Encyclopedia Astronautica
August 29


August 29 Chronology


1923 August 29 - .
1947 August 29 - .
  • XS-1 Flight 41 - . Crew: Yeager. Payload: XS-1 # 1 flight 23. Nation: USA. Related Persons: Yeager. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: AF powered flight 1. Mach 0.85..

1948 August 29 - .
  • Birth of Charles David Walker - . Nation: USA. Summary: American engineer payload specialist astronaut. Flew on STS-41-D, STS-51-D, STS-61-B..

1952 August 29 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LA. Launch Pad: LA?. LV Family: Snark. Launch Vehicle: MX-775. LV Configuration: MX-775 Dyn Model #2.
  • Test mission - . Nation: USA. Agency: USAF. Apogee: 10 km (6 mi).

1954 August 29 - .
  • X-1B Flight 1 - . Crew: McKay. Payload: X-1B flight 12. Nation: USA. Related Persons: McKay. Class: Manned. Type: Manned rocketplane. Spacecraft: X-1B. Summary: NACA flight 2. Cabin-pressure regulator malfunction causes inner canopy to crack; only low-speed, low-altitude maneuvers made..

1956 August 29 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LA. Launch Pad: LA?. LV Family: Matador. Launch Vehicle: Matador. LV Configuration: Matador GM-55-528.
  • Test mission - . Nation: USA. Agency: USAF. Apogee: 12 km (7 mi).

1957 August 29 - . 14:12 GMT - . Launch Site: San Nicolas. LV Family: Deacon. Launch Vehicle: Nike Deacon. LV Configuration: Nike Deacon NN7.45F/DAN-23.
  • NRL NN7.45F Solar ultraviolet and x-ray mission - . Nation: USA. Agency: USN. Apogee: 113 km (70 mi).

1958 August 29 - . 04:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC11. LV Family: Atlas. Launch Vehicle: Atlas B. LV Configuration: Atlas B 5B.
  • Research and development / AFSWC-1 test - . Nation: USA. Agency: USAF. Apogee: 900 km (550 mi).

1960 August 29 - .
1960 August 29 - . 03:38 GMT - . Launch Site: Wallops Island. LV Family: Trailblazer. Launch Vehicle: Trailblazer 1. LV Configuration: Trailblazer 1 TB Ic.
  • D58 Trailblazer re-entry vehicle test flight - . Nation: USA. Agency: NASA. Apogee: 260 km (160 mi).

1960 August 29 - . 06:13 GMT - . Launch Site: Wallops Island. LV Family: Trailblazer. Launch Vehicle: Trailblazer 1. LV Configuration: Trailblazer 1 TB Id.
  • D58 Trailblazer re-entry vehicle test flight - . Nation: USA. Agency: NASA. Apogee: 260 km (160 mi).

1961 August 29 - .
  • Ranger launchings would be increased to nine - . Nation: USA. Program: Ranger. Spacecraft: Ranger 6-7-8-9. NASA announced that planned Ranger launchings would be increased from five to nine. These additional spacecraft would be equipped with six high-resolution television cameras. They would be programmed to begin operating at about 800 miles above the lunar surface and continue until moments before the spacecraft crash-landed. The final pictures would record features no more than eight inches across. About 1,600 photographs were expected from each spacecraft, which would no longer carry previously planned instrumented capsules. The objective of these spacecraft now was to provide information on the lunar surface in support of the manned lunar landing mission.

1961 August 29 - . 14:35 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NE3.110.
  • Solar ultraviolet mission - . Nation: USA. Agency: NRL. Apogee: 260 km (160 mi).

1962 August 29 - . 01:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Delta. Launch Vehicle: Thor Agena D. LV Configuration: Thor Agena D 349 / Agena D 1153.
  • KH-4 9044 - . Payload: KH-4 s/n 9044 / Agena D 1153. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-4. Decay Date: 1962-09-10 . USAF Sat Cat: 377 . COSPAR: 1962-A-Sigma-1. Apogee: 400 km (240 mi). Perigee: 187 km (116 mi). Inclination: 65.2000 deg. Period: 90.40 min. Summary: KH-4; film capsule recovered 4.1 days later. Erratic vehicle attitude. Radiation fog minimal..

