Encyclopedia Astronautica
January 15


January 15 Chronology


1908 January 15 - .
  • Birth of Edward Teller - . Nation: Hungary; USA. Summary: Jewish Hungarian-American physicist, American Father of the H-Bomb. A dedicated cold warrior. Founded Livermore laboratory, convinced Reagan to proceed with 'Star Wars' using nuclear-bomb-pumped x-ray laser..

1921 January 15 - .
1941 January 15 - . Launch Vehicle: EA 1941.
  • Barre repot - . Nation: France. Related Persons: Barre. Barre completed a comprehensive report on the military potential of rocketry. He sketeched out ballistic missiles with 1000 km range, powered by liquid oxygen/gasoline engines. Armor-piercing rockets could reach 2000 m/s and defeat any tank armor. Anti-aircraft rockets would intercept aircraft in half the time. Rocket-boosted bombs would destroy enemey emplacements. Air-augmented rockets could reach even higher range and efficiencies.

1945 January 15 - . Launch Site: Peenemuende. LV Family: V-2. Launch Vehicle: V-2.
  • Train-launched A4 abandoned. - . Nation: Germany. Summary: Allied air superiority made the train-launched version unviable as a weapon, compared to the truck-towed missile, which was more easily moved and concealed. Further work on the system was abandoned..

1945 January 15 - . Launch Vehicle: Rheinbote.
  • Rheinbote in service. - . Nation: Germany. Summary: A battery is set up in Holland, and 200 rockets are fired on Antwerp harbour..

1948 January 15 - .
  • USAF policy for development of earth satellites 'at the proper time'. - . Nation: USA. Related Persons: Vandenberg, Hoyt. Summary: General Hoyt S. Vandenberg, Vice Chief of Staff, United States Air Force, approved a policy calling for the development of earth satellites at the proper time..

1948 January 15 - .
  • XS-1 Flight 64 - . Crew: Lilly. Payload: XS-1 # 2 flight 26. Nation: USA. Related Persons: Lilly. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: NACA flight 6. Turns and pull-ups to buffet. Sideslips. Mach 0.76..

1950 January 15 - .
1950 January 15 - . 23:45 GMT - . Launch Site: Bering Sea. Launch Pad: 58.0 N x 170.0 W. Launch Platform: AVM1. LV Family: Aerobee. Launch Vehicle: Aerobee RTV-N-10. LV Configuration: Aerobee RTV-N-10 A15.
  • Particles mission - . Nation: USA. Agency: APL. Apogee: 72 km (44 mi). Summary: Cosmic radiation research. Launched at 2345 GMT. Reached 72.4 km. Launched from from vessel ACM1 at Bering Sea Launch Site 1 (APL Aerobee/Norton Sound) - Latitude: 58.00 N, Longitude:170.00 W..

1952 January 15 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LA. Launch Pad: LA?. LV Family: Matador. Launch Vehicle: Matador. LV Configuration: Matador GM-554.
  • Test mission - . Nation: USA. Agency: USAF. Apogee: 12 km (7 mi).

1953 January 15 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 162R.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1954 January 15 - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: Hermes. Launch Vehicle: Hermes A-3A. LV Configuration: Hermes A-3A 7.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 30 km (18 mi).

1957 January 15 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC3. LV Family: X-17. Launch Vehicle: X-17. LV Configuration: X-17 R-19 4203-19. FAILURE: Failure.
  • Re-entry vehicle test - . Nation: USA. Agency: USAF. Apogee: 100 km (60 mi).

1958 January 15 - . LV Family: Jupiter. Launch Vehicle: Jupiter.
  • Jupiter put into operation service. - . Nation: USA. Summary: 4751st Air Defense Missile Wing to develop and conduct training program for Bomarc units, and the 864th Strategic Missile Squadron to be equipped with Jupiter IRBM, were both activated..

1958 January 15 - .
  • Eleven proposals for Project 7969 initial manned spacecraft - . Nation: USA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Spacecraft: Mercury. Summary: The Air Force received 11 unsolicited industry proposals for Project 7969, and technical evaluation was started. Observers from NACA participated..

