Encyclopedia Astronautica
October 30


October 30 Chronology


1904 October 30 - .
  • Birth of Neil H McElroy - . Nation: USA. Summary: American manager, secretary of defense 1957-1959..

1908 October 30 - .
  • Birth of Dmitri Fedorovich Ustinov - . Nation: Russia. Summary: Russian politician. Primary manager of the Soviet missile and space programs 1946-1976. In charge of development of Soviet rocketry 1946-1957. Chairman of the VPK 1957-1963. Secretary of Central Committee for Defence and Space 1965-1976..

1910 October 30 - .
1913 October 30 - .
  • Birth of Klaus Eduard Scheufelen - . Nation: Germany. Summary: German engineer, V-2 test leader. At end of war headed development of Taifun unguided antiaircraft rocket, characterised as a 'desperation project'. As of January 1947, working at Fort Bliss, Texas. Living in Lenningen, Germany in 2004..

1918 October 30 - .
  • Birth of Robert C Seamans - . Nation: USA. Summary: American engineer. Key leadership positions at NASA 1960-1968 during the Apollo program..

1944 October 30 - . Launch Site: Peenemuende. LV Family: V-2. Launch Vehicle: Wasserfall.
  • Wasserfall test - . Nation: Germany. Related Persons: Dornberger; Goering. Apogee: 18 km (11 mi). Range: 26 km (16 mi). The Wasserfall surface to air missile was launched from a table, as was the V-2. The missile was optically steered to its target, and had a potential range of 26 km and ceiling of 18 km, with a flight speed of 600 m/s. Goering observed the first launch from Test Stand IX. He was immensely fat, wearing a fantastical outfit, downing pills every five minutes, and uninterested in the proceedings. Dornberger ruefully noted that the Reich is losing the war due to the leadership's shortsightedness. They had not accepted Von Braun's rocket plans in 1939 or the Panzerfaust in 1942. They only became interested in the latter when the first American bazooka fell into German hands in Tunisia.

1946 October 30 - .
  • Birth of Robert Lee 'Hoot' Gibson - . Nation: USA. Summary: American test pilot astronaut. Flew on STS-41-B, STS-61-C, STS-27, STS-47, STS-71. Was married to astronaut Rhea Seddon..

1947 October 30 - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 11R.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1952 October 30 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-1. Launch Vehicle: R-1 8A11. LV Configuration: R-1 8A11 No 501.
  • Operational test - . Nation: USSR. Agency: Korolev. Apogee: 100 km (60 mi).

1952 October 30 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LA. Launch Pad: LA?. LV Family: Snark. Launch Vehicle: MX-775. LV Configuration: MX-775 Dyn Model #3.
  • Test mission - . Nation: USA. Agency: USAF. Apogee: 10 km (6 mi).

1952 October 30 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-1. Launch Vehicle: R-1 8A11. LV Configuration: R-1 8A11 No 520.
  • Operational test - . Nation: USSR. Agency: Korolev. Apogee: 100 km (60 mi).

1953 October 30 - .
1953 October 30 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-5. Launch Vehicle: R-5.
  • State trials Phase 2 launch - . Nation: USSR. Agency: Korolev. Apogee: 300 km (180 mi). Summary: Through December 1953 there were 7 Phase II launches, one of which was unsuccessful. A maximum range of 1185 km was reached..

1957 October 30 - .
1957 October 30 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar VLAD. Launch Vehicle: Burya. LV Configuration: Burya 2/3. FAILURE: Failure.
  • Burya flight 2 - . Nation: USSR. Apogee: 0 km ( mi).

1957 October 30 - . 21:40 GMT - . Launch Site: Pacific Ocean. Launch Pad: 60.1 S x 176.1 W. Launch Platform: AGB-4. LV Family: Rockoon. Launch Vehicle: Loki Rockoon. LV Configuration: Loki Rockoon SUI 95.
  • II5.71F Aeronomy / Chemical release mission - . Nation: USA. Agency: SUI. Apogee: 100 km (60 mi).

1959 October 30 - . 11:49 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA5A. LV Family: Black Knight. Launch Vehicle: Black Knight 201. LV Configuration: Black Knight-201 BK.06.
  • Research and development / Reentry Test / chemical release mission - . Nation: UK. Agency: RAE. Apogee: 732 km (454 mi).

1960 October 30 - .
  • Development begun of Meteor, the first Soviet weather satellite. - . Nation: USSR. Spacecraft: Meteor. Summary: Work began in 1961 at OKB-586 GKOT; in 1962 it was transferred to NII-627. Final development was completed in 1964..

1960 October 30 - .
  • Full development of Molniya-1 communications satellite authorised by government decree. - . Nation: USSR. Spacecraft: Molniya-1. Summary: Three such satellites could provide long-distance communications coverage for the entire Soviet Union. Original designed life was 1.5 to 2.0 years. Development was completed in May 1963..