1962 August 29 - . 01:01 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 2. LV Configuration: Skylark-2 SL28.
  • Test mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 109 km (67 mi).

1962 August 29 - . 18:36 GMT - . Launch Site: Hidden Hills DZ. Launch Pad: 36.1 N x 116.0 W. Launch Platform: NB-52 008. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 2-28-48.
  • X-15A Heating test - . Nation: USA. Agency: NASA; USAF. Apogee: 29 km (18 mi). Summary: Maximum Speed - 5546 kph. Maximum Altitude - 29630 m..

1963 August 29 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF07. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 625.
  • Research and development launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1963 August 29 - . 20:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Delta. Launch Vehicle: Thor Agena D SLV-2. LV Configuration: Thor SLV-2 Agena D 394 / Agena D 1169.
  • KH-4 9033 - . Payload: KH-4 s/n 9033 & Lampo / Agena D 1169. Mass: 1,000 kg (2,200 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-4. Decay Date: 1963-11-07 . USAF Sat Cat: 637 . COSPAR: 1963-035A. Apogee: 324 km (201 mi). Perigee: 292 km (181 mi). Inclination: 81.9000 deg. Period: 90.80 min. Summary: KH-5; deployed ELINT subsatellite. Considered to be best mission to date in Argon program..
  • LAMPO - . Payload: 0.1 Square Meter Target. Nation: USA. Agency: USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: LAMPO. Decay Date: 1963-09-29 . USAF Sat Cat: 638 . COSPAR: 1963-035B. Apogee: 422 km (262 mi). Perigee: 315 km (195 mi). Inclination: 81.9000 deg. Period: 92.00 min. Summary: Radar monitoring. Not identified as a subsatellite ferret by McDowell..

1964 August 29 - . 05:30 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.122GG.
  • AS / E X-ray astronomy mission - . Nation: USA. Agency: NASA. Apogee: 179 km (111 mi).

1964 August 29 - . 09:36 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LC-A. LV Family: Scout. Launch Vehicle: Blue Scout Jr SLV-1B(m). LV Configuration: Blue Scout Jr SLV-1B(m) 21-2.
  • Ion Engine Test B Technology mission - . Nation: USA. Agency: USAF. Apogee: 2,000 km (1,200 mi). The launch was designed to provide about 30 minutes of flight above an altitude of 370 km. At seven minutes into the flight the engine was operated with ion beam extraction. Full beam current of 94 mA was achieved about 10 minutes later. During the course of engine operation, an electric field strength meter was used to infer payload floating potential relative to space. Spacecraft potential was about 1000 V negative during most of the engine operation with the filament neutralizer. The absolute value of payload potential was about ten times higher than anticipated, and it was suspected that there was inadequate neutralization of the ion beam. The contact ion engine operated for 19 minutes until spacecraft reentry into the atmosphere. In addition to withstanding the environmental rigors of space flight, the ion propulsion system demonstrated electromagnetic compatibility with other spacecraft subsystems and the ability to regulate and control a desired thrust level.

1965 August 29 - .
  • Landing of Gemini 5 - . Return Crew: Conrad; Cooper. Nation: USA. Related Persons: Conrad; Cooper. Program: Gemini. Flight: Gemini 5. The crew had to use the re-entry thrusters to orient the spacecraft due to OAMS system failures. The retrofire and re-entry were conducted in darkness by the spacecraft computer. However the computer had been misprogrammed with an erroneous rotation rate of the earth (390 degrees per day instead of 360.98 degrees per day). Cooper's efforts compensated for what he recognized as an erroneous reading and brought the capsule down closer to the ship than they would otherwise have been.

1966 August 29 - . 15:20 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.156GM.
  • Airglow / Te / density Aeronomy / chemica / solar ultraviolet mission - . Nation: USA. Agency: NASA. Apogee: 206 km (128 mi).

1966 August 29 - . 19:05 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF07. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 1197.
  • Follow-on operational missile test - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1967 August 29 - . 10:01 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 7C. LV Configuration: Skylark-7C SL522.
  • Geocorona? Ultraviolet astronomy mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 124 km (77 mi).

