Encyclopedia Astronautica
February 07


February 07 Chronology


1907 February 7 - .
1907 February 7 - .
1926 February 7 - .
1932 February 7 - .
1939 February 7 - .
  • Best test of new Goddard liquid propellant pumps. - . Nation: USA. Related Persons: Goddard. Engine used 29 lb liquid oxygen; 45 lb gasoline; produced 671 lb of lift for 12 sec, with jet velocity of 4820 ft/sec; oxygen 2.15 lb/sec; gasoline, 2.28 lb/sec; mixture ratio 0.94. Over 24 pump tests were completed by the time of the last run on February 28.

1945 February 7 - . Launch Site: Peenemuende. LV Family: V-2. Launch Vehicle: V-2.
  • Submarine-launched A4 abandoned. - . Nation: Germany. Summary: Evacuation of Peenemuende brought work on the submarine-towed version to an end..

1945 February 7 - .
  • Death of Petr Ivanovich Fedorov - . Nation: Russia. Related Persons: Fedorov. Summary: Russian officer. First Director of NII-l 1944-1945. Oversaw the early search for the A-4..

1947 February 7 - .
  • XS-1 Flight 24 - . Crew: Goodlin. Payload: XS-1 # 2 flight 14. Nation: USA. Related Persons: Goodlin. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: Bell flight 14. Buffet boundary investigation..

1952 February 7 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 79R.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1955 February 7 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-1. Launch Vehicle: R-1 8A11. LV Configuration: R-1 8A11 No 1020.
  • Operational test - . Nation: USSR. Agency: Korolev. Apogee: 100 km (60 mi).

1955 February 7 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-5. Launch Vehicle: R-5.
  • Phase 3 state trials launch - . Nation: USSR. Agency: Korolev. Apogee: 300 km (180 mi).

1955 February 7 - . 18:51 GMT - . Launch Site: Holloman. Launch Complex: Holloman A. LV Family: Aerobee. Launch Vehicle: Aerobee RTV-A-1a. LV Configuration: Aerobee RTV-A-1a USAF 52.
  • AF / Utah D-layer Ionosphere mission - . Nation: USA. Agency: USAF AFSC. Apogee: 120 km (70 mi). Summary: Ionosphere research. Launched at 1151 local time. Reached 120.4 km..

1956 February 7 - . Launch Site: Point Mugu. LV Family: Loki. Launch Vehicle: Loki Dart. LV Configuration: Loki Dart WASP 1.
  • Test mission - . Nation: USA. Agency: USN ONR. Apogee: 75 km (46 mi).

1957 February 7 - . Launch Site: Wallops Island. Launch Vehicle: RM-10.
  • First RM-10 2 stage test. - . Nation: USA. Summary: First of a series of two-stage test vehicles (RM-10) to make heat transfer studies at high speed in free flight, was launched from NACA's Pilotless Aircraft Reserach Station at Wallops Island, Va. Vehicle was developed by PARD of Langley Laboratory..

1957 February 7 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC3. LV Family: X-17. Launch Vehicle: X-17. LV Configuration: X-17 R-21 4203-21.
  • Re-entry vehicle test - . Nation: USA. Agency: USAF. Apogee: 107 km (66 mi).

1958 February 7 - .
  • Advanced Research Projects Agency (ARPA) created - . Nation: USA. Related Persons: Johnson, Roy. To further the national space effort pending a decision as to permanent organization, the Secretary of Defense created the Advanced Research Projects Agency (ARPA), an organization under consideration since November 15, 1957.. ARPA was authorized to direct or perform advanced projects in the field of research and development. It was also empowered to deal directly with operational elements on all aspects of ARPA projects; for example, to bypass the Army Staff and the Chief of Ordnance in dealing with the Army Ballistic Missile Agency on what was to be the Saturn project. Roy W. Johnson was named ARPA Director. ARPA was to be a centralized group capable of handling direction of both outer space and antimissile-missile projects, whose duties in the space field were to bridge the gap until Congress could consider legislative proposals for the establishment of a National Space Agency.

1958 February 7 - . 19:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas A. LV Configuration: Atlas A 13A. FAILURE: Failure. Failed Stage: 1.
  • Research and development launch - . Nation: USA. Agency: USAF. Apogee: 120 km (70 mi).

1959 February 7 - .
  • Medical tests for the Mercury astronaut selection started. - . Nation: USA. Program: Mercury. Summary: At the Lovelace Clinic, Albuquerque, New Mexico, the medical tests for the Mercury astronaut selection were started..

1960 February 7 - .
  • Death of Igor Vasilyevich Kurchatov - . Nation: Russia. Related Persons: Kurchatov. Summary: Russian scientist. Father of Soviet atomic bomb at KB-11. Managed development of first hydrogen bomb. Design coordinated with Korolev's design bureau for use on R-7 ICBM..

1960 February 7 - . 11:03 GMT - . Launch Site: Pacific Ocean. Launch Pad: 11.6 N x 151.7 E. Launch Platform: VOKV. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Agency: GMS. Apogee: 44 km (27 mi).

