Encyclopedia Astronautica
October 06


October 06 Chronology


1927 October 6 - .
  • Birth of Boris Vladimirovich Balmont - . Nation: Russia. Summary: Russian politician. First Deputy Minister of General Machine Building 1976-1981. Chief of Chief Directorate of Ministry of General Machine Building 1965-1973..

1932 October 6 - . Launch Vehicle: HW-2.
  • HW-2 - . Nation: Germany. Related Persons: Winkler. Apogee: 0.0030 km (0.0019 mi). Following an aborted attempt on 29 September, Winkler launches his HW-2 rocket from Pillau on the Baltic. He had worked for months at the Raketenflugplatz developing the new device. However on launch day an explosive propellant mix developed in the internal compartments of the rocket, and after igniting and rising only 3 m, it was blown to smithereens.

1940 October 6 - .
  • Birth of Boris Dmitriyevich Andreyev - . Nation: Russia. Summary: Russian engineer cosmonaut, 1972-1983. Off flight roster for medical reasons. Civilian Engineer, Korolev OKB.

1943 October 6 - . Launch Site: Peenemuende. Launch Complex: Peenemuende P7. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 V-049.
  • V-2 4049 - . Nation: Germany. Summary: First Field Battery launch. Burnout at T+64 seconds. Flight duration 272 seconds..

1944 October 6 - . Launch Site: Heidekraut. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 19041. FAILURE: Air-burst of rocket but explosion of warhead at ground level..
  • V-2 WH3 187 F1 - . Nation: Germany. Summary: Planned range 225 km. Air-burst of rocket but explosion of warhead at ground level 5.3 km to the left of the planned trajectory. Circular error 6.1 km from aim point..

1947 October 6 - .
1949 October 6 - .
  • XS-1 Flight 126 - . Crew: Fleming. Payload: XS-1 # 1 flight 73. Nation: USA. Related Persons: Fleming. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: AF flight 51. Pilot familiarization..

1949 October 6 - . 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. 2. FAILURE: Failure.
  • Hermes II test - . Nation: USA. Agency: USA. Apogee: 4.00 km (2.40 mi).

1951 October 6 - . Launch Site: Camp de Suippes. LV Family: Veronique. Launch Vehicle: Veronique R. LV Configuration: Veronique R R5.
  • Test mission - . Nation: France. Agency: LRBA. Apogee: 2.00 km (1.20 mi).

1953 October 6 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 1234A.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1954 October 6 - .
  • X-1B Flight 3 - . Crew: Ridley. Payload: X-1B flight 2. Nation: USA. Related Persons: Ridley. Class: Manned. Type: Manned rocketplane. Spacecraft: X-1B. Summary: AF flight 2. Glide flight, aborted power flight because of evidence of high lox-tank pressure..

1955 October 6 - . 19:10 GMT - . Launch Site: Atlantic Ocean. Launch Pad: 65.1 N x 61.9 W. Launch Platform: AGB-5. LV Family: Rockoon. Launch Vehicle: Deacon Rockoon.
  • SUI 51 Ionosphere / aeronomy mission - . Nation: USA. Agency: SUI. Apogee: 100 km (60 mi). Summary: Launched at Atlantic Ocean Launch Site 13 Launch Point 14 - - Latitude: 65.12 N - Longitude: 61.85 W..

1958 October 6 - . LV Family: Jupiter; Redstone.
  • Negotiations for Redstone and Jupiter launch vehicles for Mercury project. - . Nation: USA. Related Persons: von Braun. Program: Mercury. Summary: Personnel from the Langley Research Center visited the Army Ballistic Missile Agency to open negotiations for procuring Redstone and Jupiter launch vehicles for manned satellite projects..

1958 October 6 - . Launch Site: Wallops Island. LV Family: Honest John. Launch Vehicle: HJ Nike Nike Recruit.
  • Polaris Re-entry Vehicle test - . Nation: USA. Agency: USN. Apogee: 26 km (16 mi).

1959 October 6 - . 05:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC11. LV Family: Atlas. Launch Vehicle: Atlas D. LV Configuration: Atlas D 18D.
  • Mk 3 Mod 1 re-entry vehicle research and development mission - . Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).

1959 October 6 - . 16:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Delta. Launch Vehicle: Thor DM-18A. LV Configuration: Thor DM-18A 235.
  • Series IV research and development launch/Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 October 6 - . 18:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LE-8. LV Family: Delta. Launch Vehicle: Thor DM-18A. LV Configuration: Thor DM-18A 239.
  • IWST - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1960 October 6 - . 03:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone 2037. FAILURE: Control system malfunction during re-entry at 375 sec..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 221 m..