1968 August 29 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 626. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3TE.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1968 August 29 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 626. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3TE.
  • Improved Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1968 August 29 - . 05:38 GMT - . Launch Site: Thumba. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.191.
  • ISRO 20.06 Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 170 km (100 mi).

1968 August 29 - . 08:45 GMT - . Launch Site: Thumba. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.192.
  • ISRO 20.07 Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 170 km (100 mi).

1968 August 29 - . 17:30 GMT - . Launch Site: Thumba. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.193.
  • ISRO 20.08 Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 168 km (104 mi).

1968 August 29 - . 19:43 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 3 AC. LV Configuration: Skylark 3 AC SL501.
  • UK SL501 Ionosphere / solar x-rays mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 210 km (130 mi).

1969 August 29 - . 09:05 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 296 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1969-09-06 . USAF Sat Cat: 4080 . COSPAR: 1969-075A. Apogee: 302 km (187 mi). Perigee: 207 km (128 mi). Inclination: 65.0000 deg. Period: 89.60 min. Summary: High resolution photo reconnaissance satellite; returned film capsule.

1970 August 29 - . 08:30 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 360 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4M. Duration: 10.00 days. Decay Date: 1970-09-08 . USAF Sat Cat: 4508 . COSPAR: 1970-068A. Apogee: 287 km (178 mi). Perigee: 207 km (128 mi). Inclination: 65.0000 deg. Period: 89.40 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable; deployed capsule..

1972 August 29 - . 11:12 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P118H.
  • E-region multiprobe Ionosphere mission - . Nation: UK. Agency: SRC. Apogee: 140 km (80 mi).

1972 August 29 - . 13:12 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P130H.
  • Solar La / X Solar ultraviolet and x-ray mission - . Nation: UK. Agency: SRC. Apogee: 135 km (83 mi).

1973 August 29 - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576A3. LV Family: Atlas. Launch Vehicle: Atlas F. LV Configuration: Atlas F 78F.
  • BMRS RVTO-3A-2 re-entry vehicle test flight - . Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).

1974 August 29 - .
  • X-24 Flight 43 - . Crew: Manke. Payload: X-24B flight 15. Nation: USA. Related Persons: Manke. Class: Manned. Type: Manned spaceplane. Spacecraft: X-24B. Summary: Maximum Speed - 1170 kph. Maximum Altitude - 22080 m. Flight Time - 467 sec..

1974 August 29 - . 07:39 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 674 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MK. Duration: 9.00 days. Decay Date: 1974-09-07 . USAF Sat Cat: 7423 . COSPAR: 1974-068A. Apogee: 323 km (200 mi). Perigee: 175 km (108 mi). Inclination: 65.0000 deg. Period: 89.50 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1974 August 29 - . 14:55 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 53719-154.
  • Cosmos 675 - . Mass: 600 kg (1,320 lb). Nation: USSR. Agency: MO. Spacecraft: Sfera. USAF Sat Cat: 7424 . COSPAR: 1974-069A. Apogee: 1,424 km (884 mi). Perigee: 1,364 km (847 mi). Inclination: 74.1000 deg. Period: 113.60 min. Summary: Investigation of the upper atmosphere and outer space. .

1975 August 29 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 645. Launch Vehicle: Poseidon.
  • FOT-14? Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1975 August 29 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF08. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT49GM Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1975 August 29 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 645. Launch Vehicle: Poseidon.
  • FOT-14? Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1976 August 29 - . 15:01 GMT - . Launch Site: Wallops Island. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 73 km (45 mi).

1977 August 29 - . 15:09 GMT - . Launch Site: Thule AFB. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 69 km (42 mi).

1978 August 29 - . 15:00 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1029 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MKM. Duration: 10.00 days. Decay Date: 1978-09-08 . USAF Sat Cat: 11012 . COSPAR: 1978-082A. Apogee: 316 km (196 mi). Perigee: 194 km (120 mi). Inclination: 62.8000 deg. Period: 89.60 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1979 August 29 - . 00:30 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 657. LV Family: Trident. Launch Vehicle: Trident C-4.
  • DASO-1? demonstration and shakedown operations launch - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1980 August 29 - . 13:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC43. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 58 km (36 mi).

