Encyclopedia Astronautica
February 17


February 17 Chronology


1922 February 17 - .
1943 February 17 - . Launch Site: Peenemuende. Launch Complex: Peenemuende P7. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 V-012.
  • V-2 4012 - . Nation: Germany. Agency: Wehrmacht. Summary: Flat trajectory; Burnout at T+61 seconds. Range 196 km.

1944 February 17 - . Launch Site: Heidelager. LV Family: V-2. Launch Vehicle: V-2.
1945 February 17 - . Launch Site: V-2 Battery 836. Launch Pad: 3./836. LV Family: V-2. Launch Vehicle: V-2. FAILURE: Failure.
  • V-2 combat launch from Hachenburg - . Nation: Germany. Summary: Hachenburg, Gehlert, rocket fired (failure)..

1949 February 17 - . 17:00 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 48.
  • Chemical release / solar extreme ultraviolet / biology mission - . Nation: USA. Agency: USA; APL. Apogee: 100 km (60 mi). Summary: Launched 10:00 local time. Reached 100.8 km. Carried cosmic and solar radiation, photo (Naval Research Lab); composition (Signal Corps Engineering Lab, University of Michigan); biological experiments for Applied Physics Lab, John Hopkins University..

1950 February 17 - . 18:01 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 53.
  • Solar x-ray / chemical release / aeronomy mission - . Nation: USA. Agency: USA; NRL. Apogee: 148 km (91 mi). Summary: Launched 11:01 local time. Reached 149 km. Carried cosmic and solar radiation, pressure, temperature experiments for Naval Research Lab..

1953 February 17 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 178R.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1954 February 17 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 1232A.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1955 February 17 - . Launch Site: White Sands. LV Family: Corporal. Launch Vehicle: Corporal. LV Configuration: Corporal 1564R.
  • Test mission - . Nation: USA. Apogee: 30 km (18 mi).

1956 February 17 - . Launch Vehicle: DF-1.
  • Plan for missile development proposed. - . Nation: China. Related Persons: Tsien. Program: Long March. Tsien Hsue-shen submits a secret proposal to the State Council for ballistic missile development - 'Prospectus for Establishment of a National Defence Aviation Industry'. The proposal calls for the establishment of a research facility for aeronautics and missile development.

1957 February 17 - . 21:36 GMT - . Launch Site: Guam. LV Family: Rockoon. Launch Vehicle: Loki Rockoon.
  • II5.099 Fields mission - . Nation: USA. Agency: SUI. Apogee: 75 km (46 mi).

1959 February 17 - .
  • Exploration of the moon a NASA responsibility - . Nation: USA. Related Persons: Johnson, Roy. Program: Apollo. Spacecraft: Apollo CSM; CSM Source Selection. Roy W. Johnson, Director of the Advanced Research Projects Agency (ARPA), testified before the House Committee on Science and Astronautics that DOD and ARPA had no lunar landing program. Herbert F. York, DOD Director of Defense Research and Engineering, testified that exploration of the moon was a NASA responsibility.

1959 February 17 - . 15:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18A. Launch Pad: LC18A. LV Family: Vanguard. Launch Vehicle: Vanguard. LV Configuration: Vanguard SLV-4.
  • Vanguard 2 - . Payload: Vanguard 2E / Cloud cover satellite. Mass: 10 kg (22 lb). Nation: USA. Agency: NASA. Program: Vanguard. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Vanguard 2. USAF Sat Cat: 11 . COSPAR: 1959-Alpha-1. Apogee: 3,049 km (1,894 mi). Perigee: 557 km (346 mi). Inclination: 32.9000 deg. Period: 122.80 min. Summary: Operated for 18 days; satellite wobble degraded data..

1960 February 17 - . 01:00 GMT - . Launch Site: Eglin. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun AA6.103C.
  • Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 120 km (70 mi).

1960 February 17 - . 17:41 GMT - . Launch Site: Rosamund Dry Lake DZ. Launch Pad: 34.7 N x 118.1 W. Launch Platform: NB-52 008. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 2-5-12.
  • X-15A SAS Evaluation test - . Nation: USA. Agency: NASA; USAF. Apogee: 16 km (9 mi). Summary: Maximum Speed - 1667 kph. Maximum Altitude - 16045 m. Automatic shutdown of one chamber in upper XLR-11..

1961 February 17 - . 07:17 GMT - . Launch Site: Wallops Island. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache AA5.391.
  • Test mission - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1961 February 17 - . 19:04 GMT - . Launch Site: Eglin. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 AA3.129.
  • Extreme ultraviolet Monochromator Solar extreme ultraviolet mission - . Nation: USA. Agency: USAF. Apogee: 275 km (170 mi).

