Encyclopedia Astronautica
May 20


May 20 Chronology


1910 May 20 - .
  • Birth of Bernard Brodie - . Nation: USA. Summary: American scientist. Political scientist, specialized in Cold War strategy, member of Rand..

1944 May 20 - .
  • Birth of David Mathieson 'Dave' Walker - . Nation: USA. Summary: American test pilot astronaut. Flew on STS-51-A, STS-30, STS-53, STS-69. Navy nickname Red Flash, a cocky pilot, over-confident in some astronaut's eyes..

1944 May 20 - . Launch Site: Heidelager. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 17686. FAILURE: Failure.
1945 May 20 - .
1949 May 20 - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 33R.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1951 May 20 - .
  • Birth of Thomas Dale 'Tom' Akers - . Nation: USA. Summary: American test pilot mission specialist astronaut. Flew on STS-41, STS-49, STS-61, STS-79..

1952 May 20 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bechar. LV Family: Veronique. Launch Vehicle: Veronique. LV Configuration: Veronique N1. FAILURE: Failure.
  • Test mission - . Nation: France. Agency: LRBA. Apogee: 19 km (11 mi).

1952 May 20 - . 16:06 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 59/TF2.
  • Test / photography / aeronomy mission - . Nation: USA. Apogee: 124 km (77 mi). Summary: Launched 09:06 local time. Reached 103.7 km. Carried composition, photography experiments for Signal Corps Engineering Lab, University of Michigan. V-2 number 58 never launched..

1953 May 20 - . 14:04 GMT - . Launch Site: Holloman. Launch Complex: Holloman A. LV Family: Aerobee. Launch Vehicle: Aerobee RTV-A-1a. LV Configuration: Aerobee RTV-A-1a USAF 36.
  • AF Airglow 3 Aeronomy mission - . Nation: USA. Agency: USAF AFSC. Apogee: 114 km (70 mi). Summary: Sky brightness, day airglow research. Launched at 0704 local time. Reached 114.3 km..

1954 May 20 - . LV Family: R-5. Launch Vehicle: R-5.
  • R-5 radiological warhead handling system demonstrated - . Nation: USSR. The Generator-S radiological warhead for the R-5 was developed in the early 1950's. In order to handle the warhead OKBT Kirov Factory built the shielded manipulator vehicle Objekt 805, which had a total mass of 72 tonnes. Following the demonstration the system was accepted by the military in 1955.

1954 May 20 - . LV Family: R-5; R-7.
  • R-7 full-scale development authorised. - . Nation: USSR. Summary: Council of Soviet Ministers (SM) Decree 956-4088s 'On approval of work on the R-7 ICBM, R-5R, and M5RD missiles' was issued..

1954 May 20 - . Launch Vehicle: Buran; Burya.
  • Soviet government decree for full-scale development of trisonic intercontinental cruise missiles. - . Nation: USSR. Related Persons: Korolev; Isayev; Glushko; Lavochkin; Myasishchev. Program: Navaho. Spacecraft: M-42; M-44. Council of Soviet Ministers (SM) Decree 957-409 'On transfer of intercontinental cruise missile work to the Ministry of Aviation Industry' was issued. Korolev had to place the highest priority on development of the R-7 ICBM. Therefore the final government decree authorised the Lavochkin and Myasishchev aircraft design bureaux to proceed in parallel with full-scale development of trisonic intercontinental cruise missiles. Both missiles would use ramjet engines by Bondaryuk, astronavigation systems by R Chachikyan, inertial navigation systems by G Tolstoysov, and aerodynamics developed by TsAGI (Central Hydrodynamics Institute). Lavochkin's Burya would use rocket booster engines built by Glushko, while Myasishchev's Buran would use Isayev engines. Both missiles were to deliver a nuclear warhead over an 8,500 km range. But the warhead design specified for the Lavochkin missile had a total mass of 2,100 kg, while that for the Myasishchev missile weighed 3,500 kg.

1956 May 20 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral RW30/12. Launch Pad: PAFB. LV Family: Matador. Launch Vehicle: Matador. LV Configuration: Matador GM-11091.
  • Test mission - . Nation: USA. Agency: USAF. Apogee: 12 km (7 mi).

1958 May 20 - .
  • NACA / Air Force Memorandum of Understanding on the DynaSoar I. - . Nation: USA. Spacecraft: DynaSoar. The National Advisory Committee for Aeronautics (NACA) and the Air Force signed a Memorandum of Understanding concerning the principles in the development and testing of the Air Force's Hypersonic Boost Glide Vehicle (Dyna Soar I). The following principles would apply to the project: (1) The project would be conducted as a joint Air Force-NACA project. (2) Overall technical control of the project would rest with the Air Force, acting with the advice and assistance of NACA. (3) Financing of the design, construction, and Air Force test of the vehicles would be borne by the Air Force. (4) Management of the project would be conducted by an Air Force project office within the Directorate of Systems Management, Headquarters, Air Research and Development Command. NACA would provide liaison representation in the project office and provide the chairman of the technical team responsible for data transmission and research instrumentation. (5) Design and construction of the system would be conducted through a negotiated prime contractor. (6) Flight tests of the vehicle and related equipment would be accomplished by NACA, the USAF, and the prime contractor in a combined test program, under the overall control of a joint NACA-USAF committee chaired by the Air Force.

