Encyclopedia Astronautica
January 09


January 09 Chronology


1945 January 9 - . Launch Site: Peenemuende. Launch Complex: Peenemuende P7. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 V-292.
1948 January 9 - .
  • XS-1 Flight 63 - . Crew: Lilly. Payload: XS-1 # 2 flight 25. Nation: USA. Related Persons: Lilly. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: NACA flight 5. Pilot familiarization..

1952 January 9 - . Launch Site: White Sands. LV Family: Honest John. Launch Vehicle: Honest John. LV Configuration: Honest John 19.
  • Test mission - . Nation: USA. Apogee: 10 km (6 mi).

1958 January 9 - . 15:35 GMT - . Launch Site: White Sands. LV Family: Asp. Launch Vehicle: Nike Asp. LV Configuration: Nike Asp II8.10.
  • Test / solar ultraviolet mission - . Nation: USA. Agency: USAF. Apogee: 15 km (9 mi).

1959 January 9 - .
  • McDonnell selected to produce the Mercury spacecraft. - . Nation: USA. Related Persons: Glennan; Silverstein. Program: Mercury. Spacecraft: Mercury. The Source Selection Board at NASA Headquarters composed of Abe Silverstein, Ralph Cushman, George Low, Walter Schier, DeMarquis Wyatt, and Charles Zimmerman, completed their findings and reported to Dr. T. Keith Glennan, the Administrator. McDonnell Aircraft Corporation was selected as the prime contractor to develop and produce the Mercury spacecraft.

1961 January 9 - . LV Family: Nova. Launch Vehicle: Nova 4L.
  • First meeting of the Manned Lunar Landing Task Group - . Nation: USA. Related Persons: Silverstein. Program: Apollo. Spacecraft: Apollo CSM; Apollo Lunar Landing; CSM Source Selection; LM Mode Debate; LM Source Selection. At the first meeting of the Manned Lunar Landing Task Group, Associate Administrator Robert C. Seamans, Jr., Director of the Office of Space Flight Programs Abe Silverstein, and Director of the Office of Advanced Research Programs Ira H. Abbott outlined the purpose of the Group to the members. After a discussion of the instructions, the Group considered first the objectives of the total NASA program:

    1. the exploration of the solar system for knowledge to benefit mankind; and
    2. the development of technology to permit exploitation of space flight for scientific, military, and commercial uses.
    NASA's lunar program was a logical step toward these objectives. In current lunar program planning, three steps were projected:

    1. a manned landing on the moon with return to earth,
    2. limited manned lunar exploration, and
    3. a scientific lunar base.
    To accomplish the first step, a great increase in launch vehicle capability would be needed beyond that provided by current funding. A comparison of a three-million-pound-thrust and a six-million-pound-thrust Nova launch vehicle was made. It was estimated that a 60,000- to 80,000-pound payload to escape velocity would be needed for a manned lunar landing mission.

1962 January 9 - . Launch Site: North Atlantic Drop Zone. LV Family: Hound Dog. Launch Vehicle: Hound Dog. LV Configuration: Hound Dog CEL-2.
  • Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 20 km (12 mi).

1963 January 9 - .
  • Agreement reached on future Vostok flights - . Nation: USSR. Related Persons: Malinovskiy; Keldysh; Smirnov; Dementiev. Flight: Vostok 5; Vostok 6; Vostok 6A; Vostok 7; Vostok 8; Vostok 9; Vostok 10. After eight months of debate, a Vostok project plan was finally agreed. There would be a single female cosmonaut flight in March-Apriil 1963. This would be followed by 4 to 5 additional Vostok flights in 1963 and 2 to 3 flights in 1964. This plan was approved by Malinovskiy, Keldysh, Smirnov, and Dementiev and forwarded to the Communist Party Central Committee. However Rudenko and others were still opposed.

1964 January 9 - . LV Family: Kosmos 2; Kosmos 3.
  • R-12U and R-14U accepted into military service. - . Nation: USSR. Summary: Decree 'On adoption of the R-12U and R-14U shaft versions into armaments' was issued..

