Encyclopedia Astronautica
May 30


May 30 Chronology


1913 May 30 - .
  • Birth of Dean E Wooldridge - . Nation: USA. Summary: American engineer, co-founder of TRW in 1953, director of TRW STL 1962-on..

1915 May 30 - .
  • Birth of Jerome B Wiesner - . Nation: USA. Summary: American scientist. Physicist, gadfly, science advisor to Presidents Eisenhower and Kennedy; opposed human spaceflight, the Apollo program, and the lunar orbit rendezvous method of lunar landing..

1934 May 30 - .
  • Birth of Aleksei Arkhipovich Leonov - . Nation: Russia. Summary: Russian pilot cosmonaut. Flew on Voskhod 2, Soyuz 19 (ASTP). First person to walk in space. Flew in first USA/USSR docking mission. Cancelled missions included first Soviet circumlunar flight and first military space station mission..

1943 May 30 - . Launch Site: Heidelager. LV Family: V-2. Launch Vehicle: V-2.
  • V-2 firing range to be established in Poland. - . Nation: Germany. Related Persons: von Braun. It is decided to move testing of production V-2s and training of combat launch crews from the Baltic Sea to the middle of Poland, at Heidelager, near Blizna. German units here operationally test fired over 100 V-2's, launching 10 on one day, only a small number of which were fully successful.

1944 May 30 - . Launch Site: Heidelager. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 17771.
  • V-2 C07 G1 - . Nation: Germany. Summary: Impact 13.1 km to the right of the planned trajectory..

1947 May 30 - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: Hermes. Launch Vehicle: Hermes B-1. LV Configuration: Hermes B-1 B-1 No. 0. FAILURE: Failure.
  • Hermes II test - . Nation: USA. Agency: USA. Apogee: 50 km (31 mi). Hermes B-1 impacts a graveyard 18.5 km south of Juarez, Mexico on its first test flight. This and the out-of-range V-2 impact on 15 May resulted in new safety measures at WSPG. 'We were the first German unit to not only infiltrate the United States, but to attack Mexico from US soil'. This vehicle was deeply classified at the time. Hermes experiments were conducted with modified V-2 rockets to test the configuration of a ramjet propulsion system. Four Hermes B-1 rockets were flown from Complex 33, none of which were noted in the contemporary records.

1954 May 30 - . Launch Site: Baikonur. LV Family: R-7. Launch Vehicle: R-7.
  • Go-ahead for R-7 ICBM by designers council - . Nation: USSR. Summary: Council of Chief designers approval to proceed with development of R-7..

1955 May 30 - .
  • Korolev rehabilitated. - . Nation: USSR. Related Persons: Korolev. Summary: Seventeen years after his arrest, and after ten years as head of the Soviet rocketry program, Korolev's arrest and imprisonment during Stalin's purges are rescinded..

1957 May 30 - .
  • Birth of Michael Warren Booen - . Nation: USA. Summary: American engineer military spaceflight engineer astronaut, 1982-1987..

1958 May 30 - .
1959 May 30 - . 21:42 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: R-7. LV Configuration: R-7 No. IZ-22. FAILURE: Failure.
  • GCh No. IZ-22 (III) test - . Nation: USSR. Agency: MVS. Apogee: 1,000 km (600 mi). Summary: Landed far from aim point..

1960 May 30 - .
  • Korolev space development plan - . Nation: USSR. Related Persons: Chelomei; Korolev; Yangel. Spacecraft: Kosmoplan. Summary: Korolev revised his earlier, disapproved plan with one that now included participation of his rivals, Chelomei and Yangel..

1961 May 30 - . 05:15 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 2. LV Configuration: Skylark-2 SL25.
  • Test mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 149 km (92 mi).

