Encyclopedia Astronautica
November 06


November 06 Chronology


1918 November 6 - .
  • Goddard demonstrates rockets to US government. - . Nation: USA. Related Persons: Goddard. After demonstrations to Army officers of work achieved at Mt Wilson, Goddard is requested to demonstrate his rockets at the Aberdeen Proving Ground in Maryland. The scientists and representatives of the Signal Corps, Air Service, Army Ordnance, are most impressed ('this will revolutionise warfare'). Goddard admits that his cartridge rocket concepts have been less successful and 'need further work'. The next day, Germany surrenders, World War I ends, and funding dries up.

1933 November 6 - . Launch Vehicle: GIRD-09. FAILURE: Failure.
  • GIRD-09 launch attempt. - . Nation: USSR. Summary: Launch failure..

1936 November 6 - .
1944 November 6 - . Launch Site: Heidekraut. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 19508.
  • V-2 Ma264 227 L1 - . Nation: Germany. Summary: Planned range 250 km. Impact 4.3 km to the right of the planned trajectory. Circular error 4.3 km from aim point..

1947 November 6 - .
  • XS-1 Flight 58 - . Crew: Yeager. Payload: XS-1 # 1 flight 38. Nation: USA. Related Persons: Yeager. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: AF flight 16. Mach 1.35 at 14823 m..

1952 November 6 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 135R.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1953 November 6 - . Launch Site: White Sands. LV Family: Corporal. Launch Vehicle: Corporal. LV Configuration: Corporal 1358R.
  • Test mission - . Nation: USA. Apogee: 30 km (18 mi).

1956 November 6 - .
  • Hywards abbreviated development plan. - . Nation: USA. Spacecraft: Dynasoar; Hywards. Summary: ARDC headquarters issued System Requirement 121, requesting information from Air Force agencies for the preparation of a Hywards abbreviated development plan..

1956 November 6 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC9. LV Family: Navaho. Launch Vehicle: Navaho G-26. LV Configuration: Navaho II SM-64 03. FAILURE: Pitched up, disintegrated at T+26 seconds - pitch rate gyro installed backwards.
  • Navaho G-26 Flight 1 - . Nation: USA. Agency: USAF. Apogee: 2.00 km (1.20 mi). Continuing problems with APU reliability delayed the launch to November. Various problems extended the countdown from the planned 7 hours 30 minutes to 14 hours 30 minutes. Successful launch, then vehicle pitched up and disintegrated 26 seconds after launch, impacting 4 km down range. It was found the pitch rate gyro had been installed backward.

1956 November 6 - . Launch Site: Wallops Island. Launch Platform: F2H2. LV Family: Recruit. Launch Vehicle: Recruit.
  • Heat Transfer Re-entry Vehicle test - . Nation: USA. Agency: NASA Cleveland. Apogee: 4.00 km (2.40 mi).

1957 November 6 - .
  • Chelomei OKB-52 gains in importance. - . Nation: USSR. Summary: Ministry of Aviation Industry (MAP) Decree 'On subordinating OKB-52 to GSNII-642' was issued..

1958 November 6 - .
  • X-1E Flight 27 - . Crew: McKay. Payload: X-1E flight 27. Nation: USA. Related Persons: McKay. Class: Manned. Type: Manned rocketplane. Spacecraft: X-1E. Summary: NACA flight 26. Elevated chamber pressure; low-altitude and low-mach investigation of U-Deta fuel. Last NASA flight..

1958 November 6 - . Launch Site: Kheysa. LV Family: R-11. Launch Vehicle: R-11A.
  • Aeronomy mission - . Nation: USSR. Agency: AN. Apogee: 103 km (64 mi).

1958 November 6 - . Launch Site: Wallops Island. LV Family: Honest John. Launch Vehicle: HJ.
  • Corvus Model test flight - . Nation: USA. Agency: NASA. Apogee: 10 km (6 mi).

