Encyclopedia Astronautica
January 30


January 30 Chronology


1934 January 30 - .
  • OSOAVIAKHIM giant stratosphere balloon reached 22 000 meters. - . Nation: USSR. Spacecraft: OSOAVIAKHIM. Apogee: 22 km (13 mi). Summary: The crew was killed when the cabin was covered with thick ice, resulting in it tearing loose from the balloon and crashing to the earth during the descent..

1945 January 30 - . Launch Site: V-2 Battery SS Abt 500. LV Family: V-2. Launch Vehicle: V-2.
  • V-2 Battery SS 500 moves - . Nation: Germany. Agency: Wehrmacht. Summary: Battery SS 500 moves to the Estate Mataram near Emmen in Dalfsen. The Leitstrahlstellung radio guidance station moves to Ommerschans..

1947 January 30 - .
  • XS-1 Flight 21 - . Crew: Goodlin. Payload: XS-1 # 2 flight 11. Nation: USA. Related Persons: Goodlin. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: Bell flight 11. Accelerated stalls. Partial power due to engine igniters. Mach 0.75..

1948 January 30 - .
  • XS-1 Flight 70 - . Crew: Yeager. Payload: XS-1 # 1 flight 41. Nation: USA. Related Persons: Yeager. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: AF flight 19. Pressure distribution survey. Mach 1.1..

1951 January 30 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-1. Launch Vehicle: R-1. LV Configuration: R-1 IIIA-5.
  • Operational test - . Nation: USSR. Agency: Korolev. Apogee: 100 km (60 mi).

1952 January 30 - .
  • NACA manned space flight test vehicle within 2 years. - . Nation: USA. Spacecraft: X-15A. An NACA report was issued covering several projects and proposals for the flight of manned and unmanned vehicles to altitudes above the earth where atmospheric density was very low. The substance of these reports was presented at the June 24, 1952, meeting of the Committee on Aerodynamics. After the presentation, committee member Robert J. Woods recommended that basic research be initiated on the problems of space flight and stated that the NACA was the logical organization to carry on this work. To accomplish this task, a small working group was established to analyze the available information on the subject of space flight. The objective of this group was to arrive at a concept of a suitable manned test vehicle that could be constructed within 2 years.

1952 January 30 - .
  • NACA study group to investigate the problems of space flight - . Nation: USA. Robert J. Woods of the Bell Aircraft Company recommended to the Committee on Aerodynamics of the National Advisory Committee for Aeronautics (NACA) that a small study group be formed to investigate the problems of space flight. On June 24, the NACA Committee adopted a resolution (1) that NACA research effort on problems of manned and unmanned flight in the upper stratosphere at altitudes between 12 and 50 miles and at Mach numbers between 4 and 10 be increased, and (2) that NACA devote a modest effort to problems associated with manned and unmanned flight at altitudes from 50 miles to infinity and at speeds from Mach 10 to the velocity of escape from earth's gravity. Additional Details: NACA study group to investigate the problems of space flight.

1952 January 30 - . Launch Site: Le Cardonnet. LV Family: Veronique. Launch Vehicle: Veronique R. LV Configuration: Veronique R R8.
  • Test mission - . Nation: France. Agency: LRBA. Apogee: 1.00 km (0.60 mi).

1952 January 30 - . 20:45 GMT - . Launch Site: Holloman. Launch Complex: Holloman A. LV Family: Aerobee. Launch Vehicle: Aerobee RTV-A-1a. LV Configuration: Aerobee RTV-A-1a USAF 21. FAILURE: Failure..
  • AF / Utah Ionosphere 1 Ionosphere mission - . Nation: USA. Agency: USAF AFSC. Apogee: 0 km ( mi). Summary: Ionosphere research. Launched at 1345 local time. Failure..

1953 January 30 - .
1953 January 30 - . Launch Site: White Sands. LV Family: Corporal. Launch Vehicle: Corporal. LV Configuration: Corporal 1E.
  • Test mission - . Nation: USA. Apogee: 30 km (18 mi).

1956 January 30 - .
  • Development of first Sputnik authorised. - . Nation: USSR. Spacecraft: Sputnik 3. Summary: Central Committee of the Communist Party and Council of Soviet Ministers Decree 149882 'On creation of the Object D artificial satellite' was issued..

1956 January 30 - .
  • Work began in the Soviet Union on military satellites. - . Nation: USSR. Spacecraft: Zenit. Design work starts on the Zenit, the first military photo-reconnaisance satellite. The necessary subsystems were defined incrementally throughout 1956 in a series of specification documents. In April the specifications for a redundant restartable engine and appropriate satellite guidance and control systems were released. In May the technical requirements document was issued for a satellite that could be oriented in orbit. In July tests began of appropriate heat shield materials.

