Encyclopedia Astronautica
Diamant



ydiamang.jpg
Diamants
Credit: © Mark Wade
In December 1961 France decided to demonstrate an indigenous satellite-launch capability, using stages in development for its ballistic missile program. Following careful evolutionary development, Diamant was successful on its first attempt in 1965. Improved versions were flown over the next ten years.

More... - Chronology...


Associated Spacecraft
  • Asterix French technology satellite. One launch, 1965.11.26. First French satellite. Launched from Hammaguir (Algeria) in order to test the "Diamant" launching vehicle for the first time. More...
  • D French earth geodetic satellite. 8 launches, 1966.02.17 (Diapason) to 1975.09.27 (Aura). Small French science and technology satellites used on early Diamant launch vehicle tests. More...
  • Diadem French earth geodetic satellite. 2 launches, 1967.02.08 (Diademe 1) and 1967.02.15 (Diademe 2). French geodetic satellites. More...
  • DIAL WIKA German technology satellite. One launch, 1970.03.10, DIAL-WIKA. More...
  • Dial MIKA French technology satellite. One launch, 1970.03.10. Engineering package; monitored launch vehicle performance. More...
  • Peole French communications satellite. One launch, 1970.12.12. Gathered data from meteorological balloon system. More...
  • Starlette French earth geodetic satellite. One launch, 1975.02.06. Geodesic satellite. More...

Associated Launch Vehicles
  • Rubis French orbital launch vehicle. Two-stage test vehicle consisting of 1 x Agate + 1 x P064. It was designed to test the upper stage and payload elements of the Diamant orbital launcher. These included fairing jettison, spin-up, release, and ignition of the P064 final stage. Six launches were used to validate the design and led to the success of the Diamant on its first flight. The last four launches were made on behalf of CNES to validate payloads for the D1 satellite and carry scientific instruments for the Paris Observatory and Max Planck Institute. More...
  • Diamant French orbital launch vehicle. In December 1961 France decided to demonstrate an indigenous satellite-launch capability, using stages in development for its ballistic missile program. Following careful evolutionary development, Diamant was successful on its first attempt in 1965. Improved versions were flown over the next ten years. More...
  • Emeraude VE121 French orbital launch vehicle. Emeraude was a step toward larger liquid propellant launch vehicles, building on the Veronique and Vesta experience. It burned 12.8 tonnes nitric acid/turpentine pressure-fed propellants in 91 seconds. Tthe engine was gimbaled for pitch and yaw control, with aerodynamic fins controlling roll. In anticipation of the next step, Saphir, a dummy Topaze stage topped the vehicle to confirm aerodynamic characteristics. The first three launches were failures due to propellant sloshing. This was remedied in the later tests. More...
  • Saphir French orbital launch vehicle. Saphir was the penultimate step in the 'precious stones' series. The variants of the two-stage vehicle were designed to allow testing of radio-controlled guidance (VE231P), inertial guidance (VE231G), and warhead separation and re-entry of an ablative RV (VE231R). Addition of a third stage would transform Saphir into the Diamant satellite launcher. More...
  • Diamant A French orbital launch vehicle. Diamant development could be done relatively quickly using stages and systems being developed for strategic missiles. In May 1962 CNES selected DMA as program manager, with SEREB as the prime contractor. The Diamant orbital launch vehicle was created by replacing the payload of the existing Saphir test vehicle with a new third stage. Prior to any all-up satellite launch attempt the P064 third stage was flight tested on the smaller suborbital Rubis test vehicle. This evolutionary approach paid off. More...
  • Diamant B French orbital launch vehicle. As a follow-on to the Diamant-A, CNES decided to evolve a more capable launch vehicle. The Diamant-B used a new first stage with 50% more propellants and 33% more thrust; the same second stage; and a fatter third stage. Six Diamant-B boosters were ordered. Originally four of these were to be used to test the Europa 2 launch vehicle's Perigee-Apogee System. These tests were cancelled and instead CNES used five of the six boosters for orbital attempts. More...
  • Diamant BP.4 French orbital launch vehicle. In January 1972 a further evolution, the Diamant BP.4, was authorized. The second stage was replaced with the P4 Rita motor developed for the MSBS SLBM. The larger 1.38 m diameter fairing developed for the British Black Arrow launcher allowed larger payloads to be accommodated. Three launches of the BP.4 in 1975 completed the Diamant saga. More...