1961 October 6 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-5. Launch Vehicle: R-5M.
  • Nuclear test - . Nation: USSR. Agency: RVSN. Apogee: 500 km (310 mi).

1961 October 6 - . Launch Site: Baikonur. Launch Complex: Baikonur LC51. LV Family: R-9. Launch Vehicle: Romashka. LV Configuration: R-9 No. E15001-21.
  • State trials missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,160 km (720 mi).

1962 October 6 - . Launch Site: Vandenberg. Launch Complex: Vandenberg 395-A1. LV Family: Titan. Launch Vehicle: Titan 1. LV Configuration: Titan I SM-35.
  • Research and development Category II test - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

1964 October 6 - . LV Family: Titan. Launch Vehicle: Titan 2.
  • The Prespacecraft Mate Combined Systems Test (CST) of Gemini launch vehicle 2 was completed at complex 19. - . Nation: USA. This test, similar to CST performed at the Martin plant, comprised an abbreviated countdown and simulation of flight events, with a simulator representing electrical characteristics of the spacecraft; its purpose was to establish confidence in the launch vehicle. Electrical Electronic Interference Tests were completed October 12. Hurricane Isbell threatened the area on October 14-15, but its path was far enough south of the Cape to make deerection unnecessary, though testing was curtailed.

1964 October 6 - . 07:12 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Voskhod 11A57. LV Configuration: Voskhod 11A57 R15000-02.
  • Cosmos 47 - . Payload: Voskhod 3KV s/n 2. Mass: 5,320 kg (11,720 lb). Nation: USSR. Related Persons: Rudenko; Kirillov; Tyulin; Korolev. Agency: Korolev. Program: Voskhod. Class: Manned. Type: Manned spacecraft. Flight: Voskhod 1. Spacecraft: Voskhod. Duration: 1.01 days. Decay Date: 1964-10-07 . USAF Sat Cat: 891 . COSPAR: 1964-062A. Apogee: 383 km (237 mi). Perigee: 174 km (108 mi). Inclination: 64.6000 deg. Period: 90.10 min. Unmanned test of Voskhod spacecraft. At 07:00 the State Commission meets at Area 2. All Chief Designers, Commanders, and Section report that all is ready for flight. The commission gives the order to proceed with the launch. Weather at the pad is 7 balls, 8-10 m/s wind with gusts to 15 m/s, temperature 9 to 12 deg C. Weather in the recovery zones is reported as winds up to 15 m/s. Weather in the recovery zone is not clear, but that is not considered an impediment, and in fact Kamanin would like to see how the landing system functions in bad conditions. Kamanin visits the pad at T-30 seconds; at T-20 seconds, the veranda at IP-1 has over 50 viewers of the launch, including 15 cosmonaut candidates and the 7 Voskhod cosmonauts. Kamanin is relegated to the IP-1 veranda this time, with Rudenko, Kirillov, and Tyulin the bunker adjacent to the pad. Korolev stays with the booster until T-5 minutes, then enters the bunker. The booster ignites precisely at 10:00; the strap-ons burn out and are jettisoned at T+120 seconds; the core burns out and the final stage ignites at T+290 seconds; and at T+523 seconds spacecraft 3KV number 2 is placed in orbit as the final stage shuts down. The spacecraft separates and all systems look normal.

    Recovered October 7, 1964 7:28 GMT. Officially: Investigation of the upper atmosphere and outer space.


1964 October 6 - . 17:04 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Delta. Launch Vehicle: Thor Able-Star. LV Configuration: Thor Ablestar-2 423 AB016.
  • Transit O-1 - . Payload: NNS 30010 / Ablestar 016 / OPS 5798. Mass: 60 kg (132 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 897 . COSPAR: 1964-063B. Apogee: 1,077 km (669 mi). Perigee: 1,046 km (649 mi). Inclination: 90.2000 deg. Period: 106.40 min. Summary: Naval Avionics Facility-assembled production spacecraft. Failed after a few days operation..
  • Calsphere 2 - . Payload: Dragsphere 2. Mass: 10 kg (22 lb). Nation: USA. Agency: USN. Class: Military. Type: Radar calibration target. Spacecraft: Calsphere. USAF Sat Cat: 902 . COSPAR: 1964-063E. Apogee: 1,078 km (669 mi). Perigee: 1,049 km (651 mi). Inclination: 90.2000 deg. Period: 106.50 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • Calsphere 1 - . Payload: Dragsphere 1. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USN. Class: Military. Type: Radar calibration target. Spacecraft: Calsphere. USAF Sat Cat: 900 . COSPAR: 1964-063C. Apogee: 1,034 km (642 mi). Perigee: 997 km (619 mi). Inclination: 90.1000 deg. Period: 105.50 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1964 October 6 - . 20:20 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 2B. LV Configuration: Black Brant IIB CC-2B-49.
  • Test mission - . Nation: Canada. Agency: CARDE. Apogee: 211 km (131 mi).