1957 January 30 - .
1959 January 30 - .
  • Navy candidates for Project Mercury. - . Nation: USA. Related Persons: Glennan. Program: Mercury. Summary: Admiral Arleigh Burke, Chief of Naval Operations, advised Dr. T. Keith Glennan that Navy candidates for Project Mercury had started in the first selection process..

1959 January 30 - . 23:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Thor DM-18A. LV Configuration: Thor DM-18A 154.
  • Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1960 January 30 - . 11:54 GMT - . Launch Site: Pacific Ocean. Launch Pad: 26.0 N x 169.4 E. Launch Platform: VOKV. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Agency: GMS. Apogee: 42 km (26 mi).

1961 January 30 - .
  • James E Webb named as NASA Administrator - . Nation: USA. Related Persons: Kennedy; Webb. Program: Apollo. President John F. Kennedy announced that he was nominating James E. Webb as Administrator of the National Aeronautics and Space Administration and Hugh L. Dryden as Deputy Administrator, Senate confirmation followed on February 9 and they were sworn in on February 14.

1961 January 30 - . LV Family: Europa. Launch Vehicle: Europa.
  • Europa conference. - . Nation: Europe. Summary: Conference of 12 European nations held at Strasbourg to discuss a British and French proposal for a European satellite launcher development program..

1961 January 30 - . 23:20 GMT - . Launch Site: Eglin. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 AA3.370.
  • Mass spectrometer Aeronomy mission - . Nation: USA. Agency: USAF. Apogee: 204 km (126 mi).

1962 January 30 - . LV Family: Atlas. Launch Vehicle: Atlas D.
  • Mercury MA-6 postponed - . Nation: USA. Program: Mercury. Summary: The Mercury-Atlas 6 (MA-6) mission was postponed because of technical difficulties with the launch vehicle..

1963 January 30 - .
  • Selection of four companies as major Apollo LEM subcontractors - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM; LM Ascent Propulsion; LM Descent Propulsion; LM ECS; LM RCS. Grumman and NASA announced the selection of four companies as major LEM subcontractors:

    1. Rocketdyne for the descent engine
    2. Bell Aerosystems Company for the ascent engine
    3. The Marquardt Corporation for the reaction control system
    4. Hamilton Standard for the environmental control system

1964 January 30 - . 09:45 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Vostok 8K72K.
  • Elektron 1 - . Payload: 2D s/n 1. Mass: 329 kg (725 lb). Nation: USSR. Agency: Korolev. Program: Elektron. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Elektron-A. USAF Sat Cat: 746 . COSPAR: 1964-006A. Apogee: 6,439 km (4,001 mi). Perigee: 413 km (256 mi). Inclination: 60.9000 deg. Period: 161.00 min. Studied inner Van Allen belt. Electron I and II launched by a single carrier rocket. Electron I: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and upper atmosphere. Electron II: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and outer space.
  • Elektron 2 - . Payload: 2D s/n 2. Mass: 444 kg (978 lb). Nation: USSR. Agency: Korolev. Program: Elektron. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Elektron-B. Decay Date: 1997-04-22 . USAF Sat Cat: 748 . COSPAR: 1964-006B. Apogee: 62,811 km (39,028 mi). Perigee: 5,611 km (3,486 mi). Inclination: 60.2000 deg. Period: 1,356.40 min. Studied outer Van Allen belt. Electron I and II launched by a single carrier rocket. Electron I: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and upper atmosphere. Electron II: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and outer space.

1964 January 30 - . 15:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC12. LV Family: Atlas. Launch Vehicle: Atlas Agena B. LV Configuration: Atlas Agena B 199D (AA8) / Agena B 6008 (AA8).
  • Ranger 6 - . Payload: RA-6. Mass: 362 kg (798 lb). Nation: USA. Agency: NASA; JPL. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 6-7-8-9. Decay Date: 1964-02-02 . USAF Sat Cat: 747 . COSPAR: 1964-007A. Impacted Moon but TV camera malfunctioned. A midcourse trajectory correction was accomplished early in the flight by ground control. On February 2, 1964, 65.5 hours after launch, Ranger 6 impacted the Moon on the eastern edge of Mare Tranquillitatis (Sea of Tranquility). No camera data were obtained, probably because of failure due to an arc-over in the TV power system when it inadvertently turned on during the period of booster-engine separation.