1965 January 9 - .
  • Cosmonaut recruitment - . Nation: USSR. Related Persons: Korolev; Tereshkova; Ponomaryova; Solovyova; Yerkina; Kuznetsova. Program: Voskhod. Flight: Voskhod 5. Spacecraft: Voskhod. Kamanin would like to get going with the training of 40 additional cosmonauts from many disciplines in order to 'storm space'. Korolev is opposed. Kamanin is also trying to get new flights scheduled for his female cosmonauts. This is never mentioned in the planning of future flights. Korolev is opposed to sending any further women into space. Kamanin would like to see a two-woman Voskhod flight, or a woman making a spacewalk. Aside from Tereshkova, Ponomaryova and Solovyova are as qualified and talented as any of the male cosmonauts for such flights. Yerkina and Kuznetsova, although they have completed the course, are ruled out by weaknesses in technical areas or character, in Kamanin's opinion.

1968 January 9 - . LV Family: Saturn I; Saturn V.
  • Budgetary restraints required additional cuts in AAP to three Saturn IB and three Saturn V launches. - . Nation: USA. Spacecraft: Orbital Workshop; Skylab; AES Lunar Base; ALSS Lunar Base. NASA budgetary restraints required an additional cut in AAP launches. The reduced program called for three Saturn IB and three Saturn V launches, including one Workshop launched on a Saturn IB, one Saturn V Workshop, and one ATM. Two lunar missions were planned. Launch of the first Workshop would be in April 1970.

1969 January 9 - . LV Family: N1. Launch Vehicle: N1.
  • State Commission for the first N1 launch - . Nation: USSR. Related Persons: Afanasyev, Sergei; Kurushin. Program: Lunar L3; Lunar L1. Spacecraft: Soyuz 7K-L1A. The State Commission for the first N1 launch, headed by Afanasyev, convenes at Area 12 of Baikonur. All of the Chief Designers and top generals of the VVS are in attendance. Many defects are identified in the review, but there seem to be no show-stoppers. Payload integration with the booster is to begin 13 January and launch by 18 February. Then Baikonur commander General Kurushin drops a bombshell - he declares he is not prepared to attempt to launch this 'unready' rocket. Much argument and discussion ensues. Finally Afanasyev asks that the issues raised be reviewed, in preparation for the next commission meeting on 11 January.

1969 January 9 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-300 ISAS. LV Configuration: S-300-1. FAILURE: Failure.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 0 km ( mi).

1969 January 9 - . 07:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-15.
  • E field antenna Ionosphere / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 188 km (116 mi).

1970 January 9 - . 09:20 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 318 - . Mass: 6,000 kg (13,200 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-2M. Duration: 12.00 days. Decay Date: 1970-01-21 . USAF Sat Cat: 4292 . COSPAR: 1970-001A. Apogee: 379 km (235 mi). Perigee: 206 km (128 mi). Inclination: 65.0000 deg. Period: 90.30 min. Summary: Area survey photo reconnaissance satellite; returned film capsule..

1971 January 9 - .
  • Shatalov comes to leadership attention after good work on Pompidou visit. - . Nation: USSR. Related Persons: Shatalov. Summary: The leadership wants to appoint Shatalov as a space adviser to the General Staff. Kamanin wants him as Deputy Commander of TsPK..

1971 January 9 - .
  • VVS Reviews TsKBM Facilities and Programs - . Nation: USSR. Related Persons: Chelomei; Ustinov; Mishin. Program: Almaz; Salyut. Spacecraft: Salyut 1; Almaz OPS. The VVS leadership visits Chelomei's facility at Reutov. Kamanin recalls first seeting the Almaz mock-up five years earlier - it was already fully defined then. But it was only in August 1970 that a resolution was issued setting a firm schedule: Chelomei was to start flight trails in the second half of 1971, and the station was to enter service in 1972. Mishin is proposing to cancel Almaz and build 10 DOS stations instead. Mishin currently supervises five design bureaux, 60,000 workers, and is working on Soyuz, 7K-S, L3, DOS-7K, and a very few other projects. Chelomei has only one design bureau and 8,000 workers. Yet he has produced well-designed, mass-produced cruise missiles for the Navy, over 1,000 ICBM's for the RVSN, and the high-quality UR-500 Proton launch vehicle. Almaz could have flown on time if Ustinov had allowed Chelomei just 10% of the resources he has let Mishin squander on DOS. Chelomei easily agrees with the VVS to a mutual schedule for Almaz crew training, crew composition, etc. The contrast with the argumentative Mishin couldn't be greater.