Associated Launch Sites
  • Hammaguira The constellation of launch complexes and nuclear weapons test sites established by France in Algeria began with the Special Weapons Test Center (CIEES). This began operations at Colomb-Bechar, Algeria, on April 24, 1947. Development of the larger Veronique series required a new facility. This went into operation at Hammaguir, 120 km southwest of Colomb-Bechar, in May 1952. The evacuation of these launch sites was a condition of the final agreement signed in March 1962 that ended the Algerian Civil War. The sites continued in use until finally turned over to the Algerian government on 1 July 1967. French missile test activities moved to Biscarosse, in France, and orbital launches to Kourou, in French Guiana. Hammaguira was known to have been used for at least 271 launches from 1952 to 1967. More...
  • Biscarosse In April 1962 France signed the final agreements with Algeria, requiring them to evacuate their rocket test ranged there by July 1967. Three months later a site on French soil on the Bay of Biscay, at Landes, near Biscarosse, was selected. The site would allow the testing of missiles over the Atlantic out to a range of 3000 km. This would put the RV impact area near the Azores, and a tracking station was opened in October 1966 on Flores island. More...
  • Kourou After the agreement with newly independent Algeria for France to evacuate their launch sites in that country, a location near Biscarosse was selected for French missile testing. However since only launches westwards across the Bay of Biscay could be made from this site, it was unsuitable for France's Diamant orbital launch vehicle. After reviewing 14 potential sites, a location in the South American French colony of Guiana was selected. This would allow over-water launches to a tremendous range of possible orbital inclinations -- from -100.5 deg to 1.5 deg. Being near the equator, it would provide the maximum assist from the earth's rotation for launches into equatorial orbits. The decision was formalized in April 1964 and in July 1966 ELDO chose the site for future launches of the Europa II launch vehicle. More...

Diamant Chronology


1964 June 10 - . 05:30 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R1.
  • A-1 capsule test - . Nation: France. Agency: ONERA. Apogee: 1,800 km (1,100 mi).

1964 June 12 - . 05:03 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R2.
  • A-1 capsule test - . Nation: France. Agency: ONERA. Apogee: 1,800 km (1,100 mi).

1964 June 15 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121. FAILURE: Failure.
  • Test mission - . Nation: France. Agency: CNES. Apogee: 0 km ( mi).

1964 June 17 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121. FAILURE: Failure.
  • Test mission - . Nation: France. Agency: CNES. Apogee: 0 km ( mi).

1964 October 12 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R3. FAILURE: Failure.
  • A-1 capsule test - . Nation: France. Agency: ONERA. Apogee: 60 km (37 mi).

1964 October 20 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121. FAILURE: Failure.
  • Test mission - . Nation: France. Agency: CNES. Apogee: 0 km ( mi).

1964 December 18 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R4. FAILURE: Failure.
  • A-1 capsule test - . Nation: France. Agency: ONERA. Apogee: 60 km (37 mi).

1965 February 27 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121.
  • Test mission - . Nation: France. Agency: CNES. Apogee: 200 km (120 mi).

1965 May 13 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121.
  • Test mission - . Nation: France. Agency: CNES. Apogee: 200 km (120 mi).

1965 May 31 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R5.
  • A-1 capsule - . Nation: France. Agency: ONERA. Apogee: 2,000 km (1,200 mi).

1965 June 3 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R6.
  • A-1 capsule - . Nation: France. Agency: ONERA. Apogee: 2,000 km (1,200 mi).

1965 June 5 - . 05:40 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R7.
  • Rubis 01/D-1 Test/Ionosphere mission - . Nation: France. Agency: CNES. Apogee: 2,020 km (1,250 mi). Summary: Carried a D-1 satellite test experiment, a magnetosphere sensor, and a Meudon radioastronomy experiment with a 36m dipole observing at 1.8 and 2.4 MHz.

1965 July 5 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 P1.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1965 July 10 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 P2. FAILURE: Failure.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 50 km (31 mi).

1965 September 30 - . 04:20 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R8.
  • Rubis 02 Radio astronomy / particles mission - . Nation: France. Agency: CNES. Apogee: 1,760 km (1,090 mi).

1965 October 9 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 P3.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,150 km (710 mi).

1965 November 26 - . 14:47 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Diamant A. LV Configuration: Diamant A No. 1.
  • Asterix 1 - . Payload: A 1. Mass: 42 kg (92 lb). Nation: France. Agency: CNES. Class: Technology. Type: Navigation technology satellite. Spacecraft: Asterix. USAF Sat Cat: 1778 . COSPAR: 1965-096A. Apogee: 1,697 km (1,054 mi). Perigee: 527 km (327 mi). Inclination: 34.3000 deg. Period: 107.50 min. Summary: First French satellite. French scientific satellite 'A-I'. Launched from Hammaguir (Algeria) in rder to test the 'Diamant' launching vehicle for the first time..

