Encyclopedia Astronautica
February 05


February 05 Chronology


1919 February 5 - .
1945 February 5 - . Launch Site: Peenemuende. Launch Complex: Peenemuende P10. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 V-285.
1946 February 5 - .
  • XS-1 Flight 2 - . Crew: Woolams. Payload: XS-1 # 1 flight 2. Nation: USA. Related Persons: Woolams. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: Bell flight 2. At Pinecastle AAF, Florida..

1946 February 5 - .
  • XS-1 Flight 3 - . Crew: Woolams. Payload: XS-1 # 1 flight 3. Nation: USA. Related Persons: Woolams. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: Bell flight 3. At Pinecastle AAF, Florida..

1947 February 5 - .
  • Birth of Dr Mary Louise Cleave - . Nation: USA. Summary: American ecologist mission specialist astronaut. Flew on STS-61-B, STS-30. Engineer..

1947 February 5 - .
  • XS-1 Flight 23 - . Crew: Goodlin. Payload: XS-1 # 2 flight 13. Nation: USA. Related Persons: Goodlin. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: Bell flight 13. Machmeter calibration..

1949 February 5 - .
1952 February 5 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 77R.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1953 February 5 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 306P.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1955 February 5 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-1. Launch Vehicle: R-1E (A-1). LV Configuration: R-1E (A-1) 2.
  • Test / biology mission - . Nation: USSR. Agency: Korolev. Apogee: 100 km (60 mi). Summary: No recovery. Carried dogs..

1957 February 5 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC1. Launch Pad: LC1/2?. LV Family: Snark. Launch Vehicle: Snark. LV Configuration: Snark N-69D 52-10983?.
  • Test mission - . Nation: USA. Agency: USAF. Apogee: 10 km (6 mi).

1958 February 5 - . 07:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18A. Launch Pad: LC18A. LV Family: Vanguard. Launch Vehicle: Vanguard. LV Configuration: Vanguard TV-3BU. FAILURE: Control system malfunction - control lost after 57 sec.. Failed Stage: G.
  • Vanguard 1B - . Payload: Vanguard Test Satellite. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USN. Program: Vanguard. Class: Technology. Type: Navigation technology satellite. Spacecraft: Vanguard 1. Decay Date: 1958-02-05 . COSPAR: F580205A. Apogee: 6.00 km (3.70 mi). Summary: Trial firing of IGY Vanguard (TV-3Bu) satellite..

1959 February 5 - .
  • Working Group on Lunar Exploration established by NASA - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM Source Selection. A Working Group on Lunar Exploration was established by NASA at a meeting at Jet Propulsion Laboratory (JPL). Members of NASA, JPL, Army Ballistic Missile Agency, California Institute of Technology, and the University of California participated in the meeting. The Working Group was assigned the responsibility of preparing a lunar exploration program, which was outlined: circumlunar vehicles, unmanned and manned; hard lunar impact; close lunar satellites; soft lunar landings (instrumented). Preliminary studies showed that the Saturn booster with an intercontinental ballistic missile as a second stage and a Centaur as a third stage, would be capable of launching manned lunar circumnavigation spacecraft and instrumented packages of about one ton to a soft landing on the moon.

1959 February 5 - . 14:45 GMT - . Launch Site: Holloman. Launch Complex: Holloman A. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 AA3.100C.
  • Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 212 km (131 mi).

1960 February 5 - .
  • US National Security Council briefed on USAF plans for an anti-satellite system. - . Nation: USA. Spacecraft: SAINT; SAINT II. Summary: Assistant Air Force Secretary Joseph Charyk presented the plan..

1960 February 5 - . Launch Vehicle: Burya.
  • Burya cruise missile canceled. - . Nation: USSR. Program: Navaho. Decree 138-48 'On termination of work on the La-350 Burya at OKB-301' was issued. Project finally cancelled based on availability and invulnerability of R-7, R-9, and R-16 ICBM's. Flight test for technology purposes of already-built missiles was allowed to the end of the year.

1960 February 5 - . 00:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Jupiter. Launch Vehicle: Jupiter. LV Configuration: Jupiter IRBM AM-30.
  • Research and development test - . Nation: USA. Agency: USAF; NASA Huntsville. Apogee: 500 km (310 mi). Summary: The 28th R&D firing was from AMR at 1919 hours EST to a pre-calculated range of 1,299 nm. The flight successfully accomplished all primary and secondary missions. The nose cone impacted 0.65 nm short and 0.52 nm right of the intended target..

1960 February 5 - . 21:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC16. LV Family: Titan. Launch Vehicle: Titan 1. LV Configuration: Titan I C-4. FAILURE: Failure.
  • RVX-3 Re-entry Vehicle test - . Nation: USA. Agency: USAF. Apogee: 0 km ( mi).

1961 February 5 - . 13:48 GMT - . Launch Site: Wallops Island. LV Family: Aerobee. Launch Vehicle: Aerobee 150A. LV Configuration: Aerobee 150A NASA 04.38NP.
  • LeRC LH2 test Technology test - . Nation: USA. Agency: NASA. Apogee: 152 km (94 mi).