1961 February 7 - . LV Family: Nova. Launch Vehicle: Saturn C-2.
  • Final report of the Low Committee - . Nation: USA. Related Persons: Seamans. Program: Apollo. Spacecraft: Apollo Lunar Landing. The Manned Lunar Landing Task Group (Low Committee) transmitted its final report to NASA Associate Administrator Robert C. Seamans, Jr. The Group found that the manned lunar landing mission could be accomplished during the decade, using either the earth orbit rendezvous or direct ascent technique. Multiple launchings of Saturn C-2 launch vehicles would be necessary in the earth orbital mode, while the direct ascent technique would require the development of a Nova-class vehicle. Information to be obtained through supporting unmanned lunar exploration programs, such as Ranger and Surveyor, was felt to be essential in carrying out the manned lunar mission. Total funding for the program was estimated at just under $7 billion through Fiscal Year 1968.

1961 February 7 - . LV Family: Atlas. Launch Vehicle: Atlas Centaur LV-3C.
  • Centaur development milestones set. - . Nation: USA. Summary: Meeting of NASA and contractor personnel held at NASA headquarters to review Centaur development program..

1961 February 7 - . 12:46 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA5A. LV Family: Black Knight. Launch Vehicle: Black Knight 201. LV Configuration: Black Knight-201 BK.13.
  • Gaslight Re-entry Vehicle test - . Nation: UK. Agency: RAE. Apogee: 687 km (426 mi).

1961 February 7 - . 20:56 GMT - . Launch Site: Silver Lake DZ. Launch Pad: 35.3 N x 116.1 W. Launch Platform: NB-52 008. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 1-21-36.
  • X-15A Stab./Control test - . Nation: USA. Agency: NASA; USAF. Apogee: 23 km (14 mi). Summary: Maximum Speed - 3660 kph. Maximum Altitude - 23820 m. Last XLR-11 flight..

1962 February 7 - .
  • Kennedy comments on moon program - . Nation: USA. Related Persons: Kennedy. Program: Apollo. At his regular press conference, President John F. Kennedy was asked for his "evaluation of our progress in space at this time" and whether the United States had changed its "timetable for landing a man on the moon." He replied: "As I said from the beginning, we have been behind . . . and we are running into the difficulties which came from starting late, We, however, are going to proceed by making a maximum effort. As you know, the expenditures in our space program are enormous . . . the time schedule, at least our hope, has not been changed by the recent setbacks (Ranger failures)."

1962 February 7 - .
  • Single-engine design for the Apollo service module - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM SPS. On the basis of a study by NAA, a single-engine configuration was chosen as the optimum approach for the service module propulsion subsystem. The results of the study were presented to MSC representatives and NAA was authorized to issue a work statement to begin procurement of an engine for this configuration. Agreement was also reached at this meeting on a vacuum thrust level of 20,000 pounds for the engine. This would maintain a thrust-to-weight ratio of 0.4 and allow a considerable increase in the lunar liftoff weight of the spacecraft.

1962 February 7 - . Launch Site: White Sands. Launch Complex: White Sands LC38. LV Family: Nike Zeus. Launch Vehicle: Nike Zeus.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 150 km (90 mi).

1962 February 7 - . 11:50 GMT - . Launch Site: Wallops Island. LV Family: Javelin. Launch Vehicle: Javelin. LV Configuration: Javelin NASA 8.16AI.
  • Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 960 km (590 mi).

1963 February 7 - . Launch Site: Cuxhaven. LV Family: Seliger. Launch Vehicle: Seliger.
  • Seliger rockets reach 80 km. - . Nation: Germany. Related Persons: Seliger. Seliger launched three rockets. The 3.4 m long single stage version reached an altitude of 52 km, and the 6.0 m long two stage version reached 80 km. Each stage had a thrust of 5000 kgf. Bochum Observatory tracked the radio transmitters of the payloads during their ascent. The wreckage of the missiles was found on the flats. Seliger announced plans to launch a three-stage rocket to 150 km altitude.

1963 February 7 - . LV Family: Saturn I; Saturn V.
  • Simplified terminology for the Saturn booster series - . Nation: USA. Program: Apollo. Summary: NASA announced a simplified terminology for the Saturn booster series: Saturn C-1 became "Saturn I," Saturn C-1B became "Saturn IB," and Saturn C-5 became "Saturn V.".

1963 February 7 - .
1963 February 7 - . Launch Site: Cuxhaven. LV Family: Seliger. Launch Vehicle: Seliger 2.
  • Test mission - . Nation: Germany. Agency: DRG. Apogee: 80 km (49 mi).

1963 February 7 - . Launch Site: Cuxhaven. LV Family: Seliger. Launch Vehicle: Seliger 1.
  • Test mission - . Nation: Germany. Agency: DRG. Apogee: 52 km (32 mi).

1963 February 7 - . Launch Site: Cuxhaven. LV Family: Seliger. Launch Vehicle: Seliger 2.
  • Test mission - . Nation: Germany. Agency: DRG. Apogee: 80 km (49 mi).

