1999 - Launch Vehicle: Roton. -
 The Roton large-scale Air Test Vehicle began flight tests Nation: USA. The Roton large-scale Air Test Vehicle began flight tests to demonstrate the autorotation and rotor capabilities. Thereafter technical challenges and lack of sufficient investment seemed to stall the project and then kill the project.
1999 January 3 - -
 US Says Chinese Obtained Secrets Nation: China. A special House committee found that technology transfers to China by Hughes Electronics and Loral Space and Communications harmed U.S. national security. The 700-page, five-volume report was classified. The Chinese government sharply denied allegations that it had mounted a 'serious and sustained' effort over the last 20 years to obtain militarily useful U.S. technology.
References: 424.
1999 January 3 - 20:21 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: SLC17B. Launch Vehicle: Delta. Model: Delta 7425-9.5. LV Configuration: Delta 7425-9.5 D265. - Mars Polar Lander Nation: USA. Mass: 576 kg (1,269 lb). Class: Planetary. Type: Mars. Spacecraft: Mars Polar Lander. Manufacturer: Lockheed Martin Astronautics, Denver. Agency: JPL. COSPAR: 1999-001A. USAF Sat Cat: 25605. Decay Date: 1999-12-03. The Mars Polar Lander was placed by the first burn of the second stage into a 157 x 245 km x 28.35 deg parking orbit. The second stage restarted at 20:55 GMT and shut down in a 226 x 740 km x 25.8 deg Earth orbit. The solid rocket third stage (a Star 48B with a Nutation Control System and a yo-yo despin device) then ignited and put the spacecraft into solar orbit, separating at 21:02 GMT. Mars Polar Lander was to land near the south pole of Mars on December 3, 1999, and conduct conduct a three month mission, trenching near its landing site and testing for the presense of frozen water and carbon dioxide. Attached were two Deep Space 2 Microprobes, penetrators which would impact the Martian surface separately from the lander and return data on subsurface conditions from widely spaced points.
When the spacecraft reached Mars on December 3, the lander separated from the cruise stage at 19:51 UTC and the two penetrators, Scott and Amundsen, were to separate about 20 seconds later. No further communications were ever received from the spacecraft. Landing had been expected at 20:01 UTC at 76.1S 195.3W, with the penetrators landing a few kilometres from each other at 75.0S 196.5W.
This failure resulted in a review and reassessment of NASA's 'faster, better, cheaper' approach to planetary missions.
References: 2.
- DS2 Microprobe 1 Nation: USA. Class: Planetary. Type: Mars. Agency: Boeing/H. COSPAR: 1999-001B. USAF Sat Cat: 25606. References: 2.
- DS2 Microprobe 2 Nation: USA. Class: Planetary. Type: Mars. Agency: Boeing/H. Perigee: 220 km (130 mi). Apogee: 645 km (400 mi). Inclination: 25.80 deg. Period: 93.23 min. COSPAR: 1999-001C. USAF Sat Cat: 25607. Decay Date: 1999-03-23. References: 2.
1999 January 5 - -
 Energia Engineer Cosmonaut Training Group 14 Supplemental selected. Nation: Russia.
1999 January 6 - - Plans for Chinese Manned Flight Officially Reported Nation: China. Spacecraft: Shenzhou. The official Chinese Liberation Daily reported that a Chinese manned flight would take place "by the end of this century or the beginning of the next," . This would make China the first country in more than 30 years to join the United States and Russia in the exclusive club of manned mission launchers.
References: 424.
1999 January 8 - - Chinese Module on ISS explored Nation: China. Program: ISS. It was reported that China and Russia once discussed docking a Chinese module to the Russian section of the International Space Station. Spare docking ports would provide attachment points for Ukrainian and Chinese modules. Such possibilities had been discussed at the highest political levels.
References: 424.
1999 January 15 - -
 Wild Fire engine test. Nation: Canada. Program: X-Prize. The da Vinci Project (Toronto, Ontario, Canada) successfully tests single engine propulsion
system.
1999 January 15 - Launch Site: Sonmiani. Launch Complex: -. Launch Pad: -. Launch Vehicle: Shaheen. Model: Shaheen 1. FAILURE: Failure. -
 Test mission Nation: Pakistan. Agency: Pakistan. Apogee: 0 km ( mi). References: 2.
