Diamant

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Orbital launch vehicle. Country: France. Status: Retired 1975.

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.

Manufacturer: SEREB. Launches: 42. Failures: 10. Success Rate: 76.19%. First Launch Date: 1964-06-10. Last Launch Date: 1975-09-27. Launch data is: complete. Version:

Rubis.
Rubis
Credit - NASA
Manufacturer's Designation: VE210.

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.

Launches: 10. Failures: 2. First Launch Date: 1964-06-10. Last Launch Date: 1967-07-05. Apogee: 2,000 km (1,200 mi). Liftoff Thrust: 186.000 kN (41,814 lbf). Total Mass: 4,000 kg (8,800 lb). Core Diameter: 0.80 m (2.62 ft). Total Length: 9.60 m (31.40 ft).

Stage1: 1 x Rubis. Gross Mass: 2,000 kg (4,400 lb). Empty Mass: 100 kg (220 lb). Motor: 1 x Agate. Thrust (vac): 190.000 kN (42,710 lbf). Burn time: 18 sec. Length: 4.50 m (14.70 ft). Diameter: 0.80 m (2.62 ft). Propellants: Solid.

Stage2: 1 x Diamant-3. Gross Mass: 703 kg (1,549 lb). Empty Mass: 68 kg (149 lb). Motor: 1 x P6. Thrust (vac): 29.400 kN (6,609 lbf). Isp: 211 sec. Burn time: 39 sec. Length: 1.98 m (6.49 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Version:

Emeraude VE121. Manufacturer's Designation: VE121.

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.

Launches: 5. Failures: 3. First Launch Date: 1964-06-15. Last Launch Date: 1965-05-13. Payload: 395 kg (870 lb). Apogee: 200 km (120 mi). Liftoff Thrust: 275.000 kN (61,822 lbf). Total Mass: 18,200 kg (40,100 lb). Core Diameter: 1.40 m (4.50 ft). Total Length: 17.93 m (58.82 ft). Boost Propulsion: Nitric acid/Turpentine.

Stage1: 1 x Diamant-1. Gross Mass: 14,685 kg (32,374 lb). Empty Mass: 1,946 kg (4,290 lb). Motor: 4 x Vexin B. Thrust (vac): 301.550 kN (67,791 lbf). Isp: 251 sec. Burn time: 93 sec. Length: 9.76 m (32.02 ft). Diameter: 1.34 m (4.39 ft). Propellants: N2O4/UDMH.

Version:

Saphir.
Saphir
Credit - via Jean-Jacques Serra
Manufacturer's Designation: 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.

Launches: 15. Failures: 2. First Launch Date: 1965-07-05. Last Launch Date: 1967-01-27. Payload: 365 kg (804 lb). Apogee: 1,000 km (600 mi). Liftoff Thrust: 280.000 kN (62,940 lbf). Total Mass: 18,058 kg (39,811 lb). Core Diameter: 1.40 m (4.50 ft). Total Length: 17.77 m (58.30 ft).

Stage1: 1 x Diamant-1. Gross Mass: 14,685 kg (32,374 lb). Empty Mass: 1,946 kg (4,290 lb). Motor: 4 x Vexin B. Thrust (vac): 301.550 kN (67,791 lbf). Isp: 251 sec. Burn time: 93 sec. Length: 9.76 m (32.02 ft). Diameter: 1.34 m (4.39 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Diamant-2. Gross Mass: 2,815 kg (6,206 lb). Empty Mass: 540 kg (1,190 lb). Motor: 1 x Topaze. Thrust (vac): 120.082 kN (26,996 lbf). Isp: 255 sec. Burn time: 39 sec. Length: 4.57 m (14.99 ft). Diameter: 0.80 m (2.62 ft). Propellants: N2O4/UDMH.

Version:

Diamant A.
Diamant A
Credit - © Mark Wade

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.

Launches: 4. Failures: 1. First Launch Date: 1965-11-26. Last Launch Date: 1967-02-15. LEO Payload: 160 kg (350 lb). to: 200 km Orbit. Apogee: 2,000 km (1,200 mi). Associated Spacecraft: Asterix, D, Diadem. Liftoff Thrust: 265.500 kN (59,687 lbf). Total Mass: 18,400 kg (40,500 lb). Core Diameter: 1.34 m (4.39 ft). Total Length: 18.95 m (62.17 ft). Flyaway Unit Cost $: 5.700 million. in: 1985 unit dollars.

