Encyclopedia Astronautica
April 07


April 07 Chronology


1907 April 7 - .
  • Birth of Johann G Tschinkel - . Nation: Austria; Germany. Summary: German-Austrian rocket technician, arrived in the United States under Project Paperclip on 1945.11.16 aboard the Argentina from La Havre. Fluent in English prior to arrival in the United States. Died in Tallahassee, Florida..

1939 April 7 - .
1944 April 7 - . Launch Site: Peenemuende. Launch Complex: Peenemuende P7. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 17043.
1948 April 7 - .
  • XS-1 Flight 82 - . Crew: Lundquist. Payload: XS-1 # 1 flight 47. Nation: USA. Related Persons: Lundquist. Class: Manned. Type: Manned rocketplane. Spacecraft: XS-1. Summary: AF flight 25. Glide flight only..

1952 April 7 - .
  • MY BIRTHDAY - . Nation: USA.

1954 April 7 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 1430E.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1955 April 7 - . Launch Site: White Sands. LV Family: Corporal. Launch Vehicle: Corporal. LV Configuration: Corporal 1574R.
  • Test mission - . Nation: USA. Apogee: 30 km (18 mi).

1956 April 7 - . LV Family: Navaho. Launch Vehicle: Navaho G-26.
  • First Navaho G-26 flight cruise stage delivered to Cape Canaveral - . Nation: USA. Program: Navaho. However continued problems and late delivery of the Auxiliary Power Unit pushed the planned first launch date from May to July. Three APU's were shipped before one was accepted. Attempts for a pad static test of the boost engines began in August. Seven attempts were made through the end of September. The fiberglass liquid oxygen tank insulation delaminated during the first propellant loading; chair springs were used to hold it on in subsequent tests. Helium lines ruptured; the engine was shut off after three seconds due to high gas generator temperatures; the G-26 cruise stage's landing gear deployed internally, cracking the skin; finally at the end of September a 34-second test was completed, but on ground power after the APU failed. The missile was pulled from the flight order and the first Broomstick flight canceled.

1958 April 7 - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Hi Ball 1 Balloon test - . Nation: USA. Agency: NASA Cleveland. Apogee: 244 km (151 mi).

1959 April 7 - . Launch Vehicle: RS.
  • NM-1 first flight - . Nation: USSR. Summary: A subsonic aerodynamic test vehicle of the RSR trisonic missile, the NM-1 was first flown oby test p[ilot Amert-Khan Sultan..

1959 April 7 - . 14:46 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 AA3.160C. FAILURE: Failure.
  • Aeronomy mission - . Nation: USA. Agency: USAF. Apogee: 317 km (196 mi).

1960 April 7 - . 02:06 GMT - . Launch Site: Eglin. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 AA3.221.
  • Infrared studies Solar infrared mission - . Nation: USA. Agency: USAF. Apogee: 236 km (146 mi).

1961 April 7 - . Launch Site: Wallops Island. LV Family: Nike. Launch Vehicle: Nike Recruit.
  • Reentry Stability re-entry vehicle test flight - . Nation: USA. Agency: NASA. Apogee: 10 km (6 mi).

1962 April 7 - .
  • ACF Electronics Division, Riverdale, California, of ACF Industries, Inc., received a $1 million subcontract from McDonnell to provide C- and S-band radar beacons for the Gemini spacecraft. - . Nation: USA. Spacecraft: Gemini; Gemini Radar. These beacons formed part of the spacecraft's tracking system. With the exception of frequency-dependent differences, the C-band beacon was nearly identical to the S-band beacon. Their function was to provide tracking responses to interrogation signals from ground stations.

1964 April 7 - .
  • First of two Apollo lunar landing research vehicles completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LLRV. Summary: Bell Aerosystems Company completed the first of two lunar landing research vehicles, to be delivered to the NASA Flight Research Center for testing..

1964 April 7 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC31B. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 443.
  • Research and development launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

1964 April 7 - . 05:29 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 2. LV Configuration: Black Brant II AA-2A-43.
  • Auroral particles Aurora / ionosphere / micrometeorites mission - . Nation: Canada. Agency: NRCC. Apogee: 155 km (96 mi).