1999 January 18 - - Chinese tracking fleet upgraded Nation: China. Spacecraft: Shenzhou. A sixteen month overhaul of China's space tracking fleet was completed in Shanghai. The upgraded ships were capable of global tracking and control with a 400-fold increase in data transfer rates. The fleet was now ready for support of the first test launch of a Chinese manned spacecraft. To support this, for the first time three Yuanwang tracking ships would be deployed in the Pacific, Indian, and Atlantic Oceans.
References: 424.
1999 January 21 - 06:13 GMT - Launch Site: Andoya. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 12. LV Configuration: Black Brant XII NASA 40.12IE. - CAPER Ionosphere mission Nation: USA. Agency: NASA. Apogee: 1,360 km (840 mi). References: 2.
1999 January 22 - 13:57 GMT - Launch Site: Poker Flat. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 12. LV Configuration: Black Brant XII NASA 40.13DP. - North Star (APEX) Active plasma mission Nation: USA. Agency: NASA. Apogee: 364 km (226 mi). References: 2.
1999 January 22 - 15:20 GMT - Launch Site: Poker Flat. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 5B. LV Configuration: Black Brant VB NASA 21.121CE. - Ionosphere mission Nation: USA. Agency: NASA. Apogee: 250 km (150 mi). References: 2.
1999 January 22 - 15:31 GMT - Launch Site: Poker Flat. Launch Complex: -. Launch Pad: -. Launch Vehicle: Honest John. Model: Taurus Orion. LV Configuration: Taurus Orion NASA 33.068UE. - Ionosphere mission Nation: USA. Agency: NASA. Apogee: 200 km (120 mi). References: 2.
1999 January 27 - 00:34 GMT - Launch Site: Cape Canaveral. Launch Complex: LC46. Launch Pad: SLC46. Launch Vehicle: Athena. Model: Athena-1. LV Configuration: Athena-1 LM-006. -
 ROCSAT-1 Nation: Taiwan. Mass: 400 kg (880 lb). Class: Earth. Spacecraft: ROCSAT. Manufacturer: TRW, Redondo Beach. Agency: NSPO. Perigee: 606 km (376 mi). Apogee: 653 km (405 mi). Inclination: 35.00 deg. COSPAR: 1999-002A. USAF Sat Cat: 25616. Taiwan's first satellite, with experimental communications, ocean imagery, and ionospheric studies instruments. The Primex OAM placed itself and the payload into an elliptical transfer orbit. A second OAM burn circularized the orbit, and ROCSAT separated into a 588 x 601 km x 35.0 deg orbit.
References: 2.
1999 February 1 - - Galileo, Europa 19 Flyby Nation: USA. Spacecraft: Galileo.
1999 February 2 - 01:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-28. -
 SELENE RF / X-ray test Ionosphere / x-ray mission Nation: Japan. Agency: ISAS. Apogee: 184 km (114 mi). References: 2.
1999 February 7 - 21:04 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17A. Launch Pad: SLC17A. Launch Vehicle: Delta. Model: Delta 7426-9.5. LV Configuration: Delta 7426-9.5 D266. - Stardust Nation: USA. Program: Discovery. Payload: Discovery 4. Mass: 370 kg (810 lb). Class: Planetary. Type: Comet. Spacecraft: Stardust. Manufacturer: Lockheed Martin Astronautics, Denver. Agency: JPL. COSPAR: 1999-003A. USAF Sat Cat: 25618. Stardust was to fly within 100 km of comet 81P/Wild-2 in January 2004 and recover cometary material using an aerogel substance. A return capsule would land on a lake bed in Utah in January 2006, returning the material to earth. The launch went as planned. The second stage ignited at 21:08 GMT and its first burn put the vehicle into a 185 km x 185 km x 28 degree parking orbit at 21:14 GMT. The second stage second burn at 21:25 changed the orbit to planned values of 178 km x 7184 km x 28.5 degrees. The Star 37FM solid third stage ignited at 21:29 GMT and placed the spacecraft into a 2 year period solar orbit. The spacecraft separated at 21:31 GMT. Meanwhile, the Delta 266 second stage burned a third time on its own, until its propellants were depleted, entering a final orbit of 294 km x 6818 km x 22.5 degrees. The Stardust probe flew past Earth at a distance of 3706 km at 1115 GMT on January 15, 2001, and flew near the Moon at a distance of 98000 km at around 0200 GMT on January 16. The gravity assist flyby changed Stardust's heliocentric orbit from 0.956 x 2.216 AU x 0.0 deg to 0.983 x 2.285 AU x 3.7 deg.
