Encyclopedia Astronautica
February 04


February 04 Chronology


1902 February 4 - .
  • Birth of Charles A Lindbergh - . Nation: USA. Summary: American pioneering aviator, first pilot to fly solo across the Atlantic in 1927. Appointed to senior government committees on aerospace development. Worked with Guggenheim to support Goddard's rocket development in Roswell in 1930s..

1925 February 4 - .
  • Birth of Vladimir Lavrentyevich Lapygin - . Nation: Russia. Summary: Russian engineer. Deputy Chief Designer, then Chief Designer of Pilyugin design bureau. Specialised in guidance and succeeded Pilyugin 1982..

1944 February 4 - . Launch Site: Peenemuende. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 V-106.
1945 February 4 - . Launch Site: Peenemuende. Launch Complex: Peenemuende P7. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 V-274.
1948 February 4 - . Launch Site: Edwards.
  • D-558-II first flight. - . Crew: Martin. Nation: USA. Related Persons: Martin. Summary: First flight of reseach airplane Douglas D-558-II (No. 1), John Martin of Douglas as pilot. Airplane had both jet and rocket engines and was flown from ground takeoff..

1949 February 4 - . Launch Vehicle: Eole.
  • Eole engine bench tests begin - . Nation: France. Related Persons: Barre. Summary: The engine runs for 13.5 seconds, 4.5 seconds early, due to heavier-than-expected liquid oxygen consumption..

1954 February 4 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LA. Launch Pad: LA?. LV Family: Matador. Launch Vehicle: Matador. LV Configuration: Matador GM-12425.
  • Test mission - . Nation: USA. Agency: USAF. Apogee: 12 km (7 mi).

1955 February 4 - . 21:55 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC33. Launch Pad: NLA. LV Family: Viking. Launch Vehicle: Viking Type 9. LV Configuration: Viking Type 9 12.
  • Viking 12 re-entry vehicle test flight - . Nation: USA. Agency: USN. Apogee: 231 km (143 mi). Summary: Re-entry nose-cone heat transfer experiment; photography; atmosphere research. Launched at 1455 local time. Reached 232 km..

1958 February 4 - . 06:17 GMT - . Launch Site: Fort Churchill. LV Family: Aerobee. Launch Vehicle: Aerobee Hi. LV Configuration: Aerobee Hi NN3.11F.
  • NRL NN3.11F Ionosphere mission - . Nation: USA. Agency: NRL. Apogee: 234 km (145 mi).

1959 February 4 - . 08:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC11. LV Family: Atlas. Launch Vehicle: Atlas B. LV Configuration: Atlas B 11B.
  • Research and development / AFSWC-4? test - . Nation: USA. Agency: USAF. Apogee: 990 km (610 mi). Summary: Last Atlas B flight, fully successful.

1960 February 4 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LC-B. LV Family: Viper. Launch Vehicle: Nike Viper I.
  • Aeronomy mission - . Nation: USA. Agency: AEC. Apogee: 80 km (49 mi).

1960 February 4 - . 18:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Delta. Launch Vehicle: Thor Agena A. LV Configuration: Thor Agena A 218 / Agena A 1052. FAILURE: Failure. Failed Stage: U.
  • Discoverer 9 - . Payload: KH-1 9006. Mass: 765 kg (1,686 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-1. Decay Date: 1960-02-04 . COSPAR: F600204A. Summary: KH-1; 1st generation low resolution photo surveillance. Mission failed..
  • SRV 113 - . Nation: USA. Agency: USAF. Spacecraft: KH-1. COSPAR: F600204B.

1960 February 4 - . 22:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC29A. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1X-12.
  • Test mission - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1961 February 4 - .
  • Death of Gennady Mikhailov. Reported killed in an orbital flight on 4 February 1961. - . Nation: Russia. Related Persons: Mikhailov. Summary: Russian phantom cosmonaut, said to have died 1962.01.24, reported by Cordiglia brothers in 1962 and later Edwards book. Based on 1959 photo of high altitude equipment tester..