1965 January 30 - .
1965 January 30 - . 07:45 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NF3.162.
  • Infrared astronomy mission - . Nation: USA. Agency: NRL. Apogee: 211 km (131 mi).

1965 January 30 - . 08:04 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC67/22. LV Family: Tsiklon. Launch Vehicle: R-36 8K67.
  • POR state trials missile launch - . Nation: USSR. Agency: RVSN. Apogee: 1,493 km (927 mi).

1965 January 30 - . 09:36 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar LC86/1. LV Family: Kosmos 2. Launch Vehicle: Kosmos 63S1.
  • Cosmos 53 - . Payload: DS-A1 s/n 5. Mass: 310 kg (680 lb). Nation: USSR. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft: DS-A1. Completed Operations Date: 1965-02-09 . Decay Date: 1966-08-12 . USAF Sat Cat: 983 . COSPAR: 1965-006A. Apogee: 1,172 km (728 mi). Perigee: 221 km (137 mi). Inclination: 48.7000 deg. Period: 98.70 min. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.

1966 January 30 - .
  • Voskhod training - . Nation: USSR. Related Persons: Volynov; Shonin; Beregovoi; Shatalov; Katys; Gorbatko. Program: Voskhod. Flight: Voskhod 3. Spacecraft: Voskhod. Kamanin observed cosmonaut training at TsPK on this Saturday. Beregovoi and Shatalov work in the Voskhod trainer. The exercises show that the Svinets military equipment is working poorly. Engineers are brought in Saturday evening and Sunday to fix the problems. Three crews are in training for Voskhod 3, prepared for flights of up to 30-40 days duration. Prime crew is now Volynov and Shonin; backup Beregovoi and Shatalov; reserve cosmonauts Katys and Gorbatko. Afterwards the daily routine for the long-duration missions is discussed - communications session protocols, scientific and military experiments (although these are still not completely developed). Of particular concern to Volynov is that each cosmonaut gulp down 2.088 litres of water per day. There is no good way of measuring the precise amount - some kind of dosage device needs to be developed. Beregovoi's worry is the unnecessary complex and irrational design of operation of the Svinets device. Shonin is concerned with problems with the NAZ survival equipment. There are so many open issues, yet the final flight program has to be established by 5 February.

1967 January 30 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF03. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 1206.
  • Follow-on operational missile test - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1968 January 30 - .
  • Three-hour review of the L1 program at the Institute of Aviation Medicine. - . Nation: USSR. Program: Lunar L1. Spacecraft: Soyuz 7K-L1. Summary: The Volchka L1 trainer, M-220 computer, centrifuge, L1 cabin, and instructor control station are in place. But many critical equipment items have not yet been installed, including essential cabin instruments and flight indicators..

1968 January 30 - . 05:03 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 2. LV Configuration: Black Brant II AKD-2A-111.
  • Aurora mission - . Nation: Canada. Agency: NRCC. Apogee: 161 km (100 mi).

1969 January 30 - . LV Family: N1. Launch Vehicle: N1.
  • N1/Ye-8-5 launch preparations - . Nation: USSR. Related Persons: Tyulin; Mishin. Program: Lunar L3; Luna. Spacecraft: Luna Ye-8-5. Summary: Mishin agrees with Tyulin that he will fly to Tyuratam on 3 February to supervise launch of the Ye-8 on 18 February and the first N1 on 21 February. .

1969 January 30 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF03. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 874.
  • FOT GT32B Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1969 January 30 - . 06:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Delta. Launch Vehicle: Delta E1. LV Configuration: Thor Delta E1 485/D65.
  • Isis 1 - . Payload: Isis A. Mass: 241 kg (531 lb). Nation: Canada. Agency: CRCSS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Isis. USAF Sat Cat: 3669 . COSPAR: 1969-009A. Apogee: 3,458 km (2,148 mi). Perigee: 578 km (359 mi). Inclination: 88.4000 deg. Period: 127.60 min. Summary: Ionospheric measurements; data correlated with measurements from Alouette 1. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1969 January 30 - . 17:10 GMT - . Launch Site: Fort Churchill. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.302GM.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 124 km (77 mi).

1970 January 30 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2A. Launch Vehicle: DF-4.
  • R&D (Minfeng target) - . Nation: China. Agency: MAI. Apogee: 500 km (310 mi). Summary: First test of prototype DF-3 (perhaps same configuration as CZ-1); not deployed..