1962 February 5 - . 20:58 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 5C. LV Configuration: Skylark-5C SL35B.
  • Test mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 215 km (133 mi).

1963 February 5 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 599. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P-110.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1963 February 5 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 599. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P-111.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1964 February 5 - . LV Family: Titan. Launch Vehicle: Titan 2.
  • Gemini launch vehicle 2 stage I and interstage were erected in the vertical test facility at Martin-Baltimore. - . Nation: USA. Summary: Stage II was erected February 7. Subsystems Functional Verification Tests began February 21..

1964 February 5 - .
  • Soyuz mock-up - . Nation: USSR. Related Persons: Korolev. Program: Vostok; Lunar L1. Flight: Vostok 7; Vostok 8; Vostok 9; Vostok 10; Vostok 11; Vostok 12; Vostok 13; Voskhod 1; Voskhod 2; Soyuz A-1; Soyuz A-2; Soyuz A-3; Soyuz A-4. Spacecraft: Vostok. The cosmonauts visit Korolev at OKB-1 for the first viewing of the mock-up of the Soyuz spacecraft. Korolev announces that single-place Vostoks will fly no more, and that instead four of the spacecraft will be completed during 1964 to take three crew members. This decision has been taken since it was now certain that Soyuz will not be ready to fly in 1964, and the impending first flights of American Gemini and Apollo spacecraft will give the USA a lead in manned spaceflight before Soyuz missions can be flown.

    Kamanin is disturbed by the decision. He recalls that in 1961 flight of the Vostok with two or three crew was discussed, with flights to occur in 1962-1963. But at that time Korolev cancelled the plans, saying the Soyuz would be used for such missions. Now Soyuz will not fly until 1965, and he has changed his tune. Furthermore, the modified Vostok is inherently risky, with no way to save the crew in case of a launch vehicle malfunction in the first 40 seconds of flight. Unlike Vostok, the three crew will not have individual ejection seats or parachutes to give them a chance of escape in the event of an abort. The crew will be subject to 10 to 25 G's during an abort. There is no assurance the environmental control system can be modified to handle three crew. It all seems very unsafe, and Kamanin believes the six consecutive successful Vostok flights have given Korolev's engineers a false sense of the safety of the Vostok system. Kamanin is perplexed. How does he plan to convert a single-place spacecraft to a three-place spacecraft in a few months? Korolev has no clear answers, but asks for the cosmonauts' support of the scheme.


1964 February 5 - . 00:39 GMT - . Launch Site: Fort Churchill. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.87GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 126 km (78 mi).

1964 February 5 - . 03:20 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.63GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 119 km (73 mi).

1965 February 5 - .
  • Vykhod redesignated Voskhod 2 - . Nation: USSR. Related Persons: Belyayev; Leonov. Program: Voskhod. Flight: Voskhod 2. Spacecraft: Voskhod. The 3KD spacecraft will be known as Voskhod-2 rather than Vykhod. It was felt that 'Vykhod' ('exit') would reveal the purpose of the flight, which should not be revealed unless the experiment succeeds. The cosmonauts are training very hard in the zero-G trainer and will use the airlock at 37 km equivalent vacuum in the TBK-60 on 8 February. The motto is "Train hard to make it easy to do".

1965 February 5 - .
  • Apollo SM 001's service propulsion engine static-fired - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM SPS. Summary: SM 001's service propulsion engine was static-fired for 10 sec at White Sands. The firing was the first in a program to verify the mission profiles for later flight tests of the module. (SM 001 was the first major piece of flight-weight Apollo hardware.).

1965 February 5 - . LV Family: Titan. Launch Vehicle: Titan 2.
  • Modifications to Gemini launch vehicle 5 were completed and stage I was erected in the vertical test facility at Martin-Baltimore. - . Nation: USA. Flight: Gemini 5. Summary: Stage II was erected February 8. Power was applied to the vehicle for the first time on February 15, and Subsystems Functional Verification Tests were completed March 8. Another modification period followed..

1966 February 5 - . Launch Site: Baikonur. Launch Complex: Baikonur LC67/21. LV Family: Tsiklon. Launch Vehicle: R-36-O. LV Configuration: R-36O 8K69 U22502 No. 02L.
  • OGCh No. 02L - . Mass: 1,700 kg (3,700 lb). Nation: USSR. Agency: RVSN. Spacecraft: OGCh. COSPAR: U660205A. Apogee: 200 km (120 mi). Summary: Second suborbital test of the FOBS system..