1972 January 9 - . 08:00 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 90 km (55 mi).

1973 January 9 - . 20:30 GMT - . Launch Site: Barking Sands. Launch Vehicle: Rocketsonde.
  • Starute, Datasonde - . Nation: USA. Agency: MRN. Apogee: 57 km (35 mi).

1974 January 9 - . 14:00 GMT - . Launch Site: Molodezhnaya. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 86 km (53 mi).

1975 January 9 - . Launch Site: Kwajalein. Launch Complex: Kwajalein RN. LV Family: Sergeant. Launch Vehicle: Castor. LV Configuration: Castor-2R.
  • Re-entry Vehicle test - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1976 January 9 - . Launch Site: Kapustin Yar. LV Family: Pioner. Launch Vehicle: Pioner.
  • Test mission - . Nation: USSR. Agency: RVSN. Apogee: 500 km (310 mi).

1978 January 9 - . 20:00 GMT - . Launch Site: White Sands. LV Family: Astrobee. Launch Vehicle: Astrobee F. LV Configuration: Astrobee F NASA 25.29GA.
  • Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 262 km (162 mi).

1979 January 9 - . 11:53 GMT - . Launch Site: White Sands. LV Family: Astrobee. Launch Vehicle: Astrobee F. LV Configuration: Astrobee F NASA 25.32UL.
  • Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 214 km (132 mi).

1980 January 9 - . 12:15 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1149 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-6U. Duration: 14.00 days. Decay Date: 1980-01-23 . USAF Sat Cat: 11652 . COSPAR: 1980-001A. Apogee: 384 km (238 mi). Perigee: 191 km (118 mi). Inclination: 72.9000 deg. Period: 90.30 min. Summary: Photo surveillance; returned film capsule..

1981 January 9 - . 14:57 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC41/1. LV Family: R-7. Launch Vehicle: Molniya 8K78M.
  • Molniya 3-14 - . Payload: Molniya-3 s/n 25. Mass: 1,600 kg (3,500 lb). Nation: USSR. Agency: MOM. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft: Molniya-3. Decay Date: 1999-07-03 . USAF Sat Cat: 12133 . COSPAR: 1981-002A. Apogee: 39,863 km (24,769 mi). Perigee: 487 km (302 mi). Inclination: 63.6000 deg. Period: 717.70 min. Replaced Molniya 3-10. Continued operation of the long-range telephone and telegraph radio-communication system within the Soviet Union and transmission of USSR central television programmes to stations in the Orbita and participating international networks (international cooperation scheme).

1983 January 9 - . 21:00 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: VOKV. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 85 km (52 mi).

1984 January 9 - . 23:59 GMT - . Launch Site: Wallops Island. LV Family: Loki. Launch Vehicle: Loki Dart. LV Configuration: Loki Dart T 1-0800.
  • Aeronomy mission - . Nation: USA. Agency: NASA Wallops. Apogee: 58 km (36 mi).

1985 January 9 - . 10:45 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1616 - . Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Yantar-4K1. Duration: 54.00 days. Decay Date: 1985-03-04 . USAF Sat Cat: 15467 . COSPAR: 1985-002A. Apogee: 356 km (221 mi). Perigee: 171 km (106 mi). Inclination: 64.9000 deg. Period: 89.80 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..