Stage1: 1 x Diamant-1. Gross Mass: 14,685 kg (32,374 lb). Empty Mass: 1,946 kg (4,290 lb). Motor: 4 x Vexin B. Thrust (vac): 301.550 kN (67,791 lbf). Isp: 251 sec. Burn time: 93 sec. Length: 9.76 m (32.02 ft). Diameter: 1.34 m (4.39 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Diamant-2. Gross Mass: 2,815 kg (6,206 lb). Empty Mass: 540 kg (1,190 lb). Motor: 1 x Topaze. Thrust (vac): 120.082 kN (26,996 lbf). Isp: 255 sec. Burn time: 39 sec. Length: 4.57 m (14.99 ft). Diameter: 0.80 m (2.62 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Diamant-3. Gross Mass: 703 kg (1,549 lb). Empty Mass: 68 kg (149 lb). Motor: 1 x P6. Thrust (vac): 29.400 kN (6,609 lbf). Isp: 211 sec. Burn time: 39 sec. Length: 1.98 m (6.49 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Version:

Diamant B.
Diamant B
Credit - © Mark Wade

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.

Launches: 5. Failures: 2. First Launch Date: 1970-03-10. Last Launch Date: 1973-05-21. LEO Payload: 160 kg (350 lb). to: 200 km Orbit. Associated Spacecraft: D, Dial MIKA, Dial WIKA, Peole. Liftoff Thrust: 349.000 kN (78,458 lbf). Total Mass: 26,990 kg (59,500 lb). Core Diameter: 1.50 m (4.90 ft). Total Length: 23.50 m (77.00 ft).

Stage1: 1 x Diamant B-1. Gross Mass: 21,500 kg (47,300 lb). Empty Mass: 3,500 kg (7,700 lb). Motor: 4 x Vexin C. Thrust (vac): 396.522 kN (89,142 lbf). Isp: 251 sec. Burn time: 110 sec. Length: 14.08 m (46.19 ft). Diameter: 1.40 m (4.50 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Diamant BP-2. Gross Mass: 4,500 kg (9,900 lb). Empty Mass: 1,000 kg (2,200 lb). Motor: 1 x P4. Thrust (vac): 176.000 kN (39,566 lbf). Isp: 273 sec. Burn time: 55 sec. Length: 2.60 m (8.50 ft). Diameter: 1.50 m (4.90 ft). Propellants: Solid.

Stage3: 1 x Diamant B-3. Gross Mass: 800 kg (1,760 lb). Empty Mass: 120 kg (260 lb). Motor: 1 x P6. Thrust (vac): 50.000 kN (11,240 lbf). Isp: 211 sec. Burn time: 46 sec. Length: 1.67 m (5.47 ft). Diameter: 0.80 m (2.62 ft). Propellants: Solid.

Version:

Diamant BP.4.
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.

Launches: 3. First Launch Date: 1975-02-06. Last Launch Date: 1975-09-27. 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.

Stage1: 1 x Diamant B-1. Gross Mass: 21,500 kg (47,300 lb). Empty Mass: 3,500 kg (7,700 lb). Motor: 4 x Vexin C. Thrust (vac): 396.522 kN (89,142 lbf). Isp: 251 sec. Burn time: 110 sec. Length: 14.08 m (46.19 ft). Diameter: 1.40 m (4.50 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Diamant BP-2. Gross Mass: 4,500 kg (9,900 lb). Empty Mass: 1,000 kg (2,200 lb). Motor: 1 x P4. Thrust (vac): 176.000 kN (39,566 lbf). Isp: 273 sec. Burn time: 55 sec. Length: 2.60 m (8.50 ft). Diameter: 1.50 m (4.90 ft). Propellants: Solid.

Stage3: 1 x Diamant B-3. Gross Mass: 800 kg (1,760 lb). Empty Mass: 120 kg (260 lb). Motor: 1 x P6. Thrust (vac): 50.000 kN (11,240 lbf). Isp: 211 sec. Burn time: 46 sec. Length: 1.67 m (5.47 ft). Diameter: 0.80 m (2.62 ft). Propellants: Solid.