1963 February 7 - . 16:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC29A. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3X-8.
  • Test mission - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1964 February 7 - .
  • Grumman reevaluated its testing concept for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Grumman received MSC's response to the "Project Christmas Present Report", and accordingly reevaluated its testing concept for the LEM. On February 19, the contractor proposed to ASPO Manager Joseph F. Shea a flight program schedule, which was tentatively approved. ASPO's forthcoming proposal was identical to Grumman's proposal. It called for 11 LEMs (which were now renumbered consecutively) and two flight test articles. All LEMs were to have full mission capability, but numbers one through three had to be capable of either manned or unmanned flight.

1966 February 7 - .
1967 February 7 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF07. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 893.
  • Follow-on operational missile test - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1967 February 7 - . 03:20 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511. LV Configuration: Soyuz 11A511 U15000-03.
  • Cosmos 140 - . Payload: Soyuz 7K-OK (P) s/n 3. Mass: 6,450 kg (14,210 lb). Nation: USSR. Agency: MOM. Program: Soyuz. Class: Manned. Type: Manned spacecraft. Spacecraft: Soyuz 7K-OK. Duration: 1.98 days. Decay Date: 1967-02-09 . USAF Sat Cat: 2667 . COSPAR: 1967-009A. Apogee: 216 km (134 mi). Perigee: 169 km (105 mi). Inclination: 51.6000 deg. Period: 88.30 min. After the self-destruction of the first Soyuz 7K-OK on re-entry, and the loss of the second one on the pad fire in December, the state commission ruled that the third 7K-OK model would be flown unpiloted on a solo mission. If this was successful then the fourth and fifth Soyuz would be flown on a manned docking mission. Once in orbit Cosmos 140 experienced attitude control problems due to a faulty star sensor resulting in excessive fuel consumption. The spacecraft couldn't keep the required orientation towards the sun to keep the solar panels illuminated, and the batteries discharged. Despite all of these problems the spacecraft remained controllable. An attempted manoeuvre on the 22nd revolution still showed problems with the control system. It malfunctioned yet again during retrofire, leading to a steeper than planned uncontrolled ballistic re-entry. The re-entry capsule itself had depressurised on separation from the service module due to a fault in the base of the capsule. A 300 mm hole burned through in the heat shield during re-entry. Although such events would have been lethal to any human occupants, the capsule's recovery systems operated and the capsule crashed through the ice of the frozen Aral Sea, 3 km from shore and 500 kilometres short of the intended landing zone. The spacecraft finally sank in 10 meters of water and had to be retrieved by divers. Still, the mission was deemed 'good enough' for the next mission to be a manned two-craft docking and crew transfer space spectacular. Mishin and Kamanin felt that a human crew could have sorted out the problems. They were also under intense pressure to achieve a manned circumlunar flight before the 50th Anniversary of the Soviet Revolution in October.

1968 February 7 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC32B. LV Family: Minuteman. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 468.
  • Research and development launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1968 February 7 - . 10:43 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Molniya 8K78M. LV Configuration: Molniya 8K78M Ya716-57. FAILURE: At T+524.6 sec Stage 3's engine 11D55 cut off prematurely because it ran out of fuel due to an excessive fuel consumption rate through the gas-generator.. Failed Stage: 3.
  • E-6LS s/n 112 - . Payload: E-6LS s/n 112. Nation: USSR. Agency: RVSN. Program: Lunar L1. Class: Moon. Type: Lunar probe. Flight: Soyuz 7K-L1 mission 1. Spacecraft: Luna E-6LS. Decay Date: 1968-02-07 . COSPAR: F680207A. Failed launch of an E-6LS radio-equipped version of the E-6 used to test tracking and communications networks for the Soviet manned lunar program. Suggestions for the abnormal consumption included the seizing up of a pintle valve for controlling fuel supply into the regulator or the seizing up of the fuel inlet control. The upper stages broke up in the atmosphere.

1969 February 7 - .
  • Beregovoi to head cosmonauts - . Nation: USSR. Related Persons: Beregovoi. Summary: Word has got out that Beregovoi is to be made head of the cosmonaut training. It is controversial, to say the least..

1969 February 7 - . 01:22 GMT - . Launch Site: Biscarosse. LV Family: Belier. Launch Vehicle: Dragon 2B. LV Configuration: Dragon 2B D-259.
  • FU-180 Mass spectrometer F4 Ionosphere mission - . Nation: France. Agency: CNES. Apogee: 413 km (256 mi).

1969 February 7 - . 13:59 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/1. LV Family: Kosmos 2. Launch Vehicle: Kosmos 11K63.
  • Cosmos 265 - . Payload: DS-P1-Yu s/n 21. Mass: 325 kg (716 lb). Nation: USSR. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft: DS-P1-Yu. Completed Operations Date: 1969-05-01 . Decay Date: 1969-05-01 . USAF Sat Cat: 3675 . COSPAR: 1969-012A. Apogee: 456 km (283 mi). Perigee: 273 km (169 mi). Inclination: 71.0000 deg. Period: 91.80 min. Summary: Development of systems for air defence and the control of outer space..