1961 October 30 - .
  • Soviet military space plans through 1965 approved. - . Nation: USSR. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On plans for the military use of space during the period 1961-65' was issued. This formalised the first true military space plans - prior to that date only the Zenit-2 and Zenit-4 reconnaissance satellites had been authorised. The following missions were identified:

    • Photo reconnaissance / cartography
    • ELINT
    • Television reconnaissance
    • Communications satellites
    • Ocean reconnaissance
    • Navigation
    • Meteorology
    • Training/target objects
    • Geodesy

1961 October 30 - .
  • Molniya-1 and Meteor-1 satellites authorised. - . Nation: USSR. Spacecraft: Molniya-1; Molniya-2; Meteor. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On approval of work on the Molniya-1 communications satellite and Meteor-1 weather satellite' was issued. Thedecree authorised work on the Molniya-1M production model, providing international communications on the centimetre band. But the protoype Molniya-1 worked so well that it was taken directly into service, and the -1M was skipped.

1961 October 30 - .
1961 October 30 - . 11:13 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-9.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 175 km (108 mi).

1962 October 30 - . LV Family: Saturn V. Launch Vehicle: Saturn V.
  • Contract for production of the S-II stage signed - . Nation: USA. Program: Apollo. NASA announced the signing of a contract with the Space and Information Systems Division of NAA for the development and production of the second stage (S-II) of the Saturn C-5 launch vehicle. The $319.9-million contract, under the direction of Marshall Space Flight Center, covered the production of nine live flight stages, one inert flight stage, and several ground-test units for the advanced Saturn launch vehicle. NAA had been selected on September 11, 1961, to develop the S-II.

1962 October 30 - . 01:50 GMT - . Launch Site: Wallops Island. LV Family: Aerobee. Launch Vehicle: Aerobee 150A. LV Configuration: Aerobee 150A NASA 04.54UG.
  • OAO sensors Ultraviolet astronomy mission - . Nation: USA. Agency: NASA. Apogee: 188 km (116 mi).

1963 October 30 - .
  • Only at 14:30 due Tereshkova and Nikolayev finally give in. - . Nation: USSR. Related Persons: Nikolayev; Tereshkova. Summary: Only at 14:30 due Tereshkova and Nikolayev finally give in. The wedding is set for three days later. 300 will attend the wedding, from Khrushchev on down. .

1963 October 30 - . LV Family: Saturn I. Launch Vehicle: Saturn IB.
  • Manned Saturn I earth orbital flights canceled - . Nation: USA. Related Persons: Mueller; Webb. Program: Apollo. Spacecraft: Apollo Lunar Landing. NASA canceled four manned earth orbital flights with the Saturn I launch vehicle. Six of a series of 10 unmanned Saturn I development flights were still scheduled. Development of the Saturn IB for manned flight would be accelerated and "all-up" testing would be started. This action followed Bellcomm's recommendation of a number of changes in the Apollo spacecraft flight test program. The program should be transferred from Saturn I to Saturn IB launch vehicles; the Saturn I program should end with flight SA-10. All Saturn IB flights, beginning with SA-201, should carry operational spacecraft, including equipment for extensive testing of the spacecraft systems in earth orbit.

    Associate Administrator for Manned Space Flight George E. Mueller had recommended the changeover from the Saturn I to the Saturn IB to NASA Administrator James E. Webb on October 26. Webb's concurrence came two days later.


1963 October 30 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Belier. Launch Vehicle: Dragon 1. LV Configuration: Dragon D-05.
  • Test mission - . Nation: France. Agency: CNES. Apogee: 470 km (290 mi).

1963 October 30 - . 14:26 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 7C. LV Configuration: Skylark-7C SL134.
  • Test mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 186 km (115 mi).

1964 October 30 - . LV Family: Redstone. Launch Vehicle: Redstone.
  • Redstone leaves Army service. - . Nation: USA. Summary: In a ceremony on the parade field at Redstone Arsenal, the Redstone missile was ceremonially retired..

1964 October 30 - .
  • LLRV first flight - . Nation: USA. Spacecraft: Apollo LLRV. Initial tests were from the old South Base area of Edwards. Research pilot Joe Walker flew it three times for a total of just under 60 seconds to a peak altitude of ten ft (3 m). Later flights were shared between Walker; another Center pilot, Don Mallick; the Army's Jack Kleuver; and NASA Manned Spacecraft Center, Houston, pilots Joseph Algranti and H.E. 'Bud' Ream.

1964 October 30 - .
  • First drop test of boilerplate 28 - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM Parachute. North American conducted the first drop test of boilerplate 28 at Downey, Calif. The test simulated the worst conditions that were anticipated in a three-parachute descent and water landing. The second drop, it was expected, would likewise simulate a landing on two parachutes. The drop appeared normal, but the spacecraft sank less than four minutes after hitting the water. Additional Details: First drop test of boilerplate 28.

1964 October 30 - .
  • Birth of Sandra Hall Magnus - . Nation: USA. Summary: American materials scientist mission specialist astronaut. Flew on STS-112, ISS EO-18-1..

1964 October 30 - . 17:51 GMT - . Launch Site: Hidden Hills DZ. Launch Pad: 36.1 N x 116.0 W. Launch Platform: NB-52 008. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 3-36-59.
  • X-15A Gear mod, BLN test - . Nation: USA. Agency: NASA; USAF. Apogee: 25 km (15 mi). Summary: Maximum Speed - 5009 kph. Maximum Altitude - 25786 m..

1964 October 30 - . 19:30 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.116GS.
  • Extreme ultraviolet spectrum / X-ray flux Solar x-ray mission - . Nation: USA. Agency: NASA. Apogee: 189 km (117 mi).