1958 January 15 - . 01:24 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-45.
  • Hardtack pod test - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Successfully fired at 2024 hours EST from AMR. The flight was successful in that all missions were accomplished.. The missile followed its predicted trajectory closely. Impact was 370 meters over and 86 meters to the tight of the predicted impact point, a radial miss distance of 380 meters. This wee the fifth complete flight test of warhead and fuse system. Missed aimpoint by 286 m.

1959 January 15 - . LV Family: Atlas. Launch Vehicle: Atlas Centaur LV-3C.
  • Centaur first contract. - . Nation: USA. Summary: Centaur project (Atlas upper stage) contracted for $7 million in its first year.

1960 January 15 - . LV Family: R-7. Launch Vehicle: Molniya 8K78.
  • Molniya 8K78 design begins - . Nation: USSR. Related Persons: Korolev. Summary: Korolev signed the order for development of a four stage rocket based on the R-7..

1960 January 15 - . 04:52 GMT - . Launch Site: Wallops Island. LV Family: Javelin. Launch Vehicle: Javelin. LV Configuration: Javelin JV-3.
  • Test / lyra-alpha mission - . Nation: USA. Agency: USAF AFSWC. Apogee: 1,200 km (700 mi).

1962 January 15 - . LV Family: Proton. Launch Vehicle: Proton.
  • Proton configuration selected. - . Nation: USSR. Manufacturer: Chelomei. Program: GR-2. Summary: The 'polyblock' design was chosen as most advantageous, following studies that indicated improved wind loads and bending moment characteristics compared to the conventional 'monoblock' design..

1962 January 15 - .
  • James A. Chamberlin named Manager of Gemini Project Office (GPO). - . Nation: USA. Related Persons: Gilruth; Chamberlin. Program: Gemini. Spacecraft: Gemini. Director Robert R. Gilruth of Manned Spacecraft Center (MSC) appointed James A. Chamberlin, Chief of Engineering Division, as Manager of Gemini Project Office (GPO). The next day MSC advised McDonnell, by amendment No. 1 to letter contract NAS 9-170, that GPO had been established. It was responsible for planning and directing all technical activities and all contractor activities within the scope of the contract.

1962 January 15 - .
  • Apollo Spacecraft Project Office established - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. The Apollo Spacecraft Project Office (ASPO) was established at MSC. Charles W. Frick was selected as Manager of the new Office, to assume his duties in February. Frick had been Chief of Technical Staff for General Dynamics Convair. Robert O. Piland was appointed Deputy Manager of ASPO and would serve as Acting Manager until Frick's arrival. ASPO would be responsible for the technical direction of NAA and other industrial contractors assigned to work on the Apollo spacecraft. Additional Details: Apollo Spacecraft Project Office established.

1962 January 15 - . 11:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Thor DSV-2D. LV Configuration: Thor DSV-2D 337.
  • AVT-1 Satellite test - . Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi).

1963 January 15 - . Launch Site: North Atlantic Drop Zone. LV Family: Hound Dog. Launch Vehicle: Hound Dog. LV Configuration: Hound Dog CEL-232.
  • Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 20 km (12 mi).

1964 January 15 - .
  • First Apollo fuel cell delivered by Pratt and Whitney - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM Fuel Cell. The first fuel cell module delivered by Pratt and Whitney Aircraft to North American was started and put on load. The module operated normally and all test objectives were accomplished. Total operating time was four hours six minutes, with one hour at each of four loads-20, 30, 40, and 50 amperes. The fuel cell was shut down without incident and approximately 1,500 cubic centimeters (1.6 quarts) of water were collected.

1964 January 15 - .
  • Phase II follow-on extended Apollo system studies. - . Nation: USA. Related Persons: Faget. Spacecraft: Apollo X. Following completion of feasibility studies of an extended Apollo system at MSC, Edward Z. Gray, Advanced Manned Missions Program Director at Headquarters, told MSC's Maxime A. Faget, Director of Engineering and Development, to go ahead with phase II follow-on studies. Gray presented guidelines and suggested tasks for such a study, citing his desire for two separate contracts to industry to study the command and service modules and various concepts for laboratory modules.

1964 January 15 - .
  • Plans for testing the Apollo heatshield under reentry conditions - . Nation: USA. Program: Apollo. Spacecraft: FIRE. MSC and Bellcomm agreed upon a plan for testing the Apollo heatshield under reentry conditions. Following Project Fire and Scout tests, the Saturn IB would be used to launch standard "all-up" spacecraft into an elliptical orbit; the SM engine would boost the spacecraft's velocity to 8,839 meters

    (29,000 feet) per second. Additional Details: Plans for testing the Apollo heatshield under reentry conditions.