1970 February 7 - .
  • Soyuz 10 and 11 crew selections; Soyuz 9 experiment review - . Nation: USSR. Program: Salyut; Soyuz. Flight: Soyuz 10; Soyuz 11; Soyuz 9. Spacecraft: Salyut 1. Kamanin meets with nine generals involved in supervising aspects of the space programme. Only one is from the VVS aviation, the rest have artillery or rocket backgrounds. Naturally they have no bad words for the RSVN or TsUKOS. At the centre, crew selection for the Soyuz 10 and Soyuz 11 missions to the DOS space station are underway. A review is conducted of the biomedical and zero-G studies planned for Soyuz 9. This is followed by a meeting with General Komarov and the cosmonauts on plans for the new cosmonaut training building and a nine-story apartment building.

1970 February 7 - . 03:00 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.262GG.
  • X-ray astronomy mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1970 February 7 - . 05:31 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 CRL AT3.726.
  • Infrared Infrared astronomy mission - . Nation: USA. Agency: USAF. Apogee: 142 km (88 mi).

1971 February 7 - . 03:45 GMT - . Launch Site: Salto di Quirra. LV Family: Skylark. Launch Vehicle: Skylark 3. LV Configuration: Skylark 3 S80/3.
  • ESRO S80 / 3 Ionosphere mission - . Nation: Europe. Agency: ESRO. Apogee: 214 km (132 mi).

1972 February 7 - . 23:33 GMT - . Launch Site: Kiruna. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk NASA 18.131IA.
  • RTG SNT 7 / 1 (S7-1) Aeronomy mission - . Nation: Sweden. Agency: NASA; RTG. Apogee: 180 km (110 mi).

1973 February 7 - . 01:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-8.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1973 February 7 - . 14:09 GMT - . Launch Site: Natal. LV Family: Black Brant. Launch Vehicle: Black Brant 5C.
  • DLR N-BBVC-54 Aeronomy mission - . Nation: Germany. Agency: DFVLR. Apogee: 211 km (131 mi).

1974 February 7 - . 09:00 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHOK. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 89 km (55 mi).

1975 February 7 - . 11:30 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 79 km (49 mi).

1976 February 7 - . 15:00 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 87 km (54 mi).

1977 February 7 - .
  • Enterprise (OV-101)/shuttle carrier aircraft mate - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft: Enterprise. Summary: Enterprise (OV-101)/shuttle carrier aircraft mate start.

1977 February 7 - . 04:51 GMT - . Launch Site: Poker Flat. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk NASA 18.1011UE.
  • Plasma mission - . Nation: USA. Agency: NASA. Apogee: 270 km (160 mi).

1977 February 7 - . 16:10 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Soyuz 24 - . Call Sign: Terek (Terek - river in the Caucasus). Crew: Glazkov; Gorbatko. Backup Crew: Berezovoi; Lisun. Support Crew: Kozelsky; Preobrazhensky. Payload: Soyuz 7K-T(A9) s/n 66. Mass: 6,800 kg (14,900 lb). Nation: USSR. Related Persons: Glazkov; Gorbatko; Berezovoi; Lisun; Kozelsky; Preobrazhensky. Agency: MOM. Program: Almaz. Class: Manned. Type: Manned spacecraft. Flight: Soyuz 24. Spacecraft: Soyuz 7K-T/A9. Duration: 17.73 days. Decay Date: 1977-02-25 . USAF Sat Cat: 9804 . COSPAR: 1977-008A. Apogee: 264 km (164 mi). Perigee: 226 km (140 mi). Inclination: 51.6000 deg. Period: 89.30 min. Soyuz 24 docked with Salyut 5 and brought repair equipment and equipment for a change of cabin atmosphere. This special apparatus was designed to allow the entire station to be vented through the EVA airlock. Because of this the planned EVA was cancelled. However analysis after arrival showed no toxins in the air. The crew changed the cabin air anyway, then returned to earth. The mission, although a short 18 days, was characterised as a busy and successful mission, accomplishing nearly as much as the earlier Soyuz 21's 50 day mission.

1977 February 7 - . 21:40 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel MOP1.
  • Ozone / La / ne Atmospheric mission - . Nation: UK. Agency: MO-UK. Apogee: 127 km (78 mi).

1977 February 7 - . 23:09 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P192H.
  • Atmospheric mission - . Nation: UK. Agency: SRC. Apogee: 146 km (90 mi).

1977 February 7 - . 23:26 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P193H.
  • Ionosphere / plasma mission - . Nation: UK. Agency: SRC. Apogee: 135 km (83 mi).

1978 February 7 - . 00:30 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P204H.
  • Ion composition Ionosphere mission - . Nation: UK. Agency: SRC. Apogee: 108 km (67 mi).