1983 August 29 - . 10:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-6.
  • MINIX Plasma physics mission - . Nation: Japan. Agency: ISAS. Apogee: 238 km (147 mi).

1983 August 29 - . 13:20 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.340UG.
  • JHU Airglow 13 (HUT) Airglow mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1984 August 29 - . 23:26 GMT - . Launch Site: Kwajalein. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 75 km (46 mi).

1985 August 29 - .
  • Death of Ivan Ivanovich Utkin - . Nation: Russia. Related Persons: Utkin, Ivan. Summary: Russian engineer. Chief Designer 1960-1970 of NII IT. Specialised in spacecraft memory data recorders..

1985 August 29 - . 10:15 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC41/1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1678 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1-17F41. Duration: 14.00 days. Decay Date: 1985-09-12 . USAF Sat Cat: 15997 . COSPAR: 1985-077A. Apogee: 280 km (170 mi). Perigee: 178 km (110 mi). Inclination: 82.3000 deg. Period: 89.10 min. High resolution photo surveillance; film capsule; maneuverable; also performed earth resource tasks. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation.

1985 August 29 - . 11:33 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1679 - . Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Yantar-4K1. Duration: 50.00 days. Decay Date: 1985-10-18 . USAF Sat Cat: 15999 . COSPAR: 1985-078A. Apogee: 341 km (211 mi). Perigee: 172 km (106 mi). Inclination: 64.9000 deg. Period: 89.60 min. Summary: High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission..

1987 August 29 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 630. LV Family: Trident. Launch Vehicle: Trident C-4.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1987 August 29 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 630. LV Family: Trident. Launch Vehicle: Trident C-4.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1987 August 29 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 630. LV Family: Trident. Launch Vehicle: Trident C-4.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1987 August 29 - . 23:43 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 630. LV Family: Trident. Launch Vehicle: Trident C-4.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1988 August 29 - . 04:23 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U2.
  • Soyuz TM-6 - . Call Sign: Proton (Proton ). Crew: Lyakhov; Mohmand; Polyakov. Backup Crew: Arzamazov; Berezovoi; Masum. Payload: Soyuz TM 11F732 s/n 56. Mass: 7,070 kg (15,580 lb). Nation: USSR. Related Persons: Lyakhov; Mohmand; Polyakov; Arzamazov; Berezovoi; Masum. Agency: MOM. Program: Mir. Class: Manned. Type: Manned spacecraft. Flight: Mir EP-3; Mir LD-2; Mir EO-3. Spacecraft: Soyuz TM. Duration: 114.23 days. Decay Date: 1988-12-21 . USAF Sat Cat: 19443 . COSPAR: 1988-075A. Apogee: 228 km (141 mi). Perigee: 195 km (121 mi). Inclination: 51.6000 deg. Period: 88.70 min. Transported to the Mir orbital station a Soviet-Afghan crew comprising the cosmonauts V A Lyakhov, V V Polyakov and A A Momand (Afghanistan) to conduct joint research and experiments with the cosmonauts V G Titov and M K Manarov. Returned Manarov, Titov (Soyuz TM-4), Chretien (Soyuz TM-7) to Earth. Initial orbit 195 X 228 km at 51. 57 deg. Maneuvered to a 235 x 259 km orbit, then docked with Mir at 05:41 GMT on 31 August at its 339 x 366 km orbit. Moved from aft to forward port 8 Sept 88.

1989 August 29 - .
  • Voyager 2 spacecraft speeds by Neptune - . Nation: USA. Summary: Voyager 2 spacecraft speeds by Neptune after making startling discoveries about the planet and its moons .

1990 August 29 - . 05:00 GMT - . Launch Site: Baikonur. LV Family: R-36M. Launch Vehicle: R-36M2 15A18M.
  • Operational missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1991 August 29 - . 06:48 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Vostok 8A92M.
  • IRS-1B - . Payload: IRS 1B. Mass: 980 kg (2,160 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: IRS. USAF Sat Cat: 21688 . COSPAR: 1991-061A. Apogee: 919 km (571 mi). Perigee: 892 km (554 mi). Inclination: 99.0000 deg. Period: 103.10 min. Summary: Remote sensing; launched commercially by USSR. Operational remote sensing satellite for natural resources management. .