1964 January 15 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC15. LV Family: Titan. Launch Vehicle: Titan 2. LV Configuration: Titan II N-31.
  • Research and development / Pod T test - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1964 January 15 - . 22:40 GMT - . Launch Site: Wallops Island. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.106CA.
  • Sodium release Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 114 km (70 mi).

1965 January 15 - . Launch Site: Green River. Launch Complex: Green River Pad 2. LV Family: Athena RTV. Launch Vehicle: Athena RTV. LV Configuration: Athena C006.
  • USAF C006 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1965 January 15 - . 21:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Delta. Launch Vehicle: Thor Agena D SLV-2A/D. LV Configuration: Thor SLV-2A Agena D 414 / Agena D SS-01A 1608.
  • KH-4A 1016 - . Payload: KH-4A s/n 1016 / Agena D 1608 / OPS 3928. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-4A. Decay Date: 1965-02-09 . USAF Sat Cat: 972 . COSPAR: 1965-002A. Apogee: 420 km (260 mi). Perigee: 180 km (110 mi). Inclination: 75.0000 deg. Period: 90.50 min. Summary: KH-4A. Smearing of highly reflective images due to reflections within camera..

1966 January 15 - . 00:00 GMT - . Launch Site: Kwajalein. LV Family: Loki. Launch Vehicle: Judi-Dart.
  • Weather mission - . Nation: USA. Agency: MRN. Apogee: 60 km (37 mi).

1968 January 15 - . 17:43 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 609. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P-138. FAILURE: Failure.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 10 km (6 mi).

1969 January 15 - .
  • Birth of Anatoli Alekseyevich Ivanishin - . Nation: Russia. Summary: Russian pilot cosmonaut, 2003-on. Ivanishin was a Captain in the Russian Air Force at Petrozavodsk when selected. A senior fighter pilot with the VVS, he had flown MiG-29 and Su-27 fighters. Russian Air Force.

1969 January 15 - . 07:04 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511.
  • Soyuz 5 - . Call Sign: Baikal (Baikal - lake in Siberia). Crew: Khrunov; Volynov; Yeliseyev. Backup Crew: Filipchenko; Gorbatko; Kubasov. Payload: Soyuz 7K-OK (P) s/n 13. Mass: 6,585 kg (14,517 lb). Nation: USSR. Related Persons: Khrunov; Volynov; Yeliseyev; Filipchenko; Gorbatko; Kubasov. Agency: MOM. Program: Soyuz. Class: Manned. Type: Manned spacecraft. Flight: Soyuz 5; Soyuz 4/5. Spacecraft: Soyuz 7K-OK. Duration: 3.04 days. Decay Date: 1969-01-18 . USAF Sat Cat: 3656 . COSPAR: 1969-005A. Apogee: 212 km (131 mi). Perigee: 196 km (121 mi). Inclination: 51.7000 deg. Period: 88.60 min. At 3 am an An-12 arrives from Moscow with ten newspapers, and letters for Shatalov, to be delivered by the Soyuz 5 crew to him as the first 'space mail'. At 05:15 the State Commission convened and approved launch at 10:04:30. The countdown proceeds normally; meanwhile communications sessions are held with Shatalov on Soyuz 4. The commission is taken by automobile convoy from Area 2, to Area 17, where the Soyuz 5 crew declares itself ready for flight. At T-25 minutes, with the crew already aboard the spacecraft, a piece of electrical equipment fails and needs to be replaced. Engineer-Captain Viktor Vasilyevich Alyeshin goes to the fuelled booster and replaces it. While doing this he notices that the access hatch has been secured with only three bolts, instead of the four required. Nevertheless the launch proceeds successfully. After Soyuz 5 is in orbit, it and Soyuz 4 begin their mutual series of manoeuvres for rendezvous and docking. Officially the flight conducted scientific, technical and medico-biological research, checking and testing of onboard systems and design elements of space craft, docking of piloted space craft and construction of an experimental space station, transfer of cosmonauts from one craft to another in orbit.