1965 October 6 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF22. LV Family: Minuteman. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 2002.
  • Research and development launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1965 October 6 - . 04:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-9.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 141 km (87 mi).

1966 October 6 - . Launch Site: Baikonur. Launch Complex: Baikonur PU32. LV Family: Tsiklon. Launch Vehicle: R-36 8K67.
  • Operational missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1966 October 6 - . Launch Site: Green River. Launch Complex: Green River Pad 3. LV Family: Athena RTV. Launch Vehicle: Athena RTV. LV Configuration: Athena D024.
  • USN D024 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1966 October 6 - . 20:16 GMT - . Launch Site: Hidden Hills DZ. Launch Pad: 36.1 N x 116.0 W. Launch Platform: NB-52 003. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 1-69-116. FAILURE: Emergency landing at Cuddleback Dry Lake..
  • X-15A Checkout mission - . Nation: USA. Agency: NASA; USAF. Apogee: 23 km (14 mi). Summary: Maximum Speed - 4666 kph. Maximum Altitude - 22980 m. Engine shut down at 90 seconds..

1966 October 6 - . 20:29 GMT - . Launch Site: Wallops Island. LV Family: Javelin. Launch Vehicle: Javelin. LV Configuration: Javelin NASA 8.38GI.
  • Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 650 km (400 mi).

1967 October 6 - .
  • Soyuz parachute trials at Fedosiya. - . Nation: USSR. Related Persons: Mishin. Program: Lunar L1; Soyuz. Spacecraft: Soyuz 7K-OK; Soyuz 7K-L1. They need to complete 70 drops, which normally would take five to six months. Mishin still insists that they be completed by 1 November. Three tests are made in one day, a record, including the drop of a Soyuz mock-up at 17:55 from an An-12. The parachute deployed correctly, but the soft landing system fired at 2000 m instead of 1.2 m. The spacecraft hit the ground on its side at 8 m/s. Because of the angle of impact the crew seat shock absorbers couldn't function. If any cosmonauts had been aboard, they would have suffered serious trauma.

1969 October 6 - .
  • Soyuz 6/7/8 experiment review - . Nation: USSR. Related Persons: Shatalov; Mishin. Program: Soyuz. Flight: Soyuz 6; Soyuz 7; Soyuz 8. Meeting between the Soyuz 6/7/8 crews and engineers. Shatalov pushes his idea for a manually flown spacecraft rendezvous, provided that Soyuz 7 and 8 visually acquire each other immediately after Soyuz 8 is put into orbit. He believes this would not only save time and fuel, but also provide the chance to develop procedures for interception of non-cooperative enemy satellites. Mishin rejects the idea, seeing a doubling of risk of an unsuccessful flight. The fact is, the Soyuz is only equipped for automatic docking. There are no on-board indicators of range and range-rate to target - necessary inputs for any manual docking. The view through the periscope is the only forward-looking view available to the crew, and it is inadequate for manual docking. Additional Details: Soyuz 6/7/8 experiment review.

1969 October 6 - . Launch Site: White Sands. Launch Complex: White Sands LC50. Launch Vehicle: Sprint. LV Configuration: Sprint ABM FLA-36. FAILURE: Failure.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 0 km ( mi).

1969 October 6 - . 01:45 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Vostok 8A92M.
  • Meteor 1-02 - . Payload: Meteor M no. 2. Mass: 3,800 kg (8,300 lb). Nation: USSR. Agency: MOM. Class: Earth. Type: Weather satellite. Spacecraft: Meteor M 11F614. Decay Date: 2002-08-20 . USAF Sat Cat: 4119 . COSPAR: 1969-084A. Apogee: 552 km (342 mi). Perigee: 513 km (318 mi). Inclination: 81.2000 deg. Period: 95.30 min. Summary: Cloud and ice cover imaging; investigated IR, thermal reflection/radiation from Earth's atmosphere. Acquisition of meteorological information needed for use by the weather service. .