1961 February 4 - . 01:18 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Molniya 8K78. LV Configuration: Molniya 8K78 L1-7. FAILURE: At T+531 sec, the fourth vernier chamber of Stage 3's 8D715K engine exploded because the LOX cut-off valve had not closed as scheduled and LOX flowed into the hot chamber.. Failed Stage: 3.
  • Sputnik 7 - . Payload: 2MV-2 s/n 1. Mass: 6,483 kg (14,292 lb). Nation: USSR. Related Persons: Korolev; Glushko. Agency: RVSN. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft: Venera 1VA. Decay Date: 1961-02-26 . USAF Sat Cat: 71 . COSPAR: 1961-Beta-1. Apogee: 318 km (197 mi). Perigee: 212 km (131 mi). Inclination: 64.9000 deg. Period: 89.80 min. The escape stage entered parking orbit but the main engine cut off just 0.8 s after ignition due to cavitation in the oxidiser pump and pump failure.. The payload attached together with escape stage remained in Earth orbit.

    The booster launched into a beautiful clear sky, and it could be followed by the naked eye for four minutes after launch. The third stage reached earth parking orbit, but the fourth stage didn't ignite. It was at first believed a radio antenna did not deploy from the interior of the stage, and it did not receive the ignition commands. Therefore the Soviet Union has successfully orbited a record eight-tonne 'Big Zero' into orbit. The State Commission meets two hours after the launch, and argues whether to make the launch public or not, and how to announce it. Glushko proposes the following language for a public announcement: 'with the objective of developing larger spacecraft, a payload was successfully orbited which provided on the first revolution the necessary telemetry'. Korolev and the others want to minimize any statement, to prevent speculation that it was a reconnaissance satellite or a failed manned launch. Kamanin's conclusion - the rocket didn't reach Venus, but it did demonstrated a new rocket that could deliver an 8 tonne thermonuclear warhead anywhere on the planet. The commission heads back to Moscow.


1963 February 4 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 599. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P-109.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1963 February 4 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 599. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P-108.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1964 February 4 - . 01:05 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 5C. LV Configuration: Skylark-5C SL88.
  • Aeronomy mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 118 km (73 mi).

1964 February 4 - . 01:35 GMT - . Launch Site: Ascension. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.22UA.
  • UM Pitot 4 Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 158 km (98 mi).

1964 February 4 - . 01:46 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.62GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 116 km (72 mi).

1965 February 4 - . 04:45 GMT - . Launch Site: Point Barrow. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.125GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 121 km (75 mi).

1965 February 4 - . 05:10 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.119GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 118 km (73 mi).

1966 February 4 - . 01:54 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.143UA.
  • Spheres (UM) Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 152 km (94 mi).

1966 February 4 - . 23:19 GMT - . Launch Site: Andoya. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure CE-16.
  • ESRO C15 / 1 Aurora mission - . Nation: Europe. Agency: ESRO. Apogee: 120 km (70 mi).

1967 February 4 - . LV Family: Proton. Launch Vehicle: Proton-K/D.
  • UR-500K/L1 manned circumlunar design authorised. - . Nation: USSR. Spacecraft: Soyuz 7K-L1. Summary: Central Committee of the Communist Party and Council of Soviet Ministers Decree 115-46 'On the Progress of the Work on the Development of the UR500K-L1 --confirmation of schedule for piloted lunar missions' was issued..

1967 February 4 - . LV Family: N1. Launch Vehicle: N1.
  • L1/L3 launch schedules set - . Nation: USSR. Program: Lunar L1; Lunar L3. Spacecraft: Soyuz 7K-L1; Soyuz 7K-LOK. The following is the schedule set be decree for the L1 and L3 projects:
    Serial # Mission               Date
    2P       Develop Block D stage Feb or Mar 67
    3P       same                  Mar 67
    4L       Unmanned lunar flyby  May 67
    5L       Unmanned lunar flyby  Jun 67
    6L       Manned lunar flyby    Jun or Jul 67
    7L&8L    Manned lunar flybys   Aug 67
    9L&10L   Manned lunar flybys   Sep 67
    11L&12L  Manned lunar flybys   Oct 67
    13L      Reserve spacecraft
     
    N1-3L
    Serial # Mission                  Date
    3L       Develop LV & Blocks G&D  Sep 67
    4L       Reserve
    5L       LOK/LK unmanned          Dec 67
    6L       LOK/LK unmanned          Feb 68
    7L       Manned LOK/unmanned LK   Apr 68
    8L       Manned LOK/unmanned LK   Jun 68
    9L       Piloted LOK/unmanned LK 
             with LK landing on moon  Aug 68
    10L      First men land on moon   Sep 68
    11L      Reserve
    12L      Reserve
    
    Kamanin's personal opinion of this schedule - manned L1 flights may occur before the end of 1967, but there will be no lunar landing until 1969.