1961 February 17 - . 20:25 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Delta. Launch Vehicle: Thor Agena B. LV Configuration: Thor Agena B 298.
  • Discoverer 20 - . Payload: KH-5 s/n 9014A / Agena B 1104. Mass: 1,110 kg (2,440 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-5. Decay Date: 1962-07-28 . USAF Sat Cat: 83 . COSPAR: 1961-Epsilon-1. Apogee: 491 km (305 mi). Perigee: 277 km (172 mi). Inclination: 80.8000 deg. Period: 92.30 min. Summary: KH-5; film capsule not ejected. Mission failed. Program malfunctioned and capsule did not reenter. First attempted ARGON mission. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..
  • SRV 520 - . Nation: USA. Agency: USAF. Spacecraft: KH-5. Decay Date: 1961-10-31 . USAF Sat Cat: 90 . COSPAR: 1961-Epsilon-4. Apogee: 327 km (203 mi). Perigee: 321 km (199 mi). Inclination: 80.7000 deg. Period: 91.00 min.

1962 February 17 - .
  • Immediate Vostok launches demanded - . Nation: USSR. Related Persons: Ustinov; Nikolayev; Popovich; Titov. Program: Vostok. Flight: Vostok 3; Vostok 4. Ustinov wants launch of two cosmonauts within a month to answer the American Glenn flight. Of seven candidates, Nikolayev and Popovich are most likely to be selected. Meanwhile Titov has more incidents. He has driven his Volga into a bus. This is his third accident within a year.

1962 February 17 - . 19:43 GMT - . Launch Site: Wallops Island. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.41NP.
  • LeRC LH2 test Technology test - . Nation: USA. Agency: NASA. Apogee: 157 km (97 mi).

1964 February 17 - . 10:00 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 ND3.143.
  • Aeronomy mission - . Nation: USA. Agency: NRL. Apogee: 268 km (166 mi).

1964 February 17 - . 16:15 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 395-B. LV Family: Titan. Launch Vehicle: Titan 2. LV Configuration: Titan II B-15.
  • Research and development test - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1964 February 17 - . 17:03 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 622. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P-257.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1965 February 17 - . LV Family: Titan. Launch Vehicle: Titan 2.
  • Gemini launch vehicle 3 and spacecraft No. 3 were mechanically mated on complex 19. - . Nation: USA. Flight: Gemini 3. The Electrical Interface Integrated Validation Test was completed February 19, the Joint Guidance and Control Test on February 22. Gemini-Titan 3 combined systems testing included the Joint Combined Systems Test on February 24 and the Flight Configuration Mode Test on March 3.

1965 February 17 - .
  • Increase in the Apollo CM's land landing capability - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM Recovery. Summary: North American proposed an idea for increasing the CM's land landing capability. This could be done, the company asserted, by raising the water impact limits (thus exceeding normal tolerances) and stiffening the shock struts.. Additional Details: Increase in the Apollo CM's land landing capability.

1965 February 17 - . 17:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC12. LV Family: Atlas. Launch Vehicle: Atlas Agena B. LV Configuration: Atlas Agena B 196D (AA13) / Agena B 6006 (AA13).
  • Ranger 8 - . Payload: RA-8. Mass: 366 kg (806 lb). Nation: USA. Agency: NASA; JPL. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 6-7-8-9. Decay Date: 1965-02-20 . USAF Sat Cat: 1086 . COSPAR: 1965-010A. Returned 7137 photos before lunar impact. The Atlas- Agena B booster injected the Agena and Ranger 8 into an Earth parking orbit at 185 km altitude 7 minutes after launch. Fourteen minutes later a 90 second burn of the Agena put the spacecraft into lunar transfer trajectory, and several minutes later the Ranger and Agena separated. The Ranger solar panels were deployed, attitude control activated, and spacecraft transmissions switched from the omni-directional antenna to the high-gain antenna by 21:30 GMT. On 18 February at a distance of 160,000 km from Earth the planned mid-course manoeuvre took place, involving reorientation and a 59 second rocket burn. During the 27 minute manoeuvre, spacecraft transmitter power dropped severely, so that lock was lost on all telemetry channels. This continued intermittently until the rocket burn, at which time power returned to normal. The telemetry dropout had no serious effects on the mission. A planned terminal sequence to point the cameras more in the direction of flight just before reaching the Moon was cancelled to allow the cameras to cover a greater area of the Moon's surface.

    Ranger 8 reached the Moon on 20 February 1965. The first image was taken at 9:34:32 GMT at an altitude of 2510 km. Transmission of 7,137 photographs of good quality occurred over the final 23 minutes of flight. The final image taken before impact has a resolution of 1.5 meters. The spacecraft encountered the lunar surface in a direct hyperbolic trajectory, with incoming asymptotic direction at an angle of -13.6 degrees from the lunar equator. The orbit plane was inclined 16.5 degrees to the lunar equator. After 64.9 hours of flight, impact occurred at 09:57:36.756 GMT on 20 February 1965 in Mare Tranquillitatis at approximately 2.67 degrees N, 24.65 degrees E. Impact velocity was slightly less than 2.68 km/s.


1965 February 17 - . 18:44 GMT - . Launch Site: Mud Lake DZ. Launch Pad: 37.9 N x 117.1 W. Launch Platform: NB-52 008. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 2-36-63. FAILURE: Landing skid extends at Mach 4.3..
  • X-15A-2 Stability test - . Nation: USA. Agency: NASA; USAF. Apogee: 29 km (18 mi). Summary: Maximum Speed - 5649 kph. Maximum Altitude - 28986 m. Right main landing gear extended at Mach 4.1; normal landing..

