was the first WorldSpace satellite. Afristar was to broadcast digital radio over Africa and the Middle East. Small hand-held radios could pick up the 24 to 96 radio channels available on the three L-band beams. Dry mass of Afristar was 1205 kg; it carried 1534 kg of propellant at launch. Geostationary at 21.0 degrees E. Positioned in geosynchronous orbit at 21 deg E in 1998-1999 As of 3 September 2001 located at 20.98 deg E drifting at 0.004 deg W per day. As of 2007 Mar 10 located at 20.98E drifting at 0.010W degrees per day. References: 2.
  • GE 5 Nation: USA. Program: Americom. Mass: 1,720 kg (3,790 lb). Class: Communications. Spacecraft: Eurostar 2000. Manufacturer: Alcatel, Cannes, France (was Aerospatiale). Agency: GE Americom. Perigee: 35,765 km (22,223 mi). Apogee: 35,808 km (22,250 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1998-063B. USAF Sat Cat: 25516. Satellite was originally built as a backup for Argentina's Nahuelsat. This allowed Dornier and Alcatel to deliver the satellite in a record twelve months. Dry mass of GE 5 was 769 kg - it carried 950 kg of propellant at launch. Geostationary at 36.4 degrees W. Positioned in geosynchronous orbit at 79 deg W in 1998-1999 As of 3 September 2001 located at 79.00 deg W drifting at 0.004 deg W per day. As of 2007 Mar 10 located at 78.99W drifting at 0.011W degrees per day. References: 2.
1998 October 29 - 19:19 GMT - Launch Site: Cape Canaveral. Launch Complex: LC39B. Launch Pad: -. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-95.
  • STS-95 Nation: USA. Program: STS. Payload: Discovery F25. Class: Manned. Type: Spaceplane. Spacecraft: Discovery. Manufacturer: Boeing-HB/Alenia. Agency: NASA JSC. Perigee: 550 km (340 mi). Apogee: 561 km (348 mi). Inclination: 28.50 deg. COSPAR: 1998-064A. USAF Sat Cat: 25519. Duration: 8.91 days. Decay Date: 1998-11-07. Crew: Brown, Lindsey, Robinson, Parazynski, Duque, Mukai, Glenn. Flight: STS-95. The flight of STS-95 provoked more publicity for NASA than any other flight in years, due to the presence of ex-astronaut Senator John Glenn on the crew, which also included the first Spanish astronaut, Pedro Duque. The US Navy PANSAT student satellite was deployed on Oct 30 into a 550 km x 561 x 28.5 degree orbit. The Spartan 201 satellite was deployed from Discovery on November 1 and retrieved on November 3. Spartan 201 was on its fifth mission to observe the solar corona. The data on this mission would be used to recalibrate the SOHO satellite which recently resumed observation of the Sun following loss of control. Discovery landed at 17:03:31 GMT November 7 on Runway 33 at the Shuttle Landing Facility at Kennedy Space Center. References: 2, 7.
  • Spartan 201 Nation: USA. Program: STS. Class: Astronomy. Spacecraft: Spartan. Manufacturer: NASA Goddard Space Flight Center, Greenbelt. Agency: NASA GSF. Perigee: 549 km (341 mi). Apogee: 560 km (340 mi). Inclination: 28.40 deg. Period: 95.74 min. COSPAR: 1998-064C. USAF Sat Cat: 25521. Decay Date: 1998-11-07. Retrieved by Discovery November 3 1998. References: 2.
  • Spacehab Nation: USA. Program: STS. Class: Manned. Type: Laboratory. Spacecraft: Spacehab. Manufacturer: Boeing-HB/Alenia. Agency: NASA JSC. Perigee: 550 km (340 mi). Apogee: 560 km (340 mi). Inclination: 28.40 deg. Period: 95.75 min. COSPAR: 1998-064xx. USAF Sat Cat: 25519. Decay Date: 1981-04-13. References: 2.
1998 November 2 - 18:20 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 9. LV Configuration: Black Brant IX NASA 36.171CS.
  • SOPHIE (NCAR / CU-7) Solar ultraviolet mission Nation: USA. Agency: NASA GSFC. Apogee: 300 km (180 mi). References: 2.
