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100 inch solid
Solid propellant rocket stage. Three-segment solid motor proposed for the Solid Titan II in the SLV-4 competition in 1961. Aerojet test fired motors with up to five segments, producing an average thrust of 268,000 kgf for 120 seconds.

Status: Study 1961. Thrust: 3,330.00 kN (748,610 lbf). Gross mass: 115,350 kg (254,300 lb). Unfuelled mass: 12,000 kg (26,000 lb). Specific impulse: 260 s. Specific impulse sea level: 235 s. Burn time: 80 s. Height: 15.60 m (51.10 ft). Diameter: 2.54 m (8.33 ft). Span: 2.54 m (8.33 ft).

The 100 inch diameter was dictated by the diameter of Aerojet's existing heat treating furnace. The segmented motor approach was dictated by the Air Force, since they required the motors to be moved by rail to Vandenberg, and a full-length motor could not be handled by the rail system. Aerojet fired four test motors, with the graphite nozzles disintegrating at 45 and 55 seconds into the burn in the last tests.



Country: USA. Launch Vehicles: Soltan. Propellants: Solid.

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