1969 January 15 - . 19:30 GMT - . Launch Site: White Sands. LV Family: Viper. Launch Vehicle: Viper-Dart. LV Configuration: Viper-Dart Sphere.
  • Meteorological Sphere Aeronomy mission - . Nation: USA. Agency: USA. Apogee: 147 km (91 mi).

1970 January 15 - . 00:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 557/D75.
  • Intelsat 3 F-6 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1977-05-13 . USAF Sat Cat: 4297 . COSPAR: 1970-003A. Apogee: 36,126 km (22,447 mi). Perigee: 36,079 km (22,418 mi). Inclination: 14.3000 deg. Period: 1,452.30 min. Stationed at 336 deg E. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 25 deg W in 1970; over the Atlantic Ocean 30 deg W in 1970-1971; over the Atlantic Ocean 20 deg W in 1971 Apr-1972 Mar; over the Indian Ocean 64 deg E in 1972-1974; over the Pacific Ocean 177 deg W in 1975 As of 5 September 2001 located at 163.49 deg E drifting at 4.024 deg W per day. As of 2007 Feb 27 located at 47.49E drifting at 4.027W degrees per day.

1970 January 15 - . 13:39 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/1. LV Family: Kosmos 2. Launch Vehicle: Kosmos 11K63.
  • Cosmos 319 - . Payload: DS-P1-Yu s/n 25. Mass: 250 kg (550 lb). Nation: USSR. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft: DS-P1-Yu. Completed Operations Date: 1970-07-01 . Decay Date: 1970-07-01 . USAF Sat Cat: 4299 . COSPAR: 1970-004A. Apogee: 1,508 km (937 mi). Perigee: 200 km (120 mi). Inclination: 82.0000 deg. Period: 102.00 min. Summary: Development of systems for air defence and the control of outer space..

1971 January 15 - .
  • Spiral to be raised at VVS Soviet. - . Nation: USSR. Related Persons: Zakharov; Leonov; Nikolayev. Spacecraft: Spiral OS. Kamanin manges to get to Zakahrov, who agrees to take the Spiral issue to the Military Soviet of the VVS. Leonov and Nikolayev review Kamanin's new draft decree to be presented to he Military Soviet. The DOS-7K is two weeks behind schedule for the planned 15 March launch date.

1971 January 15 - . 20:30 GMT - . Launch Site: Wallops Island. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk MUMP 10.
  • Aeronomy mission - . Nation: USA. Agency: USAF. Apogee: 289 km (179 mi).

1972 January 15 - . 05:37 GMT - . Launch Site: Gillam. LV Family: Black Brant. Launch Vehicle: Black Brant 3B. LV Configuration: Black Brant IIIB AAF-3B-53.
  • Auroral mission - . Nation: Canada. Agency: NRCC. Apogee: 190 km (110 mi).

1972 January 15 - . 06:01 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 5B. LV Configuration: Black Brant VB AAF-VB-33.
  • Not in FC Aeronomy / plasma mission - . Nation: Canada. Agency: NRCC. Apogee: 300 km (180 mi).

1972 January 15 - . 06:04 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 4B. LV Configuration: Black Brant IVB AAF-4B-25.
  • Not in FC Ionosphere mission - . Nation: Canada. Agency: NRCC. Apogee: 800 km (490 mi).

1972 January 15 - . 13:37 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P85H.
  • Solar La / X / ne Ionosphere / solar x-rays mission - . Nation: UK. Agency: SRC. Apogee: 147 km (91 mi).

1973 January 15 - . 23:40 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-8.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 122 km (75 mi).

1974 January 15 - . 20:00 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC36. LV Family: Black Brant. Launch Vehicle: Black Brant 5C. LV Configuration: Black Brant VC NASA 21.14DS-NP.
  • Solar mission - . Nation: USA. Agency: NASA. Apogee: 234 km (145 mi).

1975 January 15 - . 22:46 GMT - . Launch Site: Wallops Island. LV Family: Tomahawk Sandia. Launch Vehicle: Ute Tomahawk. LV Configuration: Ute Tomahawk CRL A09.105-8.
  • Aladdin 75 Reliability Test Aeronomy mission - . Nation: USA. Agency: USAF CRL. Apogee: 159 km (98 mi).

