Diamant B - Diamant B - COSPAR 1970-109 24,108 bytes. 181 x 454 pixels.

Upgraded Diamant with liquid stage; antecedent of Ariane.

Launches: 9. Failures: 3. Success Rate: 66.67% pct. First Launch Date: 10 March 1970. Last Launch Date: 27 September 1975. LEO Payload: 160 kg. to: 200 km Orbit. Liftoff Thrust: 35,600 kgf. Total Mass: 26,990 kg. Core Diameter: 1.5 m. Total Length: 22.0 m. Flyaway Unit Cost $: 9.00 million. in 1985 unit dollars.

• Stage Number: 1. 1 x Diamant B-1 Gross Mass: 21,500 kg. Empty Mass: 3,500 kg. Thrust (vac): 40,434 kgf. Isp: 251 sec. Burn time: 110 sec. Isp(sl): 221 sec. Diameter: 1.4 m. Span: 2.3 m. Length: 14.1 m. Propellants: N2O4/UDMH No Engines: 4. Vexin C

• Stage Number: 2. 1 x Diamant B-2 Gross Mass: 4,500 kg. Empty Mass: 1,000 kg. Thrust (vac): 18,000 kgf. Isp: 273 sec. Burn time: 55 sec. Isp(sl): 240 sec. Diameter: 1.5 m. Span: 1.5 m. Length: 2.6 m. Propellants: Solid No Engines: 1. P4

• Stage Number: 3. 1 x Diamant B-3 Gross Mass: 800 kg. Empty Mass: 120 kg. Thrust (vac): 3,000 kgf. Isp: 211 sec. Burn time: 45 sec. Isp(sl): 211 sec. Diameter: 1.5 m. Span: 1.5 m. Length: 2.1 m. Propellants: Solid No Engines: 1. P6

• Dial MIKA Spacecraft: Dial MIKA. Payload: DIAL Mini Kapsel/P068. Mass: 52 kg.

  Engineering package; monitored launch vehicle performance.

• DIAL-WIKA Spacecraft: Dial WIKA. Payload: DIAL Wissenschaftliche Kapsel. Mass: 63 kg.

  Engineering package.

• Peole Spacecraft: Peole. Mass: 70 kg.

  Gathered data from meteorological balloon system.

• Tournesol Spacecraft: D. Payload: D-2A. Mass: 96 kg.

• D-2A Polaire Spacecraft: D. Payload: D-2A Polaire.

• D-2A Polaire Spacecraft: D.

• Pollux Spacecraft: D. Payload: D-5A.

• Castor (D 5A) Spacecraft: D. Payload: D 5A.

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  Diamant BP.4 - Diamant BP.4 - COSPAR 1975-039 21,392 bytes. 123 x 453 pixels.

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• Starlette Spacecraft: Starlette. Payload: Starlette (BETA). Mass: 47 kg.

  Geodesic satellite.

• Castor Spacecraft: D. Payload: D-5B. Mass: 77 kg.

  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.

• Pollux Spacecraft: D. Payload: D-5A. Mass: 35 kg.

  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.

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  Diamant B Credit: © Mark Wade. 451 bytes. 26 x 231 pixels.

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• Aura Spacecraft: D. Payload: D-2. Mass: 115 kg.

  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.

• 34 - Gatland, Kenneth, Missiles and Rockets, Macmillan, New York, 1975.