1970 October 6 - .
  • Spiral spaceplane project review. - . Nation: USSR. Related Persons: Mikoyan; Dementiev; Grechko, Andrei; Zakharov; Krylov; Titov. Spacecraft: Spiral OS. Meeting with the Spiral spaceplane cosmonaut training group. Mikoyan and Dementiev (son of the MAP Minister) have been working on this project for four years. Many in the leadership (Grechko, Zakharov, Krylov, etc) are against the concept and hinder the project in any way the can. Grechko considers it 'a fantasy' and Kutakhov does not support it energetically. Engineer-Colonel Sokolov-Sokolenik is the head of the unit (having replaced Titov, who is now in staff school). The United States has hundreds of flights on the X-15, which they have taken to 90 km altitude and 7000 km/hour airspeed. In the Soviet Union, all such work has been frozen for a decade.

1970 October 6 - .
  • Cosmonaut training centre status. - . Nation: USSR. Program: Salyut; Almaz; Lunar L3. Spacecraft: Spiral OS; Almaz OPS. Kamanin reviews the work of the training centre in 1970-1971. There are 12 cosmonauts training for DOS missions; 22 for Almaz; 5 for Spiral; and a 'group' for the L3. They have flown 5000 flight hours in jet trainers. During the last two years Kamanin has increased the number of trainers and simulators available; achieved 100% of the training plan; and met the physical training requirements (all cosmonauts must accomplish a 10 km run).

1970 October 6 - . 10:50 GMT - . Launch Site: Biscarosse. LV Family: Belier. Launch Vehicle: Dragon 3. LV Configuration: Dragon 3 D-305.
  • EIDI-1 Ionosphere mission - . Nation: France. Agency: CNES. Apogee: 480 km (290 mi).

1970 October 6 - . 13:36 GMT - . Launch Site: Natal. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache N-NA-31.
  • DLR N-NA-31 Ionosphere / plasma mission - . Nation: Germany. Agency: DLR. Apogee: 200 km (120 mi).

1970 October 6 - . 15:15 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 629. Launch Vehicle: Poseidon. LV Configuration: Poseidon C3P-5.
  • PEM-5 operational test launch - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1971 October 6 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF25. LV Family: Minuteman. Launch Vehicle: Minuteman 2.
  • OT GT86F operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1971 October 6 - . 00:32 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.913-6A.
  • Density Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 189 km (117 mi).

1971 October 6 - . 00:33 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.101-5.
  • Neutral Atmosphere Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 117 km (72 mi).

1971 October 6 - . 00:42 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.102-4.
  • Sphere Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 232 km (144 mi).

1971 October 6 - . 01:03 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.913-6.
  • Sphere Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 222 km (137 mi).

1971 October 6 - . 02:45 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.101-6.
  • Neutral Atmosphere Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 119 km (73 mi).

1971 October 6 - . 09:54 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Ionosphere mission - . Nation: USSR. Apogee: 150 km (90 mi).

1971 October 6 - . 12:00 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.902-6.
  • Mass Spectrometer Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 120 km (70 mi).

1971 October 6 - . 12:11 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.101-3.
  • Mass Spectrometer Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 118 km (73 mi).

1971 October 6 - . 12:33 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Magnetic mission - . Nation: USSR. Apogee: 173 km (107 mi).

1971 October 6 - . 12:44 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.101-4.
  • Mass Spectrometer Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 119 km (73 mi).

1971 October 6 - . 13:05 GMT - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL A07.101-2.
  • Mass Spectrometer Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 117 km (72 mi).

1971 October 6 - . 14:08 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Aeronomy mission - . Nation: USSR. Apogee: 150 km (90 mi).

1972 October 6 - .
  • Death of Aleksandr Grigoryevich Mrykin - . Nation: Russia. Related Persons: Mrykin. Summary: Russian officer. First Deputy Commander of GURVO 1955-1965. Strategic Missile Forces liaison with space units..

1972 October 6 - . 17:00 GMT - . Launch Site: Antigua. Launch Vehicle: Rocketsonde.
  • Met Para, Arcasonde - . Nation: USA. Agency: MRN. Apogee: 59 km (36 mi).

1973 October 6 - . Launch Site: Vandenberg. Launch Complex: Vandenberg 395-C. LV Family: Titan. Launch Vehicle: Titan 2. LV Configuration: Titan II B-69.
  • Operational Test M2-27 - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). Summary: SSTTP M2-27 Target mission.

1973 October 6 - . 03:31 GMT - . Launch Site: El Arenosillo. LV Family: Skylark. Launch Vehicle: Skylark 4 AC. LV Configuration: Skylark 4 AC S92.
  • DLR H-GR-56 Optical astronomy / ultraviolet astronomy mission - . Nation: Germany. Agency: DFVLR. Apogee: 260 km (160 mi).