1966 October 30 - . 17:45 GMT - . Launch Site: Pacific Ocean. Launch Pad: 31.0 N x 133.0 W. Launch Platform: T-AGM-8. LV Family: Iris. Launch Vehicle: Hydra-Iris. LV Configuration: Hydra-Iris BOX-5. FAILURE: Failure.
  • LRL BOX-5 X-ray astronomy mission - . Nation: USA. Agency: USN NMC. Apogee: 12 km (7 mi).

1967 October 30 - .
  • Apollo LM delivery schedule revisions - . Nation: USA. Related Persons: Low, George. Program: Apollo. Flight: Apollo 10. Spacecraft: Apollo LM. Confirming an October 27 telephone conversation, ASPO Manager George M. Low recommended to Apollo Program Director Samuel C. Phillips that the following LM delivery schedule be incorporated into official documentation: LM-2, February 5, 1968; LM-3, April 6, 1968; LM-4, June 6, 1968. Subsequent vehicles would be delivered on two-month centers. The dates had been provided by Grumman during the last Program Management Review.

1967 October 30 - .
  • Apollo Drop Test failure 84-1 - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM Parachute. A parachute test (Apollo Drop Test 84-1) failed at EI Centro, Calif. The parachute test vehicle (PTV) was dropped from a C-133A aircraft at an altitude of 9,144 meters to test a new 5-meter drogue chute and to investigate late deployment of one of the three main chutes. Additional Details: Apollo Drop Test failure 84-1.

1967 October 30 - . 08:12 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511.
  • Cosmos 188 - . Payload: Soyuz 7K-OK (P) s/n 5. Mass: 6,530 kg (14,390 lb). Nation: USSR. Related Persons: Mishin; Mnatsakanian. Agency: MOM. Program: Soyuz. Class: Manned. Type: Manned spacecraft. Spacecraft: Soyuz 7K-OK. Duration: 3.04 days. Decay Date: 1967-11-02 . USAF Sat Cat: 3020 . COSPAR: 1967-107A. Apogee: 247 km (153 mi). Perigee: 180 km (110 mi). Inclination: 51.7000 deg. Period: 88.70 min. Docking target craft for Cosmos 186, which achieved world's first automatic rendezvous on second attempt. Hard docking achieved but electric connections unsuccessful due to misallignment of spacecraft. Ion flow sensor failed and Cosmos 188 had to make a high-G uncontrolled re-entry. When it deviated too far off course, it was destroyed by the on-board self-destruct system,. However officially the Soviet Union reported that it landed succesfully on November 2, 1967 at 09:10 GMT, and that its mission was 'investigation of outer space, development of new systems and elements to be used in the construction of space devices'. Additional Details: Cosmos 188.

1967 October 30 - . 17:59 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. Launch Pad: LC132/pad?. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M.
  • Cosmos 189 - . Payload: Tselina-O Mass Model. 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: 1978-06-08 . USAF Sat Cat: 3021 . COSPAR: 1967-108A. Apogee: 599 km (372 mi). Perigee: 510 km (310 mi). Inclination: 73.8000 deg. Period: 95.70 min. Summary: Possible ELINT satellite test..

1968 October 30 - . LV Family: Shuttle. Launch Vehicle: Shuttle.
  • Phase A Space Shuttle studies. - . Nation: USA. NASA began the design, bidding, and source selection process leading to a single national space shuttle. At the beginning the design was known by the same nomenclature previously used by the USAF - Integrated Launch and Re-entry Vehicle (ILRV). The development program was seen as: Phase A: Advanced Studies; Phase B: Project Definition; Phase C: Vehicle Design; and Phase D: Production and Operations. Four contractors or contractor teams were to be selected in Phase A; two contractors or teams for Phase B; and then a single contractor for Phases C and D (which were later combined). NASA Houston and Huntsville jointly issued the Request for Proposal for eight-month Phase A ILRV studies. The requirements were for 2,300 to 23,000 kg of payload to be delivered into a 500-km altitude orbit. The re-entry vehicle should have a cross range of at least 725 km (NASA persisted in this requirement even though it knew the USAF needed more). General Dynamics, Lockheed, McDonnell-Douglas, Martin Marietta, and North American Rockwell all were invited to bid.

    The Space Shuttle Main Engine competition was run in parallel with the main shuttle development project, and also had four phases. Oversight for this program came from the USAF Space Division and its subcontractor, the Aerospace Corporation. Despite promising classified work on linear and conventional aerospike engines at the time, NASA dictated that the design had to use a conventional bell nozzle.


1968 October 30 - . 08:06 GMT - . Launch Site: Kheysa. LV Family: MR-12. Launch Vehicle: MR-12.
  • Aeronomy mission - . Nation: USSR. Agency: AN. Apogee: 171 km (106 mi).

1968 October 30 - . 08:23 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF09. Launch Pad: LF09?. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 1136.
  • ST Olympic T. B-5 operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1968 October 30 - . 22:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. Launch Pad: LC132/pad?. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M.
  • Cosmos 250 - . 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: 1978-02-15 . USAF Sat Cat: 3526 . COSPAR: 1968-095A. Apogee: 542 km (336 mi). Perigee: 522 km (324 mi). Inclination: 74.0000 deg. Period: 95.30 min. Summary: Possible navigation satellite..