1958 May 20 - .
  • Air Force agreement for NACA participation in the Dyna-Soar program. - . Nation: USA. Spacecraft: Dynasoar. Summary: The Air Force and the National Advisory Committee for Aeronautics signed an agreement for NACA participation in the Dyna-Soar program..

1958 May 20 - .
  • Dynasoar NACA-USAF MOU. - . Nation: USA. Class: Manned. Type: Manned spaceplane. Spacecraft: Dynasoar. Summary: NACA-USAF Memorandum of Understanding signed, "Principles for Participation of NACA in Development and Testing of the Air Force System 464L Hypersonic Boost Glide Vehicle (Dyna-Soar I).".

1958 May 20 - . 04:26 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 2. LV Configuration: Skylark-2 SL05.
  • Photometers Test / aeronomy mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 150 km (90 mi).

1958 May 20 - . 09:43 GMT - . Launch Site: Holloman. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Release 2 Cs / Na Aeronomy mission - . Nation: USA. Agency: USAF. Apogee: 101 km (62 mi).

1960 May 20 - . 15:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC12. LV Family: Atlas. Launch Vehicle: Atlas D. LV Configuration: Atlas D 56D.
  • Research and development test - . Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: Atlas ICBM fired 9,040 statute miles from AMR to Indian Ocean, with operational weight nose cone plus instrumentation, longest known flight of an ICBM to date. Missile attained an apogee of about 1,000 miles..

1961 May 20 - .
  • Vostok 2 discussions - . Nation: USSR. Related Persons: Yazdovskiy; Bushuyev; Feoktistov; Korolev. Program: Vostok. Flight: Vostok 2. Spacecraft: Sever; Vostok. Kamanin, Yazdovskiy, Bushuyev, and Feoktistov fly to Sochi. Korolev arrives on the next flight, and discussions begin on plans for the second Soviet manned spaceflight. Korolev wants a one-day/16-orbit flight, but Kamanin thinks this is too daring and wants a 3 to 4 orbit flight. Korolev rejects this, saying recovery on orbits 2 to 7 is not possible since the solar orientation sensor would not function (retrofire would have to take place in the earth's shadow). But Kamanin believes one day is too big a leap since the effects of sustained zero-G are not known. He finally agrees to a one-day flight, but with the proviso that a manually-oriented retrofire can be an option on orbits 2 to 7 if the cosmonaut is feeling unwell. Korolev reports that the new Sever spacecraft should be ready for flight by the third quarter of 1962. OKB-1 is working hard on the finding solutions to the problems of manoeuvring, rendezvous, and docking in orbit. Kamanin tells Korolev that it would be difficult to recruit and train three-man crews in time to support such an aggressive schedule.

1963 May 20 - .
  • Volynov completes three days in the Vostok 5 hot mock-up. - . Nation: USSR. Related Persons: Volynov. Flight: Vostok 5. Spacecraft: Vostok.

1963 May 20 - . Launch Site: Salto di Quirra. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.137IA.
  • Sodium release Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1963 May 20 - . 02:09 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-2.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 345 km (214 mi).

1964 May 20 - .
  • Birth of Paul William Richards - . Nation: USA. Summary: American engineer mission specialist astronaut. Flew on STS-102..

1964 May 20 - . Launch Site: White Sands. LV Family: Apache. Launch Vehicle: Nike Apache.
  • Noctilucent clouds Aeronomy mission - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1964 May 20 - . Launch Site: Barking Sands. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk-12 Sandia 152-22.
  • Stovepipe Ballistic test - . Nation: USA. Agency: Sandia. Apogee: 142 km (88 mi).

1965 May 20 - . 03:45 GMT - . Launch Site: Baikonur. LV Family: UR-100. Launch Vehicle: UR-100. FAILURE: Failure.
  • State trials missile test - . Nation: USSR. Agency: RVSN. Apogee: 0 km ( mi).

1965 May 20 - . 16:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Delta. Launch Vehicle: Thor Burner 1. LV Configuration: Thor Burner 1 282.
  • DMSP-Block-4A F3 - . Payload: DAPP 12 / OPS 8386. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft: DMSP Block 4A. USAF Sat Cat: 1377 . COSPAR: 1965-038A. Apogee: 731 km (454 mi). Perigee: 503 km (312 mi). Inclination: 98.1000 deg. Period: 97.10 min. Summary: Defense Meteorological Satellite Program..

1966 May 20 - .
  • L1 recovery issues - . Nation: USSR. Program: Lunar L1. Flight: Soyuz 7K-L1 mission 1. Spacecraft: Soyuz 7K-L1. Kamanin discusses with VVS management the huge task of organizing recovery forces that can find and pick up a manned spacecraft returning from the moon anywhere on the earth. Receivers for the spacecraft's homing beacons have to be installed on a fleet of ocean-going vessels and recovery aircraft. This requirement has been known for six years, but nothing has been done yet.

1966 May 20 - . 09:30 GMT - . Launch Site: Nissaki-Karystos. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure CE-19.
  • ESRO C22 / 1 Solar ultraviolet mission - . Nation: Europe. Agency: ESRO. Apogee: 118 km (73 mi).