1962 May 30 - . 01:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Delta. Launch Vehicle: Thor Agena B. LV Configuration: Thor Agena B 336 / Agena B 1128.
  • KH-4 9035 - . Payload: KH-4 s/n 9035 / Agena B 1128. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-4. Decay Date: 1962-06-11 . USAF Sat Cat: 302 . COSPAR: 1962-Phi-1. Apogee: 350 km (210 mi). Perigee: 192 km (119 mi). Inclination: 74.1000 deg. Period: 89.90 min. Summary: KH-4; film capsule recovered 3.1 days later. Slight corona static on film..

1963 May 30 - .
  • Birth of Helen Patricia 'Lenochka' Sharman - . Nation: UK. Summary: British engineer cosmonaut. Flew on Mir Juno. Chemist. First British astronaut. First non-American, non-Soviet female astronaut..

1963 May 30 - . Launch Site: CELPA. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure C39.
  • Aeronomy mission - . Nation: France. Agency: CNES. Apogee: 150 km (90 mi).

1963 May 30 - . Launch Site: CELPA. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure C36.
  • Aeronomy mission - . Nation: France. Agency: CNES. Apogee: 150 km (90 mi).

1964 May 30 - . Launch Site: Baikonur. LV Family: R-16. Launch Vehicle: R-16U.
  • Operational test launch - . Nation: USSR. Agency: RVSN. Apogee: 1,210 km (750 mi).

1964 May 30 - . 02:30 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC67/22. LV Family: Tsiklon. Launch Vehicle: R-36 8K67.
  • Kura state trials missile launch - . Nation: USSR. Agency: RVSN. Apogee: 864 km (536 mi).

1964 May 30 - . 04:02 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC90/19. LV Family: UR-200. Launch Vehicle: UR-200.
  • State trials missile test - . Nation: USSR. Agency: RVSN. Apogee: 695 km (431 mi).

1965 May 30 - . 20:00 GMT - . Launch Site: Rarotonga. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-74.
  • LASL Eclipse Solar x-ray mission - . Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi).

1965 May 30 - . 20:00 GMT - . Launch Site: Rarotonga. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-76.
  • LASL Eclipse Solar x-ray mission - . Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi).

1965 May 30 - . 20:00 GMT - . Launch Site: Rarotonga. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-75.
  • LASL Eclipse Solar x-ray mission - . Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi).

1965 May 30 - . 20:00 GMT - . Launch Site: Rarotonga. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-77.
  • LASL Eclipse Solar x-ray mission - . Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi).

1965 May 30 - . 20:00 GMT - . Launch Site: Rarotonga. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-78.
  • LASL Eclipse Solar x-ray mission - . Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi).

1966 May 30 - . 14:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. LV Family: Atlas. Launch Vehicle: Atlas Centaur D. LV Configuration: Atlas Centaur D AC-10 / Centaur D 290D.
  • Surveyor 1 - . Payload: Surveyor SC-1. Mass: 269 kg (593 lb). Nation: USA. Agency: NASA; JPL. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. Decay Date: 1966-06-02 . USAF Sat Cat: 2185 . COSPAR: 1966-045A. Surveyor 1 soft landed on the moon in the Ocean of Storms and began transmitting the first of more than 11,150 clear, detailed television pictures to Jet Propulsion Laboratory's Deep Space Facility, Goldstone, Calif. The landing sequence began 3,200 kilometers above the moon with the spacecraft traveling at a speed of 9,700 kilometers per hour. The spacecraft was successfully slowed to 5.6 kilometers per hour by the time it reached 4-meter altitude and then free-fell to the surface at 13 kilometers per hour. The landing was so precise that the three footpads touched the surface within 19 milliseconds of each other, and it confirmed that the lunar surface could support the LM. It was the first U.S. attempt to soft land on the moon.

1967 May 30 - . 02:06 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout B. LV Configuration: Scout B S152C. FAILURE: Third stage failure.. Failed Stage: 3.
  • ESRO 2A - . Payload: Iris 1. Mass: 74 kg (163 lb). Nation: Europe. Agency: ESRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: ESRO. Decay Date: 1967-05-29 . COSPAR: F670530A.