1998 November 4 - 05:12 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) 395-02.
  • Panamsat 8 Nation: USA. Program: Panamsat. Payload: PAS 8. Class: Communications. Spacecraft: FS-1300. Manufacturer: Space Systems/Loral, Palo Alto. Agency: Panamsat. Perigee: 35,763 km (22,222 mi). Apogee: 35,810 km (22,250 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 1998-065A. USAF Sat Cat: 25522. The Proton launch vehicles Block DM3 fourth stage put the Panamsat PAS 8 into a 6784 km x 35941 km x 17.3 degree transfer orbit. PAS 8 had 24 C-band and 24 Ku-band transponders and was to be located over the Pacific after its R-4D apogee engine manoeuvred the orbit to geostationary altitude and inclination. Geostationary at 166.1 degrees E. Positioned in geosynchronous orbit at 166 deg E in 1998-1999 As of 4 September 2001 located at 166.05 deg E drifting at 0.003 deg W per day. As of 2007 Mar 9 located at 165.96E drifting at 0.002E degrees per day. References: 2.
1998 November 5 -
  • ait launch from Kodiak Launch Center Nation: USA. The USAF conducted the launch of the ait (atmospheric interceptor technology) suborbital rocket, marking the first launch from the Kodiak Launch Center in Alaska. During the 16-minute flight, the vehicle flew a trajectory that reached an altitude of about 730 km and traveled approximately 1,600 km downrange, landing in the Pacific Ocean west of Seattle, Washington. References: 4.
1998 November 6 - 01:32 GMT - Launch Site: Kodiak. Launch Complex: -. Launch Pad: -. Launch Vehicle: ait. Model: ait.
  • ait-1 test Nation: USA. Agency: USAF/OSC. Apogee: 715 km (444 mi). References: 2.
1998 November 6 - 13:37 GMT - Launch Site: Vandenberg. Launch Complex: SLC2W. Launch Pad: -. Launch Vehicle: Delta. Model: Delta 7920-10C. LV Configuration: Delta 7920-10C D262.
  • Iridium 2 Nation: USA. Program: Iridium. Payload: Iridium s/n SV087. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Manufacturer: LM-S/Motorola. Agency: Iridium. Perigee: 590 km (360 mi). Apogee: 603 km (374 mi). Inclination: 85.60 deg. Period: 96.60 min. COSPAR: 1998-066A. USAF Sat Cat: 25527. Plane 5. Ascending node 289.1 degrees. Parking orbit. References: 2.
  • Iridium 86 Nation: USA. Program: Iridium. Payload: Iridium s/n SV086. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Manufacturer: LM-S/Motorola. Agency: Iridium. Perigee: 708 km (439 mi). Apogee: 712 km (442 mi). Inclination: 86.50 deg. Period: 99.00 min. COSPAR: 1998-066B. USAF Sat Cat: 25528. Plane 5. Ascending node 293.9 degrees. Raising orbit. References: 2.
  • Iridium 85 Nation: USA. Program: Iridium. Payload: Iridium s/n SV085. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Manufacturer: LM-S/Motorola. Agency: Iridium. Perigee: 512 km (318 mi). Apogee: 536 km (333 mi). Inclination: 86.02 deg. Period: 95.12 min. COSPAR: 1998-066C. USAF Sat Cat: 25529. Decay Date: 2000-12-30. Plane 5. Ascending node 291.1 degrees. Parking orbit. References: 2.
  • Iridium 84 Nation: USA. Program: Iridium. Payload: Iridium s/n SV084. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Manufacturer: LM-S/Motorola. Agency: Iridium. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1998-066D. USAF Sat Cat: 25530. Plane 5. Ascending node 294.1 degrees. Raising orbit. References: 2.
  • Iridium 83 Nation: USA. Program: Iridium. Payload: Iridium s/n SV083. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Manufacturer: LM-S/Motorola. Agency: Iridium. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1998-066E. USAF Sat Cat: 25531. Plane 5. Ascending node 294.2 degrees. References: 2.
1998 November 7 -
  • Landing of STS-95 Nation: USA. Program: STS. Flight: STS-95. STS-95 landed at 17:03 GMT.
