The RS-27A is a liquid-fuel rocket engine developed in 1980s by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles. It provides 1.05 meganewtons (240,000 lbf) of thrust burning RP-1 and LOX in a gas-generator cycle .

The RS - 27A powerplant comprises an RS2701B main engine, and twin LR101 - NA - 11 verniers. Introduced in 1990 on the McDonnell Douglas' Delta 7000 series launcher it replaced the RS-27 as the main system for that launcher. It continues in service as part of the Atlas MA- 5A powerplant. Flown: 14 Delta plus 8 Atlas to the end of 1993.

2006年11月18日 · A Pratt & Whitney Rocketdyne (PWR) RS-27A rocket engine today powered the latest version of the Air Force’s Global Positioning System satellite into space aboard a Delta II rocket.

RS-27是Rocketdyne于1974年开发的液体螺旋桨火箭发动机，以取代三角洲的老化MB-3 。 RS-27结合了古老的MB-3和H-1设计的组件，是使用了二十年的基本设计的现代化版本。

RS-27A火箭發動機 Castor 2固體輔助火箭 2具輔助推進火箭，若是三角洲4號中型運載火箭則為液體輔助火箭 Delta K, 配備 AJ-10火箭發動機，Anik A1發射使用AJ-10-118F火箭發動機，為其中的例外 [10] FW-4D 3 超長雷神燃料槽 RS-27火箭發動機 Castor 4固體輔助火箭 3具輔助火箭

2025年2月17日 · The stage is powered by one liquid-fueled Rocketdyne RS-27A rocket engine, rated at 236,992 pounds of thrust (1,054.193 kilonewtons). Fueled with 10,000 gallons (37,854 liters) of RP-1/LOX propellant and oxidizer, the engine has 4 minutes, 25 second burn time.

2007年2月17日 · Pratt & Whitney Rocketdyne’s RS-27A rocket engine powered five NASA scientific satellites into orbit today. The purpose of the mission is to unlock the mysteries of Earth’s geomagnetic...

The RS - 27 powerplant comprises an RS2701A/B main engine, and twin LR101 - NA - 11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher it replaced the MB - 3 as the main system for that launcher.

Engine statistics; Specification Main Vernier (x2) Applications: Delta II: Roll control: Propellants: LOX/RP-1: Thrust in Vaccum: 237,000 lb: Thrust at Sea Level

The RS-27A is a liquid-fuel rocket engine developed in 1980s by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles. It provides 1.05 meganewtons (240,000 lbf) of thrust burning RP-1 and LOX in a gas-generator cycle .