1973 October 6 - . 12:30 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 597 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MK. Duration: 6.00 days. Decay Date: 1973-10-12 . USAF Sat Cat: 6858 . COSPAR: 1973-071A. Apogee: 290 km (180 mi). Perigee: 206 km (128 mi). Inclination: 65.4000 deg. Period: 89.50 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1975 October 6 - . 09:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Delta. Launch Vehicle: Delta 2910. LV Configuration: Delta 2910 600/D115.
  • Explorer 54 - . Payload: AE D. Mass: 676 kg (1,490 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Atmosphere satellite. Spacecraft: AE. Decay Date: 1976-03-12 . USAF Sat Cat: 8353 . COSPAR: 1975-096A. Apogee: 3,819 km (2,373 mi). Perigee: 151 km (93 mi). Inclination: 90.1000 deg. Period: 126.80 min. Summary: Atmospheric Explorer; atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1976 October 6 - . 15:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC43. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 9.00 km (5.50 mi).

1978 October 6 - . 01:55 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Ionosphere mission - . Nation: USSR. Apogee: 125 km (77 mi).

1978 October 6 - . 15:30 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1042 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MKM. Duration: 13.00 days. Decay Date: 1978-10-19 . USAF Sat Cat: 11052 . COSPAR: 1978-092A. Apogee: 299 km (185 mi). Perigee: 179 km (111 mi). Inclination: 62.8000 deg. Period: 89.30 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1979 October 6 - . 04:23 GMT - . Launch Site: Kwajalein. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 79 km (49 mi).

1980 October 6 - . 23:27 GMT - . Launch Site: Andoya. LV Family: Loki. Launch Vehicle: Super Loki. LV Configuration: Super Loki TY1-6191.
  • Aeronomy mission - . Nation: USA. Agency: NASA Wallops. Apogee: 84 km (52 mi).

1981 October 6 - . 11:27 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Delta. Launch Vehicle: Delta 2310. LV Configuration: Delta 2310 639/D157.
  • SME - . Payload: Solar Mesosphere Explorer. Mass: 437 kg (963 lb). Nation: USA. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: SME. Decay Date: 1991-03-05 . USAF Sat Cat: 12887 . COSPAR: 1981-100A. Apogee: 337 km (209 mi). Perigee: 335 km (208 mi). Inclination: 97.6000 deg. Period: 91.30 min. Summary: Solar Mesosphere Explorer. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..
  • Oscar 9 - . Payload: UoSAT 1. Mass: 52 kg (114 lb). Nation: UK. Agency: Surrey. Manufacturer: Surrey. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Microsat SSTL. Decay Date: 1989-10-13 . USAF Sat Cat: 12888 . COSPAR: 1981-100B. Apogee: 374 km (232 mi). Perigee: 372 km (231 mi). Inclination: 97.6000 deg. Period: 92.00 min. University of Surrey research microsatellite. Radio science; also carried amateur radio package. Communication and geophysics research satellite. Launch time 1127 GMT. Also registered by the United States in ST/SG/SER.E/59, with category D and orbital parameters 95.3 min, 531 x 533 km x 97.5 deg. UoSAT-OSCAR 9 was launched piggyback with Solar Mesosphere Explorer satellite. Weight 52 kg. Box shaped 740 x 420 x 420 mm. Deployable gravity gradient boom. Firsts: First on-board computer (IHU - Integrated Housekeeping Unit) for battery and attitude management, remote control, and experiments. Built by the University of Surrey in the United Kingdom, UO-9 was UoSAT's first experimental satellite. It was a scientific and educational low-Earth orbit satellite containing many experiments and beacons but no amateur transponders. UO-9 was fully operational until it re-entered October 13, 1989 from a decaying orbit after nine years of service.

1982 October 6 - . 01:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 86 km (53 mi).

1983 October 6 - . 02:00 GMT - . Launch Site: Kwajalein. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 74 km (45 mi).

1984 October 6 - . 07:00 GMT - . Launch Site: White Sands. LV Family: Black Brant. Launch Vehicle: Black Brant 8C. LV Configuration: Black Brant 8C NASA 27.71UG.
  • IMAPS 1 Far ultraviolet astronomy mission - . Nation: USA. Agency: NASA. Apogee: 273 km (169 mi).

1986 October 6 - . 05:40 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-8 (14).
  • FSW-0 No. 8 - . Payload: FSW-0 No. 08. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 5.00 days. Decay Date: 1986-10-23 . USAF Sat Cat: 17001 . COSPAR: 1986-076A. Apogee: 337 km (209 mi). Perigee: 169 km (105 mi). Inclination: 57.0000 deg. Period: 89.60 min. Summary: Fanhui Shi Weixing recoverable satellite; capsule re-entered October 11 after five day mission..