1994 August 29 - . 17:38 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Atlas. Launch Vehicle: Atlas E. LV Configuration: Atlas E 20E / Star-37S-ISS.
  • USA 106 - . Payload: DMSP 23545/Star 37S S/N 15030 / DMSP 5D-1 F12. Mass: 830 kg (1,820 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft: DMSP Block 5D-2. USAF Sat Cat: 23233 . COSPAR: 1994-057A. Apogee: 860 km (530 mi). Perigee: 840 km (520 mi). Inclination: 98.8900 deg. Period: 101.94 min. Summary: Defense Meteorological Satellite Program..

1995 August 29 - . 00:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-117.
  • JCSAT 3 - . Mass: 1,841 kg (4,058 lb). Nation: Japan. Agency: JSAT. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23649 . COSPAR: 1995-043A. Apogee: 35,794 km (22,241 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.0000 deg. Period: 1,436.20 min. 8 transponders for digital TV. Stationed at 128.1 deg E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 128 deg E in 1995-1999 As of 5 September 2001 located at 128.05 deg E drifting at 0.005 deg E per day. As of 2007 Feb 20 located at 126.99E drifting at 0.144W degrees per day.

1995 August 29 - . 06:41 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44P. LV Configuration: Ariane 44P-3 V77.
  • N-Star a - . Mass: 3,100 kg (6,800 lb). Nation: Japan. Agency: NTT. Program: N-STAR. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 23651 . COSPAR: 1995-044A. Apogee: 35,791 km (22,239 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Stationed at 131.9 deg E. Positioned in geosynchronous orbit at 132 deg E in 1995-1999 As of 1 September 2001 located at 131.99 deg E drifting at 0.017 deg W per day. As of 2007 Mar 11 located at 25.96E drifting at 4.123W degrees per day..

1996 August 29 - . 05:22 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/3. LV Family: R-7. Launch Vehicle: Molniya 8K78M. LV Configuration: Molniya 8K78M-2BL.
  • Microsat - . Payload: Victor. Mass: 32 kg (70 lb). Nation: Argentina. Agency: Cordoba. Class: Earth. Type: Magnetosphere satellite. Spacecraft: MuSat. Decay Date: 1999-11-12 . USAF Sat Cat: 24291 . COSPAR: 1996-050A. Apogee: 19,176 km (11,915 mi). Perigee: 804 km (499 mi). Inclination: 62.8000 deg. Period: 94.70 min. MuSat-1 Victor separated from the launch vehicle at 05:31 GMT, becoming the first Argentine-built satellite. Measuring 340 x 340 x 450mm."Victor " was an experimental vehicle, intended to evaluate in-orbit behaviour of low-cost space technologies. It carried two video cameras, oriented for earth-imaging, as well as transceivers in both UHF and S bands. The beacon could be heard every 90 seconds at 137.95 MHz as a brief burst of CW ("Hi hi de MUSAT"). Electrical power was provided by four 88-Si cells solar panels, with an end-of-life electrical power of 8 W. Its position was determined by means of a 3-axis, flux-gate magnetometer, as well as both solar and horizon sensors, while its attitude was 3-axis controlled by magnetic coils and reaction wheels, with a pointing precision of 0.5 deg. MuSat-1 was developed and built by a 25-person team at the Instituto Universitario Aeronautico, under the sponsorship of the government of the province of Cordoba, in a 3.5 year, $1.2 million effort.
  • Interbol 2 - . Payload: SO-M2 s/n 512. Mass: 1,400 kg (3,000 lb). Nation: Russia. Agency: VKS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Prognoz-M. USAF Sat Cat: 24293 . COSPAR: 1996-050C. Apogee: 18,604 km (11,559 mi). Perigee: 1,369 km (850 mi). Inclination: 63.6000 deg. Period: 347.20 min. Summary: Auroral research. Paired with Magion 5 subsatellite..
  • Magion 5 - . Payload: S2. Mass: 58 kg (127 lb). Nation: Czech Republic. Agency: RAKA. Program: Intercosmos. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Magion. USAF Sat Cat: 24292 . COSPAR: 1996-050B. Apogee: 18,608 km (11,562 mi). Perigee: 1,366 km (848 mi). Inclination: 63.6000 deg. Period: 347.20 min. Summary: The S2-A Magion 5 sub-satellite deployed from Interbol-2 on 30 August 1996 and conducted auroral studies in conjunction with Interbol-2. It was believed lost due to a solar panel failure until it was revived on the 14 May 1998..