1964 April 7 - . 14:13 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 KP3.4.
  • Dayglow Aeronomy mission - . Nation: USA. Agency: KPNO. Apogee: 223 km (138 mi).

1965 April 7 - .
  • A LEM/Apollo CSM interface meeting uncovered a number of design problems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM; CSM RCS; LM Communications; LM RCS. A LEM/CSM interface meeting uncovered a number of design problems and referred them to the Systems Engineering Division (SED) for evaluation: the requirement for ground verification of panel deployment prior to LEM withdrawal; the requirement for panel deployment in earth orbit during the SA-206 flight; the absence of a backup to the command sequencer for jettisoning the CSM (Flight Projects Division (FPD) urged such a backup signal); and Grumman's opposition to a communications link with the LEM during withdrawal of the spacecraft (FPD felt that such a link was needed through verification of reaction control system ignition). SED's recommendations on these issues were anticipated by April 22.

1966 April 7 - . 16:00 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 643. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3P-445. FAILURE: Failure.
  • Operational Test / 1 of 2 launches failed - . Nation: USA. Agency: USN. Apogee: 20 km (12 mi).

1966 April 7 - . 16:30 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 643. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3P-400.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1966 April 7 - . 22:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Delta. Launch Vehicle: Thor Agena D SLV-2A/D. LV Configuration: Thor SLV-2A Agena D 474 / Agena D SS-01B 1627.
  • KH-4A 1031 - . Payload: KH-4A s/n 1031 / Agena D 1627 / OPS 1612. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-4A. Decay Date: 1966-04-26 . USAF Sat Cat: 2136 . COSPAR: 1966-029A. Apogee: 312 km (193 mi). Perigee: 193 km (119 mi). Inclination: 75.1000 deg. Period: 89.60 min. Summary: KH-4A. The aft-looking camera malfunctioned after the recovery of bucket '1'. No material was received in bucket '2' (1031-2)..

1967 April 7 - .
  • Joseph F Shea, appointed Deputy Associate Administrator - . Nation: USA. Related Persons: Low, George; Shea. Program: Apollo. Joseph F. Shea, MSC Apollo Spacecraft Program Office Manager, was appointed NASA Deputy Associate Administrator for Manned Space Flight, with responsibility for technical aspects of the program.

    George M. Low, MSC Deputy Director, would succeed Shea as ASPO Manager. Changes were to be effective April 10.


1967 April 7 - . 08:25 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.186UG.
  • Ultraviolet astronomy mission - . Nation: USA. Agency: NASA. Apogee: 176 km (109 mi).

1967 April 7 - . 11:19 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576B2. LV Family: Atlas. Launch Vehicle: Atlas D. LV Configuration: Atlas D 38D.
  • ABRES AX-1 / Pod 30 Reentry test / ionosphere mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).

1967 April 7 - . 19:57 GMT - . Launch Site: Kiruna. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.328IE.
  • DLR K-NA-1 Aurora / barium release mission - . Nation: Germany. Agency: NASA; DLR. Apogee: 231 km (143 mi).

1967 April 7 - . 21:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF09. Launch Pad: LF09?. LV Family: Minuteman. Launch Vehicle: Minuteman 1B. LV Configuration: Minuteman 1B 1426. FAILURE: Failure.
  • Follow-on operational missile test - . Nation: USA. Agency: USAF SAC. Apogee: 10 km (6 mi).

1968 April 7 - . 05:45 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NRL NB3.204.
  • Stellar X-ray Scan X-ray astronomy mission - . Nation: USA. Agency: NRL. Apogee: 158 km (98 mi).

1968 April 7 - . 10:09 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Molniya 8K78M. LV Configuration: Molniya 8K78M Ya716-58.
  • Luna 14 - . Payload: E-6LS s/n 113. Mass: 1,700 kg (3,700 lb). Nation: USSR. Agency: MOM. Program: Lunar L3. Class: Moon. Type: Lunar probe. Spacecraft: Luna E-6LS. USAF Sat Cat: 3178 . COSPAR: 1968-027A. Lunar Orbiter; studied lunar gravitational field, Earth-Moon gravitational relationship, and conducted further scientific experiments in circumlunar space. Not revealed until years later was that the E-6LS was primarily intended to test tracking and communications networks for the Soviet manned lunar program. The Luna 14 spacecraft entered a 140 x 870 km x 42 degree lunar orbit on April 10, 1966. The spacecraft instrumentation was similar to that of Luna 10 and provided data for studies of the interaction of the earth and lunar masses, the lunar gravitational field, the propagation and stability of radio communications to the spacecraft at different orbital positions, solar charged particles and cosmic rays, and the motion of the Moon. This flight was the final flight of the second generation of the Luna series.