1968 October 30 - .
  • Landing of Soyuz 3 - . Return Crew: Beregovoi. Nation: USSR. Related Persons: Beregovoi. Program: Soyuz. Flight: Soyuz 3. Spacecraft: Soyuz 7K-OK. Telemetry analysis has shown Soyuz 3 used 30 kg of propellant during 20 minutes of manoeuvring in the automatic regime during docking, followed by 40 kg consumed in two minutes of manual manoeuvring. Essentially Beregovoi was trying to dock the spacecraft upside down. This was either due to incorrect configuration of the running lights or cosmonaut error. Soyuz 2 had two continuously illuminated lights on its upper side and two blinking lights on the lower side. Evidently Beregovoi didn't identify these correctly in weightlessness.

    In case Beregovoi has to do a ballistic re-entry, Be-2 seaplanes are in the air in case of a splashdown in the Aral Sea. On his 81st revolution, Beregovoi manually oriented the spacecraft for retrofire, then engaged the vertical sensor and ion orientation system. But the spacecraft hit on ion pocket and it took two to three minutes for the automated system to engage. Retrofire started 3 seconds late, coming at 9:45:05 and continuing for 149 seconds, producing a delta V of 95 m/s. The main parachute deployed at 10:12:24 at 7000 m altitude. Beregovoi spent 13 minutes under the main parachute, descending at 4 to 5 m/s. Soyuz 3 landed 10 km from the aimpoint at 07:25 GMT.


1969 October 30 - . 16:30 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 622. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3E.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1970 October 30 - .
  • Shatalov and Yeliseyev selected for first space station flight. - . Nation: USSR. Program: Salyut. Flight: Soyuz 10. Shatalov and Yeliseyev are selected as the prime crew to man DOS#1. This selection is made even though they have both made two flights already and other cosmonauts have been waiting six years with no flight assignment. The choice is due to the role of the pilot, who it is felt must have prior docking experience. Kamanin reviews the training schedule for the pair, plus a tour of India they will have to make before the flight.

1970 October 30 - . 02:36 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC90/19. Launch Pad: LC90/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-2.
  • Cosmos 375 - . Mass: 1,400 kg (3,000 lb). Nation: USSR. Agency: PKO. Class: Military. Type: Anti-satellite system. Spacecraft: IS-A. Decay Date: 1970-10-30 . USAF Sat Cat: 4598 . COSPAR: 1970-091A. Apogee: 1,986 km (1,234 mi). Perigee: 579 km (359 mi). Inclination: 62.8000 deg. Period: 111.20 min. ASAT interceptor. Intercept on second orbit. Blown up on instructions from ground. Dual launch of interceptors was intended to help ground staff perfect computational methods for quick-response launches when orbital methods of target were not precisely known.

1970 October 30 - . 13:20 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 376 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4M. Duration: 13.00 days. Decay Date: 1970-11-12 . USAF Sat Cat: 4599 . COSPAR: 1970-092A. Apogee: 286 km (177 mi). Perigee: 207 km (128 mi). Inclination: 65.4000 deg. Period: 89.40 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1971 October 30 - . LV Family: Shuttle. Launch Vehicle: Shuttle.
  • Shuttle Phase C/D Request for Proposal - . Nation: USA. Request for Proposals were sent to Grumman/Boeing, McDonnell-Douglas/Martin Marrietta, and North American Rockwell for final proposals for Shuttle full-scale development. However the NASA specifications kept shifting. In December 1971 NASA decided to require parallel burn of the shuttle orbiter and booster stages, so the bid due date was shifted from 15 December 1971 to 1 June 1972.

1972 October 30 - . 17:45 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 NASA 13.67US.
  • Solar mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1973 October 30 - . 00:37 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout A-1. LV Configuration: Scout A-1 S178C.
  • Transit O-20 - . Mass: 58 kg (127 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 6909 . COSPAR: 1973-081A. Apogee: 1,120 km (690 mi). Perigee: 885 km (549 mi). Inclination: 89.8000 deg. Period: 105.20 min. Summary: Operational life over 20 years..

1973 October 30 - . 08:08 GMT - . Launch Site: Kheysa. LV Family: MR-12. Launch Vehicle: MR-12.
  • Aeronomy/Plasma mission - . Nation: USSR. Apogee: 150 km (90 mi).

1973 October 30 - . 18:50 GMT - . Launch Site: Andoya. LV Family: Skylark. Launch Vehicle: Skylark 6. LV Configuration: Skylark 6 SL1122.
  • UK High Latitude Rocket Ionosphere / aurora mission - . Nation: UK. Agency: BAC. Apogee: 229 km (142 mi).

1973 October 30 - . 19:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 53749-158.
  • Intercosmos 10 - . Payload: DS-U2-IK s/n 3. Mass: 550 kg (1,210 lb). Nation: USSR. Agency: IK. Program: DS. Class: Earth. Type: Ionosphere satellite. Spacecraft: DS-U2-IK. Completed Operations Date: 1974-06-07 . Decay Date: 1977-07-01 . USAF Sat Cat: 6911 . COSPAR: 1973-082A. Apogee: 1,453 km (902 mi). Perigee: 257 km (159 mi). Inclination: 74.0000 deg. Period: 102.00 min. Summary: Geophysical research at high latitudes to study the electromagnetic coupling of the earth's magnetosphere and ionosphere..