1986 January 9 - .
  • Stephen Synnott's Discovery of Uranus Moon Cressida - . Nation: USA.

1986 January 9 - . 02:48 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. Launch Pad: LC132/2?. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 47122-337.
  • Cosmos 1716 - . Payload: Strela-1M no. 289. Mass: 40 kg (88 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-1M. USAF Sat Cat: 16449 . COSPAR: 1986-002A. Apogee: 1,492 km (927 mi). Perigee: 1,463 km (909 mi). Inclination: 74.0000 deg. Period: 115.50 min. Summary: Eight satellites launched by a single carrier rocket..
  • Cosmos 1719 - . Payload: Strela-1M no. 292. Mass: 40 kg (88 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-1M. USAF Sat Cat: 16452 . COSPAR: 1986-002D. Apogee: 1,485 km (922 mi). Perigee: 1,454 km (903 mi). Inclination: 74.0000 deg. Period: 115.30 min.
  • Cosmos 1720 - . Payload: Strela-1M no. 293. Mass: 40 kg (88 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-1M. USAF Sat Cat: 16453 . COSPAR: 1986-002E. Apogee: 1,484 km (922 mi). Perigee: 1,440 km (890 mi). Inclination: 74.0000 deg. Period: 115.20 min.
  • Cosmos 1721 - . Payload: Strela-1M no. 294. Mass: 40 kg (88 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-1M. USAF Sat Cat: 16454 . COSPAR: 1986-002F. Apogee: 1,483 km (921 mi). Perigee: 1,427 km (886 mi). Inclination: 74.0000 deg. Period: 115.00 min.
  • Cosmos 1723 - . Payload: Strela-1M no. 296. Mass: 40 kg (88 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-1M. USAF Sat Cat: 16456 . COSPAR: 1986-002H. Apogee: 1,482 km (920 mi). Perigee: 1,400 km (800 mi). Inclination: 74.0000 deg. Period: 114.70 min.
  • Cosmos 1722 - . Payload: Strela-1M no. 295. Mass: 40 kg (88 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-1M. USAF Sat Cat: 16455 . COSPAR: 1986-002G. Apogee: 1,484 km (922 mi). Perigee: 1,413 km (877 mi). Inclination: 74.0000 deg. Period: 114.80 min.
  • Cosmos 1718 - . Payload: Strela-1M no. 291. Mass: 40 kg (88 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-1M. USAF Sat Cat: 16451 . COSPAR: 1986-002C. Apogee: 1,496 km (929 mi). Perigee: 1,475 km (916 mi). Inclination: 74.0000 deg. Period: 115.70 min.
  • Cosmos 1717 - . Payload: Strela-1M no. 290. Mass: 40 kg (88 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-1M. USAF Sat Cat: 16450 . COSPAR: 1986-002B. Apogee: 1,513 km (940 mi). Perigee: 1,475 km (916 mi). Inclination: 74.0000 deg. Period: 115.90 min.

1987 January 9 - . 12:38 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1811 - . Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Yantar-4K1. Duration: 35.00 days. Decay Date: 1987-02-13 . USAF Sat Cat: 17292 . COSPAR: 1987-002A. Apogee: 345 km (214 mi). Perigee: 169 km (105 mi). Inclination: 64.9000 deg. Period: 89.70 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..

1989 January 9 - . 11:25 GMT - . Launch Site: Thumba. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 83 km (51 mi).

1990 January 9 - . 12:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-32R.
  • STS-32 - . Call Sign: Columbia. Crew: Brandenstein; Dunbar; Ivins; Low; Wetherbee. Payload: Columbia F09 / Syncom-4 5 [Orbus-7S]. Mass: 12,014 kg (26,486 lb). Nation: USA. Related Persons: Brandenstein; Dunbar; Ivins; Low; Wetherbee. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-32. Spacecraft: Columbia. Duration: 10.88 days. Decay Date: 1990-01-20 . USAF Sat Cat: 20409 . COSPAR: 1990-002A. Apogee: 361 km (224 mi). Perigee: 296 km (183 mi). Inclination: 28.5000 deg. Period: 91.10 min. Manned five crew. Deployed Leasat 5, retrieved LDEF. Night landing. Payloads: Deployment of Syncom IV-5, retrieval of Long Duration Exposure Facility (LDEF), Fluids Experiment Apparatus (FEA)-3, Protein Crystal Growth (PCG) III-2, Latitude/Longitude Locator (L3), American Flight Echocardiograph (AFE), Characterization of Neurospora Circadian Rhythms in Space (CNCR)-01, Air Force Maui Optical Site (AMOS)-4, Mesoscale Lightning Experiment (MLE), IMAX, Interim Operational Contamination Monitor (lOCM).
  • Leasat 5 - . Payload: Columbia F9 / Syncom-4 5 [Orbus-7S]. Mass: 3,400 kg (7,400 lb). Nation: USA. Agency: HCI. Program: Leasat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 20410 . COSPAR: 1990-002B. Apogee: 35,797 km (22,243 mi). Perigee: 35,776 km (22,230 mi). Inclination: 4.4000 deg. Period: 1,436.10 min. Deployed from STS 32 1/10/89; 177 deg W; leased to U.S. government. The Leasat series was developed as a commercial venture to provide dedicated communications services to the U. S. military. Positioned in geosynchronous orbit at 178 deg E in 1990; 72 deg E in 1990-1997; 77 deg E in 1997-1998; 155 deg E in 1998-1999 As of 5 September 2001 located at 155.70 deg E drifting at 0.023 deg W per day. As of 2007 Mar 11 located at 100.05E drifting at 0.003E degrees per day. Additional Details: Leasat 5.