References: 2.
1999 February 9 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Trident. Model: Trident D-5. LV Configuration: Trident D-5 FCET-20. - 82? Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1999 February 9 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Trident. Model: Trident D-5. LV Configuration: Trident D-5 FCET-20. - Trident D-5 82? operational test launch Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1999 February 9 - 03:53 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Soyuz 11A511U. LV Configuration: Soyuz 11A511U/Ikar S15000-058 ST01. - Globalstar FM36 Nation: USA. Mass: 222 kg (489 lb). Class: Communications. Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. COSPAR: 1999-004A. USAF Sat Cat: 25621. The first launch of the Soyuz- Ikar launch vehicle, selected by Orbcomm after failure of the Zenit launcher. The Ikar upper stage was derived from the Yantar reconnaissance satellite's propulsion module. The Soyuz second stage separated at 8 minutes 48 seconds into flight after placing the Ikar into a 236 km x 884 km x 52.0 deg transfer orbit. The Ikar stage burned at the second apogee passage, at 06:23 GMT, and released the Globalstar satellite at the top of the dispenser into a 915 km x 947 km x 52.0 deg orbit at 07:27 GMT. The three remaining satellites mounted around the side of the dispenser were released into a 903 km x 946 km x 52.0 deg orbit. This was also the first launch carried out by the Starsem organization, a joint venture including Aerospatiale and TsSKB-Progress (the launch vehicle manufacturer). The dispenser was built by Aerospatiale/Aquitaine (Bordeaux).
References: 2.
- Globalstar FM23 Nation: USA. Mass: 222 kg (489 lb). Class: Communications. Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. COSPAR: 1999-004B. USAF Sat Cat: 25622. References: 2.
- Globalstar FM38 Nation: USA. Mass: 222 kg (489 lb). Class: Communications. Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. COSPAR: 1999-004C. USAF Sat Cat: 25623. References: 2.
- Globalstar FM40 Nation: USA. Mass: 222 kg (489 lb). Class: Communications. Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. COSPAR: 1999-004D. USAF Sat Cat: 25624. References: 2.
1999 February 10 - 08:06 GMT - Launch Site: Vandenberg. Launch Complex: LF04. Launch Pad: -. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 GT169GM. - FOT GT169GM Follow-on Test launch Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi). References: 2.
1999 February 11 - 06:45 GMT - Launch Site: Poker Flat. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 10. LV Configuration: Black Brant X NASA 35.032UE. - ENSTROPHY Ionosphere mission Nation: USA. Agency: NASA GSFC. Apogee: 1,071 km (665 mi). References: 2.
1999 February 12 - - China to Test Reusable Spacecraft at the end of 2000 Nation: China. Spacecraft: Shenzhou. China planned to launch its own re-usable "space shuttle" with a maiden unmanned mission at the end of next year, said an astronomical engineer in charge of one of dozens of scientific research payloads that will be aboard. The engineer said the lift-capacity problems have already been resolved and he had been briefed on the cost of the Chinese shuttle but that he could not reveal it, as the information is classified. (AFP)
References: 424.
1999 February 15 - 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) 396-01. - Telstar 6 Nation: USA. Program: Telstar. Mass: 3,700 kg (8,100 lb). Class: Communications. Spacecraft: FS-1300. Manufacturer: Space Systems/Loral, Palo Alto. Agency: Loral Sk. Perigee: 35,781 km (22,233 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. COSPAR: 1999-005A. USAF Sat Cat: 25626. Loral Skynet's Telstar 6 had a mixed C and Ku band communications payload. The Block DM3 upper stage released Telstar 6 in a 6638 km x 35,756 km x 17.4 degree geosynchronous transfer orbit. After the first burn of its on-board R-4D engine on February 18, Telstar 6 was in a 15,037 km x 35,800 km x 7.9 deg transfer orbit heading for its final geosynchronous slot at 93 deg W Positioned in geosynchronous orbit at 93 deg W in 1999. As of 2 September 2001 located at 93.01 deg W drifting at 0.004 deg W per day. As of 2007 Mar 11 located at 93.03W drifting at 0.007W degrees per day.