1970 January 30 - . Launch Site: Baikonur. Launch Complex: Baikonur LC142/34. LV Family: Tsiklon. Launch Vehicle: R-36 8K67M.
  • State trials missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1970 January 30 - . Launch Site: Baikonur. Launch Complex: Baikonur LC161/35. LV Family: Tsiklon. Launch Vehicle: R-36 8K67M.
  • State trials missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1970 January 30 - . 15:40 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/1. LV Family: Kosmos 2. Launch Vehicle: Kosmos 11K63. FAILURE: Second stage failed 128 seconds after launch.. Failed Stage: 2.
  • DS-P1-I s/n 6 - . Payload: DS-P1-I. Nation: USSR. Agency: RVSN. Program: DS. Class: Military. Type: Military target satellite. Spacecraft: DS-P1-I. COSPAR: F700130A. Summary: Operational radar target for the ABM forces..

1970 January 30 - . 22:30 GMT - . Launch Site: Natal. LV Family: Javelin. Launch Vehicle: Javelin. LV Configuration: Javelin N-J-20.
  • DLR N-J-20 Ionosphere mission - . Nation: Germany. Agency: DLR. Apogee: 800 km (490 mi).

1971 January 30 - .
  • Warsaw Pact officers tour Gagarin Cosmonaut Training Centre. - . Nation: USSR. Summary: The TsPK is visited by participants in a meeting of the Warsaw Pact General Staff. This amounts to 29 generals, 2 to 3 from each country of the pact..

1972 January 30 - . 09:00 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 30 - . 06:35 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 SL1205.
  • GX2+5 Lunar Occultation X-ray astronomy mission - . Nation: UK. Agency: BAC. Apogee: 234 km (145 mi).

1974 January 30 - . Launch Site: Biscarosse. Launch Complex: Biscarosse BLB. LV Family: SSBS. Launch Vehicle: SSBS S2. LV Configuration: SSBS S2 S-1E-2603.
  • Operational test - . Nation: France. Agency: DMA. Apogee: 1,000 km (600 mi).

1974 January 30 - . 11:00 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 630 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MK. Duration: 14.00 days. Decay Date: 1974-02-13 . USAF Sat Cat: 7104 . COSPAR: 1974-004A. Apogee: 346 km (214 mi). Perigee: 203 km (126 mi). Inclination: 72.8000 deg. Period: 90.00 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1975 January 30 - . 02:15 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 5B. LV Configuration: Black Brant VB AED-VB-43.
  • Auroral/Aeronomy mission - . Nation: Canada. Agency: NRCC. Apogee: 244 km (151 mi).

1975 January 30 - . 14:10 GMT - . Launch Site: El Arenosillo. LV Family: Skua. Launch Vehicle: Skua 4. LV Configuration: Skua 4 S4CL0-75001.
  • Aeronomy / ionosphere mission - . Nation: UK. Agency: INTA; DLR. Apogee: 117 km (72 mi).

1975 January 30 - . 15:02 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC41/1. LV Family: R-7. Launch Vehicle: Molniya 8K78M.
  • Cosmos 706 - . Payload: Oko #4. Mass: 1,250 kg (2,750 lb). Nation: USSR. Agency: MOM. Class: Military. Type: Early warning satellite. Spacecraft: Oko. USAF Sat Cat: 7625 . COSPAR: 1975-007A. Apogee: 35,365 km (21,974 mi). Perigee: 4,977 km (3,092 mi). Inclination: 67.8000 deg. Period: 717.60 min. Summary: Covered Oko constellation planes 7/8 - 182 degree longitude of ascending node..

1976 January 30 - . Launch Site: Baikonur. Launch Complex: Baikonur LC103. LV Family: R-36M. Launch Vehicle: R-36M.
  • Operational missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 January 30 - . 01:07 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 7 AC. LV Configuration: Skylark 7 AC SL1302.
  • Quiet Coronal Structure Solar x-ray mission - . Nation: UK. Agency: BAC. Apogee: 278 km (172 mi).

1977 January 30 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF21. LV Family: Minuteman. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 STM-13W.
  • Research and development launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1978 January 30 - . 20:52 GMT - . Launch Site: Andoya. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk NASA 18.211IE/UE.
  • Auroral mission - . Nation: USA. Agency: NASA. Apogee: 220 km (130 mi).

1978 January 30 - . 21:37 GMT - . Launch Site: Andoya. LV Family: Skylark. Launch Vehicle: Skylark 12. LV Configuration: Skylark 12 DLR A-GRC-86.
  • T / NL 4C Gitti Aurora mission - . Nation: Germany. Agency: DFVLR. Apogee: 540 km (330 mi).