1998 November 11 - 19:23 GMT -
  • EVA Mir EO-26-2 Nation: Russia. Program: Mir. Class: Manned. Type: Space station. Spacecraft: Mir. Crew: Padalka, Avdeyev. Flight: Mir EO-26, Mir EO-26/-27. EVA Duration: 0.25 days. Padalka and Avdeyev made the EVA from the Kvant-2 airlock on the Mir. The walk began at 19:24 GMT. The cosmonauts installed a meteoroid detector in for the upcoming Leonid shower, and hand-launched the Spoutnik-41 amateur-radio mini-satellite. The space walk concluded at 01:18 GMT on November 11.
1998 November 18 - 15:40 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 9. LV Configuration: Black Brant IX NASA 36.178NM.
  • Microgravity mission Nation: USA. Agency: NASA GSFC. Apogee: 300 km (180 mi). References: 2.
1998 November 18 - 23:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1A. LV Configuration: TR-1A TR-1A-7.
  • Microgravity mission Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi). References: 2.
1998 November 19 -
  • China Astronaut Training Group 1 selected. Nation: China. Selection of astronauts to fly the Project 921 / Shenzhou manned spacecraft began at the end of 1995. Only PLAAF pilots were considered. Review of service records identified 1504 candidates, further reduced to 886 after stricter screening. In the summer of 1996, 60 candidates passed initial testing at their home bases and were sent to Beijing for final tests and interviews. By April 1997 the candidate list had been pared down to 20, and the final 12 were selected at the end of 1997. The group was officially established in January 1998. In March, 1998, the two Chinese astronauts trained in Russia in 1996, who were also the trainers of this first group of 12 cosmonauts, joined the group officially as candidates for future spaceflights, bringing the total to 14.
1998 November 20 - Launch Site: Barking Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Aries. LV Configuration: Aries TTV-1.
  • TTV-1 Target mission Nation: USA. Agency: USA SMDC. Apogee: 322 km (200 mi). References: 2.
1998 November 20 - 06:40 GMT - Launch Site: Baikonur. Launch Complex: LC81/23. Launch Pad: -. Launch Vehicle: Proton. Model: Proton-K. LV Configuration: Proton-K 395-01.
  • Zarya Nation: USA. Program: ISS. Payload: FGB 77KM s/n 175-01. Class: Manned. Type: Space station. Spacecraft: ISS Zarya. Manufacturer: Khrunichev. Agency: NASA. Perigee: 397 km (246 mi). Apogee: 402 km (249 mi). Inclination: 51.60 deg. COSPAR: 1998-067A. USAF Sat Cat: 25544. This was the first launch in the assembly of the International Space Station. The Zarya FGB was funded by NASA and built by Khrunichev in Moscow under subcontract from Boeing for NASA. Its design from the TKS military station resupply spacecraft of the 1970’s and the later 77KS Mir modules. Zarya included a multiple docking adapter, a pressurised cabin section, and a propulsion/instrument section with a rear docking port. Initial orbit was 176 lm x 343 km x 51.6 degrees. By November 25 it had manoeuvred to a 383 km x 396 km x 51.7 degree orbit, awaiting the launch of Shuttle mission STS-88 which docked the Unity node to it. References: 2.
1998 November 22 -
  • Galileo, Europa 18 Flyby Nation: USA. Spacecraft: Galileo.
1998 November 22 - 23:54 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: SLC17B. Launch Vehicle: Delta. Model: Delta 7925-9.5. LV Configuration: Delta 7925-9.5 D263.
  • BONUM-1 Nation: Russia. Program: BONUM. Class: Communications. Spacecraft: HS 376. Manufacturer: Hughes Space and Communications, El Segundo. Agency: Telenor. Perigee: 35,785 km (22,235 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.10 deg. COSPAR: 1998-068A. USAF Sat Cat: 25546. BONUM-1 provided domestic Russian television service for Media Most, a Moscow media enterprise, broadcasting 50 channels to western Russia from a geostationary orbit at 36 degrees E. Mass was 1426 kg at launch, 800 kg of that propellant. BONUM-1 carried 8 Ku-band transponders. The Delta upper stage raised the initial 157 km x 189 km at 29.2 degree parking orbit to 159 km x 1304 km and then 1228 km x 1683 km at 26.7 degrees. A Thiokol Star 48B solid third stage boosted BONUM-1 to a 1285 x 36703 km x 19.5 degree geostationary transfer orbit, with the Thiokol Star 30 apogee kick motor placing the satellite in its final geostationary orbit. After separation of the spacecraft, the Delta made a final depletion burn to lower its orbit to 274 km x 1552 km x 25.6 degree to ensure it would quickly decay and burn up in the atmosphere. Geostationary at 35.9 degrees E. From 8 August 2000 position was 56.0 degrees E. Positioned in geosynchronous orbit at 36 deg E in 1998-1999 55 deg E in 2000. As of 5 September 2001 located at 56.03 deg E drifting at 0.016 deg W per day. As of 2007 Mar 10 located at 55.94E drifting at 0.008W degrees per day. References: 2.