Diamant Chronology

1964 June 10 - 05:30 GMT - Hammaguira Bacchus. Rubis R1 A-1 capsule test Agency: ONERA. Apogee: 1,800 km (1,100 mi).

1964 June 12 - 05:03 GMT - Hammaguira Bacchus. Rubis R2 A-1 capsule test Agency: ONERA. Apogee: 1,800 km (1,100 mi).

1964 June 15 - Hammaguira Brigitte. FAILURE: Failure. Test mission Agency: CNES. Apogee: 0 km ( mi).

1964 June 17 - Hammaguira Brigitte. FAILURE: Failure. Test mission Agency: CNES. Apogee: 0 km ( mi).

1964 October 12 - Hammaguira Bacchus. Rubis R3 FAILURE: Failure. A-1 capsule test Agency: ONERA. Apogee: 60 km (37 mi).

1964 October 20 - Hammaguira Brigitte. FAILURE: Failure. Test mission Agency: CNES. Apogee: 0 km ( mi).

1964 December 18 - Hammaguira Bacchus. Rubis R4 FAILURE: Failure. A-1 capsule test Agency: ONERA. Apogee: 60 km (37 mi).

1965 February 27 - Hammaguira Brigitte. Test mission Agency: CNES. Apogee: 200 km (120 mi).

1965 May 13 - Hammaguira Brigitte. Test mission Agency: CNES. Apogee: 200 km (120 mi).

1965 May 31 - Hammaguira Bacchus. Rubis R5 A-1 capsule Agency: ONERA. Apogee: 2,000 km (1,200 mi).

1965 June 3 - Hammaguira Bacchus. Rubis R6 A-1 capsule Agency: ONERA. Apogee: 2,000 km (1,200 mi).

1965 June 5 - 05:40 GMT - Hammaguira Bacchus. Rubis R7 Rubis 01/D-1 Test/Ionosphere mission Agency: CNES. Apogee: 2,020 km (1,250 mi). 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 - Hammaguira Brigitte. Saphir VE231 P1 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1965 July 10 - Hammaguira Brigitte. Saphir VE231 P2 FAILURE: Failure. Re-entry Vehicle test Agency: ONERA. Apogee: 50 km (31 mi).

1965 September 30 - 04:20 GMT - Hammaguira Bacchus. Rubis R8 Rubis 02 Radio astronomy / particles mission Agency: CNES. Apogee: 1,760 km (1,090 mi).

1965 October 9 - Hammaguira Brigitte. Saphir VE231 P3 Re-entry Vehicle test Agency: ONERA. Apogee: 1,150 km (710 mi).

1965 November 26 - 14:47 GMT - Hammaguira Brigitte. Diamant A No. 1 Asterix 1 Mass: 42 kg (92 lb). Spacecraft: Asterix. Agency: CNES. Perigee: 527 km (327 mi). Apogee: 1,697 km (1,054 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 - Hammaguira Brigitte. Diamant A No. 2 Diapason Mass: 19 kg (41 lb). Spacecraft: D. Agency: CNES. Perigee: 502 km (311 mi). Apogee: 2,484 km (1,543 mi). Inclination: 34.10 deg. Period: 115.80 min. Scientific satellite 'D-I' launched from Hammaguir (Algeria).

1966 March 13 - Hammaguira Brigitte. Saphir VE231 G1 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 March 18 - Hammaguira Brigitte. Saphir VE231 G2 Re-entry Vehicle test Agency: CNES. Apogee: 1,000 km (600 mi).

1966 March 28 - Hammaguira Brigitte. Saphir VE231 R2 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 April 5 - Hammaguira Brigitte. Saphir VE231 R1 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 April 22 - 20:00 GMT - Hammaguira Bacchus. Rubis R9 Rubis 03 / MPE Ba-17 Plasma / ionosphere / barium release mission Agency: CNES. Apogee: 2,035 km (1,264 mi).

1966 June 23 - Hammaguira Brigitte. Saphir VE231 R4 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 October 5 - Hammaguira Brigitte. Saphir VE231 R3 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 October 28 - Hammaguira Brigitte. Saphir VE231 G3 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 November 2 - Hammaguira Brigitte. Saphir VE231 G4 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1966 December 2 - Hammaguira Brigitte. Saphir VE231 R5 FAILURE: Failure. Re-entry Vehicle test Agency: ONERA. Apogee: 50 km (31 mi).