1978 January 30 - . 22:10 GMT - . Launch Site: Andoya. LV Family: Skylark. Launch Vehicle: Skylark 12. LV Configuration: Skylark 12 DLR A-GRC-88.
  • T / NL 2D Susanne Aurora mission - . Nation: Germany. Agency: DFVLR. Apogee: 541 km (336 mi).

1979 January 30 - .
  • Start orbiter/ET/SRB burnout mated vibe tests - . Nation: USA. Program: STS. Summary: Start orbiter/ET/SRB burnout mated vertical ground vibration test, MSFC.

1979 January 30 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF08. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT66GM Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1979 January 30 - . 15:15 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1073 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MKM. Duration: 29.00 days. Decay Date: 1979-02-12 . USAF Sat Cat: 11255 . COSPAR: 1979-006A. Apogee: 328 km (203 mi). Perigee: 182 km (113 mi). Inclination: 62.8000 deg. Period: 89.60 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1979 January 30 - . 21:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta 2914. LV Configuration: Delta 2914 629/D148.
  • SCATHA - . Payload: P 78-2. Mass: 360 kg (790 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft: SCATHA. Completed Operations Date: 1991-05-28 . USAF Sat Cat: 11256 . COSPAR: 1979-007A. Apogee: 42,860 km (26,630 mi). Perigee: 28,018 km (17,409 mi). Inclination: 10.2000 deg. Period: 1,418.40 min. Spacecraft charging experiments. The SCATHA spacecraft had two charged particle injection systems, one of which was the Satellite Positive-Ion-Beam System (SPIBS). This was a xenon ion source which included some of the technologies used in thrusters: however, the discharge chamber was not performance optimized as was done with ion engines. Maximum operating power was 0.045 kW, and the ion source could produce a thrust of about 0.14 mN at a specific impulse of 350 s. Ions could be ejected at 1 keV or 2 keV. Neutralization was accomplished by a tantalum filament. The specific impulse was low because there was no attempt to optimize the propellant efficiency. The SPIBS system was ground-tested for a period of 600 hours. The SCATHA spacecraft was placed in a near geosynchronous orbit. Ion beam operations were performed intermittently over a 247 day period. The SCATHA flight demonstrated that a charged spacecraft, and the dielectric surfaces on it, could be safely discharged by emitting a very low energy (<50 eV) neutral plasma -- in effect shorting the spacecraft to the ambient plasma before dangerous charging levels could be reached. As of 28 August 2001 located at 153.98 deg W drifting at 4.513 deg E per day. As of 2007 Mar 8 located at 19.65W drifting at 4.513E degrees per day.

1980 January 30 - . 12:51 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Vostok 8A92M.
  • Cosmos 1154 - . Payload: Tselina-D no. 24. Mass: 3,800 kg (8,300 lb). Nation: USSR. Agency: MOM. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-D. Decay Date: 2002-11-05 . USAF Sat Cat: 11682 . COSPAR: 1980-008A. Apogee: 545 km (338 mi). Perigee: 540 km (330 mi). Inclination: 81.2000 deg. Period: 95.50 min.

1981 January 30 - . 16:27 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Molniya 8K78M.
  • Molniya 1-49 - . Payload: Molniya-1T. Mass: 1,600 kg (3,500 lb). Nation: USSR. Agency: MOM. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft: Molniya-1T. USAF Sat Cat: 12156 . COSPAR: 1981-009A. Apogee: 38,759 km (24,083 mi). Perigee: 1,571 km (976 mi). Inclination: 63.7000 deg. Period: 717.30 min. Summary: Replaced Molniya 1-41. Uncertain if Molniya-1T model was Molniya-1 or Molniya-1T. Operation of the long-range telephone and telegraph radiocommunications system in the USSR; transmission of television programmes to stations in the Orbita network..

1982 January 30 - . 11:30 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1336 - . Payload: Yantar-2K s/n 953. Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Yantar-2K. Duration: 27.00 days. Decay Date: 1982-02-26 . USAF Sat Cat: 13045 . COSPAR: 1982-008A. Apogee: 352 km (218 mi). Perigee: 170 km (100 mi). Inclination: 70.3000 deg. Period: 89.70 min. Summary: Area survey photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission..

1982 January 30 - . 16:30 GMT - . Launch Site: ETR Launch Area. Launch Platform: UK S26. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3TK.
  • Chevaline demonstration and shakedown operations launch - . Nation: UK. Agency: RN. Apogee: 1,000 km (600 mi).

1984 January 30 - . 18:02 GMT - . Launch Site: White Sands. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 98 km (60 mi).