1976 January 15 - . 05:34 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Titan. Launch Vehicle: Titan 3E. LV Configuration: Titan IIIE 23E-5 / Centaur D-1T E-5.
  • Helios 2 - . Mass: 376 kg (828 lb). Nation: Germany. Agency: DFVLR. Class: Astronomy. Type: Solar astronomy satellite. Spacecraft: Helios. USAF Sat Cat: 8582 . COSPAR: 1976-003A. Summary: Solar probe. Solar Orbit (Heliocentric). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1977 January 15 - . 00:50 GMT - . Launch Site: Kiruna. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache SSC S18-1.
  • SSC S18 / 1 D Layer Ionosphere mission - . Nation: Sweden. Agency: SSC. Apogee: 104 km (64 mi).

1977 January 15 - . 01:40 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC36. LV Family: Black Brant. Launch Vehicle: Black Brant 5C. LV Configuration: Black Brant VC NASA 21.49UL.
  • Colorado microchannel Ultraviolet astronomy mission - . Nation: USA. Agency: NASA. Apogee: 268 km (166 mi).

1977 January 15 - . 06:17 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 170A. LV Configuration: Aerobee 170A NASA 13.122UH.
  • Wisconsin Soft X-ray Survey X-ray astronomy mission - . Nation: USA. Agency: NASA. Apogee: 196 km (121 mi).

1979 January 15 - . 14:00 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 92 km (57 mi).

1980 January 15 - . 01:14 GMT - . Launch Site: Kwajalein. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 74 km (45 mi).

1981 January 15 - . 20:00 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 86 km (53 mi).

1982 January 15 - . 09:20 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-73.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 303 km (188 mi).

1983 January 15 - . 03:14 GMT - . Launch Site: Eareckson. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 50 km (31 mi).

1984 January 15 - . 20:00 GMT - . Launch Site: Andoya. LV Family: Viper. Launch Vehicle: Viper 3A. LV Configuration: Viper 3A MAP/WINE.
  • M-F 25 Aeronomy mission - . Nation: Germany. Agency: DFVLR. Apogee: 118 km (73 mi).

1985 January 15 - . 14:50 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32. Launch Pad: LC32/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Cosmos 1617 - . Payload: Strela-3 no. 1. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 15469 . COSPAR: 1985-003A. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 82.6000 deg. Period: 114.10 min. Summary: First launch of new Strela-3 store-dump military communications satellite. Six Strelas are put into medium earth orbits with each launch. In the first two launches, four of the satellites are mass-model mockups..
  • Cosmos 1620 - . Payload: Strela-3 Mass Model. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 15472 . COSPAR: 1985-003D. Apogee: 1,413 km (877 mi). Perigee: 1,391 km (864 mi). Inclination: 82.6000 deg. Period: 113.80 min. Summary: Mass model of Strela-3..
  • Cosmos 1619 - . Payload: Strela-3 Mass Model. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 15471 . COSPAR: 1985-003C. Apogee: 1,413 km (877 mi). Perigee: 1,383 km (859 mi). Inclination: 82.6000 deg. Period: 113.70 min. Summary: Mass model of Strela-3..
  • Cosmos 1621 - . Payload: Strela-3 Mass Model. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 15473 . COSPAR: 1985-003E. Apogee: 1,413 km (877 mi). Perigee: 1,396 km (867 mi). Inclination: 82.6000 deg. Period: 113.90 min. Summary: Mass model of Strela-3..
  • Cosmos 1622 - . Payload: Strela-3 Mass Model. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 15474 . COSPAR: 1985-003F. Apogee: 1,414 km (878 mi). Perigee: 1,401 km (870 mi). Inclination: 82.6000 deg. Period: 113.90 min. Summary: Mass model of Strela-3..
  • Cosmos 1618 - . Payload: Strela-3 no. 2. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 15470 . COSPAR: 1985-003B. Apogee: 1,414 km (878 mi). Perigee: 1,408 km (874 mi). Inclination: 82.6000 deg. Period: 114.00 min.

1986 January 15 - . 14:20 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1724 - . Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Yantar-4K1. Duration: 59.00 days. Decay Date: 1986-03-15 . USAF Sat Cat: 16490 . COSPAR: 1986-004A. Apogee: 330 km (200 mi). Perigee: 167 km (103 mi). Inclination: 67.1000 deg. Period: 89.50 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 January 15 - . 08:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-9.
  • E field Ionosphere / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 365 km (226 mi).