1958 November 6 - . 00:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone CC-57. FAILURE: Boost phase normal. Space phase malfunction..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Redstone final development test. Missile test failure. Missed aimpoint by 5,010 m..

1959 November 6 - . 07:25 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NN2.78C.
  • Airglow Aeronomy mission - . Nation: USA. Agency: NRL. Apogee: 142 km (88 mi).

1959 November 6 - . 16:36 GMT - . Launch Site: Fort Churchill. LV Family: Aerobee. Launch Vehicle: Aerobee 300. LV Configuration: Aerobee 300 AA10.187C.
  • Utah ne probe Ionosphere mission - . Nation: USA. Agency: USAF. Apogee: 393 km (244 mi).

1961 November 6 - . LV Family: Saturn V. Launch Vehicle: Saturn V.
  • Saturn S-II to use five J-2 engines - . Nation: USA. Program: Apollo. Summary: Marshall Space Flight Center directed NAA to redesign the advanced Saturn second stage (S-II) to incorporate five rather than four J-2 engines, to provide a million pounds of thrust..

1962 November 6 - .
1962 November 6 - . 19:45 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 AC3.148.
  • HR solar spectrum Solar extreme ultraviolet mission - . Nation: USA. Agency: USAF. Apogee: 308 km (191 mi).

1963 November 6 - . 19:30 GMT - . Launch Site: Cape Canaveral. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike Smoke 375.
  • Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 19 km (11 mi).

1964 November 6 - .
  • All major Apollo LEM subcontracts issued - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

1964 November 6 - .
  • Significant milestones for the Apollo LEM planned - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM; LM Structural. NASA anticipated five significant milestones for the LEM during the forthcoming year:

    1. A major review of the entire LEM program (with especial emphasis upon the fiscal picture for 1965 and 1966)
    2. Start of production on LEM-1 (the first LEM flight article)
    3. Delivery of LEM Test Article (LTA)-2 (a dynamic test article) to Huntsville
    4. Start of vibration and static testing on the complete LEM structure
    5. Sea level and altitude qualification testing in the continuing development of the LEM's propulsion systems.

1964 November 6 - . Launch Site: Barking Sands. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-59.
  • Ballistic HRT Aeronomy mission - . Nation: USA. Agency: Sandia. Apogee: 289 km (179 mi).

1964 November 6 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF07. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 848.
  • Operational missile test - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1964 November 6 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF02. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 960. FAILURE: Failure.
  • Operational missile test - . Nation: USA. Agency: USAF SAC. Apogee: 0 km ( mi).

1964 November 6 - . Launch Site: Reggane. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure C66.
  • Sodium / TMA release Aeronomy mission - . Nation: France. Agency: CNES. Apogee: 150 km (90 mi).

1964 November 6 - . Launch Site: Ile du Levant. Launch Pad: CERES. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure C71.
  • TMA Aeronomy mission - . Nation: France. Agency: CNES. Apogee: 150 km (90 mi).

1964 November 6 - . 00:02 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.133GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 120 km (70 mi).

1964 November 6 - . 00:08 GMT - . Launch Site: Thumba. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.131IA.
  • ISRO 10.04? TERLS-12 Aeronomy sodium release mission - . Nation: USA. Agency: NASA. Apogee: 192 km (119 mi).

1964 November 6 - . 05:20 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.134GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 120 km (70 mi).

1964 November 6 - . 08:31 GMT - . Launch Site: CELPA. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure C79.
  • Aeronomy mission - . Nation: France. Agency: CONAE. Apogee: 179 km (111 mi).

1964 November 6 - . 10:00 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.135GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 125 km (77 mi).