1969 April 7 - .
  • A small film canister, designed and fabricated at MSFC, was delivered to KSC for flight test on Apollo 10. - . Nation: USA. Spacecraft: Apollo ATM. The canister, packed with a variety of photographic film, would obtain information on the sensitivity of film to the thermal, pressure, and radiation environment of space, in part equivalent to those which would be experienced by the ATM in flight. The test would also complement ground testing and theoretical analyses that were conducted to evaluate potential film fogging in a space environment.

1970 April 7 - . Launch Vehicle: Spiral 50-50.
  • Spiral spaceplane programme stalled - . Nation: USSR. Related Persons: Goreglyad; Frolov; Titov; Mikoyan; Afanasyev, Sergei; Dementiev; Kutakhov. Spacecraft: Spiral OS. Kamanin reviews the Spiral manned spaceplane program with Goreglyad, Frolov, and cosmonaut Titov. Work on the KLA orbiter began in 1961-1962. In the following eight years Kamanin has tried to push the leadership many times to accelerate the project, but without result. Still, the work is proceeding, albeit very slowly. Mikoyan has decided the first phase of the project will use rocket launch only - the air-breathing winged first stage will only be introduced later. Afanasyev has finally responded to the project, only to declare that the KLA must be not only for military missions, but serve as a transport shuttle for civilian space missions as well. Dementiev is holding the whole project up because he doesn't want to overburden the aircraft design bureaux and factories. And Kutakhov won't push the program without Dementiev's support.

1970 April 7 - . 03:20 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 3 AC. LV Configuration: Skylark 3 AC SL803.
  • Solar ultraviolet echelle Solar ultraviolet mission - . Nation: UK. Agency: BAC. Apogee: 204 km (126 mi).

1970 April 7 - . 11:10 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. Launch Pad: LC132/pad?. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M.
  • Cosmos 330 - . 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: 1979-06-12 . USAF Sat Cat: 4360 . COSPAR: 1970-024A. Apogee: 543 km (337 mi). Perigee: 514 km (319 mi). Inclination: 74.1000 deg. Period: 95.20 min. Summary: Possible navigation satellite. Replaced Cosmos 250..

1971 April 7 - .
  • DOS crew commanders inspect completed DOS#1 station. - . Nation: USSR. Related Persons: Shatalov; Leonov; Dobrovolsky. Program: Salyut. Flight: Soyuz 10; Soyuz 11; Soyuz 12 / DOS 1. Spacecraft: Salyut 1. Shatalov, Leonov, and Dobrovolsky are all working hard on final preparations for DOS-7K. The station is fully complete. Only small defects have been noted. This is the first look by the crews at their future home in space in its fully completed version. On the bus back to the hotel the cosmonauts discuss the poor quality and inedibility of 'space food'.

1971 April 7 - . 06:00 GMT - . Launch Site: Thule AFB. LV Family: Arcas. Launch Vehicle: Sparrow Arcas. LV Configuration: Sparrow Arcas PCA.
  • Ionosphere mission - . Nation: USA. Agency: AFCRL. Apogee: 122 km (75 mi).

1971 April 7 - . 07:10 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Vostok 8A92M.
  • Cosmos 405 - . Payload: Tselina-D no. 2. Mass: 3,800 kg (8,300 lb). Nation: USSR. Agency: MOM. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-D. USAF Sat Cat: 5117 . COSPAR: 1971-028A. Apogee: 603 km (374 mi). Perigee: 594 km (369 mi). Inclination: 81.2000 deg. Period: 96.70 min.

1972 April 7 - .
  • Birth of Timothy Nagel Peake - . Nation: UK. Summary: British pilot mission specialist astronaut, 2009-on..