1987 January 15 - . 11:20 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1813 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Earth. Type: Earth resources satellite. Spacecraft: Zenit-8. Decay Date: 1989-03-13 . USAF Sat Cat: 17297 . COSPAR: 1987-004A. Apogee: 397 km (246 mi). Perigee: 347 km (215 mi). Inclination: 72.8000 deg. Period: 92.00 min. Summary: Military cartographic satellite; reentry capsule destroyed in orbit..

1987 January 15 - . 15:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC46. LV Family: Trident. Launch Vehicle: Trident D-5. LV Configuration: Trident D-5 D5X-1.
  • Research and development launch - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1988 January 15 - . 03:49 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32. Launch Pad: LC32/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Cosmos 1909 - . Payload: Strela-3 no. 23. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 18788 . COSPAR: 1988-002A. Apogee: 1,413 km (877 mi). Perigee: 1,411 km (876 mi). Inclination: 82.6000 deg. Period: 114.00 min. Summary: Military store-dump communications satellite. Six satellites launched by a single carrier rocket..
  • Cosmos 1912 - . Payload: Strela-3 no. 26. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 18791 . COSPAR: 1988-002D. Apogee: 1,411 km (876 mi). Perigee: 1,395 km (866 mi). Inclination: 82.6000 deg. Period: 113.90 min.
  • Cosmos 1910 - . Payload: Strela-3 no. 24. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 18789 . COSPAR: 1988-002B. Apogee: 1,411 km (876 mi). Perigee: 1,407 km (874 mi). Inclination: 82.6000 deg. Period: 114.00 min.
  • Cosmos 1914 - . Payload: Strela-3 no. 28. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 18793 . COSPAR: 1988-002F. Apogee: 1,411 km (876 mi). Perigee: 1,383 km (859 mi). Inclination: 82.6000 deg. Period: 113.70 min.
  • Cosmos 1913 - . Payload: Strela-3 no. 27. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 18792 . COSPAR: 1988-002E. Apogee: 1,411 km (876 mi). Perigee: 1,390 km (860 mi). Inclination: 82.6000 deg. Period: 113.80 min.
  • Cosmos 1911 - . Payload: Strela-3 no. 25. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 18790 . COSPAR: 1988-002C. Apogee: 1,411 km (876 mi). Perigee: 1,400 km (800 mi). Inclination: 82.6000 deg. Period: 113.90 min.

1989 January 15 - . 07:02 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: BUGAEV. Launch Vehicle: MMR-06.
  • Aeronomy mission - . Nation: USSR. Agency: GMS. Apogee: 65 km (40 mi).

1990 January 15 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 734. LV Family: Trident. Launch Vehicle: Trident D-5.
  • PEM-7 operational test launch - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1991 January 15 - .
  • SAC transferred Vandenberg AFB, California, to Air Force Space Command. - . Nation: USA.

1991 January 15 - . Launch Site: Vandenberg.
  • Space Command takes over Vandenberg AFB from SAC. - . Nation: USA. Summary: Host base responsibilities for Vandenberg AFB transferred from Strategic Air Command to Air Force Space Command..

1991 January 15 - . 23:10 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44L. LV Configuration: Ariane 44L V41.
  • Italsat 1 - . Mass: 1,865 kg (4,111 lb). Nation: Italy. Agency: ASI. Class: Communications. Type: Civilian communications satellite. Spacecraft: Italsat. USAF Sat Cat: 21055 . COSPAR: 1991-003A. Apogee: 35,919 km (22,318 mi). Perigee: 35,817 km (22,255 mi). Inclination: 4.2000 deg. Period: 1,440.20 min. Experimental commsat; 13.2 deg E. ITALSAT is a body stabilized geostationary satellite and it is proposed to provide pre-operational domestic telecommunications services on the 20/30 GHz bands. Geographic longitude 13.2 deg E. Longitudinal tolerance +/- 0.1 deg. Positioned in geosynchronous orbit at 13 deg E in 1991-1999 As of 4 September 2001 located at 144.14 deg E drifting at 1.021 deg W per day. As of 2007 Mar 11 located at 86.26E drifting at 1.156W degrees per day.
  • Eutelsat II F2 - . Mass: 1,878 kg (4,140 lb). Nation: Europe. Agency: Eutelsat. Program: Eutelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 100. USAF Sat Cat: 21056 . COSPAR: 1991-003B. Apogee: 35,814 km (22,253 mi). Perigee: 35,759 km (22,219 mi). Inclination: 2.2000 deg. Period: 1,436.10 min. Stationed at 10 deg E. Telecommunications satellite. Registered by France in ST/SG/SER.E/234 and 239 until EUTELSAT can register the satellite. EUTELSAT is the European Telecommunications Satellite Organization. Positioned in geosynchronous orbit at 10 deg E in 1991-1999 12 deg W in 1999-2000 As of 4 September 2001 located at 12.60 deg W drifting at 0.009 deg W per day. As of 2007 Mar 10 located at 28.49E drifting at 4.801W degrees per day.