1985 January 30 - . 19:30 GMT - . Launch Site: Andoya. LV Family: Skylark. Launch Vehicle: Skylark 12. LV Configuration: Skylark 12 DLR A-GRC-134.
  • CAESAR 2 Auroral mission - . Nation: Germany. Agency: DFVLR. Apogee: 703 km (436 mi).

1986 January 30 - . 21:05 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 79 km (49 mi).

1987 January 30 - . 09:19 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/40. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 341-01. FAILURE: Block DM-2 ignition failure, remained in LEO.. Failed Stage: 4.
  • Cosmos 1817 - . Payload: Ekran-M s/n 11L. Mass: 2,000 kg (4,400 lb). Nation: USSR. Agency: MOM. Class: Communications. Type: Military communications satellite. Spacecraft: Ekran-M . Decay Date: 1987-01-31 . USAF Sat Cat: 17365 . COSPAR: 1987-010A. Apogee: 208 km (129 mi). Perigee: 173 km (107 mi). Inclination: 51.6000 deg. Period: 88.30 min. Summary: Geosynchronous ballistic missile early warning satellite. Launch vehicle failure; left in unusable orbit. Investigation of the upper atmosphere and outer space. .

1988 January 30 - . 11:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32. Launch Pad: LC32/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Meteor 2-17 - . Payload: Meteor-2 no. 17. Mass: 2,750 kg (6,060 lb). Nation: USSR. Agency: MO. Class: Earth. Type: Weather satellite. Spacecraft: Meteor-2. USAF Sat Cat: 18820 . COSPAR: 1988-005A. Apogee: 958 km (595 mi). Perigee: 934 km (580 mi). Inclination: 82.5000 deg. Period: 104.00 min. Summary: Gathering meteorological information and data on penetrating radiation fluxes in circumterrestrial space..

1989 January 30 - . 21:14 GMT - . Launch Site: Andoya. LV Family: Black Brant. Launch Vehicle: Black Brant 10B. LV Configuration: Black Brant XB AAF-XB-02.
  • OEDIPUS A Plasma / tether mission - . Nation: Canada. Agency: CSA. Apogee: 512 km (318 mi).

1990 January 30 - . 11:20 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32. Launch Pad: LC32/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Cosmos 2058 - . Payload: Tselina-D no. 68. Mass: 2,000 kg (4,400 lb). Nation: USSR. Agency: MO. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-D. USAF Sat Cat: 20465 . COSPAR: 1990-010A. Apogee: 645 km (400 mi). Perigee: 616 km (382 mi). Inclination: 82.5000 deg. Period: 97.30 min. Summary: Investigation of outer space. .

1990 January 30 - . 21:22 GMT - . Launch Site: Wallops Island. LV Family: Super Chief. Launch Vehicle: HPB. LV Configuration: HPB GL A26.804.
  • TM2-1 test - . Nation: USA. Agency: OSC. Apogee: 422 km (262 mi).

1991 January 30 - . 15:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 71 km (44 mi).

1992 January 30 - .
1994 January 30 - . 22:00 GMT - . Launch Site: Poker Flat. LV Family: Black Brant. Launch Vehicle: Black Brant 8C. LV Configuration: Black Brant 8C NASA 27.137UE.
  • Plasma mission - . Nation: USA. Agency: NASA. Apogee: 340 km (210 mi).

1996 January 30 - . 18:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 61 km (37 mi).

1997 January 30 - . Launch Site: Point Mugu. Launch Platform: C-130. Launch Vehicle: SR19. FAILURE: Failure.
  • AltAir (Have Gold) test - . Nation: USA. Agency: USAF NAIC. Apogee: 15 km (9 mi).

1997 January 30 - . 07:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-18.
  • Lunar Penetrator test technology mission - . Nation: Japan. Agency: ISAS. Apogee: 309 km (192 mi).

1997 January 30 - . 08:42 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF26. Launch Pad: LF26?. LV Family: Minuteman. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 GT163GB.
  • FOT GT163GB Follow-on Test launch - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi).

1997 January 30 - . 22:04 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44L. LV Configuration: Ariane 44L-3 V93.
  • GE 2 - . Nation: USA. Agency: GE Americom. Manufacturer: RCA. Program: Americom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 24713 . COSPAR: 1997-002A. Apogee: 35,801 km (22,245 mi). Perigee: 35,772 km (22,227 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Geosynchronous. Stationed over 84.9W Positioned in geosynchronous orbit at 85 deg W in 1997-1999 As of 5 September 2001 located at 84.89 deg W drifting at 0.007 deg W per day. As of 2007 Mar 9 located at 85.05W drifting at 0.004W degrees per day..
  • Nahuel 1A - . Nation: Argentina. Agency: ArSat. Manufacturer: Cannes. Program: Nahuel. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 2000. USAF Sat Cat: 24714 . COSPAR: 1997-002B. Apogee: 35,798 km (22,243 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Geosynchronous. Stationed over 71.8W Positioned in geosynchronous orbit at 72 deg W in 1997-1999 As of 3 September 2001 located at 71.82 deg W drifting at 0.007 deg W per day. As of 2007 Mar 9 located at 71.83W drifting at 0.002W degrees per day..