1968 May 30 - .
  • Soviet of the Chief Designers. - . Nation: USSR. Related Persons: Feoktistov; Ustinov; Mishin; Beregovoi; Volynov; Shatalov. Program: Soyuz. Spacecraft: Soyuz 7K-OK. Mishin still wants to eventually conduct a 2+2 mission, but now wants the flight in August to be a 0+1 test flight. In this he is supported by Keldysh and Ustinov. He wants Feoktistov to be the pilot. Kamanin is adamantly opposed and offers him Beregovoi, Volynov, or Shatalov.

1968 May 30 - . 13:32 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Aeronomy mission - . Nation: USSR. Agency: AN. Apogee: 172 km (106 mi).

1968 May 30 - . 20:29 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/1. LV Family: Kosmos 2. Launch Vehicle: Kosmos 11K63.
  • Cosmos 222 - . Payload: DS-P1-Yu s/n 12. Mass: 325 kg (716 lb). Nation: USSR. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft: DS-P1-Yu. Completed Operations Date: 1968-10-12 . Decay Date: 1968-10-11 . USAF Sat Cat: 3272 . COSPAR: 1968-044A. Apogee: 488 km (303 mi). Perigee: 285 km (177 mi). Inclination: 70.9000 deg. Period: 92.30 min. Summary: Development of systems for air defence and the control of outer space..

1968 May 30 - . 21:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Auroral mission - . Nation: USSR. Agency: AN. Apogee: 168 km (104 mi).

1969 May 30 - . Launch Site: Biscarosse. Launch Complex: Biscarosse BLB. LV Family: SSBS. Launch Vehicle: SSBS S02. LV Configuration: SSBS S02 V3.
  • S02V-3 test - . Nation: France. Agency: DMA. Apogee: 1,000 km (600 mi).

1969 May 30 - . 08:51 GMT - . Launch Site: Fort Churchill. LV Family: Javelin. Launch Vehicle: Javelin. LV Configuration: Javelin CRL AF19.291.
  • B field Plasma mission - . Nation: USA. Agency: USAF. Apogee: 825 km (512 mi).

1970 May 30 - .
  • Soyuz 9 final inspection. - . Nation: USSR. Related Persons: Nikolayev; Sevastyanov; Mishin. Program: Soyuz. Flight: Soyuz 9. Spacecraft: Soyuz 7K-OK. The backup crews were to train in the Soyuz 9 spacecraft from 10:00, followed by the prime crew at 12:00, but Mishin didn't allow the backups to start until 11:00. Inspectors have found 15 discrepancies in the spacecraft, 3 to 4 of them serious (including incorrect mounting of the crew head rests, unusable photographic equipment).

1970 May 30 - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576A3. LV Family: Atlas. Launch Vehicle: Atlas/Trident F. LV Configuration: Atlas F/Trident 91F.
  • RMP-B-17 re-entry vehicle test flight - . Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).

1971 May 30 - . 22:23 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas Centaur SLV-3C. LV Configuration: SLV-3C Centaur AC-23 / Centaur D-1A 5404C.
  • Mariner 9 - . Payload: Mariner 71J. Mass: 974 kg (2,147 lb). Nation: USA. Agency: NASA; JPL. Program: Mariner. Class: Mars. Type: Mars probe. Spacecraft: Mariner 8-9. USAF Sat Cat: 5261 . COSPAR: 1971-051A. The first spacecraft to orbit another planet. The Mariner Mars 71 mission was planned to consist of two spacecraft on complementary missions. Mariner 8 was to map 70 % of the Martian surface and Mariner 9 was to study temporal changes in the Martian atmosphere and on the Martian surface. The launch failure of Mariner 8 forced Mariner 9 to combine the mission objectives of both. For the survey portion of the mission, the planetary surface was to be mapped with the same resolution as planned for the original mission, although the resolution of pictures of the polar regions would be decreased due to the increased slant range. The variable features experiments were changed from studies of six given areas every 5 days to studies of smaller regions every 17 days. Mariner 9 was launched on a direct trajectory to Mars. Separation from the booster occurred at 22:36 GMT. The four solar panels were deployed at 22:40 GMT. The sensors locked onto the Sun at 23:16, shortly after the spacecraft left the Earth's shadow and Canopus acquisition was achieved at 02:26 GMT 31 May. A planned midcourse maneuver was executed on 5 June. Mariner 9 arrived at Mars on 14 November 1971 after a 167 day flight. A 15 minute 23 second rocket burn put the spacecraft into Mars orbit. The insertion orbit had a periapsis of 1398 km and a period of 12 hr, 34 min. Two days later a 6 second rocket burn changed the orbital period to just under 12 hours with a periapsis of 1387 km. A correction trim maneuver was made on 30 December on the 94th orbit which raised the periapsis to 1650 km and changed the orbital period to 11:59:28 so that synchronous data transmissions could be made to the Goldstone 64-m DSN antenna.