1964 November 6 - . 12:02 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA3. LV Family: Scout. Launch Vehicle: Scout X-4. LV Configuration: Scout X-4 S133R.
  • Explorer 23 - . Payload: S-55C. Mass: 134 kg (295 lb). Nation: USA. Agency: NASA Langley. Program: Explorer. Class: Earth. Type: Micrometeoroid satellite. Spacecraft: S-55. Decay Date: 1983-06-29 . USAF Sat Cat: 924 . COSPAR: 1964-074A. Apogee: 980 km (600 mi). Perigee: 463 km (287 mi). Inclination: 51.9000 deg. Period: 99.20 min. Summary: Micrometeoroid data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1964 November 6 - . 13:45 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA5B. Launch Pad: LA5B?. LV Family: Black Knight. Launch Vehicle: Black Knight 301/C2. LV Configuration: Black Knight-301/C2 BK.20.
  • Dazzle re-entry vehicle test - . Nation: UK. Agency: RAE. Apogee: 629 km (390 mi).

1965 November 6 - . 18:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta E. LV Configuration: Thor Delta E 457/D34.
  • Explorer 29 - . Payload: GEOS A. Mass: 175 kg (385 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Astronomy. Type: Solar astronomy satellite. Spacecraft: GEOS. USAF Sat Cat: 1726 . COSPAR: 1965-089A. Apogee: 2,269 km (1,409 mi). Perigee: 1,120 km (690 mi). Inclination: 59.4000 deg. Period: 120.30 min. The primary objective of GEOS-A was to provide global geodetic measurements for determining the positions of fiducial control points on the Earth to an accuracy of 10 meters in an Earth centre of mass co-ordinate system, and to determine the structure of the Earth's gravity field to 5 parts in 10 million. Instrumentation included (1) four optical beacons, (2) laser reflectors, (3) a radio range transponder, (4) Doppler beacons, and (5) a range and range rate transponder. These were designed to operate simultaneously to fulfil the objectives of locating observation points (geodetic control stations) in a three dimensional earth centre-of-mass co-ordinate system within 10 m of accuracy, of defining the structure of the earth's irregular gravitational field and refining the locations and magnitudes of the large gravity anomalies, and of comparing results of the various systems onboard the spacecraft to determine the most accurate and reliable system. In January 1967, a failure in the satellite's command system rendered several geodetic systems inoperable. Radio doppler measurements and the passive laser reflector experiment could continue indefinitely, however. Additional Details: Explorer 29.

1966 November 6 - . 23:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC13. LV Family: Atlas. Launch Vehicle: Atlas Agena D SLV-3. LV Configuration: SLV-3 Agena D 5802 (AA18) / Agena D 6631.
  • Lunar Orbiter 2 - . Payload: Lunar Orbiter B. Mass: 390 kg (850 lb). Nation: USA. Agency: NASA Langley. Class: Moon. Type: Lunar probe. Spacecraft: Lunar Orbiter. Decay Date: 1967-10-11 . USAF Sat Cat: 2534 . COSPAR: 1966-100A. Lunar Orbiter II was launched at 6:21 p.m. EST from Launch Complex 13 at Cape Kennedy, to photograph possible landing sites on the moon for the Apollo program. The Atlas-Agena D booster placed the spacecraft in an earth-parking orbit and, after a 14-minute coast, injected it into its 94-hour trajectory toward the moon. A midcourse correction maneuver on November 8 increased the velocity from 3,051 to 3,133 kilometers per hour. At that time the spacecraft was 265,485 kilometers from the earth.

    The spacecraft executed a deboost maneuver at 3:26 p.m., November 10, while 352,370 kilometers from the earth and 1,260 kilometers from the moon and traveling at a speed of 5,028 kilometers per hour. The maneuver permitted the lunar gravitational field to pull the spacecraft into the planned initial orbit around the moon. On November 15, a micrometeoroid hit was detected by one of the 20 thin-walled pressurized sensors.

    The spacecraft was transferred into its final close-in orbit around the moon at 5:58 p.m. November 15 and the photo-acquisition phase of Lunar Orbiter II's mission began November 18. Thirteen selected primary potential landing sites and a number of secondary sites were to be photographed. By the morning of November 25, the spacecraft had taken 208 of the 211 photographs planned and pictures of all 13 selected potential landing sites. It also made 205 attitude change maneuvers and responded to 2,421 commands.

