|
Delta 3 - 1
|
|
Gross Mass: 104,377 kg (230,111 lb). Empty Mass: 6,822 kg (15,039 lb). Thrust (vac): 1,085.790 kN (244,095 lbf). Isp: 302 sec. Burn time: 320 sec. Propellants: Lox/Kerosene. Isp(sl): 254 sec. Diameter: 2.44 m (8.00 ft). Span: 4.00 m (13.10 ft). Length: 20.00 m (65.00 ft). Country: USA. No Engines: 1. Engine: RS-27A. Status: Out of production. First Flight: 1998. Last Flight: 2000. No Launched: 3. 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.
Used on Launch Vehicles:
|
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2007 except where otherwise noted.
|
|
|
|