1978 February 7 - . 01:01 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P198H.
  • Atomic oxygen Atmospheric mission - . Nation: UK. Agency: SRC. Apogee: 139 km (86 mi).

1979 February 7 - .
  • Death of Robert B Young - . Nation: USA. Related Persons: Young, Robert. Summary: American engineer. Key manager at Aerojet, working there from the 1940's, responsible for the rocket engines for the Titan, the Apollo SPS, and Shuttle OMS..

1979 February 7 - . 19:14 GMT - . Launch Site: White Sands. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 98 km (60 mi).

1980 February 7 - . 11:00 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1155 - . 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: 1980-02-21 . USAF Sat Cat: 11685 . COSPAR: 1980-009A. Apogee: 393 km (244 mi). Perigee: 191 km (118 mi). Inclination: 72.8000 deg. Period: 90.30 min. Summary: Photo surveillance; returned film capsule..

1980 February 7 - . 21:10 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Titan. Launch Vehicle: Titan 3D. LV Configuration: Titan IIID 23D-19.
  • KH-11 no. 3 - . Payload: KH-11 no. 3 / OPS 2581. Mass: 13,300 kg (29,300 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-11. Decay Date: 1982-10-30 . USAF Sat Cat: 11687 . COSPAR: 1980-010A. Apogee: 498 km (309 mi). Perigee: 220 km (130 mi). Inclination: 97.0000 deg. Period: 91.70 min. Summary: KH-11 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1981 February 7 - . 20:13 GMT - . Launch Site: Kiruna. LV Family: Petrel. Launch Vehicle: Petrel 2. LV Configuration: Petrel 2 P219K.
  • Atomic oxygen Aeronomy mission - . Nation: UK. Agency: SRC. Apogee: 171 km (106 mi).

1981 February 7 - . 20:30 GMT - . Launch Site: Kiruna. LV Family: Hawk. Launch Vehicle: Nike Orion. LV Configuration: Nike Orion SSC S35.
  • OXYGEN Aeronomy mission - . Nation: Sweden. Agency: SSC. Apogee: 145 km (90 mi).

1983 February 7 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 640. LV Family: Trident. Launch Vehicle: Trident C-4.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1983 February 7 - . Launch Site: Kwajalein. Launch Vehicle: HOE. LV Configuration: HOE HOE 1.
  • HOE 1 ABM test - . Nation: USA. Agency: USAF AFSC. Apogee: 200 km (120 mi).

1983 February 7 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF06. LV Family: Minuteman. Launch Vehicle: Minuteman 1B.
  • RSLP STREP-11 (HOE) re-entry vehicle test flight - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1983 February 7 - . 02:14 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 9. LV Configuration: Black Brant IX AAF-IXC-2.
  • WATERHOLE 3 Plasma mission - . Nation: Canada. Agency: NRCC. Apogee: 333 km (206 mi).

1983 February 7 - . 09:25 GMT - . Launch Site: Wallops Island. LV Family: Loki. Launch Vehicle: Super Loki. LV Configuration: Super Loki T 1-0507.
  • Test / aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 111 km (68 mi).

1983 February 7 - . 13:42 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 640. LV Family: Trident. Launch Vehicle: Trident C-4.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1984 February 7 - .
1984 February 7 - . 09:09 GMT - . Launch Site: Poker Flat. LV Family: Black Brant. Launch Vehicle: Black Brant 10. LV Configuration: Black Brant X NASA 35.006UE.
  • Plasma mission - . Nation: USA. Agency: NASA. Apogee: 1,020 km (630 mi).

1984 February 7 - . 09:10 GMT - . Launch Site: Fort Yukon. LV Family: Terrier. Launch Vehicle: Terrier Malemute. LV Configuration: Terrier Malemute NASA 29.21UE.
  • Plasma mission - . Nation: USA. Agency: NASA. Apogee: 500 km (310 mi).

1984 February 7 - . 20:00 GMT - . Launch Site: Andoya. LV Family: Viper. Launch Vehicle: Viper 3A. LV Configuration: Viper 3A MAP/WINE.
  • M-F 42 Aeronomy mission - . Nation: Germany. Agency: DFVLR. Apogee: 121 km (75 mi).

1985 February 7 - . 09:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-15.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 213 km (132 mi).

1986 February 7 - . 08:45 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U2.
  • Cosmos 1731 - . Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Yantar-4KS1. Duration: 238.00 days. Decay Date: 1986-10-03 . USAF Sat Cat: 16589 . COSPAR: 1986-013A. Apogee: 263 km (163 mi). Perigee: 233 km (144 mi). Inclination: 64.7000 deg. Period: 89.50 min. Summary: Photo/digital surveillance..

1987 February 7 - . 10:30 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1819 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Earth. Type: Earth resources satellite. Spacecraft: Zenit-8. Duration: 11.00 days. Decay Date: 1987-02-18 . USAF Sat Cat: 17484 . COSPAR: 1987-014A. Apogee: 227 km (141 mi). Perigee: 188 km (116 mi). Inclination: 72.8000 deg. Period: 88.70 min. Summary: Military cartographic satellite; returned film capsule..