1966 February 17 - . 08:33 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Diamant A. LV Configuration: Diamant A No. 2.
  • Diapason - . Payload: D-1A. Mass: 19 kg (41 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: D. USAF Sat Cat: 2016 . COSPAR: 1966-013A. Apogee: 2,484 km (1,543 mi). Perigee: 502 km (311 mi). Inclination: 34.1000 deg. Period: 115.80 min. Summary: Scientific satellite 'D-I' launched from Hammaguir (Algeria)..

1966 March 13 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 G1.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 March 18 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 G2.
  • Re-entry Vehicle test - . Nation: France. Agency: CNES. Apogee: 1,000 km (600 mi).

1966 March 28 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 R2.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 April 5 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 R1.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 April 22 - . 20:00 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bacchus. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R9.
  • Rubis 03 / MPE Ba-17 Plasma / ionosphere / barium release mission - . Nation: France. Agency: CNES. Apogee: 2,035 km (1,264 mi).

1966 June 23 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 R4.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 October 5 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 R3.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 October 28 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 G3.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 November 2 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 G4.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 December 2 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 R5. FAILURE: Failure.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 50 km (31 mi).

1966 December 13 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 R6.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1967 January 19 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 G5.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1967 January 27 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir. LV Configuration: Saphir VE231 G6.
  • Re-entry Vehicle test - . Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi).

1967 February 8 - . 09:39 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Diamant A. LV Configuration: Diamant A No. 3. FAILURE: Partial Failure - injected into too low an orbit.. Failed Stage: 3.
  • Diademe 1 - . Payload: Diademe D-1C. Mass: 23 kg (50 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: Diadem. USAF Sat Cat: 2674 . COSPAR: 1967-011A. Apogee: 1,084 km (673 mi). Perigee: 545 km (338 mi). Inclination: 40.0000 deg. Period: 101.20 min. Summary: Orbit too low. Launch time of Diadem I was 10:39:40 on 8 Feb 1967. Launch time of Diadem II was 11:06:57 on 15 Feb 1967..

1967 February 15 - . 10:06 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Diamant A. LV Configuration: Diamant A No. 4.
  • Diademe 2 - . Payload: Diademe D-1D. Mass: 23 kg (50 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: Diadem. USAF Sat Cat: 2680 . COSPAR: 1967-014A. Apogee: 1,733 km (1,076 mi). Perigee: 584 km (362 mi). Inclination: 39.4000 deg. Period: 108.50 min. Summary: Launch time of Diadem I was 10:39:40 on 8 Feb 1967. Launch time of Diadem II was 11:06:57 on 15 Feb 1967. .

1967 July 5 - . 14:07 GMT - . Launch Site: Biscarosse. LV Family: Diamant. Launch Vehicle: Rubis. LV Configuration: Rubis R10.
  • Rubis 04 Astronomy mission - . Nation: France. Agency: CNES. Apogee: 1,560 km (960 mi). Summary: Radio-astronomy experiment; measured the MHz range radio background.

1970 March 10 - . 12:20 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B. LV Configuration: Diamant B No. 1.
  • DIAL-WIKA - . Payload: DIAL Wissenschaftliche Kapsel. Mass: 63 kg (138 lb). Nation: Germany. Agency: CNES; BMW. Class: Technology. Type: Navigation technology satellite. Spacecraft: Dial WIKA. Decay Date: 1978-10-05 . USAF Sat Cat: 4344 . COSPAR: 1970-017A. Apogee: 1,631 km (1,013 mi). Perigee: 301 km (187 mi). Inclination: 5.4000 deg. Period: 104.20 min. Summary: Engineering package..
  • Dial MIKA - . Payload: DIAL Mini Kapsel/P068. Mass: 52 kg (114 lb). Nation: France. Agency: CNES; BMW. Class: Technology. Type: Navigation technology satellite. Spacecraft: Dial MIKA. Decay Date: 1974-09-09 . USAF Sat Cat: 4345 . COSPAR: 1970-017B. Apogee: 1,638 km (1,017 mi). Perigee: 310 km (190 mi). Inclination: 5.4000 deg. Period: 104.56 min. Summary: Engineering package; monitored launch vehicle performance. .

1970 December 12 - . 13:04 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B. LV Configuration: Diamant B No. 2.
  • Peole - . Mass: 70 kg (154 lb). Nation: France. Agency: CNES. Class: Communications. Type: Civilian communications satellite. Spacecraft: Peole. Decay Date: 1980-06-16 . USAF Sat Cat: 4801 . COSPAR: 1970-109A. Apogee: 750 km (460 mi). Perigee: 634 km (393 mi). Inclination: 15.0000 deg. Period: 98.60 min. Summary: Gathered data from meteorological balloon system. .

