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Delta 3 - 1
Part of Thor DM-19 Family
LOx/Kerosene propellant rocket stage. The first stage of the Delta III is powered by a Rocketdyne RS-27A main engine which has a 12:1 expansion ratio and employs a turbine/turbopump, a regeneratively cooled thrust chamber and nozzle, and a hydraulically gimbaled thrust chamber and nozzle that provides pitch and yaw control.

Status: Retired 2000. Thrust: 1,085.79 kN (244,095 lbf). Gross mass: 104,377 kg (230,111 lb). Unfuelled mass: 6,822 kg (15,039 lb). Specific impulse: 302 s. Specific impulse sea level: 254 s. Burn time: 320 s. Height: 20.00 m (65.00 ft). Diameter: 2.44 m (8.00 ft). Span: 4.00 m (13.10 ft).

Two Rocketdyne vernier engines provide roll control during main-engine burn, and attitude control between main-engine cutoff (MECO) and second-stage separation. High repeatability of mixture ratio ensures very accurate propellant utilization for the engines. The Rocketdyne RS-27A main and vernier engines are both unchanged from Delta II.



Country: USA. Engines: RS-27A. Launch Vehicles: Delta 8930. Propellants: Lox/Kerosene.

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