1966 May 20 - . 09:30 GMT - . Launch Site: Koroni. Launch Complex: Koroni LP1. Launch Platform: RREC. LV Family: Arcas. Launch Vehicle: Boosted Arcas. LV Configuration: Boosted Arcas NASA 15.28GI.
  • Eclipse ionosphere / solar mission - . Nation: USA. Agency: NASA. Apogee: 102 km (63 mi).

1966 May 20 - . 09:41 GMT - . Launch Site: Koroni. Launch Complex: Koroni LP2. LV Family: Arcas. Launch Vehicle: Boosted Arcas. LV Configuration: Boosted Arcas A004.
  • ESRO A23 / 4 Eclipse ionosphere / solar mission - . Nation: Europe. Agency: ESRO. Apogee: 102 km (63 mi).

1966 May 20 - . 10:40 GMT - . Launch Site: Koroni. Launch Complex: Koroni LP2. LV Family: Arcas. Launch Vehicle: Boosted Arcas. LV Configuration: Boosted Arcas A006.
  • ESRO A23 / 6 Eclipse ionosphere / solar mission - . Nation: Europe. Agency: ESRO. Apogee: 103 km (64 mi).

1966 May 20 - . 11:05 GMT - . Launch Site: Koroni. Launch Complex: Koroni LP1. Launch Platform: RREC. LV Family: Arcas. Launch Vehicle: Boosted Arcas. LV Configuration: Boosted Arcas NASA 15.30GI.
  • Eclipse ionosphere / solar mission - . Nation: USA. Agency: NASA. Apogee: 101 km (62 mi).

1966 May 20 - . 11:40 GMT - . Launch Site: Koroni. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure CE-20.
  • ESRO C22 / 2 Solar ultraviolet mission - . Nation: Europe. Agency: ESRO. Apogee: 114 km (70 mi).

1966 May 20 - . 15:10 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.95GS.
  • XRT (2) Solar x-ray mission - . Nation: USA. Agency: NASA. Apogee: 172 km (106 mi).

1966 May 20 - . 19:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC67/22. LV Family: Tsiklon. Launch Vehicle: R-36-O. LV Configuration: R-36O 8K69 U22502 No. 04L.
  • OGCh No. 04L - . Mass: 1,700 kg (3,700 lb). Nation: USSR. Agency: RVSN. Spacecraft: OGCh. COSPAR: U660519A. Summary: Possible suborbital test of FOBS booster or failed FOBS test. Not mentioned as FOBS-related in contemporary CIA assessments..

1966 May 20 - . 19:04 GMT - . Launch Site: Wallops Island. LV Family: Javelin. Launch Vehicle: Javelin. LV Configuration: Javelin NASA 8.44GR.
  • RAE development Radio astronomy mission - . Nation: USA. Agency: NASA. Apogee: 998 km (620 mi).

1966 May 20 - . 23:30 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.92GS.
  • Solar mission - . Nation: USA. Agency: NASA. Apogee: 195 km (121 mi).

1967 May 20 - .
  • LII Soyuz parachute findings - . Nation: USSR. Program: Soyuz; Lunar L1. Flight: Soyuz 1. Spacecraft: Soyuz 7K-OK; Soyuz 7K-L1. The drop of the Soyuz 1 mock-up at Fedosiya was cancelled due to the great likelihood of loss of the spacecraft and the low likelihood of obtaining any new data as a result. The LII assessment of the parachute system has been completed:
    • The likely cause of non-deployment of the primary parachute on Soyuz 1 was insufficient drag force created by the drogue chute to pull it out of the container (the drogue needs to produce 3 tonnes of force, but tests show only 1.1 to 1.8 tonnes of force are being produced at an ambient pressure of 0.67 atmospheres)
    • The reliable operation of the reserve parachute and the drogue parachute at the same time was never demonstrated in trials. The chance of them getting tangled was actually very likely.
    LII's recommended changes:
    • Remove the reserve parachute and have a system of two main parachutes, with landing possible even if one of the main chutes does not deploy
    • Develop through extensive actual testing reliable inflation of the drogue chute
    • Add controls to allow manual parachute deployment by the crew, with appropriate cockpit instruments
    • Increase the jettison time of the heat shield from 60.7 seconds to 100 seconds after parachute deployment to allow the full interval for operation of the automatic landing system.

1967 May 20 - .
  • Contract for three additional Apollo CSMs requested - . Nation: USA. Program: Apollo. Flight: Apollo 204. Spacecraft: Apollo CSM; CSM Block II. MSC notified NASA Hq. that - with the changes defined for the Block II spacecraft following the January 27 Apollo 204 fire and with CSM delivery schedules now reestablished - it was necessary to complete a contract for three additional CSMs requested in 1966. North American Aviation had responded September 15, 1966, to MSC's February 28 request for a proposal, but action on a contract had been suspended because of the AS-204 accident. NASA Hq. on June 27, 1967, authorized MSC to proceed.