1967 February 5 - . 01:17 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC13. LV Family: Atlas. Launch Vehicle: Atlas Agena D SLV-3. LV Configuration: SLV-3 Agena D 5803 (AA20) / Agena D 6632.
  • Lunar Orbiter 3 - . Payload: Lunar Orbiter C. Mass: 385 kg (848 lb). Nation: USA. Agency: NASA Langley. Class: Moon. Type: Lunar probe. Spacecraft: Lunar Orbiter. Decay Date: 1967-10-09 . USAF Sat Cat: 2666 . COSPAR: 1967-008A. Summary: Crashed into Moon; returned 182 photos of lunar surface. Selenocentric orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1968 February 5 - .
  • 40 per-cent nitrogen prelaunch atmosphere in Apollo - . Nation: USA. Related Persons: Faget; Slayton. Program: Apollo. Spacecraft: Apollo CSM; CSM Communications. A Senior Flammability Review Board meeting at MSC reached a number of decisions on the CSM. Attending were Robert R. Gilruth, chairman; George M. Low, Kenneth S. Kleinknecht, Aleck C. Bond, Maxime A. Faget, Donald K. Slayton, Charles A. Berry, and Rodney G. Rose, all of MSC; Samuel C. Phillips, NASA Hq.; William B. Bergen and Dale D. Myers, North American Rockwell; and George Stoner, Boeing (nonvoting observer).

    Several previous action assignments were reviewed:

    1. Component level Flammability Test Program - North American reviewed the results of its material identification and test program, the component test program, and the boilerplate 1,250 tests. These tests had provided the basis for design decisions on selection and application of CM nonmetallic materials.
    2. Boilerplate 1224 configuration comparison to CSMs 2TV-1 and 101 - North American presented the comparison and the Board decided that the boilerplate configuration was representative of the "worst case" configuration, considering both 2TV-l and 101.
    3. Internal ignition rationale - ignition rationale for the boilerplate 1224 tests was presented to the Board. Nichrome wire ignitors were used with the ignitor wire embedded in potting. In some locations a Ladicote cover was applied over the potting and ignitor. The Board pointed out that the ignition techniques were not really representative of actual operating conditions and were indeed overly severe.
    4. Crew communications umbilical - North American was evaluating a fluorel crew communications umbilical as well as fluorel oxygen umbilicals. A Beta sleeve over the oxygen and crew communications umbilicals would also be evaluated for its operational acceptability by the Crew.
    The Board presented a review of test results. In the tests at pressure of 4.3 newtons per square centimeter (6.2 pounds per square inch) in a 95-percent oxygen atmosphere, there were 38 ignitions in boilerplate 1224. Of these,5 produced fires large enough to require further consideration. In tests at 11.2 newtons per sq cm (16.2 psia) in a 60-percent-oxygen and 40-percent nitrogen atmosphere, there were 31 ignitions. Of these, 4 produced fires large enough to require further consideration.

    The Board concluded that the material changes made in the CM had resulted in a safe configuration in both the tested atmospheres. The Board agreed "that there will always be a degree of risk associated with manned space flight," but the risk of fire "was now substantially less than the basic risks inherent in manned space flight."

    Among decisions reached were:

    1. the CSM 2TV-1 and 101 coaxial cable configuration would be tested in the 60-percent-oxygen and 40-percent nitrogen atmosphere;
    2. material improvements and testing would be continued and changes would be phased in, pending the availability of proved materials; and
    3. action would be taken to be prepared to use a 60-percent-oxygen and 40-percent-nitrogen prelaunch atmosphere in CSM 101.
    A final decision would be made at the Design Certification Review on March 7.

1968 February 5 - . 19:00 GMT - . Launch Site: Wallops Island. LV Family: Tomahawk Sandia. Launch Vehicle: D-Region Tomahawk. LV Configuration: D-Region Tomahawk NASA 12.08GT.
  • Test mission - . Nation: USA. Agency: NASA. Apogee: 119 km (73 mi).

1968 February 5 - . 22:22 GMT - . Launch Site: Fort Churchill. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.263GM.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 127 km (78 mi).

1969 February 5 - .
  • Cosmonaut centre plans - . Nation: USSR. Related Persons: Vershinin. Program: Soyuz. Kamanin flies back to Moscow aboard an An-24. Plans for the Cosmonaut Centre are discussed during the flight. It is to consist of 600 officer, 8 generals (vs. 1 currently), 3 directorates (vs. 1 now), and 6 deputy positions (instead of 3). It will become the country's centre for both cosmonaut training and scientific research. Vershinin had spent all day at Chkalovskiy on 3 February. He was unable to get anything going on these plans despite promises to implement them by higher officers.

1969 February 5 - . 21:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Delta. Launch Vehicle: Thorad Agena D SLV-2G. LV Configuration: Thorad SLV-2G Agena D 519 / Agena D 1650.
  • KH-4B 1106 - . Payload: KH-4B s/n 1106 / Agena D 1650 / OPS 3890. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-4B. Decay Date: 1969-02-24 . USAF Sat Cat: 3672 . COSPAR: 1969-010A. Apogee: 275 km (170 mi). Perigee: 147 km (91 mi). Inclination: 81.6000 deg. Period: 88.70 min. Summary: KH-4B. The best image quality to date..
  • OPS 2644 - . Payload: EHH C2. Nation: USA. Agency: USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. USAF Sat Cat: 3673 . COSPAR: 1969-010xx. Apogee: 1,429 km (887 mi). Perigee: 1,391 km (864 mi). Inclination: 80.4000 deg. Period: 114.00 min.
  • SRV 801R - . Payload: SRV 1106-1 / OPS 2644. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO; USAF. Spacecraft: KH-4B. USAF Sat Cat: 3673 . COSPAR: 1969-010B. Apogee: 1,428 km (887 mi). Perigee: 1,391 km (864 mi). Inclination: 80.4000 deg. Period: 114.00 min. Summary: ABM monitoring..

