Diamant BP.4 Credit - © Mark Wade

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.

Manufacturer: SEREB. Launches: 3. Success Rate: 100.00%. First Launch Date: 1975-02-06. Last Launch Date: 1975-09-27. Launch data is: complete. LEO Payload: 150 kg (330 lb). Apogee: 2,000 km (1,200 mi). Associated Spacecraft: D, Starlette. Liftoff Thrust: 316.000 kN (71,039 lbf). Total Mass: 26,300 kg (57,900 lb). Core Diameter: 1.40 m (4.50 ft). Total Length: 21.60 m (70.80 ft). Flyaway Unit Cost $: 9.000 million. in: 1985 unit dollars.

1975 February 6 - 16:35 GMT - Launch Site: Kourou. Launch Complex: Diamant. Launch Pad: Diamant. Launch Vehicle: Diamant BP.4. Model: Diamant BP.4. LV Configuration: Diamant BP.4 No. 1.

• Starlette Nation: France. Payload: Starlette (BETA). Mass: 47 kg (103 lb). Class: Earth. Type: Geodetic. Spacecraft: Starlette. Agency: CNES. Perigee: 805 km (500 mi). Apogee: 1,108 km (688 mi). Inclination: 49.80 deg. Period: 104.20 min. COSPAR: 1975-010A. USAF Sat Cat: 7646. Geodesic satellite. References: 1, 2, 5, 6.

• Pollux Nation: France. Payload: D-5A. Mass: 35 kg (77 lb). Class: Earth. Type: Geodetic. Spacecraft: D. Agency: CNES. Perigee: 299 km (185 mi). Apogee: 1,256 km (780 mi). Inclination: 30.00 deg. Period: 100.40 min. COSPAR: 1975-039A. USAF Sat Cat: 7801. Decay Date: 1975-08-05. 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.References: 1, 2, 5, 6.

• Castor Nation: France. Payload: D-5B. Mass: 77 kg (169 lb). Class: Earth. Type: Geodetic. Spacecraft: D. Agency: CNES. Perigee: 277 km (172 mi). Apogee: 1,275 km (792 mi). Inclination: 29.90 deg. Period: 100.30 min. COSPAR: 1975-039B. USAF Sat Cat: 7802. Decay Date: 1979-02-18. 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.References: 1, 2, 5, 6.

• Aura Nation: France. Payload: D-2. Mass: 115 kg (253 lb). Class: Earth. Type: Geodetic. Spacecraft: D. Agency: CNES. Perigee: 476 km (295 mi). Apogee: 697 km (433 mi). Inclination: 37.10 deg. Period: 96.50 min. COSPAR: 1975-092A. USAF Sat Cat: 8332. Decay Date: 1982-09-30. 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.References: 1, 2, 5, 6.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Gatland, Kenneth, Missiles and Rockets, Macmillan, New York, 1975. ISBN: 0713735058. Covers rocketry of all nations. More at amazon.com...

• Serra, Jean-Jacques, Rockets in Europe, . Accessed at: http://www.univ-perp.fr/fuseurop/index_e.htm.