1986 October 6 - . 07:40 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1784 - . Payload: Yantar-1KFT no. 6. Mass: 6,600 kg (14,500 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Cartographic satellite. Spacecraft: Yantar-1KFT. Duration: 36.00 days. Decay Date: 1986-11-11 . USAF Sat Cat: 17003 . COSPAR: 1986-077A. Apogee: 283 km (175 mi). Perigee: 190 km (110 mi). Inclination: 64.8000 deg. Period: 89.20 min. Summary: Military topographic / cartographic satellite..

1987 October 6 - . 17:02 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC46. LV Family: Trident. Launch Vehicle: Trident D-5. LV Configuration: Trident D-5 D5X-8.
  • Research and development launch - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1990 October 6 - . 11:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. LV Family: Shuttle. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-41.
  • STS-41 - . Call Sign: Discovery. Crew: Akers; Cabana; Melnick; Richards; Shepherd. Payload: Discovery F11 / Ulysses [IUS + PAM-S]. Mass: 22,140 kg (48,810 lb). Nation: USA. Related Persons: Akers; Cabana; Melnick; Richards; Shepherd. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-41. Spacecraft: Discovery. Duration: 4.09 days. Decay Date: 1990-10-10 . USAF Sat Cat: 20841 . COSPAR: 1990-090A. Apogee: 307 km (190 mi). Perigee: 300 km (180 mi). Inclination: 28.5000 deg. Period: 90.60 min. Manned five crew. Deployed Ulysses spacecraft. Payloads: Deploy Ulysses, Shuttle Solar Backscatter Ultraviolet, Intelsat Solar Array Coupon, Solid-Surface Combustion Experiment, Investigations Into Polymer Membrane Processing, Chromo-some and Plant Cell Division in Space, Physiological Systems Experiment, Voice Command System, Radiation Monitoring Equipment III, Air Force Maui Optical Site.
  • Ulysses - . Payload: Discovery F11 / Ulysses [IUS + PAM-S]. Mass: 367 kg (809 lb). Nation: USA. Agency: NASA; JPL. Class: Astronomy. Type: Solar astronomy satellite. Spacecraft: Ulysses. USAF Sat Cat: 20842 . COSPAR: 1990-090B. Apogee: 300 km (180 mi). Perigee: 285 km (177 mi). Inclination: 28.4000 deg. Period: 90.10 min. Deployed from STS 41 10/6/90; solar research. Ulysses is a scientific spacecraft, within the framework of the international solar/polar mission. It will be the first spacecraft to fly over the poles of the sun. Frequency 2111.6073/2293.1481 MHz, 8408.2099 MHz., interplanetary trajectory i nto a polar flyby over the sun. Designator ESA/90/01. Also registered by the United States in ST/SG/SER.E/250, orbital data are taken from that document.

1992 October 6 - . 06:20 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. Launch Pad: LA2B?. LV Family: CZ. Launch Vehicle: CZ-2C. LV Configuration: Chang Zheng 2C CZ2C-13 (29).
  • Freja - . Payload: FSW-1 4 / Freja. Mass: 259 kg (570 lb). Nation: Sweden. Agency: SSC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Freja. USAF Sat Cat: 22161 . COSPAR: 1992-064A. Apogee: 1,763 km (1,095 mi). Perigee: 590 km (360 mi). Inclination: 63.0000 deg. Period: 108.90 min. Ionospheric, auroral, amgnetospheric studies. Freja is a Swedish/German satellite designed for research into the aurora. The satellite was launched piggyback on a Long March 2C (CZ-2C) rocket and weighs 214 kg in orbit. It is a sun-pointing spinner (10 rpm) with a 2.2 m diameter. It will make high re solution measurements in the upper ionosphere and lower magnetosphere. Data will be received at Esrange, Kiruna, Sweden and at the Prince Albert Satellite Station in Canada's Saskatchewan Province. Launch time 0620 UT.
  • Freja - . Nation: Sweden. Agency: PRC. Spacecraft: Freja. USAF Sat Cat: 22161 . COSPAR: 1992-064xx. Apogee: 1,782 km (1,107 mi). Perigee: 521 km (323 mi). Inclination: 63.0000 deg. Period: 108.40 min.
  • FSW-1 No. 4 - . Payload: FSW-1 No. 04. Mass: 2,100 kg (4,600 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Duration: 6.00 days. Decay Date: 1992-10-31 . USAF Sat Cat: 22162 . COSPAR: 1992-064B. Apogee: 309 km (192 mi). Perigee: 213 km (132 mi). Inclination: 63.0000 deg. Period: 89.70 min. Summary: Fanhui Shi Weixing recoverable imaging satellite; carried remote sensing, microgravity experiments; capsule recovered October 13 after 6 days in orbit..