1970 February 5 - . Launch Site: Wallops Island. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 NASA 13.13GT.
  • Test mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1970 February 5 - . 02:21 GMT - . Launch Site: Fort Churchill. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk NASA 18.101UA.
  • Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 340 km (210 mi).

1971 February 5 - .
  • Soviet view of Apollo 14. - . Nation: USSR. Related Persons: Mishin; Keldysh; Smirnov; Ustinov; Shonin. Program: Apollo; Lunar L3. Summary: Apollo 14 successfully lands on the moon. Kamanin notes that the Soviet Union is now five to six years behind, due to the mistakes of Mishin, Keldysh, Smirnov, and Ustinov. Shonin is training on Soyuz s/n 32 at the KIS of TsKBEM..

1971 February 5 - . 05:20 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF04. LV Family: Minuteman. Launch Vehicle: Minuteman 2.
  • OT GT60M operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1971 February 5 - . 09:18 GMT - .
  • Apollo 14 lands on the moon - . Nation: USA. Flight: Apollo 14. After rechecking the systems in the LM, astronauts Shepard and Mitchell separated the LM from the CSM and descended to the lunar surface. Shepard piloted the spacecraft to a routine landing at 09:18:11 GMT about 350 miles (563 kilometers) west-southwest of the center of the moon's visible side. Antares was only 175 feet (53 meters) from its targeted landing site. Additional Details: Apollo 14 lands on the moon.

1971 February 5 - . 14:42 GMT - .
  • EVA Apollo 14-1 - . Crew: Shepard; Mitchell. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.20 days. Nation: USA. Related Persons: Shepard; Mitchell. Program: Apollo. Class: Moon. Type: Manned lunar lander. Flight: Apollo 14. Spacecraft: Apollo LM. Summary: Explored lunar surface near LM and deployed ALSEP unmanned scientific station equipment..

1971 February 5 - . 22:46 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 4B. LV Configuration: Black Brant IVB AKF-4B-24.
  • Impedance dipole Aurora / ionosphere / meteorology mission - . Nation: Canada. Agency: NRCC. Apogee: 784 km (487 mi).

1972 February 5 - . 06:00 GMT - . Launch Site: Thumba. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P59T/C.
  • ISRO 18.07 Ionosphere mission - . Nation: UK. Agency: SRC. Apogee: 139 km (86 mi).

1973 February 5 - . 04:48 GMT - . Launch Site: Poker Flat. LV Family: Tomahawk Sandia. Launch Vehicle: Sandhawk Tomahawk. LV Configuration: Sandhawk Tomahawk Sandia 152-201. FAILURE: Failure.
  • Barium release ZURITA Aeronomy / Fields mission - . Nation: USA. Agency: Sandia. Apogee: 500 km (310 mi).

1974 February 5 - .
  • Mariner 10, Venus Flyby - . Nation: USA. Spacecraft: Mariner 10.

1975 February 5 - . Launch Site: Kwajalein. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk Barium cloud.
  • Magnetospheric mission - . Nation: USA. Agency: Sandia. Apogee: 185 km (114 mi).

1975 February 5 - . 06:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Q. LV Family: Mu. Launch Vehicle: ETV. LV Configuration: ETV-2.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 167 km (103 mi).

1975 February 5 - . 13:15 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 53753-212.
  • Cosmos 707 - . Mass: 900 kg (1,980 lb). Nation: USSR. Agency: MO. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-O. Decay Date: 1980-09-07 . USAF Sat Cat: 7637 . COSPAR: 1975-008A. Apogee: 548 km (340 mi). Perigee: 491 km (305 mi). Inclination: 74.0000 deg. Period: 95.00 min. Summary: Investigation of the upper atmosphere and outer space. .

1975 February 5 - . 14:40 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF09. Launch Pad: LF09?. LV Family: Minuteman. Launch Vehicle: Minuteman 3. FAILURE: Failure.
  • OT GT29GM-1 operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 500 km (310 mi).

1976 February 5 - .
1976 February 5 - . 05:22 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 4B. LV Configuration: Black Brant IVB AAF-4B-33.
  • Test / aurora / ionosphere mission - . Nation: Canada. Agency: NRCC. Apogee: 730 km (450 mi).

1976 February 5 - . 14:30 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/1. LV Family: Kosmos 2. Launch Vehicle: Kosmos 11K63.
  • Cosmos 801 - . Payload: DS-P1-I s/n 16. Mass: 400 kg (880 lb). Nation: USSR. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft: DS-P1-I. Completed Operations Date: 1976-12-14 . Decay Date: 1978-01-05 . USAF Sat Cat: 8658 . COSPAR: 1976-012A. Apogee: 796 km (494 mi). Perigee: 268 km (166 mi). Inclination: 71.0000 deg. Period: 95.30 min. Summary: Operational radar target for the ABM forces..