1967 February 4 - . 05:21 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 2. LV Configuration: Black Brant II AA-2-101.
  • Recovery test / Ionosphere Aurora / ionosphere / meteorology mission - . Nation: Canada. Agency: NRCC. Apogee: 183 km (113 mi).

1967 February 4 - . 23:53 GMT - . Launch Site: Kiruna. Launch Complex: Kiruna C. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure CE-22.
  • ESRO C21 / 2 Aurora / chemical release mission - . Nation: Europe. Agency: ESRO. Apogee: 126 km (78 mi).

1968 February 4 - . 05:33 GMT - . Launch Site: Kiruna. Launch Complex: Kiruna C. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure CE-35.
  • ESRO C36 / 2 Aeronomy mission - . Nation: Europe. Agency: ESRO. Apogee: 146 km (90 mi).

1969 February 4 - . LV Family: Proton. Launch Vehicle: Proton-K/D.
  • UR-500K failure state commission - . Nation: USSR. Related Persons: Konopatov; Babakin. Program: Luna. Spacecraft: Luna Ye-8. At Area 81 a State Commission is held on failures of the UR-500K booster. A D Konopatov describes the analysis of the stage 2 and 3 failures on the 20 January launch attempt. The number 4 engine of stage 2 shut down 25 seconds into its burn due to high temperatures detected in the turbopump. The same thing occurred on the third stage. The couldn't pin down the source of the problem. Engines of this type had worked correctly 700 times on earlier flights. Despite the cause of the failure not being identified, approval is given at 14:30 for the launch of the Ye-8 to proceed. Babakin confirms the spacecraft is ready.

1969 February 4 - . 14:35 GMT - . Launch Site: Fort Churchill. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.272UA.
  • Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 186 km (115 mi).

1970 February 4 - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-4.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1970 February 4 - . 02:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Delta. Launch Vehicle: Thorad Agena D SLV-2G. LV Configuration: Thorad SLV-2G Agena D 534 (TA12) / Agena D.
  • SERT 2 - . Mass: 1,404 kg (3,095 lb). Nation: USA. Agency: NASA Cleveland. Class: Technology. Type: Ion engine technology satellite. Spacecraft: SERT. USAF Sat Cat: 4327 . COSPAR: 1970-009A. Apogee: 1,046 km (649 mi). Perigee: 1,039 km (645 mi). Inclination: 99.2000 deg. Period: 106.00 min. Space Electric Rocket Test; the ion engines aboard were operated until 1981. The SERT 2 development program started in 1966 and included thruster ground tests of 6742 hours and 5169 hours duration. A prototype version of the SERT 2 spacecraft was ground-tested for a period of 2400 hours with an operating ion engine. In addition to diagnostic equipment and related ion engine hardware, the spacecraft had two identical 15 cm diameter, mercury ion engines. Flight objectives included in-space operation for a period of 6 months, measurement of thrust, and demonstration of electromagnetic compatibility. The thruster maximum power level was 0.85 kW, and this provided operation at a 28 mN thrust level at 4200 s specific impulse. Flight data were obtained from 1970 to 1981 with an ion engine operating intermittently in one of three different modes, namely, HV ion extraction, discharge chamber operation only, or just neutralizer operation. Major results were that two mercury engines thrusted for periods of 3781 hours and 2011 hours. Test duration was limited due to shorts in the ion optical system. Thrust measured in space and on the ground agreed within the measurement uncertainties. Up to 300 thruster restarts were demonstrated. One power-processing unit accumulated nearly 17,900 hours during the course of the mission. Additionally, the ion propulsion system was electromagnetically compatible with all other spacecraft systems.

1970 February 4 - . 04:41 GMT - . Launch Site: Fort Churchill. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.441UI.
  • Aurora / ionosphere mission Aurora / ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 141 km (87 mi).

1970 February 4 - . 05:26 GMT - . Launch Site: Kiruna. Launch Complex: Kiruna C. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure C57/1.
  • ESRO C57 / 1 Aeronomy mission - . Nation: Europe. Agency: ESRO. Apogee: 172 km (106 mi).

1970 February 4 - . 06:19 GMT - . Launch Site: Fort Churchill. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk NASA 18.100UA.
  • Aurora / aeronomy / chemica mission - . Nation: USA. Agency: NASA. Apogee: 310 km (190 mi).