1966 February 17 - .
  • Soviet Lunar Landing Plans - . Nation: USSR. Program: Lunar L3. Flight: Soviet Lunar Landing. Spacecraft: Soyuz 7K-LOK; LK. Kamanin presents his plan to train 5 to 6 crews for the lunar landing mission over a 30 month period. Only experienced cosmonauts, with prior spaceflight experience, will be assigned to these crews. Kamanin lays out for the VVS leadership the complex series of events the cosmonauts will have to complete in the L3 lunar-orbit rendezvous scheme, including transfer between spacecraft of a single lunar landing cosmonaut in free space in lunar orbit. Crews need to be formed immediately, with two cosmonauts per crew - the L3 mission commander, and the second cosmonaut who will land on the moon. In order to accomplish the mission on schedule, a new air regiment needs to be formed, with the necessary flying laboratories, simulators and trainers, space suits, test stands and surface simulators, and other equipment necessary to train the crew for the mission.

1966 February 17 - . LV Family: Titan. Launch Vehicle: Titan 2.
  • The tanking test of Gemini launch vehicle (GLV) 8 was conducted. - . Nation: USA. Flight: Gemini 8. While the launch vehicle was being cleaned up after the test, spacecraft No. 8 Final Systems Test was completed February 23. On February 25, GLV and spacecraft were temporarily mated for an erector-cycling test. The extravehicular support package and life support system were checked out and installed in the spacecraft between February 26 and March 5, while GLV systems were modified and revalidated February 28 to March 3.

1966 February 17 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 644. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3P-14.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1966 February 17 - . Launch Site: Green River. Launch Complex: Green River Pad 2. LV Family: Athena RTV. Launch Vehicle: Athena RTV. LV Configuration: Athena D014.
  • USAF D014 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1966 February 17 - . 08:33 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Diamant A. LV Configuration: Diamant A No. 2.
  • Diapason - . Payload: D-1A. Mass: 19 kg (41 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: D. USAF Sat Cat: 2016 . COSPAR: 1966-013A. Apogee: 2,484 km (1,543 mi). Perigee: 502 km (311 mi). Inclination: 34.1000 deg. Period: 115.80 min. Summary: Scientific satellite 'D-I' launched from Hammaguir (Algeria)..

1966 February 17 - . 09:45 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 395-B. LV Family: Titan. Launch Vehicle: Titan 2. LV Configuration: Titan II B-61.
  • Black Hawk operational test - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1966 February 17 - . 16:16 GMT - . Launch Site: Wallops Island. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.243UE.
  • E / B currents Plasma mission - . Nation: USA. Agency: NASA. Apogee: 186 km (115 mi).

1967 February 17 - . 04:18 GMT - . Launch Site: Fort Churchill. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.163UA.
  • JHU Aurora 5 Aurora mission - . Nation: USA. Agency: NASA. Apogee: 168 km (104 mi).

1968 February 17 - .
  • Soyuz VI cancellation approved. - . Nation: USSR. Related Persons: Mishin; Kozlov; Afanasyev, Sergei. Spacecraft: Soyuz VI. Summary: The NTK General Staff approves Mishin's cancellation fo the 7K-VI. Kozlov has agreed only under duress. The military is opposed to the cancellation, but Afanasyev won't listen to them..

1968 February 17 - . 02:24 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 KP3.22.
  • Stellar ultraviolet Ultraviolet astronomy mission - . Nation: USA. Agency: KPNO. Apogee: 183 km (113 mi).

1969 February 17 - . 20:02 GMT - . Launch Site: Fort Churchill. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.374UI.
  • Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 135 km (83 mi).

1970 February 17 - .
  • Apollo Applications Program redesignated the Skylab Program. - . Nation: USA. Program: Skylab. Spacecraft: Skylab. NASA announced that the Apollo Applications Program had been redesignated the Skylab Program. The name Skylab, a contraction connoting a laboratory in the sky, was proposed by Donald L. Steelman, USAF, while assigned to NASA. The name was proposed following an announcement by NASA in 1968 that they were seeking a new name for AAP. Then NASA decided to postpone renaming the program because of budgetary restrictions. Skylab was later referred to the NASA Project Designation Committee and was approved 17 February 1970.

1971 February 17 - .
  • Management plans for Gagarin Cosmonaut Centre jeopardised. - . Nation: USSR. Related Persons: Mishin; Belyayev; Leonov. Summary: Management of TsPK is in question due to intrigues by Mishin and his allies within the VVS. After the death of Belyayev it was committed that Leonov would become head of the First Directorate of TsPK. This is now in doubt..