1976 February 5 - . 15:51 GMT - . Launch Site: El Arenosillo. LV Family: Skua. Launch Vehicle: Skua 2. LV Configuration: Skua 2 INTA MSCL-76006.
  • Aeronomy / ionosphere mission - . Nation: UK. Agency: INTA; DLR. Apogee: 102 km (63 mi).

1976 February 5 - . 22:30 GMT - . Launch Site: El Arenosillo. LV Family: Skua. Launch Vehicle: Skua 4. LV Configuration: Skua 4 INTA MS4CLO-76003.
  • Aurora / aeronomy / ionosphere mission - . Nation: UK. Agency: INTA; DLR. Apogee: 101 km (62 mi).

1977 February 5 - . 03:03 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 628. Launch Vehicle: Poseidon. LV Configuration: Poseidon C3 +1 other?.
  • FOT-27 Follow-on Test launch - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1979 February 5 - . 21:20 GMT - . Launch Site: Koroni. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 81 km (50 mi).

1980 February 5 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF09. Launch Pad: LF09?. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT71GM Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1980 February 5 - . Launch Site: Kwajalein. Launch Complex: Kwajalein RN. Launch Vehicle: DOT.
  • DOT 2 Interceptor mission - . Nation: USA. Agency: USAF. Apogee: 324 km (201 mi).

1981 February 5 - . LV Family: Energia. Launch Vehicle: Energia.
  • Decree for Gerkules nuclear-electric interorbital tug - . Nation: USSR. Spacecraft: Mars 1986. NPO Energia developed for the Ministry of Defence the interorbital tug Gerkules with 550 kW maximum output and continuous operation in the 50-150 kW range for 3 to 5 years. In 1986 an interorbital tug was studied to solve the specific application of transporting heavy satellites of 100 tonnes to geostationary orbit, launched by Energia.

1981 February 5 - . 11:25 GMT - . Launch Site: Poker Flat. LV Family: Sergeant. Launch Vehicle: Sounding Rocket. LV Configuration: Sergeant GL A30.072.
  • FWIF IV Auroral mission - . Nation: USA. Agency: USAF GL. Apogee: 130 km (80 mi).

1982 February 5 - . 09:12 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/40. LV Family: Proton. Launch Vehicle: Proton-K/DM. LV Configuration: Proton-K/DM 308-01.
  • Ekran 8 - . Payload: Ekran s/n 22L. Mass: 1,970 kg (4,340 lb). Nation: USSR. Agency: MOM. Class: Communications. Type: Military communications satellite. Spacecraft: Ekran . Completed Operations Date: 1984-01-01 . USAF Sat Cat: 13056 . COSPAR: 1982-009A. Apogee: 36,010 km (22,370 mi). Perigee: 35,756 km (22,217 mi). Inclination: 10.0000 deg. Period: 1,441.00 min. Transmission of Central Television programmes to a network of receivers for collective use. Positioned in geosynchronous orbit at 99 deg E in 1982-1983 As of 28 August 2001 located at 30.39 deg W drifting at 1.165 deg W per day. As of 2007 Mar 11 located at 85.74E drifting at 1.235W degrees per day.

1983 February 5 - . 20:00 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 87 km (54 mi).

1984 February 5 - . 18:44 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3E. LV Family: Atlas. Launch Vehicle: Atlas H. LV Configuration: Atlas H 6003H / 6003H.
  • NOSS 6 - . Payload: PARCAE 7 / OPS 8737. Nation: USA. Agency: USN. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: NOSS. USAF Sat Cat: 14690 . COSPAR: 1984-012A. Apogee: 1,172 km (728 mi). Perigee: 1,052 km (653 mi). Inclination: 63.4000 deg. Period: 107.00 min. Summary: Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE..
  • JD2 - . Payload: SSU. Nation: USA. Agency: USN. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: NOSS-Subsat. USAF Sat Cat: 14729 . COSPAR: 1984-012D. Apogee: 1,172 km (728 mi). Perigee: 1,052 km (653 mi). Inclination: 63.4000 deg. Period: 107.00 min. Summary: Deployed from NOSS 6..
  • JD1 - . Payload: SSU. Nation: USA. Agency: USN. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: NOSS-Subsat. USAF Sat Cat: 14728 . COSPAR: 1984-012C. Apogee: 1,172 km (728 mi). Perigee: 1,052 km (653 mi). Inclination: 63.4000 deg. Period: 107.00 min. Summary: Deployed from NOSS 6..
  • JD3 - . Payload: SSU. Nation: USA. Agency: USN. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: NOSS-Subsat. USAF Sat Cat: 14795 . COSPAR: 1984-012F. Apogee: 1,172 km (728 mi). Perigee: 1,052 km (653 mi). Inclination: 63.4000 deg. Period: 107.00 min.