1970 February 4 - . 20:38 GMT - . Launch Site: ETR Launch Area. Launch Platform: EAG-154. Launch Vehicle: Poseidon. LV Configuration: Poseidon C3XT-20.
  • Test mission - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1971 February 4 - .
  • Second Svinets test successful. - . Nation: USSR. Program: Salyut. Spacecraft: Salyut 1. Summary: The DOS crews return from Tyuratam. The second missile launch was observed successfully by the Svinets apparatus as well. Cosmonaut teams are assigned to public relations tours of Egypt, USA, Italy, Viet Nam, and Hungary..

1971 February 4 - .
  • X-24 Flight 22 - . Crew: Powell. Payload: X-24A flight 22. Nation: USA. Related Persons: Powell. Class: Manned. Type: Manned spaceplane. Spacecraft: X-24A. Summary: Powell's check flight, glide. Maximum Speed - 700 kph. Maximum Altitude - 13716 m. Flight Time - 235 sec..

1971 February 4 - . 22:45 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 632. Launch Vehicle: Poseidon. LV Configuration: Poseidon C3E-19.
  • Demonstration and shakedown operations launch - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1972 February 4 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF05. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • OT GT12GM operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1972 February 4 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 598. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3T.
  • Demonstration and shakedown operations launch - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1973 February 4 - . 19:00 GMT - . Launch Site: Koroni. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 90 km (55 mi).

1974 February 4 - . Launch Site: Baikonur. Launch Complex: Baikonur LC177. LV Family: MR-UR-100. Launch Vehicle: MR-UR-100.
  • State trials missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 February 4 - . 14:40 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 6 AC. LV Configuration: Skylark 6 AC SL1203.
  • XRB / extreme ultraviolet survey X-ray / extreme ultraviolet astronomy mission - . Nation: UK. Agency: BAC. Apogee: 197 km (122 mi).

1975 February 4 - .
  • Death of Anatoli Arkadyevich Blagonravov - . Nation: Russia. Related Persons: Blagonravov. Summary: Russian scientist. President, Academy Artillery Sciences 1946-1950, leading development of first Soviet sounding rockets. Soviet representative to UN COPUOS and negotiator with NASA on cooperative space projects in early 1960's..

1975 February 4 - . Launch Site: Wallops Island. Launch Platform: F-4. LV Family: Recruit. Launch Vehicle: Pedro Recruit. LV Configuration: Pedro Recruit FLAME 1.
  • FLAME test - . Nation: USA. Agency: USAF. Apogee: 17 km (10 mi).

1975 February 4 - . Launch Site: Baikonur. Launch Complex: Baikonur LC140/18. LV Family: R-36M. Launch Vehicle: R-36M.
  • Joint flight trials launch - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 February 4 - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-3. FAILURE: Stage 2 thrust vector control failure.. Failed Stage: 2.
  • Corsa A - . Mass: 92 kg (202 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Corsa A. Decay Date: 1976-02-04 . COSPAR: F760204A.

1977 February 4 - . 10:00 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 86 km (53 mi).

1978 February 4 - . 07:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3H. LV Configuration: Mu-3H M-3H-2.
  • SS-05 Kyokko - . Payload: Exos A. Mass: 103 kg (227 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Ionosphere satellite. Spacecraft: EXOS. USAF Sat Cat: 10664 . COSPAR: 1978-014A. Apogee: 3,952 km (2,455 mi). Perigee: 639 km (397 mi). Inclination: 65.4000 deg. Period: 134.00 min. Auroral studies. Active life - two years. Function: 1) Observation of wide angle global auroral pictures using UV television camera. 2) Spectrophotometry of ultraviolet air glow. 3) Observation of the energy spectrum of photoelectrons and auroral electrons. 4) Mass spect rometry of the ionized atmospheric species in the thermosphere. 5) Measurements of density and temperature of ambient electrons in the thermosphere. 6) Observation of electromagnetic and plasma waves and the emission associated with auroral phenomena.

1979 February 4 - . 20:00 GMT - . Launch Site: Koroni. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 83 km (51 mi).

1980 February 4 - . 02:42 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 654. Launch Vehicle: Poseidon.
  • FOT-39? Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1981 February 4 - . 01:10 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC36. Launch Vehicle: Aries. LV Configuration: Aries GL A24.7S1-01.
  • IRBS (BMP) ABM infrared sensor limb characterization technology mission - . Nation: USA. Agency: USAF GL. Apogee: 387 km (240 mi).