    Imaging of the surface of Mars by Mariner 9 was delayed by a dust storm which started on 22 September 1971 in the Noachis region. The storm quickly grew into one of the largest global storms ever observed on Mars. By the time the spacecraft arrived at Mars no surface details could be seen except the summits of Olympus Mons and the three Tharsis volcanoes. The storm abated through November and December and normal mapping operations began. The spacecraft gathered data on the atmospheric composition, density, pressure, and temperature and also the surface composition, temperature, gravity, and topography of Mars. A total of 54 billion bits of scientific data were returned, including 7329 images covering the entire planet. After depleting its supply of attitude control gas, the spacecraft was turned off on 27 October 1972. Mariner 9 was left in an orbit which should not decay for at least 50 years, after which the spacecraft will enter the Martian atmosphere.

    The Mariner 9 mission resulted in a global mapping of the surface of Mars, including the first detailed views of the martian volcanoes, Valles Marineris, the polar caps, and the satellites Phobos and Deimos. It also provided information on global dust storms, the gravity field as well as evidence for surface aeolian activity.


1972 May 30 - . 21:26 GMT - . Launch Site: Point Mugu. Launch Vehicle: Rocketsonde.
  • Starute, Datasonde - . Nation: USA. Agency: MRN. Apogee: 58 km (36 mi).

1973 May 30 - . 09:00 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 91 km (56 mi).

1974 May 30 - . 12:45 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 657 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MK. Duration: 14.00 days. Decay Date: 1974-06-13 . USAF Sat Cat: 7317 . COSPAR: 1974-038A. Apogee: 296 km (183 mi). Perigee: 177 km (109 mi). Inclination: 62.8000 deg. Period: 89.20 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1974 May 30 - . 13:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan 3C. LV Configuration: Titan IIIC 23C-9 (3C-27).
  • ATS 6 - . Payload: ATS F. Mass: 930 kg (2,050 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft: ATS-6. Completed Operations Date: 1979-08-02 . USAF Sat Cat: 7318 . COSPAR: 1974-039A. Apogee: 35,444 km (22,023 mi). Perigee: 35,184 km (21,862 mi). Inclination: 13.1000 deg. Period: 1,412.00 min. Application Technology Satellite; experimental communications satellite. The purpose of the ATS-6 flight experiment was to demonstrate north-south stationkeeping of a geosynchronous satellite using two cesium ion engine systems. Thruster development tests included a life test of 2614 hours and 471 cycles. Thruster input power was 0.15 kW, which resulted in a thrust of 4.5 mN at a specific impulse of 2500 s. One of the ion engines operated for about one hour and the other for 92 hours. Both of the engines failed to provide thrust on restart due to discharge chamber cesium flooding. The feed system flooding problem caused overloading of the discharge and high voltage power supplies. This failure mechanism was verified through a series of ground tests. However engine operation demonstrated an absence of EMI related to spacecraft systems, verified predictions of spacecraft potential with engines operating, and demonstrated compatibility with the spacecraft's star tracker. It was found that the ion engines or just the neutralizer could discharge large negative spacecraft potentials at all times. Positioned in geosynchronous orbit over the Americas at 94 deg W in 1974-1975; over the Indian Ocean 35 deg E in 1975-1976; over the Americas at 140 deg W in 1976-1979. As of 2 September 2001 located at 172.56 deg W drifting at 6.144 deg E per day. As of 2007 Mar 8 located at 29.12W drifting at 6.125E degrees per day.