1984 February 5 - . 20:00 GMT - . Launch Site: Andoya. LV Family: Viper. Launch Vehicle: Viper 3A. LV Configuration: Viper 3A MAP/WINE.
  • M-F 41 Aeronomy mission - . Nation: Germany. Agency: DFVLR. Apogee: 114 km (70 mi).

1985 February 5 - . 14:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 67 km (41 mi).

1986 February 5 - . 12:35 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 85 km (52 mi).

1987 February 5 - . 06:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-3.
  • Ginga - . Payload: Astro C. Mass: 420 kg (920 lb). Nation: Japan. Agency: ISAS. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Astro. Decay Date: 1991-11-01 . USAF Sat Cat: 17480 . COSPAR: 1987-012A. Apogee: 450 km (270 mi). Perigee: 395 km (245 mi). Inclination: 31.0000 deg. Period: 93.00 min. Summary: Studyied galactic gamma ray, X-ray sources. ASTRO-C (Ginga). Observation of variabilities of X-rays from active galactic nuclei and galactic compact sources. Launching organization ISAS. Launch time 0630 GMT. .

1987 February 5 - . 21:38 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U2.
  • Soyuz TM-2 - . Call Sign: Taimyr (Taimyr - Russian peninsula). Crew: Laveykin; Romanenko. Backup Crew: Serebrov; Titov, Vladimir. Payload: Soyuz TM 11F732 s/n 52. Mass: 7,100 kg (15,600 lb). Nation: USSR. Related Persons: Laveykin; Romanenko; Serebrov; Titov, Vladimir. Agency: MOM. Program: Mir. Class: Manned. Type: Manned spacecraft. Flight: Mir EO-2; Mir LD-1. Spacecraft: Soyuz TM. Duration: 174.14 days. Decay Date: 1987-07-30 . USAF Sat Cat: 17482 . COSPAR: 1987-013A. Apogee: 365 km (226 mi). Perigee: 341 km (211 mi). Inclination: 51.6000 deg. Period: 91.60 min. Summary: Mir Expedition EO-02. Docked with Mir 7 February 1987. Carried Yuri Romanenko, Aleksander Laveykin to Mir; returned Laveykin, crew of Soyuz TM-3 to Earth..

1988 February 5 - . 14:10 GMT - . Launch Site: Ascension. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 81 km (50 mi).

1989 February 5 - . 07:06 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: PASSAT. Launch Vehicle: MMR-06.
  • Aeronomy mission - . Nation: USSR. Agency: GMS. Apogee: 60 km (37 mi).

1990 February 5 - . 06:08 GMT - .
  • EVA Mir EO-5-5 - . Crew: Viktorenko; Serebrov. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.16 days. Nation: USSR. Related Persons: Viktorenko; Serebrov. Program: Mir. Class: Manned. Type: Manned space station. Flight: Mir EO-5. Spacecraft: Mir. Summary: Viktorenko tested SPK manoeuvring unit..

1991 February 5 - . 02:36 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 47148-407.
  • Cosmos 2123 - . Payload: Tsikada/RS-12/RS-13. Mass: 810 kg (1,780 lb). Nation: USSR. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Tsikada. USAF Sat Cat: 21089 . COSPAR: 1991-007A. Apogee: 1,005 km (624 mi). Perigee: 963 km (598 mi). Inclination: 82.9000 deg. Period: 104.80 min. Civilian navigation satellite. Positioned in plane 13 of constellation. Testing of components and equipment of a space navigation system being set up to determine the position of civil aircraft and ships of the USSR merchant marine and fishing fleet at any point on the oceans and seas. Two amateur satellite transponders, RS12 and RS13, were secondary payloads on the Cosmos 2123 navigation satellite. These transponders were developed at the Kaluga Electromechanical Plant under the direction of Aleksander Papkov and were launched aboard several satellites by the USSR during 1978-1991.

1992 February 5 - . Launch Site: Baikonur. Launch Complex: Baikonur LC45/1. LV Family: Zenit. Launch Vehicle: Zenit-2. FAILURE: Second stage malfunction due to heating problems in main engine.. Failed Stage: 2.
  • Tselina-2 - . Payload: Tselina-2 no. 12. Mass: 6,000 kg (13,200 lb). Nation: Russia. Agency: UNKS. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-2. COSPAR: F920205A.

1993 February 5 - . 16:24 GMT - . Launch Site: White Sands. Launch Complex: White Sands SULF. Launch Vehicle: Storm. LV Configuration: Storm S3.
  • BTTV-3 Validation test - . Nation: USA. Agency: USA. Apogee: 200 km (120 mi).