1998 November 24 - 09:53 GMT - Launch Site: Kiruna. Launch Complex: -. Launch Pad: -. Launch Vehicle: Maxus. LV Configuration: Maxus MAXUS 3.
  • Biological/Physics mission Nation: Europe. Agency: SSC/ESA. Apogee: 713 km (443 mi). References: 2.
1998 December 3 - 11:04 GMT - Launch Site: Kiruna. Launch Complex: -. Launch Pad: -. Launch Vehicle: Hawk. Model: Nike Improved Orion. LV Configuration: Nike Improved Orion DLR K-NO2-237.
  • Mini-Texus 6 Microgravity mission Nation: Germany. Agency: DLR. Apogee: 140 km (80 mi). References: 2.
1998 December 4 - 08:35 GMT - Launch Site: Cape Canaveral. Launch Complex: LC39A. Launch Pad: -. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-88.
  • STS-88 Nation: USA. Program: ISS. Payload: Endeavour F13. Class: Manned. Type: Spaceplane. Spacecraft: Endeavour. Manufacturer: Boeing Palmdale (formerly Rockwell/North American). Agency: NASA JSC. Perigee: 180 km (110 mi). Apogee: 322 km (200 mi). Inclination: 51.60 deg. COSPAR: 1998-069A. USAF Sat Cat: 25549. Duration: 11.80 days. Decay Date: 1998-12-16. Crew: Cabana, Sturckow, Ross, Currie, Newman, Krikalyov. Flight: STS-88. First attempted launch of STS-88 was scrubbed at 09:03 GMT on December 3 due to a problem with a hydraulic system sensor. Launch came the next day, with Endeavour entering an initial 75 km x 313 km x 51.6 degree orbit. Half an orbit after launch, at 09:19 GMT, Endeavour fired its OMS engines to raise the orbit to 180 km x 322 km x 51.6 degree.

    On December 5 at 22:25 GMT Nancy Currie unberthed the Unity space station node from the payload bay using the RMS arm. She then moved the Unity to a position docked to the Orbiter Docking System in the payload bay in readiness for assembly with the Russian-launched Zarya FGB ISS component. After rendezvous with the Zarya FGB module, on December 6 at 23:47 GMT Endeavour grappled Zarya with the robot arm, and at 02:07 GMT on December 7 it was soft docked to the PMA-1 port on Unity. After some problems hard dock was achieved at 02:48 GMT. Unity and Zarya then formed the core of the future International Space Station. Ross and Newman made three space walks to connect cables between Zarya and Unity, on December 7, 9 and 12. On the last EVA a canvas tool bag was attached to the exterior of Unity to provide tools for future station assembly workers. Docking cables were disconnected to prevent Unity and Zarya from inadvertently undocking. Following an internal examination of the embryonic space station, Endeavour undocked at 20:30 GMT on December 13. The SAC-A and Mightysat satellites were ejected from the payload bay on December 14 and 15. Deorbit burn was December 16 at 03:48 GMT, and Endeavour landed at 04:53:29 GMT, on Runway 15 at the Kennedy Space Center.

    Payloads included:

    • Sill: RMS arm No. 303
    • Bay 1-2: Tunnel Adapter 002
    • Bay 3-4: Orbiter Docking System/External Airlock (Boeing/Palmdale)
    • Bay 7-13: Unity (Node 1) (Boeing/Huntsville), including the PMA-1 and PMA-2 docking adapters (Boeing/Huntington Beach)
    • Bay 2 Port: GABA adapter with SAC-A satellite
    • Bay 4 Starboard: Carrier with Tool Stowage Assembly
    • Bay 5 Port: GABA adapter with two PFR space walk platforms and one PFR stanchion.
    • Bay 5 Starboard: GABA adapter with two more PFR space walk platforms and one PFR stanchion.