1971 February 17 - . Launch Site: Baikonur. Launch Complex: Baikonur LC161/35. LV Family: Tsiklon. Launch Vehicle: R-36 8K67.
  • Operational missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1971 February 17 - . 03:52 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Delta. Launch Vehicle: Thor Burner 2. LV Configuration: Thor Burner 2 249.
  • DMSP-Block-5A F3 - . Payload: DAPP 3526 / OPS 5268. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft: DMSP Block 5A. USAF Sat Cat: 4953 . COSPAR: 1971-012A. Apogee: 799 km (496 mi). Perigee: 741 km (460 mi). Inclination: 98.7000 deg. Period: 100.20 min. Summary: Defense Meteorological Satellite Program..
  • Calsphere 5 - . Payload: NRL PL170C / OPS 5268. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: NRL. Class: Military. Type: Radar calibration target. Spacecraft: Calsphere. Decay Date: 1990-01-07 . USAF Sat Cat: 4963 . COSPAR: 1971-012E. Apogee: 360 km (220 mi). Perigee: 340 km (210 mi). Inclination: 98.2000 deg. Period: 91.50 min. Summary: Radar calibarion sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • Calsphere 3A - . Payload: NRL PL170A / OPS 5268. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: NRL. Class: Military. Type: Radar calibration target. Spacecraft: Calsphere. Decay Date: 1989-10-17 . USAF Sat Cat: 4957 . COSPAR: 1971-012C. Apogee: 531 km (329 mi). Perigee: 509 km (316 mi). Inclination: 98.4000 deg. Period: 95.00 min. Summary: Radar calibarion sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • Calsphere 4 - . Payload: NRL PL170B / OPS 5268. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: NRL. Class: Military. Type: Radar calibration target. Spacecraft: Calsphere. Decay Date: 1989-09-20 . USAF Sat Cat: 4958 . COSPAR: 1971-012D. Apogee: 502 km (311 mi). Perigee: 486 km (301 mi). Inclination: 98.4000 deg. Period: 94.50 min. Summary: Radar calibarion sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1971 February 17 - . 07:25 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF02. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • OLD FOX 05M demonstration and shakedown operations launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1971 February 17 - . 20:04 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Delta. Launch Vehicle: Thorad Agena D SLV-2H. LV Configuration: Thorad SLV-2H Agena D 537 / Agena D 1659. FAILURE: Failure. Failed Stage: U.
  • KH-4B 1113 - . Payload: KH-4B s/n 1113. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-4B. Decay Date: 1971-02-17 . COSPAR: F710217A. KH-4B. The launch vehicle had a very cold boattail due to a hose discovered to be leaking away warming air to the boattail. The boattail was colder than usual, below freezing. Based on earlier tests of the Thor for just that condition, as relayed by Ed Dierdorf, Thor chief engineer at the time, the temp low was of no concern.

    The only problem was that those tests were made with a Thor that carried a Rocketdyne engine lubricated with "lube oil". The Thor being launched used a fuel additive, "Orinite" (like STP "super snot"). The technician that pumped the Orinite into its cannister later stated, "It wasn't for lack of orinite. I put it in just like the procedure said, and I could feel when it was full (with the hand pump). To make sure, I gave it another slug."

    That "other slug" cracked the output valve that was only supposed to be cracked by turbopump output pressure. When it cracked the output valve a bit of the "honey" squirted down the tube toward engine bearing jets. This line had a low spot in it by design. The Orinite settled there. When it was chilled by the low temp air at lox loading, the Orinite formed a plug.

    Unaware of this chain of circumstances, Launch Director Philip Payne made the decision to launch. The rocket (carrying Agena D and payload) flew for 18 seconds, then wiped out its gears, causing the turbine to overspeed and shed its vanes. These punctured various parts in the boattail like machine gun bullets. With loss of power, the rocket fell not far from the launch pad into Bear Creek canyon.

    The final cause was therefore found to be loss of engine lubrication at startup.

  • SRV 825 - . Payload: SRV 1113-1. Nation: USA. Agency: USAF. Spacecraft: KH-4B. COSPAR: F710217B.
  • SRV 826 - . Payload: SRV 1113-2. Nation: USA. Agency: USAF. Spacecraft: KH-4B. COSPAR: F710217C.

1971 February 17 - . 21:09 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 53727-117.
  • Cosmos 395 - . Mass: 875 kg (1,929 lb). Nation: USSR. Agency: MO. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-O. Decay Date: 1980-04-06 . USAF Sat Cat: 4955 . COSPAR: 1971-013A. Apogee: 546 km (339 mi). Perigee: 529 km (328 mi). Inclination: 74.0000 deg. Period: 95.40 min. Summary: Possible ELINT satellite..

1972 February 17 - . 08:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-7.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 118 km (73 mi).

1972 February 17 - . 13:48 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P111H.
  • Faraday rotation Ionosphere mission - . Nation: UK. Agency: SRC. Apogee: 134 km (83 mi).

1973 February 17 - .
  • The Manned Spacecraft Center renamed the Lyndon B Johnson Space Center. - . Nation: USA. Related Persons: Johnson, Lyndon. Program: Apollo. The Manned Spacecraft Center was renamed the Lyndon B. Johnson Space Center by Public Law 93-8. The late President's interest and support of the space program began while he was Chairman of the Senate Committee on Aeronautical and Space Sciences and continued during his tenure as Vice President and President.

1973 February 17 - . 23:57 GMT - . Launch Site: Biscarosse. LV Family: Belier. Launch Vehicle: Dragon 3.
  • FU-211 EIDI-3 Ionosphere mission - . Nation: France. Agency: CNES. Apogee: 460 km (280 mi).

1974 February 17 - . 19:00 GMT - . Launch Site: Koroni. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 79 km (49 mi).