1996 August 29 - . 17:38 GMT - . Launch Site: Wallops Island. LV Family: Black Brant. Launch Vehicle: Black Brant 5C.
  • Target mission - . Nation: USA. Agency: BMDO. Apogee: 100 km (60 mi).

1997 August 29 - . 15:02 GMT - . Launch Site: Point Arguello WADZ. Launch Pad: 36.0 N x 123.0 W. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL. LV Configuration: Pegasus XL 019/F17.
  • FORTE - . Nation: USA. Agency: USAF STP. Manufacturer: Los Alamos. Class: Technology. Type: Navigation technology satellite. Spacecraft: FORTE. USAF Sat Cat: 24920 . COSPAR: 1997-047A. Apogee: 833 km (517 mi). Perigee: 799 km (496 mi). Inclination: 70.0000 deg. Period: 101.20 min. FORTE - 'Fast On-orbit Recording of Transient Events' - was a US Los Alamos National Laboratory satellite designed to study natural and artificial radio emissions from the ionosphere. This data was needed to develop technology for monitoring nuclear test ban treaties.

1998 August 29 - .
  • Mir News 436: Soyuz-TM28 - . Nation: Russia. Program: Mir. Flight: Mir EO-26; Mir EO-26/-27. Padalka and Avdeyev redocked this ship from the aft to the forward docking port of the Mir-complex on 27.08.1998. They separated from Mir at 0544 UTC and docked again at 06.07.09 UTC. Padalka accomplished the approach and docking manually, so if the Russian treasury is able to bear this he can expect his 2nd manual docking bonus.

    Communications during this operation was via the VHF channel of Soyuz-TM28 on 121.750 mc. For listeners in Western Europa there was a short pass during an elevation of 1 degree. Nevertheless such a lot of traffic could be monitored between 0600 and 0603 UTC that it was clear that the operation proceeded flawlessly. At 06.00.20 UTC Padalka reported that they had finished the fly around and that the Soyuz-TM28 was station keeping on the X-axis. They had the target dish exactly in the centre and were able to see the docking port. The fuel consumption had been very low and the SIRT indicated that there still was 463 KG available. Padalka reported that he did not want to wait and that he was about to approach and dock. At 06.02.30 UTC the distance to Mir was 15 M.

    Traffic during the pass in orbit 71521, 0731-0741 UTC, made it clear that the redocking had been successful. The cosmonauts were back on board of Mir. They switched back on all the systems they had switched off before the operation. An air hose had been deployed from the base block to the Soyuz-TM28 and they started the conservation of that ship. During the following passes these activities were still going on.

    The new crew: This crew, that of the 26th Mir Main Expedition, presents themselves as if they already were on board for months. Every time I am surprised that cosmonauts making their first spaceflight very quickly adjust themselves to the new situation and demonstrate that they fully have things in hand. Those who selected and trained these cosmonauts did their work well. (This time Padalka is making his first flight, Avdeyev his 3rd.)

    Altair-2:

    On 13.08.1998 something went wrong with this geostationary satellite over 16 degrees West. During the transfer of data of the relaksatsiya experiment from Mir to TsUP the antenna actuator failed. The communications stopped for the antenna of Altair-2 was no longer aimed at the ground station Shcholkovo near Moscow. A provisional damage assessment seems to justify the conclusion that Altair-2 might be lost.

    Luch-1/Gelios (95054A - 23680): This relay satellite is placed over 77 degrees East. After the launch on 11.10.1995 it was reported that this satellite would be used for the data , telephony and Television relays for Russian manned space flight. Observers in Eastern Europe who can 'see' this satellite better than we in the west, reported that they never heard or saw anything from that object. Just like Altair-2 Luch-1 has been registered as a military satellite.