1966 December 13 - Hammaguira Brigitte. Saphir VE231 R6 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1967 January 19 - Hammaguira Brigitte. Saphir VE231 G5 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1967 January 27 - Hammaguira Brigitte. Saphir VE231 G6 Re-entry Vehicle test Agency: ONERA. Apogee: 1,000 km (600 mi).

1967 February 8 - 09:39 GMT - Hammaguira Brigitte. Diamant A No. 3 FAILURE: Partial Failure - injected into too low an orbit. Diademe 1 Mass: 23 kg (50 lb). Spacecraft: Diadem. Agency: CNES. Perigee: 545 km (338 mi). Apogee: 1,084 km (673 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 - Hammaguira Brigitte. Diamant A No. 4 Diademe 2 Mass: 23 kg (50 lb). Spacecraft: Diadem. Agency: CNES. Perigee: 584 km (362 mi). Apogee: 1,733 km (1,076 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.

1967 July 5 - 14:07 GMT - Biscarosse -. Rubis R10 Rubis 04 Astronomy mission Agency: CNES. Apogee: 1,560 km (960 mi). Radio-astronomy experiment; measured the MHz range radio background

1970 March 10 - 12:20 GMT - Kourou Diamant. Diamant B No. 1 DIAL-WIKA Mass: 63 kg (138 lb). Spacecraft: Dial WIKA. Agency: CNES/BMw. Perigee: 301 km (187 mi). Apogee: 1,631 km (1,013 mi). Inclination: 5.40 deg. Period: 104.20 min. Engineering package.

1970 December 12 - 13:04 GMT - Kourou Diamant. Diamant B No. 2 Peole Mass: 70 kg (154 lb). Spacecraft: Peole. Agency: CNES. Perigee: 634 km (393 mi). Apogee: 750 km (460 mi). Inclination: 15.00 deg. Period: 98.60 min. Gathered data from meteorological balloon system.

1971 April 15 - 09:19 GMT - Kourou Diamant. Diamant B No. 3 Tournesol Mass: 96 kg (211 lb). Spacecraft: D. Agency: CNES. Perigee: 457 km (283 mi). Apogee: 696 km (432 mi). Inclination: 46.30 deg. Period: 96.20 min.

1971 December 5 - 16:20 GMT - Kourou Diamant. Diamant B No. 4 FAILURE: Second stage failed. D-2A Polaire Spacecraft: D. Agency: CNES.

1973 May 21 - Kourou Diamant. Diamant B No. 5 FAILURE: Failure - fairing did not jettison. Castor (D 5A) Spacecraft: D. Agency: CNES.

1975 February 6 - 16:35 GMT - Kourou Diamant. Diamant BP.4 No. 1 Starlette Mass: 47 kg (103 lb). Spacecraft: Starlette. Agency: CNES. Perigee: 805 km (500 mi). Apogee: 1,108 km (688 mi). Inclination: 49.80 deg. Period: 104.20 min. Geodesic satellite.

1975 May 17 - 10:32 GMT - Kourou Diamant. Diamant BP.4 No. 2 Pollux Mass: 35 kg (77 lb). Spacecraft: D. Agency: CNES. Perigee: 299 km (185 mi). Apogee: 1,256 km (780 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.

1975 September 27 - 08:37 GMT - Kourou Diamant. Diamant BP.4 No. 3 Aura Mass: 115 kg (253 lb). Spacecraft: D. Agency: CNES. Perigee: 476 km (295 mi). Apogee: 697 km (433 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.

Bibliography:

McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: http://msl.jpl.nasa.gov/home.html.
Gatland, Kenneth, Missiles and Rockets, Macmillan, New York, 1975.
Bramscher, Robert G, Spaceflight, "A Survey of Launch Vehicle Failures", 1980, Volume 22, page 351.
McDowell, Jonathan, Launch Log, October 1998. Web Address when accessed: http://hea-www.harvard.edu/~jcm/space/log/launch.html.
Serra, Jean-Jacques, Rockets in Europe, Web Address when accessed: http://www.univ-perp.fr/fuseurop/index_e.htm.

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Diamant A
Diamant A - COSPAR 1965-096

Diamant 2

Diamant B

Diamant B
Diamant B - COSPAR 1970-109

Diamant BP.4
Diamant BP.4 - COSPAR 1975-039