1972 April 7 - . 07:00 GMT - . Launch Site: Thumba. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.412IP.
  • ISRO 10.43 Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 147 km (91 mi).

1972 April 7 - . 10:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Intercosmos 6 - . Payload: Energia s/n 1. Mass: 6,000 kg (13,200 lb). Nation: USSR. Agency: MOM. Program: Intercosmos. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Energia. Completed Operations Date: 1972-04-11 . Decay Date: 1972-04-11 . USAF Sat Cat: 5936 . COSPAR: 1972-027A. Apogee: 326 km (202 mi). Perigee: 203 km (126 mi). Inclination: 51.8000 deg. Period: 89.80 min. Summary: Investigation of primary cosmic radiation and meteoritic particles in near-earth outer space. .

1972 April 7 - . 14:20 GMT - . Launch Site: Sonmiani. LV Family: Belier. Launch Vehicle: Centaure 1. LV Configuration: Centaure 1 Rehbar 23.
  • Aeronomy / ionosphere mission - . Nation: Pakistan. Agency: SUPARCO. Apogee: 150 km (90 mi).

1973 April 7 - . 09:00 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 85 km (52 mi).

1975 April 7 - . 11:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC90/19. Launch Pad: LC90/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-2.
  • Cosmos 724 - . Mass: 3,800 kg (8,300 lb). Nation: USSR. Agency: MO. Program: RORSAT. Class: Surveillance. Type: Military naval surveillance radar satellite. Spacecraft: US-A. Decay Date: 1975-08-07 . USAF Sat Cat: 7922 . COSPAR: 1975-025B. Apogee: 943 km (585 mi). Perigee: 852 km (529 mi). Inclination: 65.6000 deg. Period: 102.90 min. Summary: Ocean surveillance; nuclear powered..

1976 April 7 - . Launch Site: Biscarosse. Launch Platform: S613. LV Family: MSBS. Launch Vehicle: MSBS M20.
  • Operational test - . Nation: France. Agency: DMA. Apogee: 600 km (370 mi).

1976 April 7 - . 13:05 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Vostok 8A92M.
  • Meteor 1-24 - . Payload: Meteor M s/n 37. Mass: 3,800 kg (8,300 lb). Nation: USSR. Agency: MOM. Class: Earth. Type: Weather satellite. Spacecraft: Meteor M 11F614. USAF Sat Cat: 8799 . COSPAR: 1976-032A. Apogee: 881 km (547 mi). Perigee: 832 km (516 mi). Inclination: 81.3000 deg. Period: 102.10 min. Summary: Acquisition of meteorological information needed for use by the weather service. .

1977 April 7 - . 08:59 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 902 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MK. Duration: 13.00 days. Decay Date: 1977-04-20 . USAF Sat Cat: 9908 . COSPAR: 1977-026A. Apogee: 279 km (173 mi). Perigee: 168 km (104 mi). Inclination: 81.4000 deg. Period: 89.00 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1978 April 7 - . 00:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC13. LV Family: Atlas. Launch Vehicle: Atlas Agena D SLV-3A. LV Configuration: SLV-3A Agena D 5505A / Agena D A 1554.
  • OPS 8790 - . Payload: AFP-472 AQUACADE 4. Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRO; CIA. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Rhyolite. USAF Sat Cat: 10787 . COSPAR: 1978-038A. Apogee: 35,855 km (22,279 mi). Perigee: 35,679 km (22,169 mi). Inclination: 0.2000 deg. Period: 1,435.10 min. Summary: Fourth and final launch of Rhyolite geostationary ELINT satellite. Code name changed to Aquacade after Rhyolite name came out in trial of spy Boyce..

1978 April 7 - . 10:45 GMT - . Launch Site: Atlantic Ocean. Launch Pad: 38.0 N x 75.0 W. Launch Platform: VISE. LV Family: MR-12. Launch Vehicle: MR-12.
  • Aeronomy/Ionosphere mission - . Nation: USSR. Apogee: 178 km (110 mi).