1994 October 6 - . 06:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-111 / Centaur II 8202.
  • Intelsat 703 - . Payload: NSS 703. Mass: 3,656 kg (8,060 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 23305 . COSPAR: 1994-064A. Apogee: 35,792 km (22,240 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.0400 deg. Period: 1,436.07 min. 38 C-band and 20 Ku-band transponders. Initially positioned in geosynchronous orbit at 177 deg E in 1994-1996. Then reassigned to Intelsat subsidiary New Skies, redesignated NSS 703, and moved to 57 deg E after 1996. At the crossroads of three continents, NSS-703 provided cross-connectivity for Europe, Africa and Asia. NSS-703 was used for video contribution from Europe to India and Africa, and was capable of bringing signals from London to India and Australia in one hop. NSS-703's coverage included a global beam, and two C-band hemispheric beams, which covered Africa and the triangle from Eastern Iran to Japan and Australia, including all of India and China. Three steerable Ku-band spot beams targeted Europe and Iran, Central Asia and Afghanistan-Pakistan-North India. Expected end of life March 2009. As of 2007 Mar 9 located at 56.96E drifting at 0.001E degrees per day.

1994 October 6 - . 13:22 GMT - . Launch Site: Alcantara. LV Family: Black Brant. Launch Vehicle: Black Brant 5C. LV Configuration: Black Brant VC NASA 21.112GE. FAILURE: Failure.
  • GUARA Electrojet Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 120 km (70 mi).

1995 October 6 - . 03:23 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M.
  • Cosmos 2321 - . Mass: 825 kg (1,818 lb). Nation: Russia. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Parus. Decay Date: 1997-08-21 . USAF Sat Cat: 23676 . COSPAR: 1995-052A. Apogee: 754 km (468 mi). Perigee: 256 km (159 mi). Inclination: 82.9000 deg. Period: 87.10 min. Summary: Second stage anomaly; failed to reach desired orbit; military navigation..

1996 October 6 - .
  • Death of Richard W Porter - . Nation: USA. Related Persons: Porter. Summary: American engineer; his 400-strong GE team at Malta, NY, built US versions of the V-2 and Wasserfall, and engine for Vanguard. Influential, on many committees, but Malta was a dead-end, and closed in 1984..

1997 October 6 - .
  • Mir News 387: Communications Mir during mission STS86 - . Nation: Russia. Program: Mir. Flight: STS-86; Mir NASA-5; Mir NASA-4; Mir EO-24. The communications to and from the Mir during the link-up period of Atlantis and Mir demonstrated what we can expect when of the International Space station the Russian and American segments will be operational. For matters regarding the whole complex the American side will take care for the communications and traffic between the Russian segment and TsUP-M will only concern Russian matters (experiments, maintenance, advice, etc.) The lion's share of the communications went via Atlantis. During windows in which the Mir was able to communicate via Russian tracking facilities they only handled Russian matters. The communications between Mir and Atlantis took place via an intercom system. Sometimes Atlantis also took care of the Packet Radio traffic for Mir. During the link-up Mir seldom used the Altair-2 facility. Images of the approach of Atlantis and the EVA of Parazynski and Titov made from inside Mir were directly transmitted to earth via Russian tracking stations on UHF frequencies. Sometimes the comments on those images went via the VHF channel. On 28.09 Altair-2 was in use for the relay of video-recordings.

    Progress-M36:

    This freighter blasted off from Baykonur on 5.10.1997 at 15.08.57 UTC. All went well. The Progress-M36 will deliver the normal cargo: water, food, fuel, experiments and a spare computer. Among the repair material is a special glue ('germetik') to be used during the repair of the Spektr. Progress-M36 is expected to dock at Mir's aft docking port (Kvant-1 +X axis) on 7.10 at 1642 UTC.

    Transmissions Progress-M36:

    On 5.10 during the 3d orbit (1944-1946 UTC) Telemetry was heard in the 165 and 166 mc bands. During the 4th orbit (2114-2119 UTC) the signals in the 165 and 166 mc were very strong. The transmitter on 922.755mc was active during that pass. TCA was at 21.15.54 UTC

    Progress-M35:

    This old freighter is no longer needed and will separate from Mir on 6.10 at 1124 UTC for a short autonomous flight and decay in the atmosphere over a designated area in the Pacific East of New Zealand at 1424 UTC.