    • Bay 6 Port: GABA adapter with Mightysat
    • Bay 6 Starboard: APC carrier with TCS laser rendezvous sensor
    • Bay 7 Starboard: APC carrier with TCS laser rendezvous sensor
    • Bay 13 Port: GABA adapter with SEM-7 and G-093 canisters
    • Bay 13 Starboard: GABA adapter with IMAX Cargo Bay Camera
    References: 2, 7.
  • SAC-A Nation: Argentina. Program: SAC. Mass: 68 kg (149 lb). Class: Technology. Spacecraft: SAC-A. Manufacturer: INVAP SE, Bariloche, Argentina. Agency: CONAE. Perigee: 381 km (236 mi). Apogee: 398 km (247 mi). Inclination: 51.60 deg. COSPAR: 1998-069B. USAF Sat Cat: 25550. Decay Date: 1999-10-25. SAC-A was to provide engineering bench testing for new space science technology instruments and equipment that will be used in a more complex spacecraft for the Argentine space program. References: 2.
  • Mightysat 1 Nation: USA. Mass: 320 kg (700 lb). Class: Technology. Spacecraft: Mightysat 1. Manufacturer: Orbital Sciences Corp., McLean (formerly DSI and CTA). Agency: USAF. Perigee: 381 km (236 mi). Apogee: 395 km (245 mi). Inclination: 51.60 deg. COSPAR: 1998-069C. USAF Sat Cat: 25551. Decay Date: 1999-11-21. First flight of a USAF Philips Laboratory/Space Experiments Directorate ejectable technology demonstration platform. Four advanced technologies demonstrated, including composite structure, advanced solar cells, advanced electronics, and a shock device. References: 2.
  • Unity Nation: USA. Program: ISS. Class: Manned. Type: Space station. Spacecraft: ISS Unity. Manufacturer: Boeing Huntington Beach (formerly McDonnell Douglas). Agency: NASA JSC. Perigee: 387 km (240 mi). Apogee: 400 km (240 mi). Inclination: 51.50 deg. Period: 92.43 min. COSPAR: 1998-069F. USAF Sat Cat: 25575. Decay Date: 1972-01-01. References: 2.
1998 December 6 - 00:43 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 42L. LV Configuration: Ariane 42L-3 V114.
  • Satmex 5 Nation: Mexico. Program: Morelos. Mass: 4,135 kg (9,116 lb). Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: Satmex. Perigee: 35,774 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1998-070A. USAF Sat Cat: 25558. The Ariane placed the Satmex 5 satellite into a 211km x 21516 km x 7.0 degree orbit from which the satellite was to use its on-board engine to reach geostationary orbit. Satmex 5 was operated by Satellites Mexicanos S.A. de C.V, which took over the Morelos constellation from Mexican Secretaria de Comunicaciones y Transportes. Satmex 5 replaced Morelos 2 and carried the XIPS ion engine station-keeping system. Positioned in geosynchronous orbit at 116 deg W in 1998-1999 As of 5 September 2001 located at 116.79 deg W drifting at 0.008 deg W per day. As of 2007 Mar 10 located at 116.81W drifting at 0.002W degrees per day. References: 2.
1998 December 6 - 00:57 GMT - Launch Site: Point Arguello WADZ. Launch Complex: -. Launch Pad: 36.0 N x 123.0 W. Launch Vehicle: Pegasus. Model: Pegasus XL. LV Configuration: Pegasus XL F25.
  • SWAS Nation: USA. Program: Small Explorer. Class: Astronomy. Spacecraft: SWAS. Manufacturer: NASA Goddard Space Flight Center, Greenbelt. Agency: NASA GSF. Perigee: 637 km (395 mi). Apogee: 651 km (404 mi). Inclination: 69.90 deg. COSPAR: 1998-071A. USAF Sat Cat: 25560. On December 3 the Orbital Sciences L-1011 Stargazer took off from Vandenberg AFB Runway 30/12 carrying a Pegasus XL launch vehicle with the SWAS satellite aboard. It reached the drop box at 36.0N 123.0W over the Pacific, but due to a software-related problem the range ordered the launch scrubbed and the L-1011 returned to base. After a further delay due to weather, the L-1011 took off at 23:58 GMT on December 5 and SWAS reached orbit and separated from the third stage at 01:09 GMT. SWAS, the Sub-millimetre Wave Astronomy Satellite, had a 0.6m telescope with a 490 to 550 GHz sub-millimetre receiver and an acousto-optical spectrometer. SWAS was used to study the cooling of molecular cloud cores, the sites of star formation in our galaxy, by measuring lines from molecular oxygen and water. References: 2.