1992 January 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R806.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 January 15 - . 09:24 GMT - . Launch Site: Ascension. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 91 km (56 mi).

1994 January 15 - .
  • Mir News 204: Soyuz-TM17 returned to earth - . Nation: Russia. Program: Mir. Flight: Mir EO-15; Mir EO-14; Mir LD-4. On 14.01.1994 at 0819 UTC (08 hrs 18 mins 20 secs) the return capsule of the Soyuz-TM18 landed at 215 KM West of Karaganda in Kazakhstan. The cosmonauts (Tsibliyev and Serebrov) felt well after their flight of 197 days. They will be flown to Starcity near Moscow this afternoon. Again a routine-message about a routine-operation, but yet 'it has been a near thing' and nearly I had to draft a real shocking message!

    Return operation:

    At 0145 UTC the hatch of Soyuz-TM17 was closed behind Tsibliyev and Serebrov. At 0430 UTC the Soyuz-TM17 undocked from Mir. Tsibliyev had got orders to make a short inspection flight around the Mir-complex. They had to make images of the outer surface and they had to give special attention to the APAS89 docking system on Kristall (Module-T). In a distance of 30 Meters S- TM17 deviated from the desired course and collided with the Mir-station. Immediately radio contact with Soyuz-TM17 was lost. After 10 minutes TsUP managed to re-established radio contact with Soyuz-TM17 and the crew reported that their ship did not suffer damages and that the air-seal was still in good order. They also did not see any damages on the Mir-complex. Soyuz-TM17 made its last 2 orbits around the earth and the descent started at abt. 0715 UTC. At 0804 UTC the parachute opened and the 2-tonne heavy capsule made a safe landing at 08.18.20 UTC.

    Mir:

    The new crew (15th Main Expedition) immediately started observations through the portholes to try to determine eventual damages. During the passes in orbits 45206 (1100 UTC) and 45207 (1234 UTC) they transmitted to earth video-images which they made during the departure and fly-around of Soyuz-TM17. Shortly Afanasyev and Usachov will have to make a non-scheduled spacewalk to inspect the place, where Soyuz-TM17 hit the Mir- station. (probably near the APAS89 docking device on Kristall -Module-T).

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


1995 January 15 - . 13:45 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-8. FAILURE: Failure of second stage attitude control system.. Failed Stage: 2.
  • Express 1 - . Nation: Japan. Agency: ISAS. Class: Materials. Type: Materials science satellite. Spacecraft: Express 1. Decay Date: 1995-01-15 . COSPAR: F950115A. At first thought not to have reached orbit. Later the re-entry vehicle was discovered in Ghana having reentered and deployed its parachute on January 15. At T+103 sec, during the second stage burn, the vehicle veered off course. The payload service module entered a 110 x 250 km x 33 degree orbit, instead of the intended 270 x 380 km and re-entered on its second orbit. The re-entry capsule was found later in Ghana. A failure of the second stage attitude control system was blamed, although it was considered likely that the payload was too heavy for the vehicle, being twice the mass of earlier MU-3S payloads.

1996 January 15 - . 05:35 GMT - .
  • EVA STS-72-1 - . Crew: Chiao; Barry. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.26 days. Nation: USA. Related Persons: Chiao; Barry. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-72. Spacecraft: Endeavour. Summary: Tested tools and techniques for extravehicular activity..