    Mini-sputnik:

    A small copy of Sputnik-1 will also be delivered by Progress-M36. During the next EVA of Solovyov and Vinogradov on 16.10.1997 this Sputnik will be 'launched' manually. This satellite will send 'bleeps' on a frequency in the 2 Meter amateur band to recall the launch of the first artificial earth satellite on 4.10.1957.

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


1997 October 6 - .
2000 October 6 - . 23:00 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 42L. LV Configuration: Ariane 42L-3 V133.
  • N-SAT-110 - . Mass: 3,531 kg (7,784 lb). Nation: Japan. Agency: SCC. Manufacturer: Lockheed. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 26559 . COSPAR: 2000-060A. Apogee: 35,792 km (22,240 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. N-SAT-110, also known as Superbird 5, was jointly owned by SCC (Space Communications Corporation of Tokyo) and JSat (Japan Satellite Systems). SCC controlled the vehicle on orbit. The satellite carried 24 Ku-band transponders. By October 15 N-SAT-110 was in a 35610 x 35752 km x 0.1 deg orbit drifting past 109 deg E. Stationed at 110 deg E. Positioned in geosynchronous orbit at 110 deg E in 2000. As of 4 September 2001 located at 110.06 deg E drifting at 0.012 deg W per day. As of 2007 Mar 11 located at 110.07E drifting at 0.007W degrees per day.

2001 October 6 - . 16:45 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 405-01?.
  • Raduga-1 - . Payload: Globus 2 / Raduga 1-6. Mass: 2,000 kg (4,400 lb). Nation: Russia. Agency: VKS. Manufacturer: Reshetnev. Class: Communications. Type: Military communications satellite. Spacecraft: Raduga-1. USAF Sat Cat: 26936 . COSPAR: 2001-045A. Apogee: 35,801 km (22,245 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.9000 deg. Period: 1,436.00 min. The Blok-DM2 upper stage put the Russian geosynchronous military communications satellite into a geosynchronous transfer orbit at 1755 GMT. A second burn at 2318 GMT to circularized the orbit at geostationary altitude. As of 2007 Mar 10 located at 106.48E drifting at 9.104W degrees per day.

2004 October 6 - . Launch Site: Wake Island. LV Family: Minuteman. Launch Vehicle: SR19/SR19.
  • CMP-4B Target mission - . Nation: USA. Agency: USA SMDC; MDA. Apogee: 200 km (120 mi).

2004 October 6 - . Launch Site: Thumba. LV Family: RH. Launch Vehicle: RH-200.
  • Middle Atmosphere Aeronomy mission - . Nation: India. Agency: ISRO. Apogee: 74 km (45 mi).

2005 October 6 - . 21:30 GMT - . Launch Site: Barents Sea Launch Area. Launch Pad: 69.5 N x 34.2 E. Launch Platform: K-496. LV Family: R-29. Launch Vehicle: Volna SLV.
  • IRDT-2R re-entry vehicle test flight - . Nation: Germany. Agency: VMF. Apogee: 200 km (120 mi). Suborbital test of the Demonstrator inflatable reentry technology test vehicle. The reentry vehicle could not be located in the Kamchatka Peninsula impact zone and was not recovered. Test delayed from the fourth quarter of 2003, then May and October 2004, then July 5, July 8, September 15, September 27, 2005.

2006 October 6 - .
2009 October 6 - . Launch Site: Okhotsk. Launch Platform: K-43. LV Family: R-29. Launch Vehicle: Volna SLV.
  • Volna RV - . Mass: 1,000 kg (2,200 lb). Nation: Russia. Agency: VMF. Summary: Operational test.

2010 October 6 - . 00:49 GMT - . Launch Site: Taiyuan. LV Family: CZ. Launch Vehicle: CZ-4B.
  • SJ-6G - . Payload: SJ-6/4A. Mass: 1,000 kg (2,200 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Surveillance satellite. Spacecraft: SJ-6. USAF Sat Cat: 37179 . COSPAR: 2010-051A. Apogee: 606 km (376 mi). Perigee: 587 km (364 mi). Inclination: 97.7000 deg. Period: 96.60 min. Summary: Fourth pair of SJ-6 military surveillance satellites..
  • SJ-6H - . Payload: SJ-6/4B. Mass: 200 kg (440 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Surveillance satellite. Spacecraft: SJ-6. USAF Sat Cat: 37180 . COSPAR: 2010-051B. Apogee: 604 km (375 mi). Perigee: 588 km (365 mi). Inclination: 97.7000 deg. Period: 96.60 min.

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