RS-27A (rocket engine)


RS-27A (rocket engine)

The RS-27A is a medium-sized rocket engine developed by Rocketdyne for use on the Delta II and Delta III rockets. It is fueled by a kerosene / LOX mixture in a gas-generator cycle. The engine is a modified version of its predecessor, the RS-27; its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude.

pecifications

* Thrust (vac): 237,000 lbf (1.05 MN)
* Isp (vac): 302 s
* Isp (sea level): 255 s
* Mass: 2,528 lb (1,147 kg)
* Diameter: 67 in (1.70 m)
* Length: 12 ft 5 in (3.78 m)
* Chambers: 2
* Chamber pressure: 700 psia (4.8 MPa)
* Area ratio: 12:1
* Oxidizer to fuel ratio: 2.245:1
* Thrust to Weight ratio: 93

External links

* [http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=7f1f2b1f547ee010VgnVCM100000c45a529fRCRD Pratt and Whitney page on the RS-27A]
* [http://www.astronautix.com/engines/rs27a.htm Astronautix.com page on RS-27A]


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