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.

3 stage vehicle consisting of 1 x Emeraude + 1 x Topaze + 1 x P064.

LEO Payload: 160 kg (350 lb) to a 200 km orbit. Flyaway Unit Cost 1985$: 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.