1968 May 20 - .
  • Tests to evaluate feasibility of '1+2' Soyuz mission profile. - . Nation: USSR. Related Persons: Volynov; Feoktistov; Khrunov; Yeliseyev. Program: Soyuz. Spacecraft: Soyuz 7K-OK; Yastreb. Volynov conducts tests in a pressurised suit to see if it is possible to go from the SA capsule to the BO living module in a two-man crew transfer scenario. He shows it is not possible - exit from the SA to the BO is very unsafe, there is a good chance of getting stuck in the hatch. This shows it would be difficult or impossible for the spacecraft commander in the SA to go to the assistance of a single cosmonaut attempting to transfer from one Soyuz to another. Feoktistov proposes another alternative - launch of 3 cosmonauts in one Soyuz, one cosmonaut in another. After docking, a single cosmonaut would transfer from one Soyuz to another, but at least a second cosmonaut would be in the BO to assist him in case of difficulties. Two cosmonauts would return in each Soyuz capsule, meeting the reserve parachute mass limitations. This solution also takes care of a problem with the 1+2 scenario, in that it implied a crew consisting of Khrunov and Yeliseyev, but neither has been trained as a spacecraft commander. A crew could consist of Volynov and one of these, but then the problem is that no spacesuit has been fabricated for Volynov, and it requires two months to make one.

1968 May 20 - . 15:00 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.230GS.
  • Ultraviolet solar imager Solar mission - . Nation: USA. Agency: NASA. Apogee: 165 km (102 mi).

1968 May 20 - . 15:51 GMT - . Launch Site: Kiruna. Launch Complex: Kiruna C. LV Family: Belier. Launch Vehicle: Centaure 1. LV Configuration: Centaure 1 CE-38.
  • ESRO C42 / 1 Meteorites mission - . Nation: Europe. Agency: ESRO. Apogee: 135 km (83 mi).

1969 May 20 - .
  • HL-10 Flight 18 - . Crew: Dana. Payload: HL-10 flight 18. Nation: USA. Related Persons: Dana. Program: NASA Lifting Body. Class: Manned. Type: Manned spaceplane. Spacecraft: HL-10. Summary: Maximum Speed - 959 kph. Maximum Altitude - 14970 m. Flight Time - 414 sec..

1969 May 20 - .
  • Apollo 10 trumps Venera missions - . Nation: USSR. Flight: Apollo 10. Summary: Kamanin notes that the Apollo 10 mission is a ten-times greater achievement that the Venera missions being trumpeted by the Soviet media..

1969 May 20 - . Launch Site: Vandenberg. Launch Complex: Vandenberg 395-B. LV Family: Titan. Launch Vehicle: Titan 2. LV Configuration: Titan II B-83.
  • Glory Trip 39T - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). Summary: FOT GT39T Follow-on Test launch.

1969 May 20 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF26. Launch Pad: LF26?. LV Family: Minuteman. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 (64-15525).
  • OT GT9F operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1969 May 20 - . 08:40 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 282 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1969-05-28 . USAF Sat Cat: 3944 . COSPAR: 1969-044A. Apogee: 321 km (199 mi). Perigee: 202 km (125 mi). Inclination: 65.4000 deg. Period: 89.70 min. Summary: High resolution photo reconnaissance satellite; returned film capsule.

1970 May 20 - .
  • Soyuz 9 crew preparations at Baikonur - . Nation: USSR. Related Persons: Nikolayev; Sevastyanov. Program: Soyuz. Flight: Soyuz 9. Soyuz 9 is planned to launch at 24:00. A new feature is that the crews' sleeping hours have been modified to put them in synch with the shifts at ground control over the long mission. The cosmonauts spent all day at Area 17, preparing the flight plan and logs. It is 28 degrees in the shade, and Kamanin plays tennis with the crews in the late afternoon. In the evening the American film 'One Million Years BC' is shown. Kamanin found the struggle between the savages interesting.

1970 May 20 - . 09:20 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 345 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4. Duration: 8.00 days. Decay Date: 1970-05-28 . USAF Sat Cat: 4403 . COSPAR: 1970-039A. Apogee: 296 km (183 mi). Perigee: 153 km (95 mi). Inclination: 52.0000 deg. Period: 89.00 min. Summary: High resolution photo reconnaissance satellite; returned film capsule.

1970 May 20 - . 21:35 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 555 / Agena D 1656.
  • KH-4B 1110 - . Payload: KH-4B s/n 1110 / Agena D 1656 / OPS 4720. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-4B. Decay Date: 1970-06-17 . USAF Sat Cat: 4405 . COSPAR: 1970-040A. Apogee: 247 km (153 mi). Perigee: 162 km (100 mi). Inclination: 83.0000 deg. Period: 88.60 min. Summary: KH-4B. The overall image quality is less than that provided by recent missions and 2,000 feet of S0-349.
  • OPS 8520 - . Payload: EHH B19. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO; USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1974-03-08 . USAF Sat Cat: 4406 . COSPAR: 1970-040B. Apogee: 499 km (310 mi). Perigee: 490 km (300 mi). Inclination: 83.1000 deg. Period: 94.50 min. Summary: Radar monitoring; may or may not have existed!!!..

1971 May 20 - . 22:00 GMT - . Launch Site: Sea-launched. Launch Pad: UNKMR. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 88 km (54 mi).

1972 May 20 - . 09:24 GMT - . Launch Site: Barking Sands. LV Family: Tomahawk Sandia. Launch Vehicle: Terrier Tomahawk. LV Configuration: Terrier Tomahawk Sandia 281-?.
  • LRL ACS-7A (TT-9) X-ray astronomy mission - . Nation: USA. Agency: Sandia. Apogee: 300 km (180 mi).