1971 April 15 - . 09:19 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B. LV Configuration: Diamant B No. 3.
  • Tournesol - . Payload: D-2A. Mass: 96 kg (211 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: D. Decay Date: 1980-01-28 . USAF Sat Cat: 5128 . COSPAR: 1971-030A. Apogee: 696 km (432 mi). Perigee: 457 km (283 mi). Inclination: 46.3000 deg. Period: 96.20 min.

1971 December 5 - . 16:20 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B. LV Configuration: Diamant B No. 4. FAILURE: Second stage failed.. Failed Stage: 2.
  • D-2A Polaire - . Payload: D-2A Polaire. Nation: France. Agency: CNES. Class: Earth. Type: Atmosphere satellite. Spacecraft: D. COSPAR: F711205B.

1973 May 21 - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B. LV Configuration: Diamant B No. 5. FAILURE: Failure - fairing did not jettison.. Failed Stage: S.
  • Castor (D 5A) - . Payload: D 5A. Nation: France. Agency: CNES. Class: Technology. Type: Navigation technology satellite. Spacecraft: D. Decay Date: 1972-05-21 . COSPAR: F730521A.
  • Pollux - . Payload: D-5A. Nation: France. Agency: CNES. Spacecraft: D. COSPAR: F730521B.

1975 February 6 - . 16:35 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant BP.4. LV Configuration: Diamant BP.4 No. 1.
  • Starlette - . Payload: Starlette (BETA). Mass: 47 kg (103 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: Starlette. USAF Sat Cat: 7646 . COSPAR: 1975-010A. Apogee: 1,108 km (688 mi). Perigee: 805 km (500 mi). Inclination: 49.8000 deg. Period: 104.20 min. Summary: Geodesic satellite. .

1975 May 17 - . 10:32 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant BP.4. LV Configuration: Diamant BP.4 No. 2.
  • Pollux - . Payload: D-5A. Mass: 35 kg (77 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: D. Decay Date: 1975-08-05 . USAF Sat Cat: 7801 . COSPAR: 1975-039A. Apogee: 1,256 km (780 mi). Perigee: 299 km (185 mi). Inclination: 30.0000 deg. Period: 100.40 min. D5A: Weight 36 kg. Testing in space of a hydrazine catalytic decomposition micropropulsion unit. Responsible organization: Societe Europeene de Propulsion. D5B: Weight 76 kg. Testing in space of the CACTUS accelerometer (ultrasensitive triaxial capacitive accelerometric sensor). Responsible organization: ONERA, Chatillon-sous-Berneux, France.
  • Castor - . Payload: D-5B. Mass: 77 kg (169 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: D. Decay Date: 1979-02-18 . USAF Sat Cat: 7802 . COSPAR: 1975-039B. Apogee: 1,275 km (792 mi). Perigee: 277 km (172 mi). Inclination: 29.9000 deg. Period: 100.30 min. D5A: Weight 36 kg. Testing in space of a hydrazine catalytic decomposition micropropulsion unit. Responsible organization: Societe Europeene de Propulsion. D5B: Weight 76 kg. Testing in space of the CACTUS accelerometer (ultrasensitive triaxial capacitive accelerometric sensor). Responsible organization: ONERA, Chatillon-sous-Berneux, France.

1975 September 27 - . 08:37 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant BP.4. LV Configuration: Diamant BP.4 No. 3.
  • Aura - . Payload: D-2. Mass: 115 kg (253 lb). Nation: France. Agency: CNES. Class: Earth. Type: Geodetic satellite. Spacecraft: D. Decay Date: 1982-09-30 . USAF Sat Cat: 8332 . COSPAR: 1975-092A. Apogee: 697 km (433 mi). Perigee: 476 km (295 mi). Inclination: 37.1000 deg. Period: 96.50 min. Solar UV radiation experiments. Study of solar and stellar ultraviolet radiation. 1. Spectral analysis of small and large sources located close to the plane of the ecliptic. Responsible organization: Laboratoire d'Astronomie Spatiale, Traverse du Siphon, 13000- Marseille (France). 2. St udy of solar ultraviolet radiation and its absorption by the earth's atmosphere. Responsible organization: Laboratoire de Physique Stellaire et Planetaire, Meudon, France. Weight 106.6 kg.

Home - Browse - Contact
© / Conditions for Use