Encyclopedia Astronautica
Diamant A



ydiamaac.jpg
Diamant A
Credit: © Mark Wade
ydiamana.jpg
Diamant A
Credit: © Mark Wade
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.

LEO Payload: 160 kg (350 lb) to a 200 km orbit. Failures: 1. First Fail Date: 1967-02-08. Last Fail Date: 1967-02-08 in 1985 dollars. Flyaway Unit Cost $: 5.700 million.

Stage Data - Diamant A

  • Stage 1. 1 x Diamant-1. Gross Mass: 14,685 kg (32,374 lb). Empty Mass: 1,946 kg (4,290 lb). Thrust (vac): 301.550 kN (67,791 lbf). Isp: 251 sec. Burn time: 93 sec. Isp(sl): 221 sec. Diameter: 1.34 m (4.39 ft). Span: 2.30 m (7.50 ft). Length: 9.76 m (32.02 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: Vexin B. Other designations: Emeraude. Status: Out of Production.
  • Stage 2. 1 x Diamant-2. Gross Mass: 2,815 kg (6,206 lb). Empty Mass: 540 kg (1,190 lb). Thrust (vac): 120.082 kN (26,996 lbf). Isp: 255 sec. Burn time: 39 sec. Isp(sl): 225 sec. Diameter: 0.80 m (2.62 ft). Span: 0.80 m (2.62 ft). Length: 4.57 m (14.99 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Topaze. Other designations: Topaze. Status: Out of Production.
  • Stage 3. 1 x Diamant-3. Gross Mass: 703 kg (1,549 lb). Empty Mass: 68 kg (149 lb). Thrust (vac): 29.400 kN (6,609 lbf). Isp: 211 sec. Burn time: 39 sec. Isp(sl): 211 sec. Diameter: 0.66 m (2.16 ft). Span: 0.66 m (2.16 ft). Length: 1.98 m (6.49 ft). Propellants: Solid. No Engines: 1. Engine: P6. Other designations: P-6. Status: Out of Production.

Gross mass: 18,400 kg (40,500 lb).
Payload: 160 kg (350 lb).
Height: 18.95 m (62.17 ft).
Diameter: 1.34 m (4.39 ft).
Thrust: 265.50 kN (59,687 lbf).
Apogee: 200 km (120 mi).
First Launch: 1965.11.26.
Last Launch: 1967.02.15.
Number: 4 .

More... - Chronology...


Associated Countries
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...

See also
  • Diamant 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...

Associated Manufacturers and Agencies
  • SEREB French manufacturer of rocket engines and rockets. SEREB, France. 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...

Associated Stages
  • Diamant-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 2,815/540 kg. Thrust 120.08 kN. Vacuum specific impulse 255 seconds. More...
  • Diamant-3 Solid propellant rocket stage. Loaded/empty mass 703/68 kg. Thrust 29.40 kN. Vacuum specific impulse 211 seconds. More...
  • Diamant-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 14,685/1,946 kg. Thrust 301.55 kN. Vacuum specific impulse 251 seconds. More...

Diamant A Chronology


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)..

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. .

Home - Browse - Contact
© / Conditions for Use