1998 January 30 - . 17:00 GMT - . Launch Site: Rothera. LV Family: Viper. Launch Vehicle: Viper-Dart.
  • TPS13 Aeronomy mission - . Nation: UK. Agency: DLR. Apogee: 100 km (60 mi).

1999 January 30 - .
  • Mir News 451: Orbit corrections - . Nation: Russia. Program: Mir. Flight: Mir EO-26; Mir EO-26/-27. For the period between 27.01 and 2.02.99 three orbit corrections were planned. The 1st one took place on 27.01.99 at 1418 UTC and was relatively small. This correction was to check the performance of a number of systems. The impulse given by the engines of the freighter Progress-M40 lasted 97 seconds and increased the velocity with 0.35 Meters/second. The orbit was raised approx. 600 Meters. The greater correction, meanwhile executed, was scheduled for 29.01.1999 at 1337 UTC and had to increase the velocity with 1.44 Meters/second. (No exact details as yet) The 3rd and last correction of this sequence is planned for 2.02.1999 and has to add 0.85 Meters/second. Due to the planned last correction it is not yet possible to give exact predictions of Mir's (and Progress-40's) passes during the Znamya 2.5 reflector experiment.

    Znamya 2.5:

    On 3.02.1999 at about 2200 UTC (for Moscow time already 4.02) Progress-M40 will separate from Mir and remain in a distance of a couple of 100 Meters. The Mir crew will control the Progress-M40 with the TORU system and push the packages with the Znamya 2.5 sail in open space. By spinning the freighter around her X-axis the centrifugal forces will unfold and open the packages. These forces will also have to maintain the reflector sail unfolded in right angles towards sun and earth.

    Mir and Progress-M40 and possibly the light beam can be seen in Western Europa somewhere between 1700 and 2000 UTC on 4.02.1999. Due to Mir's orbit correction on 2.02.1999 it is not yet possible to calculate exact predictions the passes in which Mir/Progress-M40 are still in sunlight and we in the earth's shadow. As soon as I have the Kepler elements after the correction I will issue a small Mir-report with times and other details (azimuth and elevation) for my position. The reflector beam will cause a spot of approx. 6 KM in diameter, but this spot will move very fast: approx. 8 KM/second

    Progress-M40:

    After the 24 hours which will be used for this experiment the freighter will be put on a destruction course into the atmosphere and burn up over a designated area in the Pacific Ocean East of New-Zealand.

    Mir-routine:

    Daily between 0500-2000 UTC the cosmonauts executed the prescribed programmes. This was not very exciting, but also not boring. They paid attention to a number of well known experiments such as: the French Fiziolab (medical), Ionozond (sensing the ionosphere in the benefit of the ionospheric stations in Narafominsk and Rostov), the Greenhouse, Portapress (blood circulation), Relaksatsiya (the study of the influence on molecules of products of combustion for which now and then small impulses of the engines were needed), Silay (the study of small particles from outer space resulting in minor flashes in the eyes of the cosmonauts), etc.

    Apart from these and their experiments they had to do maintenance work, for instance the replacement of a ventilator of the Gas Analyser, mending the system for the transfer of urine, the installation and dismounting of experimental equipment and the separation of water in one of the Elektron oxygen generators. Regularly the crew reported the pressure in Mir's atmosphere: always approx. 705 MM mercury.

    They also now and then checked the pressure in the Spektr module. Another regular reported measurement was the radiation level on board. This was always done by Avdeyev who used the Doza system. The values (doses) were given in ug-s and the velocities in mg-s per hour.

    Communications:

    Now and then the geostationary satellite Luch-1/Gelios was in use for instance for TV-transmissions, but also for a TV-link in which high speed data transfer took place. On 25.01.99 TsUP told the crew that the DLR was very pleased with the data of the Titus experiments transmitted by Mir and directly received by DLR. The Mir crew promised to transmit more. (Unclear whether the Germans received these signals via the 166, 165, 636 or 638 mc/s telemetry channels or via the Luch-1/Gelios. Theoretically GSOC in Oberpfaffenhofen must be able to 'see' Luch-1)

    Avdeyev often used the amateur radio frequency 145.985 mc/s for several modes: Packet Radio, Phone and SSTV images. Now and then Avdeyev, using call sign R0Mir, transmitted for phone on a somewhat lower frequency around 145.970 mc/s. He made his calls in Russian as well in English.