1975 February 17 - . 14:45 GMT - . Launch Site: Thule AFB. Launch Vehicle: Rocketsonde.
  • Starute, AN/DMQ-9- - . Nation: USA. Agency: MRN. Apogee: 73 km (45 mi).

1976 February 17 - . LV Family: Energia; N1.
  • Energia; Buran; Mir; Luch; Potok approved; N1 formally cancelled. - . Nation: USSR. Spacecraft: Buran; Mir; Mir-2; Gamma; Potok; Luch. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On work on Energia-Buran, DOS-7K nos. 7 and 8, Gamma. Geyzer (Potok), and Altair (Luch) and cancellation of the N1' was issued. The design of an improved model of the Salyut DOS-17K space station was authorised as part of the third generation of Soviet space systems in a decree. At that time it was planned that the two stations (DOS-7 and DOS-8) would be equipped with two docking ports at either end of the station and an additional two ports at the sides of the forward small diameter compartment. Luch and Potok were elements of the second generation global command and control system (GKKRS) deployed in the first half of the 1980's. Luch satellites, analogous to the US TDRS, provided communications service to the Mir space station, Buran space shuttle, Soyuz-TM spacecraft, military satellites, and the TsUPK ground control center. They also served to provide mobile fleet communications for the Soviet Navy. Additional Details: Energia; Buran; Mir; Luch; Potok approved; N1 formally cancelled..

1977 February 17 - . 08:30 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA8. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 NASA 13.124UG.
  • JHU UVS (Sirius B) Ultraviolet astronomy mission - . Nation: USA. Agency: NASA. Apogee: 192 km (119 mi).

1977 February 17 - . 14:05 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA8. LV Family: Aerobee. Launch Vehicle: Aerobee 200A. LV Configuration: Aerobee 200A NASA 26.57GG.
  • Ultraviolet astronomy mission - . Nation: USA. Agency: NASA. Apogee: 197 km (122 mi).

1978 February 17 - .
  • Crew module on dock, Palmdale, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft: Columbia.

1978 February 17 - . 16:33 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 53746-312.
  • Cosmos 990 - . Mass: 750 kg (1,650 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-2M. USAF Sat Cat: 10676 . COSPAR: 1978-019A. Apogee: 791 km (491 mi). Perigee: 764 km (474 mi). Inclination: 74.0000 deg. Period: 100.40 min.

1978 February 17 - . 21:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC25C. LV Family: Trident. Launch Vehicle: Trident C-4. LV Configuration: Trident C-4 C4X-14.
  • Test mission - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1979 February 17 - .
  • Fourth SRB firing, Thiokol - . Nation: USA. Program: STS.

1980 February 17 - . Launch Site: Thumba. LV Family: Belier. Launch Vehicle: Centaure 2B. LV Configuration: Centaure 2B ISRO 5.65/C.59.
  • NO Photometer Aeronomy mission - . Nation: India. Agency: ISRO. Apogee: 150 km (90 mi).

1980 February 17 - . 00:40 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-1.
  • Tansei 4 - . Payload: MS T4. Mass: 134 kg (295 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. Decay Date: 1983-05-12 . USAF Sat Cat: 11706 . COSPAR: 1980-015A. Apogee: 608 km (377 mi). Perigee: 517 km (321 mi). Inclination: 38.7000 deg. Period: 95.90 min.

1981 February 17 - . 13:30 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 84 km (52 mi).

1982 February 17 - . 21:56 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 65067-261.
  • Cosmos 1339 - . Mass: 810 kg (1,780 lb). Nation: USSR. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Tsikada. USAF Sat Cat: 13065 . COSPAR: 1982-012A. Apogee: 1,014 km (630 mi). Perigee: 948 km (589 mi). Inclination: 82.9000 deg. Period: 104.70 min. Summary: Civilian naval navigation satellite. Replaced Cosmos 1092..

1983 February 17 - . Launch Site: Baikonur. Launch Complex: Baikonur LC106. LV Family: R-36M. Launch Vehicle: R-36M.
  • Joint flight trials launch - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1984 February 17 - . 20:35 GMT - . Launch Site: Eareckson. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 53 km (32 mi).