1998 December 8 - 11:25 GMT - Launch Site: Plesetsk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Topol. Model: Topol M. LV Configuration: Topol-M 6.
  • Test mission Nation: Russia. Agency: RVSN RF. Apogee: 1,000 km (600 mi). References: 2.
1998 December 8 - 22:10 GMT - 1998 December 9 - 10:20 GMT - Launch Site: Plesetsk. Launch Complex: -. Launch Pad: -. Launch Vehicle: RT-23. Model: RT-23U 15Zh61. LV Configuration: RT-23U 15Zh61 15Zh61.
  • Test mission Nation: Russia. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 2.
1998 December 10 - Launch Site: Baikonur. Launch Complex: -. Launch Pad: -. Launch Vehicle: UR-100N. Model: UR-100NU.
  • Operational test Nation: Russia. Agency: RVSN RF. Apogee: 1,000 km (600 mi). References: 2.
1998 December 10 - 11:57 GMT - Launch Site: Plesetsk. Launch Complex: LC132/1. Launch Pad: -. Launch Vehicle: Kosmos 3. Model: Kosmos 11K65M.
  • Nadezhda 5 Nation: Russia. Payload: Tsikada-Kospas. Class: Navigation. Spacecraft: Nadezhda. Manufacturer: AKO Polyot, Omsk. Agency: MO RF. Perigee: 976 km (606 mi). Apogee: 1,013 km (629 mi). Inclination: 83.00 deg. COSPAR: 1998-072A. USAF Sat Cat: 25567. References: 2.
  • Astrid-2 Nation: Sweden. Mass: 30 kg (66 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Astrid-2. Manufacturer: Swedish Space Corporation. Agency: SSC. Perigee: 978 km (607 mi). Apogee: 1,013 km (629 mi). Inclination: 83.00 deg. COSPAR: 1998-072B. USAF Sat Cat: 25568. Swedish Space Corporation micro-satellite Astrid-2 was ejected from the Nadezdha 5 COSPAS satellite at 15:25 GMT and was to measure the auroral electromagnetic fields and particle environment. References: 2.
1998 December 10 - 20:33 GMT -
  • EVA STS-88-2 Nation: USA. Program: ISS. Class: Manned. Type: Space station. Spacecraft: International Space Station. Crew: Ross, Newman. Flight: STS-88. EVA Duration: 0.29 days. Continued assembly of International Space Station. Connected cables between Zarya and Unity modules and deployed antennae.
1998 December 11 - 18:45 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17A. Launch Pad: SLC17A. Launch Vehicle: Delta. Model: Delta 7425-9.5. LV Configuration: Delta 7425-9.5 D264.
  • Mars Climate Orbiter Nation: USA. Program: Mars Surveyor. Mass: 629 kg (1,386 lb). Class: Planetary. Type: Mars. Spacecraft: MCO. Manufacturer: Lockheed Martin Astronautics, Denver (formerly Martin). Agency: JPL. COSPAR: 1998-073A. USAF Sat Cat: 25571. Decay Date: 1999-09-23. The Mars Climate Orbiter was the second flight of the Mars Surveyor Program. The probe was to enter a 160 km x 38600 km polar orbit around Mars on September 23,1999, and use aerobraking to reach a 373 km x 437 km x 92.9 degree sun-synchronous mapping orbit by November 23 1999. While the Mars Orbit Insertion burn began as planned on September 23, 1999 at 08:50 GMT, no signal was received after the spacecraft went behind the planet. Subsequent investigation showed that the spacecraft had plunged deep into the Martian atmosphere, with its closest approach to Mars being 57 km. It was concluded that the spacecraft burnt up in the atmosphere. It was later found that cutbacks in tracking, combined with incorrect values in a look-up table imbedded deep in the spacecraft software (use of pounds force instead of newtons) were to blame. This failure led to a shake-up of NASA's 'faster, better, cheaper' approach to unmanned spaceflight. Additional Details: Mars Climate Orbiter. References: 2.