1994 February 5 - . 08:46 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 375-02.
  • Raduga 1-3 - . Payload: Raduga-1. Mass: 2,000 kg (4,400 lb). Nation: Russia. Agency: MOM. Class: Communications. Type: Military communications satellite. Spacecraft: Raduga-1. USAF Sat Cat: 22981 . COSPAR: 1994-008A. Apogee: 36,513 km (22,688 mi). Perigee: 36,513 km (22,688 mi). Inclination: 1.4000 deg. Period: 1,473.00 min. Joined Raduga 1-2 at 48 deg E; third launch of alternate Raduga design. Extension of the telephone and telegraph radio communications system on the territory of the Russian Federation. Positioned in geosynchronous orbit at 49 deg E in 1994-1999 As of 1 September 2001 located at 49.75 deg E drifting at 0.057 deg W per day. As of 2007 Mar 10 located at 100.54E drifting at 0.021W degrees per day.

1996 February 5 - . 07:19 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44P. LV Configuration: Ariane 44P-3 V83.
  • N-STAR b - . Mass: 3,400 kg (7,400 lb). Nation: Japan. Agency: NTT. Program: N-STAR. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 23781 . COSPAR: 1996-007A. Apogee: 35,801 km (22,245 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.1000 deg. Period: 1,436.20 min. Summary: Geostationary at 128.9E. Positioned in geosynchronous orbit at 136 deg E in 1996-1999 As of 1 September 2001 located at 136.01 deg E drifting at 0.012 deg W per day. As of 2007 Mar 9 located at 136.04E drifting at 0.012W degrees per day..

1997 February 5 - . 02:16 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12. LV Configuration: MR-12 AGRE (D75MG).
  • Flaksus-2 Plasma/Active mission - . Nation: Russia. Agency: AN; APL. Apogee: 160 km (90 mi).

1998 February 5 - . 08:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: SS-520. LV Configuration: SS-520 SS-520-1.
  • ENA / EPS / LAP Test / plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 750 km (460 mi).

1999 February 5 - .
  • Mir News 453: Znamya 2.5 - . Nation: Russia. Program: Mir. Flight: Mir EO-26; Mir EO-26/-27. A tragic conjunction of circumstances caused the failure of this experiment. In soviet times successes caused an enormous publicity explosion. Nowadays the balance goes the other way: extensive information and publicity before an interesting hazardous operation and when there is a failure a strong hangover afterwards. For me the days before the execution of the experiment were hectic. Lots of people, among them even some who never before were not interested in spaceflight, tackled me to get information. The media had given them the impression that the Russians were about to install a real midsummer night's sun. As much as possible, often even disappointing those enthusiasts, I tried to explain them that this was just an experiment to try out the methods and the technologies of a solar reflector for the far future and that it had not been planned to surprise us with an overwhelming happening.

    It was clear the Russians were not happy with the enthusiasm and attention before and that some of them would prefer a little bit soviet-like publicity: so exuberant joy when a risky attempt was successful , but silence after a failure.

    What went wrong? Just when Padalka transmitted the command to unfold the reflector packages, the Progress-M40 got a command from earth to deploy a Kurs antenna. One slip of the reflector got stuck behind this antenna and the unfolding process stopped. After the retraction of the antenna and a motor burn of the Progress-M40 the reflector came free, but a second attempt to deploy the reflector with the centrifugal forces of the spinning around its X-axis Progress-M40 failed. After analyses and nightly deliberations the Russians decided to blow off the experiment and to put the Progress-M40 on a destruction course.

    Progress-M40:

    On 4.02.1999 at 09.59.32 UTC the freighter separated from the aft (Kvant-1) docking port of Mir.

    On 5.02.1999 at 1016 UTC Progress-M40 got the impulse to bring it back into the atmosphere. At 1110 UTC Progress-M40 burnt up over a designated area in the Pacific East of New-Zealand.

    Communications:

    These began with the reception between 1302 and 13.03.30 UTC of the 922.755 mc beacon and telemetry transmitter of Progress-M40. This was for me the prove that Progress-M40 was flying autonomously. Mir's radio conversations during the following passes of Mir and Progress-M40 made it clear that the experiment was not proceeding according to plan. Padalka reported hat he had switched off several systems and obviously the crew transferred the control of Progress-M40 to TsUP.

    Avdeyev continuously reported to TsUP the distances between Mir and Progress-M40 with the times. During the pass in orbit 74054, 1439-1440 UTC, he reported that at 13.54.40 UTC the distance had been 4090 Meters. At about 1439 UTC the distance was approx. 2 KM. For the measurements Avdeyev had to soar from port-hole to port-hole. Regularly he reported that it was difficult to track and to observe the Progress-M40 due to the sunlight shining in his eyes and now and then Mir's solar panels hampered him. Possibly Avdeyev had to report the distances to the man at TsUP who controlled the Progress-M40.

    Now and then the UKW-2 (130.165 mc) was in use for communications. During the pass in orb. 74055, (1606-1615 UTC) he continued to report the distances. One of my friends, radio-amateur Hans van Dijk (NL number 10204), picked up images of the Progress-M40 transmitted to earth with SSTV on 145.985 mc.