1986 February 17 - . 12:34 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 17 - . 21:55 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC36. LV Family: Honest John. Launch Vehicle: Taurus Orion. LV Configuration: Taurus Orion NASA 33.56UE.
  • UM Airglow payload Plasma mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1988 February 17 - . 00:23 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/39. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 346-02. FAILURE: Block DM-2 failure, remained in LEO.. Failed Stage: 4.
  • Cosmos 1917 - . Payload: Glonass s/n 38L. Mass: 1,400 kg (3,000 lb). Nation: USSR. Agency: MOM. Class: Navigation. Type: Navigation satellite. Spacecraft: Glonass . Decay Date: 1988-02-17 . USAF Sat Cat: 18857 . COSPAR: 1988-009A. Apogee: 152 km (94 mi). Perigee: 134 km (83 mi). Inclination: 64.8000 deg. Period: 87.30 min. Triple Glonass launch; three satellites (Cosmos 1917, 1918, 1919) failed to separate. A Proton carrier rocket was put into staging orbit to test components, also apparatus for a space navigation system. The satellites were not put into their designed orbit owing to a malfunction in the separation assembly controls.
  • Cosmos 1918 - . Payload: Glonass s/n 37L. Nation: USSR. Agency: UNKS. Class: Navigation. Type: Navigation satellite. Spacecraft: Glonass. COSPAR: 1988-009xx.
  • Cosmos 1919 - . Payload: Glonass s/n 36L. Nation: USSR. Agency: UNKS. Class: Navigation. Type: Navigation satellite. Spacecraft: Glonass. COSPAR: 1988-009xx.
  • Cosmos 1918 - . Payload: Glonass s/n 37L. Mass: 1,400 kg (3,000 lb). Nation: USSR. Agency: RVSN. Class: Navigation. Type: Navigation satellite. Spacecraft: Glonass. Decay Date: 1988-02-17 . USAF Sat Cat: 18857 . COSPAR: 1988-009B. Apogee: 194 km (120 mi). Perigee: 166 km (103 mi). Inclination: 64.8000 deg. Period: 87.90 min. Triple Glonass launch; three satellites (Cosmos 1917, 1918, 1919) failed to separate. A Proton carrier rocket was put into staging orbit to test components, also apparatus for a space navigation system. The satellites were not put into their designed orbit owing to a malfunction in the separation assembly controls.
  • Cosmos 1919 - . Payload: Glonass s/n 36L. Mass: 1,400 kg (3,000 lb). Nation: USSR. Agency: RVSN. Class: Navigation. Type: Navigation satellite. Spacecraft: Glonass. Decay Date: 1988-02-17 . USAF Sat Cat: 18857 . COSPAR: 1988-009C. Apogee: 194 km (120 mi). Perigee: 166 km (103 mi). Inclination: 64.8000 deg. Period: 87.90 min. Triple Glonass launch; three satellites (Cosmos 1917, 1918, 1919) failed to separate. A Proton carrier rocket was put into staging orbit to test components, also apparatus for a space navigation system. The satellites were not put into their designed orbit owing to a malfunction in the separation assembly controls.

1989 February 17 - . 14:59 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 2003 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Earth. Type: Earth resources satellite. Spacecraft: Zenit-8. Duration: 14.00 days. Decay Date: 1989-03-03 . USAF Sat Cat: 19818 . COSPAR: 1989-015A. Apogee: 255 km (158 mi). Perigee: 244 km (151 mi). Inclination: 62.8000 deg. Period: 89.50 min. Summary: Military cartographic satellite; returned film capsule..

1990 February 17 - . 20:24 GMT - . Launch Site: Andoya. LV Family: Viper. Launch Vehicle: Viper 3A. LV Configuration: Viper 3A Chaff.
  • DYANA DAC42 Aeronomy mission - . Nation: USA. Agency: DLR. Apogee: 90 km (55 mi).

1992 February 17 - . 22:05 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 65078-418.
  • Cosmos 2180 - . Mass: 825 kg (1,818 lb). Nation: Russia. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Parus. USAF Sat Cat: 21875 . COSPAR: 1992-008A. Apogee: 1,014 km (630 mi). Perigee: 960 km (590 mi). Inclination: 82.9000 deg. Period: 104.90 min. Summary: Military navigation satellite. Positioned in plane 6 of constellation..

1993 February 17 - . 20:09 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 362-01.
  • Cosmos 2234 - . Payload: Glonass s/n 73L. Mass: 1,400 kg (3,000 lb). Nation: Russia. Agency: MOM. Class: Navigation. Type: Navigation satellite. Spacecraft: Glonass . USAF Sat Cat: 22512 . COSPAR: 1993-010A. Apogee: 19,152 km (11,900 mi). Perigee: 19,106 km (11,871 mi). Inclination: 64.9000 deg. Period: 675.70 min. Summary: Glonass navigation spacecraft. Work on the Glonass global space navigation system being set up to determine the position of civil aircraft and vessels of the merchant marine and fishing fleet. .
  • Cosmos 2236 - . Payload: Glonass s/n 57L. Mass: 1,400 kg (3,000 lb). Nation: Russia. Agency: MOM. Class: Navigation. Type: Navigation satellite. Spacecraft: Glonass. USAF Sat Cat: 22514 . COSPAR: 1993-010C. Apogee: 19,156 km (11,902 mi). Perigee: 19,104 km (11,870 mi). Inclination: 66.0000 deg. Period: 675.70 min. Glonass navigation spacecraft. Work on the Glonass global space navigation system being set up to determine the position of civil aircraft and vessels of the merchant marine and fishing fleet. Constellation 1. Put into service on 14 March 1993 and taken out of service on 23 August 1997.
  • Cosmos 2235 - . Payload: Glonass s/n 59L. Mass: 1,400 kg (3,000 lb). Nation: Russia. Agency: MOM. Class: Navigation. Type: Navigation satellite. Spacecraft: Glonass. USAF Sat Cat: 22513 . COSPAR: 1993-010B. Apogee: 19,144 km (11,895 mi). Perigee: 19,115 km (11,877 mi). Inclination: 65.9000 deg. Period: 675.70 min. Glonass navigation spacecraft. Work on the Glonass global space navigation system being set up to determine the position of civil aircraft and vessels of the merchant marine and fishing fleet. Constellation 1. Put into service on 25 August 1993 and taken out of service on 4 August 1997.