1973 October 30 - . 19:15 GMT - . Launch Site: Andoya. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P142A.
  • High Latitude / e, p Aurora mission - . Nation: UK. Agency: SRC. Apogee: 133 km (82 mi).

1973 October 30 - . 20:04 GMT - . Launch Site: Andoya. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P143A.
  • High Latitude / e, p Aurora mission - . Nation: UK. Agency: SRC. Apogee: 135 km (83 mi).

1974 October 30 - . 22:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 90 km (55 mi).

1975 October 30 - . 23:52 GMT - . Launch Site: Poker Flat. LV Family: Sergeant. Launch Vehicle: Sounding Rocket. LV Configuration: Sergeant EX530.90-1/S75-2.
  • PF-SGT-101 test - . Nation: USA. Agency: DNA. Apogee: 100 km (60 mi).

1976 October 30 - . 03:30 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 200A. LV Configuration: Aerobee 200A NASA 26.56DG.
  • NRL Mk II ultraviolet Camera Ultraviolet astronomy mission - . Nation: USA. Agency: NASA. Apogee: 182 km (113 mi).

1977 October 30 - . 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: 150 km (90 mi).

1978 October 30 - . 05:23 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Molniya 8K78M. LV Configuration: Molniya 8K78M-SOL.
  • Prognoz 7 - . Payload: SO-M s/n 507. Mass: 950 kg (2,090 lb). Nation: USSR. Agency: MOM. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Prognoz. Decay Date: 1980-09-22 . USAF Sat Cat: 11088 . COSPAR: 1978-101A. Apogee: 202,627 km (125,906 mi). Perigee: 472 km (293 mi). Inclination: 64.9000 deg. Period: 5,881.10 min. Magnetospheric investigations. Investigation of the corpuscular and electromagnetic radiation of the sun, of solar plasma fluxes and of the magnetic fields in circumterrestrial space in order to determine the effects of solar activity on the interplanetary medium and the magnetosphere of the earth; investigation of galactic ultraviolet rays, X-rays and gamma rays. In addition to Soviet apparatus, carried scientific apparatus produced in the USSR, the Czechoslovak Socialist Republic, France, the Hungarian People's Republic and Sweden.

1979 October 30 - . 14:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout G. LV Configuration: Scout G-1 S203C.
  • Magsat - . Payload: AEM 3. Mass: 181 kg (399 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Magsat. Decay Date: 1980-06-11 . USAF Sat Cat: 11604 . COSPAR: 1979-094A. Apogee: 561 km (348 mi). Perigee: 352 km (218 mi). Inclination: 96.8000 deg. Period: 93.70 min. Summary: Measured near-Earth magnetic field and crustal anomalies. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1980 October 30 - . 10:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1218 - . Payload: Yantar-4K1 s/n 3. Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Yantar-4K1. Duration: 43.00 days. Decay Date: 1980-12-12 . USAF Sat Cat: 12039 . COSPAR: 1980-086A. Apogee: 285 km (177 mi). Perigee: 158 km (98 mi). Inclination: 64.9000 deg. Period: 88.90 min. Successful state acceptance test flight of Yantar-4K1 satellite. Led to Yantar-4K1 acceptance for Red Army service the following year. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission.

1981 October 30 - . 06:04 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/40. LV Family: Proton. Launch Vehicle: Proton-K/D-1. LV Configuration: Proton-K/D-1 311-01.
  • Venera 13 - . Payload: 4V-1 s/n 760. Mass: 4,500 kg (9,900 lb). Nation: USSR. Agency: MOM. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft: Venera 4V-1. USAF Sat Cat: 12927 . COSPAR: 1981-106A. Venera 13 and 14 were identical spacecraft built to take advantage of the 1981 Venus launch opportunity and launched 5 days apart. After launch and a four month cruise to Venus, the descent vehicle separated and plunged into the Venus atmosphere on 1 March 1982. As it flew by Venus the bus acted as a data relay for the brief life of the descent vehicle, and then continued on into a heliocentric orbit. After the descent vehicle braked to subsonic speed a parachute was deployed. At an altitude of 47 km the parachute was released and simple airbraking was used the rest of the way to the surface. Venera 13 landed about 950 km northeast of Venera 14 at 7 deg 30 min S, 303 E, just east of the eastern extension of an elevated region known as Phoebe Regio. The area was composed of bedrock outcrops surrounded by dark, fine-grained soil. After landing an imaging panorama was started and a mechanical drilling arm reached to the surface and obtained a sample, which was deposited in a hermetically sealed chamber, maintained at 30 degrees C and a pressure of about .05 atmospheres. The composition of the sample, as determined by the X-ray flourescence spectrometer, put it in the class of weakly differentiated melanocratic alkaline gabbroids. The lander survived for 127 minutes (the planned design life was 32 minutes) in an environment with a temperature of 457 degrees C and a pressure of 84 Earth atmospheres. The bus carried instruments built by Austrian and French specialists, as well as Soviet scientific equipment.