    Preparations Znamya 2.5:

    A lot activities in this field during the last days. For instance just before drafting this report TsUP spoke with the crew about the observations during the undocking and the deployment of the Znamya 2.5 sail. Padalka will control the TORU from the base block and Avdeyev will execute observations and make images with through a porthole (nr. 5 in Module-D or the porthole in the PSO).

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


2000 January 30 - . 10:25 GMT - . Launch Site: Poker Flat. LV Family: Hawk. Launch Vehicle: Orion Sounding Rocket. LV Configuration: Orion NASA 30.044UP.
  • Student SRP-3 Education mission - . Nation: USA. Agency: NASA. Apogee: 79 km (49 mi).

2001 January 30 - . 07:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Delta. Launch Vehicle: Delta 7925-9.5. LV Configuration: Delta 7925-9.5 D283.
  • USA 156 - . Payload: GPS 2R-7 / GPS SVN 54. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft: GPS Block 2R. USAF Sat Cat: 26690 . COSPAR: 2001-004A. Apogee: 20,208 km (12,556 mi). Perigee: 20,157 km (12,524 mi). Inclination: 55.2000 deg. Period: 718.00 min. Summary: GPS Block IIR production no. SV 14. Placed in Plane E Slot 4 of the constellation..

2002 January 30 - .
  • EUVE Spacecraft Reenter's Earth Atmosphere - . Nation: USA.

2002 January 30 - .
2003 January 30 - . 13:00 GMT - . Launch Site: Kiruna. LV Family: Loki. Launch Vehicle: Super Loki.
  • MM-LFS- Aeronomy mission - . Nation: Germany. Agency: NASA. Apogee: 117 km (72 mi).

2007 January 30 - . 23:22 GMT - . Launch Site: Kiritimati. Launch Pad: 0.0 N x 154.0 W. Launch Platform: ODYSSEY. LV Family: Zenit. Launch Vehicle: Zenit-3SL. LV Configuration: Zenit-3SL 24SL. FAILURE: First stage exploded just after ignition, damaging launch platform.. Failed Stage: 1.
  • NSS 8 - . Mass: 6,100 kg (13,400 lb). Nation: Netherlands. Agency: New Skies. Manufacturer: El Segundo. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 702. COSPAR: F20070130. The platform was designed to survive such an explosion, but the flame deflector was blown off and the blast doors unhinged. The launch platform was towed back to Long Beach for repairs. The time required to repair the platform and the investigation to determine and fix the cause would certainly impact the 2007 Zenit-3SL and Zenit-2 launch schedules, probably forcing customers to be diverted to other boosters. NSS-8 was to have been placed at a 57 East orbital position to satisfy demand in the Indian Ocean region with 56 C-band and 36 Ku-band transponders. NSS-703, with an expected end-of-life in 2009, would have to continue in service until a replacement was built and launched.

2008 January 30 - . 09:56 GMT - .
  • EVA ISS EO-16-5 - . Crew: Whitson; Tani. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.30 days. Nation: USA. Related Persons: Whitson; Tani. Program: ISS. Flight: ISS EO-16. Summary: The astronauts replaced a motor on the starboard truss beta gimbal and carried out further inspections of the failed solar array alpha rotary joint..

2009 January 30 - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/2. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Koronas-Foton - . Payload: AUOS-SM-KF. Mass: 1,900 kg (4,100 lb). Nation: Russia. Agency: RAKA. Manufacturer: Yuzhnoye. Class: Astronomy. Type: Solar astronomy satellite. Spacecraft: AUOS. USAF Sat Cat: 33504 . COSPAR: 2009-003A. Apogee: 561 km (348 mi). Perigee: 539 km (334 mi). Inclination: 82.5000 deg. Period: 95.70 min. Carried ten instruments to study in the sun throughout the electromagnetic spectrum, primarily Russian: Natalya-2M spectrometer; RT-2 gamma-telescope (India); Pingvin-M polarimeter; Konus-RF x-ray and gamma spectrometer; BRM x-ray detector; FOKA UV-detector; TESIS telescope/spectrometer with SphinX soft X-ray spectrophotometer (Poland); Electron-M-Peska charged particles analyser; STEP-F Electron and proton detector(Ukraine); SM-8M magnetometer. Follow-up to 2001 Koronas-F launch.

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