1982 February 4 - . 20:05 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 85 km (52 mi).

1983 February 4 - . 08:37 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-10(F).
  • Sakura 2A - . Payload: CS-2A. Mass: 772 kg (1,701 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-2. Completed Operations Date: 1990-12-04 . USAF Sat Cat: 13782 . COSPAR: 1983-006A. Apogee: 36,070 km (22,410 mi). Perigee: 35,994 km (22,365 mi). Inclination: 10.6000 deg. Period: 1,448.70 min. Business communications. Launch time 0837 GMT. Launching organization NASDA (National Space Development Agency of Japan). N launch vehicle No. 10(F) (N-II launch vehicle). Osaki launch site, NASDA Tanegashima Space Center, Kagoshima, Japan. Geostationary position 132 deg E. Estab lishment of domestic satellite telecommunications network mainly for natural disaster, emergency and for remote islands using submillimetre wavelength and microwavelength signals. Development of the technology of communications satellite. Positioned in geosynchronous orbit at 132 deg E in 1983-1988; 128 deg E in 1988-1990 As of 30 August 2001 located at 140.81 deg E drifting at 3.111 deg W per day. As of 2007 Mar 10 located at 31.02W drifting at 3.113W degrees per day.

1986 February 4 - . 11:15 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1730 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Earth. Type: Earth resources satellite. Spacecraft: Zenit-8. Duration: 9.00 days. Decay Date: 1986-02-13 . USAF Sat Cat: 16540 . COSPAR: 1986-012A. Apogee: 303 km (188 mi). Perigee: 191 km (118 mi). Inclination: 72.9000 deg. Period: 89.50 min. Summary: Military cartographic satellite; returned film capsule..

1987 February 4 - . 09:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF26. Launch Pad: LF26?. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT120GB Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1989 February 4 - . 03:03 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 643. LV Family: Trident. Launch Vehicle: Trident C-4.
  • DASO-32 technology mission / demonstration and shakedown operations launch - . Nation: USA. Agency: SDIO. Apogee: 1,000 km (600 mi).

1990 February 4 - . 12:28 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-6 (21).
  • Zhongxing-3 - . Payload: STTW 4. Mass: 1,024 kg (2,257 lb). Nation: China. Agency: Chinasat. Class: Communications. Type: Military communications satellite. Spacecraft: DFH-2. Completed Operations Date: 1998-07-01 . USAF Sat Cat: 20473 . COSPAR: 1990-011A. Apogee: 35,795 km (22,241 mi). Perigee: 35,783 km (22,234 mi). Inclination: 0.0000 deg. Period: 1,436.30 min. National operational communications satellite. Designation 1990-2. Operated in geosynchronous orbit at 98 deg E in 1990-1998. As of 4 September 2001 located at 52.36 deg E drifting at 0.045 deg W per day. As of 2007 Mar 10 located at 96.88E drifting at 0.061W degrees per day.

1992 February 4 - .
  • Death of Paver Vladimirovich Tsybin - . Nation: Russia. Related Persons: Tsybin. Summary: Russian Chief Designer OKB-256 1945-1959. Designs: LL rocketplanes, RS Mach 3 ramjet aircraft, PKA spaceplane. Bureau closed, worked for Korolev on Vostok, Soyuz, AMS and Molniya satellites. Deputy Designer of Buran space shuttle, 1974-1992..

1994 February 4 - . Launch Site: Vandenberg.
  • Initial demonstration flight of the Astrid - . Nation: USA. Summary: Initial demonstration flight of the Astrid (Advanced Single Stage Rapid Insertion) interceptor vehicle..

1994 February 4 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF08. Launch Pad: LF08/Rail. Launch Vehicle: Astrid.
  • Pumped Propulsion test - . Nation: USA. Agency: Livermore. Apogee: 2.00 km (1.20 mi).

1998 February 4 - . 23:29 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44LP. LV Configuration: Ariane 44LP-3 V105.
  • Brasilsat B3 - . Nation: Brazil. Agency: Embratel. Manufacturer: El Segundo. Program: Brasilsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376W. USAF Sat Cat: 25152 . COSPAR: 1998-006A. Apogee: 35,795 km (22,241 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Geostationary at 84.0 degrees W. Positioned in geosynchronous orbit at 84 deg W in 1998-1999 As of 3 September 2001 located at 84.03 deg W drifting at 0.009 deg W per day. As of 2007 Mar 9 located at 84.07W drifting at 0.013W degrees per day..
  • Inmarsat 3 F5 - . Mass: 1,021 kg (2,250 lb). Nation: International. Agency: Inmarsat. Manufacturer: RCA. Program: Inmarsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 4000. USAF Sat Cat: 25153 . COSPAR: 1998-006B. Apogee: 35,797 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.5000 deg. Period: 1,436.10 min. Summary: Geostationary at 25.0 degrees E. Positioned in geosynchronous orbit at 25 deg E in 1998-1999 As of 24 July 2001 located at 25.09 deg E drifting at 0.020 deg E per day. As of 2007 Mar 10 located at 25.07E drifting at 0.017W degrees per day..