1978 April 7 - . 22:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta 2914. LV Configuration: Delta 2914 626/D140.
  • Yuri 1 - . Payload: BSE-1. Mass: 678 kg (1,494 lb). Nation: Japan. Agency: NASDA. Program: BS. Class: Technology. Type: Communications technology satellite. Spacecraft: Yuri. Completed Operations Date: 1982-01-28 . USAF Sat Cat: 10792 . COSPAR: 1978-039A. Apogee: 35,868 km (22,287 mi). Perigee: 35,736 km (22,205 mi). Inclination: 11.7000 deg. Period: 1,436.90 min. Experimental comsat. Medium-scale broadcasting satellite for experimental purposes (BSE). Launch vehicle Delta 2914-140. Launch time 2201 GMT. Location 110 deg E. Characteristics of satellite: Weight approx 355 kg in an early stage in orbit. Configuration - box shaped satelli te with 2 solar array panels with overall span of 8.95m. Height 3.09m, width 1.32m, length 1.19m. 3-axis stabilized attitude control. Expected life 3 years. Positioned in geosynchronous orbit over the Indian Ocean at 110 deg E in 1978-1982 As of 4 September 2001 located at 44.59 deg E drifting at 0.116 deg E per day. As of 2007 Mar 11 located at 108.19E drifting at 0.031E degrees per day.

1979 April 7 - . 01:48 GMT - . Launch Site: Kheysa. LV Family: MR-12. Launch Vehicle: MR-12.
  • Ionosphere mission - . Nation: USSR. Apogee: 170 km (100 mi).

1979 April 7 - . 06:20 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 65082-424.
  • Cosmos 1091 - . Mass: 810 kg (1,780 lb). Nation: USSR. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Parus. USAF Sat Cat: 11320 . COSPAR: 1979-028A. Apogee: 1,008 km (626 mi). Perigee: 960 km (590 mi). Inclination: 82.9000 deg. Period: 104.80 min. Summary: Military navigation satellite..

1980 April 7 - . 13:30 GMT - . Launch Site: Ascension. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 62 km (38 mi).

1981 April 7 - . 10:51 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1262 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-6U. Duration: 14.00 days. Decay Date: 1981-04-21 . USAF Sat Cat: 12385 . COSPAR: 1981-032A. Apogee: 372 km (231 mi). Perigee: 191 km (118 mi). Inclination: 72.9000 deg. Period: 90.20 min. Summary: Photo surveillance; returned film capsule; maneuverable..

1982 April 7 - . 13:42 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC16/2. LV Family: R-7. Launch Vehicle: Molniya 8K78M.
  • Cosmos 1348 - . Payload: Oko #25. Mass: 1,250 kg (2,750 lb). Nation: USSR. Agency: MOM. Class: Military. Type: Early warning satellite. Spacecraft: Oko. USAF Sat Cat: 13124 . COSPAR: 1982-029A. Apogee: 35,126 km (21,826 mi). Perigee: 5,269 km (3,273 mi). Inclination: 68.4000 deg. Period: 718.60 min. Summary: Replaced Cosmos 1172. Covered Oko constellation plane 9 - 236 degree longitude of ascending node..

1983 April 7 - . 03:00 GMT - . Launch Site: Eareckson. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 48 km (29 mi).

1984 April 7 - . 07:20 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 729. LV Family: Trident. Launch Vehicle: Trident C-4.
  • Demonstration and shakedown operations launch - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1986 April 7 - . 14:17 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 85 km (52 mi).

1987 April 7 - . 20:05 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 83 km (51 mi).

1988 April 7 - . 16:04 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 77 km (47 mi).

1989 April 7 - . 13:00 GMT - . Launch Site: Zingst. Launch Vehicle: MMR-06.
  • MMR06-M Zingst launch 7 - . Nation: USSR. Agency: GMS. Apogee: 72 km (44 mi). Summary: Unsuccessful. Earth impacted at 620 seconds. Reached 72 km. Probe crashed with no braking..