1991 January 9 - . 22:14 GMT - . Launch Site: Wallops Island. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 94 km (58 mi).

1992 January 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R805.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 January 9 - .
  • Mir News 202: Soyuz-TM18 blasted off for flight to Mir - . Nation: Russia. Program: Mir. Flight: Mir EO-15; Mir EO-14; Mir LD-4. Soyuz-TM18 has been launched from Baykonur on 8.01.94 at 1005 UTC. All went well and at 1014 UTC Soyuz-TM18 had reached the right orbit. For the flight the 1st crew had been selected, so: Captain V. Afanasyev, who makes his 2d flight, board engineer (rookie) Yu. Usachev (pronunciation Usachov ) and the physician Dr. V. Polaykov, making his 2d flight. He will try to remain 427 days in space. The call of the crew is Derbent, so resp. Derbent-1, 2 and 3. For radio-amateur traffic resp. U9Mir, R3Mir and U3Mir. Soyuz-TM18 came in range during orbit 3, 1307 UTC. Strong transmissions on the known frequencies (121.750, 165.874 and 922.755 mc). Afanasyev reported that all went well and he added some pressure values. After abt. 30 mins Mir (orb. 45114) could be heard here. TsUP told the Mir-crew that all on board Soyuz-TM18 was normal. In the pass in the 4th orbit (1436 UTC) Afanasyev reported that the Soyuz-TM18 executed 2 orbit corrections without significant problems. During the pass in the 5th orbit (1609- UTC) Afanasyev reported the successful performance of Soyuz-TM18 during the 3d orbit correction. Afanasyev got the order to adjust the Globus position indicator and Dr. Polyakov stated that the condition of the crew was excellent. On 10.01.94 at 1150 UTC Soyuz-TM18 has to dock to the Mir-complex. This will be abt 4 mins. after LOS of the space objects in Mir's orbit nr. 45144.

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


1996 January 9 - . 18:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 73 km (45 mi).

1998 January 9 - . 23:08 GMT - .
  • EVA Mir EO-24-6 - . Crew: Solovyov; Vinogradov. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.13 days. Nation: Russia. Related Persons: Solovyov; Vinogradov. Program: Mir. Class: Manned. Type: Manned space station. Flight: Mir NASA-5; Mir EO-24. Spacecraft: Mir. Summary: Recovered equipment; began repairs on leaky Kvant-2 airlock. Examination of airlock indicated cause was loose belt, resulting in 10 mm gap..

2000 January 9 - . 20:50 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-29.
  • WAVE2000 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 179 km (111 mi).

2001 January 9 - . 17:00 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan SLS. LV Family: CZ. Launch Vehicle: CZ-2F. LV Configuration: Chang Zheng 2F CZ2F-2 (65).
  • Shenzhou 2 - . Mass: 7,400 kg (16,300 lb). Nation: China. Agency: CASC. Manufacturer: CALT. Class: Manned. Type: Manned spacecraft. Spacecraft: Shenzhou. Duration: 6.77 days. Decay Date: 2001-01-16 . USAF Sat Cat: 26664 . COSPAR: 2001-001A. Apogee: 345 km (214 mi). Perigee: 330 km (200 mi). Inclination: 42.6000 deg. Period: 91.30 min. The second unmanned test flight of the Shenzhou manned spacecraft design carried a monkey, a dog and a rabbit in a test of the spaceship's life support systems. Shenzhou 2 was the first test of an all-up flight model of the spacecraft, with a functioning orbital module. It was also the most ambitious space science laboratory ever launched by China. It carried 64 scientific payloads: 15 in the re-entry module, 12 in the orbital module and 37 on the forward external pallet. These included a micro-gravity crystal growing device; life sciences experiments with 19 species of animals and plants, cosmic ray and particle detectors; and China's first gamma ray burst detectors.