2002 February 4 - .
  • ISS goes out of control. - . Nation: USA. Program: ISS. Flight: ISS EO-4. The International Space Station lost attitude control on for several hours. After Zvezda computers developed communications problems and failed to transfer data to the US gyros on the Z1 module, the GNC MDM computer on the US side stopped stabilizing the station. The computer problems also prevented Z1 from handing over control to the backup thruster system on Zvezda.. At 1318 UTC the Station tumbled, in danger of losing electrical power, and experiments were shut down as systems were put in emergency mode. The crew were able to manually point the US solar arrays, preventing any loss of power. The station was restored to operation later in the day, with attitude control resuming at 1843 UTC on thrusters and 1920 UTC on gyros.

2002 February 4 - . 02:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-2F.
  • MDS-1 - . Mass: 304 kg (670 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: MDS. USAF Sat Cat: 27367 . COSPAR: 2002-003A. Apogee: 35,753 km (22,215 mi). Perigee: 373 km (231 mi). Inclination: 28.3000 deg. Period: 633.80 min. Technology qualification flight - maiden flight of H-2A booster. Launch delayed from January 31 and February 3. The second stage began its first burn at 0251 UTC and at 0257 UTC entered a 500 km circular parking orbit. After a 12 minute coast the second burn put stage 2 in geostationary transfer orbit. At 0315 UTC the small DASH vehicle was meant to separate from the upper adapter, but this apparently did not occur. At 0325 UTC VEP-3/upper adapter/DASH combination separated from the second stage, followed by two semi-cylindrical side panels, revealing the previously enclosed MDS-1 technology satellite which was ejected at 0331 UTC. At 0425 UTC the second stage was scheduled to make a third burn to test engine restart, completing the H-2A-2F mission.
  • DASH - . Mass: 70 kg (154 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: DASH 2002. USAF Sat Cat: 27368 . COSPAR: 2002-003B. Apogee: 35,778 km (22,231 mi). Perigee: 357 km (221 mi). Inclination: 28.3000 deg. Period: 634.00 min. The VEP-3 launch instrumentation package mounted on top of the DASH had a mass of 33 kg. The side adapter panels were halves of a 4.1m long 4.0m diameter cylinder. DASH (Demonstrator of Atmospheric Reentry System and Hypervelocity) was to test the reentry system for the MUSES-C asteroid probe. The plan was to fire the deorbit motor three days after launch, then separate the reentry capsule which would enter the Earth's atmosphere at 10 km/s and land in the Hodh el Gharbi region of Mauritania at about 8.5W 17.2N. Typical satellite reentries are at only 7.5 km/s, while hyperbolic (escape) velocity at the top of the atmosphere is over 11 km/s, so DASH would have been travelling much faster than typical reentry vehicles, but not quite at escape velocity.

2003 February 4 - .
  • Memorial Service For The Columbia Astronauts - . Nation: USA.

2004 February 4 - .
  • Ulysses Closest Approach To Jupiter (0.8 AU) - . Nation: Germany. Spacecraft: Ulysses.

2005 February 4 - .
2007 February 4 - .
  • International Space Station Status Report #07-07 - . Nation: USA. Related Persons: Williams; Lopez-Alegria. Program: ISS. Flight: ISS EO-14; ISS EO-15-1. Summary: For the second time in four days, two residents of the International Space Station stepped outside for a spacewalk to complete connecting cooling loops from a temporary to a permanent system. This time the excursion lasted just over seven hours.. Additional Details: International Space Station Status Report #07-07.

2008 February 4 - . LV Family: Shahab. Launch Vehicle: Safir-2.
  • Iran tests satellite launcher. - . Nation: Iran. Agency: IRSA. Summary: Iran's president tours new space launch facilities and a rocket is launched, said by some to be a test version of the Shahab satellite vehicle without operative upper stages..

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