1997 January 15 - . Launch Site: Barents Sea Launch Area. Launch Pad: 69.5 N x 34.2 E. Launch Platform: KALMAR. LV Family: R-29. Launch Vehicle: Volna SLV.
  • Operational test - . Nation: Russia. Agency: VMF. Apogee: 1,000 km (600 mi).

1999 January 15 - .
  • Wild Fire engine test. - . Nation: Canada. Program: X-Prize. Summary: The da Vinci Project (Toronto, Ontario, Canada) successfully tests single engine propulsion system..

1999 January 15 - . Launch Site: Sonmiani. LV Family: DF-15. Launch Vehicle: Shaheen 1. FAILURE: Failure.
  • Test mission - . Nation: Pakistan. Apogee: 0 km ( mi).

2001 January 15 - .
  • Stardust, Earth Flyby - . Nation: USA. Spacecraft: Stardust.

2003 January 15 - . 12:50 GMT - .
  • EVA ISS EO-6-1 - . Crew: Pettit; Bowersox. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.29 days. Nation: USA. Related Persons: Pettit; Bowersox. Program: ISS. Flight: ISS EO-6. The spacewalk was originally planned for December 12 and a crew of Budarin and Bowersox. But Budarin was prohibited by NASA from further EVA's (at least using US spacesuits) for undisclosed medical reasons. It took over a month for the plans for the spacewalk to be revised (since Budarin was not qualified to operate the space arm, Petit and Bowersox would have to move around the outside of the gigantic station without its assistance). They deployed the 23 m high central radiator panel on the P1 struss, cleaned up a docking port, installed external lighting on the S1 truss, and retrieved tools left on the Z1 truss.

2003 January 15 - . 13:02 GMT - . Launch Site: Kiruna. LV Family: Loki. Launch Vehicle: Super Loki.
  • SAGE-3 1 Aeronomy mission - . Nation: Germany. Agency: NASA. Apogee: 110 km (60 mi).

2004 January 15 - .
  • Spirit Rover Drives Onto Martian Surface - . Nation: USA. Spacecraft: MER.

2006 January 15 - .
  • Stardust, Capsule Return To Earth - . Nation: USA. Spacecraft: Stardust.

2006 January 15 - .
  • Cassini, Titan Flyby - . Nation: USA. Spacecraft: Cassini.

2008 January 15 - . 11:49 GMT - . Launch Site: Sea-launched. Launch Pad: KIR. Launch Platform: ODYSSEY. LV Family: Zenit. Launch Vehicle: Zenit-3SL. LV Configuration: Zenit-3SL s/n SL36.
  • Thuraya 3 - . Mass: 5,173 kg (11,404 lb). Nation: UAE. Agency: Thuraya. Manufacturer: Boeing. Program: Thuraya. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 702. USAF Sat Cat: 32404 . COSPAR: 2008-001A. Apogee: 35,820 km (22,250 mi). Perigee: 35,756 km (22,217 mi). Inclination: 6.2000 deg. Period: 1,436.20 min. Launch vehicle return-to-flight after on-pad explosion one year earlier damaged launch platform. The satellite was positioned at 98.5 degrees East Longitude to provide L-band and C-band mobile voice, broadband, maritime, rural telephony, and fleet management to Thuraya subscribers. Design lifetime of 12 years.

2010 January 15 - . 07:00 GMT - . Launch Site: Thumba. LV Family: RH. Launch Vehicle: RH-300 Mk II.
  • Eclipse - . Nation: India. Agency: ISRO. Apogee: 116 km (72 mi). Summary: Solar.

2010 January 15 - . 07:30 GMT - . Launch Site: Thumba. LV Family: RH. Launch Vehicle: RH-300 Mk II.
  • Eclipse - . Nation: India. Agency: ISRO. Apogee: 116 km (72 mi). Summary: Solar.

2010 January 15 - . 07:45 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560/300 Mk II.
  • Eclipse - . Nation: India. Agency: ISRO. Apogee: 523 km (324 mi). Summary: Solar.

2010 January 15 - . 10:30 GMT - . Launch Site: Thumba. LV Family: RH. Launch Vehicle: RH-300 Mk II.
  • Eclipse - . Nation: India. Agency: ISRO. Apogee: 116 km (72 mi). Summary: Solar.

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