1995 February 17 - .
  • Mir News 246: Successful docking Progress-M26 at Mir - . Nation: Russia. Program: Mir. Flight: Mir EO-17; Mir LD-4. Freighter Progress-M26 docked at the aft (Kvant-1) docking port of the Mir-complex on 17.02.1995 at 182136 UTC in orb. 51427. Approach and docking took place in the automatic mode with the system Kurs. Viktorenko was ready to take over manually (by TORU) if necessary. He reported the movements of the Progress-M26 which enabled me to monitor the operation until 'kasaniye' (touch, soft docking). For TV-transmissions and phone the Russians used the geostationary Altair. This time the docking was executed in the earth's shadow. A searchlight had been installed on the Progress-M26. During the next orbit (0912 UTC) the crew reported that the airseal was good. It lasted a long time before the crew could enter the Progress-M26 due to some obstructing goods.

    Decay of Progress-M25: Progress-M25 left the aft docking port on 16.02.1995 at 1303 UTC. After two autonomous orbits the Progress-M25 got an impulse at 1606 UTC to enter the dense layers of the atmosphere. She decayed in a for that purpose designated area over the Pacific East of New-Zealand. Progress-M25 did not carry a VBK (ballistic return capsule). The Russians do not equip Progress-M ships with such a capsule if the landing has to take place in the winter.

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


1996 February 17 - . 20:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta 7925-8. LV Configuration: Delta 7925-8 D232.
  • NEAR - . Payload: Discovery 1. Mass: 818 kg (1,803 lb). Nation: USA. Agency: NASA Greenbelt. Program: Discovery. Class: Asteroids. Type: Asteroid probe. Spacecraft: NEAR. Decay Date: 2001-02-12 . USAF Sat Cat: 23784 . COSPAR: 1996-008A. Near Earth Asteroid Rendezvous (NEAR) mission was the first of NASA's Discovery missions, a series of small-scale spacecraft designed to proceed from development to flight in under three years for a cost of less than $150 million. The spacecraft's mission was to rendezvous with and achieve orbit around the asteroid Eros in January 1999, and study the asteroid for one year. However as it flew by the Earth on 23 January 1998, a problem caused an abort of the first encounter burn. The mission had to be rescoped for a later encounter but successfully entered orbit around Eros on Valentine's Day 2000 and ended the mission by gently landing on its surface on 12 February 2001.

1997 February 17 - . 01:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-127.
  • JCSAT 4 - . Nation: Japan. Agency: JSAT. Manufacturer: El Segundo. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 24732 . COSPAR: 1997-007A. Apogee: 35,793 km (22,240 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 150.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 150 deg E in 1997-1998; 124 deg E in 1998-1999; 127 deg E in 1999. As of 5 September 2001 located at 127.02 deg E drifting at 0.015 deg W per day. As of 2007 Mar 7 located at 150.01E drifting at 0.008W degrees per day.

1997 February 17 - . 03:45 GMT - .
  • EVA STS-82-4 - . Crew: Harbaugh; Tanner. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.27 days. Nation: USA. Related Persons: Harbaugh; Tanner. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-82. Spacecraft: Discovery; HST. Summary: Hubble Space Telescope Servicing Mission 2 - Solar array drive replacement..

1998 February 17 - . 10:35 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 2349 - . Payload: Yantar-1KFT s/n 19. Mass: 6,600 kg (14,500 lb). Nation: Russia. Agency: RAKA. Manufacturer: Kozlov. Class: Surveillance. Type: Cartographic satellite. Spacecraft: Yantar-1KFT. Duration: 44.00 days. Decay Date: 1998-04-02 . USAF Sat Cat: 25167 . COSPAR: 1998-009A. Apogee: 327 km (203 mi). Perigee: 212 km (131 mi). Inclination: 70.4000 deg. Period: 89.90 min. Summary: Topographic mapping for the Army General Staff. Landed in Kazakhstan April 2 1998..

1999 February 17 - .
  • ISS Status Report: ISS 99-07 - . Nation: USA. Program: ISS. Summary: Flight control teams in Houston and Moscow continue to work in tandem to monitor the health of systems aboard the two-segment International Space Station.. Additional Details: ISS Status Report: ISS 99-07.

2000 February 17 - .
  • ISS Status Report: ISS 00-07 - . Nation: USA. Program: ISS. Flight: STS-99. As the International Space Station continues to orbit the Earth in good shape, its automatic docking system was tested twice this week without problems in an effort to verify that the system is ready to support the rendezvous with the Zvezda service module this summer. Meanwhile, Space Shuttle and Station managers formally approved the Shuttle visit to the Station to outfit Zvezda for occupancy by the first resident crew. Additional Details: ISS Status Report: ISS 00-07.