1989 February 7 - . 23:36 GMT - . Launch Site: Kiruna. Launch Complex: Kiruna S. LV Family: Skylark. Launch Vehicle: Skylark 2. LV Configuration: Skylark 2 DLR K-CR-164.
  • ROSE III Aeronomy mission - . Nation: Germany. Agency: DFVLR. Apogee: 124 km (77 mi).

1990 February 7 - .
  • Soviet Communists relinquish sole power - . Nation: USSR.

1990 February 7 - . 01:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-21(F).
  • MOS-1b - . Payload: Momo 1B. Mass: 740 kg (1,630 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Sea satellite. Spacecraft: Marine Observation Satellite. USAF Sat Cat: 20478 . COSPAR: 1990-013A. Apogee: 909 km (564 mi). Perigee: 908 km (564 mi). Inclination: 99.1000 deg. Period: 103.20 min. Summary: Marine observation. Continuation of Earth observation functions of MOS-1; establishment of common technology necessary for Earth-observation satellites. Launching organization NASDA. Name MOS-1b 'Momo-1b'. Launch time 0133 UT..
  • Debut - . Payload: Orizuru. Mass: 50 kg (110 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: Debut. USAF Sat Cat: 20479 . COSPAR: 1990-013B. Apogee: 1,743 km (1,083 mi). Perigee: 911 km (566 mi). Inclination: 99.0000 deg. Period: 112.20 min. Summary: Boom, umbrella test. DEBUT 'Orizuru'. Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA. Launch time 0133 UT..
  • Oscar 20 - . Payload: JAS 1b. Mass: 50 kg (110 lb). Nation: Japan. Agency: JARL. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 20480 . COSPAR: 1990-013C. Apogee: 1,745 km (1,084 mi). Perigee: 912 km (566 mi). Inclination: 99.0000 deg. Period: 112.20 min. Summary: JAS-1b 'Fuji-2'. Continuation of amateurradio services of JAS-1; extension of amateur radio communications area; advancement of amateur radio technology. Launching organization NASDA. Launch time 0133 UT..

1991 February 7 - .
  • Salyut 7 re-enters - . Nation: USSR. Program: Salyut 7. Spacecraft: Salyut 7. Salyut 7 had been put into a high storage orbit in June 1986, which was supposed to allow it to remain in orbit for ten years before decaying. But much greater than expected solar activity caused the orbit to decay rapidly. By the end of 1990 the station was no longer controllable, and on 7 February 1991 the station came down over South America.

1991 February 7 - . 08:15 GMT - . Launch Site: Plesetsk. LV Family: Topol. Launch Vehicle: Topol.
  • Test mission - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1991 February 7 - . 18:15 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC16/2. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 2124 - . Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Yantar-4K1. Duration: 59.00 days. Decay Date: 1991-04-07 . USAF Sat Cat: 21092 . COSPAR: 1991-008A. Apogee: 316 km (196 mi). Perigee: 186 km (115 mi). Inclination: 62.8000 deg. Period: 89.50 min. Summary: High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission..

1991 February 7 - . 22:54 GMT - . Launch Site: Scud Batteries. Launch Pad: IRAQ-S. LV Family: R-17. Launch Vehicle: Al Hussein.
  • Riyadh - . Nation: Iraq. Apogee: 100 km (60 mi).

1992 February 7 - . 18:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 68 km (42 mi).

1993 February 7 - . Launch Site: Balasore. LV Family: Prithvi. Launch Vehicle: Prithvi. LV Configuration: Prithvi 10.
  • Test mission - . Nation: India. Agency: IDRDL. Apogee: 100 km (60 mi).

1994 February 7 - .
  • Air Force Space Command launches the first Milstar satellite, a new generation military satellite communications system. - . Nation: USA.

1994 February 7 - . 21:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan Centaur 401A. LV Configuration: Titan 401A/Centaur K-10/TC-12 (45E-3).
  • USA 99 - . Payload: Milstar 1-01 / DFS 1. Mass: 4,500 kg (9,900 lb). Nation: USA. Agency: USAF. Class: Communications. Type: Military communications satellite. Spacecraft: Milstar. USAF Sat Cat: 22988 . COSPAR: 1994-009A. Apogee: 35,790 km (22,230 mi). Perigee: 35,733 km (22,203 mi). Inclination: 12.0000 deg. Period: 1,434.00 min. Summary: Military communications. Positioned in geosynchronous orbit at 90 deg W in 1994; 120 deg W in 1995-1999..

1995 February 7 - . Launch Site: White Sands. Launch Complex: White Sands SULF. Launch Vehicle: Storm. LV Configuration: Storm S9.
  • BTTV-8 THAAD Demo Target mission - . Nation: USA. Agency: USA. Apogee: 200 km (120 mi).

1997 February 7 - .
  • Starchaser LEXX launch. - . Nation: UK. Program: X-Prize. Spacecraft: Starchaser 5. Summary: Starchaser Industries (Hyde, England, UK) successfully launches LEXX vehicle..