1975 May 30 - . 04:35 GMT - . Launch Site: Chilca. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.524UE.
  • Plasma mission - . Nation: USA. Agency: NASA. Apogee: 187 km (116 mi).

1975 May 30 - . 06:45 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/3. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 741 - . Mass: 6,000 kg (13,200 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-2M. Duration: 12.00 days. Decay Date: 1975-06-11 . USAF Sat Cat: 7877 . COSPAR: 1975-047A. Apogee: 231 km (143 mi). Perigee: 210 km (130 mi). Inclination: 81.3000 deg. Period: 88.90 min. Zenit-2M (area survey photo reconnaissance) satellite used for earth resources studies as part of 'Gektor-Priroda' project. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation.

1977 May 30 - . 22:30 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 53749-161.
  • Cosmos 913 - . Mass: 550 kg (1,210 lb). Nation: USSR. Agency: MO. Class: Military. Type: Radar calibration target. Spacecraft: Taifun-2. Decay Date: 1979-12-29 . USAF Sat Cat: 10028 . COSPAR: 1977-042A. Apogee: 520 km (320 mi). Perigee: 474 km (294 mi). Inclination: 74.0000 deg. Period: 94.50 min. Summary: Released 21 Romb radar calibration subsatellites..

1978 May 30 - .
  • Start Enterprise (OV-101)/ ET mated vibe test - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft: Enterprise. Summary: Start Enterprise (OV-101)/ ET mated vertical ground vibration test, MSFC.

1978 May 30 - . 20:35 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Ionosphere/Plasma/Fields mission - . Nation: USSR. Apogee: 170 km (100 mi).

1979 May 30 - .
  • ET used for ground vibration to be refurbished. - . Nation: USA. Program: STS. Summary: Deliver ET used in mated vertical ground vibration test from MSFC to Martin Marietta for refurbishment.

1980 May 30 - . 14:00 GMT - . Launch Site: Wallops Island. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 90 km (55 mi).

1981 May 30 - . 00:36 GMT - . Launch Site: Kwajalein. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 76 km (47 mi).

1982 May 30 - . 19:30 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 79 km (49 mi).

1983 May 30 - . Launch Site: Plesetsk. LV Family: Topol. Launch Vehicle: Topol.
  • Test mission - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1984 May 30 - . 18:46 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC90/19. Launch Pad: LC90/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-2.
  • Cosmos 1567 - . Mass: 3,000 kg (6,600 lb). Nation: USSR. Agency: MO. Program: EORSAT. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: US-P. Decay Date: 1988-04-03 . USAF Sat Cat: 15009 . COSPAR: 1984-053A. Apogee: 369 km (229 mi). Perigee: 353 km (219 mi). Inclination: 65.0000 deg. Period: 91.80 min. Summary: Ocean monitoring..

1985 May 30 - . 01:14 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 47144-148.
  • Cosmos 1655 - . Mass: 810 kg (1,780 lb). Nation: USSR. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Tsikada. USAF Sat Cat: 15751 . COSPAR: 1985-041A. Apogee: 1,013 km (629 mi). Perigee: 976 km (606 mi). Inclination: 83.0000 deg. Period: 105.00 min. Summary: Civilian naval navigation satellite. Replaced Cosmos 1447..

1985 May 30 - . 14:59 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/40. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 313-02.
  • Cosmos 1656 - . Payload: Tselina-2 no. 2. Mass: 6,000 kg (13,200 lb). Nation: USSR. Agency: MOM. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-2. USAF Sat Cat: 15755 . COSPAR: 1985-042A. Apogee: 852 km (529 mi). Perigee: 802 km (498 mi). Inclination: 71.1000 deg. Period: 101.40 min.

