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VLM

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AKA: Veiculo Lancador de Microsatelites. Status: Development ended 1997. Payload: 100 kg (220 lb). Thrust: 262.20 kN (58,945 lbf). Gross mass: 15,900 kg (35,000 lb). Height: 20.00 m (65.00 ft). Diameter: 1.00 m (3.20 ft). Apogee: 200 km (120 mi).

LEO Payload: 100 kg (220 lb) to a 200 km orbit at 5.00 degrees. Payload: 18 kg (39 lb) to a 800 km SSO in 1999 dollars. Flyaway Unit Cost 1985$: 4.000 million.

Stage Data - VLM

• Stage 1. 1 x VLS-1. Gross Mass: 8,720 kg (19,220 lb). Empty Mass: 1,536 kg (3,386 lb). Thrust (vac): 320.600 kN (72,074 lbf). Isp: 277 sec. Burn time: 58 sec. Isp(sl): 170 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 8.10 m (26.50 ft). Propellants: Solid. No Engines: 1. Engine: S-43TM. Other designations: Veiculo Lancador de Satelites. Status: In production.

• Stage 2. 1 x VLS-2. Gross Mass: 5,664 kg (12,486 lb). Empty Mass: 1,212 kg (2,672 lb). Thrust (vac): 208.390 kN (46,848 lbf). Isp: 275 sec. Burn time: 56 sec. Isp(sl): 204 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 5.80 m (19.00 ft). Propellants: Solid. No Engines: 1. Engine: S-40TM. Other designations: Veiculo Lancador de Satelites. Status: In production.

• Stage 3. 1 x VLS-3. Gross Mass: 1,025 kg (2,259 lb). Empty Mass: 190 kg (410 lb). Thrust (vac): 33.240 kN (7,473 lbf). Isp: 282 sec. Burn time: 68 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 1.80 m (5.90 ft). Propellants: Solid. No Engines: 1. Engine: S-44. Other designations: Veiculo Lancador de Satelites. Status: In production.

• Stage 4. 1 x VLM-4. Gross Mass: 377 kg (831 lb). Empty Mass: 57 kg (125 lb). Thrust (vac): 20.490 kN (4,606 lbf). Isp: 275 sec. Burn time: 43 sec. Diameter: 0.66 m (2.16 ft). Span: 0.66 m (2.16 ft). Length: 1.25 m (4.10 ft). Propellants: Solid. No Engines: 1. Engine: S-30. Other designations: Veiculo Lancador de Satelites. Status: In production.