2005 February 17 - . Launch Site: Kwajalein. Launch Vehicle: OBV. FAILURE: Launch abort - booster shut down in silo..
  • IFT-14 launch attempt. - . Mass: 55 kg (121 lb). Nation: USA. Agency: MDA. Delayed from October 2004. Missile Defense Technology / EKV Prototype planned intercept attempt. The interceptor failed to leave the silo. As in IFT-13C, Orbital Sciencesí booster, carrying Raytheonís production kill vehicle, was supposed to fly from Kwajalein and hit a target coming out of Kodiak, Alaska. The system shut itself down just a few seconds before launch. Arms that held the interceptor in the silo did not fully retract, and the launch software aborted the mission. MDA failure analysis resulted in a redesign of the launch mechanism and improved quality control.

2005 February 17 - .
  • Cassini, Enceladus Flyby, Successful - . Nation: USA. Spacecraft: Cassini.

2006 February 17 - .
2007 February 17 - . 23:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Delta. Launch Vehicle: Delta 7925. LV Configuration: Delta 7925-10C D323.
  • Themis P1 - . Payload: Themis A. Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30580 . COSPAR: 2007-004A. Apogee: 87,254 km (54,217 mi). Perigee: 1,003 km (623 mi). Inclination: 14.1000 deg. Period: 1,882.70 min. The five simultaneously-launched Time History of Events and Macroscale Interactions during Substorms (THEMIS) satellites were the fifth medium-class mission under NASA's Explorer Program. They formed part of a combined ground- and space- based system designed to determine what physical process in near-Earth space initiate the violent eruptions of the aurora that occur during substorms in the Earth's magnetosphere.
  • Themis P2 - . Payload: Themis B. Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30581 . COSPAR: 2007-004B. Apogee: 87,114 km (54,130 mi). Perigee: 1,004 km (623 mi). Inclination: 14.1000 deg. Period: 1,878.80 min.
  • Themis P3 - . Payload: Themis C. Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30582 . COSPAR: 2007-004C. Apogee: 87,792 km (54,551 mi). Perigee: 736 km (457 mi). Inclination: 14.2000 deg. Period: 1,890.30 min.
  • Themis P4 - . Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30797 . COSPAR: 2007-004D. Apogee: 67,517 km (41,953 mi). Perigee: 4,048 km (2,515 mi). Inclination: 4.6000 deg. Period: 1,435.90 min.
  • Themis P5 - . Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30798 . COSPAR: 2007-004E. Apogee: 67,523 km (41,956 mi). Perigee: 4,045 km (2,513 mi). Inclination: 5.1000 deg. Period: 1,436.00 min.

2008 February 17 - .
  • ISS On-Orbit Status 02/17/08 - . Nation: USA. Related Persons: Eyharts; Frick; Love; Malenchenko; Melvin; Poindexter; Schlegel; Tani; Walheim; Whitson; Yi So-yeon. Program: ISS. Flight: ISS EO-16; ISS EO-16-1; ISS EO-16-2; STS-122. Sunday --- Mission 1E Flight Day 11 (FD11).

    Dan Tani's 118th day in space (116 aboard ISS). Ahead: Week 18 of Increment 16.

    Wake/sleep cycle shifted further back to prepare for 2/18 undocking: 1:45am - 4:15pm EST (incl. Eyharts), Shuttle crew: 1:45am - 4:45pm (incl. Tani).

    CDR Peggy Whitson performed her final INTEGRATED IMMUNE blood collection, assisted by MS1 Leland Melvin, right before hatch closure. FE-2 Dan Tani will continue his saliva collections, both liquid and dry, and blood collections aboard the Atlantis all the way home FE-2-16 Leo Eyharts transferred his and Peggy's saliva return pouches and blood sleeves as well as Dan's saliva collection kit to the Shuttle for return. (Background: IMMUNE assessment, integrated with the Russian IMMUNO, is a 24-hr. test of human immune system changes, with the objective to investigate immune neuro-endocrine reactions in the space environment by studying samples of saliva, blood and urine using collection kits and the biomedical (MBI) protection kit, to develop and validate an immune monitoring strategy consistent with operational flight requirements and constraints. The strategy uses both long and short duration crewmembers as study subjects. The saliva is collected in two forms, dry and liquid. The dry samples are collected at intervals during the collection day using a specialized book that contains filter paper. The liquid saliva collections require that the crewmember soak a piece of cotton inside their mouth and place it in a salivette bag; there are four of the liquid collections during docked operations. The on-orbit blood samples are collected right before undocking and returned on the Shuttle so that analysis can occur with 48 hours of the sampling. This allows assays that quantify the function of different types white blood cells and other active components of the immune system. For cold storage, samples are secured in the MELFI (Minus-Eighty Laboratory Freezer for ISS). Also included are entries in a fluid/medications intact log, and a stress-test questionnaire to be filled out by the subject at begin and end. Urine is collected during a 24-hour period, conventionally divided into two twelve-hour phases: morning-evening and evening-morning.) Additional Details: ISS On-Orbit Status 02/17/08.


2010 February 17 - .
  • EVA STS-130-3 - . Crew: Behnken; Patrick. EVA Type: Extravehicular activity. EVA Duration: 0.24 days. Nation: USA. Program: ISS. Flight: STS-130; ISS EO-22; ISS EO-21. Summary: Installed additional ammonia plumbing between Unity and Tranquility, removed insulation and launch locks from the Cupola, installed additional handrails on the exterior of Tranquility and performed get-ahead tasks to support the installation of a PDGF on .

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