1986 May 30 - . 06:49 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 80 km (49 mi).

1988 May 30 - . 08:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/1. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Cosmos 1950 - . Payload: Geo-IK no. 10. Mass: 1,500 kg (3,300 lb). Nation: USSR. Agency: MO. Class: Earth. Type: Geodetic satellite. Spacecraft: Geo-IK. USAF Sat Cat: 19195 . COSPAR: 1988-046A. Apogee: 1,522 km (945 mi). Perigee: 1,484 km (922 mi). Inclination: 73.6000 deg. Period: 116.10 min. Summary: Investigation of the upper atmosphere and outer space. .

1990 May 30 - . 12:00 GMT - . Launch Site: Zingst. Launch Vehicle: MMR-06.
  • MMR06-M Zingst launch 27 - . Nation: USSR. Agency: GMS. Apogee: 66 km (41 mi). Summary: Successful. Earth impacted at 4271 seconds. Reached 74.4 km. .

1991 May 30 - . 08:04 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U2. LV Configuration: Soyuz 11A511U2 R15000-050.
  • Progress M-8 - . Payload: Progress M s/n 207. Mass: 7,296 kg (16,084 lb). Nation: USSR. Agency: MOM. Program: Mir. Class: Manned. Type: Manned logistics spacecraft. Flight: Mir EO-9; Mir LD-3. Spacecraft: Progress M. Duration: 77.95 days. Completed Operations Date: 1991-08-16 07:02:29 . Decay Date: 1991-08-16 07:02:29 . USAF Sat Cat: 21395 . COSPAR: 1991-038A. Apogee: 396 km (246 mi). Perigee: 390 km (240 mi). Inclination: 51.6000 deg. Period: 92.40 min. Summary: Unmanned resupply vessel to Mir. Docked with Mir on 1 Jun 1991 09:44:37 GMT. Undocked on 15 Aug 1991 22:16:59 GMT. Destroyed in reentry on 16 Aug 1991 06:56:32 GMT. Total free-flight time 2.43 days. Total docked time 75.52 days..
  • Naduvaniy gazovoy ballon - . Payload: Balloon subsatellite. Nation: USSR. Agency: MOM. Program: Mir. Flight: Mir EO-9; Mir LD-3. Decay Date: 1991-08-29 . USAF Sat Cat: 21661 . COSPAR: 1986-017FJ. Apogee: 198 km (123 mi). Perigee: 187 km (116 mi). Inclination: 51.5000 deg. Period: 88.34 min.

1992 May 30 - . 08:11 GMT - . Launch Site: Arecibo. LV Family: Black Brant. Launch Vehicle: Black Brant 9. LV Configuration: Black Brant IX NASA 36.65DE.
  • EL COQUI AA-4 / IFH Plasma mission - . Nation: USA. Agency: NASA. Apogee: 308 km (191 mi).

1993 May 30 - . Launch Site: Gitdaeryung. LV Family: R-17. Launch Vehicle: Hwasong 6.
1996 May 30 - . 08:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF02. Launch Vehicle: Peacekeeper. LV Configuration: Peacekeeper 21PA.
  • Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

1996 May 30 - . 18:20 GMT - .
1997 May 30 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 742. LV Family: Trident. Launch Vehicle: Trident D-5. LV Configuration: Trident D-5 DASO-15.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1998 May 30 - . 10:00 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3B. LV Configuration: Chang Zheng 3B CZ3B-4 (52).
  • Zhongwei 1 - . Nation: China. Agency: Chinasat. Manufacturer: Lockheed. Program: Chinastar. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 25354 . COSPAR: 1998-033A. Apogee: 35,798 km (22,243 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Also known as Chinastar 1; comsat to serve China, India, Korea and Southeast Asia with 18 C-band and 20 Ku-band transponders. Operated by the China Orient Telecommunications Satellite Company, part of the Chinese telecommunications ministry. Zhongwei 1 and the CZ-3B's final liquid hydrogen upper stage were placed in an initial supersynchronous 216 x 85,035 km x 24.4 deg transfer orbit. Geostationary at 87.6 degrees E. Positioned in geosynchronous orbit at 87 deg E in 1998-1999 As of 6 September 2001 located at 87.49 deg E drifting at 0.013 deg W per day. As of 2007 Mar 11 located at 87.64E drifting at 0.010W degrees per day.