    Unbelievably soon after the failure of Altair-2 the Russians inserted Luch-1 in the communications chain for Mir -TsUP traffic. After a test communication in the morning of 15.08.1998 the first regular relay of phone and TV between Mir and TsUP could be realised some orbits later. The Russian Television complex Ostankino in Moscow serves as tracking station for Luch-1.

    Ostankino is able to handle phone and TV relays to and from Mir, but modifications have to be implemented to do the same with Telemetry (and possibly Packet Radio).

    For spacewalks (EVA's), docking and descent operations the position over 16 degrees West is better than that over 77 degrees East. Also NASA preferred 16 degrees West during Phase 1 of Shuttle/Mir and after the failure of Altair-1 in the beginning of 1997 they asked the Russians to transfer Altair-2 from 96 degrees East to 16 degrees West.

    More about communications:

    I just have learned that the Mir voice relay sites at NASA's bases in the US will remain in operation, at NASA's expense, per a decision by Frank Culbertson to demonstrate US generosity.

    The loss of Altair-2 means that the amount of information monitored by me will decrease. I now am depending on that what I can monitor via the VHF-channels.

    For some weeks the Russians have problems with the transfer of radiograms by Packet Radio via the service frequencies. Probably the problem has something to with the uplink from a number of tracking stations in Russia. In this period they use for the transfer of radiograms the old RTTY system.

    There are no problems with the Packet Radio in the radio-amateur band. Recently they used the 145.985 mc for that purpose, but now they regularly can be heard on 145.940 mc.

    Progress-M39:

    The redocking of this freighter was scheduled for 29.08.1998 but has been put back. Now this operation is now planned for 1.09.1998. Based on calculations I think that this will take place at about 0400 UTC. The plan is to execute the approach and docking in the automatic mode by the system Kurs, but Padalka and Avdeyev prepared the TORU, the remote control system for eventual use. Padalka will be ready to take over manually if necessary and maybe he has a chance to earn his 3rd manual docking bonus. For us in Western Europe the elevation during the pass in which the objects are in range during the final phase of the approach (orb. Mir 71596, 0350-0353 UTC) is only 1 degree.

    Chris v.d. Berg, NL-9165/A-UK3202.


1999 August 29 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC107/1. Launch Pad: LC107/pad?. LV Family: Kosmos 3. Launch Vehicle: K65M-R. FAILURE: Failure. Failed Stage: 1.
  • Re-entry Vehicle test - . Nation: Russia. Agency: RVSN. Apogee: 675 km (419 mi).

2001 August 29 - . 07:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-1F.
  • LRE - . Mass: 3,500 kg (7,700 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Geodetic satellite. Spacecraft: LRE. USAF Sat Cat: 26898 . COSPAR: 2001-038A. Apogee: 36,214 km (22,502 mi). Perigee: 271 km (168 mi). Inclination: 28.0000 deg. Launch postponed from february, July 22 and August 25. First launch of the H-2A launch vehicle. A failure after all of the problems with the earlier H-2 version would probably have resulted in cancellation of the program. The Laser Ranging Experiment satellite carried 126 laser retro reflectors and separated from the second stage at 0739 GMT into its operational 'Molniya' type orbit. The eventual goal of H-2A was to launch geosynchronous spacecraft at costs comparable to those of other countries. The LRE remained in a simulated geosynchronous transfer orbit; laser reflections from it would be used to precisely ascertain the orbital injection accuracy of the H-2A.
  • VEP-2 - . Mass: 3,500 kg (7,700 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: VEP. USAF Sat Cat: 26899 . COSPAR: 2001-038B. Apogee: 35,979 km (22,356 mi). Perigee: 291 km (180 mi). Inclination: 28.6000 deg. Period: 636.60 min. Summary: Vehicle Evaluation Payload-2 consisted of ballast and monitoring instrumentation that remained attached to the launch vehicle's second stage. It included a Doppler ranging experiment for orbit determination..

2002 August 29 - . 10:00 GMT - . Launch Site: Andoya. LV Family: Viper. Launch Vehicle: Viper 3A.
  • RO-A-FS-04 Aeronomy mission - . Nation: Germany. Agency: DLR. Apogee: 75 km (46 mi).

