This page no longer updated from 31 October 2001. Latest version can be found at Delta 3 - 1

Gross Mass: 104,377 kg. Empty Mass: 6,822 kg. Thrust (vac): 110,720 kgf. Isp: 302 sec. Burn time: 320 sec. Propellants: Lox/Kerosene Isp(sl): 254 sec. Diameter: 2.4 m. Span: 4.0 m. Length: 20.0 m. Country: USA. No Engines: 1. RS-27A Status: Dev.

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. 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.

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Last update 12 March 2001.
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© Mark Wade, 2001 .