1999 May 30 - . 02:56 GMT - .
  • EVA STS-96-1 - . Crew: Jernigan; Barry. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.33 days. Nation: USA. Related Persons: Jernigan; Barry. Program: ISS. Class: Manned. Type: Manned space station. Flight: STS-96. Spacecraft: International Space Station. Summary: On May 30 at 02:56 GMT Tammy Jernigan and Dan Barry entered the payload bay of space shuttle Discovery from the tunnel adapter hatch. During the space walk they transferred equipment to the exterior of the station..

2001 May 30 - .
  • ISS Status Report: ISS 01-16 - . Nation: USA. Related Persons: Barry; Forrester; Helms; Voss. Program: ISS. Flight: ISS EO-2. International Space Station engineers are continuing to troubleshoot problems with the Canadarm2 robotic arm on the complex after an unsuccessful attempt earlier today to solve a communications glitch with one of the crane's joints through a software modification. Additional Details: ISS Status Report: ISS 01-16.

2002 May 30 - .
  • Death of Friedrich Staats - . Nation: Germany. Related Persons: Staats. Summary: German electronics engineer, worked for Steinhoff at Peenemuende, but stayed in Germany after war. Founded and led the leading German rocket society 1952-1990 (designated sequentially DAFRA, DRG, HOG, DGLR)..

2002 May 30 - . 02:00 GMT - . Launch Site: Wake Island. LV Family: Minuteman. Launch Vehicle: SR19/SR19. LV Configuration: SR19/SR19 MBRV-2.
  • PAC-3 OT-2a Target mission - . Nation: USA. Agency: USA SSDC. Apogee: 270 km (160 mi).

2003 May 30 - . 09:35 GMT - . Launch Site: Wallops Island. LV Family: Black Brant. Launch Vehicle: Black Brant 11. LV Configuration: Black Brant XI NASA 39.05DP.
  • RED DOG Target mission - . Nation: USA. Agency: NASA; Lincoln. Apogee: 300 km (180 mi).

2007 May 30 - .
2008 May 30 - .
  • ISS On-Orbit Status 05/30/08 - . Nation: USA. Related Persons: Drew; Fossum; Garan; Ham; Hoshide; Kelly, Mark; Kononenko, O D; Nyberg; Reisman; Volkov, Sergey. Program: ISS. Flight: ISS EO-16-3; ISS EO-17; STS-124. FE-2 Reisman conducted 'Week 6' sampling of potable water for chemical and microbial analysis from the SVO-ZV tap and two SRV-K taps, the latter after preliminary heating of the water (four heating cycles) and flushing.

    (Garrett collected three 450 mL samples (for postflight microbial analysis) and two 750 mL samples (for postflight chemical analysis) from each of three ports (SRV-K hot, SRV-K warm, SVO-ZV) for return on STS-124/1J. The small amounts of water used for flushing the equipment were later reclaimed from the flush bag.)

    CDR Volkov serviced the Russian BMP (Harmful Impurities Removal System), starting the "bake-out" cycle to vacuum on absorbent bed #2 of the regenerable dual-channel filtration system. The regen process will be terminated tonight at ~5:15pm EDT. Filter bed #1 was regenerated yesterday. (Regeneration of each of the two cartridges takes about 12 hours and is conducted only during crew awake periods.) Additional Details: ISS On-Orbit Status 05/30/08.


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