2003 August 29 - . 01:47 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U. LV Configuration: Soyuz-U D15000-682.
  • Progress M-48 - . Payload: Progress M s/n 248. Mass: 7,250 kg (15,980 lb). Nation: Russia. Agency: RAKA. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Flight: ISS EO-7. Spacecraft: Progress M. Duration: 152.00 days. Decay Date: 2004-01-28 . USAF Sat Cat: 27873 . COSPAR: 2003-039A. Apogee: 383 km (237 mi). Perigee: 376 km (233 mi). Inclination: 51.6000 deg. Period: 92.10 min. Delayed from July 30, moved up from September 18 and August 30. Docked with the Zvezda module of the ISS on August 31. Undocked from the station at 08:36 GMT on 28 January 2004 after being filled with trash and unneeded equipment. Deorbited and reentered over the Pacific at 13:46 GMT.

2003 August 29 - . 23:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta IV Medium. LV Configuration: Delta 4M D4-3 (301) 4040.
  • USA 170 - . Payload: DSCS-3-B6. Mass: 1,235 kg (2,722 lb). Nation: USA. Agency: USAF. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 27875 . COSPAR: 2003-040A. Summary: Delayed from July 1, 11 and 23, then August 3 and 28..

2004 August 29 - . 07:26 GMT - . Launch Site: Balasore. Launch Complex: Balasore IC4. LV Family: Agni. Launch Vehicle: Agni 2.
  • Operational test - . Nation: India. Agency: IDRDL. Apogee: 1,000 km (600 mi).

2004 August 29 - . 07:50 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-25 (78).
  • FSW-3 No. 2 - . Payload: FSW-19. Mass: 2,100 kg (4,600 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 26.67 days. Decay Date: 2004-11-07 . USAF Sat Cat: 28402 . COSPAR: 2004-033A. Apogee: 547 km (339 mi). Perigee: 168 km (104 mi). Inclination: 63.0000 deg. Period: 91.70 min. Recoverable satellite officially stated to be conducting space scientific research, land surveying, mapping and other scientific experiments. Said to have improved experimental technology, with higher orientation precision and more complex on-board computers and software. Controlled from the Xian Satellite Monitoring and Control Centre. Successfully re-entered and recovered after 27 days in space at 23:55 GMT on 24 September.

2005 August 29 - . 08:45 GMT - . Launch Site: Jiuquan. LV Family: CZ. Launch Vehicle: CZ-2D. LV Configuration: Chang Zheng 2D CZ2D-7 (87).
  • FSW-3 No. 5 - . Payload: FSW-22. Mass: 3,000 kg (6,600 lb). Nation: China. Agency: CAST. Manufacturer: SAST. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 49.00 days. Decay Date: 2005-10-17 . USAF Sat Cat: 28824 . COSPAR: 2005-033A. Apogee: 224 km (139 mi). Perigee: 178 km (110 mi). Inclination: 63.0000 deg. Period: 88.50 min. Summary: Decayed 17 October 2005..

2009 August 29 - . 04:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Shuttle.
  • Leonardo - . Nation: USA. Agency: Clemson. Class: Manned. Type: Manned spacecraft. COSPAR: 2009-045x.
  • STS-128 - . Call Sign: Discovery. Crew: Sturckow; Ford; Forrester; Hernandez; Fuglesang; Olivas; Stott. Payload: Discovery F36 /. Mass: 121,420 kg (267,680 lb). Nation: USA. Agency: NASA. Program: ISS. Class: Manned. Type: Manned spacecraft. Flight: STS-128; ISS EO-20; ISS EO-19. Spacecraft: Discovery . Duration: 13.87 days. Decay Date: 2009-09-12 00:53:00 . USAF Sat Cat: 35811 . COSPAR: 2009-045A. Apogee: 352 km (218 mi). Perigee: 310 km (190 mi). Inclination: 51.6000 deg. Period: 91.20 min. Crew: Sturckow, Ford, Forrester, Hernandez, Fuglesang, Olivas. Deliver to the ISS and install the Multi-Purpose Logistics Module (MPLM); Lightweight Multi-Purpose Experiment Support Structure Carrier (LMC); Three-crew quarters, galley, and second treadmill (TVIS2); and the Crew Health Care System 2 (CHeCS 2).

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