References: 2.
1999 February 16 - 01:45 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36A. Launch Pad: SLC36A. Launch Vehicle: Atlas. Model: Atlas IIAS. LV Configuration: Atlas IIAS AC-152. - JCSAT-6 Nation: Japan. Program: JCSAT. Mass: 2,900 kg (6,300 lb). Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: JSAT. Perigee: 35,784 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1999-006A. USAF Sat Cat: 25630. JCSAT-6 carried a Ku-band relay system. It was operated by Japan Satellite Systems, Inc., Tokyo, provided communications and data relay for Japan and the Pacific Rim. Two burns of the Centaur upper stage placed it into a supersynchronous transfer orbit of 258 km x 96736 km x 24.1 degrees. JCSAT-6's on-board R-4D engine would maneuver it into its final geostationary location. Dry mass of the spacecraft was 1230 kg. Stationed at 124 deg E Positioned in geosynchronous orbit at 123 deg E in 1999. As of 5 September 2001 located at 124.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 10 located at 124.01E drifting at 0.011W degrees per day.
References: 2.
1999 February 20 - 04:18 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Soyuz 11A511U. LV Configuration: Soyuz 11A511U M15000-662. - Soyuz TM-29 Nation: Russia. Program: Mir. Payload: Soyuz TM 11F732 s/n 78. Class: Manned. Type: Spacecraft. Spacecraft: Soyuz TM. Manufacturer: RKK Energiya im. S.P. Korolyov, Kaliningrad-Korolyov. Agency: RKA. Perigee: 341 km (211 mi). Apogee: 357 km (221 mi). Inclination: 51.60 deg. Period: 91.52 min. COSPAR: 1999-007A. USAF Sat Cat: 25632. Duration: 188.85 days. Decay Date: 1999-08-28. Crew: Afanasyev, Haignere, Bella. Flight: Mir EO-27, Mir Stefanik, Mir EO-26, Mir EO-26/-27. Soyuz TM-29 docked with Mir on February 22 at 05:36 GMT. Since two crew seats had been sold (to Slovakia and France), Afansyev was the only Russian cosmonaut aboard. This meant that Russian engineer Avdeyev already aboard Mir would have to accept a double-length assignment. After the February 27 departure of EO-26 crew commander Padalka and Slovak cosmonaut Bella aboard Soyuz TM-28, the new EO-27 Mir crew consisted of Afanasyev as Commander, Avdeyev as Engineer and French cosmonaut Haignere. Follwoing an extended mission and three space walks, the last operational crew aboard Mir prepared to return. The station was powered down and prepared for free drift mode.
References: 2.
1999 February 20 - 04:45 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 9. LV Configuration: Black Brant IX NASA 36.180UG. - SPINR 2 Ultraviolet astronomy mission Nation: USA. Agency: NASA GSFC. Apogee: 300 km (180 mi). References: 2.
1999 February 23 - 10:29 GMT - Launch Site: Vandenberg. Launch Complex: SLC2W. Launch Pad: -. Launch Vehicle: Delta. Model: Delta 7920-10. LV Configuration: Delta 7920-10 D267. - ARGOS Nation: USA. Payload: P91-1. Class: Technology. Type: Ion engine. Spacecraft: ARGOS. Manufacturer: Boeing, Seal Beach. Agency: USAF SMC. Perigee: 825 km (512 mi). Apogee: 839 km (521 mi). Inclination: 98.80 deg. COSPAR: 1999-008A. USAF Sat Cat: 25634. ARGOS was a USAF Space Test Program P91-1 technology satellite, equipped with an ion engine, ionosphere, x-ray, and dust detectors. Much delayed, it finally was placed into orbit on the eleventh (!) launch attempt. References: 2.