    The failure of the experiment was discussed during radio traffic. Padalka did not make a fuss about this, but he was disappointed about the fact that the crew had not been able to carry out their work. He expressed his satisfaction about the fact that the control of Progress-M40 with the TORU and the transfer of commands for the experiment worked flawlessly. He regretted the fact that they had installed all equipment to film and photograph the events in vain. He joked that they might be able to try it again in 6 years. About this all and the plans with this experiment for the next day he had a conversation with Flight control chief V.A. Solovyov.

    During the communication window in orb. 74057/58, 1915-1926 UTC, the crew, certainly unintended, startled the flight controller at TsUP by switching off the transmitter. This man possibly thought that something was wrong (in fact a free flying freighter not far from Mir!) and reacted immediately. Avdeyev told him that all was well on board.

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


2000 February 5 - . 14:09 GMT - . Launch Site: Fort Wingate. Launch Complex: Fort Wingate LC96. Launch Vehicle: Hera. LV Configuration: Hera 18.
  • MBRV-3/PAC-3 DT-5 Target mission - . Nation: USA. Agency: USA SSDC. Apogee: 60 km (37 mi).

2002 February 5 - . 20:58 GMT - . Launch Site: Mayport DZ. Launch Pad: 29.0 N x 78.5 W. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL. LV Configuration: Pegasus XL F31.
  • HESSI - . Payload: SA-200S. Mass: 449 kg (989 lb). Nation: USA. Agency: NASA. Manufacturer: Gilbert. Class: Astronomy. Type: Solar astronomy satellite. Spacecraft: HESSI. USAF Sat Cat: 27370 . COSPAR: 2002-004A. Apogee: 599 km (372 mi). Perigee: 574 km (356 mi). Inclination: 38.0000 deg. Period: 96.40 min. HESSI, the sixth Small Explorer, carried a rotating modulation collimator transform telescope, imaging solar flares in the hard X-ray spectrum. The launch marked the return to flight of Pegasus after the Hyper-X failure. The launch was originally to have occurred on 28 March 2001. The L-1011 launch aircraft took off at 19:29 GMT from the Cape Canaveral Skid Strip RW30/12, and headed out to the drop area at 28.0 N 78.5 W over the Atlantic. Drop of the Pegasus in the Atlantic Drop Zone at 28.0 N 78.5 W was at 20:58 GMT, with ignition 5 seconds later. The Pegasus reached orbit at 21:07 GMT. On the first pass it was confirmed that the solar panels had opened.

    The satellite rotated at 15 rpm, imaging by reconstructing the Fourier components from the time modulation of the solar x-ray flux through a set of 9 grids each 9 cm in diameter. It was expected to make images with a resolution of 2 arcseconds at 40 keV energies and 36 arcseconds at 1 MeV energies. The launch delays meant that HESSI missed some of the best flares at solar max.


2003 February 5 - .
  • STS-107 MCC Status Report #23 - . Nation: USA. Related Persons: Bowersox; Budarin; Pettit. Program: ISS. Flight: ISS EO-6. Summary: The search for clues about what caused Columbia's breakup during reentry Saturday, and the hunt for key debris from the orbiter, expanded today with recovery teams deployed in California and Arizona.. Additional Details: STS-107 MCC Status Report #23.

2004 February 5 - . 23:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. Launch Pad: SLC36A. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-165.
  • AMC-10 (GE-10) - . Mass: 2,340 kg (5,150 lb). Nation: USA. Agency: SES Americom. Manufacturer: Lockheed. Program: Americom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 28154 . COSPAR: 2004-003A. Apogee: 35,798 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0100 deg. Period: 1,436.09 min. Americom 10 (AMC-10) was a replacement satellite for Satcom C3. It was to be located at 135 deg W. The C-band satellite, to be accompanied by AMC-11 later in 2004, were designed to support SES Americom's cable network in the United States, Canada, the Caribbean, and Mexico. The satellite had a design life of 15 years and carried 24 x 36 MHz C-band transponders. As of 2007 Mar 10 located at 134.97W drifting at 0.005E degrees per day.

2008 February 5 - . 13:03 GMT - . Launch Site: Baikonur. LV Family: R-7. Launch Vehicle: Soyuz 11A511U. LV Configuration: Soyuz 11A511U s/n 1730.
  • Progress M-63 - . Payload: Progress M s/n 363. Mass: 7,130 kg (15,710 lb). Nation: Russia. Agency: RKA. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Flight: ISS EO-16; ISS EO-16-1. Spacecraft: Progress M. Duration: 61.96 days. Decay Date: 2008-04-07 12:00:00 . USAF Sat Cat: 32484 . COSPAR: 2008-004A. Apogee: 339 km (210 mi). Perigee: 338 km (210 mi). Inclination: 51.6000 deg. Period: 91.30 min. Summary: Docked with the ISS at the Pirs module on 7 February at 14:38 GMT. Undocked on 7 April at 08:49 GMT and was deorbited over the Pacific later the same day..

2011 February 5 - . 08:11 GMT - . Launch Site: Poker Flat. LV Family: Black Brant. Launch Vehicle: Black Brant 9.
  • NASA 36.256UE - . Nation: USA. Apogee: 260 km (160 mi). Summary: Earth atmosphere probe..

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