1998 December 13 - 20:33 GMT -
  • EVA STS-88-3 Nation: USA. Program: ISS. Class: Manned. Type: Space station. Spacecraft: International Space Station. Crew: Ross, Newman. Flight: STS-88. EVA Duration: 0.29 days. Completed initial assembly of International Space Station. A canvas tool bag was attached to the exterior of Unity to provide tools for future assembly workers. Also disconnected some docking cables, so that Unity and Zarya could no longer undock.
1998 December 15 -
  • Landing of STS-88 Nation: USA. Program: ISS. Flight: STS-88. STS-88 landed at 04:16 GMT.
1998 December 18 - 1998 December 19 - 11:39 GMT - Launch Site: Taiyuan. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: CZ. Model: CZ-2C/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-20 (55).
  • Iridium 11 Nation: USA. Program: Iridium. Payload: Iridium s/n SV088?. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Manufacturer: LM-S/Motorola. Agency: Iridium. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1998-074A. USAF Sat Cat: 25577. Plane 2. Ascending node 197 degrees. Parking orbit. References: 2.
  • Iridium 20 Nation: USA. Program: Iridium. Payload: Iridium s/n SV089?. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Manufacturer: LM-S/Motorola. Agency: Iridium. Perigee: 709 km (440 mi). Apogee: 710 km (440 mi). Inclination: 86.50 deg. Period: 99.00 min. COSPAR: 1998-074B. USAF Sat Cat: 25578. Plane 2. Ascending node 197.2 degrees. Parking orbit. References: 2.
1998 December 22 - 01:08 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 42L. LV Configuration: Ariane 42L-3 V115.
  • PAS 6B Nation: USA. Program: Panamsat. Mass: 3,475 kg (7,661 lb). Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: Panamsat. Perigee: 35,782 km (22,233 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1998-075A. USAF Sat Cat: 25585. The Ariane third stage placed the PAS 6B into a 228 km x 35717 km x 7.0 degree orbit. The satellite’s on board rocket system will move it into its final geostationary position over South America. PAS 6B will provide direct TV broadcasting service in replacement of PAS 6, a Loral satellite which had problems with its solar arrays. The new satellite had 32 Ku-band transponders. Positioned in geosynchronous orbit at 43 deg W in 1999. As of 3 September 2001 located at 43.17 deg W drifting at 0.020 deg W per day. As of 2007 Mar 9 located at 43.11W drifting at 0.015W degrees per day. References: 2.
1998 December 24 - 20:02 GMT - Launch Site: Plesetsk. Launch Complex: LC132/1. Launch Pad: -. Launch Vehicle: Kosmos 3. Model: Kosmos 11K65M.
  • Cosmos 2361 Nation: Russia. Mass: 825 kg (1,818 lb). Class: Navigation. Spacecraft: Parus. Manufacturer: AKO Polyot, Omsk. Agency: MO RF. Perigee: 969 km (602 mi). Apogee: 1,013 km (629 mi). Inclination: 82.90 deg. COSPAR: 1998-076A. USAF Sat Cat: 25590. A Parus navigation satellite in the same orbital plane as Cosmos 2233. References: 2.
1998 December 30 - Launch Site: Baikonur. Launch Complex: LC200/39. Launch Pad: -. Launch Vehicle: Proton. Model: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 385-02.
  • Cosmos 2362 Nation: Russia. Class: Navigation. Spacecraft: Glonass. Manufacturer: AKO Polyot, Omsk. Agency: MOM. Perigee: 19,115 km (11,877 mi). Apogee: 19,134 km (11,889 mi). Inclination: 64.80 deg. COSPAR: 1998-077A. USAF Sat Cat: 25593. References: 2.
  • Cosmos 2363 Nation: Russia. Class: Navigation. Spacecraft: Glonass. Manufacturer: AKO Polyot, Omsk. Agency: MOM. Perigee: 19,122 km (11,881 mi). Apogee: 19,126 km (11,884 mi). Inclination: 64.80 deg. COSPAR: 1998-077B. USAF Sat Cat: 25594. References: 2.
  • Cosmos 2364 Nation: Russia. Class: Navigation. Spacecraft: Glonass. Manufacturer: AKO Polyot, Omsk. Agency: MOM. Perigee: 19,125 km (11,883 mi). Apogee: 19,127 km (11,884 mi). Inclination: 64.80 deg. COSPAR: 1998-077C. USAF Sat Cat: 25595. References: 2.
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