    The status report of the Lunar Orbiter II mission as of November 28 indicated that the first phase of the photographic mission was completed when the final photo was taken on the afternoon of November 25. On November 26, the developing web was cut with a hot wire in response to a command from the earth. Failure to achieve the cut would have prevented the final readout of all 211 photos. Readout began immediately after the cut was made. One day early, December 6, the readout terminated when a transmitter failed, and three medium-resolution and two high-resolution photos of primary site 1 were lost. Full low-resolution coverage of the site had been provided, however, and other data continued to be transmitted. Three meteoroid hits had been detected.


1967 November 6 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 624. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1967 November 6 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 624. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1967 November 6 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 624. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1968 November 6 - . 19:10 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4W. LV Family: Titan. Launch Vehicle: Titan 3B. LV Configuration: Titan IIIB 3B-19.
  • OPS 5296 - . Payload: KH-8 no. 17 / Agena D. Mass: 3,000 kg (6,600 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-8. Decay Date: 1968-11-20 . USAF Sat Cat: 3532 . COSPAR: 1968-099A. Apogee: 390 km (240 mi). Perigee: 130 km (80 mi). Inclination: 106.0000 deg. Period: 89.70 min. Summary: KH-8 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1969 November 6 - .
1969 November 6 - . 20:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC32B. LV Family: Minuteman. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 FTM-209.
  • Research and development launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1970 November 6 - . 02:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF05. LV Family: Minuteman. Launch Vehicle: Minuteman 2.
  • OT GT52M operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1970 November 6 - . 03:36 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Vehicle: Cockatoo. LV Configuration: Cockatoo 108.
  • Aeronomy mission - . Nation: Australia. Agency: WRE. Apogee: 100 km (60 mi).

1970 November 6 - . 10:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan 3C. LV Configuration: Titan IIIC 23C-1 (3C-19). FAILURE: Partial Failure.. Failed Stage: 3.
  • IMEWS 1 - . Payload: DSP Phase 1 s/n 1 / OPS 5960. Mass: 900 kg (1,980 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: DSP. Completed Operations Date: 1973-12-31 . USAF Sat Cat: 4630 . COSPAR: 1970-093A. Apogee: 36,128 km (22,448 mi). Perigee: 25,840 km (16,050 mi). Inclination: 16.4000 deg. Period: 1,197.90 min. First generation geosynchronous ballistic missile launch detection satellite; placed in incorrect subsynchronous orbit. One account claimed that it exhausted its propellant before it could be put into operation, but a 2007service history chart showed that is was considered operational for three years, well beyond its planned life.

1972 November 6 - . 00:04 GMT - . Launch Site: Eglin. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk CRL A08.215-2.
  • Sphere Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 212 km (131 mi).

1973 November 6 - . 15:40 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA8. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 NASA 13.104UG.
  • Astronomy mission - . Nation: USA. Agency: NASA. Apogee: 167 km (103 mi).

1973 November 6 - . 17:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Delta. Launch Vehicle: Delta 0300. LV Configuration: Delta 0300 576/D98.
  • NOAA 3 - . Payload: ITOS F. Mass: 345 kg (760 lb). Nation: USA. Agency: NOAA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. USAF Sat Cat: 6920 . COSPAR: 1973-086A. Apogee: 1,510 km (930 mi). Perigee: 1,501 km (932 mi). Inclination: 102.1000 deg. Period: 116.10 min. Summary: Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1974 November 6 - . 10:00 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 95 km (59 mi).

1975 November 6 - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Delta. Launch Vehicle: Thor DSV-2J. LV Configuration: Thor DSV-2J 274.
  • DG-3 - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).

1976 November 6 - . 11:00 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 83 km (51 mi).

1978 November 6 - . 21:29 GMT - . Launch Site: Barking Sands. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 54 km (33 mi).