-
 Orsted Nation: Denmark. Mass: 62 kg (136 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Orsted. Manufacturer: CRI, Kobenhaven. Agency: DMI. Perigee: 644 km (400 mi). Apogee: 863 km (536 mi). Inclination: 96.50 deg. COSPAR: 1999-008B. USAF Sat Cat: 25635. Denmark's Orsted gravity gradient stabilised satellite was to map the Earth's magnetic field. It was managed and operated by the Danish Meteorological Institute in Copenhagen. The satellite's prime contractor was CRI , Copenhagen. References: 2.
-
 Sunsat Nation: South Africa. Class: Technology. Spacecraft: Sunsat. Manufacturer: Stellenbosch University, Cape Town. Agency: Stellenb. Perigee: 644 km (400 mi). Apogee: 865 km (537 mi). Inclination: 96.50 deg. COSPAR: 1999-008C. USAF Sat Cat: 25636. Sunsat was built by students at Stellenbosch University, South Africa and carried a small imager and a message relay payload. References: 2.
1999 February 24 - - US Blocks Blocks AMPT communictions satellite project with China. Nation: China. The United States rejected a $450 million Hughes satellite deal with China over fears it could compromise U.S. national security. The APMT satellite was designed to provide mobile telephone links over much of Asia and was 51 percent owned by Chinese interests. This marked the end of Chinese-US commercial collaboration in space, with China thereafter concentrating on deals with European or other developing world partners.
References: 424.
1999 February 26 - 22:44 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44L. LV Configuration: Ariane 44L-3 V116. -
 Arabsat 3A Nation: Arab States. Program: Arabsat. Mass: 2,708 kg (5,970 lb). Class: Communications. Spacecraft: Spacebus 3000. Manufacturer: Alcatel, Cannes. Agency: Arabsat. Perigee: 35,779 km (22,231 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 1999-009A. USAF Sat Cat: 25638. The Arab League satellite had 20 Ku-band transponders and was to be stationed at 26 degrees East. Dry mass was 1200 kg. Positioned in geosynchronous orbit at 26 deg E in 1999. As of 29 August 2001 located at 25.93 deg E drifting at 0.007 deg E per day. As of 2007 Mar 9 located at 25.89E drifting at 0.003E degrees per day.
References: 2.
-
 Skynet 4E Nation: UK. Program: Skynet. Mass: 1,490 kg (3,280 lb). Class: Communications. Type: Military. Spacecraft: ECS/OTS. Manufacturer: Matra Marconi Space-UK, Stevenage. Agency: UK MoD. Perigee: 35,774 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 3.30 deg. COSPAR: 1999-009B. USAF Sat Cat: 25639. Skynet 4E was a SHF/UHF military communications satellite for the UK Ministry of Defense. Dry mass was 759 kg; it used a Thiokol Star 30 solid apogee motor. Stationed at 53 deg E. Positioned in geosynchronous orbit at 53 deg E in 1999. As of 5 September 2001 located at 52.91 deg E drifting at 0.000 deg W per day. As of 2007 Mar 11 located at 53.02E drifting at 0.005E degrees per day.
References: 2.
1999 February 28 - 04:00 GMT - Launch Site: Baikonur. Launch Complex: LC81/23. Launch Pad: -. Launch Vehicle: Proton. Model: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 387-01. - Raduga-1 Nation: Russia. Payload: Raduga-1 s/n 14. Class: Communications. Spacecraft: Raduga-1. Manufacturer: NPO Prikladnoi Mekhaniki, Zhelenogorsk. Agency: MO RF. Perigee: 35,778 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 1.20 deg. COSPAR: 1999-010A. USAF Sat Cat: 25642. Geosynchronous communications satellite, stationed at 35 deg E. Positioned in geosynchronous orbit at 35 deg E in 1999. As of 5 September 2001 located at 34.80 deg E drifting at 0.013 deg E per day. As of 2007 Mar 10 located at 107.14E drifting at 0.165W degrees per day.
References: 2.
1999 February 28 -
1999 March 1 - - First nonstop balloon flight around world completed in 20 days Nation: UK.
1999 March 1 - - Chinese Manned Space Plans Nation: China. Spacecraft: Shenzhou. Zhang Heqi, the chief astronomer of the Chinese space program said that an earlier report regarding a Chinese 'shuttle' was incorrect - 'It is a manned spacecraft, not a shuttle'. There was to be an unmanned launch in one or two years. A manned launch would follow this test in the next few years.The first unmanned spacecraft might carry animals to pave the way for future manned flights. It was also reported that China had selected several astronaut candidates from PLA Air Force fighter pilots.