1997 February 7 - . Launch Site: Bigen Island. LV Family: R-17. Launch Vehicle: R-17. LV Configuration: Scud FMA.
  • Willow Dune Target mission - . Nation: USA. Agency: USA. Apogee: 200 km (120 mi).

1998 February 7 - . 07:40 GMT - . Launch Site: Kiruna. Launch Complex: Kiruna S. LV Family: Skylark. Launch Vehicle: Skylark 7. LV Configuration: Skylark 7 DLR K-GR-231.
  • TEXUS 36 Microgravity mission - . Nation: Sweden. Agency: SSC. Apogee: 238 km (147 mi).

1999 February 7 - . 21:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Delta. Launch Vehicle: Delta 7426-9.5. LV Configuration: Delta 7426-9.5 D266.
  • Stardust - . Payload: Discovery 4. Mass: 370 kg (810 lb). Nation: USA. Agency: JPL. Manufacturer: Martin. Program: Discovery. Class: Comet. Type: Comet probe. Spacecraft: Stardust. USAF Sat Cat: 25618 . COSPAR: 1999-003A. Stardust was to fly within 100 km of comet 81P/Wild-2 in January 2004 and recover cometary material using an aerogel substance. A return capsule would land on a lake bed in Utah in January 2006, returning the material to earth. The launch went as planned. The second stage ignited at 21:08 GMT and its first burn put the vehicle into a 185 km x 185 km x 28 degree parking orbit at 21:14 GMT. The second stage second burn at 21:25 changed the orbit to planned values of 178 km x 7184 km x 28.5 degrees. The Star 37FM solid third stage ignited at 21:29 GMT and placed the spacecraft into a 2 year period solar orbit. The spacecraft separated at 21:31 GMT. Meanwhile, the Delta 266 second stage burned a third time on its own, until its propellants were depleted, entering a final orbit of 294 km x 6818 km x 22.5 degrees. The Stardust probe flew past Earth at a distance of 3706 km at 1115 GMT on January 15, 2001, and flew near the Moon at a distance of 98000 km at around 0200 GMT on January 16. The gravity assist flyby changed Stardust's heliocentric orbit from 0.956 x 2.216 AU x 0.0 deg to 0.983 x 2.285 AU x 3.7 deg.

2001 February 7 - . 09:28 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF10. LV Family: Minuteman. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 GT175GB.
  • GT175GB Functional Dependency gate operational test launch - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi).

2001 February 7 - . 23:05 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44L. LV Configuration: Ariane 44L-3 V139.
  • Sicral - . Payload: Sicral 1. Mass: 2,596 kg (5,723 lb). Nation: Italy. Agency: ADI. Manufacturer: Alenia. Class: Communications. Type: Civilian communications satellite. Spacecraft: Italsat. USAF Sat Cat: 26694 . COSPAR: 2001-005A. Apogee: 35,801 km (22,245 mi). Perigee: 35,773 km (22,228 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Sicral, (Sistema Italiana de Communicazione Riservente Allarmi) was a communications satellite for the Italian defense ministry's procurement division, the Segretariato Generale della Difesa's Direzione Nazionale degli Armamenti. Sicral was built by Alenia Aerospazio and derived from the Italsat series. Its mass was 2596 kg full, 1253 kg dry and it carried a liquid apogee engine. The 3.3 kW, 3.4 m x 4.9 m, triaxially-stabilized spacecraft carried a total of nine transponders in the SHF-, UHF-, and EHF-bands to enable secure communications after parking over 16.2 deg-E longitude. Positioned in geosynchronous orbit at 16 deg E in 2001 As of 26 August 2001 located at 16.27 deg E drifting at 0.004 deg W per day. As of 2007 Mar 9 located at 16.34E drifting at 0.018E degrees per day.
  • Skynet 4F - . Mass: 2,596 kg (5,723 lb). Nation: UK. Agency: MoD. Manufacturer: Alenia. Program: Skynet. Class: Communications. Type: Military communications satellite. Spacecraft: ECS/OTS. USAF Sat Cat: 26695 . COSPAR: 2001-005B. Apogee: 35,801 km (22,245 mi). Perigee: 35,772 km (22,227 mi). Inclination: 2.9000 deg. Period: 1,436.10 min. Skynet 4F was a communications satellite for the UK Ministry of Defense, and the last of the venerable ECS (European Communications Satellite) class of satellites built by Astrium/Stevenage. It carried a Thiokol Star 30 apogee motor and its mass was 1489 kg full, 830 kg dry - a dry mass more than twice the first OTS. The spacecraft carried a total of eight transponders in the SHF-, UHF-, and S-bands to provide secure communications after parking over either 1 deg-E or 6 deg-W. Positioned in geosynchronous orbit at 6 deg E in 2001 As of 5 September 2001 located at 8.77 deg E drifting at 0.284 deg W per day. As of 2007 Mar 10 located at 6.01E drifting at 0.004E degrees per day.