1979 November 6 - . 01:14 GMT - . Launch Site: Kwajalein. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 79 km (49 mi).

1980 November 6 - . 12:55 GMT - . Launch Site: Ascension. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 62 km (38 mi).

1981 November 6 - . 21:00 GMT - . Launch Site: Barking Sands. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 95 km (59 mi).

1984 November 6 - . 15:49 GMT - . Launch Site: Antigua. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 61 km (37 mi).

1985 November 6 - . 17:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 73 km (45 mi).

1985 November 6 - .
1986 November 6 - . 16:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 55 km (34 mi).

1987 November 6 - . 05:22 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 83 km (51 mi).

1988 November 6 - . Launch Site: Vandenberg. LV Family: Titan. Launch Vehicle: Titan 34D.
  • Final Titan 34D launch from Vandenberg AFB - . Nation: USA. Summary: Final Titan 34D launch from Vandenberg AFB (first launch on 20 June 1983)..

1988 November 6 - . 18:03 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Titan. Launch Vehicle: Titan 34D. LV Configuration: Titan 34D 34D-14 (04D-7).
  • USA 33 - . Payload: KH-11 no. 9. Mass: 13,500 kg (29,700 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-11. USAF Sat Cat: 19625 . COSPAR: 1988-099A. Apogee: 1,012 km (628 mi). Perigee: 156 km (96 mi). Inclination: 97.9000 deg. Period: 96.40 min. Summary: Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1989 November 6 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF10. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT136GM Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1990 November 6 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF04. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT142GM Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1991 November 6 - . 15:14 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 83 km (51 mi).

1992 November 6 - . 13:09 GMT - . Launch Site: Wallops Island. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 93 km (57 mi).

1995 November 6 - . 05:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan Centaur 401A. LV Configuration: Titan 401A/Centaur K-21/TC-13 (45E-7).
  • USA 115 - . Payload: Milstar DFS 2. Mass: 4,500 kg (9,900 lb). Nation: USA. Agency: USAF. Class: Communications. Type: Military communications satellite. Spacecraft: Milstar. USAF Sat Cat: 23712 . COSPAR: 1995-060A. Apogee: 35,787 km (22,236 mi). Perigee: 35,787 km (22,236 mi). Inclination: 10.0000 deg. Summary: Secure military communication. Positioned in geosynchronous orbit at 4 deg E in 1995-2001. As of 2005 Mar 14 located at 10.26E drifting at 0.012E degrees per day..

1996 November 6 - . 13:06 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF02. Launch Vehicle: Peacekeeper. LV Configuration: Peacekeeper 23PA.
  • Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

1997 November 6 - . 00:12 GMT - .
1997 November 6 - . 00:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta 7925. LV Configuration: Delta 7925 D249.
  • USA 134 - . Payload: GPS 2A-28 / GPS SVN 38. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 25030 . COSPAR: 1997-067A. Apogee: 20,394 km (12,672 mi). Perigee: 19,970 km (12,400 mi). Inclination: 55.0000 deg. Period: 718.00 min. Summary: Final GPS Block 2A satellite. Placed in Plane A Slot 3..

1998 November 6 - . 01:32 GMT - . Launch Site: Kodiak. LV Family: ait. Launch Vehicle: ait.
  • ait-1 test - . Nation: USA. Agency: USAF; OSC. Apogee: 715 km (444 mi).