1972 May 20 - . 15:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4W. LV Family: Titan. Launch Vehicle: Titan 24B. LV Configuration: Titan 24B 24B-4 (3B-35). FAILURE: Failure.
  • OPS 6574 - . Payload: KH-8 no. 35 / Agena D. Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-8. COSPAR: F720520A.
  • SRV-1 - . Payload: SRV-1. Nation: USA. Agency: USAF. Spacecraft: KH-8. COSPAR: F720520B.
  • SRV-2 - . Payload: SRV-2. Nation: USA. Agency: USAF. Spacecraft: KH-8. COSPAR: F720520C.

1973 May 20 - . 01:17 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC43. Launch Vehicle: Rocketsonde.
  • Starute, Datasonde - . Nation: USA. Agency: MRN. Apogee: 61 km (37 mi).

1974 May 20 - . 17:56 GMT - . Launch Site: Wallops Island. Launch Vehicle: Rocketsonde.
  • Chaff - . Nation: USA. Agency: MRN. Apogee: 55 km (34 mi).

1975 May 20 - . 14:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan 3C. LV Configuration: Titan IIIC 23C-7 (3C-25). FAILURE: Transtage gyro platform lost power; attitude control lost; orbit too low.. Failed Stage: G.
  • DSCS II-05 - . Payload: DSCS II F-5 / OPS 9435. Mass: 566 kg (1,247 lb). Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS II. Decay Date: 1975-05-26 . USAF Sat Cat: 7807 . COSPAR: 1975-040A. Apogee: 256 km (159 mi). Perigee: 160 km (90 mi). Inclination: 28.6000 deg. Period: 88.60 min. Summary: Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
  • DSCS II-06 - . Payload: DSCS II F-6 / OPS 9436. Mass: 566 kg (1,247 lb). Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS II. Decay Date: 1975-05-26 . USAF Sat Cat: 7808 . COSPAR: 1975-040B. Apogee: 256 km (159 mi). Perigee: 160 km (90 mi). Inclination: 28.6000 deg. Period: 88.60 min. Summary: Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

1976 May 20 - . 09:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 819 - . Mass: 6,000 kg (13,200 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-2M. Duration: 11.00 days. Decay Date: 1976-06-01 . USAF Sat Cat: 8853 . COSPAR: 1976-045A. Apogee: 293 km (182 mi). Perigee: 207 km (128 mi). Inclination: 64.9000 deg. Period: 89.50 min. Summary: Area survey photo reconnaissance satellite; returned film capsule..

1977 May 20 - .
  • Nose landing gear doors on dock, Palmdale(STA-099) - . Nation: USA. Program: STS.

1978 May 20 - . 13:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. LV Family: Atlas. Launch Vehicle: Atlas Centaur SLV-3D. LV Configuration: SLV-3D Centaur AC-50 / Centaur D-1AR 5030.
  • Pioneer Venus Orbiter - . Payload: Pioneer-Venus 1. Mass: 582 kg (1,283 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Venus. Type: Venus probe. Spacecraft: Pioneer 12. Decay Date: 1992-10-22 . USAF Sat Cat: 10911 . COSPAR: 1978-051A. The Pioneer Venus Orbiter was inserted into an elliptical orbit around Venus on December 4, 1978. After entering orbit around Venus in 1978, the spacecraft returned global maps of the planet's clouds, atmosphere and ionosphere, measurements of the atmosphere-solar wind interaction, and radar maps of 93 percent of the planet's surface. Additionally, the vehicle made use of several opportunities to make systematic UV observations of several comets. From Venus orbit insertion to July 1980, periapsis was held between 142 and 253 km (at 17 degrees north latitude) to facilitate radar and ionospheric measurements. The spacecraft was in a 24 hour orbit with an apoapsis of 66,900 km. Thereafter, the periapsis was allowed to rise (to 2290 km at maximum) and then fall, to conserve fuel. In 1991 the Radar Mapper was reactivated to investigate previously inaccessible southern portions of the planet. In May 1992 Pioneer Venus began the final phase of its mission, in which the periapsis was held between 150 and 250 km until the fuel ran out and atmospheric entry destroyed the spacecraft. With a planned primary mission duration of only eight months, the spacecraft remained in operation until October 8, 1992 when it finally burned up in Venus' atmosphere after running out of propellant.

1980 May 20 - . 09:21 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 47175-116.
  • Cosmos 1181 - . Mass: 810 kg (1,780 lb). Nation: USSR. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Parus. USAF Sat Cat: 11803 . COSPAR: 1980-039A. Apogee: 1,004 km (623 mi). Perigee: 969 km (602 mi). Inclination: 82.9000 deg. Period: 104.80 min. Summary: Military navigation satellite..

1981 May 20 - . 14:00 GMT - . Launch Site: Molodezhnaya. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 78 km (48 mi).

