 | Scout 2
Credit - ESA
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All-solid orbital launch vehicle. Year: 1993. Family: Scout. Country: USA. Status: Study 1993. Alternate Designation: Scout 2. Proposed upgrade of Scout proposed by the University of Rome with two strap-ons from the Ariane 4. Launch would have been from Italy's San Marco platform off Kenya. Further work cancelled in 1993. Manufacturer: Vought. LEO Payload: 521 kg (1,148 lb). to: 200 km Orbit. at: 1.00 degrees. Liftoff Thrust: 1,259.300 kN (283,102 lbf). Total Mass: 39,530 kg (87,140 lb). Core Diameter: 1.14 m (3.74 ft). Total Length: 23.00 m (75.00 ft). Flyaway Unit Cost $: 8.000 million. in: 1985 unit dollars.
Stage Data - Advanced Scout - Stage Number: 0. 2 x Stage: Ariane 3-0. Gross Mass: 9,663 kg (21,303 lb). Empty Mass: 2,313 kg (5,099 lb). Thrust (vac): 689.990 kN (155,116 lbf). Isp: 263 sec. Burn time: 29 sec. Isp(sl): 240 sec. Diameter: 1.07 m (3.51 ft). Span: 1.07 m (3.51 ft). Length: 8.32 m (27.29 ft). Propellants: Solid. No Engines: 1. Engine: SPB 7.35. Other designations: SPB 7.35.
- Stage Number: 1. 1 x Stage: Algol 3. Gross Mass: 14,320 kg (31,570 lb). Empty Mass: 1,600 kg (3,500 lb). Thrust (vac): 471.905 kN (106,088 lbf). Isp: 284 sec. Burn time: 75 sec. Isp(sl): 238 sec. Diameter: 1.14 m (3.74 ft). Span: 1.14 m (3.74 ft). Length: 9.40 m (30.80 ft). Propellants: Solid. No Engines: 1. Engine: Algol 3.
- Stage Number: 2. 1 x Stage: Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Isp(sl): 232 sec. Diameter: 0.79 m (2.59 ft). Span: 0.79 m (2.59 ft). Length: 6.04 m (19.81 ft). Propellants: Solid. No Engines: 1. Engine: TX-354-3.
- Stage Number: 3. 1 x Stage: Mage 2. Gross Mass: 530 kg (1,160 lb). Empty Mass: 40 kg (88 lb). Thrust (vac): 45.483 kN (10,225 lbf). Isp: 293 sec. Burn time: 44 sec. Isp(sl): 0 sec. Diameter: 0.77 m (2.52 ft). Span: 0.77 m (2.52 ft). Length: 1.52 m (4.98 ft). Propellants: Solid. No Engines: 1. Engine: Mage 2.
- Stage Number: 4. 1 x Stage: Altair 3. Gross Mass: 301 kg (663 lb). Empty Mass: 25 kg (55 lb). Thrust (vac): 27.400 kN (6,160 lbf). Isp: 280 sec. Burn time: 27 sec. Isp(sl): 255 sec. Diameter: 0.64 m (2.09 ft). Span: 0.64 m (2.09 ft). Length: 2.53 m (8.30 ft). Propellants: Solid. No Engines: 1. Engine: FW-4S, TEM640.
Bibliography and Further Reading - Covault, Craig, Aviation Week and Space Technology, "US to Bolster Its Capability In Small Launch Vehicles", 1987-12-07, page 73.
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