1998 November 6 - . 13:37 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Delta. Launch Vehicle: Delta 7920-XC. LV Configuration: Delta 7920-10C D262.
  • Iridium 2 - . Payload: Iridium s/n SV087. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25527 . COSPAR: 1998-066A. Apogee: 603 km (374 mi). Perigee: 590 km (360 mi). Inclination: 85.6000 deg. Period: 96.60 min. Summary: Plane 5. Ascending node 289.1 degrees. Parking orbit..
  • Iridium 86 - . Payload: Iridium s/n SV086. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25528 . COSPAR: 1998-066B. Apogee: 712 km (442 mi). Perigee: 708 km (439 mi). Inclination: 86.5000 deg. Period: 99.00 min. Summary: Plane 5. Ascending node 293.9 degrees. Raising orbit..
  • Iridium 85 - . Payload: Iridium s/n SV085. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2000-12-30 . USAF Sat Cat: 25529 . COSPAR: 1998-066C. Apogee: 536 km (333 mi). Perigee: 512 km (318 mi). Inclination: 86.0200 deg. Period: 95.12 min. Summary: Plane 5. Ascending node 291.1 degrees. Parking orbit..
  • Iridium 84 - . Payload: Iridium s/n SV084. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25530 . COSPAR: 1998-066D. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 5. Ascending node 294.1 degrees. Raising orbit..
  • Iridium 83 - . Payload: Iridium s/n SV083. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25531 . COSPAR: 1998-066E. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 5. Ascending node 294.2 degrees..

2000 November 6 - .
  • ISS Status Report: ISS 00-51 - . Nation: USA. Related Persons: Gidzenko; Shepherd. Program: ISS. Flight: ISS EO-1. Summary: The Expedition One crewmembers installed backup rendezvous equipment and conducted the first exercise on board the International Space Station as they near the end of the first week of their four-month mission.. Additional Details: ISS Status Report: ISS 00-51.

2002 November 6 - . Launch Site: Mojave. Launch Vehicle: Tier One.
  • White Knight Flight 15 - . Nation: USA. Related Persons: Binnie; Siebold. Program: X-Prize. Spacecraft: SpaceShipOne. Flight Time: 2.4 hours Pilot: Siebold Copilot: Binnie. Objectives: Continued engine, ECS and avionics evaluation. High-rate nose wheel steering assessment. Results: Difficulty maintaining afterburner on left engine near 50,000 feet. Improved ECS configuration showed improved resistance to fogging. Nose wheel steering gearing change about the same.

2004 November 6 - . 03:10 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: CZ-4B. LV Configuration: Chang Zheng 4B CZ4B-8 (82).
  • ZY-2C - . Nation: China. Agency: SISE. Class: Earth. Type: Earth resources satellite. Spacecraft: ZY. USAF Sat Cat: 28470 . COSPAR: 2004-044A. Apogee: 504 km (313 mi). Perigee: 479 km (297 mi). Inclination: 97.3000 deg. Period: 94.40 min. Summary: Zi Yuan 2-3 was a low earth orbit digital imaging spacecraft used by the Chinese government, probably for both civilian and military reconnaissance purposes..

2004 November 6 - . 05:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Delta. Launch Vehicle: Delta 7925-9.5. LV Configuration: Delta 7925-9.5 D308.
  • USA 180 - . Payload: GPS 2R-13 / Navstar 61. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft: GPS Block 2R. USAF Sat Cat: 28474 . COSPAR: 2004-045A. Apogee: 20,413 km (12,684 mi). Perigee: 19,810 km (12,300 mi). Inclination: 54.9000 deg. Period: 715.10 min. Summary: Launch delayed from September 22, October 8, 25 and 30, November 5. Fired its apogee motor at around 02:40 GMT on November 9 to transfer from its initial 159 x 20380 km x 39.1 deg transfer orbit to its operational orbit in the GPS constellation..

2007 November 6 - .
2010 November 6 - . 02:20 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Delta. Launch Vehicle: Delta 7420-10.
  • Cosmo-SkyMed 4 - . Nation: Italy. Class: Surveillance. Type: Civilian surveillance radar satellite. Spacecraft: Cosmo-SkyMed. USAF Sat Cat: 37216 . COSPAR: 2010-060A. Apogee: 623 km (387 mi). Perigee: 622 km (386 mi). Inclination: 97.9000 deg. Period: 97.20 min. Summary: X-band radar satellite..

Home - Browse - Contact
© / Conditions for Use