2001 February 7 - . 23:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-98.
  • STS-98 - . Call Sign: Atlantis. Crew: Cockrell; Polansky; Curbeam; Ivins; Jones. Payload: Atlantis F23. Mass: 90,225 kg (198,912 lb). Nation: USA. Related Persons: Cockrell; Polansky; Curbeam; Ivins; Jones. Agency: NASA Houston. Manufacturer: Boeing. Program: ISS. Class: Manned. Type: Manned spaceplane. Flight: STS-98. Spacecraft: Atlantis. Duration: 12.89 days. Decay Date: 2001-02-20 . USAF Sat Cat: 26698 . COSPAR: 2001-006A. Apogee: 337 km (209 mi). Perigee: 183 km (113 mi). Inclination: 51.3000 deg. Period: 89.71 min. ISS Assembly flight. Launch delayed from January 18 and February 6. International Space Station assembly mission; delivered the Destiny and PMA-2 modules. Destiny was an American ISS module, an 8.4 meter long and 4.2 meter wide cylindrical structure with a mass of 15 tonnes. It was to function as a science and technology module and the primary control module for the ISS. The shuttle orbiter was placed in an initial 74 x 323 km x 51.6 deg orbit. At 2357 GMT the OMS engines fired for the OMS-2 burn which raised Atlantis' orbit to 204 x 322 km x 51.6 deg. Atlantis docked with the Station at 1651 GMT on February 9 at the PMA-3 port on Unity's nadir. At 1500 GMT on Feb 10 Marsha Ivins used the RMS arm to unberth the PMA-2 docking port from Unity. Tom Jones and Bob Curbeam then conducted three spacewalks on Februay 10 to 14 to attach the Destiny and PMA-2 modules to the station. The crew also delivered over a tonne of food, fuel and equipment to the ISS. Atlantis undocked from Alpha at 1406 GMT on February 16. Atlantis landed at Edwards AFB on February 20; plans to land on February 18 and 19 were called off due to persistent wind problems at Kennedy Space Center. The deorbit burn was at 1927 GMT and lowered the orbit from 370 x 386 km to about 50 x 380 km. The nominal entry interface at 122 km came at 2002 GMT and touchdown on runway 22 was at 20:33 GMT. On March 1 Atlantis was flown on the back of NASA's SCA 911 carrier aircraft to Altus AFB, Oklahoma, en route to Kennedy.

2003 February 7 - .
  • International Space Station Status Report #03-6 - . Nation: USA. Related Persons: Bowersox; Budarin; Pettit. Program: ISS. Flight: ISS EO-6. Summary: As they complete their eleventh week on orbit, the International Space Station's Expedition 6 crewmembers are unpacking a new shipment of supplies while helping mission managers plan for the remainder of their time in space.. Additional Details: International Space Station Status Report #03-6.

2007 February 7 - . 08:14 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF10. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • GT-193GM 1 RV operational test launch - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi).

2008 February 7 - .
  • Death of Gay Ilich Severin - . Nation: Russia. Related Persons: Severin. Summary: Russian engineer. Chief Designer and General Designer from 1961 of OKB Zvezda. Specialised in spacesuits and EVA airlocks..

2008 February 7 - . 19:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-122.
  • STS-122 - . Call Sign: Atlantis. Crew: Frick; Poindexter; Melvin; Walheim; Schlegel; Love; Eyharts. Payload: Atlantis F29 / Columbus. Mass: 117,850 kg (259,810 lb). Nation: USA. Related Persons: Frick; Poindexter; Melvin; Walheim; Schlegel; Love; Eyharts. Agency: NASA. Program: ISS. Class: Manned. Type: Manned spaceplane. Flight: STS-122; ISS EO-16; ISS EO-16-2; ISS EO-16-1. Spacecraft: Atlantis. Duration: 12.77 days. Decay Date: 2008-02-20 14:07:00 . USAF Sat Cat: 32486 . COSPAR: 2008-005A. Apogee: 343 km (213 mi). Perigee: 329 km (204 mi). Inclination: 51.6000 deg. Period: 91.20 min. ISS flight 1E's primary mission was the long-delayed delivery and installation of the European Columbus module. The shuttle entered an initial 58 km x 230 km orbit at 19:54 GMT. The OMS-2 circularization burn at 20:23 GMT put it into a 215 km x 233 km chase orbit. Atlantis docked with the PMA-2 port of the ISS at 17:17 GMT on 9 February. Eyharts was dropped off at the station, Tani, already aboard the ISS, returned to Earth on Atlantis. Atlantis undocked from the ISS on 20 February at 09:24 GMT; began its deorbit burn at 12:59; and landed at the Kennedy Space Center at 14:07.

2010 February 7 - . 05:20 GMT - . Launch Site: Balasore. Launch Complex: Balasore IC4. LV Family: Agni. Launch Vehicle: Agni 3.
  • Agni III test - . Nation: India. Agency: IDRDL. Apogee: 350 km (210 mi). Range: 3,500 km (2,100 mi). Summary: Fourth Agni III test..

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