    The launch was originally scheduled for January 5, but the second stage of the launch vehicle was dented by an access platform while being prepared for roll-out in the vehicle assembly building. This caused several days of delay until it was cleared for flight. Shenzhou 2 made three orbit-raising manoeuvres during its flight, reaching a 330 x 345 km orbit by the end of the initial phase of the mission. Ninety minutes before landing the orbital module depressurised, and the spacecraft went briefly out of control. However this was regained after venting of the atmosphere from the module ended. The descent module and service modules separated from the forward orbital module and external pallet normally. After retrofire by the service module, it separated and the descent module landed at 11:22 GMT on January 16 in Inner Mongolia. Lack of post-recovery photographs led to speculation that the recovery may not have been completely successful. The Shenzhou orbital module had its own solar panels and remained operational in orbit, conducting scientific experiments. It was actively controlled for six months, maneuvering in orbit several times (reaching a final orbit of 394 x 405 km). It then was allowed to decay and reentered the atmosphere at 09:05 GMT on August 24, 2001. The reentry point was near 33.1 deg S in latitude and 260.4 deg E in longitude, over the western Pacific Ocean between Easter Island and Chile.


2003 January 9 - . 03:17 GMT - . Launch Site: Balasore. Launch Complex: Balasore IC4. LV Family: Agni. Launch Vehicle: Agni 1.
  • Agni RV Mk 2 - . Nation: India. Agency: IDRDL. Apogee: 300 km (180 mi). Summary: MRBM test with dummy warhead..

2004 January 9 - . 18:40 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF21. Launch Vehicle: Orbus. LV Configuration: GBI BV-5.
  • GMDS BVT-5 'BV+' test - . Nation: USA. Agency: USAF AFSPC. Apogee: 200 km (120 mi). Dummy EKV payload. Launch delayed from August, September, and December 18, 2003. Booster Verification Test -5 tested a three-stage booster configuration for use with the Missile Defense Agency's Ground-based Midcourse Defense System. Built by Lockheed Martin Corp., the booster was one of two slated for use with the GMD system. The system was designed to intercept and destroy long-range ballistic missiles.

2008 January 9 - .
  • ISS On-Orbit Status 01/09/08 - . Nation: USA. Related Persons: Anderson, Clayton; Love; Malenchenko; Tani; Whitson; Williams, Dave. Program: ISS. Flight: ISS EO-15-2; ISS EO-16; ISS EO-16-1. CDR Whitson and FE-2 Tani started out with the daily reading of SLEEP (Sleep-Wake Actigraphy and Light Exposure during Spaceflight) experiment data accumulated during the night, for logging and filling in questionnaire entries in the SLEEP session file on the HRF-1 laptop for downlink.

    (To monitor the crewmembers' sleep/wake patterns and light exposure, Dan and Peggy wear a special Actiwatch device which measures the light levels encountered by him as well as his patterns of sleep and activity throughout the Expedition. The log entries are done within 15 minutes of final awakening for seven consecutive days, as part of the crew's discretionary 'job jar' task list.)

    The FE-2 worked in the Airlock (A/L), starting on a lengthy (2h 25m) troubleshooting procedure on the EACP (EVA/EMU Audio Control Panel), first setting up comm from the A/L, then activating the EACP and connecting it via the 'low clearance' Y-cable to ATU-4 (Audio Terminal Unit, #4) and ATU-6 on the A/L Avionics Rack. After initial testing, the EACP was turned off again. (ATU-6 was installed by Clay Anderson on 10/11/07 in place of a failed unit, and the failed ATU-6 was returned on 10A. The new ATU-6 has been experiencing periodic lockups and PBIT (passive built-in test) faults. Engineering analysis and testing indicate that these issues may be caused by improperly mated J3 & J4 connections, a problem with the address connector, or a dirty fiber-optic connector. There are 3 ATUs in the A/L, one of which must be functional for EVAs, so long as the suited EVA crew has established UHF (Ultra High Frequency) radio communication.) Additional Details: ISS On-Orbit Status 01/09/08.


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