1990 April 7 - . 13:30 GMT - . Launch Site: Xichang. Launch Complex: Xichang LC1. LV Family: CZ. Launch Vehicle: CZ-3. LV Configuration: Chang Zheng 3 CZ3-7 (22).
  • Asiasat 1 - . Mass: 1,442 kg (3,179 lb). Nation: China. Agency: Asiasat. Manufacturer: El Segundo. Program: Asiasat. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 20558 . COSPAR: 1990-030A. Apogee: 35,789 km (22,238 mi). Perigee: 35,786 km (22,236 mi). Inclination: 2.7000 deg. Period: 1,436.20 min. First commercial Chinese launch; Stationed at 105 deg E; formerly Westar 6 (retrieved by STS-51A and refurbished). Fixed-satellite telecommunication services and transmission of television signals. Operational life about 10 years. Orbital position 105.5E. Owner/operator: Asia Satellite Telecommunications Co, Ltd. 23-24/F, East Exchange Tower, 38-40 Leighton Rd, Hong K ong. Telex 68345 ASAT HX Fax 852 576 4111. Operated in geosynchronous orbit at 105 deg E in 1990-1999; 122 deg E in 1999-2000. As of 3 September 2001 located at 121.97 deg E drifting at 0.009 deg E per day. As of 2007 Mar 10 located at 23.96E drifting at 3.706W degrees per day.

1991 April 7 - .
  • EVA STS-37-1 - . Crew: Ross; Apt. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.19 days. Nation: USA. Related Persons: Ross; Apt. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-37. Spacecraft: Atlantis. Summary: Manually deployed Gamma-Ray Observatory's high-gain antenna..

1993 April 7 - . 02:07 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R850.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1995 April 7 - . 23:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. LV Family: Atlas. Launch Vehicle: Atlas IIA. LV Configuration: Atlas IIA AC-114.
  • AMSC-1 - . Mass: 2,700 kg (5,900 lb). Nation: USA. Agency: AMSC. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23553 . COSPAR: 1995-019A. Apogee: 35,796 km (22,242 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Mobile communicaitons. Stationed at 101.1 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 101 deg W in 1995-1999 As of 5 September 2001 located at 101.01 deg W drifting at 0.024 deg W per day. As of 2007 Mar 11 located at 100.99W drifting at 0.003W degrees per day.

1997 April 7 - .
1998 April 7 - . 02:13 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K/17S40. LV Configuration: Proton-K/17S40 (DM2) 391-02.
  • Iridium 62 - . Payload: Iridium s/n SV062. 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: 25285 . COSPAR: 1998-021A. Apogee: 778 km (483 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 1. Ascending node 167.9 degrees..
  • Iridium 63 - . Payload: Iridium s/n SV063. 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: 25286 . COSPAR: 1998-021B. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 1. Ascending node 167.8 degrees..
  • Iridium 68 - . Payload: Iridium s/n SV068. 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: 25291 . COSPAR: 1998-021G. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. The Proton launch vehicle placed the Iridium cluster and the Block DM2 stage into low parking orbit. The DM2 fired twice to enter the deployment orbit and dispensed the seven satellites, which used their own propulsion units to reach operational altitude. The DM2 stage then fired again to deorbit itself, to avoid creating space debris. SV068 placed in Plane 1. Ascending node 167.8 degrees.
  • Iridium 67 - . Payload: Iridium s/n SV067. 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: 25290 . COSPAR: 1998-021F. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 1. Ascending node 167.8 degrees..
  • Iridium 66 - . Payload: Iridium s/n SV066. 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: 25289 . COSPAR: 1998-021E. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 1. Ascending node 167.8 degrees..
  • Iridium 65 - . Payload: Iridium s/n SV065. 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: 25288 . COSPAR: 1998-021D. Apogee: 778 km (483 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 1. Ascending node 167.9 degrees..
  • Iridium 64 - . Payload: Iridium s/n SV064. 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: 25287 . COSPAR: 1998-021C. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 1. Ascending node 167.6 degrees..

1999 April 7 - .
  • ISS Status Report: ISS 99-14 - . Nation: USA. Related Persons: Barry; Jernigan. Program: ISS. Summary: Flight controllers in Houston and Moscow indicate that the Unity module of the International Space Station, in its present position in space, can be adequately heated prior to the Space Shuttle's arrival.. Additional Details: ISS Status Report: ISS 99-14.