References: 424.
1999 March 5 - Launch Site: Edwards. Launch Complex: -. Launch Pad: -. - X-38 V-132 Flight 1 Nation: USA. Program: ISS. Class: Manned. Type: Spaceplane. Spacecraft: X-38. X-38 atmospheric test vehicle V-132 was dropped from carrier plane NB-52 # 8 at 16:17 GMT. The V-132 subscale version of the X-38 successfully deployed its parafoil and glided to a landing on the lakebed after a 9 minute flight. V-132 tested the rudders and flaps; the simpler V-131, which made two drop tests earlier, tested the parafoil control system.
1999 March 5 - - U.S. accuses China of stealing nuclear secrets Nation: China.
1999 March 5 - - Starchaser Tempest launch. Nation: UK. Program: X-Prize. Spacecraft: Starchaser 5. Starchaser Industries (Hyde, England, UK) successfully launches TEMPEST vehicle.
1999 March 5 - 02:56 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 F26/M-22. - WIRE Nation: USA. Class: Astronomy. Spacecraft: WIRE. Manufacturer: NASA Goddard Space Flight Center, Greenbelt. Agency: NASA GSF. Perigee: 537 km (333 mi). Apogee: 582 km (361 mi). Inclination: 97.50 deg. COSPAR: 1999-011A. USAF Sat Cat: 25646. NASA's long-delayed WIRE (Wide Field Infrared Explorer) astronomy satellite was the fifth Small Explorer (SMEX) mission managed by NASA-Goddard. The L-1011 Stargazer launch aircraft took off from Vandenberg's runway 30/12 at 01:55 GMT on March 2 for the first launch attempt. The planned 02:56 GMT launch was cancelled at T-46 seconds due to a problem with the tail fin release mechanism of the Pegasus XL launch vehicle. The second attempt was successful, with the Pegaus XL being dropped at 36 degrees N x 123 degrees W over the Pacific Ocean at 02:56 GMT. However the WIRE ran into serious trouble shortly after orbit injection. The cover of the solid hydrogen telescope ejected prematurely, and the cryogenic coolant evaporated and vented, spinning the satellite out of control. WIRE was going to make an infrared photometry survey, generating a large catalog of galaxies and quasars.
References: 2.
1999 March 10 -
1999 March 10 - 08:01 GMT - Launch Site: Vandenberg. Launch Complex: LF02. Launch Pad: -. Launch Vehicle: Peacekeeper. LV Configuration: Peacekeeper 28PA. - 8 RVs operational test launch Nation: USA. Agency: USAF 90SW. Apogee: 1,000 km (600 mi). References: 2.
1999 March 11 - Launch Vehicle: CZ. Model: CZ-2F. - Chinese Man-Rated Launch Vehicle Test Predicted Nation: China. Spacecraft: Shenzhou. It was reported on the Internet that the maiden flight of a new version of the CZ-2E designed to carry a manned vehicle would be made by mid-1999. References: 424.
1999 March 12 - - Czech Republic, Poland, and Hungary join NATO Nation: USA.
1999 March 12 - - China Proposes Ban on Space Weapons Nation: China. China, backed by Pakistan and Egypt, proposed a ban on weapons in outer space. Formal negotiations would take place via the UN Conference on Disarmament. The USA did not respond to China's proposal. References: 424.
1999 March 15 - 03:06 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Soyuz 11A511U. LV Configuration: Soyuz 11A511U/Ikar - ST02. - Globalstar M022 Nation: USA. Mass: 222 kg (489 lb). Class: Communications. Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. COSPAR: 1999-012A. USAF Sat Cat: 25649. In the second Soyuz/Ikar launch four Globalstar satellites were delivered with the Ikar upper stage into a 235 km x 899 km x 52.0 degree transfer orbit. The Ikar stage then placed itself and its payload into a 897 km x 950 km x 52.0 degree deployment orbit. Satellite M022 was separated first from the top of the dispenser, followed by ejection of the other three satellites from the sides at 06:37 GMT. After dispensing the satellites, the Ikar deorbited itself on March 16.