1982 May 20 - . 13:09 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC41/1. LV Family: R-7. Launch Vehicle: Molniya 8K78M.
  • Cosmos 1367 - . Payload: Oko #26. Mass: 1,250 kg (2,750 lb). Nation: USSR. Agency: MOM. Class: Military. Type: Early warning satellite. Spacecraft: Oko. USAF Sat Cat: 13205 . COSPAR: 1982-045A. Apogee: 35,764 km (22,222 mi). Perigee: 4,640 km (2,880 mi). Inclination: 67.9000 deg. Period: 718.80 min. Summary: Covered Oko constellation plane 1 - 276 degree longitude of ascending node..

1983 May 20 - . 07:40 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: MUSSON. Launch Vehicle: MMR-06.
  • Aeronomy mission - . Nation: USSR. Agency: GMS. Apogee: 60 km (37 mi).

1985 May 20 - . 18:22 GMT - . Launch Site: Wallops Island. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 74 km (45 mi).

1986 May 20 - . 16:45 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 659. Launch Vehicle: Poseidon.
  • Demonstration and shakedown operations launch - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1987 May 20 - . 11:40 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: VOKV. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 86 km (53 mi).

1991 May 20 - . 07:30 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC36. Launch Vehicle: Aries. LV Configuration: Aries NASA 24.11CH.
  • SXT / XOGS X-ray astronomy mission - . Nation: USA. Agency: NASA. Apogee: 300 km (180 mi).

1992 May 20 - . 00:30 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. Launch Vehicle: ASLV. LV Configuration: ASLV ASLV-D3. FAILURE: Insufficient spin stabilization of fifth stage. Partial Failure.. Failed Stage: 5.
  • SROSS 3 - . Payload: SROSS C. Mass: 106 kg (233 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SROSS. Decay Date: 1992-07-14 . USAF Sat Cat: 21968 . COSPAR: 1992-028A. Apogee: 436 km (270 mi). Perigee: 251 km (155 mi). Inclination: 46.0000 deg. Period: 91.40 min. Stretched Rohini Satellite Series; carried gamma-ray detector, ionosphere monitor. SROSS-C satellite carries two scientific payloads: 1) Retarding Potential Analyser (RPA), consisting of two planar detectors to measure plasma parameters and investigate energetics of the equatorial ionosphere. (2) Gamma Ray Burst (GRB) detectors, consist ing of two scintillation detectors to study celestial gamma ray bursts in the energy range of 20 keV to 3000 keV. Launch vehicle: Augmented Satellite Launch Vehicle.

1993 May 20 - . 13:44 GMT - . Launch Site: Wallops Island. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 84 km (52 mi).

1994 May 20 - . 02:01 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 357-01.
  • Gorizont 30 - . Payload: Gorizont s/n 42L. Mass: 2,125 kg (4,684 lb). Nation: Russia. Agency: MOM. Class: Communications. Type: Civilian communications satellite. Spacecraft: Gorizont . USAF Sat Cat: 23108 . COSPAR: 1994-030A. Apogee: 35,833 km (22,265 mi). Perigee: 35,800 km (22,200 mi). Inclination: 4.8000 deg. Period: 1,437.60 min. Stationed at 142.5 deg E as 'Rimsat-2' - leased to Rimsat Corporation, using an orbital slot allocated to Tonga. Communications satellite intended for use under commercial conditions. Positioned in geosynchronous orbit at 142 deg E in 1994-1997; 122 deg E in 1997-1999; 142 deg E in 1999. As of 5 September 2001 located at 142.86 deg E drifting at 0.016 deg W per day. As of 2007 Mar 9 located at 173.22W drifting at 0.132W degrees per day.

1995 May 20 - . 03:33 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K. LV Configuration: Proton-K 378-02.
  • Spektr - . Payload: 77KSO s/n 17301. Mass: 19,640 kg (43,290 lb). Nation: Russia. Agency: MOM. Program: Mir. Class: Manned. Type: Manned space station. Flight: Mir EO-18. Spacecraft: Spektr. Decay Date: 2001-03-23 . USAF Sat Cat: 23579 . COSPAR: 1995-024A. Apogee: 335 km (208 mi). Perigee: 221 km (137 mi). Inclination: 51.6800 deg. Period: 89.78 min. Summary: MIR experiment module. Docked to Mir Jun 1
    Officially: Docked to Mir Jun 1 .

1997 May 20 - . 07:07 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC45/1. LV Family: Zenit. Launch Vehicle: Zenit-2. FAILURE: Strut in first stage engine failed at T+48 seconds.. Failed Stage: 1.
  • Heavy ELINT - . Payload: Tselina-2 no. 21. Nation: Russia. Agency: VKS. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-2. COSPAR: F970520A.

1997 May 20 - . 22:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta 7925. LV Configuration: Delta 7925 D243.
  • Thor 2 - . Payload: Thor 2A. Nation: Norway. Agency: Telenor. Manufacturer: El Segundo. Program: Thor Comsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 24808 . COSPAR: 1997-025A. Apogee: 35,793 km (22,240 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Geosynchronous. Stationed over 0.8W Positioned in geosynchronous orbit at 1 deg W in 1997-1999 As of 5 September 2001 located at 0.73 deg W drifting at 0.000 deg E per day. As of 2007 Mar 9 located at 0.76W drifting at 0.002W degrees per day..

