Diamant
Launch vehicle · France
Original archive entry. The text, images and links below are kept as they were written.
Credit: © Mark Wade
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. Although France abandoned the planned ICBM for the solid-propellant SSBS, Diamant technology was used in the European Europa and Ariane launch vehicles.
More at: Diamant.
Subtopics
- Emeraude VE121 Emeraude was a step toward larger liquid propellant launch vehicles, building on the Veronique and Vesta experience. It burned 12.8 metric tons nitric acid/turpentine pressure-fed propellants in 91 seconds. The 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.
Saphir VE231 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.
Diamant A 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.
Diamant B 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.
Diamant BP.4 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.
Related
- Family
- orbital launch vehicle
- Country
- France
- Stages
- P6
- Agency
- SEREB
Photo Gallery
Diamant A
Diamant A - COSPAR 1965-096
Diamant 2 
Diamant A
Credit: © Mark Wade
Diamant B 
Diamant B
Diamant B - COSPAR 1970-109
Diamant BP.4
Diamant BP.4 - COSPAR 1975-039
Diamant B
Credit: © Mark Wade
Chronology
32 events
1964 June 15
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121. FAILURE: Failure.1964 June 17
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121. FAILURE: Failure.1964 October 20
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121. FAILURE: Failure.1965 February 27
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121.1965 May 13
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Emeraude VE121.1965 July 5
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1965 July 10
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231. FAILURE: Failure.1965 October 9
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1965 November 26
14:47 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Diamant A.- 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: 34.30 deg. Period: 107.50 min. 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.- 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: 34.10 deg. Period: 115.80 min. Scientific satellite 'D-I' launched from Hammaguir (Algeria)..
1966 March 13
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1966 March 18
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1966 March 28
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1966 April 5
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1966 June 23
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1966 October 5
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1966 October 28
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1966 November 2
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1966 December 2
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231. FAILURE: Failure.1966 December 13
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1967 January 19
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1967 January 27
Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Saphir VE231.1967 February 8
09:39 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Brigitte. LV Family: Diamant. Launch Vehicle: Diamant A. 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: 40.00 deg. Period: 101.20 min. 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.- 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: 39.40 deg. Period: 108.50 min. 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. .
1970 March 10
12:20 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B.- DIAL-WIKA - . Payload: DIAL Wissenschaftliche Kapsel. Mass: 63 kg (138 lb). Nation: Germany. Agency: BMW, CNES. 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: 5.40 deg. Period: 104.20 min. Engineering package..
- Dial MIKA - . Payload: DIAL Mini Kapsel/P068. Mass: 52 kg (114 lb). Nation: France. Agency: BMW, CNES. 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: 5.40 deg. Period: 104.56 min. 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.- 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: 15.00 deg. Period: 98.60 min. 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.- 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: 46.30 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. 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.
1973 May 21
Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant B. 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.
1975 February 6
16:35 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant BP.4.- 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: 49.80 deg. Period: 104.20 min. Geodesic satellite. .
1975 May 17
10:32 GMT - . Launch Site: Kourou. Launch Complex: Kourou Diamant. LV Family: Diamant. Launch Vehicle: Diamant BP.4.- 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: 30.00 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: 29.90 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.- 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: 37.10 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.