1982 October 30 - . 04:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan 34D/IUS. LV Configuration: Titan 34D/IUS 34D-1 (04D-5?).
  • DSCS II-15 - . Payload: DSCS II F-15. Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS II. Completed Operations Date: 1997-05-23 . USAF Sat Cat: 13636 . COSPAR: 1982-106A. Apogee: 37,332 km (23,196 mi). Perigee: 37,277 km (23,162 mi). Inclination: 11.3000 deg. Period: 1,514.40 min. Positioned in geosynchronous orbit at 15 deg W in 1983-1987; 66 deg E in 1987; 60 deg E in 1987-1994; 65 deg E in 1994-1997 As of 5 September 2001 located at 114.00 deg W drifting at 18.661 deg W per day. As of 2007 Mar 9 located at 172.94E drifting at 18.658W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).
  • DSCS III-01 - . Payload: DSCS III F-1. Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 13637 . COSPAR: 1982-106B. Apogee: 36,171 km (22,475 mi). Perigee: 36,132 km (22,451 mi). Inclination: 8.8000 deg. Period: 1,454.80 min. Summary: Positioned in geosynchronous orbit at 105 deg W in 1982-1983; 135 deg W in 1983-1989; 130 deg W in 1989-1999. As of 2006 Sep 9 located at 94.39E drifting at 5.469W degrees per day..

1985 October 30 - . 17:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-29/61-A.
  • STS-61-A - . Call Sign: Challenger. Crew: Bluford; Buchli; Dunbar; Furrer; Hartsfield; Messerschmid; Nagel; Ockels. Payload: Challenger F09 / GLOMR 1. Mass: 14,451 kg (31,859 lb). Nation: USA. Related Persons: Bluford; Buchli; Dunbar; Furrer; Hartsfield; Messerschmid; Nagel; Ockels. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-61-A. Spacecraft: Challenger. Duration: 7.03 days. Decay Date: 1985-11-06 . USAF Sat Cat: 16230 . COSPAR: 1985-104A. Apogee: 331 km (205 mi). Perigee: 319 km (198 mi). Inclination: 57.0000 deg. Period: 91.00 min. Manned eight crew. Launched GLOMR; carried Spacelab D1. Payloads: Spacelab D-1 with habitable module and 76 experiments. Six of the eight crew members were divided into a blue and red team working 12-hour shifts for 24-hour-a-day operation. The remaining two crew members were 'switch hitters.'.
  • Spacelab D-1 - . Payload: Spacelab Long Module. Nation: USA. Agency: NASA. Program: Spacelab. Class: Manned. Type: Manned space laboratory. Spacecraft: Spacelab. Decay Date: 1985-11-06 . USAF Sat Cat: 16230 . COSPAR: 1985-104xx. Apogee: 332 km (206 mi). Perigee: 322 km (200 mi). Inclination: 57.0000 deg. Period: 91.10 min.
  • USS - . Nation: USA. Agency: NASA. Program: STS. Decay Date: 1985-11-06 . USAF Sat Cat: 16230 . COSPAR: 1985-104xx. Apogee: 332 km (206 mi). Perigee: 322 km (200 mi). Inclination: 57.0000 deg. Period: 91.10 min.
  • GLOMR; GLOMAR - . Payload: Challenger F9 / GLOMR 1. Mass: 52 kg (114 lb). Nation: USA. Agency: USN. Class: Communications. Type: Military communications satellite. Spacecraft: GLOMR. Decay Date: 1986-12-26 . USAF Sat Cat: 16231 . COSPAR: 1985-104B. Apogee: 332 km (206 mi). Perigee: 317 km (196 mi). Inclination: 57.0000 deg. Period: 91.00 min. Summary: Released from STS 61A 11/1/85. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1986 October 30 - . 13:06 GMT - . Launch Site: Ascension. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 69 km (42 mi).

1987 October 30 - . 16:30 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 81 km (50 mi).

1989 October 30 - . 12:59 GMT - . Launch Site: Antigua. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 69 km (42 mi).

1990 October 30 - . 21:45 GMT - .
  • EVA Mir EO-7-1 - . Crew: Manakov; Strekalov. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.11 days. Nation: USSR. Related Persons: Manakov; Strekalov. Program: Mir. Class: Manned. Type: Manned space station. Flight: Mir EO-7. Spacecraft: Mir. Summary: Attempt to repair Kvant 2 hatch..

1990 October 30 - . 23:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta 6925. LV Configuration: Delta 6925 D200.
  • Inmarsat 2 F1 - . Mass: 1,385 kg (3,053 lb). Nation: International. Agency: Inmarsat. Manufacturer: Toulouse. Program: Inmarsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 1000. USAF Sat Cat: 20918 . COSPAR: 1990-093A. Apogee: 35,800 km (22,200 mi). Perigee: 35,775 km (22,229 mi). Inclination: 1.7000 deg. Period: 1,436.20 min. Mobile communications; 64.5 deg E. Positioned in geosynchronous orbit at 65 deg E in 1990-1996; 179 deg E in 1996-1999 As of 5 September 2001 located at 178.97 deg E drifting at 0.004 deg W per day. As of 2007 Mar 8 located at 143.50E drifting at 0.015W degrees per day.

1991 October 30 - . Launch Site: Negev. LV Family: Jericho. Launch Vehicle: Jericho 1.
  • Operational test - . Nation: Israel. Agency: IDF. Apogee: 100 km (60 mi).