1998 May 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1999 May 20 - . 22:30 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K/DM-2M. LV Configuration: Proton-K/DM-2M (DM3) 396-02.
  • Nimiq 1 - . Nation: Canada. Agency: Telesat. Manufacturer: Lockheed. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 25740 . COSPAR: 1999-027A. Apogee: 35,801 km (22,245 mi). Perigee: 35,772 km (22,227 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Telesat Canada's Nimiq television broadcasting satellite was placed into a 7050 km x 35790 km x 15.9 degree transfer orbit. The Nimiq was to use its liquid apogee engine (Royal Ordnance Leros 1) to reach geosynchronous orbit. Telesat Canada also operated the Anik Canadian domestic communications satellites, the first of which was launched in 1972. Positioned in geosynchronous orbit at 91 deg W in 1999. As of 4 September 2001 located at 91.11 deg W drifting at 0.002 deg W per day. As of 2007 Mar 9 located at 91.18W drifting at 0.012W degrees per day.

2000 May 20 - .
  • Galileo, Ganymede 28 Flyby - . Nation: USA. Spacecraft: Galileo.

2001 May 20 - . 22:32 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz FG. LV Configuration: Soyuz-FG F15000-001?.
  • Progress M1-6 - . Payload: Progress M1 s/n 255. Mass: 7,250 kg (15,980 lb). Nation: Russia. Agency: RAKA. Manufacturer: Korolev. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Flight: ISS EO-2. Spacecraft: Progress M1. Duration: 93.44 days. Decay Date: 2001-08-22 . USAF Sat Cat: 26773 . COSPAR: 2001-021A. Apogee: 402 km (249 mi). Perigee: 391 km (242 mi). Inclination: 51.6000 deg. Period: 92.50 min. ISS Servicing flight. Launch delayed from april 12. This Progress resupply mission to the ISS was launched by the first Soyuz-FG rocket - a modified Soyuz-U with 5 percent improved perfomance using new fuel utilisation systems. Progress M1-6 after launch was also designated as ISS supply mission 4P. It carried 2.5 tonnes of food, fuel, water, life-support material, and equipment, including spare computer equipment for the ISS Destiny module. Nearly one tonne of the fuel was for raising the altitude of the ISS. Progress M1-6 docked with Zvezda's aft (-Y) port at 0024 GMT on May 23. It undocked at 0601 GMT on August 22 and deorbited at around 0900 GMT the same day.

2003 May 20 - . Launch Site: Mojave. Launch Complex: Mojave RW12/30. Launch Platform: W-Knight. Launch Vehicle: Tier One.
  • White Knight/SpaceShipOne Flight 24C / 01C - . Nation: USA. Related Persons: Binnie; Siebold. Agency: Scaled. Program: X-Prize. Spacecraft: SpaceShipOne. Apogee: 14 km (8 mi). Objectives: First captive carry flight with mated White Knight and SpaceShipOne. Vibration and aerodynamic interface assessment. Mated handling qualities evaluation. Envelope expansion to 130 knots / Mach 0.5 above 45,000 feet. Stalls and 2/3-rudder sideslips. SpaceShipOne systems inactive, controls locked and cabin unmanned. Launch system was qualified and functional for this flight. Additional Details: White Knight/SpaceShipOne Flight 24C / 01C.

2004 May 20 - . 17:47 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Pegasus. Launch Vehicle: Taurus 3210. LV Configuration: Taurus 3210 T7 (XL).
  • ROCSAT 2 - . Payload: LeoStar 500XO. Mass: 760 kg (1,670 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: EADS Astrium. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft: ROCSAT. USAF Sat Cat: 28254 . COSPAR: 2004-018A. Apogee: 891 km (553 mi). Perigee: 887 km (551 mi). Inclination: 99.1000 deg. Period: 102.80 min. Summary: Delayed from October, November 25, 2003; January 17, February 26, April 9 and 22, May 17, 2004..

2005 May 20 - .
  • Richard Feynman Postage Stamp Released - . Nation: USA.

2005 May 20 - . 10:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Delta. Launch Vehicle: Delta 7320-XC. LV Configuration: Delta 7320-10C D312.
  • NOAA 18 - . Payload: NOAA-N. Mass: 1,420 kg (3,130 lb). Nation: USA. Agency: NOAA. Manufacturer: Lockheed. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Advanced Tiros N. USAF Sat Cat: 28654 . COSPAR: 2005-018A. Apogee: 866 km (538 mi). Perigee: 847 km (526 mi). Inclination: 98.7000 deg. Period: 102.10 min. Summary: Delayed from June 30, 2004, February 12, March 10 and 19, May 11, 12, 13 and 14..

2006 May 20 - .
  • Cassini, Titan Flyby - . Nation: USA. Spacecraft: Cassini.

2008 May 20 - .
  • ISS On-Orbit Status 05/20/08 - . Nation: USA. Related Persons: Kononenko, O D; Reisman; Volkov, Sergey. Program: ISS. Flight: ISS EO-16-3; ISS EO-17; STS-124. CDR Volkov and FE-1 Kononenko had several hours between them for Progress 29P unloading and cargo transfers, while logging movements in the IMS (Inventory Management System).

    FE-2 Reisman meanwhile spent 2.5 hrs in the US Airlock (A/L) completing the previously initiated EVA tool configuration in preparation for the STS-124/1J spacewalks.