2001 April 7 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Delta. Launch Vehicle: Delta 7925-9.5. LV Configuration: Delta 7925-9.5 D284.
  • 2001 Mars Odyssey - . Mass: 725 kg (1,598 lb). Nation: USA. Agency: JPL. Class: Mars. Type: Mars probe. Spacecraft: Mars Odyssey. USAF Sat Cat: 26734 . COSPAR: 2001-013A. The 2001 Mars Odyssey probe (formerly the Mars Surveyor 2001 Orbiter) was the first spacecraft in the revamped NASA Mars Exploration Program. Built by Lockheed Martin Astronautics (Denver) and JPL, the satellite was similar to Mars Climate Orbiter. It carried a 6-meter boom with a gamma ray spectrometer for remote sensing of Martian surface mineralogy, as well as an infrared imager and a radiation environment monitor. The probe had a dry mass of 376 kg and carried 349 kg of propellant. 2001 Mars Odyssey entered a 195 x 215 km x 52 deg parking orbit 10 minutes after launch. After a 12 minute coast the Delta second stage fired again and separated from the third stage, which placed the probe on an Earth escape trajectory into a 0.982 x 1.384 AU x 3.05 deg solar orbit. It escaped Earth's nominal gravitational sphere of influence at around 19:00 GMT on April 10.

    The 2001 Mars Odyssey probe entered Mars orbit on October 24, 2001. The orbit insertion burn with the main 640 N bipropellant N2O4/hydrazine engine began at 0218 GMT lasted 20 min 19 sec. Mass of the spacecraft was then 456 kg, including 79 kg of fuel left. Initial orbit was was 272 x 26818 km x 93.42 deg with periapsis near the Martian north pole. 76 days of aerobraking began on October 26 to slowly circularise the orbit to its 400 km altitude, 2 hour period sun synchronous operational orbit. The solar panels reached 180 deg C as Odyssey skimmed through upper atmosphere of Mars on each orbit.

    After reaching the operational orbit, the probe was to conduct a 917 day mapping program. It was to also serve as a communications relay for American and international landers expected to arrive in 2003/2004. In the Martian orbit, it was to map the distribution of elements and minerals on the surface, the distribution of hydrogen (embedded in water ice) and the radiation environment. The second was to assess the likelyhood of past or present life, and the third was to assess the radiation hazard to manned missions. The three major instruments on board were THEMIS (Thermal Emission Imaging System at the visible and infrared light) for the distribution, at 100 meter resolution, of minerals that form only in the presence of water, GRS (Gamma Ray Spectrometer) for determining hydrogen and other elements, and MARIE (presumably, MArs RadIation Environment) for determining the radiation hazard. THEMIS was to also enable site selection for a future manned landing. THEMIS was expected to provide 15,000 images, each covering 20 x 20 km. GRS carried two neutron monitors also. The gamma rays and neutrons come out of the surface in distinct, element-specific energies, released by cosmic ray bombardment.


2001 April 7 - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. LV Family: Proton. Launch Vehicle: Proton/Briz M. LV Configuration: Proton-M/Briz-M 535-01.
  • Ekran-M No. 18 - . Payload: Ekran-M s/n 18L. Mass: 1,970 kg (4,340 lb). Nation: Russia. Agency: GPKS. Manufacturer: Reshetnev. Class: Communications. Type: Military communications satellite. Spacecraft: Ekran-M. USAF Sat Cat: 26736 . COSPAR: 2001-014A. Apogee: 35,801 km (22,245 mi). Perigee: 35,771 km (22,227 mi). Inclination: 1.1000 deg. Period: 1,436.10 min. Direct Broadcasting satellite. Maiden flight of new version of Proton. Launch delayed from August 2000, March 16 and April 6. Ekran-M No. 18 was a UHF television broadcasting satellite which was to be stationed at 99 deg E to provided television service to the Russian Far East. The satellite had a launch mass of around 2100 kg and was to replace the recently failed Ekran-M 15 that had been operating since October 1992 at the 105 deg-E longitude orbital slot.