References: 2.
- Globalstar M041 Nation: USA. Mass: 222 kg (489 lb). Class: Communications. Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. COSPAR: 1999-012B. USAF Sat Cat: 25650. References: 2.
- Globalstar M046 Nation: USA. Mass: 222 kg (489 lb). Class: Communications. Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,412 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg. COSPAR: 1999-012C. USAF Sat Cat: 25651. References: 2.
- Globalstar M037 Nation: USA. Mass: 222 kg (489 lb). Class: Communications. Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. COSPAR: 1999-012D. USAF Sat Cat: 25652. References: 2.
1999 March 15 - 09:52 GMT - Launch Site: Alcantara. Launch Complex: -. Launch Pad: -. Launch Vehicle: Sonda. Model: VS-30. LV Configuration: VS-30 XV-04. -
 Operacao San Marcos Microgravity mission Nation: Brazil. Agency: AEB. Apogee: 128 km (79 mi). References: 2.
1999 March 21 - 00:09 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) 388-01. - Asiasat 3S Nation: China. Program: Asiasat. Payload: HS 601HP. Mass: 3,463 kg (7,634 lb). Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: Asiasat. Perigee: 35,780 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.10 deg. COSPAR: 1999-013A. USAF Sat Cat: 25657. A replacement for Asiasat 3, placed in the wrong orbit by a Proton launch in 1997, Asiasat 3S carried C and Ku band transponders. The Blok DM3 upper stage placed it a 9,677 km x 35,967 km x 13.1 deg geosynchronous transfer orbit. Asiasat's on-board R4D apogee engine was to be used to raise perigee to geostationary altitude. Mass in transfer orbit was 3,463 kg, down to 2,500 kg after insertion in geostationary orbit. Operated in geosynchronous orbit at 105 deg E from 1999. As of 4 September 2001 located at 105.52 deg E drifting at 0.008 deg E per day. As of 2007 Mar 11 located at 105.46E drifting at 0.017W degrees per day.
References: 2.
1999 March 23 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Trident. Model: Trident C-4. LV Configuration: Trident C-4 FCET-50. - Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1999 March 23 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Trident. Model: Trident C-4. LV Configuration: Trident C-4 FCET-50. - Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1999 March 25 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Trident. Model: Trident C-4. LV Configuration: Trident C-4 FCET-50. - Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1999 March 25 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Trident. Model: Trident C-4. LV Configuration: Trident C-4 FCET-50. - Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1999 March 28 - 01:29 GMT - Launch Site: Kiritimati. Launch Complex: -. Launch Pad: 0.0 N x 154.0 W. Launch Vehicle: Zenit. Model: Zenit-3SL. - DemoSat Nation: USA. Payload: HS 702. Mass: 4,500 kg (9,900 lb). Class: Technology. Manufacturer: Boeing, Kent/Seattle. Agency: SeaLaunc. Perigee: 658 km (408 mi). Apogee: 36,045 km (22,397 mi). Inclination: 1.40 deg. COSPAR: 1999-014A. USAF Sat Cat: 25661. 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.
References: 2.
1999 March 28 - 09:00 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 8C. LV Configuration: Black Brant 8C NASA 27.141UH. - XQC F3 X-ray astronomy mission Nation: USA. Agency: NASA GSFC. Apogee: 220 km (130 mi). References: 2.
1999 March 29 - 12:06 GMT - Launch Site: White Sands. Launch Complex: LC94. Launch Pad: FIX. Launch Vehicle: Hera. LV Configuration: Hera 13. - BRV/THAAD Target 4 Target mission Nation: USA. Agency: USA?. Apogee: 300 km (180 mi). References: 2.
1999 March 29 - 12:13 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: THAAD. LV Configuration: THAAD FT-09. - ABM test Nation: USA. Agency: USA. Apogee: 100 km (60 mi). References: 2.
1999 March 31 - 00:15 GMT - Launch Site: Barking Sands. Launch Complex: LP1. Launch Pad: -. Launch Vehicle: SR19. - SRALT/MBRV-3 test Nation: USA. Agency: USA/USAF. Apogee: 99 km (61 mi). References: 2.
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