    Later, Reisman used the G1 video camcorder to take documentary footage of the EVA tools in their final configuration and the current state of the A/L, including mini workstations and contents of the ORU bags to be used, for review by EVA specialists on the ground.

    With the SSRMS (Space Station Remote Manipulator System) powered up and the VDS (Video Distribution Subsystem) configured by ground commanding, the FE-2 conducted the pre-launch checkout of the RWS (Robotics Workstations). Additional Details: ISS On-Orbit Status 05/20/08.


2009 May 20 - . Launch Site: Semnan. LV Family: Seijil. Launch Vehicle: Seijil. LV Configuration: Sejjil-2.
  • Missile test - . Nation: Iran. Apogee: 800 km (490 mi). Summary: Test.

2010 May 20 - . 21:58 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Hayato - . Payload: K-SAT. Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Spacecraft: Cubesat. Decay Date: 2010-06-28 . USAF Sat Cat: 36573 . COSPAR: 2010-020A. Apogee: 172 km (106 mi). Perigee: 166 km (103 mi). Inclination: 30.0000 deg. Period: 87.90 min. Summary: Cubesat for Kagoshima University, released in parking orbit..
  • Waseda-SAT2 - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Surveillance satellite. Spacecraft: Cubesat. Decay Date: 2010-07-12 . USAF Sat Cat: 36574 . COSPAR: 2010-020B. Apogee: 183 km (113 mi). Perigee: 177 km (109 mi). Inclination: 30.0000 deg. Period: 88.10 min. Summary: Cubesat for Waseda University, Tokyo, released in parking orbit..
  • Negai - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Surveillance satellite. Spacecraft: Cubesat. Decay Date: 2010-06-26 . USAF Sat Cat: 36575 . COSPAR: 2010-020C. Apogee: 190 km (110 mi). Perigee: 176 km (109 mi). Inclination: 30.0000 deg. Period: 88.20 min. Summary: Cubesat for Soka University, Tokyo, released in parking orbit..
  • Akatsuki - . Payload: Planet-C. Mass: 320 kg (700 lb). Nation: Japan. Agency: Mitsubishi. Class: Venus. Type: Venus probe. Spacecraft: Akatsuki. USAF Sat Cat: 36576 . COSPAR: 2010-020D. Summary: Venus-orbiting weather satellite with visible, infrared and ultraviolet cameras. Reached Venus on 6 December 2010 but the main engine malfunctioned, preventing the braking burn into Venus orbit. The spacecraft sailed past Venus into solar orbit..
  • Ikaros - . Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Solar sail technology satellite. Spacecraft: Ikaros. USAF Sat Cat: 36577 . COSPAR: 2010-020E. Solar sail test vehicle. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg. Deployed sail by 11 June, and acceleration due to the pressure of the light from the sun was as expected. Flyby of Venus at 80,000 km distance at 07:39 GMT on 8 December 2010 returned images of sail with crescent Vensu in the background.
  • Unitec-1 - . Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Technology satellite. Spacecraft: Unitec. USAF Sat Cat: 36578 . COSPAR: 2010-020F. Summary: Space qualification of university-built computers. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg..

2011 May 20 - .
  • EVA STS-134-1 - . Crew: Feustel; Chamitoff. EVA Type: Extravehicular activity. EVA Duration: 0.26 days. Nation: USA. Program: ISS. Flight: STS-134; ISS EO-27. Summary: Retrueved MISSE 7 experiments and replaced them with MISSE 8, and performed maintenance on the station exterior..

2011 May 20 - . Launch Site: Barents Sea Launch Area. Launch Platform: K-84. LV Family: R-29. Launch Vehicle: Sineva.
  • 4 x RV - . Nation: Russia. Summary: Operational test..

2011 May 20 - . 13:21 GMT - . Launch Site: SWRS. LV Family: SpaceLoft. Launch Vehicle: SpaceLoft XL.
  • SL-5 - . Nation: USA. Summary: Education/burial mission.

2011 May 20 - . 19:15 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/39. LV Family: Proton. Launch Vehicle: Proton/Briz M. LV Configuration: Proton-M/Briz-M.
  • Telstar 14R - . Mass: 4,970 kg (10,950 lb). Nation: USA. Program: Telstar. Class: Communications. Type: Communications satellite. Spacecraft: FS-1300. COSPAR: 2011-021A. Apogee: 35,798 km (22,243 mi). Perigee: 35,776 km (22,230 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Ku-band direct-broadcast satellite providing satellite television to Brazil. Failed to fully deploy one of its solar arrays..

2011 May 20 - . 20:38 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • Gsat 8 - . Payload: Insat-3000. Mass: 3,150 kg (6,940 lb). Nation: India. Program: Insat. Class: Communications. Type: Communications satellite. Spacecraft: Insat 3. COSPAR: 2011-022A. Apogee: 35,816 km (22,254 mi). Perigee: 35,757 km (22,218 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Communications satellite with a GAGAN navigation payload..
  • ST-2 - . Mass: 5,090 kg (11,220 lb). Nation: Japan. Program: ST. Class: Communications. Type: Communications satellite. Spacecraft: DS2000. COSPAR: 2011-022B. Apogee: 35,793 km (22,240 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Singapore-Taiwan 2 communications satellite with both C and Ku band transmitters..

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