    The improved 3-stage Proton launch vehicle, with a new digital flight control system and enhanced first stage engines, delivered its payload section to a suborbital trajectory at 0356 GMT. The Briz-M upper stage then fired to enter a 200 km parking orbit. It appears that only two more burns were used to reach geostationary orbit: one at around 0440 GMT to enter a 200 x 35800 km GTO, after which the Briz-M toroidal drop tank was jettisoned, and one at around 1000 GMT, to circularize the orbit at geostationary altitude. Briz-M reportedly separated from its payload at 1031 GMT. Ekran was expected to reach its 99 deg E final location on around April 24. As of 5 September 2001 located at 99.27 deg E drifting at 0.009 deg E per day. As of 2007 Mar 11 located at 99.30E drifting at 0.005W degrees per day.


2006 April 7 - . 13:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF26. Launch Pad: LF26?. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • GT-190GM FDEP operational test launch - Guam - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi).

2007 April 7 - . 17:31 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz FG. LV Configuration: Soyuz-FG 019.
  • Soyuz TMA-10 - . Call Sign: Pulsar. Crew: Yurchikhin; Kotov; Simonyi. Return Crew: Yurchikhin; Kotov; Muszaphar. Payload: Soyuz TMA s/n 220 / ISS-14S. Mass: 7,200 kg (15,800 lb). Nation: Russia. Related Persons: Simonyi; Yurchikhin; Kotov; Muszaphar. Agency: RAKA. Manufacturer: Korolev. Program: ISS. Class: Manned. Type: Manned spacecraft. Flight: ISS EO-15; ISS EP-12. Spacecraft: Soyuz TMA. Duration: 196.71 days. Decay Date: 2007-10-21 . USAF Sat Cat: 31100 . COSPAR: 2007-008A. Apogee: 341 km (211 mi). Perigee: 330 km (200 mi). Inclination: 51.6000 deg. Period: 91.20 min. Carried the Expedition 15 crew and space tourist Charles Simonyi to the International Space Station. Soyuz TMA-10 docked at the Zarya port of the International Space Station at 19:10 GMT on 9 April. It undocked from Zarya at 19:20 GMT on Sep 27 September and docked at the Zvezda port at 19:47 GMT to clear Zarya for Soyuz TMA-10.

    The EO-15 crew and EP-13 space tourist Shukor (brought to the station by Soyuz TMA-11) boarded Soyuz TM-10 and undocked from the Zvezda port at 07:14 GMT on 21 October. The re-entry burn began at 09:47 and was normal. But afterwards, due to failure of an explosive bolt, the Soyuz service module remained connected to the re-entry capsule. The Soyuz tumbled, then began re-entry with the forward hatch taking the re-entry heating, until the connecting strut burned through. The Soyuz the righted itself with the heat shield taking the heating, but defaulted to an 8.6 G ballistic re-entry, landing 340 km short of the aim point at 10:36 GMT. Improved procedures after the ballistic re-entry of Soyuz TMA-1 meant a helicopter recovery crew reached the capsule only 20 minutes after thumpdown. However the true nature of the failure was concealed from the world until the same thing happened on Soyuz TMA-11.


2008 April 7 - .
  • ISS On-Orbit Status 04/07/08 - . Nation: USA. Related Persons: Love; Malenchenko; Reisman; Whitson; Yi So-yeon. Program: ISS. Flight: ISS EO-16; ISS EO-16-3; ISS EP-14. Underway: Week 25 of Increment 16.

    This morning at 4:49am EDT, Progress M-63/28P successfully undocked from the ISS. All separation burns went off nominally, and the deorbit burn followed at 7:50am for destructive reentry over the Pacific Ocean. This freed the DC1 Docking Compartment port for Soyuz TMA-12/16S docking on 4/10 at ~9:02am. (For the undocking, ISS attitude control was handed over to Russian MCS (Motion Control System) at ~2:55am and returned to U.S. momentum management at ~5:45am, still in earth-fixed LVLH (local vertical/local horizontal). During the undocking, the station was in free drift for ~9 min. Structural response data were taken by MAMS (Microgravity Acceleration Measuring System) and the external truss-mounted SDMS (Structural Dynamic Measurement System). The undocking was preceded at ~4:15am by a temporary shutdown of the amateur radio equipment in the FGB (Ericsson) & SM (Kenwood) to prevent radiofrequency interference with the departing Progress vehicle.) Additional Details: ISS On-Orbit Status 04/07/08.


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