1992 October 30 - . 14:59 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 372-01.
  • Ekran 20 - . Payload: Ekran-M s/n 15L. Mass: 1,970 kg (4,340 lb). Nation: Russia. Agency: MOM. Class: Communications. Type: Military communications satellite. Spacecraft: Ekran-M . USAF Sat Cat: 22210 . COSPAR: 1992-074A. Apogee: 35,803 km (22,246 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.7000 deg. Period: 1,436.30 min. Transmission of television programmes to a network of multiple user receiving stations. Positioned in geosynchronous orbit at 99 deg E in 1992-1999 As of 5 September 2001 located at 79.69 deg E drifting at 0.201 deg W per day. As of 2007 Mar 10 located at 78.67E drifting at 0.192E degrees per day.

1993 October 30 - .
  • Mir News 196: 5th Spacewalk (EVA) Mir-crew on 29.10.93 - . Nation: Russia. Program: Mir. Flight: Mir EO-14. The crew opened the hatch at 1338 UTC and closed this behind them at 1750 UTC, so the duration of this EVA was 4 hrs and 12 mins. They fully accomplished their tasks: the experiment Panorama, during which Sererbrov made video-images of the outer surface of the station, they removed samples of materials which had been exposed to open space and placed new samples and on instructions from experts on earth they carried out an inspection of objects on the outside, for instance the solar panels. They also carried out prophylactic work. Most of the radio-communications was relayed by the satellite Altair. During the first 2 passes for our position the EVA was still going on and the radio-traffic could be heard on VHF as well as on Altair. During the pass in orbit 44010, 1742-1752 UTC, the cosmonauts returned to the airlock and they told TsUP that they were ready to close the hatch on TsUP's command. So they did at 1750 UTC and they immediately started with the equalisation of the pressures between the airlock (S.Sh.O.) and the Instrument-Scientific compartment (P.N.O.). OM Peter monitored phone as well as TV-images and in co-ordination with him I was able to determine that all went well during this EVA. During the first communication session via Altair after the EVA the cosmonauts transmitted images made during the EVA to TsUP. So OM Peter could see how the crew during their EVA jettisoned an old (probably no longer usable)EVA or spacesuit. They succeeded in sending away this dummy in such a shape that it looked like someone who saluted like a soldier. After analyses of the monitored radio-traffic I hope to tell something about the crew's assessment of the damage, which had been caused by micro-meteorites around 12.08.93.

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


1997 October 30 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G. LV Configuration: Ariane 5G V101 (502).
  • MAQSAT-H/TEAMSAT - . Payload: MAQSAT-H. Nation: Europe. Agency: ESA. Manufacturer: Kayser-Threde. Class: Technology. Type: Navigation technology satellite. Spacecraft: MAQSAT. USAF Sat Cat: 25023 . COSPAR: 1997-066A. Apogee: 26,504 km (16,468 mi). Perigee: 545 km (338 mi). Inclination: 7.6000 deg. Period: 465.70 min. Summary: Dummy communications satellite instrumented to report the actual payload bay environment during launch. It included the TEAMSAT technology experiment payload, developed by ESTEC.
  • MAQSAT-B/EPS - . Payload: MAQSAT-B. Nation: Europe. Agency: ESA. Manufacturer: Kayser-Threde. Class: Technology. Type: Navigation technology satellite. Spacecraft: MAQSAT. USAF Sat Cat: 25024 . COSPAR: 1997-066B. Apogee: 26,549 km (16,496 mi). Perigee: 541 km (336 mi). Inclination: 7.6000 deg. Period: 466.40 min. Summary: Dummy satellite in the lower bay of the SPELTRA dual launch adapter..
  • YES - . Payload: Young Engineers Satellite. Nation: Europe. Agency: ESA. Manufacturer: ESTEC. Class: Technology. Type: Navigation technology satellite. Spacecraft: YES. USAF Sat Cat: 25025 . COSPAR: 1997-066C. Apogee: 26,604 km (16,530 mi). Perigee: 558 km (346 mi). Inclination: 7.6000 deg. Period: 467.70 min. Summary: Young Engineers Satellite with several technology experiments. Ejected from MAQSAT-H/TEAMSAT..

1998 October 30 - .
1999 October 30 - .
  • Discovery of the Los Angeles Meteorite (Mars Meteorite) - . Nation: USA.

2000 October 30 - . Launch Site: Xichang. Launch Complex: Xichang LC2. LV Family: CZ. Launch Vehicle: CZ-3A. LV Configuration: Chang Zheng 3A CZ3A-5 (63).
  • Beidou 1A - . Mass: 2,200 kg (4,800 lb). Nation: China. Agency: CNSA. Manufacturer: CAST. Class: Navigation. Type: Navigation satellite. Spacecraft: Beidou. USAF Sat Cat: 26599 . COSPAR: 2000-069A. Apogee: 35,805 km (22,248 mi). Perigee: 35,774 km (22,228 mi). Inclination: 2.6000 deg. Period: 1,436.20 min. Beidou was China's first experimental navigation technology satellite, developed by CAST/Beijing. The satellite was placed in an initial 195 x 41889 km x 25.0 deg orbit geostationary transfer orbit before entering its final geosynchornous orbit at around 0500 GMT on November 6. Stationed at 140 deg E, still maintaining its position within 0.1 deg as of 2007.

2001 October 30 - . 02:31 GMT - . Launch Site: Woomera. LV Family: Terrier. Launch Vehicle: Terrier Orion Mk 70. LV Configuration: Terrier Mk 70 Orion T-Orion 5A. FAILURE: Failure.
  • Hyshot 1 'Hilary' Technology mission - . Nation: Australia. Agency: UQU. Apogee: 100 km (60 mi). First launch attempt in the HyShot Flight Program. The scramjet payload was to be used to verify pressure measurements made of supersonic combustion in The University of Queensland's T4 shock tunnel by those made in an actual flight. A failure of stabilising fins meant that the rocket fell far short of the planned 330-km apogee and the scramjet experiment was not conducted.

2002 October 30 - . 03:11 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz FG. LV Configuration: Soyuz-FG E15000-004.
  • Soyuz TMA-1 - . Call Sign: Yenisey. Crew: Zalyotin; De Winne; Lonchakov. Payload: Soyuz TMA s/n 211. Mass: 7,250 kg (15,980 lb). Nation: Russia. Related Persons: Zalyotin; De Winne; Lonchakov. Agency: RAKA. Manufacturer: Korolev. Program: ISS. Class: Manned. Type: Manned spacecraft. Flight: ISS EP-4. Spacecraft: Soyuz TMA. Duration: 185.96 days. Decay Date: 2003-05-04 . USAF Sat Cat: 27552 . COSPAR: 2002-050A. Apogee: 295 km (183 mi). Perigee: 278 km (172 mi). Inclination: 51.6200 deg. Period: 90.20 min. Launch delayed from October 22, 28 pending investigation of causes of failure of another Soyuz booster on 15 October. Soyuz-TMA 1 was a Russian automatic passenger craft. It carried the EP-4 visiting crew of three astronauts (two Russians and one Belgian) to automatically dock with the International Space Station (ISS). This was the first flight of the new Soyuz-TMA model. It was to remain parked at the ISS as the escape craft, relieving the Soyuz TM-34. The crew conducted several microgravity experiments on the ISS during their 10-day stay before returning in Soyuz TM-34.

2003 October 30 - . 13:43 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot 4921921121.
  • Servis-1 - . Mass: 840 kg (1,850 lb). Nation: Japan. Agency: USEF. Class: Technology. Type: Navigation technology satellite. Spacecraft: SERVIS. USAF Sat Cat: 28060 . COSPAR: 2003-050A. Apogee: 1,016 km (631 mi). Perigee: 984 km (611 mi). Inclination: 99.5000 deg. Period: 105.10 min. The mission of the 'Space Environment Reliability Verification of Integrated System' was to flight test a range of commerical-grade spacecraft components including a computer, star tracker, battery, and laser gyro. The objective was to lower the cost of future satellites.

2006 October 30 - . 23:49 GMT - . Launch Site: Kiritimati. Launch Pad: 0.0 N x 154.0 W. Launch Platform: ODYSSEY. LV Family: Zenit. Launch Vehicle: Zenit-3SL. LV Configuration: Zenit-3SL 22SL/DM-SL-24L.
  • XM-Blues - . Mass: 6,100 kg (13,400 lb). Nation: USA. Agency: XM Radio. Manufacturer: El Segundo. Program: XM. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 702. USAF Sat Cat: 29520 . COSPAR: 2006-049A. Apogee: 35,787 km (22,236 mi). Perigee: 35,785 km (22,235 mi). Inclination: 0.0000 deg. Period: 1,436.09 min. Summary: Adds to XM Satellite Radio's constellation of direct-broadcast radio to North America (XM Rock, Roll, and Rhythm launched earlier). As of 2007 Mar 10 located at 115.02W drifting at 0.006W degrees per day..

2007 October 30 - . 08:45 GMT - .
  • EVA STS-120-3 - . Crew: Parazynski; Wheelock. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.29 days. Nation: USA. Related Persons: Parazynski; Wheelock. Program: ISS. Flight: STS-120; ISS EO-16; ISS EO-16-1. The astronauts emerged from the Quest hatch at 08:44 GMT. They assisted in the mating of the P6 to P5 trusses and deployment of a radiator from P6. Wheelock transferred a spare Main Bus Switching Unit (MBSU) from the Shuttle bay to the External Stowage Platform 3 (ESP3). P6 solar array wing 2B was successfully redeployed; but deployment of array 4B had to be halted when a tear developed in the solar panel.

2010 October 30 - . 03:06 GMT - . Launch Site: Barking Sands. Launch Vehicle: Castor 4B.
  • MRT-9 - . Nation: USA. Apogee: 150 km (90 mi). Summary: ABM target. Successful intercept..
  • Aegis KV - . Nation: USA. Apogee: 150 km (90 mi). Summary: Successful ABM test from Japanese Aegis ship..

2011 October 30 - .
  • Progress M-13M - . Nation: Russia. Program: ISS. Flight: ISS EO-28. Spacecraft: Progress M. USAF Sat Cat: 37857 . COSPAR: 2011-062A. Apogee: 403 km (250 mi). Perigee: 374 km (232 mi). Inclination: 51.6000 deg. Period: 92.30 min.

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